t.o. 1b-52h-1-13 - electronic warfare officers manual - b-52h (01!06!2006)

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T.O. 1B-52H-1-13

31 AUGUST 1996

CHANGE 14 – 1 JUNE 2006

Electronic Warfare Officer’s Manual

USAF SERIES B-52H AIRCRAFT

THE BOEING COMPANY

F33657-79-C-0416F34601-03-D-0066

This manual contains unverified procedures. Refer to the validation/verification statuspage(s) prior to performing any operation or maintenance procedure.

THIS PUBLICATION IS INCOMPLETE WITHOUT T.O. 1B-52H-1 AND T.O. 1B-52H-1-13-1 AND IS USED WITH T.O. 1B-52H-1-12SUPPLEMENTARY PUBLICATIONS ARE PROVIDED TO SUPPLY OPERATIONAL COVERAGE IN NONSTANDARD CONFIGURATIONSSEE T.O. 0-1-CD-1 FOR NUMERICAL INDEX OF BOMBER TECHNICAL PUBLICATIONS.

SEE T.O. 0-1-CD-1 FOR CURRENT STATUS OF FLIGHT MANUALS, SAFETY SUPPLEMENTS, OPERATIONAL SUPPLEMENTS, ANDFLIGHT CREW CHECKLISTS.

COMMANDERS ARE RESPONSIBLE FOR BRINGING THIS PUBLICATION TO THE ATTENTION OF ALL AIR FORCE PERSONNELCLEARED FOR OPERATION OF SUBJECT AIRCRAFT.

DISTRIBUTION STATEMENT E – Distribution authorized to the Department of Defense Components only, due to Direct Military Support, 29October 1996. Other requests shall be referred to 327 BMSG/EN, Tinker AFB, OK 73145-3021.

WARNING –This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, et seq.or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App. 2401 et seq. Violations of these export laws are subject to severecriminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

HANDLING AND DESTRUCTION NOTICE – Comply with distribution statement and destroy by any method that will prevent disclosure ocontents or reconstruction of the document. Demil code D.

PUBLISHED UNDER AUTHORITY OF THE SECRETARY OF THE AIR FORCE



INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.

*The asterisk indicates pages changed, added, or deleted by the current change.

Dates of issue for original and changed pages are:

NOTE: The portion of the text affected by the changes is indicated by avertical line in the outer margins of the page. Changes to illustrationsare indicated by miniature pointing hands. Changes to wiringdiagrams are indicated by shaded areas.

LIST OF EFFECTIVE PAGES

Upon receipt of the second and subsequent changes to this technical order, personnel responsible for maintaining this publication in currentstatus will ascertain that all previous changes have been received and incorporated. Action should be taken promptly if the publication isincomplete.

T.O. 1B-52H-1-13

A Change 14 USAF

ADDITIONAL COPIES OF THIS PUBLICATION MAY BE OBTAINED BY USAF ACTIVITIES IN ACCORDANCE WITH T.O. 00-5-1.

Technical orders are normally distributed promptly after printing. Date(s) shown on the title page (lower right corner) are for identification only. Theseare not distribution dates. Processing time sometimes causes distribution to only appear to have been delayed.

Original 0 31 Aug 96

Change 1 30 Dec 98

Change 2 1 May 99

Change 3 30 Jun 99

Change 4 1 Mar 00

Change 5 30 Dec 00

Change 6 30 Jun 01

Change 7 1 Oct 01

Change 8 1 Mar 02

Change 9 1 Sep 02

Change 10 1 Apr 03

Change 11 1 Apr 04

Change 12 1 Dec 04

Change 13 1 Jul 05

Change 14 1 Jun 06

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 272 CONSISTING OF THE FOLLOWING:

Page Change Page Change Page Change Page Change No. No. No. No. No. No. No. No.

* Title 14. . . . . . . . . . . . . . . . . . . .

* A 14. . . . . . . . . . . . . . . . . . . . .Flyleaf-1 9. . . . . . . . . . . . . . . . .

Flyleaf-2 Blank 0. . . . . . . . . . .

V/VS-1 Added 13. . . . . . . . . . .

V/VS-2 Blank Added 13. . . . .

i – ii 10. . . . . . . . . . . . . . . . . . . .

iii 0. . . . . . . . . . . . . . . . . . . . . . .

iv 13. . . . . . . . . . . . . . . . . . . . . .

v 4. . . . . . . . . . . . . . . . . . . . . . .

vi 0. . . . . . . . . . . . . . . . . . . . . . .

vii 13. . . . . . . . . . . . . . . . . . . . .

viii 0. . . . . . . . . . . . . . . . . . . . . .

1-1 7. . . . . . . . . . . . . . . . . . . . .

1-2 Blank 0. . . . . . . . . . . . . . . .

* 1-3 14. . . . . . . . . . . . . . . . . . . .

1-4 11. . . . . . . . . . . . . . . . . . . .

1-5 0. . . . . . . . . . . . . . . . . . . . .

1-6 9. . . . . . . . . . . . . . . . . . . . .1-6A – 1-6B Added 9. . . . . . .

1-7 9. . . . . . . . . . . . . . . . . . . . .

1-8 – 1-9 10. . . . . . . . . . . . . . .

1-10 – 1-11 0. . . . . . . . . . . . . .

1-12 Blank 0. . . . . . . . . . . . . . .

1-13 7. . . . . . . . . . . . . . . . . . . .

1-14 – 1-16 2. . . . . . . . . . . . . .

1-16A Added 2. . . . . . . . . . . .

1-16B Blank Added 2. . . . . . .

1-17 0. . . . . . . . . . . . . . . . . . . .

1-18 2. . . . . . . . . . . . . . . . . . . .

1-19 – 1-21 0. . . . . . . . . . . . . .

1-22 7. . . . . . . . . . . . . . . . . . . .

1-23 – 1-26 2. . . . . . . . . . . . . .

1-26A – 1-26D Added 2. . . . .

1-26E – 1-26H 5. . . . . . . . . . .

1-27 – 1-32 7. . . . . . . . . . . . . .

1-33 9. . . . . . . . . . . . . . . . . . . .1-34 – 1-42 7. . . . . . . . . . . . . .

1-42A – 1-42H Added 7. . . . .

1-42J – 1-42L Added 7. . . . .

1-42M Blank Added 7. . . . . .

1-43 – 1-44 7. . . . . . . . . . . . . .

1-45 – 1-46 0. . . . . . . . . . . . . .

1-47 7. . . . . . . . . . . . . . . . . . . .

1-48 1. . . . . . . . . . . . . . . . . . . .

1-49 – 1-51 7. . . . . . . . . . . . . .

1-52 0. . . . . . . . . . . . . . . . . . . .

1-53 7. . . . . . . . . . . . . . . . . . . .

1-54 Blank 0. . . . . . . . . . . . . . .

1-55 – 1-56 7. . . . . . . . . . . . . .

1-57 0. . . . . . . . . . . . . . . . . . . .

1-58 9. . . . . . . . . . . . . . . . . . . .

1-59 – 1-61 0. . . . . . . . . . . . . .

1-62 Blank 0. . . . . . . . . . . . . . .1-63 – 1-66 9. . . . . . . . . . . . . .

1-66A Added 9. . . . . . . . . . . . .

1-66B Blank Added 9. . . . . . .

1-67 – 1-72 9. . . . . . . . . . . . . .

1-72A – 1-72H Added 9. . . . .

1-72J – 1-72N Added 9. . . . .

1-72P – 1-72V Added 9. . . . .

1-73 – 1-74 9. . . . . . . . . . . . . .

1-74A – 1-74D Added 9. . . . .

1-75 – 1-76 0. . . . . . . . . . . . . .

1-77 9. . . . . . . . . . . . . . . . . . . .

1-78 – 1-91 0. . . . . . . . . . . . . .

1-92 1. . . . . . . . . . . . . . . . . . . .

1-93 – 1-101 0. . . . . . . . . . . . .

1-102 Blank 0. . . . . . . . . . . . . .

1-103 – 1-105 0. . . . . . . . . . . .

1-106 – 1-107 9. . . . . . . . . . . .

1-108 – 1-111 0. . . . . . . . . . . .1-112 Blank 0. . . . . . . . . . . . . .

1-113 1. . . . . . . . . . . . . . . . . . .

1-114 0. . . . . . . . . . . . . . . . . . .

1-115 – 1-116 9. . . . . . . . . . . .

1-117 10. . . . . . . . . . . . . . . . . .

1-118 – 1-119 0. . . . . . . . . . . .

1-120 1. . . . . . . . . . . . . . . . . . .

2-1 9. . . . . . . . . . . . . . . . . . . . .

2-2 – 2-3 0. . . . . . . . . . . . . . . .

2-4 10. . . . . . . . . . . . . . . . . . . .

2-5 – 2-6 12. . . . . . . . . . . . . . .

2-7 8. . . . . . . . . . . . . . . . . . . . .

2-8 0. . . . . . . . . . . . . . . . . . . . .

* 2-9 14. . . . . . . . . . . . . . . . . . . .

2-10 12. . . . . . . . . . . . . . . . . . .

2-11 0. . . . . . . . . . . . . . . . . . . .

2-12 4. . . . . . . . . . . . . . . . . . . .2-13 – 2-14 9. . . . . . . . . . . . . .

2-15 5. . . . . . . . . . . . . . . . . . . .

2-16 0. . . . . . . . . . . . . . . . . . . .

2-17 – 2-18 9. . . . . . . . . . . . . .

2-19 – 2-20 Deleted 9. . . . . . .

2-21 10. . . . . . . . . . . . . . . . . . .

2-22 9. . . . . . . . . . . . . . . . . . . .

2-23 12. . . . . . . . . . . . . . . . . . .

2-24 0. . . . . . . . . . . . . . . . . . . .

2-25 – 2-26 5. . . . . . . . . . . . . .

2-26A 7. . . . . . . . . . . . . . . . . . .

2-26B Blank Added 5. . . . . . .

2-27 – 2-30 12. . . . . . . . . . . . .

2-31 – 2-32 10. . . . . . . . . . . . .

2-33 5. . . . . . . . . . . . . . . . . . . .

2-34 0. . . . . . . . . . . . . . . . . . . .

2-35 – 2-36 12. . . . . . . . . . . . .

2-37 7. . . . . . . . . . . . . . . . . . . .2-38 – 2-39 0. . . . . . . . . . . . . .

2-40 9. . . . . . . . . . . . . . . . . . . .

2-41 12. . . . . . . . . . . . . . . . . . .

2-42 – 2-43 9. . . . . . . . . . . . . .

2-44 1. . . . . . . . . . . . . . . . . . . .

2-45 – 2-46 9. . . . . . . . . . . . . .

2-47 1. . . . . . . . . . . . . . . . . . . .

2-48 0. . . . . . . . . . . . . . . . . . . .

3-1 9. . . . . . . . . . . . . . . . . . . . .

3-2 Blank 0. . . . . . . . . . . . . . . .

3-3 10. . . . . . . . . . . . . . . . . . . .

3-4 5. . . . . . . . . . . . . . . . . . . . .

3-5 7. . . . . . . . . . . . . . . . . . . . .

3-6 Blank 0. . . . . . . . . . . . . . . .

3-7 – 3-10 7. . . . . . . . . . . . . . .

3-11 0. . . . . . . . . . . . . . . . . . . .

3-12 7. . . . . . . . . . . . . . . . . . . .3-13 0. . . . . . . . . . . . . . . . . . . .

3-14 Blank 0. . . . . . . . . . . . . . .

3-15 0. . . . . . . . . . . . . . . . . . . .

3-16 Blank 0. . . . . . . . . . . . . . .

3-17 – 3-20 9. . . . . . . . . . . . . .

3-20A 13. . . . . . . . . . . . . . . . .

3-20B – 3-20F Added 9. . . . .

3-21 – 3-25 0. . . . . . . . . . . . . .

3-26 Blank 0. . . . . . . . . . . . . . .

3-27 7. . . . . . . . . . . . . . . . . . . .

3-28 9. . . . . . . . . . . . . . . . . . . .

Glossary-1 Added 10. . . . . . .

Glossary-2Blank Added 10. .

Index-1 9. . . . . . . . . . . . . . . . . .

Index-2 12. . . . . . . . . . . . . . . . .

Index-3 – Index-4 9. . . . . . . . .

CURRENT FLIGHT CREW CHECKLIST

Electronic Warfare Officer’s Abbreviated Checklist T.O. 1B-52H-1-13CL-1 31 Aug 96 Change 11 - 1 Jun 06



T.O. 1B-52H-1-13

Change 9 Flyleaf-1/(Flyleaf-2 blank)

STATUS OF SAFETY AND OPERATIONAL SUPPLEMENTS

This supplement st a tus pa ge is based on informat ion ava ilable to the manu al editor as of the dat e of

this publica tion. The informa tion may not be current a s it must be updated by a ny subsequent supple-

ment st a tu s pa ges a nd b y referen ce to T.O. 0-1-1-2.

SUPPLEMENTS IN THIS CHANGE

Number Date Short Title Section Affected

S -4 30 D ec 00 Inst a lla t ion Of D U AL MOD E M Rescinded

AFSATCOM

OUTSTANDING SUPPLEMENTS

Number Date Short Title Section Affected



BL



T.O. NO. PTO CHANGE NO. – DATE

TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE

(A)

DATA ELEMENT

V A L I D A T I O N

DATE

VERIFIED

LEGEND:

(A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE

(B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP)

DATE

VALIDATED M E T H O D

(B)

V E R I F I C A T I O N

M E T H O D

(B)

REMARKS

BASIC DATE CHANGE NO. – DATE

This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accor-dance with TOs 00-5-1 and 00-5-3. Performance of unverified procedures may result in injury to personnel or damage toequipment.

WARNING

V/VS-1/(V/VS-2 blank)

T.O 1B-52H-1-13 31 AUG 1996 13 – 1 JUL 2005 AMI

TCTO Listings(P, PG vii) 7/15/02 AALQ-172 Fault Status(P: PG 3-20A) 7/10/02 A



BL



T.O. 1B-52H-1-13

Change 10 i

Table of Contents

PAGE

SECTION I Systems Description and Operation 1-1*

SECTION II Normal Procedures 2-1

SECTION III Defensive Systems Abnormal Operationsand Malfunction Analysis 3-1

SECTION IV Crew Duties **

SECTION V Operating Limitations **

SECTION VI Flight Characteristics **

SECTION VII All Weather Operation **

Glossary Glossary 1

Alphabetical Index Index 1

* Classified Defensive Systems Information is contained in T.O. 1B-52H-1-13-1

** Refer to T.O. 1B-52H-1.

LIST OF ILLUSTRATIONS - Titles included in alphabetical index



T.O. 1B-52H-1-13

ii Change 10

Before operating the B-52 aircraftread the following pages carefully!

SCOPE. This manual provides the electronic warfare officer with a general knowl-edge of the defensive systems on the B-52H aircraft, their characteristics, and specif-ic norma l procedures, syst ems a bnormal opera ting procedures and systems m alfunc-tion a na lysis. This m a nua l, w hen u sed w ith T.O. 1B -52H -1-13-1, provides d eta iledoperating procedures and technical description of the defensive systems. Instruc-tions in this manual are for a crew inexperienced in the operation of this aircraft .This manual provides the best possible operating instructions under most circum-sta nces, but it is a poor substit ute for sound judgment.

COMPLEMENTARY MANUALS. This manual must be used with one or more of the fol-lowing manuals to obtain all the information necessary for safe and efficientoperation of the B-52H aircraft . These manua ls ha ve been separ at ed from t his ma n-ual for your convenience in handling information which may be classified, applicableonly to certain aircraft configurations, or used only by certain crewmembers.

T.O. 1B -52H -1 B -52H Fligh t Ma nua lT.O. 1B-52H-1-12 B -52H Rad ar Naviga tor’s/Naviga tor’s Man ualT.O. 1B -52H -1-13-1 B -52H E lectronic Wa rfa re Officer’s M a nua l C las sified

Su pplement (SE CR ET) (Title Uncla ssified)

PERMISSIBLE OPERATIONS. The Flight Manual takes a ‘‘positive approach’’ andnormally states only what you can do. Unusual operations or configurations areprohibited unless specifically covered herein. Clearance from the using commandmust be obtained before any questionable operation, which is not specifically per-mitted in this manual, is at tempted. Before granting the clearance, the using com-ma nd ma y request coordina tion or engineering ass ista nce/a pprova l from Oklah omaCity ALC. Request should be made through the Flight Ma nua l Mana ger.

HOW TO BE ASSURED OF HAVING LATEST DATA. Ref er t o T.O. 0-1-1-2 for a list ing of

all current flight manuals, safety, or operational supplements, and checklists. Also,check the flight manual cover page, the t it le block of each safety and operationalsupplement and all status pages attached to formal safety and operational supple-ments. Clear up all discrepancies before flight.



T.O. 1B-52H-1-13

iii

ARRANGEMENT. The ma nua l is divided into seven fairly ind ependent sections to sim-plify reading it str aight through or using it a s a reference manua l.

SAFETY SUPPLEMENTS. Information involving safety will be promptly forwarded toyou in a safety supplement. Urgent information is published in interim safety sup-plements a nd t ra nsmitt ed by t eletype. Formal supplements ar e ma iled. The supple-ment title block and status page (published with formal supplement only) should bechecked to determine the supplement’s effect on the manual and other outstanding

supplements.

OPERATIONAL SUPPLEMENTS. Information involving changes to operating proce-dures will be forwarded to you by operational supplements. The procedure for han-dling opera tional supplements is the sa me a s for safety supplements.

CHECKLISTS. The flight ma nua l conta ins itemized procedures w ith n ecessary am pli-fications. The checklist contains itemized procedures without the amplification. Pri-ma ry line items in the flight ma nua l and checklist ar e identical. If a forma l safety oroperational supplement affects your checklist, the affected checklist page will be at-tached to the supplement. Cut it out and insert it over the affected page but neverdiscard the checklist page in case the supplement is rescinded and the page is need-ed .

FLIGHT MANUAL BINDERS. Looseleaf binders and sectionalized ta bs a re ava ilable foruse with your man ual. They ar e obta ined through local purchase procedures a nd a relisted in the Federal Supply Schedule (FSC Group 75, Office Supplies, Part 1).Check with your supply personnel for assistance in procuring these items.

WARNINGS, CAUTIONS, AND NOTES. The following definitions apply to ‘‘Warnings,’’‘‘Ca utions,’’ and ‘‘Notes’’ found thr oughout th e ma nua l.

Operating procedures, techniques, etc, which could result in personalinjury or loss of life if not ca refully followed.

Operating procedures, techniques, etc, which could result in damage toequipment if n ot carefully followed.

NOTE

An operat ing procedure, technique, etc, which is considered essentia l toemphasize.

SHALL, WILL, SHOULD, and MAY. The following d efinitions a pply to the w ords:

SHALL or WILL The ins t ruct ions or procedures prefaced by ‘‘sha l l’’ or ‘‘w i l l’’are mandatory.

S H OU LD Norma lly used to indica te a preferred but nonma nda tory method of a ccomplishment.

MAY An a ccept a ble or suggest ed mea ns of a ccomplishment .



T.O. 1B-52H-1-13

iv Change 13

CHANGE SYMBOLS. Changes to existing material and addition of new material areindicat ed by one of th ree types of symbols determined by t he na ture of the ma teriala ffected. Text mat erial ut ilizes a vert ical line in the ma rgin a djacent to the affectedarea. New il lustrations (figures) uti l ize a vertical l ine in the outer margin of thepage. Photographs and l ine draw ings use a minia ture pointing ha nd to highlight t heaffected a rea. D iagra ms a nd schematics uti l ize a grey tone (screening) to highlightthe affected area. Change symbols are not used for blank space resulting from dele-tions, indexes, and tabular data where changes cannot be identified, relocation of

material, or correction of minor inaccuracies unless such correction changes themeaning.

YOUR RESPONSIBILITY – TO LET US KNOW. Every effort is made to keep the FlightManua l current. Review conferences w ith operating personnel a nd a consta nt review of accident a nd fl ight test reports a ssure inclusion of the latest da ta in the ma nua l .However, we cannot correct an error unless we know of its existence. In this regard,i t is essential th at you do your pa rt . C omments, corrections, and questions regar dingthis ma nua l , supplementa ry ma nua ls, checklists, or an y phase of the Flight Ma nua lprogram a re welcomed. These should be forw a rded t o your loca l sta nda rdiza tion/eva-luation unit and routed as directed by AFI 11-215 to the Flight Manual Manager,327 B MS G /E N, Tink er AFB , Okla homa 73145-3021.



T.O. 1B-52H-1-13

Change 4 v

Aircraft Coding

The information contained in this manual covers all B-52H aircraft . USAF Serial numbersare used to dist inguish information related to one aircraft or group of aircraft from thatwhich is applicable to the other aircraft . When serial numbers appear by a paragraph orillustration, the information applies only to the aircraft represented by the serial numbers.Where no serial n umbers a ppear on a para graph or illustra tion, the informa tion is applicableto all B -52H a ircraft .

• S ym bol mea ns ‘‘thr u’’ or ‘‘on.’’ E xa mple:

60-001 60-015 – Id ent ifies B -52H AF60-001 t hr u AF60-015

61-016 – Id ent ifies B -52H AF61-016 a nd on

• AIRC RAFT NO LONGE R IN S ERVICE

• CS Aircraft modified by TCTO 1B -52H-756 (Int egra ted Conventiona l S tores

Mana gement S ystem)

• # Aircraft not CS RL capa ble

USAF B-52H Serial No.

60-001 CS

60-002 #

60-003 CS

60-004 CS

60-005 #

60-006

60-007 CS

60-008

60-009 CS

60-010 CS

60-011 CS

60-012 #

60-013 CS

60-014 CS

60-015 CS

60-016 CS

60-017 CS

60-018 CS

60-019 CS

60-020 CS

60-021 #

60-022 CS

60-023 CS

60-024 #

60-025 CS

60-026 CS

60-027

60-028

60-029 CS

60-030

60-031 CS

60-032 CS

60-033 CS

60-034 CS

60-035 CS

60-036

60-037 CS

60-038 CS

60-039

60-040

60-041 CS

60-042

60-043 CS

60-044 CS

60-045 CS

60-046 CS

60-047

60-048 #

60-049 CS

60-050 CS

60-051 CS

60-052 CS

60-053

60-054

60-055

60-056

60-057 CS

60-058 CS

60-059 CS

60-060 CS

60-061 CS

60-062 CS

61-001

61-002 CS

61-003 CS

61-004 CS

61-005 #

61-006 CS

61-007 CS

61-008 CS

61-009 CS

61-010 CS

61-011 CS

61-012 #

61-013 CS

61-014 #

61-015 #

61-016 CS

61-017 CS

61-018 #

61-019 CS

61-020 CS

61-021 CS

61-022 CS

61-023 CS

61-024 CS

61-025 #

61-026

61-027 CS

61-028

61-029 CS

61-030

61-031 CS

61-032 CS

61-033

61-034 #

61-035 #

61-03661-037

61-038 CS

61-039 CS

61-040



T.O. 1B-52H-1-13

vi

Personnel Coding

Where necessa ry t o distinguishcrewmembers, t he followin gcode letters w ill be used

(P ) P ilot(CP ) Copilot(N) Na viga t or(G ) G unner(R N) R ada r Na viga t or(E W) E W Off icer

(IP ) I nst ruct or P ilot(I N) I ns tr uct or N a viga t or(D I) D efen se I nst ruct or(G C) G round C rew (10th) Tenth Crewmember

The amplified checklist describes in detail the steps to be completed. Each majorpart of multi-crewmember checklists has been assigned to a crewmember to be readby that crewmember, and to be accomplished by others in the crew. When necessaryto show which crewmember will accomplish certain steps, the normal crew coding isused and the code letters will appear a fter the response to each step. Where a da sh

(-) is used in crew coding, such as P-CP, P-CP-RN, or any combination of crewmem-bers, each crew member w ill a ccomplish th e step. Where a sla sh (/) is used, s uch a sP /CP, eith er crewm ember w ill accomplish t he st ep. A verba l response will be givenby the crewmember(s) performing the action. There are exceptions to the verbal re-sponse as some of the checklists a re to be accomplished silently. When a single crew-member is responsible for a checklist and accomplishment of all items, no crew cod-ing will appear. All duties and responsibilities of the aerial gunner are deleted. Anycrew member occupying the gunner’s ejection seat will continue to be referred to as“Gunner” .



T.O. 1B-52H-1-13

Change 13 vii

Retrofit Coding

The following code symbols along with the word ‘‘L ess ’’ are used to distinguish informationrelated to aircraft that have the described retrofi t change incorporated from that which is

applicable to aircraft not yet retrofitted. This list contains only TCTO’s currently active.Those known to be completed are not included.

CODING EXAMPLE: DR T.O. 1B -52H-792, Ins t a lla ti on of IU /TACAN Repla cement onB -52H aircraft . Informat ion a pplicable to a ircra ft unt i l they a re modified in a ccordance with

T.O. 1B -52H-792 wil l be coded L ess DR . Information applicable to aircraft modified in accor-

da nce w ith T.O. 1B -52H -792 w ill be coded DR .

SYMBOL T.O. NO. TITLE

CS

1B-52H-753

1B-52H-756

Installation of Global Positioning System (GPS) on B-52H Aircraft (ECP 0109).

Installation of Integrated Conventional Stores Management System (ICSMS) onB-52H Aircraft (ECP 0109).

CHDJ 1B-52H-749 Installation of AN/ARC-210(V) V/UHF Radio on B-52H Aircraft.

CHDS None Replacement of ALR-20 Indicator (IP-1168) with ALR-20 Indicator (IP-1168B) onB-52H Aircraft.

CHDT 1B-52H-798 Installation of Electronic Countermeasures Improvement on all B-52H Aircraft.

CHDZ 1B-52H-796 Removal of CM-442 Signal Processor, Part Number 327370-6 and Replacementwith CM-479 Signal Processor, Part Number 9284225-2 on all B-52H Aircraft.

[AMI] 1B-52H-830 Replacement of Ballistics Computer Set AN/AYQ-10 and Inertial Navigation SystemAN/ASN-136 on B-52H Aircraft. Baseline for [AMI] includes .DJ



T.O. 1B-52H-1-13

viii

The B-52H Stratofortress



T.O. 1B-52H-1-13

Change 7 1-1/(1-2 blank)

Defensive SystemsOperation and Procedures section I

table of contents page

THE AIRCRAFT 1-3

RECEIVER SYSTEMS 1-13

AN/ALR-20A SEARCH RECEIVER 1-13

RADAR WARNING RECEIVER 1-27

SENSOR INTEGRATION SYSTEM 1-43

BLANKING SYSTEM 1-55

TRANSMITTER SYSTEMS 1-57

AN/ALT-16A 1-57

AN/ALT-28(V) JAMMING TRANSMITTER 1-57

AN/ALT-32A JAMMING TRANSMITTER 1-57

RECEIVER-TRANSMITTER SYSTEMS 1-63

AN/ALQ-172 COUNTERMEASURES SET 1-63

AN/ALQ-122/AN/ALT-16A COUNTERMEASURES SYSTEM 1-75

AN/ALQ-153(V) TAIL WARNING SYSTEM 1-83

AN/ALQ-155(V) POWER MANAGEMENT SYSTEM 1-92

EXPENDABLE COUNTERMEASURES SYSTEMS 1-103

AN/ALE-24 DISPENSER SET 1-103

AN/ALE-20 FLARE EJECTOR SET 1-113



BL



T.O. 1B-52H-1-13

Change 14 1-3

THE AIRCRAFT

DESCRIPTION

The Boeing B-52 ‘‘Stratofortress’’ aircraft is of theland based heavy bombardment class designed forlong range fl ight at high speed and alt i tude. The

tactical mission is the destruction of surface objec-tives by bombs and m issiles. The a ircraft ha s provi-sions for ten crewmembers: a basic crew of five,three instructors a nd t wo a dditional crewmembers.The ba sic crew consists of pilot, copilot, ra da r n a vi-gator, navigator and electronic warfare officer. Theinstr uctor crew includes an in stru ctor pilot, inst ruc-tor na vigator a nd instr uctor electronic wa rfare offi-cer. Fina lly, the gunn er an d tenth man positions a realso ava ilable for a dditiona l seating. A highly va ri-able weapons load may be carried on external py-lons in combination with internal cluster, multiplecarria ge clip-in or CSR L mounted w eapons load s.

NOTE

AG M-86C/D m issiles w ill not be car ried inmixed loads with AGM-86B or AGM-129.

The C S RL can car ry up t o eight AG M-86B /86C/D ,B-61, or B-83 weapons internally. These weaponloa ds cannot be mixed on th e CSRL .

The aircraft can suspend a variety of gravity w eap-ons intern a lly on either clip-in (tw o MHU -20 ra cks,up to eight weapons total) or cluster rack assem-blies (th ree cluster ra ck assemblies, up to 27 weap-ons total). Externally, the B-52 can suspend weap-ons using an AGM-28 pylon under each wing with

standa rd rack ada pter beams a t ta ched to each py-lon and two sets of multiple ejector racks (MER)giving a total external carriage capabil i ty of 24weapons. The heavy stores adapter beam (HSAB)can be attached to a stub pylon and up to nineMAU -12 bomb racks can be a tt a ched to ea ch HS ABfor a total externa l carr iage capabil i ty on the HS ABof up to 18 w ea pons.

SPECIAL FEATURES

The aircraft is characterized by swept wings andempennage, four underslung nacelles housing eightturbofan engines, a quadricycle main landing gear,

and a t ip gear near each outboard engine nacelle.Engine bleed air provides the air supply for air con-ditioning and anti-icing. Cartridge starters are in-stal led to provide for engine starts without assis-ta nce from a n a uxiliary a ir cart or a uxiliary electri-cal power cart. Primary electrical power is 205-voltac and is provided by four engine-driven genera-

tors. Hydraulic pressure is supplied by six enginedriven hydraulic pumps and two electric motordriven hydraulic pumps. Primary pitch and yawcontrol is maintained by hydraulically actuatedrudder an d elevat ors. Lat eral control is mainta ined

by operation of hydraulically actuated spoilers. Byvarying the method of control, these same spoilersserve as airbrakes. The entire horizontal stabilizeris moved by a hydr a ulic mechan ism to provide pitchtrim. A steering and crosswind crab system provides steering of the forwar d ma in landing gea r a ndalso properly positions both forwa rd a nd rea r ma inlanding gea r for crosswind landings. A hydraulically driven revolver-type launcher installation in thaft bomb bay provides umbilical and ejector rackconnections for the weapons which may belaunched/released a utomat ically or ma nua lly by thena vigat ors. The w eapon/missile equipment interfa ces wit h t he AN/AS Q-176 offensive a vionics sys

tem, AN/AP N-224 rad a r a ltimeter, a nd the a ircraftelectrical, bleed air, and body hydraulic systemsWeapon selective jettison capability is available tothe navigator and radar navigator . Ei ther theWeapons Control Panel (WCP) or backup MFD display and the keyboard may be used for computercontrolled safe jettison of individual or multipleweapons. The pilot is provided with an ejector unlock consent switch and a prearm consent switch(cooperative with the WCP on the navigators’ fronpanel), a launcher hydraulic system selector switchand a bomb bay and missile jett ison control whichwill jettison a ll wea pons from th e aircra ft. The pilois also provided with pylon jettison switches and

pylon jettison consent switches. The Radar Navigator is provided with a bomb bay and missile jettisonswitch, which will jettison only conventional gravityweapons. This switch is inoperative for all CSRLgravity weapons and al l nuclear and conventionamissiles.

For additional information with missiles instal ledrefer t o T.O. 1B -52H-30-1 for AG M-129 mis silesT.O. 1B -52H-30-4 for AG M-86B mis siles ; a nd T.O1B -52H-34-2-9 for AG M-86C/D mi ss iles .

An electr o-optical viewing syst em (EVS) is inst a lledto provide pilots and navigators with a visual pre

sentation of the area ahead of the aircraft duringboth da y a nd night missions.

A GPS Navigation System which provides positionupdates a nd emulat ed TACAN da ta to the crew an da moving ma p display t o the pilots has been a dded



T.O. 1B-52H-1-13

1-4 Change 11

An Air Force Satellite Communications System(AFSATCOM) terminal is installed and is a half-du-plex UHF terminal providing communications inboth line-of-sight (LOS ) and s a tellite modes. A dualmodem capability DL has been added to theAFSATCO M. The Airborn e Min ia tu re R eceive Ter-mina l (MR T) AN/ARR-85(V) is in st a lled t o providereliable VLF/LF reception a nd printout of secure

and nonsecure messages at extended ranges in nu-clea r a nd/or jamm ing environment s.

DIMENSIONS

Wing S pa n 185 feetFusela ge Lengt h 159 feet 4 inchesHeight

To t op of fin 40 feet 8 inchesFin folded 21 feet 6 inches

Trea dCenterline outboard

ma in t ires 11 feet 4 inchesCenterline t ip gear

t o t ip gea r 148 feet 5 inches

For aircraft turning radius and minimum groundclear a nce, refer t o Section I I of T.O. 1B -52H-1.

DEFENSIVE SYSTEMS

The followin g B -52H defensive syst ems a re coveredin this manual :

• RECE IVER SYSTEMS

AN/ALR-20A Sea rch Receiver

Ra da r Wa rning Receiver (RWR)

Sensor Integration System

• BLANKING SYSTEM

• TRANSMITTER SYSTEMS

AN/ALT-16A

AN/ALT-28(V) J a mm ing Tra ns mi tt er

AN/ALT-32A J a mm ing Tra ns mi tt er

• RECEIVER TRANSMITTER SYSTEMS

AN/ALQ-172 Coun ter mea sur es Set

AN/ALQ-122/AN/ALT-16A C oun ter mea su res System

AN/ALQ-153(V) Ta il Wa rn in g S ys tem

AN/ALQ-155(V) P ower Ma na gemen t Sy st em

• EXPENDABLE COUNTERMEASURESSYSTEMS

AN/ALE -24 Dis pens er S et

AN/ALE -20 Fla re E jector S et

The following B -52H aircraft systems which ma y bea pplica ble to the E W Officer a re cont a ined in T.O.1B -52H-1.

• DOORS AND WINDOWS

• OXYGEN SYSTEM

• EMERGENCY EQUIPMENT• ESCAPE SYSTEMS

• ELECTRICAL POWER SYSTEMS

• LIGHTING EQUIPMENT

• PNEUMATIC SYSTEMS (Air Conditioning and Pressurization)

• INSTRUMENTS

• NAVIG ATION RADI OS

• COMMUNICATION AND ASSOCIATEDELECTRONIC EQUIP MENT

• MISCE LLANEOUS EQUIP MENT.

For classified information on B-52H defensive sys-t ems refer to T.O. 1B -52H-1-13-1.

GROUND COOLING

The critical cooling requ irements of the E CM eq uip-ment demand some precautions during groundoperation. Ground cooling must be supplied to theapplicable ram air inlet or aircraft compartmentwhen extended ground operation of ECM equip-ment is conducted. For ECM equipment t ime andtemperature limitations without ground coolingequipment, see Section II , ECM EQUIPMENTOP ERATIONAL REQU IRE MENTS.

EQUIPMENT CIRCUIT PROTECTION ANDSYSTEM DATA FLOW DIAGRAMS

The description section of each piece of defensiveequipment contains basic system power require-ments and the location of inflight accessible circuitbreakers. Defensive systems circuit breakers andtheir locations are listed in Section II I of this ma nu-al. For more detailed information on power require-ments and system data f low diagrams, refer toT.O. ’s 1B -52H -1-13-1, 1B 52G -2-20 a nd -20-1. F orlocations of all circuit breakers accessible in flight

and additional circuit protection information, referto the applicable subsection in Section I of T.O.1B -52H-1.



T.O. 1B-52H-1-13

1-5

PREFLIGHT AND OPERATIONAL CHECKS

ECM equipment preflight, operational checks,safety checks, and the dispensing of expendableswill be in accordance with the EW officer’s check-lists contained in Section II and procedures out-lined in other governing directives.

AIRCREW EMERGENCY PROCEDURES

Sect ion III of T.O. 1B-52H -1 conta ins t he a ircrew emergency procedures for a ll crewmembers.

ABNORMAL OPERATION ANDMALFUNCTION ANALYSIS

For abnormal operation and ma lfunction ana lysis ofB -52H defensive syst ems see Section II I. For cla s-sified informa tion on B-52H defensive syst ems referto T.O. 1B -52H -1-13-1.

EW OFFICER’S STATION

Figure 1-1 illustrates the layout of a typical EW of-ficers station.

ECM ANTENNAS

The antennas illustrated in figure 1-2 reflect stan-dard loading for B -52H aircraft . Actual a ircraft con-figuration may vary with antenna availability , forECM systems configuration, and special missionrequirements. For more detailed information ofECM jamming antennas and antenna radia t ion

pa tt ern s, ref er t o T.O. 1B -52H-1-13-1.

TRANSMITTER ANTENNA TYPES

Figure 1-3 ant enna d raw ings ar e provided to famil-iarize the EW officer with the physical shape andorientation of the externally mounted transmitter

antennas. Those transmitter antennas completelyenclosed in sh rouds a nd/or wit h n o distinctivesha pe have not been pictured. Due to load ing sta bility and enclosed locations, individual receiverant ennas h ave not been included.

ANTENNA PATTERNS

The a nt enna pat tern s cont a ined in T.O1B-52H-1-13-1 are antenna gain patterns illustrated in terms of isotropic gain (maximum sensi-tivity of the a ntenna in a ll directions). The a ntennapatterns are typical and their limitations must berecognized if they are to be used effectively. The iso-tropic gain of unity for each ant enna is esta blishedby determining the maximum omnidirectional sensitivity of the antenna. The complete three dimen-sional pattern coverage determines this value foreach pattern. The basis for this measurementtherefore is relat ive only to one antenna . Comparison of one antenna pattern with another to estab-lish relative merit is not possible since the isotropicvalue for each antenna will differ . It should beemphasized that these patterns indicate only thedegree of efficiency of a pa rticular a ntenna insta llat ion in different elevations and azimuths. The dis-tance values on the patterns are merely distancedto the ground for a part icular elevation angle wh enflying at 50,000 feet altitude and do not necessarilyindicat e the receiving capa bility of a particular setWhile antenna gain has a direct bearing on receiving capabilit ies of the aircraft , other parameterssuch as threat radar transmitted power, sensit ivityof receiver aboard the aircraft, losses involved intransmission lines, frequency, etc, must be known

to obtain actual receiving capabilities. For examplea threat radar with a very st rong signal might beeffectively received by an antenna with one-half iso-tropic gain at the threat distance and directionwhile a t hreat ra dar w ith a very weak signal mighnot be detected by an antenna with twice isotropicgain a t the threa t dista nce an d direction.



T.O. 1B-52H-1-13

1-6 Change 9

EW Officer’s Station (Typical) DT

Figure 1-1 (Sheet 1 of 4)



T.O. 1B-52H-1-13

Change 9 1-6A

1 LIGHT CONTROL PANEL2 SPOTLIGHT3 ALT-32L CONTROL INDICATOR (SYSTEM 20)4 ALE-24 SELECTOR CONTROL PANEL5 ALE-20 FLARE PROGRAMMING CONTROL

PANEL6 ALT-16A CONTROL INDICATOR (SYSTEM 21)7 ESCAPE HATCH8 OXYGEN REGULATOR9 ALQ-122 CONTROL MONITOR

10 ALR-20A CONTROL PANEL11 SIDE PANEL FLOOD LIGHTS12 DT ALQ-172 AUXILIARY PANEL13 DT ALQ-172 CONTROL DISPLAY UNIT (CDU)14 UPPER AISLE AND ENTRY LIGHT15 UPPER AIR OUTLET16 ALR-20A INDICATOR17 ECM CIRCUIT BREAKER PANEL18 ALQ-172 LOW PRESSURE WARNING AND

BLANKING PANEL19 RWR CONTROL INDICATOR20 EMERGENCY ALARM LIGHT

21 ALQ-153 CONTROL INDICATOR PANEL22 SI MULTIFUNCTION DISPLAY23 TEMPERATURE CONTROL PANEL24 SI CONTROL PANEL25 MASTER EXPENDABLES CONTROL PANEL26 ALR-20A LOOK THRU PANEL27 ALT-28 ANTENNA SELECTOR PANEL

28 ALQ-155 CONTROL INDICATOR PROGRAMMER(SYSTEMS 1 & 2)

29 MAIN REFUEL VALVE EMERGENCY CONTROLLEVER

30 SPECIAL WEAPONS MANUAL LOCK HANDLE

STOWAGE BRACKET31 SPECIAL WEAPONS MANUAL LOCK HANDLE32 ALQ-155 CONTROL INDICATOR PROGRAMMER

(SYSTEMS 3 & 5)33 ALQ-155 CONTROL INDICATOR PROGRAMMER

(SYSTEMS 4 & 8)34 INTERPHONE FOOT SWITCH35 ALQ-155 CONTROL INDICATOR PROGRAMMER


(SYSTEMS 7 & 14)37 ALT-16A CONTROL INDICATOR (SYSTEM 9)38 INTERPHONE CONTROL PANELS (2)39 ALE-24 PROGRAMMER CONTROL PANEL40 AERP BLOWER ELECTRICAL CONNECTER41 AERP BLOWER MOUNTING BRACKET42 ASHTRAY

43 ALT-32H CONTROL INDICATOR (SYSTEM 11)44 ALT-32H CONTROL INDICATOR (SYSTEM 12)45 MAIN CONSOLE LIGHT CONTROL PANEL46 OXYGEN BOTTLE RECHARGER47 PORTABLE OXYGEN BOTTLE48 GROUND EMERGENCY EGRESS HANDLE49 ESCAPE ROPE CONTAINER




T.O. 1B-52H-1-13

1-6B Change 9

EW Officer’s Station (Typical) (Cont)Less DT




T.O. 1B-52H-1-13

Change 9 1-7

1 LIGHT CONTROL PANEL2 SPOTLIGHT3 ALQ-122 CONTROL MONITOR4 OXYGEN REGULATOR5 ALT-32H CONTROL INDICATOR (SYSTEM 12)

6 ALT-32L CONTROL INDICATOR (SYSTEM 20)7 ALE-20 FLARE PROGRAMMING CONTROLPANEL

8 ESCAPE HATCH9 RWR CONTROL INDICATOR

10 ALR-20A CONTROL PANEL11 SIDE PANEL FLOOD LIGHTS12 ALE-24 PROGRAMMER CONTROL PANEL13 ALE-24 SELECTOR CONTROL PANEL14 UPPER AISLE AND ENTRY LIGHT15 UPPER AIR OUTLET16 ALR-20A INDICATOR17 ECM CIRCUIT BREAKER PANEL18 ALQ-172 LOW PRESSURE WARNING AND

BLANKING PANEL19 ALQ-172 CONTROL INDICATOR20 EMERGENCY ALARM LIGHT

21 ALQ-172 CONTROL MONITOR22 ALQ-153 CONTROL INDICATOR PANEL23 SI MULTIFUNCTION DISPLAY24 TEMPERATURE CONTROL PANEL25 SI CONTROL PANEL26 MASTER EXPENDABLES CONTROL PANEL27 ALR-20A LOOK THRU PANEL

28 ALT-28 ANTENNA SELECTOR PANEL29 ALQ-155 CONTROL INDICATOR PROGRAMMER

(SYSTEMS 1 & 2)30 MAIN REFUEL VALVE EMERGENCY CONTROL

LEVER

31 SPECIAL WEAPONS MANUAL LOCK HANDLESTOWAGE BRACKET32 SPECIAL WEAPONS MANUAL LOCK HANDLE33 ALQ-155 CONTROL INDICATOR PROGRAMMER


(SYSTEMS 4 & 8)35 INTERPHONE FOOT SWITCH36 ALQ-155 CONTROL INDICATOR PROGRAMMER


(SYSTEMS 7 & 14)38 INTERPHONE CONTROL PANELS39 ALT-32H CONTROL INDICATOR (SYSTEM 11)40 AERP BLOWER ELECTRICAL CONNECTER41 AERP BLOWER MOUNTING BRACKET42 ASHTRAY

43 ALT-16A CONTROL INDICATOR (SYSTEM 9)44 ALT-16A CONTROL INDICATOR (SYSTEM 21)45 MAIN CONSOLE LIGHT CONTROL PANEL46 OXYGEN BOTTLE RECHARGER47 PORTABLE OXYGEN BOTTLE48 GROUND EMERGENCY EGRESS HANDLE49 ESCAPE ROPE CONTAINER




T.O. 1B-52H-1-13

1-8 Change 10

ECM Antenna Locations

1A TRANSMIT ANTENNA (ALQ-172, SYSTEM 16)1 PHASED ARRAY (ALQ-172 TRANSMIT/

RECEIVER, SYSTEM 16) (ONE EACH SIDE)2 SCIMITAR OR DIPOLE (ALR-20A, TN-390A,

AND TN-391A) (ALT-28 MONITOR)3 A/B BAND SCIMITAR (ALR-20A, TN-386A)4 LEFT WINGTIP (ALT-32A, SYSTEM 20)5 RIGHT WINGTIP (ALR-20A, TN-386A)6 G/H-BND CONICAL HORN/SLOT ALQ-155 SYS 17 G/H-BND CONICAL HORN/SLOT ALQ-155 SYS 38 E/F-BND CONICAL HORN/SLOT ALQ-155 SYS 59 D/E-BND CONICAL HORN/SLOT ALQ-155 SYS 7

10 E/F-BND CONICAL HORN/SLOT ALQ-155 SYS 8

11 G/H-BND CONICAL HORN/SLOT ALQ-155 SYS 612 G/H-BND CONICAL HORN/SLOT ALQ-155 SYS 413 G/H-BND CONICAL HORN/SLOT ALQ-155 SYS 214 HORN (ALQ-172 OMNI RECEIVE SYSTEM 16)

15 H/I-BAND (ALQ-155, SYSTEM 2)16 H/I-BAND (ALQ-155, SYSTEM 1)17 RWR ANTENNA18 HELIX (ALR-20A, TN-388A)19 SPIRAL (ALR-20A, TN-387A)20 HELIX (ALR-20A, TN-389A)21 HORN (ALR-20A, TN-390A)22 I/J-BAND HORN (ALR-20A, TN-391A FWD)23 C-BAND DIPOLE ARRAY (ALT-16A, AS-3087A)




T.O. 1B-52H-1-13

Change 10 1-9

24 C-BAND WINGED BLADE(ALQ-122/ALT-16A, SYSTEM 9)25 ALQ-153 (AS-3193) ANTENNA (LEFT SIDE VIEW,

RIGHT SIDE OPPOSITE)26 HORN (ALQ-172 OMNI RECEIVE SYSTEM 15)27 RWR ANTENNA (ONE EACH SIDE)28 A/B-BAND BLADE (ALT-32A, SYSTEM 11)29 E/F-BAND CONICAL HORN/SLOT

(ALQ-155, SYSTEM 13)

30 D/E-BAND CONICAL HORN/SLOT(ALQ-155, SYSTEM 14)31 A/B-BAND BLADE (ALT-32A, SYSTEM 12)32 I/J-BAND HORN (ALR-20A, TN-391A AFT)

(ONE EACH SIDE FUSELAGE)33 PHASED ARRAY (ALQ-172 TRANSMIT/

RECEIVER, SYSTEM 15)




T.O. 1B-52H-1-13

1-10

Transmitter Antenna Types




T.O. 1B-52H-1-13

1-11/(1-12 blank)




BL



T.O. 1B-52H-1-13

Change 7 1-13

RECEIVER SYSTEMS

AN/ALR-20A SEARCH RECEIVER 1-13

FUNCTIONAL DESCRIPTION 1-13

COMPONENT DESCRIPTION 1-15

CONTROLS AND INDICATORS 1-23

RADAR WARNING RECEIVER 1-27


OPERATIONAL MODES 1-28GUNNER STATION 1-31



NORMAL OPERATION 1-42K

SENSOR INTEGRATION SYSTEM 1-43




NORMAL OPERATION 1-53

AN/ALR-20A SEARCH RECEIVER

FUNCTIONAL DESCRIPTION

The AN/ALR-20A receiving set provides th e ca pa -bility of simultaneously surveying, detecting, anddisplaying all radio frequency transmissions in thefrequency band covered. Onboard OAS Radar Settransmitter is blanked to prevent display of thetransmitted signals. The receiving set is tied inw ith th e ALT-32A a nd ALT-16A jam min g t ra nsm it-ters to enable the EW officer to look through thejamming signal. Audio examination of the receivedsignals is accomplished through t ie-in with the in-

terphone system. Self-test features provide compre-hensive checks of the receiving set on t he ground ordur ing fli ght . AN/ALR-20A component locat ions a resh own in f igu re 1-4. The AN/ALR-20A cont rols a ndindicat ors ar e cont a ined in figur e 1-10.

System Function

Seven radio frequency tuners are provided to coverthe system frequency spectrum. System operationis cont rolled from th e C-9449/ALR-20A receivi ngset control a nd th e IP -1168/ALR-20A indica tor Less

DS , or I P -1168B /ALR-20A ind ica t or DS .

Tw o modes of opera tion a re provided to opera te t hetuners and the display of the ALR-20A receivingsystem. The primary mode is the automatic mode(SWEE P WID TH cont rol in MAX). In th is mode, alltuners are tuned by a linear rising sawtooth. Thesystem responds t o both cw an d modulated signa ls.Special circuits are used to intensify the receivedsignals for ease of identification on the indicator.The secondary mode of operation is the manualmode (SWEEP WIDTH control less than MAX).

This mode allows the operator to singularly tune aselected tuner through the use of the MAN FREQCONTROL. In order to facilitate frequency identification, an intensified spot is placed on the selectedtrace at a position corresponding to the tuner frequency. Special provisions for audio examination ofthe received signals are also provided whenSWEEP WIDTH control is in AUDIO. The audiooutput feeds into the interphone system enablingthe opera tor to further evalua te th e received signaand aid in the determination of approximate pulserepetition frequency.

The C-4782/ALR-20 cont rol en a bles th e opera tor to

look through his own jammer signals to surveyother signals in the band. This look through isaccomplished with a minimum of jammer signainterruption. In look through operation, the jammers remain on continuously for 50%of the sweeptime. During the 50%look through period, the jammers a re chopped on a nd off. The 50%look t hroughperiod shifts from left to right such t ha t in not lessthan 10 sweep periods, it is possible to look at signals a cross the full band.

POWER DISTRIBUTION

The m a st er pow er su pply, P P -3406A/ALR-20A, pro

vides th e ma in low volta ge regulat ed power for thesystem. Input aircraft electrical power supplied tothe power supply is 115-vac, three-phase, 400-Hzpower a nd 28-vdc pow er. Special h igh volta ge powersupplies are provided for each tuner and for thecathode ray tube in the indicator. System powerand operation are controlled from the IP-1168ALR-20A indicator Less DS , or I P -1168B/ALR -20Aindicator DS a nd t he C -9449/ALR-20A receivercontrol.



T.O. 1B-52H-1-13

1-14 Change 2

RECE IVING AND DI SP LAY

The receiving and display circuits are comprised ofthose circuits which receive, process, and displaydetected RF energy within the frequency range ofthe RF tun ers. Two modes of opera tion a re used tocontrol the tuners and the display of the ALR-20Asystem. The primary mode of operation is the auto-

matic mode (SWEEP WIDTH control in MAX). Inthis mode, all tuners are tuned throughout theirfrequency range by a linear rising sawtooth signal(tun ing s igna l). The seconda ry mode of operat ion isthe manual mode (SWEEP WIDTH control lessthan MAX). This mode allows the operator tomanually tune a selected tuner by selecting thesweep length w ith t he SWEE P WID TH control andpositioning the selected sweep length with theMAN FREQ CONTROL. In order to facilitate fre-quency identification, an intensified spot (audiodot) is displayed on the selected trace at a positioncorresponding approximately to the tuner fre-quency when the SWEEP WIDTH control is in

AUDIO.

DS

An arrow is displayed below the audio dot. The fre-quency corresponding to the location of audio dot isdisplay ed below th e left side of the tra ce.

The low freq uen cy t un er TN-386A/ALR-20A is f un c-tionally different from the other tuners. The inputcircuitry to this tuner is such that RF energy fromtw o antenna s is a pplied to six tuner modules whichmake up the tuner bandwidth .

E a ch of t he TN-387A/ALR -20A th ru TN-391A/

ALR-20A RF tuners is identical in function. Eachunit is tuned across its frequency range by meansof a ma gnetically t una ble filter.

The C -9449/ALR-20A receiver cont rol cont a ins a llcircuitry necessary to generate the top-chop andbottom-chop signals, the main sweep (tuning sig-nal), main sweep retrace blanking and wobble, andindicat or intensity signals. I n a ddit ion, circuitry forprocessing video, video test signals expanded videoan d a udio is conta ined within t he control unit .

Less DS

The d ispla y of vid eo on t he I P -1168/ALR-20A ind i-cator received from the seven system tuners isaccomplished through the use of a special six-guncat hode ra y t ube. Tra ce 1 displa ys video receivedfrom t he TN-386A/ALR-20A tu ner th roug h t he us eof gun 1. Tra ces 2 and 3 displa y video received fromTN-387A/ALR -20A a nd TN-388A/ ALR-20A tu ners

respectively through the use of gun 2. In order touse a single gun to display two traces, the t imeshare chopper function generator generates a bot-tom-chop and then a top-chop signal in a repeatingsequence. When the bottom-chop signal is receivedvid eo from t he TN-387A/ALR-20A t un er i s d is-played on trace 2. When the top-chop signal isreceived, v ideo fr om t he TN-388A/ALR-20A t un er is

display ed on tr a ce 3. Thus, gun 2, on a time-sha ringbasis, is used to generat e two tra ces. Indicator guns3 and 4 are likewise used to display video from theother four tuners. Indicator guns 5 and 6 are usedin t he expand mode only.

DS

The di spla y of video on t he I P -1168B /ALR-20A ind i-cator received from the seven system tuners isaccomplished through the use of an anolog to digi-tal conversion and displayed on the monochromecathode ray t ube.

Special provisions are made for audio examination

of the received signal while operating in themanual mode. With the SWEEP WIDTH control inAU DIO, a n int ensified spot w ill be displayed on theindicator for the corresponding trace. The horizon-tal position of the intensified spot is controlled bythe MAN FREQ CONTROL. Any received signal atthe frequency indicated by the position of the inten-sified spot will produce an audio output. The audiooutput is routed to the aircraft interphone system.The operator can evaluate the received signal anddetermine the approximate pulse repetition fre-quency or general t ype of other modulat ion.

EXPAND MODE

The expand mode allows the operator to simulta-neously select received video from any two RF tun-ers for expansion displa y on the indicat or.

Less DS

Two separa te guns w ithin t he indicat or a re used forthe expansion display; gun 5 for expansion trace Band gun 6 for expansion trace A. Guns 5 and 6 arealso used to display the markers used with expan-sion A and B tra ces.

DS

Two separa te tr a ces a re used for th e expan sion dis-

play.

The portion of the trace that is expanded is deter-mined by the settings of the SWEEP WIDTH con-trol and the MAN FREQ CONTROL.



T.O. 1B-52H-1-13

Change 2 1-15

J AMMER BLANKING

The C-4782/ALR-20 jam mer cont rol (fig ur e 1-6)enables the operator to look through selected on-boar d jammer signals t o survey other signals in theband. This look through is accomplished with mini-mum interruption of the jammer signals. In thelook through mode, the jammers remain on for 90%

of the normal receiver sweep time and the tunersare blanked out. During the 10%look through time,the jammers and tuners are chopped on and off atalterna te intervals such tha t ea ch is on for 100 mi-croseconds and off for 100 microseconds. The 10%look through period shifts from left to right suchthat in not less than 10 sweep periods, it is possibleto look at signals a cross the full ban d.

The four pushbuttons on the front of the jammercontrol are spring loaded to the off position. Whenlook through of a particular jamming signal is de-sired, the corresponding switch on the front of thejamm er cont rol must be held depressed.

RF TEST MODE

The RF test mode provides a coarse check on theoverall operation of the system. The RF TESTswitch is located on the front of the ALR-20A indi-cator. Depressing this switch results in an RF testenable signal being routed through theP P -3406A/ALR-20A pow er su pply t o oscill a t orswith in each of the RF t uners.

VIDEO TEST MODE

Video test permits a complete test of the video cir-cuits exclusive of the tuner inputs. The video testcircuits are activated by depressing the VIDEOTEST switch located under the adjustment cover atthe top of the indicator Less DS , or the top of thefront panel DS .

COMPONENT DESCRIPTION

Receiver-Control (C-9449/ALR-20A)

The receiver-control (figure 1-5) is located in theleft side of the EW officer front panel. The controlpanel contains seven sets of three controls, one setfor each of seven tuners. The three controls consist

of a SWEEP WIDTH control, a MAN FREQ CON-TROL, and an RF LEVEL control. The SWEEPWIDTH control controls the sweep width of the as-sociated trace as displayed on the IP-1168ALR-20A indicator Less DS , or I P -1168B/ALR -20Aindicator DS and supplied to the tuner when ro-tated from MAX to AUDIO. When the SWEEPWIDTH control is in AUDIO, the sweep width wilbe approximately zero and an intensified dot w ill bedisplayed on the indicator. The MAN FREQ CON-TROL is used to position the sweep for a particulartrace, with SWEEP WIDTH control not in AUDIOor position the intensified dot for a particular tracewith the SWEEP WIDTH control in AUDIO. Any

processed video at the frequency indicated by theintensified dot will be routed to audio amplifier circuits for analysis by the EW officer through theinterphone system. The RF LEVEL control is usedto adjust the gain of a traveling wave tube amplifi-er and thus, in turn, the display of received videoon the indicat or.

Look Through Panel (C-4782/ALR-20)

The look through panel (figure 1-6) initiates the“look through” function for the ALR-20A. This function permits the E W officer to look through h is ownjam ming tra nsmitt er signals. In look through mode

of operation, the jamming effectiveness of the se-lected a ircraft t ran smitters is reduced by only 10%of the transmitter duty cycle. This minimizes theeffect of look through on jammer effectiveness andpermits the EW officer to observe and track athreat signal frequency shift . Controls on the lookthrough panel consist of four buttons: one for highfreq uen cy ALT-32A, one for low freq uen cy ALT-32Aone for th e ALT-16A an d on e for a ll ALT-32A an dALT-16A tra nsmit ters. When a ny butt on isdepressed, the output is routed to the look throughlogic circuit board of the receiver control whichoperates in conjunction with the look through gen-erator and driver circuits to perform the look

through function.



T.O. 1B-52H-1-13

1-16 Change 2

ALR-20A Indicator (IP-1168) And Controls Less DS

The IP-1168 indicator (figure 1-10) is located in thelower center of the EW officer front panel. In addi-tion to displaying received signal information, thepanel contains eight primary controls: SCALEILL U M, RF TES T, VOLU ME , POWER, EXP AN-SION A, EXPANSION B, LEFT MARK, and

RIGHT MARK. The SCALE ILLUM control is usedfor obtaining desired graticule illumination. The RFTEST switch activates test oscillators located ineach tuner. The signals injected into the tuners bythe oscillators are processed and displayed on theindicator. If all test signals are present and rela-tively equal in amplitude, the system can beassumed to be operating normally. The VOLUMEcontrol sets the desired level of the processed audiooccurring a s a result of received video. The P OWERswitch has three positions: OFF, STBY, and ON.OFF position prohibits power from being applied toany ALR-20A circuits. STBY position permits theapplication of power to filaments, heaters, and allsystem devices requiring warmup prior to opera-tion. The two expansion switches, EXPANSION Aand EXPANSION B, have an OFF posit ion andseven num erical positions, one for ea ch tr a ce. Thesetw o switches permit t he expa nsion of received videofrom any two selected traces. The LEFT MARKcontrol and the RIGHT MARK control positions thereference ma rkers for expand t races A and B .

NOTE

Some trace 6 strobing and marker jit teringshould be considered normal operation and

the degree of strobing requiring mainte-nance will be determined by the electronicwar fa re o f f icer in coord ina t ion w i th themaintenance technician.

ALR-20A Indicator (IP-1168B) And Controls DS

The I P -1168B indi cat or (figure 1-10A) is loca ted inthe lower center of the EW officer front panel. Inaddit ion to displaying received signal information,the panel contains eleven primary controls: MAS-TER ILLUMINATION, EDGE ILLUMINATION,SCALE ILLUMINATION, EMITTER PERSIS, RFTES T, P OWE R, RI G HT MARK, EXP ANSI ON A,

EXPANSION B, LEFT MARK, and VOLUME. Thethree ILLUMINATION controls are used to obtainthe desired display illumination. EMITTER PER-SIS is used to vary the length of t ime a signal isdisplayed after the actual intercepted signal hasdisappeared. The RF TEST switch activates test

oscillators located in each tuner. The signalsinjected into the tuners by the oscillators are pro-cessed and display ed on t he indicat or. If all t est sig-nals are present and relatively equal in amplitude,the system can be assumed to be operating nor-mally. The POWER switch has three positions:OFF, STBY, and ON. OFF position prohibits powerfrom being applied to any ALR-20A circuits. STBY

position permits the application of power to fila-ments, heaters, and all system devices requiringwarmup prior to operation. The LEFT MARK con-trol and the RIGHT MARK control positions thereference markers for expand traces A and B. Thetwo expansion switches, EXPANSION A andEXPANSION B, have an OFF posit ion and sevennumerical positions, one for each trace. These twoswitches permit the expansion of received videofrom any two selected traces. The VOLUME controlsets the desired level of the processed audio occur-ring as a result of received video. In addit ion, theindicator BIT SELECT switch in the BIT 1 positiongenerates a st at ic test screen th at provides both in-dicator internal status information and permits anassessment of indicator video performance. BITSelections BIT 2, BIT 3, and ALIGN are mainte-nance functions. For a BIT failure, a BIT FAIL mes-sage is displayed in reverse video below the rightend of E xpans ion Tra ce A for both n orma l an d B IT2 displays.

Power Supply (PP-3406A/ALR-20A)

The power supply (figure 1-7) is located in the up-per left electrical equipment rack below the crew bunk. The power supply provides the necessary

supply voltages required by the ALR-20A system,serves as a junction box for all components of thesystem, a nd conta ins t iming a nd protection circuits.The power supply receives prim e input pow er fromthe aircraft electrical system consisting of 115-voltthree-phase ac and TR power. Input and outputvoltages are protected by fuses located on the frontpanel. A voltmeter and selector switch are alsolocated on the front panel for manual monitoring ofthe operating condition of the power supply. Whenthe ALR-20A system is initially placed ON or inSTBY, a time delay of approximately 1 minute isactua ted wh ich delays a pplicat ion of volta ges to allcircuits except system heater circuits, and DS in

a ddition S TB Y applies 115 va c to fully pow er the in-dicator. The delay will occur automatically even ifth e pow er selector is pla ced in ON position init ially.The 1-minute time delay is fully reset in the eventpower selector is placed to OFF position and thenba ck to STB Y or ON.



T.O. 1B-52H-1-13

Change 2 1-16A/(1-16B blank)

RF Tuner (TN-386A/ALR-20A)

The TN-386A/ALR-20A RF t un er (figu re 1-8) is lo-cated in the EW officer compartment. This unittunes a cross its frequency ra nge through the use oftuner modules. Each of the tuner modules isswitched on electrically at preset intervals of t imeand tuned by the voltage-controlled capacitance

tuning elements. In addit ion to the tuner modules,the unit contains a video amplifier, ramp pick-offcircuit, frequency control circuits, and a test oscilla-tor. The test oscillator provides test signals at fre-quencies.

RF Tuners (TN-387A/ALR-20A through TN-391A/ALR-20A)

The tuners (figure 1-8) are located as shown in fig-ure 1-4. Ea ch unit t unes across its frequency rangeby means of electronically tunable solid-state fil-ters. Each unit contains a RF amplifier and asso-ciated power supply, video detector, log video ampli-fier, and a test signal generator for self-test.

Blanking Amplifier

ALR-20A OAS blanking is provided through theblanking amplifier (figure 1-9) which prevents thetriggering of the ALR-20A receiver circuits by the

OAS radar. This eliminates the possibility of confusing the aircraft OAS signal with external signals .

Antennas

Antenn a s used w ith the ALR-20A receiving set consist of a scimitar a ntenna in the forw ard w heel welarea , a wingt ip antenna on the r ight wing; twoRX-1 antennas located in external blisters on theleft and right sides of section 49; and two RL-1 an-tennas, two RS-1 antennas, and a 10-30257 anten-na loca ted in th e nose rad ome. A 4125A monitoringscimitar or dipole antenna is installed on the un-derside of the fuselage just forward of the crew en-trance hatch.

Monitoring Antenna

The monitoring antenna allows monitoring of thesystems operating in the frequency range of theTN-390A and TN-391A tuners. The monitoringantenna can be momentarily disconnected, when

look through of jamming signals is desired, bypressin g t he ALT-28 MONI TOR (OMNI)pushbut ton on t he ALT-28 ant enna selector pa nel(S ee ALT-28 ANTE NNA S E LE CTOR P ANEL , inthis s ection.)



BL



T.O. 1B-52H-1-13

1-17

ALR-20A Component Locations




TN 389A/ALR 20A RF TUNER (A6671)



PP 3406A/ALR 20APOWER SUPPLY (A6667)

TN390A/ALR 20ARF TUNER (A6672)

LEFT LOAD CENTRAL

BLANKING AMPLIFIER (A6585)

UPPER LEFT EQUIPMENT RACK

SECTION 41

ANTENNA AS3102/A(E6254)

ADAPTER UG27D/U

TN 386A/ALR 20ARF TUNER (A6668)

TO WING TIPANTENNA VR 1

EW OFFICER’S STATION

A67339

C 9449/ALR 20ARECEIVER CONTROL (A6665)

INDICATOR (A6666)

C 4782/ALR 20JAMMERCONTROL(A6695)

BLANKING MODULE

ALR 20A

T.O. 1B-52H-1-13

1-18 Change 2

ALR-20A Component Locations (Cont)




T.O. 1B-52H-1-13

1-19

C-9449/ALR-20A Receiver-Control

1 MANUAL FREQUENCY CONTROL(TN-391A/ALR-20A RF TUNER, AFT)

2 RF LEVEL CONTROL (TN-391A/ALR-20A RFTUNER, AFT)

3 MANUAL FREQUENCY CONTROL(TN-391A/ALR-20A RF TUNER, FWD)

4 RF LEVEL CONTROL (TN-391A/ALR-20A RFTUNER, FWD)

5 MANUAL FREQUENCY CONTROL(TN-390A/ALR-20A RF TUNER)

6 RF LEVEL CONTROL (TN-390A/ALR-20A RF

TUNER)7 MANUAL FREQUENCY CONTROL(TN-389A/ALR-20A RF TUNER)

8 RF LEVEL CONTROL (TN-389A/ALR-20A RFTUNER)







15 SWEEP WIDTH CONTROL (TN-386A/ALR-20A RFTUNER)


17 SWEEP WIDTH CONTROL (TN-388A/ALR-20A RF

TUNER)18 SWEEP WIDTH CONTROL (TN-389A/ALR-20A RFTUNER)


20 SWEEP WIDTH CONTROL (TN-391A/ALR-20A RFTUNER, FWD)

21 SWEEP WIDTH CONTROL (TN-391A/ALR-20A RFTUNER, AFT)

Figure 1-5



T.O. 1B-52H-1-13

1-20

ALR-20A Look-Thru Panel

1 ALT-32A LOW BAND LOOK THRU BUTTON2 ALT-32A HIGH BAND LOOK THRU BUTTON3 ALT-16A LOOK THRU BUTTON4 “ALL” LOOK THRU BUTTON

Figure 1-6



T.O. 1B-52H-1-13

1-21

PP-3406A/ALR-20A Power Supply

1 POWER SUPPLY PROTECTION FUSES2 VOLTAGE MONITOR METER3 EXTERNAL METER CONNECTORS4 VOLTAGE MONITOR METER SELECTOR SWITCH

5 ELAPSED TIME INDICATOR6 INPUT POWER CONNECTOR7 SPARE FUSES

Figure 1-7

RF Tuners

RF TUNER TN-386A/ALR-20A RF TUNER TN-( )A/ALR-20A

Figure 1-8



T.O. 1B-52H-1-13

1-22 Change 7

Blanking Amplifier

1 AN/ALQ-172(V) NO. 15, NO. 162 BLANKING OUTPUT TO RWR SIGNAL PROCESSOR3 BLANKING OUTPUT TO AN/ALR-20A RECEIVER4 OAS BLANKING INPUT5 POWER-ON INDICATOR LIGHT6 POWER RECEPTACLE7 OPERATING FUSE

8 SPARE FUSEFigure 1-9



T.O. 1B-52H-1-13

Change 2 1-23

ALR-20A Controls and Indicators Less DS

IP-1168 CONTROL-INDICATOR

1 SWEEP WIDTH CONTROLS (7)2 MANUAL FREQUENCY CONTROLS (7)3 RF LEVEL CONTROLS (7)4 SCALE ILLUMINATION CONTROL5 INTENSITY AND FOCUS ADJUSTMENTS6 HP, V, AST, AND WIDTH ADJUSTMENTS7 VIDEO TEST BUTTON8 RF TEST BUTTON9 ELAPSED TIME INDICATOR

10 RIGHT MARKS

11 INOPERATIVE12 CRT SCREEN13 POWER SELECTOR14 RIGHT MARKER CONTROL15 EXPANSION TRACE SELECTOR (B TRACE)16 EXPANSION TRACE SELECTOR (A TRACE)17 LEFT MARKER CONTROL18 VOLUME CONTROL19 LEFT MARKS




T.O. 1B-52H-1-13

1-24 Change 2

ALR-20A Controls and Indicators Less DS (Cont)

NO.CONTROL-INDICATOR FUNCTION

C-9449/ALR-20A CONTROL

1 SWEEP WIDTH Controls (7 places) Seven sweep width controls, one for each trace, control the width ofsweep of the tuners. The controls are adjustable from 0 to 100%. Only theselected position of the band is available for viewing and the rest of thetrace is lost. When the control is in MAX position (full CW), the full tuningrange (100%) of the tuner is displayed. When the control is in AUDIO det-ent (full CCW), a dot will appear at the frequency selected by the manualfrequency control and audio of that frequency is available.

2 Manual Frequency Controls (7 places) Seven manual frequency controls, one for each trace, control the positionof the tuning range on the main trace when the sweep width control is outof AUDIO detent. When the sweep width control is in the AUDIO detent,the manual frequency control controls the position of the dot (frequency)on the main trace.

3 RF LEVEL Controls (7 places) Seven RF level controls, one for each trace, provide a means of adjustingthe signal strength of the associated bands.

IP-1168/ALR-20A INDICATOR

4 Scale Illumination Control Provides a means of adjusting the illumination of the frequency scale.

5 Intensity and Focus Adjustments Provides means of adjusting trace intensity and focus.

6 HP, V AST, and Width Adjustments Provides means of adjusting trace posit ion, astigmatism, and width.

Adjustments of the intensity, focus, HP, V, AST, and width con-trols should be accomplished only by ground maintenance per-sonnel or during SIOP/contingency operations. The use ofextreme care and an insulated screwdriver is recommendeddue to the fragile potentiometers and possible contact with highvoltages.

7 VIDEO TEST Button Provides a means of testing the video circuitry exclusive of the tuners.When depressed, a signal of 3/16 inch minimum in amplitude shouldappear at the left edge of each trace (with the RF level control in MAXposition).

8 RF TEST Button For RF test frequencies, refer to T.O. 1B-52H-1-13-1)

9 Elapsed Time Indicator Indicates the total elapsed time that the IP-1168/ALR-20A indicator hasbeen in operation.

10 Right Marks Right reference marks for expand trace A and B.

11 Inoperative




T.O. 1B-52H-1-13

Change 2 1-25


IP-1168/ALR-20A INDICATOR (Cont)

12 CRT Screen Provides a panoramic display of intercepted radar signals present withinthe frequency range of the ALR-20A system. The CRT screen has sevenmain traces representing seven individual bands of frequencies plus twoexpansion traces used for closer analysis of any signal appearing on anyof the seven main traces. Intercepted signals are shown as vertical spikesextending from the baseline of each trace. Signals appearing on the lowersix main traces and the expansion traces appear above the baselinewhile signals on main trace No. 7 appear below the baseline. Traces 6and 7 cover the same frequency range and will display signals receivedon the forward and aft tuners, respectively. The height of the spike is anindication of signal strength and the position of the spike along the base-line is a measure of the center frequency of the intercepted radar signal.

13 Power Selector STBY position applies power to filaments, heaters, and all system

devices requiring warmup prior to operation. ON position applies all sys-tem voltages for full operation. OFF position removes all power from theALR-20A circuits.

14 Right Marker Control Controls the position of the right marker on both expansion traces.

15 Expansion Trace Selector (B Trace) Provides a means for selecting a main trace for expansion on B trace.When moved from OFF position to a numbered position, that portionselected by the sweep width control will be displayed on the appropriateexpansion trace.

16 Expansion Trace Selector (A Trace) Provides a means for selecting a main trace for expansion on A trace.When moved from OFF position to a numbered position, that portionselected by the sweep width control will be displayed on the appropriateexpansion trace.

17 Left Marker Control Controls the position of the left marker on both expansion traces.

18 VOLUME Control Provides a means of adjusting the volume of audio received in theintercom system. Operative only when sweep width control is full CCW(in detent).

19 Left Marks Left reference marks for expand trace A and B.




T.O. 1B-52H-1-13

1-26 Change 2

ALR-20A Controls and Indicators DS

IP-1168B CONTROL-INDICATOR

1 SWEEP WIDTH CONTROLS (7)2 MANUAL FREQUENCY CONTROLS (7)3 RF LEVEL CONTROLS (7)4 MASTER ILLUMINATION CONTROL5 EDGE ILLUMINATION CONTROL6 SCALE ILLUMINATION CONTROL7 EMITTER PERSISTENCE SELECTOR8 BIT SELECT SWITCH9 VIDEO TEST BUTTON

10 RF TEST BUTTON11 CRT SCREEN12 POWER SELECTOR13 RIGHT MARK CONTROL14 EXPANSION TRACE SELECTOR (B TRACE)15 EXPANSION TRACE SELECTOR (A TRACE)16 LEFT MARK CONTROL17 VOLUME CONTROL

Figure 1-10A (Sheet 1 of 4)



T.O. 1B-52H-1-13

Change 2 1-26A

NO. CONTROL-INDICATOR FUNCTION

C-9449/ALR-20A CONTROL

1 SWEEP WIDTH Controls (7 places) Seven sweep width controls, one for each trace, control the width ofsweep of the tuners. The controls are adjustable from 0 to 100%. Only theselected position of the band is available for viewing and the rest of thetrace is lost. When the control is in MAX position (full CW), the full tuningrange (100%) of the tuner is displayed. When the control is in AUDIO det-ent (full CCW), a dot will appear at the frequency selected by the manualfrequency control and audio of that frequency is available. An arrow is dis-played below the audio dot. The frequency corresponding to the locationof audio dot is displayed below the left side of the trace.

2 Manual Frequency Controls (7 places) Seven manual frequency controls, one for each trace, control the positionof the tuning range on the main trace when the sweep width control is outof AUDIO detent. When the sweep width control is in the AUDIO detent,the manual frequency control controls the position of the dot (frequency)on the main trace.

3 RF LEVEL Controls (7 places) Seven RF level controls, one for each trace, provide a means of adjustingthe signal strength of the associated bands.

IP-1168B/ALR-20A INDICATOR

4 MASTER ILLUMINATION Control Provides a means of adjusting the overall brightness of the CRT screen.All displayed images including trace video, frequencies, and graticule areequally affected.

5 EDGE ILLUMINATION Control Provides means of adjusting the writing surface edge lighting brightness.Only user markings are affected.

6 SCALE ILLUMINATION Control A sixteen position (0-15) digital selector controls relative brightness of

displayed frequencies and graticule.

NOTE

Rapid movement of the Scale Illumination control may delaythe re-drawing of the displayed frequencies and the graticule.

7 EMITTER PERSIS Selector A sixteen position selector selects one of 5 persistence values. As a mini-mum, 5 rates are provided: P0 thru P4.

P0 - No electronic persistence. The emitter trace is visible only as longas it is being received.

P1 - Persistence approximately equal to the IP1168 ALR-20A Indicator

P2 - Increased persistence over P1

P3 - Increased persistence over P2

P4 - Infinite persistence causes the displayed signals to remain displayeduntil power is removed or persistence is changed.

NOTE

Operating the system with a P4 level of persistence may de-grade the operators ability to detect new signals.




T.O. 1B-52H-1-13

1-26B Change 2

ALR-20A Controls and Indicators DS (Cont)


IP-1168B/ALR-20A INDICATOR (Cont)

8 BIT SELECT Switch The BIT SELECT Switch selects display operating mode

NOTE

• To prevent the inadvertent selection of a BIT mode (BIT 2,

BIT 3, or ALIGN) there is a five second delay between opera-tor positioning of the switch and engagement of the selectedmode.

• The BIT 3 routine requires 5 minutes to complete. Once BIT

3 has completed, it requires approximately 70 seconds to exitBIT 3 and return to normal operation after the BIT SELECTSWITCH is placed to OFF.

OFF – Normal operation

BIT 1 – Static test screen with status (such as temperature, fan rotation,firmware) displayed. See fig 1-10B.

BIT 2 – Normal screen layout but uses internally generated video/sweepsignals. See fig. 1-10C.

BIT 3 – Dynamic test of all memory and display circuits. This screen isintended for factory testing only.

NOTE

If BIT 3 is entered and terminated early before the BIT auto-matically completes, indicator alignment may be lost . In addi-tion frequency data may be lost which cannot be reloaded inflight.

ALIGN – Alignment mode allows maintenance personnel to adjust traceheight, width, and position. The parameters adjustable at this positionare: Video Offset, Video Gain, Sweep Offset, and Sweep Gain.

1. Move BIT SELECT control to ALIGN.2. All traces will appear on screen with parameter selection text below

each line. Video Test function is automatically enabled. The currentlyselected parameter will be displayed in reverse video. See figure1-10D.

3. To select the parameter of interest, rotate the SCALE control until thedesired parameter is shown in reverse video. The SCALE controlrotation is continuous, moving from line to line in sequence throughthe displayed traces.

4. Once the desired trace and parameter are selected, the EMITTER

PERSIS control is rotated to affect the desired change. The Operatorobserves trace height, width, and position while making theadjustment.




T.O. 1B-52H-1-13

Change 2 1-26C


IP-1168B/ALR-20A INDICATOR (Cont)

9 VIDEO TEST Button Provides a means of testing the video circuitry exclusive of the tuners.When depressed, a signal of 3/16 inch minimum in amplitude shouldappear at the left edge of each trace.

10 RF TEST Button Refer to T.O. 1B-52H-1-13-1 for RF test frequencies.

11 CRT Screen Provides a panoramic display of intercepted radar signals present withinthe frequency range of the ALR-20A system. The CRT screen has sevenmain traces representing seven individual bands of frequencies plus twoexpansion traces used for closer analysis of any signal appearing on anyof the seven main traces. Intercepted signals are shown as vertical spikesextending from the baseline of each trace. Signals appearing on the lowersix main traces and the expansion traces appear above the baselinewhile signals on main trace No. 7 appear below the baseline. Traces 6and 7 cover the same frequency range and will display signals received

from the forward and aft tunners respectively. The height of the spike isan indication of signal strength and the position of the spike along thebaseline is a measure of the center frequency of the intercepted radar sig-nal.The audio dot, arrow, and frequency (represented by XXXX) areshown below the fourth main trace. The frequency is based on the calibra-tion of the display.

12 Power Selector STBY position applies power to filaments, heaters, CRT display, and allsystem devices requiring warmup prior to operation. The OFF to STBYaction takes approximately 50 seconds. ON position applies all systemvoltages for full operation. STBY to ON action (full up display) takes 10seconds. OFF to ON (full up display) takes approximately 60 seconds.OFF position removes all power from the ALR-20A circuits.

13 Right Mark Control Controls the position of the right marker on both expansion traces.

14 Expansion Trace Selector (B Trace) Provides a means for selecting a main trace for expansion on B trace.When moved from OFF position to a numbered position, that portionselected by the sweep width control will be displayed on the appropriateexpansion trace.

15 Expansion Trace Selector (A Trace) Provides a means for selecting a main trace for expansion on A trace.When moved from OFF position to a numbered position, that portionselected by the sweep width control will be displayed on the appropriateexpansion trace.

16 Left Mark Control Controls the position of the left marker on both expansion traces.

17 VOLUME Control Provides a means of adjusting the volume of audio received in the

interphone system. Operative only when sweep width control is full CCW(in detent).




TempTop FAN SPEED

SCALE

TempBottom

0123456789ABCDEFGHIJKLMNOPQRSTUVWXYZ

abcdefghijklmnopqrstuvwxyz

RPM

1

2

3

4

5

6

7

8

A67544

°F °F

PERSISTENCE

6

T.O. 1B-52H-1-13

1-26D Change 2

IP-1168B BIT 1 SCREEN DS

This screen (figure 1-10B) is displayed when theunit is placed in the BIT 1 mode, by rotation of theBIT SELECT knob located on the unit’s top frontpanel . I t presents unit in ternal sta tus and par tnum ber/revis ion inform a tion, provides feedba ck onP ersistence and Scale Illumina tion knob operation,

and provides images which aid in determining unitvideo performance (including size, geometry, band-width , focus, and intensity ran ge).

Geometry

The box that runs the perimeter of the screen isdrawn at the limits of the display. It is normal forth e box to disa ppear in th e corners. The five circlesand squares located in the corners and center areuseful in determining the display’s geometry. Thecircles should be nearly round, not egg shaped. The

squares should be nearly square and not rectangle.A complete character list is displayed at thescreen’s bottom center. The characters should beclear an d reada ble.

IP1168B BIT 1 Screen DS

Figure 1-10B (Sheet 1 of 3)



T.O. 1B-52H-1-13

Change 5 1-26E

IP1168B BIT 1 Screen DS (Cont)


1 Unit and Firmware Information These boxes provide part number and other information about the dis-play. None of this information changes or is affected by BIT.

2 Intensity Gradients (2 places) These two areas display all 16 levels of intensity, from full black to fullbright. They can be used to verify display range by direct observation ofthe gradients.

3 Display Bandwidth (2 places) These two locations provide a means to determine the display’s band-width. The top two boxes contain lines spaced at 128 lines per inch (LPI),while the bottom two boxes are at 64 lines per inch. The individual linesin all boxes should be distinguishable.

NOTE

The upper left box (128 vertical) is the most difficult to distin-guish. To distinguish individual lines it is necessary to use mag-nification (such as an eye loupe) and to adjust the Master Illumi-nation control for optimal view-ability.

4 Scale Readout This display is intended for testing the IP-1168B front panel SCALE Illumi-nation Control. The numbers in this box increment or decrement, depend-ing on the rotation direction of the front panel control knobs. The specificvalues range from 0 to 15, and they rollover. With each click of the knobthe displayed value will either increment or decrement by one and changethe scale illumination respectively. If knob is rotated quickly, some dis-played values may be missed. Scale illumination will change when thecontrol is moved.

5 Fan Speed The number in this box is the measured speed of the display’s internal fanor blower. At room temperature/sea level the fan speed should be 3400to 3800 RPM. At air temperatures below about 50° F, an internal thermalswitch turns off the fan, producing a fan speed readout of 0000 RPM. Ifthe temperature is above 77°F (25°C) and fan speed is below 2000 RPM,a failure condition exists and the BIT FAIL message will be displayed in

reverse video on the normal or BIT 2 display.

NOTE

The Fan Speed BIT failure condition requires maintenance ac-tion as soon as possible. No fire hazard exists. However, contin-ued usage of the system without repair will reduce the reliabilityof a number of components in the system. Therefore, only con-tinue to run the system in a tactically urgent situation. The sys-tem may shut itself down at any time without warning followingthis failure.




T.O. 1B-52H-1-13

1-26F Change 5

IP1168B BIT 1 Screen DS (Cont)


6 Temperature (Top and Bottom) These are temperature reading on the Trace Generator CCA, one locatedat the top of the CCA and the other at the bottom of the CCA. After warm-up, the temperatures read about 20° F higher than the ambient inlet air

temperature. If the average of the two temperature readings is 176°F (80°C) or higher, a potential failure condition exists and the BIT FAIL messagewill be displayed in reverse video on the normal or BIT 2 display.

NOTE

The Temperature BIT failure condition requires maintenanceaction as soon as possible. No fire hazard exists. However, con-tinued usage of the system without repair will reduce the reliabil-ity of a number of components in the system. Therefore, onlycontinue to run the system in a tactically urgent situation. Thesystem may shut itself down at any time without warning follow-ing this failure.

7 Persistence Readout This display is intended for testing the IP-1168B front panel EMITTERPERSIS selector. The numbers in this box increment or decrement, de-pending on the rotation direction of the front panel control knobs. The spe-cific values are meaningless, but range from 0 to 15, and they rollover.With each click of the knob the displayed value will either increment ordecrement by one. If knob is rotated quickly, some displayed values maybe missed. The persistence of the display will not change.

8 Intensity Boxes (5 places) The five intensity boxes, located in the four corners and in the center ofthe screen, are intended for use during test and debug. The intensity ofthe boxes is initially set to maximum and is controlled by the SCALE Illu-mination control. The scale readout value equates to the intensity level,where 15 is maximum brightness and 00 is minimum brightness.




T.O. 1B-52H-1-13

Change 5 1-26G

IP1168B BIT 2 SCREEN DS

BIT 2 is intended to test as much of the hardwareas practical. All video generated during BIT 2 is in-ternal to the display. It does not test the receiversys tem cont rols: Audio Volume, Righ t/Left M a rkers ,A/B E xpa nsi on S elect, Video Test , a nd RF Test.

P a ss/Fa il determina tion is left up to the operat or ortechnician through observation of the BIT 2 screenand through operation of Master, Edge, Scale Illu-mination, and Persistence controls. If the patternshown below is displayed and is constantly updated, then BIT 2 is considered a PASS.

IP1168B BIT 2 Screen DS

Figure 1-10C



T.O. 1B-52H-1-13

1-26H Change 5

IP1168B Align Screen DS

Figure 1-10D



T.O. 1B-52H-1-13

Change 7 1-27

RADAR WARNING RECEIVER


The Ra da r Wa rning Receiver (RWR) is a n im provedversion over earlier RWR systems having an en-larged memory and the capability to detect addi-tional types a nd more sophisticated t hreat s. An up-

graded CM-479 processor, employing reprogram-mable Electrically Erasable Read Only Memory(EEROM) is installed. The EEROM processor canbe reprogrammed in the aircraft by a portableMK -2278/AP M-379 conver sion kit , sign a l processor,ASM-695 Program Loader Verifier (PLV)MemoryLoader Verifier (MLV). The receiver alerts the EWofficer, and in some instances the gunner, whenparticular threat radar signals are received. Thesystem is designed to protect the aircraft wit h mini-mum inflight ma nipulat ion of the controls. Tha t is,most modes of operation are selected before takeoffor before ta rget ingr ess. AN/ALQ-172(V)2 P R t ra ns-mitters blank the warning receiver to prevent dis-

play of associated transmitted signals. Audio ex-amination of received signals is accomplishedthrough tie-in with the interphone system. Self-testfeat ures provide comprehensive checks of th e wa rn-ing receiver on the ground or during flight. Compo-nent locations are shown in figure 1-11. RWR con-trols an d indicat ors are show n in figure 1-13.

Symbology

The symbology for the threat files in the RWR isshown in figure 1-13. These files are stored in theprocessor’s EEROM and can be reprogrammed inth e a ircra ft b y a porta ble MK -2278/APM -379 con-

version kit, signal processor, MLV. The three filescan be briefly described as follow s:

1. N or m a l F il e - Con t a ins la n d a n d w a t e r ba sedsurface-to-air missile, AAA systems, and all air-borne int erceptors.

2. Terra in File - Conta ins land based sur face-to-air missile systems, all airborne interceptors, andland based AAA rada rs.

3. Sea F i le - Conta ins wa ter based sur face-to-a i rmissile systems, w at er based AAA, an d a ll airborneinterceptors.

Scan Routines

The RWR provides both TWS a nd conical sca n a na lyses.

Antisymbol Splitting Routines

The RWR incorporates special routines to avoid

symbol split t ing. S ymbol split t ing is a n effect whichis due to aircraft rolls and banks. During thesema neuvers the sam e emitter is seen a t new relat iveangles by the antennas. Were it not for the anti-symbol split t ing routines, these changes in relat iveangles would cause multiple symbols for the sameemitter to appear as the aircraft maneuvers. TheRWR antisymbol splitting routines minimize suchdegrada tion. After a n emitter h as once been identified, the allowable angle variat ions during eachsuccessive intercept are widened. This allows thesystem to track an emitter through most aircraftmaneuvers.

Audio

The audio heard is a function of the environmentan d opera tor selection.

NORMAL AUD IO

In norma l operation, audio from a ll emitters whichare strong enough to be processed by the RWR wilbe heard. Sea rch rada rs (those of long pulse widths)will only be heard when S EARCH is selected on th eindicator control. The amplitude of each PRF wilbe proportional to the power received from the

threat. The AUDIO control on the indicator controcan be used to adjust the level of audio from maxi-mum to completely off.

DIAMOND AUDIO

Any time the operator wishes to hear audio fromany one of the displayed emitters, he can do so bypressing the HANDOFF button on the indicator-control. He will then hear only the audio from thesymbol which has the diamond - diamond audioAudio amplitude will be constant regardless ofrange to the threat. The AUDIO control on the indicator-control can be used to adjust diamond audio

from ma ximum t o completely off.



T.O. 1B-52H-1-13

1-28 Change 7

Diamond Routines

Two routines a re used in the RWR system.

FLOATING DIAMOND

In this mode, a diamond symbol is always on thehighest priority emitter displayed at that moment.

It f loats with the highest display priority in a pre-programmed order as the environment changes. Inthis mode, norma l aud io will be heard.

LATCHED DIAMOND

In this mode, a diamond symbol is latched on thedisplayed emitter selected by the operator. Whenlatched, the diamond will stay on that emitterregardless of the state of the environment, untilthat emitter is off the display, or the operatorselects another emitter, or emitter file. In thismode, diamond a udio will be heard .

OPERATIONAL MODES

Power On

The system is energized by pressing and releasingthe POWER button on the indicator-control.P OWER ON light should come on. A time-in periodof 9 seconds is allowed for azimuth indicator fila-ment warmup. During this t ime the indicator-con-trol lights may flash randomly. After t ime-in, thesystem will be in open mode, normal file, floatingdiamond, and normal audio. SEARCH will be offand ALTITUDE will be in the position it held when

the wa rning receiver wa s last used.

Auto-Restart

If at any t ime after turn-on the system suffers amomentary power loss or surge, the system willmomentarily turn itself off. When this occurs, thesystem will auto-restart within 15 seconds. Auto-re-start is followed by a 9 second time-in period. Fol-lowing a uto-restar t a nd t ime-in, the syst em will bein OPEN mode, normal file, f loating diamond, andnormal audio. The SEARCH button will be out(even if it were energized before the power shut-down) while ALTITUDE will be in the position it

held before the power loss.

Modes

Following initiation of system power and time-in,the MODE button indicates the system is in OPENmode. In this mode, up to 16 threats may be pro-cessed and displayed using appropriate alphanu-meric symbols. Azimuth angles are displayed rela-tive to aircraft heading. Distance from the aircraft

to the threat is displayed as a function of symboldisplacement from the center of the screen. Thisdista nce is norma lized in terms of the threat s lethalrange. Threats beyond the outer ring of the azi-muth indicator are beyond lethal range of theweapon associated with that threat . Symbols whichappear inside the outer ring are within lethalra nge. The th reat from wh ich aud io ca n/w ill beheard is emphasized by having a diamond placedaround it. The ALQ-155 Mode is controlled by theSens or Int egra tion ind icatorr cont rol. The ALQ-155mode is selected by pressing and releasing theMODE pushbutton. There may be a momentarydelay before the system enters the ALQ-155 mode.

Do not press the button again during this delay.This mode is indicated by illumination of the leg-end.

Handoff

In n ormal operat ion, the dia mond is float ing. It fol-lows a list of preprogrammed display priorit ies asthe environment changes. When the HANDOFFpushbutton is depressed, a ny collocated t argets ar eseparated and the diamond rotates through all dis-played threats in a preprogrammed order and con-tinues to do so as long a s th e pushbutton is held in.If the pushbutton is released, the diamond stays

latched to the threat symbol it currently enclosesregardless of other environment activity. When thediamond is latched, audio is diam ond audio and thediamond legend on the HANDOFF button comes on(the HANDOFF legend is illuminated wheneverpower is applied). As the diamond cycles throughthe displayed threat priorit ies, the operator willhear the audio of each emitter as the diamondencloses it. The diamond is returned to floatingmode by (1) momentarily pressing the HANDOFFbutton, (2) loss of the threat on which it waslatched, or (3) a change from one threat file toanother. If the HANDOFF button is pressed andheld, the dia mond will continue cycling th rough the

displayed emitters.



T.O. 1B-52H-1-13

Change 7 1-29

Target Separate

BEFORE DZ Momentarily separates symbolswhich are collocated on the azimuth indicator (butnot necessarily collocated on the ground) so that theoperator may clearly identify them. The symbolsare displaced along a 45° line whose direction isdetermined by the location of the display on the azi-

muth indicat or. The highest display priority threa twill alw ays be at the bottom of the dia gonal. Tar getseparate is obtained by depressing the T button,which will illuminate the ON legend (the lowerTGT SEP legend will go out). The symbols willremain separa ted for approximat ely 3 seconds aft errelease of the button. During the diamond HAND-OFF mode, no apparent movement of the diamondmay be observed. In this case, T may be depressedto determine if several collocated identical threatsare being displayed.

AFTER DZ

Tar get S epar at e toggles separa tion ofdisplayed symbols collocated on the azimuth indica-

tor(but not necessarily collocated on the ground) tomore clearly identify them. The symbols move ra-dially along the azimuth of threats. If the symbolsreach the indicat or edge, they will wrap a round theouter edge of the display in a clockwise direction.Ta rget separ a te is obta ined by depressing the Tbutton, which will illuminate the ON legend. Thelow er TG T SE P legend will go out.

Unknown

Unknown a ssumes tha t t he system has ident i f ied aradar whose characterist ics are not stored in theprocessors threat files or which ha s not tra nsmitt ed

enough parameters to make unambiguous identifi-cation possible. The processor will identify thisrada r a s a n unknown emitter. This will cause the Ulegend on the UNKNOWN button to flash at a 16Hz ra te. (The U NKNOWN legend is a lwa ys illumi-nated). By pushing and releasing the UNKNOWNbutton, a band coded symbol will be displayed atthe proper posit ion on the azimuth indicator andthe U legend will be on st eadily.

Search

BEFORE DZ The RWR is primarily a terminalthrea t wa rning system. Terminal threa ts can be

characterized by narrow pulsewidths; nonterminalthreats have long pulsewidths. Long pulsewidththreats can be added to the processing and displaycycle by pressing and releasing the SEARCH but-ton on the indicator-control. (The S legend willcome on; the SEARCH legend is etched on the but-ton). The system will remain in search until thebutton is again pressed or power is removed.Acquisit ion, GCI, and heightfinder radars will now

be displayed by the symbol S. All other existingthreats will remain displayed. It should be notedthat search radars can only be heard when thesearch button is depressed.

NOTE

The S emitt ers ha ve very low priority. Thus,

it is possible, particularly in the P RIORITYmode, that no S symbols will appear eventhough they exist in the environment, areilluminating the aircraft , and are heard innormal audio.

AFTER DZ System is pr imar i ly a terminal threatRWR a nd a ctivation of the SE ARCH further identifies less lethal threats. When depressed, this elec-tr ica l ly la tching switch a l lows C to J Ba nd Searchtype Radars to be displayed with an S symbol onthe azimuth indicator. All other symbols on the azi-muth indicat or are reta ined. The S legend is illuminated when the Search function is selected or dur

ing the lamp check phase of system test . Certainknown Search Radars have narrow PW and wil ldisplay even if this mode is not selected. Selectionof the Search mode does not significantly impactsystem response time, but could increase the number of symbols displayed on the azimuth indicatorIn a dense threat environment, the extra symbolsmay clutter the display. This button, when de-pressed during system test , activates the ExtendedB IT.

Altitude Priority

By use of the ALTITUDE pushbutton the operator

can change the display priority as the missionchanges. Tha t is, a t low alt itudes some AAA threatsand low alt itude missiles can be given display priority, wh ile at high a lt itudes, display priorit ies can beassigned to SAMs. This display priority change isaccomplished by pressing the ALTITUDE buttonHI ALT or LO ALT legend will be illuminatedwhichever w as selected last .

Excess Noise Strobes

As a maintenance assist , excess noise bars havebeen added to the scope display at 9, 12, and 3o’clock. During system test , a fourth bar may

appear at 6 o’clock. It has no meaning in the pres-ent RWR configuration. Clockwise from 9 o’clockthe presence of the bars indicates normal amplifierdetector noise in the low-mid-high-bands. The barswill be either off or on. Excess noise in any bandwill extinguish that band bar. When a thresholdbar is missing, but SYS TES T for th at band is goodthe detection range for tha t ba nd ha s been reducedbut the system is st ill usable with caut ion.



T.O. 1B-52H-1-13

1-30 Change 7

Cycle Timer

At the left-hand end of the 3 o’clock noise bar willappear a shor t ver t ica l bar tha t a l ternately pointsup and down. Ea ch movement of the ba r representsthe t ime used to input and process data from allthree frequency ba nds. The ra te a t w hich the cycletimer moves will vary with pulse density of the

threa t environment a nd the a mount of t ime neededby th e computer to process th e pulse da ta .

System Test

BEFORE DZ The frequency coverage provided bythe RWR is divided int o three ban ds for the purposeof improving signal to noise ratio. The three bandsare called 1, 2, and 3. During SYSTEM TEST bands1, 2, an d 3 symbols a re displayed in each qua dra ntindicating that the respective azimuth channel isoperational. There will also be a dot in each quad-rant and at the center of the azimuth indicator.Presence of the quadrant dots indicates that the

deflection circuitry in the signal processor is prop-erly aligned when th e dots a ppear on the outer ringof the azimuth indicat or. If t he four dots a re shiftedfrom the outer ring, the lethality envelope has beenshifted by that same amount. If one of the dots ismissing, tha t portion of the azimut h display is inop-erable. The center dot serves to locate the center ofthe a zimuth indicator in da rkened environments. Afifth dot appears at the bottom of the azimuth indi-cator during system test . I ts only function is toinform the operator that the system is an RWR.The sensitivity of the complete system (except theantennas and triplexers) is properly aligned whenthe quadrant dots are near the centers of the sym-

bols. If a dot appears outside of the diamond bymore tha n 1/8 inch, th e system r equires a lignment .The diamond will cycle clockwise to each symboland a different diamond audio will be heard. Anumber is printed at the top of the display indicat-ing the softwa re version being used. If the numera lis flashing, it indicates the computer checksuma nd/or memory tests fa iled. Illumina tion of the ONlegend on the SYS TEST button indicates that thechecksum and memory tests were successful.

BEFORE DZ Bands 1, 2, and 3 system tests areinitiated by pressing the SYS TEST pushbutton forat least 2 seconds. The SYS TEST legend is alwaysilluminated. The ON legend comes on if thememory self-test s a re successful. Total time of t hetest is 15 seconds. U pon init iat ion of SYS TE ST,every light on the indicator-control may come onbriefly. Those which do not come on should be

pressed. If they come on when pressed, the lamptest is successfully completed. During system test,the a ntenna s a re not disabled from t he processor sotha t a ny other ra dars in the environment which areilluminating the aircraft will be received and pro-cessed. Any PRF received within the system testlimits will be displayed by the appropriate bandsymbol and not by their real identifying symbology.Thus, band symbols not associated with a processordot may be displayed. Except wh en it is known tha tno other radars are in the area, these extra bandsymbols can be ignored.

AFTER DZ The self-test of the RWR) system con-

sists of two levels of reports, self test (short summa-ry) and extended self test (deta il required for ma in-tena nce). Self test provides quick sta tus of the sys-tem and check of the operator indicators throughtwo Azimuth indicator screen displays that com-plete in five seconds. Self test may be init iat ed andrepeated as often as necessary to verify proper op-era tion. Acceptable self-test results are indicat edby OK symbols. NOGO will be highlighted byflashing BAD symbols. Indicators will change aftertwo seconds to screen one indicating SYS SWVnumber, LAMPS ON and AUDIO ON then se-quence automa tically to screen t wo. Screen tw o pro-vides detailed software versions for OFP and EID

and a comprehensive summary of system status.An acceptable self-test will report all OK results.INIT reports the hardware logic init ialization re-sults. Fa ilure will be indicat ed by a flashing BADon Azimut h Indicat or. MEM ORY report s th e ra mand non-volatile memory checksum results. Duringself-test, memory locations are numericallychecked. Failure to pass check sum will be indi-cated by a flashing BAD on Azimuth Indicat or. DFreports Band 1,2,3 video and Amplifier Detectorstatus. Failure will be indicated by a flashing BADon Azimuth Indicator. Antennas and associatedcabling are not included in self test and must betested by ma intenance personnel using a ppropriate

test equipment.



T.O. 1B-52H-1-13

Change 7 1-31

Terrain File

For missions which are flown against only land-based threats, terrain file is used. This file isobtained by pressing and releasing SYS TEST fol-lowed by pressing and releasing T within one sec-ond. No legends w ill come on. A symbol will a ppearat the bottom of the azimuth indicator to denote

this mode of opera tion. When in terra in file, only 15emitter symbols can be displayed since the symbol

is a lwa ys present. The system can be returned tonormal file by momentarily pressing SYS TEST fol-low ed by pressing t he T butt on wit hin 1 second.

Sea File

To keep the num ber of ambiguit ies on the t hrea tdisplay to a minimum, the sea file was added foruse over w a ter. This file is obta ined by pressing a ndreleasing SYS TES T followed by w ithin 1second. Return to normal file is obtained by repeat-ing t his procedure. No legends w ill come on. A ship

symbol will appear a t t he bottom of the azimuth in-dicator to denote this mode. In this mode, only 15emitters can be displayed since the ship symbol isa lwa ys present .

GUNNER STATION

The following indications are provided at the gun-ner station. The RWR will update these indicationsas follows:

1. Sys tem Test - The four quadran t dot s w i l l bedisplayed and band 3 audio will simultaneously be

heard from all four quadrants during the entiresyst em test cycle. Durin g ba nd 3 portion of cycle, AIsymbols will be displayed at each of the four dotsThe entire system, except t he an tenna s a nd a mplifier-detectors triplexers, is properly aligned whenthe AI sym bol is with in 1/8 inch of the q ua dra ntdot. The RWR dot will be displayed.

2. Excess Noise Strobes - Strobes wil l be inver tedas are displays at this stat ion, so that the low-bandbar is at 3 o’clock, mid-band at 6 o’clock andhigh-band at 9 o’clock.

3. Threa t Symbols - The on ly threa t symbolswhich will be displayed are the airborne intercep

tors. The a nd symbols w ill be displa yedwhen in those modes.

4. Audio - Only band 3 audio w i l l be present a tthis stat ion.


The RWR system consists of four spiral antennas

for high-band coverage, an AM-6639 amplifier-detector for each ant enna w hich separa tes the RF signals into three bands (for signal-to-noise improvement), a CM-479 signal processor (employing repro-gramma ble EE ROM) which handles a l l threat ana lysis, an a zimuth indicator for a lphanumeric displayof the th rea t env ironm ent , an d C -11528/RWR ind icator-control unit which controls and displays themodes of the system. Threats are displayed on theRWR Azimuth Indicator. Sensor Integration (SI)display displays RWR threat and system status in-formation.



T.O. 1B-52H-1-13

1-32 Change 7

RWR Component Locations




T.O. 1B-52H-1-13

Change 9 1-33




T.O. 1B-52H-1-13

1-34 Change 7

CM-479 Signal Processor DZ

1 PROVIDES SIGNAL DATA INTERFACE TO CONTROL-INDICATOR2 PROVIDES POWER AND SIGNAL DATA INTERFACE TO AMPLIIER DETECTORS3 ELAPSED TIME INDICATOR4 NOT USED5 SPARE FUSE6 PROVIDES PRIMARY POWER AND SIGNAL DATA INTERFACE TO CONTROL-INDICATOR7 5 AMP FUSE (PRIMARY 115 VAC CIRCUIT)




T.O. 1B-52H-1-13

Change 7 1-35

ALR-46(V)-4 Signal Processor Less DZ

1 SPARE FUSE2 PROVIDES POWER AND SIGNAL DATA TO CONTROL-INDICATOR3 PROVIDES POWER AND SIGNAL DATA TO CONTROL-INDICATOR4 ELAPSED TIME INDICATOR5 PROVIDES POWER AND SIGNAL DATA TO CONTROL-INDICATOR6 5 AMP FUSE (115 VAC CIRCUIT)




T.O. 1B-52H-1-13

1-36 Change 7

RWR Controls and Indicators

CONTROL-INDICATOR

1 INTENSITY CONTROL2 CRT INDICATOR3 LAUNCH INDICATOR4 SYSTEM TEST BUTTON-INDICATOR5 AUDIO CONTROL6 DIMMING CONTROL7 PROCESSOR REPROGRAMMING INPUT8 POWER BUTTON-INDICATOR

9 ACTIVITY INDICATOR10 UNKNOWN BUTTON11 TARGET SEPARATION BUTTON-INDICATOR12 HANDOFF BUTTON-INDICATOR13 MODE BUTTON-INDICATOR14 ALTITUDE BUTTON-INDICATOR15 SEARCH BUTTON-INDICATOR




T.O. 1B-52H-1-13

Change 7 1-37

RWR Controls and Indicators (Cont)


1 Intensity Control Varies the intensity level of CRT.

2 CRT Indicator Displays threat symbols indicating relative bearing, relative signalstrength, and type of threat radar. The top of the EW officer’s indicatorrepresents 0° in azimuth relative to the aircraft heading, that is, a threatradar directly ahead of the aircraft would present a symbol at the 12o’clock position. However, the CRT indicator at the gunner’s station is ori-ented so that the top of the indicator represents 180° azimuth relative toaircraft heading. A symbol at the 12 o’clock position on the gunner’s indi-cator represents a threat directly aft of the aircraft. Relative signalstrength of a threat radar is indicated by its distance from the center of theindicator; that is, the weaker signals appear at the edge of the indicatorand the stronger signals, near the center. The type of threat radar is indi-cated by a characteristic symbol.

3 LAUNCH Indicator When the SAM threat guidance commands are received, the MISSILEand LAUNCH indicators light and a flashing circle is placed around theappropriate threat symbol. Pressing the button will generate a burst oflaunch audio over the ALR-46 Audio on the interphone.

4 System Test Button-Indicator Refer to T.O. 1B-52H-1-13-1

5 AUDIO Control Varies the level of audio received in the interphone system.

6 Dimming Control Varies the brightness of the legends on control-indicator.

7 Processor Reprogramming Input Input connection for Memory Loader Verifier (MLV) to reprogram thesignal processor.

8 POWER Button-Indicator Pressing and releasing this button provides power to the system. ON

POWER legend will illuminate.

9 ACTIVITY Indicator When SAM threat guidance commands are received, the MISSILE andACTIVITY indicators light and a circle is placed around the appropriatethreat symbol.

10 UNKNOWN Button Refer to T.O. 1B-52H-1-13-1

11 Target Separation Button-Indicator BEFORE When depressed, targets that are collocated on the CRTwill separate for easier identification and the ON legend will illuminate.The symbols will r emain separated as long as the button-indicator is helddepressed. When released the targets will remain separated for approxi-mately 3 seconds before returning to their original positions.

DZ

AFTER Target Separate toggles separation of displayed symbolscollocated on the azimuth indicator(but not necessarily collocated on theground) to more clearly identify them. The symbols move radially alongthe azimuth of threats. If the symbols reach the indicator edge, they willwrap around the outer edge of the display in a clockwise direction. Targetseparate is obtained by depressing the T button, which will illuminate theON legend. The lower TGT SEP legend will go out.

DZ




T.O. 1B-52H-1-13

1-38 Change 7

RWR Controls and Indicators (Cont)


12 HANDOFF Button-Indicator A diamond is superimposed over the highest priority threat on CRT dis-play. When the HANDOFF button is depressed, the diamond rotates

through all displayed threats in preprogrammed order of descendingpriority, and continues to do so as long as button is pressed. When buttonis released, diamond latches to threat symbols currently enclosedregardless of other environments. With diamond latched, diamond audiois heard and diamond symbol is illuminated on handoff button-indicator.Pressing the HANDOFF button also engages Target Separate.

13 MODE Button-Indicator Refer to T.O. 1B-52H-1-13-1

14 ALTITUDE Button-Indicator At high altitudes, display priority is given to AIs and high altitude SAM sys-tem when HI ALT legend is illuminated. By pressing and releasing ALTI-TUDE button-indicator, low altitude display priority can be given to someAAA and low altitude SAMs. LO ALT legend is then illuminated. PressingALTITUDE button again returns system to high altitude priority, the LOALT legend will go out and HI ALT again illuminates.

15 SEARCH Button-Indicator Refer to T.O. 1B-52H-1-13-1




T.O. 1B-52H-1-13

Change 7 1-39

RWR Controls and Indicators (Cont)DISPLAY SYMBOLOGY SCREEN 1 DZ

INDEX NUMBER TYPED NOTATION SUGGESTED PRONUNCIATION

1 WFF Wingform F

2 19 STAFF Nineteen Staff

3 A. A Dot

4 A: A Two Dot

5 A:. A Three Dot

6 U. U Dot

7 U: U Two Dot

8 U:. U Three Dot

9 -A- A Bar

10 C STAFF C Staff

11 -2- Two Bar

12 8 STAFF Eight Staff

13 WF Wingform

14 WFI Wingform One

15 AI AI

16 BOAT Boat




T.O. 1B-52H-1-13

1-40 Change 7

DISPLAY SYMBOLOGY SCREEN 2 DZ


17 L L

18 R R

19 15 STAFF Fifteen Staff20 -P- P Bar

21 1 One

22 2 Two

23 3 Three

24 4 Four

25 5 Five

26 6 Six

27 7 Seven

28 8 Eight

29 9 Nine30 C C

31 G G

32 H H




T.O. 1B-52H-1-13

Change 7 1-41

RWR Controls and Indicators (Cont)DISPLAY SYMBOLOGY SCREEN 3 DZ


33 19 Nineteen

34 T Training

35 ML Missile Launch

36 UML Uncorrelated Missile Launch

37 THRESHOLD BARS Threshold Bars

38 10 Ten

39 0 Zero

40 11 Eleven

41 12 Twelve

42 DIAMOND Diamond

43 BROKEN DIAMOND Broken Diamond

44 S Search

45 15 Fifteen




T.O. 1B-52H-1-13

1-42 Change 7

ALR-46(V)-4 Indications Less DZ

INITIATED BY PRESSING SYS TEST BUTTON FOR ONE SECOND. DIAMOND SYMBOL WILL CYCLE CLOCKWISE TOEACH TEST BAND SYMBOL(S). BAND 3 SYMBOL SHOWN WILL ALTERNATE WITH NUMERAL 3 AT EW POSITION. DOTAT BOTTOM OF DISPLAY DURING TEST DENOTES ALR-46(V)4 SYSTEM. TEST DURATION IS APPROXIMATELY 15SECONDS.

NOTE

• Not to scale.

• An electronic dot coincident with an etched dot at the CRT center is present during allmodes of operation in order to define the center of the display in a darkened environment.




T.O. 1B-52H-1-13

Change 7 1-42A

ALR-46(V)-4 Indications Less DZ (Cont)




T.O. 1B-52H-1-13

1-42B Change 7





T.O. 1B-52H-1-13

Change 7 1-42C





T.O. 1B-52H-1-13

1-42D Change 7

RWR Operational CheckoutSYSTEM SELF-TEST DZ

NOTE

During aut o self-test , a low frequency a udio tone last ing a pproximately

one second will be heard. System self-test must be performed to deter-mine if an actual fault exists in the system.

STEP RESULT

On RWR INDICATOR CONTROL UNIT (ICU)set audio control to mid-range.

On RWR INDICATOR CONTROL UNIT (ICU) POWER and all lower legends except LAUNCH and SEARCHilluminate steadily. Also some or all of theremaining legends may illuminate briefly.

After 10 second warm-up, observe-noise bars only appear onazimuth indicator.

After warm-up observe that all legends illuminate, exceptLAUNCH and ACTIVITY.

On RWR ICU depress and hold SYS TEST switchuntil noise bars disappear on azimuth indicator.

Azimuth Indicator flashes first screen showing version number,then advances to second screen.




T.O. 1B-52H-1-13

Change 7 1-42E

RWR Controls and Indicators (Cont)SYSTEM SELF-TEST DZ (Cont)

STEP RESULT

SYS TEST (Cont) Azimuth Indicator flashes second screen indicating OFP andEID version number.

Degraded performance will be indicated by flashing version

number or “OK” status shows “BAD”.

Azimuth Indicator returns to normal display (noise bars only).

For addit ional testing as determined, proceed to EXTENDED SELF-TEST

NOTE

• Extended (maintenance) self-test may be init iated and repeated asoften as necessa ry to verify proper opera tion. Operat ors shall be fam il-iar with self-test prior to test start .

• If failures are identified as a result of system self-test , ensure thatappropriate testing and maintenance is performed.

• There are t welve different screens in the m aint enance test display se-quence. A short press of the SE ARCH swit ch will hold display se-quence on th e screen of interest, a lterna ting w ith a dva nce/a bort screen.

• Since the system continues to receive radar signals during extendedself-test , ra dar s in the vicinity ma y cause erroneous results.




T.O. 1B-52H-1-13

1-42F Change 7

RWR Operational Checkout (Cont)EXTENDED SYSTEM SELF-TEST DZ

STEP RESULT

To begin Extended self test, Depress and release SYSTEST switch, then at second screen, depress and hold

SEARCH switch until “BEGINNING EXTENDED BIT”screen appears on Azimuth Indicator (then release).

RESULT 1: “BEGINNING EXTENDED BIT” screen appears onAzimuth Indicator

RESULT 2: After 5 seconds, screen appears announcingblanking of azimuth indicator while test are being performed.

RESULT 3: ML audio is heard.

RESULT 4: All THREAT WARNING panel lights except LOWcome on for 1 second then extinguish.

RESULT 5: Audio song is heard at low and varying level.




T.O. 1B-52H-1-13

Change 7 1-42G

RWR Operational Checkout (Cont)EXTENDED SYSTEM SELF-TEST DZ (Cont)

STEP RESULT

NOTE

Normal maintenance test indications are “000” or “OK” Faults will be highlighted by flashing symbol at 1 Hz rate.

RESULT 6: CM-479 A4 Status screen is displayed.

RESULT 7: ADVANCE/ABORT screen appears alternately withA4 status screen.

NOTE

A short press of the SEARCH switch will hold a screen of interest for indefinite display, alternating withADVANCE/ABORT screen. A second press of the SEARCH switch will continue the sequence of test results.

Depress and release SEARCH switch whileADVANCE/ABORT screen is being displayed.

RESULT 8: CM-479 CCA5 test status is displayed for 5seconds.




T.O. 1B-52H-1-13

1-42H Change 7

EXTENDED SYSTEM SELF-TEST DZ (Cont)

STEP RESULT



RESULT 11: System Memory test status is displayed for 5seconds.

RESULT 12: DF test status is displayed for 5 seconds. (“DF”and all numbers should be present and steady.)




T.O. 1B-52H-1-13

Change 7 1-42J

RWR Operational Checkout (Cont)EXTENDED SYSTEM SELF-TEST DZ (Cont)

STEP RESULT

RESULT 13: Software status is displayed for 5 seconds.

RESULT 14: END OF EXTENDED BIT screen is displayed for5 seconds.

RESULT 15: Azimuth indicator returns to normal display.(Noise BArs only).




T.O. 1B-52H-1-13

1-42K Change 7

RWR NORMAL OPERATION

Turn-On Procedure

Turn -on of the RWR will b e accomplished in a ccor-dan ce with t he basic flight ma nua ls.

Self-Test

BEFORE DZ The self-test provides a check of allsystem components except a ntenna s a nd a ssociatedcabling. This check will be performed during thecalibration and interference check. The EW officermay also accomplish the self-test to determineoperational capability any t ime during flight whensystem performa nce is questioned. As th e an tenna sare not disabled during self-test , environmentalradars are allowed to be received and processed.Any ra dar s received w ith P RI w ithin self-test limitswill be displayed with appropriate test band sym-bol, not t heir r eal identifyin g sy mbology. Therefore,addit ional symbols may be displayed during self-

test . The test is init iated by pressing the S YS TES Tpushbutton for approximately 1 second. When SYSTEST is pressed, every light on the control panelshould illuminate briefly, or blink, those which donot should be pressed after the test to verify thatthey light when pressed. When activated, the SYSTEST ON legend illuminates momentarily indicat-ing a valid memory self-test. The system sensitivityalignment is verified when the four test quadrantdots are within or touching the diamond signal.Posit ion of the quadrant dots also represents thelethal range of threat radars. If the four dots areshifted from the outer ring, the lethality envelopehas been shifted by that same amount. If the ver-sion number blinks, then the operational flight pro-gram or emitter identification dat a (OFP /EI D)memory has an error. If an R appears on the CRTthen an error in the processor ram memory hasbeen detected. Either of these errors could causeincorrect threat information to be displayed; there-fore, the processor should be repaired as soon aspossible. If an “M” appears on the CRT an error inthe loader software exists. This error will not affectoperation of the OFP but could a dversely a ffect thereprogram ming process.

AFTER DZ The self-test of the RWR system con-

sists of two levels of reports, self test (short summa-ry) and extended self test (detail required for main-

tena nce). Self test provides quick sta tus of the sys-tem and check of the operator indicators throughtwo Azimuth indicator screen displays that com-plete in five seconds. Self test may be init iat ed andrepeated as often as necessary to verify proper op-era tion. Acceptable self-test results are indicat edby OK symbols. NOGO will be highlighted byflashing BAD symbols. Indicators will change after

two seconds to screen one indicating SYS SWVnumber, LAMPS ON and AUDIO ON then se-quence automa tically to screen t wo. Screen tw o pro-vides detailed software versions for OFP and EIDand a comprehensive summary of system status.An acceptable self-test will report all OK results.INIT reports the hardware logic init ialization re-sults. Fa ilure will be indicat ed by a flashing BADon Azimut h Indicat or. MEM ORY report s th e ra mand non-volatile memory checksum results. Duringself-test, memory locations are numericallychecked. Failure to pass check sum will be indi-cated by a flashing BAD on Azimuth Indicator. DFreports Band 1,2,3 video and Amplifier Detector

status. Failure will be indicated by a flashing BADon Azimuth Indicat or. Antenna s an d associat edcabling are not included in self test and must betested by ma intenance personnel using a ppropriatetest equipment.

Extended Self-Test AFTER DZ

Extended self-test is interruptive of normal warn-ing function and takes in excess of two minutes tocomplete. A tota l of tw elve screens are display ed onthe Azimuth Indicator, summarizing specific detailsof system sta tus. Syst em self-test should be per-formed at the maintenance level to further define

self test faults reported by air crews. Init ia t ing ex-tended self test will assist maintenance personnelin fault isolation. Upon completion of self test, soft-ware will re-init ialize and Azimuth Indicator willreturn to normal display.

Cycle Timer

The cycle t imer is a short vertical bar at tached tothe left side of the 3 o’clock noise bar and alter-nately points either up or down. The cycle timerchanges position each time the RWR has processeddata from all frequency bands. Therefore, the rateat which the cycle timer moves is dependent on the

complexity of the environment that is being pro-cessed.



T.O. 1B-52H-1-13

Change 7 1-42L/(1-42M blank)

Threat Files

The multitude of threats in today’s environmentrequires the RWR to be very discriminating inorder to reduce ambiguity. Three expanded threatfiles are available to the operator.

(1) Normal file contains land and water-based sur-

face-to-air missile systems, all airborne intercep-tors, a nd la nd a nd sea -ba sed AAA syst ems. This fileis for use over land and in coastal areas. Normalfile is automatically selected when power is appliedto th e syst em. To return to norma l file followin goperator selection of terrain file, momentarily pressSYS TEST button followed by TGT SEP button oncont rol-indicat or wit hin 1 second.

(2) Terra in file cont a ins la nd-bas ed sur fa ce-to-a irmissile systems, airborne interceptor, and land-based: AAA radars and is for use over land areasonly. This file is obtained by pressing and releasingSYS TEST followed by pressing and releasing T(Ta rget S epara tion) button w ithin 1 second. No leg-ends will illumina te but a symbol “T” w ill appear atthe bottom of the a zimuth indicator a t t he EW offi-cer position. When in terrain file, only 15 emittersymbols will be displayed w ith t he “T” symbol.

(3) Sea file contains water-based surface-to-air mis-sile systems, all a irborne interceptors, a nd a ll ship-board AAA radars. This file is obtained by pressingand releasing SYS TEST followed by the ship sym-bol UNKNOWN button on the control-indicatorwithin 1 second. Only 15 emitter symbols may bedisplayed with the ship symbol which is always

present in th is file. To select sea file when in nor-mal or terrain files, momentarily press SYS TESTbutton followed by UNKNOWN button on control-indicator within 1 second.

AFTER DZ (4) Tra inin g file is to be u sed only fortra ining purposes as it conta ins only those emitterswhich are present a t tra ining sites and ra nges. Thisfile is selected by pressing and releasing SYS TESTand then pressing and releasing the MODE andHANDOFF buttons simultaneously within one (1)second. An “H ” will a ppear a t t he bott om of the a zimuth indicat or.

Audio Scheme

The following audio schemes are available as afunction of environment and the operators selectionof contr ol-indicat or pushbut tons:

(1) Normal proportional audio, (diamondpushbutton not latched), from all emitters whichare of sufficient strength to be processed, will beheard. The amplitude of each prf will be proportional to the power received from the threat. TheAUDIO control (figure 1-13) on the control-indica-tor can be used to a djust th e level of this a udio.

(2) Diamond audio, (diamond pushbutton latched)is provided to the crewmember who wishes to hearthe audio from only the symbol enclosed by the diamond by pressing the HANDOFF button on thecontrol-indicator. Diamond audio amplitude isconstant , regardless of range of threat . Diamondaudio level can be adjusted w ith t he AUD IO controon the control-indicator.

(3) La unch audio, a sy nthetic launch w ar ning toneis generated whenever an emitter guidance signagoes into a launch state. It consists of one burst of

approximately seven beeps in 1.5 seconds of a 1 kctone generat ed in the signa l processor.



BL



T.O. 1B-52H-1-13

Change 7 1-43

SENSOR INTEGRATION SYSTEM


The sensor integration (SI) system is designed toenhance the ra dar w arn ing display capability of theB-52 defensive avionics. The SI system collectsthrea t wa rning informa tion from the Rada r War n-

ing Receiver (RWR), threat warning and jamminginforma tion from th e ALQ-172(V) EC M syst em, a ndthreat w arning a nd jamming informat ion from theALQ-155(V) ECM system. The SI system then ana-lyzes the information from the respective systemsand optimizes the threat information on a multi-function display. The SI countermeasures set con-sists of one-half of the signal processor CM-465A/ALQ-155(V) (S I/P MS sig na l process or), onecont rol pa nel ID -2463/ALQ-155(V) (S I cont rol-indi-cat or), one mu ltif unct ion dis pla y I P -1362/ASQ-175(SI display), and ten data bus couplers for thedefensive avionics bus installed with the SI set . Inaddition, the CM-479 processor must be repro-

grammed for the SI function. Component locationsare shown in figure 1-15. Sensor Integration con-trols an d indicat ors are show n in figure 1-16.

The S I sy st em conta ins B uilt -In -Test (B IT) to pro-vide a status of the warning system. The SI systemals o provides t he th rea t d a ta to th e ALQ-155(V) forautomatic mode operation. Reprogramming of theSI /P MS processor can be accomplished w ith t heASM-695 Program Loader Verifier (PLV).

The SI countermeasures set uses both 28-volt dcand 115-volt, 400 Hz ac power from the aircraftbuses.


Control-Indicator ID-2463/ALQ-155(V)

The control-indicator (SI control) provides the con-trols and indicators for the operation and control ofthe S I s yst em. Ten sw itch/indicat ors, conta ininglamps for back-lighting front legends, and a lampintensity control are provided on the front panel ofthe SI control. Control is also provided for switch-ing operating power to the SI subsystem on or offan d for init iat ing self-test (B IT). S ee figure 1-16 forcont rol-indica tor push but ton/indi cat or legends .

Signal Processor CM-465A/ALQ-155(V)

The signal processor (SP) is the system controllerfor t he Countermeasures S et , operating under software control. It can integrate up to six control-indicat or/progra mm ers w ith each cont rol-indica tor/progra mmer ca pable of cont rolling tw o receiver/tr a nsmitt ers (RCVR/XMTRs). The S P interfa ces wit h t he

cont rol-indica tor /progr a mm er, RC VR/XMTR, RWRALQ-172(V) countermeasures set, and theID -2463/ALQ-155(V) cont rol-indica t or. Thr ea t inf ormation is available in video format on theIP -1362/ASQ-175 multif unct ion dis pla y (MFDwhich operates under the control of the SP. The SPis programmed to provide all control functions andimplement the basic instruction set for the Countermeasures S et . The SP consists of tw o functionasections. These sections are the ALQ-155(V) signaprocessor and the Sensor Integration (SI) signaprocessor.

The ALQ-155(V) ha lf of th e SI /P MS processor con

sists of a central processing unit (CPU) circuit cardassembly (CCA) and an ALQ-155 interface CCAThe CPU CCA contains a microprocessor circuitand an electrically erasable programmable readonly-memory (EEPROM). The microprocessor circuit operates on instructions contained in theEE P ROM to automat ically control the actions of theALQ-155(V) system. The ALQ-155 interface CCAprovides data routing circuits which interface thecont rol-indicat or/program mer t o th e sy stem receivers. The contr ol-indi cat or/progra mm er providescontrols and indications required for remote controof the system and controls for init iat ing the jamming program desired. The sensor integration half

of the SI /P MS pr ocessor consist s of thr ee CC As. TheCPU CCA acts upon instructions contained inEEPROM to create the information presented onthe multifunction display (MFD). The sensorintegration interface CCA provides data communications between the RWR system, theALQ-172(V) system, and the CPU CCA. If the sen-sor integra tion ha lf of the SI /P MS processor is n oopera tive, the dat a from t he RWR is pa ssed throughto the ALQ-155(V) half. The MFD driver CCA con-ta ins the circuits n ecessary to control the MF D.

If the Sensor Integration half of the signal proces-sor is not operative, the data from the RWR is

pass ed th rough t o the ALQ-155(V) ha lf of the sign aprocessor. The MFD driver CCA contains the circuits necessary to control the MFD.



T.O. 1B-52H-1-13

1-44 Change 7

SI Display IP-1362/ASQ-175

The SI display ha s a cathode ray tube (CRT) whichprovides the operator wit h t hreat jamming, a ngle ofarrival, frequency, and pulse repetit ion interval(PRI) information along with ALQ-155, RWR, andALQ-172 self test results. Brightness and contrastcontrols are provided to adjust the intensity of the

MFD CR T display. The SI display is shown in figure1-16.

The display may be divided in functional areas asfollows:

1. Th rea t D is pla y.

2. D i a m on d Th r ea t a n d Associ a t ed E m i t t erSection.

3. Indent i fy ing Sensors Sect ion . Appropria te Sys-tem box(es) illuminate to indicate which sensors are

receiving the t hreat enclosed in the H ANDOFF dia-mond.

4. RWR St at us Box.

5. AL Q-172 S t a t us B ox.

6. S I Mod e S ta t us B ox.

7. S ys tem Fa u lt S ta t us B ox.



T.O. 1B-52H-1-13

1-45

Sensor Integration Component Locations

1 SI PROCESSOR2 DATA BUS COUPLERS

Figure 1-15



T.O. 1B-52H-1-13

1-46

Sensor Integration Controls and Indicators

SI CONTROL PANEL

1 ALQ-155 MODE PUSHBUTTON-INDICATOR2 BIT STATUS PUSHBUTTON-INDICATOR3 HANDOFF PUSHBUTTON-INDICATOR

4 SEARCH/UNKNOWN PUSHBUTTON-INDICATOR5 BLANK6 AUDIO CONTROL7 DIMMING CONTROL8 SYSTEM POWER PUSHBUTTON-INDICATOR9 RESET PUSHBUTTON-INDICATOR

10 TARGET SEPARATION PUSHBUTTON-INDICATOR11 SYSTEM TEST PUSHBUTTON-INDICATOR12 PRIORITY MODE PUSHBUTTON-INDICATOR




T.O. 1B-52H-1-13

Change 7 1-47

SI MULTIFUNCTION DISPLAY (MFD)

13 THRESHOLD BARS (THREAT DISPLAY)14 JAM 155-172 (THREAT DISPLAY)15 AZIMUTH CIRCLE (THREAT DISPLAY)16 SPECIAL TECHNIQUE (THREAT DISPLAY)17 DIAMOND THREAT AND ASSOCIATED EMITTERS

18 IDENTIFYING SENSORS19 ALQ-172 STATUS BOX20 RWR STATUS BOX21 SI MODE AND SYSTEM FAULT BOXES




T.O. 1B-52H-1-13

1-48 Change 1

Sensor Integration Controls and Indicators (Cont)


SI CONTROL PANEL

1 ALQ-155 MODE Pushbutton-Indicator When pressed (upper legend ALQ-155 illuminated), allows diamondsymbol to be moved to only those threats detectable by the AN/ALQ-155system. When pressed (lower legend OPEN illuminated), allows dia-mond symbol to be moved to any displayed threat .

2 BIT STATUS Pushbutton-Indicator When pressed (upper legend STATUS illuminated), toggles MFD be-tween BIT status display and tactical display. When pressed (lower leg-end STATUS illuminated), provides continuously illuminated control leg-end.

3 HANDOFF Pushbutton-Indicator When pressed (upper legend diamond symbol il luminated), the diamondsymbol rotates through threats displayed on the MFD as determined bythe ALQ-155 Mode pushbutton-indicator. When pressed and quicklyreleased, causes diamond to move to the highest priority threat. When

pressed (lower legend HANDOFF illuminated) provides continuously illu-minated control legend.

4 SEARCH/UNKNOWN Pushbutton-Indicator

When pressed (upper legend SEARCH illuminated), allows concurrentdisplay of search and other type symbols on the MFD. When pressed(lower legend UNKNOWN illuminated), allows display of unknown sym-bols on the MFD. Any of four combinations of these modes is possible.

5 Blank

6 AUDIO Control Rotate CW to increase audio volume. Rotate CCW to decrease audio vol-ume

7 Dimming Control Rotate CW to increase legend light intensity. Rotate CCW to decrease

legend light intensity

8 SYSTEM POWER Pushbutton-Indicator

When pressed (both upper and lower POWER legend illuminated),115-volt AC operating power is applied to the Sl subsystem

9 RESET Pushbutton-Indicator SYMBOL (upper)When depressed, clears threat information and re-acquires current SI in-formation from sensors.

RESET (Lower)Provides continuously illuminated control legend.

10 Target Separation Pushbutton-Indicator

When pressed (upper legend SEP DEF illuminated) emitters displayedon MFD are compressed to their original location (target separationdefeated). When released, operates in target separate mode. Targets

are separated so that individual symbols do not overlap and display.Lower legend, TGT SEP is illuminated regardless of mode.

11 System Test Pushbutton-Indicator When pressed (upper legend ON illuminated), toggles built-in-test (BIT)BIT may be stopped by pressing button during test. When pressed (lowerlegend SYS TEST illuminated) provides continuously illuminated controllegend.




T.O. 1B-52H-1-13

Change 7 1-49


SI MULTIFUNCTION DISPLAY (MFD)

12 PRIORITY MODE Pushbutton-Indicator

When pressed (upper legend PRIORITY illuminated), MFD displays fivesymbols of highest priority for 30 seconds. The display may be stoppedby pressing button during the 30 second period. When pressed (lowerlegend PRIORITY illuminated) provides continuously illuminated controllegend.

13 Threshold Bars (Threat Display) Each of the three bars represents a frequency band received by the RWRsystem. When present, the bar indicates that noise in the RWR amplifier-detectors is below a predetermined limit. If a bar is not present, the RWRsystem has detected excess noise in the associated band and is operat-ing at a reduced threshold level.

14 JAM 155-172 (Threat Display) Indicates that the ALQ-155 and ALQ-172 jamming systems are counter-ing the same threat. This legend is displayed with an inverted video back-

ground.

15 Azimuth Circle (Threat Display) Provides angle of arrival information for threats sensed by EW sensors.Top of display is current aircraft heading. Threat symbology is similar tothat used in standard radar warning receiver systems. Threats being

jammed are presented on a light background (inverted video).

16 SPECIAL TECHNIQUE(Threat Display)

When ALQ-172 is countering a threat using special technique, an indica-tion of this jamming appears in this area. The threat symbol jamming indi-cation (inverted video background) associated with this techniqueflashes on and off. This legend is displayed with an inverted video back-ground.

17 Diamond Threat and AssociatedEmitters

This section displays emitter information for the threat enclosed in theHANDOFF diamond. Information for four associated emitters can be dis-played. When an emitter is being countered by the ALQ-155 or ALQ-172system, the information is presented on a light background (invertedvideo). Emitter types are identified by the following symbols:

Type Symbol

TTR No symbol

Missile Activity,Missile Launch, orMissile Guidance (Circle)

Acquisition (Square)

FREQ is a display of emitter frequency.

SCAN is the scan type of the emitter.

PRF is a display of emitter PRF. PRF also displays CW or CYCLER forappropriate emitters.




T.O. 1B-52H-1-13

1-50 Change 7

Sensor Integration Controls and Indicators (Cont)


SI MULTIFUNCTION DISPLAY (MFD) (Cont)

18 Identifying Sensors Boxes illuminate to indicate which sensors are receiving the threatenclosed in the HANDOFF diamond.

19 ALQ-172 Status Box

PR O or S Indicates the operational status of the ALQ-172 pulse radar systemFORE and AFT (F and A).

O - OperationalS - Standby

PD O or S Indicates the operational status of the ALQ-172 pulse Doppler systemFORE and AFT (F and A).

O - OperationalS - Standby

HIGH or LOW Indicates the ALQ-172 system altitude mode.

T or W Indicates the ALQ-172 mode.

T - Training modeW - War mode

See ALQ-172, this section, for explanation of ALQ-172 modes.

20 RWR Status Box RWR operational mode:

T Terrain Mode

N, or N Normal mode- Sea mode

See ALR-46, this section, for explanation of ALR-46 modes.

OPEN or 155 Indicates the state of the ALQ-155 mode pushbutton-indicator.

HIGH or LOWSU

Indicates the RWR altitude mode.Indicates the RWR Search mode is enabled.Indicates the RWR Unknown mode is enabled.




T.O. 1B-52H-1-13

Change 7 1-51


21 SI Mode and System Fault Boxes

OPEN or 155 Indicates the state of the SI ALQ-155 mode pushbutton-indicator.

TOP 5 Indicates that the PRIORITY mode pushbutton has been depressed.

S Indicates that the SI Search mode is selected.

U Indicates that the SI Unknown mode is selected.

SI FAULT Indicates that a built-in-test (BIT) failure is detected in the SI subsystem.

46 FAULT Indicates that a BIT failure is detected in the RWR system.

155 FAULT Indicates that a BIT failure is detected in the ALQ-155 system.

172 F FAULT Indicates that a BIT failure is detected in the ALQ-172 FORE system orthat the MIL-STD-1553 data bus is inoperative.

172A FAULT Indicates that a BIT failure is detected in the ALQ-172 AFT system or thatthe MIL-STD-1553 data bus in operative.




T.O. 1B-52H-1-13

1-52

Sensor Integration BIT Displays

SI MFD INITIATED BIT DISPLAY

SI MFD OPERATIONAL BIT STATUS DISPLAY

Figure 1-17



T.O. 1B-52H-1-13


NORMAL OPERATION

The SI system collects threat warning data fromthe RWR and threat warning data and jamminginformation from both the ALQ-172(V) and theALQ-155(V). Therefore, these systems must befunctiona l to interact w ith the SI system for normaloperat ion. To operat e the SI syst em, ensure th e SI

control and SI display circuit breakers located onthe A177 ECM circuit breaker panel are in. The SIcontrol panel contains pushbutton-indicators andcontrol knobs for SI operation. The audio controlknob should be set to minim um volume for check ofthe missile launch tone. Operational displays areshown in figure 1-16. P ress and release the SYS-TEM POWER button-indicator. Lamps on the SI

control panel illuminate; then, after 20 secondsoperat ional da ta and sta tus appears on the SIMFD. P ress an d release the SYS TES T button-indicator. Ensure the missile launch tone is audible forapproximately 1.5 seconds and verify the initiatedBIT display (figure 1-17) appears on the SI MFDSet the audio control knob to mid range. Furtheraudio adjustment may be necessary as the mission

dictates. Press and release the SYS TEST buttonindicator again to return the SI MFD operationadata and sta tus presenta t ion. Press and release theB IT STATU S butt on-indicat or. The operat ional B ITsta tus appears on the SI MFD. Press and releasethe B IT STATU S bu tt on-indicat or aga in to retu rnto the SI MFD to the opera t ional da ta and sta tuspresentation.



BL



T.O. 1B-52H-1-13

Change 7 1-55

BLANKING SYSTEM


B lanking t o the EC M receiving systems is providedby the OAS Radar Set Group (Radar Set). Theblan king pulses cut off th e receivers t o avoid receiv-

ing transmitted signals from the Radar Set . Thisavoids the possibility of confusing the Radar Settransmitted signals with those of an enemy radarunit .

Radar Set blanking signals are supplied throughthe blanking amplifier to the ALR-20A system, orto the RWR, a nd t errain computer t hrough the for-

w a rd CV-3809/ALQ-172(V) sign a l d a ta convert erand through the forward and aft ALQ-172(V)2 system. ALQ-172(V)2 forward PR transmitter blanking

is supplied to the radar receiver-transmitterth rough t he forwa rd C V-3809/ ALQ-172(V) sign adata converter. ALQ-172(V)2 aft PR transmitterblanking is supplied to the RWR through the aftCV-3809/ALQ-172(V) sig na l d a t a conver ter. Theblanking system equipment locat ion is shown in figure 1-18.



T.O. 1B-52H-1-13

1-56 Change 7

Equipment Locations

1 R-2247/ALQ-172(V) RECEIVER (SYSTEM NO. 16)2 RWR SIGNAL PROCESSOR3 CV-3809/ALQ-172(V) SIGNAL DATA CONVERTER

(SYSTEM 16)4 C-9449/ALR-20A RECEIVER CONTROL5 BLANKING AMPLIFIER6 BLANKING CABLE STOWAGE RECEPTACLE7 BLANKING MODULE (SYSTEM NO. 16)8 BLANKING MODULE (SYSTEM NO. 15)

9 CV-3809/ALQ-172(V) SIGNAL DATA CONVERTER(SYSTEM 15)

10 R-2247/ALQ-172(V) RECEIVER (SYSTEM NO. 15)

Figure 1-18



T.O. 1B-52H-1-13

1-57

TRANSMITTER SYSTEMS

AN/ ALT-16A 1-57

AN/ ALT-28(V) JAMMING TRANSMITTER 1-57

AN/ ALT-32A JAMMING TRANSMITTER 1-57


AN/ALT-16A

Tw o AN/ALT-16A tr a nsm itt er set s a re in tegr a tedw ith th e AN/ALQ-122 to ma ke up t he AN/ALQ-122/AN/ALT-16A count ermea su res s ys t em(see ALQ -122/AN/ALT-16A COU NTER ME ASU RE SSYSTEM, under RE CE IVER TRANSMI TTER SYS-TEMS, this section).

AN/ALT-28(V) JAMMING TRANSMITTER

The AN/ALT-28(V) ja mm ing t ra ns mi t t er sy st em

(used as alternate mission equipment to the AN/ALQ-155(V) power ma na gement syst em) is capa bleof providing various types of RF power output cov-ering a w ide frequency range by using interchange-able transmitter groups. (see ALQ-155(V) POWERMANAGEMENT SYSTEM under RECEIVER-TRANSMITTER SYSTEMS, this section).

Each transmitter group has a specific frequencyrange and power output which is designated as aba nd . E a ch s ys t em consis t s of a T-1150/ALT-28(V)tr a ns mi tt er, HD -766A/ALT-28(V) du a l elect roni cequipment liquid cooler, a nt enna syst em, a nd 1/2 ofa C-10130/ALQ-155(V) cont rol ind ica t or/progr a m-

mer. Locat ion of syst em components is sh own in fig-ure 1-29. The transmitter contains an M-type back-ward wave oscillator (BWO) and most of the func-tional circuits of the syst em. The tra nsmitt er hous-ing is a magnesium casting which provides mount-ing for the B WO, and liquid an d air-cooled cavit iesin which modules containing the power supplies,regulators, and modulators associated with theBWO are mounted. The liquid cooler comprises areservoir for cooling fluid, a single motor which

drives both a pump and fan, a cooling coil, and cir-cuitry for control of the system timing periods. TheAN/ALQ-155(V) cont rol-indi ca t or provi des con tr olsand indications required for remote control of thesystem. Circuitry from the control-indicator to thetra nsmitt er passes th rough the liquid cooler providing interlock protection. The programmer providescontrols for init iat ing the jamming programdes ir ed. The C-9525/ALT-28(V) a nt enna selectpanel drives a waveguide switch for systems No. 1and 2 to transfer electromagnetic energy from thetransmitter to either the forward or omni antennasCircuits within the pan el control dc voltages used t o

disable the transmitters during waveguide switch-ing t ime.

AN/ALT-32A JAMMING TRANSMITTER

The AN/ALT-32A jam min g t ra nsm itt er is a n a irborne countermeasures t ran smitt er capable of jammin g en emy ra da r. The complet e AN/ALT-32A sy stem includes low-band and high-band sets. Onelow-band set is installed in position No. 20 and twohigh-band sets are installed in positions No. 11 and12. The low -ba nd set is compr ised of a T-1086AALT-32A ra dio t ra ns mi t t er, T-1087/ALT-32A ra diotr a nsm itt er, P P -1087/ALT-32 power supply, a nd aC-7721/ALT-32A contr ol in dica t or. The h igh -ba ndset is compri sed of a T-1087/ALT-32A ra dio t ra nsmit t er, P P -1087/ALT-32 power su pply, a nd aC-7722/ALT-32A cont rol-indica t or. All opera t ingcontrols and indicators are located on the frontpanel of the control-indicators. Component loca-tions a re s how n in figur e 1-19. ALT-32A controlsan d indicat ors are sh own in figure 1-20.



T.O. 1B-52H-1-13

1-58 Change 9

ALT-32A Component Locations




T.O. 1B-52H-1-13

1-59




T.O. 1B-52H-1-13

1-60

ALT-32A Operating Controls and Indicators

1 SPOT A FREQUENCY CONTROL2 SPOT A BANDWIDTH CONTROL3 SPOT B BANDWIDTH CONTROL4 TRANSMIT CHANNEL SELECTOR5 RADIATE LIGHT

6 FAULT LIGHT7 STANDBY LIGHT8 WARMUP LIGHT9 SPOT B FREQUENCY CONTROL




T.O. 1B-52H-1-13

1-61/(1-62 blank)


1 Spot A Frequency Control Adjusts the center frequency of spot A transmitted signal.

2 Spot A Bandwidth Control Adjusts the bandwidth of the center frequency of spot A transmittedsignal.

3 Spot B Bandwidth Control Adjusts the bandwidth of the center frequency of spot B transmittedsignal.

4 TRANSMIT Channel Selector A rotary selector controls the application of power to the equipment andselects the mode of operation. STBY position provides power to theblower circuits and to the standby light. SPOT A position energizes thespot A noise circuits and applies operating power to that portion of thetransmitter. SPOT B position energizes the spot B noise circuits andapplies operating power to that portion of the transmitter. SPOT A & Bposition simultaneously energizes both spot A and spot B noise circuitsand applies operating power to that portion of the transmitter. BARRAGE

1, 2, 3 and 4 deenergizes the spot noise circuits, activates the barragenoise circuits, and applies operating power to the transmitter. Barragenoise will be radiated in the channelized bandwidth determined by thenumerical position selected.

NOTE

If transmitter is placed in A, B, or A & B Modes with Spot (A orB) frequency control knob CCW, the transmitter may not comeinto operation. Move the appropriate (Spot A or B) frequencycontrol knob clockwise until the transmitter comes into opera-tion. The frequency control knob may then be returned to theCCW position if desired.

5 RADIATE Light A green light,when illuminated, indicates that the transmitter is radiatingRF energy.

6 FAULT Light A white light, when illuminated, indicates the failure of the 3–phase acinput, or a reduction of the inputs by 50% or more. When illuminated, theprimary power circuit is deenergized preventing operation of blowers.

7 STANDBY Light An amber light, when illuminated, indicates that the transmit channelselector is in STANDBY position. The 60-second warmup is complete,and the delay control relay is energized.

8 WARMUP Light (Not functional)

9 Spot B Frequency Control Adjusts the center frequency of spot B transmitted signal.

10 Shaft Locks A shaft lock, mounted concentrically with each frequency control andeach bandwidth control, locks the control in place. Clockwise rotation ofthe lock locks the control, while counterclockwise rotation unlocks thecontrol.




BL



T.O. 1B-52H-1-13

Change 9 1-63

RECEIVER-TRANSMITTER SYSTEMS

AN/ALQ-172 COUNTERMEASURES SET 1-63


CONTROL DISPLAY UNIT (CDU) 1-65

AN/ALQ-172 AUXILIARY PANEL 1-72G

CONTROL DISPLAY UNIT (CDU) OPERATION 1-72J

CDU SYMBOL SET 1-72V

NORMAL OPERATION 1-73CDU NORMAL OPERATION 1-74

KEYBOARD COMMANDS 1-74D

AN/ALQ-122/AN/ALT-16A COUNTERMEASURES SYSTEM 1-75



AN/ALQ-153(V) TAIL WARNING SYSTEM 1-83




AN/ALQ-155(V) POWER MANAGEMENT SYSTEM 1-92




AN/ALQ-172(V)2 COUNTERMEASURES SET


The AN/ALQ-172(V)2 coun t erm ea su res s et is a ful -ly automatic receiving and transmitt ing ECM set .The set provides the aircraft with protectiona ga inst th rea t r a da rs. The AN/ALQ-172(V)2 setconsists of tw o systems, designat ed systems 15 (aft )

and 16 (fwd). Each system includes one counter-mea su res receiver R-2247/ALQ-172(V) (receiver)(LR U -1), one count ermea sur es tra nsm itt er T-1470/ALQ-172(V) (PR transmitter) (LRU-2), one counter-mea su res t ra ns mit t er T-1476/ALQ-172(V) (P D /CWtransmitter) (LRU-4), one countermeasures conver-ter C V-3773/ALQ-172(V)2 (conver t er ) (LRU -7), tw opha sed a rr a y a nt enna s AS-4078/ALQ-172(V)2 (an-tenna) (LRU-8), one quadrant switch SA-2396/ALQ-172(V)2 (switch) (LRU-9), one countermea-su res s ign a l cont roller C-11271/ALQ-172(V) (PD /CW processor) (LRU -10), and one signal data con-ver ter CV-3809/ALQ-172(V). The f orw a rd sy st ema lso cont a ins one t ra ns mi t ter T-1471/ALQ-172(V)2

(LRU-12) (See figures 1-22 and 1-23). Additionallythe forward and aft systems each utilize an omnireceive antenna E6329 (FWD) and E6337 (AFT).The forward system equipment (system 16) is in-stalled in the forward radome. The aft systemequipment (system 15) is installed in the tail sec-tion. See figure 1-21.

Less DT The systems sh a re a common cont rol-indica tor C-11213/ALQ-172(V) (cont rol-indica tor(LRU -5) a nd cont rol-monit or C -11270/ALQ-172(V(control-monitor) (LRU-6). Both controls are installed at the EW officer stat ion.

DT The systems share a common Control-DisplayU ni t (CD U ) C -12615/ALQ-172(V) (LRU -21). Thi scontrol is installed at the EW officer station. TheC-12615/ALQ-172(V) Cont rol-Displa y U nit (CD U(LRU -21) provides control a nd display functions forthe two ALQ-172(V)2 systems. In addition it provides communication and threat hand off betweenthe two ALQ-172 systems. The CDU allows forALQ-172(V) memory loading and reading via aPCMCIA card (Personal Computer Memory CardInterna tional Associat ion) inserted in the front pa nel. The PCMCIA card is the approximate dimen-sions of a credit card, but is thicker. Only Wing EWofficer approved PCMCIA cards may be used with

the CDU. The function of the PCMCIA interface isto a llow for da ta loading of the ALQ-172(V)2 syst emincluding CDU, data recording and playback. AnAuxiliary Panel is also installed which includesswitches for system power an d H IG H/LOW alt itudeoverride. Both controls are installed at the EW offi-cer stat ion.



T.O. 1B-52H-1-13

1-64 Change 9

E a ch AN/ALQ-172(V)2 sys tem compr ises a P ulseRadar (PR) and a Pulse Doppler (PD) subsystem.The P R subsyst em detects threa ts from convention-al pulse radar fire control systems and applies ap-propriate countermeasures. The PD subsystem rec-ognizes threat s from P D types of fire control rad arsand applies appropriate countermeasures. All oper-ation is automatic including the reception and rec-

ognition of threat s a nd the programming a nd a ppli-cation of suitable countermeasures. The set con-ta ins comprehensive B uilt-In-Test (B IT) feat ures.These features test overall functions of the systemLRUs from the antenna inputs to the control-indi-cators. For flight line maintena nce, the set B IT pro-vides the means of isolating most failures to a par-ticular LRU . B IT is init iat ed by pressing the TES Tbutton on DT t he C-12615/ALQ-172(V) Cont rol D is-play Unit or Less DT the C -11213/ALQ -172(V) con-trol-indicator. Programmed tests are then con-ducted aut omatically. These results a re indicated t othe operator on the DT C-12615/ALQ -172(V) Con-trol Display Unit or Less DT l ights on the

C-11213/ALQ-172(V) cont rol-indica tor a nd dis pla yson t he C-11270/ALQ-172(V) cont rol-monit or.

DT The CDU receives ALQ-172 bit, system statusand situation information via an internal ALQ-172local 1553B Data Bus (figure 1-20A). Also, the for-ward and aft receivers are connected to the SensorIntegration (SI) countermeasures set through theDefensive System 1553B Data Bus. This enablesthreat and system status information to be dis-played on the SI display.

Less DT The forward and aft R-2247 receivers areinterconnected with the SI countermeasures set

through da ta bus couplers. This enables threat an dsystem sta tus informat ion to be displayed on the SIdisplay.

Aircraft Interface

The AN/ALQ-172(V)2 a ft P R r eceiver i s bla nkedfrom t he B -52 Ra da r S et; th e AN/ALQ-172(V)2 for-wa rd P R receiver is blanked only by the B-52 Ra darSet. This avoids electromagnetic interference to theP R subsystem. These blan king signals a re routed tothe PR receivers through the blanking modules.Blanking is provided from both forward and aft PRtr a nsm itt ers to th e AN/ALR-46 receiver, and from

the forwa rd P R tra nsmit ter to the B-52 Rada r Set .This blanking signal is routed to the receiverth roug h th e CV-3809/ALQ-172(V) sig na l da ta con-verters. Forward and aft systems are intercon-nected w ith t he AN/ALQ-155 power ma na gemen tsystem. This provides compatibility between theAN/ALQ-155 ba nd 12 tra nsm itt ers a nd the AN/

ALQ-172(V)2 P D subsys tem. An R F filter in th e for-w a rd AN/ALQ-172(V)2 PR subs yst em pr ovides com-pat ibility bet ween the AN/ALQ-155 ba nd 12 tra ns-mi t ter s/receivers a nd t he AN/ALQ-172(V)2 P R su b-system.

Pressurized waveguides are used for all the trans-mitt ing RF transmission lines and for the

waveguide that connects the transmitter output tothe RF switch input. Pressurization for thew a veguide is s upplied fr om t wo P N 2830400-3 com-pressors , one forwa rd a nd one a ft. Tw o SA-377/ASQpressure switches a re insta lled w ith ea ch compres-sor. The high pressure sw itch opera tes t he compres-sor when the waveguide pressurization falls below 30.5 inches of Hg, while the low pressure switchoperates the waveguide low pressure warninglights when waveguide pressure falls below 24(±0.5) inches of Hg. The forwa rd a ir compressor a lsosupplies pressu re to t he AN/ALQ-155(V) syst ems 1an d 2 wa veguides.

Two w a veguide low pressure light s, one for the for-ward and one for the aft system, are located on theALQ-172 waveguide low pressure warning andblanking panel (figure 1-24). Illumination of eitherlight indicates insufficient pressure in the applica-ble system for proper operation and the pump inthat system will continue to operate until shut offby pulling th e ass ociat ed pump circuit brea ker(s) lo-cated on the Overhead A117 DECM CB Panel.When either waveguide low pressure light illumi-na tes r efer to th e AN/ALQ-172 Ma lfun ction Ana ly-sis Checklist in Section II I of this ma nua l.

The forward air compressor supplies pressure for

both th e AN/ALQ-172(V)2 forwa rd a nd th e th e AN/ALQ-155(V) syst ems 1 a nd 2 w a veguide runs. P res-sure tubing from the forward compressor connectsdirect ly t o th e AN/ALQ-155(V) syst em 1 a nd 2 omniantenna waveguide runs. This configuration pro-vides complete pressurization for systems 1 and 2omni antenna , forward antenna , and the t ransmit-ter w a veguide runs. Wa veguide pressure for th eAN/ALQ-172(V)2 forw a rd sys tem is s upplied b y apressu re tu be run nin g from t he AN/ALQ-155 sys -tem 2 forwa rd a ntenna w aveguide.

Tw o 5-a mp 28 volt-dc circuit br ea kers on th e DE CMcircuit breaker panel labeled SYS 15 PRE SS P UMP

and SYS 16 PRE SS P UMP supply control voltagesto high pressure sw itches. The sw itches provide on-off control for the compressors. A 5-amp 28 volt-dccircuit breaker on the DECM circuit breaker panellabeled PRESS PUMP INDICATOR supplies con-trol voltage t o the wa veguide low pressure wa rninglight(s) and low pressure switches.



T.O. 1B-52H-1-13

Change 9 1-65

DT CONTROL DISPLAY UNIT (CDU)

The AN/ALQ-172(V) LR U -21 Cont rol D ispl a y U ni t(CD U ) C-12615/ALQ-172(V) repla ces L RU -5 a ndLRU-6. The CDU performs the Operator Interface,the ha nd off of threat signals between systems, andthe communication between the systems and CDUvia th e ALQ-172 local 1553 B us; plus t he capa bility

to load t he EID, OFP and E CM da ta via the 1553Bdata bus through the CDU, using a PCMCIA cardas a stora ge/tra nsport medium. The CD U a lso pro-vides ma intenan ce diagn ostics capability by report-ing the results of the 172 systems self test. Detaileddiagnostics files can also be selected to assist withfau lt isolation. The C DU a lso provides record/play-back capability a s w ell as display of OAS NAV data .

The CD U performs the follow ing ma jor functions:

• Power and control of ALQ-172 FWD and AFTLRUs.

• Threat situation display.

• System status display.

• Signal handoff.

• Overt empera tu re report/override.

• Self test results display.

• Self test details and fault diagnostics.

• OFP /E ID /E CM file da ta loading.

• Configuration identification.

• Recording and playback.

• OAS NAV dat a display.

The CDU is capable of controlling up to threeALQ-172 syst ems in either t he F a il/Sa fe or CD U

GO mode of operation. It consists of three modules(figure 1-20B ); a Sw itch/Displa y m odule wit h aPCMCIA module; an Electronics module; and theP ersona lity module.

The CDU controls two ALQ-172 systems, config-ured as FWD and AFT systems. The CDU has twomodes, the fail-safe interface mode and the CDUGO mode. See CONTROL DISPLAY UNIT (CDU)OPERATION this section for discussion of the twomodes.

Figure 1-23A shows th e front view of the CD U . TheCDU conta ins a Liquid Crysta l Display (LCD),

sw itches for power on, test initia te, an d sta ndby/op-

erate enable, and two sets of four software pro-grammable switches. The programmable switchesare arranged along the bottom for display controa nd down the righ t side for syst em contr ol. A rockerswitch var ies the intensity of the LCD display. TheCDU has a carry ing handle tha t is used to assistwith installat ion, removal, and transportation ofthe CDU. The handle should always be stowed and

locked in the upright position after installation.

NOTE

The handle must always be in the stowedand locked (upright position) inflight.

The Displa y module provides th e operat or interfa ceIt contains three single function switches, onededicated indicator, 8 programmable switches, aP CMC IA interface, a keyboar d connector, a a mbienlight sensor and dimming control, and a 6 by 8Color Active Matrix Liquid Crystal Display paneincorpora tin g a Touch Screen. The necessa ry

electronics and lighting for the active matrix LCDand the programmable switches are contained inthis module.

The electronics module contains the processor andcommunications electronics to communicate withboth ALQ-172 systems and the display module andprocess and display the data reported. It alsocontains the power supplies for all functions. Thismodule stores the software (in solid state memoryto run the CDU GO mode of operation. The CDUcan be booted with a PCMCIA card installedbypassing the installed software stored in theelectronics unit. This is used for loading ALQ-172

system files (EID, OFP, ECM) into the 172 systemsfor maintenance troubleshooting, as well as forupdating the software stored in the CDUelectronics unit. (i.e. if the user requires loading anew version of CDU software it can be loaded froma preprogram med P CMC IA car d).

The personality module contains the interface forthree ALQ-172 systems and the Aircraft(Connectors) and the relay logic for fail safeoperation. The present aircraft design uses only twosystems. The third system is for future growthThis logic, similar to the LRU-5 logic circuitsprovides for operation of the ALQ-172 systems in

the event of a CD U fa ilure.



T.O. 1B-52H-1-13

1-66 Change 9

ALQ-172 Component Block Diagram DT

Figure 1-20A

The CDU provides a continuous threat status dis-play of the type of threat (PR, PD, CW), direction ofthrea t (relat ive to aircraft h eading), the syst em’s re-sponse to the threat (jam indictions) and threatsymbology ba sed upon th e threat identification andmode i.e. search, track, illuminate or guidance.Threat symbols are displayed at the relative bear-ing as reported by the ALQ-172 systems and at arelative range from the center or the area depend-ing on their received signal strength. The display isa bulls eye consisting of two concentric circles. Sig-na ls detected, but below jam t hreshold, will be dis-played in red in the outer ring of the bulls eye. Asthe signal strength increases, the symbol will bepositioned closer to the inner ring. When the signalis above jam threshold and actively being jammed,the symbol color will change to green. If the signaldoes not ha ve a va lid DF report , t he symbol will ap-pear in yellow regardless of whether or not it is be-ing jammed. Signals with invalid DF reports willappear along the 225° (AFT) or 315° (FWD) azi-

muth a t a rela t ive range based on signal st rength .It will change to the appropriate red or green uponreceipt of a valid DF report from the ALQ-172 sys-tems.

This condition can occur during periods where thesignal is above 172 system receiver threshold butnot yet a bove ant enna subsystem receiver thresholdor during the signal acquisit ion interval where the172 trackers have not yet established signal track-ing gates required by the antenna system.

The yellow symbol can be displayed at any beamposition not just default if invalid DF report is pro-cessed after receipt of a valid DF report . In thiscase the symbol will be placed at the last knownvalid DF posit ion with its color changing from redor green to yellow until another valid DF report isreceived in which case its color will switch back tored or green a s a ppropriate.



T.O. 1B-52H-1-13


ALQ-172 Control Display Unit DT

Figure 1-20B

System resource status is displayed on the screen

in the upper right corner i .e. how many channelsare tracking signals. LRU failure indications aswell as r esource activity indicat ors display t he typeof system resources available to handle new threats. Threat data for a selected threat is dis-played in the system status data field. A threat canbe selected by touching the screen where the sym-bol appears or using the handoff pushbutton. Whena threat is selected by placing the select diamondaround t he symbol, the corresponding da ta from t hethreat is displayed in the threat da ta f ie ld . Datadisplayed includes the threat name, symbol fre-quency, PRF, mode, the ALQ-172 system process-ing/engaging t he threa t , a nd t he emitter a ngle of

arrival (AOA) and clock position. Selecting thehandoff pushbutton repeatedly will sequencethrough the threats being displayed in the orderthat the threats were received and placed into theCD U tr ack file.

If only one symbol is present on the display, thesymbol will aut omatically be selected a nd it s corre-sponding data displayed in the threat da ta field.

In situations where both the FWD and AFT sys

tems detect the same signal, the CDU will controsignal handoff so that only one symbol will appearon t he display an d only one system jams t he signalThe CDU continuously monitors the threat process-ing conditions and determines when to perform sig-nal handoff to the other system. The decision criteria is based on threat frequency, PRF and ampli-tud e report s. Tra nsit ion from one system t o anotherwill only occur at the completion of an ECM cycleAs a result , signal handoff will not be commandedin the middle of an E CM program sequence.

The frequency activity indicator is at the bottom ofthe situation display. Signals reported by both sys

tems are displayed in 1 GHz increments start ing atA-2 on th e left a nd incrementin g to C+ 4 on th eright . Naviga tion da ta received from th e OAS NAVdat a bus is displayed at t he top of the situa tion display. The data includes heading, altitude, air speedlatitude and longitude. Time is displayed in the sys-tem status area. The t ime can be set manually orobta ined automa tically from t he OAS.



T.O. 1B-52H-1-13

Change 9 1-67

ALQ-172 Component Locations




T.O. 1B-52H-1-13

1-68 Change 9

ALQ-172 Component Locations (Cont)




T.O. 1B-52H-1-13

Change 9 1-69




T.O. 1B-52H-1-13

1-70 Change 9

ALQ-172 Component Locations (Cont)




T.O. 1B-52H-1-13

Change 9 1-71




T.O. 1B-52H-1-13

1-72 Change 9

ALQ-172 Controls and IndicatorsLess DT

C-11213/ALQ-172 CONTROL-INDICATOR

1 MODE SELECTOR INDICATOR2 FAIL INDICATOR3 COLD INDICATOR4 HOT INDICATOR LIGHT/OVERRIDE SWITCH INDICATOR5 CONTROL-INDICATOR LAMP TEST PUSHBUTTON6 POWER SWITCH INDICATOR7 TEST STATUS INDICATOR8 SECURE SWITCH9 SELF-TEST PUSHBUTTON-INDICATOR

10 TEST STATUS INDICATOR

11 PD AFT STANDBY/OPERATE PUSHBUTTON-INDICATOR12 PD FWD STANDBY/OPERATE PUSHBUTTON-INDICATOR13 PR AFT STANDBY/OPERATE PUSHBUTTON-INDICATOR14 PR FWD STANDBY/OPERATE PUSHBUTTON-INDICATOR15 AFT TEST INDICATOR16 FWD TEST INDICATOR

Refer to T.O. 1B-52H-1-13-1 for ALQ-172 control and indicator functions.

Figure 1-22



T.O. 1B-52H-1-13

Change 9 1-72A

ALQ-172 Control MonitorLess DT

C-11270/ALQ-172 CONTROL MONITOR

1 PD FWD JAM INDICATOR LIGHT2 THREAT DISPLAY INDICATOR

3 PD AFT JAM INDICATOR LIGHT4 DIMMER CONTROL

5 CONTROL MONITOR LAMP TEST PUSHBUTTON6 PR AFT JAM INDICATOR LIGHT

7 PR FWD JAM INDICATOR LIGHT8 WEDGE VALUES

Refer to T.O. 1B-52H-1-13-1 for ALQ-172 control and indicator functions.

Figure 1-23



T.O. 1B-52H-1-13

1-72B Change 9

ALQ-172 Control Display UnitDT

1 BACK LIT COLOR LCD SCREEN2 GO INDICATOR3 POWER PUSHBUTTON-INDICATOR4 FWD STANDBY/OPERATE PUSHBUTTON-INDICATOR5 SPARE PUSHBUTTON INDICATOR6 KEYBOARD CONNECTOR7 AFT STANDBY/OPERATE PUSHBUTTON-INDICATOR8 HOT/COLD/FAIL INDICATOR/OVERRIDE PUSHBUTTON-INDICATOR

9 TEST INITIATE PUSHBUTTON-INDICATOR10 MASTER STANDBY/OPERATE INDICATOR11 PCMCIA INTERFACE12 SELECT KEY INDICATOR/SWITCHES13 LCD BRIGHTNESS CONTROL14 LIGHT SENSOR

Refer to T.O. 1B-52H-1-13-1 for Classified functions.




T.O. 1B-52H-1-13

Change 9 1-72C


1 LCD Color Display A back lit 6 X 8 inch color touch screen with a minimum 640 X 480 pixelcolor active matrix display is used for displaying situation awareness and

system status. Sixteen colors are available for display. The touch screencan be activated with or without gloves.

2 Go Indicator The pushbutton switch indicator comes on to indicate power status ofsystem components. Pressing the Go Indicator will perform a Lamp Test,which will light all non-programmable switches including LWR which is forfuture growth.

CDU (Green) CDU indicator comes on to indicate that the CDU GO mode is active.

FWD (Green) FWD indicator comes on to indicate that the forward system is powered.

AFT (Green) AFT indicator comes on to indicate that the aft system is powered.

3 POWER Pushbutton-Indicator The pushbutton switch indicator applies power to the FWD and AFTsystems and the CDU. Provided that the Auxiliary Panel switches are on.

POWER (Green) POWER is always lit when power is available to the CDU.

//// (Green) The presence of green diagonal lines indicate power has been appliedto the CDU.

4 FWD Standby/OperatePushbutton/Indicator

The software programmable pushbutton switch indicator is used for FWDsystem control indicates when FWD System is in Standby/OperateMode. Pressing the pushbutton when in Standby switches the FWD sys-tem to Operate Mode. Pressing the pushbutton when in Operate Modeswitches the system into Standby Mode.

The Operate state is indicated by both the PR and PD legends being high-lighted in reverse video (i.e. Operate mode selected). Pressing the push-button switch will result in the following sequence:

PR StandbyPD (Reverse Video) Operate

PR (Reverse Video) OperatePD Standby

PR StandbyPD Standby

PR (Reverse Video) OperatePD (Reverse Video) Operate

5 Spare Pushbutton Switch Indicator Spare software programmable pushbutton switch indicator is reservedfor the third, Lower (LWR) system, when installed.

6 Keyboard Connector The keyboard connector that allows the operator to connect a standard

keyboard with a MIL STD cable adapter to the CDU processor for ex-tended functions.




T.O. 1B-52H-1-13

1-72D Change 9

ALQ-172 Control Display Unit (Cont)DT


7 AFT Standby/OperatePushbutton/Indicator

The software programmable pushbutton switch indicator used for AFTsystem control indicates when AFT System is in Standby/Operate Mode.Pressing the pushbutton when in Standby switches the AFT system toOperate Mode. Pressing the pushbutton when in Operate Mode switchesthe system into Standby Mode.

The Operate state is indicated by both the PR and PD legends being high-lighted in reverse video (i.e. Operate mode selected). Pressing the push-button switch will result in the following sequence:

PR StandbyPD (Reverse Video) Operate

PR (Reverse Video) OperatePD Standby

PR StandbyPD Standby

PR (Reverse Video) OperatePD (Reverse Video) Operate

8 Hot/Cold/Fail Indicator/OverridePushbutton/Indicator

The software programmable pushbutton switch indicator used for systemcontrol and displays Hot, Cold and Fail indications all in green text.

HOT indicator comes on to indicate that a system HOT has been de-tected. Pressing the pushbutton with the HOT indication will enable Over-ride Mode for 60 seconds. The switch will display the count down time.Override can be discontinued anytime by pressing the button.

COLD indicator comes on to indicate that a system COLD has been de-tected.

FAIL indicator comes on to indicate that a system transmitter FAULT hasbeen detected.

This pushbutton will display any system over temperature, overheat,TWT FAIL and cold indication. Overtemp and overheat conditions resultin the 172 system to be placed in a STBY mode. Over temperature andoverheat conditions can be overridden by depressing the pushbutton.The pushbutton will display a 60 second countdown.

During this period, the applicable subsystem will be placed back into OP-ERATE mode. The applicable subsystem will go through autonomousself test for 8 seconds before actual RF transmissions will continue. Theoverride can be repeated every 60 seconds as required with the knowl-edge that the identified subsystem is reporting an over temperature/over-heat condition. Therefore, system operation may be degraded.

When a TWT FAIL indication is reported, the pushbutton will display thefailed condition. The FAIL message will continue to flash continuously.However, by depressing the pushbutton, the FAIL message will no longerbe displayed. However, the indication will still be displayed on the situa-tion screen.

(Continued)




T.O. 1B-52H-1-13

Change 9 1-72E


Hot/Cold/Fail Indicator/OverridePushbutton/Indicator (Cont)

The following legends can be displayed on this pushbutton:

A2 HOT AFT LRU-2 High Voltage OverheatA4 HOT AFT LRU-4 High Voltage OverheatA A HOT AFT Antenna Subsystem Over tempAFT Cold AFT System ColdA PD HOT AFT PD Subsystem Over tempA PD TWT FAIL AFT LRU-4 TWT FailureA PR HOT AFT PR System Over tempA PR TWT FAIL AFT LRU-2 TWT FailureF2 HOT Forward LRU-2 High Voltage OverheatF4 HOT Forward LRU-4 High Voltage OverheatF12 HOT Forward LRU-12 High Voltage OverheatF A HOT Forward Antenna Subsystem Over tempF PD HOT Forward PD Subsystem Over tempF PD TWT FAIL Forward LRU-4/12 TWT FailureF PR HOT Forward PR Subsystem Over temp

F PR TWT FAIL Forward LRU-2 TWT FailureFWD Cold Forward System Cold

9 Test Init iate Pushbutton/Indicator The pushbutton switch has three built in legends. The top half indicatorindicates operator initiated self-test (TEST in white). The bottom half-leftindicator indicates a BIT (BIT in green). The bottom half-right indicator in-dicates a fault (FAU in yellow).

TEST (White) TEST pushbutton switch top half indicator indicates operator initiatedself-test. Pressing this button initiates BIT in the FWD and AFT systems.During BIT the TEST light is off.

BIT (Green) Bottom half-left BIT indicator comes on to indicate that a self test in prog-ress. The BIT segment will stay illuminated for approximately 14 sec-onds.

FAU (Orange) Bottom half-right FAU indicator comes on to indicate when any systemfails.

10 MASTER Standby/OperatePushbutton/Indicator

Alternate action pushbutton switch indicator selects and indicatesSTANDBY (STBY orange text) or OPERATE (OPER green text). Operateapplies power to select transmitters (all transmitters in Fail Safe mode).When the pushbutton is depressed while the system is in CDU Go Mode,only those systems assigned to operate via controls 4 and 7 will be al-lowed to go into Operate Mode.

STBY (Orange) STBY indicates the system is in standby. STBY will come on when the firstof the FWD or AFT PR or PD subsystems times into STBY (less than 240seconds). Status of all subsystems can be observed on the CDU display.

OPER (Green) OPER indicates the system is in operate.




T.O. 1B-52H-1-13

1-72F Change 9

ALQ-172 Control Display Unit (Cont)DT


11 PCMCIA Interface The PCMICA Interface is a single PCMCIA drive slot. A properly config-ured PC card will boot the processor from the drive slot (E drive). Thedrive is used to load the ALQ-172 OFP/EID/ECM files and databurn pro-gram. The drive is also used to record and playback recorded data via thePC card. The PC card can be 40 - 200MB or greater. Only Wing EW officerapproved PCMCIA cards are authorized.

NOTE

The PCMCIA drive slot has a firm ejection spring. Care shouldbe taken to keep from dropping the PCMCIA card when ejectingit from the drive slot.

12 Select Key Indicator/Switches (Text

Green)

Four programmable select key indicator/switches are located below the

display. Pressing the bottom bar of the respective switch frame will enablethe feature indicated in the display portion of the switch or will swap thefunctions of the normal video and reverse video features. Figure 1-24Dlists and defines the possible switch text items.

13 Brightness control The rocker dimmer control varies the intensity of the LCD display. Pro-vides baseline illumination for the LCD display. Pressing the top of theswitch increases intensity. Pressing the bottom of the switch decreasesintensity.

14 Light Sensor The light sensor automatically maintains the LCD brightness under vary-ing lighting conditions. The initial baseline brightness is adjusted with thebrightness control (13).




T.O. 1B-52H-1-13

Change 9 1-72G

ALQ-172 Waveguide Low Pressure Warning andBlanking Panel

1 WAVEGUIDE LOW PRESSURE LIGHTS2 BLANKING SWITCH

Figure 1-24

DT AN/ALQ-172 AUXILIARY PANEL

The ALQ-172 Auxiliary Control Panel (figure1-24A) provides switches for manual powering offeither the FWD or AFT systems independently af-ter application of system power by the CDU. Theswitches are mechanical sw itches which function byremoving ground from the relays in the individualsystem LRU s, thereby disabling the respective sys-tem LRU s. The lights a re 5 volt a c with power sup-plied when aircraft power is applied. Brightness iscontrolled by the main console panel light switch.The lights indicate the respective switch positionregardless of the power st at e of the CD U.

If the CD U fa ils, the system HIG H/LOW alt itudemode defaults to HI G H. The CDU alt itude overrideswitch allows the EW Officer to override the CDUaltitude mode default and places both FWD andAFT systems simultaneously in the LOW altitudemode. If OVRD LO is selected with a functioningCDU in HIGH mode the systems will switch to lowan d LOW will be displayed on the CD U in red. Sett ing th e switch ba ck to CDU ALT will change LOWon the C DU from red LOW to yellow H IG H a nd default to the CDU set t ing.



T.O. 1B-52H-1-13

1-72H Change 9

ALQ-172 Auxiliary PanelDT


1 Forward (FWD) System Power Push-button/Indicator

The switch allows the operator to prevent initial power application to theFWD system or to remove power from the FWD system. The switch is analternate action mechanical pushbutton.

FWD (Green) When the FWD (upper half of the switch) is lit the FWD system power ap-plication/removal is controlled by the CDU.

FWD OFF (Yellow) When the FWD OFF (lower half of the switch) is lit, power to the FWD sys-tem has been removed.

2 Lower (LWR) System Power Pushbut-ton/Indicator

Not functional - Switch is reserved for the third Lower (LWR) system wheninstalled.

3 Aft (AFT) System Power Pushbutton/In-dicator

The switch allows the operator to prevent initial power application to theAFT system or to remove power from the AFT system. The switch is analternate action mechanical pushbutton.

AFT (Green) When the AFT (upper half of the switch) is lit the power application/remov-al is controlled by the CDU.

AFT OFF (Yellow) When the AFT OFF (lower half of the switch) is lit, power to the AFT sys-tem has been removed.

4 CDU Altitude Override Switch If the CDU fails the altitude mode defaults to HIGH. The switch is an alter-nate action mechanical pushbutton which allows the operator to overridethe HIGH altitude mode selection by the CDU and commands bothALQ-172 systems to the LOW altitude mode.

CDU ALT (Green) When the upper half (CDU ALT) of the switch is lit, the CDU is controllingthe altitude mode.

OVRD LO (Yellow) When the lower half (OVRD LO) of the switch is lit, both ALQ-172 systemsare placed in the LOW mode.

Figure 1-24A



T.O. 1B-52H-1-13

Change 9 1-72J

DT CONTROL DISPLAY UNIT (CDU) OPERATION

Fail Safe Mode

With th e Fa il Sa fe mode, all cont rol/monitoring isaccomplished through a combination of indicatorsand single function switches. Minimal informationis provided while each system automatically pro-

cesses t he t hrea ts. The followin g sw itch/indicat orsare functiona l in the Fa il Sa fe mode:

• CDU POWER Switch

• CDU, FWD and AFT Go Indicator.

• TE S T S w it ch/In dica t or (TE S T, B IT, FAU )

• Ma ster OP E R/STB Y S wit ch/Ind icator

The lower half of the POWER switch will lightwhen pressed, indicating that a ground has beenprovided for both systems. The FWD and AFT goindicators will come on as the respective subsystemis powered. When the CDU indicator comes on, theCDU will have exited the Fail Safe mode and will

be in the C DU G O mode. If the CD U indicat or doesnot come on, the CD U is in Fa il Sa fe mode.

The Ma ster OP ER /STB Y S wit ch/Ind icator contr olsthe t ra nsitions from S TB Y (St an dby) to OP ER (Oper-ate) for both systems. In the Fail Safe Mode, as soonas one system reports Standby, the STBY legendcomes on, a nd t ha t syst em can be placed into opera -tion. P lacing this sw itch into the operat e mode placesall systems int o opera te as soon a s they t ime out toS TB Y.

CDU Go Mode

In the CDU GO mode the CDU controls both

ALQ-172 systems and display da ta tha t is ar ran gedon three pages; the Situat ion Page, Sta tus Pageand the Deta i led Sta tus Pa ge.

Situation Page

The Situation page contains the data necessary forthe EW Officer to make the decisions to transmitagainst the various signals illuminating the air-craft . The Sit ua tion page is shown in figure 1-24B .

Across the top of the page is a n a rea w here Naviga-tion informa tion from t he OAS NAV bus is dis-played w hen provided by OAS.

The system resource status is displayed on the up-per right area of the screen and indicates whichFile (EID) has been selected. This area indicates anabbreviated system sta tus, with fa iled LRU ’s shownas part of the corresponding system. Resource activ-ity indicators display the portion of system re-sources available to handle new threats. A yellow box will appear a s a cha nnel is assigned to a signa l.For the P R subsyst em only, a red box will appear ifa cha nnel has been disabled due to a self test fault .

Threat data for selected threats is displayed belowthe system status data. When a threat is selectedby touching the threat symbols on the screen, orpressing the H ANDOFF pushbutton, the select dia-mond is placed around the threat and the corresponding data from the system is displayed in theThreat Da ta ar ea. Threat na me, symbol, frequencyPRF, Mode of the threat, the ALQ-172 system pro-

viding the data, and the emitter Angle Of Arrival(AOA)/clock positi on a re d ispla yed .

Along the bottom of th e Situa tion page is th e Activity indicat or. This a rea display s t he signa ls reportedby both syst ems in a Frequ ency/Amplitude d isplay.

The remainder of the page is used to display thethreat symbols at the relative bearing a s reported bythe systems, an d at a relat ive ra nge from the centerof the area depending on their received signastr ength. The display is a bulls eye consisting of tw oconcentric circles. Signals detected, but below theJ am threshold, will be displayed red in the outer ringof the bull’s eye. Signa ls ar e displayed ba sed upon sig

na l strength. U pon being received a t t heir predetermined J am Threshold, the sym bol will change togreen. J am indicat ors for both systems ma ke up therest of this area. The FWD PR indicator is on theupper left of the area , the FWD P D indicator is on theupper right of the ar ea. At th e bottom level of the bullseye is the AFT system indicator. Betw een t he syst emindicat ors is a n a rea t hat is used to deconflict signaselection when several signals are selected by thetouch screen. When several signals are under thetouch screen select box, all the symbols under thetouch screen select box are displayed in this areaFrom this area a single threat can be selected bytouching the appropriate symbol.

In addit ion to displaying data, the CDU performsa nother ta sk, acting as the integrator of both systemsThe CD U performs t he ta sk of determining wh en asignal is handed off to another system. In a typicascenario a signal will be received first in the FWDsystem, an d reported to the C DU , an d then receivedby th e AFT syst em as t he aircra ft a pproaches the siteThe CD U w ill assign th e signal to only one system toJ am , in this case the FWD syst em. At t he appropriatetime, the CDU will hand off the signal to the AFTsystem for continu ed ja mming a nd prevent th e FWDsystem from jamming t he signal.

Status Display Page

The St at us D isplay page provides system self test a ndconfigurat ion da ta . The Sta tus pa ge is shown in figure 1-24C.

Detailed Status Page

The Deta iled S ta tus P age provides deta iled self-testdata for a specific system. The Detailed StatusScreen is shown in figure 1-24E. S ee section II I.



T.O. 1B-52H-1-13

1-72K Change 9

CDU Situation Display DT


1 OAS Navigation Data The top of the CDU screen displays the aircraft navigation data. The datais obtained from the OAS MIL-STD-1553A Controls and Displays B andD buses from the Navigation and Weapon Delivery Avionics Control Unit.The data is received at a rate of approximately 16 times per second andupdated on the CDU at the CDU refresh rate of approximately 5 times persecond. The following data is displayed as follows:

HDG Magnetic heading in degrees

AGL/MSL OAS altitude in feet. The default altitude displayed is MSL altitude. Whenbelow 5000 feet with a valid radar altimeter AGL altitude is displayed.

KTAS True airspeed in knots

Latitude Latitude in degrees, minutes, seconds

Longitude Longitude in degrees, minutes, seconds




T.O. 1B-52H-1-13

Change 9 1-72L


2 System Status Displays the status of the 172 systems as reported.

File Indicates which database file is selected by the operator (File 1 or File 2).HIGH/LOW Indicates whether the 172 systems are in HIGH mode or LOW mode. If

there is a detected difference between the mode selected by the operatorand the mode reported by the 172 systems, the mode of the 172 systemswill be displayed in red. This discrepancy can occur if the AUXILIARYPANEL CDU Altitude Override switch is set to OVRD LO with HIGH se-lected on the CDU.

FWD Indicates the status of the FWD 172 system. If no self test failures de-tected, FWD will appear in green. If self test failures detected or commu-nications not established, FWD will appear in red. Any failed LRUs de-tected and reported during self test will display their LRU number i.e., 1,2, 4,10, 7, 8R, 8L, 9, 12.

For a hard failure the LRU number is displayed in red; For a soft failurethe LRU number will appear in yellow; and for a software configurationfault the LRU number will appear in orange.

The channel initialization status bar segments will appear in green if thereare no signals being tracked. The segments will appear in yellow indicat-ing the number of channels that are actively tracking signals in the PRsubsystem and PD subsystem.

For the PR subsystem only, a red box will appear if a channel has beendisabled due to a self test fault detect.(Refer to T.O. 1B-52H-1-13-1 for additional information)

AFT Indicates the status of the AFT 172 system. All other information dis-played, except for LRU-12, is the same description as the FWD system.

Time of day is displayed in hours/minutes/ seconds in green at the bottomof the system status field. Time of day can be set manually or is automati-cally obtained from the OAS NAV data bus.

REC The letters REC in red indicate that record mode is in progress.

PLY The letters PLY in green indicate that playback mode is in progress.

3 Threat Information This field displays the particular emitter information that is pertinent to aselected threat symbol enclosed in the HANDOFF diamond. If the HAND-OFF function is selected or the touch screen function is used to select athreat, a diamond will appear around the threat symbol. When this occurs,the selected emitter’s parameters will be displayed in the field. The pa-rameters include:

Threat Name Threat name as defined in data base and symbol table by the mission pro-grammer. It is referenced by the T Type.

Symbol Based upon the CDU symbol set. Some emitter types will also have attrib-ute symbols along with the emitter symbol as follows:

Missile Activity/Alert (circle)

Missile Guidance (circle)

Missile Launch (flashing circle)

Acquisition (square). Symbols and attributes are referenced by T Type.

FREQ Is a display of the emitter frequency.(Refer to T.O. 1B-52H-1-13-1 for additional information)

(Continued)




T.O. 1B-52H-1-13

1-72M Change 9

CDU Situation Display (Cont)DT


PRF Is a display of emitter PRF. PRF also displays CW or NO TRK.(Refer to T.O. 1B-52H-1-13-1 for additional information)

MODE Is the scan type of the emitter.(Refer to T.O. 1B-52H-1-13-1 for additional information)

SYSTEM Is a display of which system is handling and is processing the signal i.e.FWD or AFT.

AOA Is a display of the actual angle of arrival of the emitter signal in both de-grees azimuth and clock position from the nose of the aircraft (0 degreesand 12 o’clock) as reported by the antenna subsystem.

4 Frequency Spectrum Displays the frequency of all signals detected by the 172 systems and dis-played on the CDU. The color i.e. red, green or yellow corresponds to thecolor of the symbol as displayed in the azimuth circle. Symbol that hasthe diamond select will be displayed under the corresponding frequency.

The height of the frequency spectral line is proportional to the reportedamplitude. The frequency spectrum displays frequencies from A-2 (leftmost edge) to C+4 (right most edge). Each tick on the display line repre-sents 1 GHz increments. (Refer to T.O.1B-52H-1-13-1 for additional infor-mation)

5 Handoff When pressed, the diamond symbol rotates through threats displayed onthe CDU. When FWD pressed and quickly released, causes diamond tomove to the first signal in the track file. When pressed again the diamondwill move to the next signal in the track file. When REV pressed and quick-ly released, causes the diamond to move to the next higher signal in thetrack file.

6 AFT Subsystem Status Under each subsystem legends i.e. PR (lower left corner) or PD (lowerright corner) will indicate the system mode as follows:

Blank Subsystem has not yet timed in, after power up system should time inwithin 240 seconds.

STBY (Yellow) Subsystem transmitters have timed in.

OPER (Green) Subsystem transmitters have been placed into operate mode.

JAM (Green) Subsystem transmitters are actively jamming one or more emitters.

HOT (Red) An overtemp or overheat condition has been detected in the AFT subsys-tem. This condition can be overridden for 60 seconds by pressing theOVRD button.

FAIL (Red) An overcurrent condition has been detected in the subsystem transmitter.When the FAIL indication appears all RF transmissions for that subsys-tem will be terminated.

7 Azimuth Circle (Threat Display) Provides angle of arrival information for threats sensed by EW sensors.

Top of display is current aircraft heading. Threat symbology is similar tothat used in standard radar warning receiver systems.

Threats being detected with valid DF are presented in the RED.Threats being jammed with valid DF are presented in the GREEN.Threats being detected or jammed without valid DF are presented inYELLOW.

(Continued)




T.O. 1B-52H-1-13

Change 9 1-72N


Threat symbols are displayed at the relative bearing as reported by theALQ-172 systems and at a relative range from the center or the area de-

pending on their received signal strength. The display is a bulls eye con-sisting of two concentric circles. Signals detected, but below jam thresh-old, will be displayed in red in the outer ring of the bulls eye. As the signalstrength increases, the symbol will be positioned closer to the inner ring.When the signal is above jam threshold and actively being jammed, thesymbol color will change to green. If the signal initially does not have avalid DF report, the symbol will appear in yellow regardless of whether ornot it is being jammed. Signals with invalid DF reports will appear alongthe 225° (AFT) or 315° (FWD) azimuth at a relative range based on signalstrength. It will change to the appropriate red or green upon receipt of avalid DF report from the ALQ-172 systems.

This condition can occur during periods where the signal is above 172system receiver threshold but not yet above antenna subsystem receiverthreshold or during the signal acquisition interval where the 172 trackershave not yet established signal tracking gates required by the antenna

system.

A yellow symbol can be displayed at any beam position not just defaultif invalid DF report is processed after receipt of a valid DF report. In thiscase the symbol will be placed at the last known valid DF position with itscolor changing from red or green to yellow until another valid DF reportis received in which case its color will switch back to red or green as ap-propriate.

Signals detected by the forward system are displayed in the upper he-misphere. Signals detected by the AFT system are displayed in the lowerhemisphere. The threat symbols that are displayed correspond to thesymbols selected by the mission programmer and correspond to thethreat data programmed into the ALQ-172 mission data file.

8 FWD Subsystem Status Under each subsystem legends i.e. PR (upper left corner) or PD (upper

will indicate the system mode as follows:

Blank Subsystem has not yet timed in, after power up system should time inwithin 240 seconds.

STBY (Yellow) Subsystem transmitters have timed in.

OPER (Green) Subsystem transmitters have been placed into operate mode.

JAM (Green) Subsystem transmitters are actively jamming one or more emitters.

HOT (Red) An overtemp or overheat condition has been detected in the FWD sub-system. This condition can be overridden for 60 seconds by pressing theOVRD button.

FAIL (Red) An overcurrent condition has been detected in the subsystem transmitter.When the FAIL indication appears all RF transmissions for that subsys-tem will be terminated.

9 Special Technique When ALQ-172 is countering a threat requiring use of the special tech-nique, an indication of this jamming appears in this area. (Refer toT.O.1B-52H-1-13-1 for additional information)




T.O. 1B-52H-1-13

1-72P Change 9

CDU Status DisplayDT


1 Self Test Status Displays the self test status of each LRU within the ALQ-172 shipset. Thefollowing color convention is utilized:

Green LRU passed and good.

Yellow LRU soft failure detected. At least half the number of channels are still op-erational.

Red LRU hard failure detected. Subsystem or system associated with LRU orLRUs is inoperative.

Orange LRU-1 and 10 only. Configuration error detected. OFP, EID or ECM filesdo not match correctly. Reported checksum or version number is not cor-rect. May be a data load problem or hardware problem.

2 System Configuration This area will display the version number of the CDU software residentin the CDU along with the release date. It will also display the versionnumber and release date of the HI and LO symbol table files. Also dis-played by system will be the PR & PD EID version numbers as well as the

overall LRU-1 and LRU-10 software configuration (CFG) number. Theoperator should verify that the proper CDU and system software hasbeen reported prior to performing any further operations with theALQ-172 system.

3 1553 Communications If 1553 communication has not been established the words 1553 DIS-CONNECTED will appear in this area in the color red. The words SELFTEST IN PROGRESS will appear in the color yellow during system selftest.

Figure 1-24C



T.O. 1B-52H-1-13

Change 9 1-72Q

CDU Select Key MatrixDT

Figure 1-24D (Sheet 1 of 4)



T.O. 1B-52H-1-13

1-72R Change 9

CDU Select Key Matrix (Cont)DT

PROGRAMMABLE PUSHBUTTON STATE DESCRIPTIONS

KEY LEGEND FUNCTION

AFT Selects/deselects the AFT system.

AFTANALYZE

Selecting this button allows the op-erator to view an analyze screenfor the AFT 172 System which pro-vides more detailed information onthe fault description. SRU/LRUand probability factor (weighing).

AFTERRORS

Displays any errors detected in theAFT System.

AFTID

Displays the results of the AFT IDrequest.

AFTSTATUS

Selecting this button allows the op-erator to view the detailed self testresults for the AFT 172 system asreported on the 1553 bus.

AFTSYSTEM

Displays the results of the AFT IDrequest by major function and anyerror blocks that were detected.

BRIGHT Selecting this button will increasethe light intensity of the program-mable pushbutton switches. Eachselection will result in a further in-crease in light intensity.

CANCEL Selecting this button returns theoperator to the Situation Display

Screen. ORSelecting this button returns theOperator to the CDUBURNScreen. - As applicable

CHANGEFIELD

Selects which field to be altered.Default is hours.Six fields can be altered as follows:

Hours Minutes Seconds (24 HourClock)

Month Day Year

Repeated pushing the button willallow the operator to select the

next field.CLOSE

FILEAllows the operator to stop the PlayBack function and return to the Sit-uation Display Screen.

DATAFUNCTION

Selects a sub-menu to alter the de-fault setting for which data functionto be executed.

KEY LEGEND FUNCTION

DATALOAD

Selecting this button allows the op-erator to select a sub-menu for per-forming data loading via the CDUand 1553 data bus.

DETAIL Selects a sub-menu.

DETAILS Selecting this button allows the op-erator to branch to a substate to se-lect which system detailed self teststatus results to be viewed.

DIM Selecting this button will decreasethe light intensity of the program-mable push button switches. Each

selection will result in a further de-crease light intensity.

ECM Allows the operator to select/dese-lect the ECM file for loading or veri-fying.

ESCAPE Selecting this button brings the op-erator to the next highest submenulevel.

ERRORDETAIL

Selects a sub-menu to display ei-ther the FWD or AFT errors de-tected.

FILE SELECT Selecting this button allows the op-erator to branch to a substate to se-

lect which database file and high/ low state to command the 172hardware and software.

FILETYPES

Selects a sub-menu to alter the de-fault settings.

FILE 1FILE 2

Selecting this button selects thedatabase file setting that will berecognized by 172 System.

FWD Selects/deselects the FWD sys-tem

FWDANALYZE

Selecting this button allows the op-erator to view an analyze screenfor the FWD 172 System which

provides more detailed informationon the fault description. SRU/LRUand probability factor (weighing).

FWD

ERRORS

Displays any errors detected in theFWD System.




T.O. 1B-52H-1-13

Change 9 1-72S

KEY LEGEND FUNCTION

FWDID

Displays the results of the FWD IDrequest.

FWDSTATUS

Selecting this button allows the op-erator to view the detailed self–testresults for the FWD 172 system asreported on the 1553 bus.

FWDSYSTEM

Displays the results of the FWD IDrequest by major function and anyerror blocks that were detected.

HANDOFF Selecting this button allows the op-erator to return to the Handoffmenu.

HANDOFFFWD

Selecting this button places thediamond symbol around the sym-bol of the first threat in the track file.Repetitively selecting this buttonwill place the diamond symbolaround the next threat symbolentry in the track file.

HANDOFFREV

Selecting this button reverses thediamond symbol selection pro-cess.

HIGHLOW

Selecting this button sets the 172system into the proper altitude set-ting which will determine the prop-er threat jam and lethal thresholdsas well as priorities.

IDSUMMARY

Provides a summary of the ID re-quest status reporting PR Configu-ration # and Pass/Fail. Any faileditems will appear in Red.

IDDETAIL

Selects a sub-menu to display ei-ther the FWD ID or AFT ID.

IDREQUEST

Selects the ID Request function.

LAMPTEST

Selecting this button causes all pro-grammable pushbutton switches toilluminate with a test pattern thatlights all pixels along with the failsafe button lamps. Depressing anyprogrammable pushbutton returnsthe operator to the original menustate.

LOAD Selects the Load function.

MIS # –1

Decrements the mission numbereach time by 1.

MIS #+1

Increments the mission numbereach time by 1.

MISSIONDATA

Allows the operator to select/dese-lect Mission Data File for loading orverifying.

MISSIONRUN

Selects a sub-menu to select themission or run number.

KEY LEGEND FUNCTION

MORE Selecting this button at any place inthe menu will bring the operatorinto the next sub-menu or sub-state.

NEW RUN

Selecting this button allows the op-erator to branch to a sub-menu to

select Run numbers and missionnumbers for the Record file.

NUMBERX

Selecting this button allows the op-erator to have a numeric code bydisplayed for each fault reported.Selecting this button again resultsin the report reverting back to an Xfor each fault reported.

OK Selecting this button allows the op-erator to start the Situation DisplayProgram.The PCMCIA card must be re-moved in order for the CDU to bootoff of internal memory and load the

Situation Display Program. It takesapproximately 80 seconds to re-load the program.

OFP Allows the operator to select/dese-lect the OFP file for loading or veri-fying.

OK Selecting this button allows the op-erator to start the Data Load Pro-gram.The PCMCIA card must beinstalled into the CDU PC drive inorder for the Data Load Program tobe loaded into the CDU.

PAGE DOWN Selecting this button allows the op-

erator to page down through thetext. This button will bring the oper-ator to the bottom of the page.

PAGEDOWN

Scrolls down the ID Details screento the bottom of the text file.

PAGE UP Selecting this button allows the op-erator to page thru the text. Thisbutton will bring the operator to thetop of the page.

PAGEUP

Scrolls up the ID Details screen tothe top of the text file.

PLAY BACKFUNCTIONS

Selecting this button allows the op-erator to select the Play Back sub-

menu.

PLAY BACKSTART

Selecting this button allows the op-erator to start the Play Back of pre-viously recorded data. The PCcard with the recorded data mustbe installed in the PC drive forproper operation.




T.O. 1B-52H-1-13

1-72T Change 9

CDU Select Key Matrix (Cont)DT

KEY LEGEND FUNCTION

RECORD

FUNCTIONS

Selecting this button will allow the

operator to branch to a sub-menuto enable the record of the 1553messages.

RECORDOFF

Selecting this button stops record-ing

RECORDON

Selecting this button starts record-ing.

OPENFILE

Returns the operator to the pre-vious sub-menu.

RETURN Allows the operator to Return to theprevious sub-menu.

RUN Allows the operator to Run the datain real time. ORAllows the operator to Run the dataload program by selecting a sub-menu. - As applicable

RUNMISSION

Selects a submenu to select themission number or run number.

RUNOPTION

Selecting this button allows the op-erator to select a submenu tochange the default options.

RUN # –1

Decrements the run number eachtime by 1.

RUN #+1

Increments the run number eachtime by 1.

SYSTEMSUMMARY

Selecting this button provides a toplevel summary of the data beingloaded or verified into the 172 sys-temInformation presented includes IDcode, function, % complete, # er-rors and status.

TIMESET

Selects a sub-menu to set the timeand date.

SELECTSYSTEM

Selects a sub-menu to alter the de-fault settings for which system tobe loaded or verified.

SITUATIONPAGE Selecting this button will result inthe sub-menu for exiting of theCDUBURN Program and will re-turn the operator to the SituationDisplay Program and situation Dis-play Screen.

ORSelecting this button returns theoperator to the situation screen.

KEY LEGEND FUNCTION

START Selecting this button will result in

the OFP/EID/ECM files to beloaded, verified or identified intothe FWD and AFT ALQ-172 Sys-tems via the CDU 1553 interface.A typical data load will be com-pleted in less than 8 minutes. Thedefault options are as follows:

File Type: Mission DataOFP FilesECM Files

System #: FWD SystemAFT System

1553 Functions: Load

Premature termination of data

loading will result in an inoperativesoftware load in the ALQ-172 sys-tem.

STATUSPAGE

Selecting this button selects theSelf Test Status Page.

STEPFORWARD

Allows the operator to Stepthrough the data with time incre-menting.

STEPREVERSE

Allows the operator to Stepthrough the data with time decre-menting.

STOP Selecting this button results in theCDUBURN stopping during the

data load operation. Hitting thisbutton during loading will result inan invalid OFP/EID/ECM load intothe 172 systems.

SYSTEMDETAIL

Selects a sub-menu to display ei-ther the FWD or AFT system de-tails.

VERIFY Selects the verify function.

VIEW Selects a sub-menu for obtainingmore detailed information con-cerning the data loaded into the172 System.

–1 Decrements the number by 1.

+1 Increment the number by 1.




T.O. 1B-52H-1-13

Change 9 1-72U

CDU Detailed Status ScreenDT

Figure 1-24E



T.O. 1B-52H-1-13

1-72V Change 9

DT CDU SYMBOL SET

The symbol set used for this configuration is repre-sented in figure 1-24F. This is the CDU version ofthe S ensor In tegrat ion symbol set .

To verify all t he sym bols in the C DU , th e hook up ofan externa l keyboar d t o the J 6 connector is re-quired. Select the menu item Q and observe thesymbol set displayed on the CD U.

CDU Symbol SetDT

Figure 1-24F



T.O. 1B-52H-1-13

Change 9 1-73

Less DT NORMAL OPERATION (ALQ-172)

Turn-On Procedures

Turn -on of t he ALQ-172 will be a ccomplis hed inaccordance wit h th e section II procedures.

ALQ-172 System Tests

OPERATOR INITIATED SELF-TEST

The operator initiated self-test provides an end-to-end checkout of all ALQ-172 system components. Itis conducted during the EW Officer’s Calibrationand Interference check and anytime the EW Officerquestions system performance. Both forward andaf t systems are ca l ibra ted and tested dur ing theself-test. The self-test is initiated by pressing theTEST button on the ALQ-172 control indicator (9figure 1-22). The ON light in the power switch (6figure 1-22), and the FWD and AFT test status in-dicators (16 and 15, figure 1-22) should illuminate

for the duration of the self-test. The wedges on theALQ-172 control monitor (figure 1-23) are num-bered and some will illuminate in the forward andaft sectors during the test , indicating the missiondata software version number. The operator initi-ated self-test takes approximately 10 seconds, dur-ing which RF energy is transmitted for approxi-ma tely 1.5 seconds.

AUTONOMOUS SE LF-TES T

An autonomous self-test is automatically init iatedevery 10 minutes by the ALQ-172 for the respectivesystem provided that no RF activity has been re-

ceived during that time. Additionally, the EW Offi-cer can force the ALQ-172 to initiate an autono-mous self-test by momentarily placing either FWDan d/or AFT subset fr om STB Y to OP ER a nd ba ck to

STB Y in ra pid succession (1-2 seconds). Dur ing t hea utonomous self-test , t he a pplica ble FWD a nd/orAFT test status indicators will light for the test. Allsystems components are checked except for thehigh volta ge power supply (HVP S) and the high level tra veling w a ve tube a mplifier s (H LTWTA), ther efore, no RF energy is transmitted during this testThe autonomous self-test takes approximately 10

seconds. If malfunctions are detected during thetest, applicable ALQ-172 control indicator fault status lights will illuminate a long w ith control monitorw edges. To displa y F WD a nd /or AFT fa ult codes onth e cont rol monit or th e WAR/TRAIN s w itch m ustbe in TRAIN . To displa y F WD a nd /or AFT P R s ubsystem faults on the control monitor, the HIGHLOW MODE switch (1, figure 1-22) must be inHI G H . To display FWD a nd/or AFT P D s ubsyst emfau lts on th e control monitor, the H IG H/LOWMOD E sw itch (1, figur e 1-22) mus t b e in L OW. Thenumbers on the lighted wedges indicate specificmalfunctioning LRUs. See Section III for wedgevalue indicat ions.

TEST STATUS INDICATORS

If a failure is detected during either the operatorinitiated self-test or the autonomous self-test, theTE ST STATU S indica tors P R (RX a nd TX), P D/CW(RX and TX), or ANT (EU, R, L, SW) (7 and 10, fig-ure 1-22) will illuminate. If a failure is catastrophic(ha rd), the a ppropriat e LRU fail indicator light w ilcome on and remain on until power is removed oranother self-test cycle is initiated. In the case of ahard failure, the associated subsystem is inopera-tive. If a non catastrophic (soft) failure is detectedthe appropriate fail indicator light will come on, re-

main on for 5-10 minutes and then go off. A softfailure indicates that the associated system may bedegraded.



T.O. 1B-52H-1-13

1-74 Change 9

DT CDU NORMAL OPERATION (ALQ-172)

The CD U P rogram is a control program for t he AN/ALQ-172 Counterm easu res S et. This progra m is de-signed to communicate with the ALQ-172 systemover the 1553B Local Bus that connects the CDUhardware to the systems (figure 1-20A). The CDUHardware is connected to the FWD and AFT

ALQ-172 Systems and the CDU Program can dis-play the information from these systems and con-trol their reaction to th reats in the environment.

NOTE

If the ALQ-172 CDU fails both, FWD andAFT systems default to the HIGH alt itudemode. LOW altitude mode can be selectedfor both systems by selecting OVRD LO onthe ALQ-172 Auxiliary Panel CDU AltitudeOverride Switch.

Starting The CDU Program

The CDU Program is designed to startup automati-cally from powering on the CDU hardware or uponexit ing from the CDUBURN Program as long asthere is no PC MCIA card inserted into the PC MCIAslot a t the front o f the CDU hardw are.

Running The CDU Program

Once the CDU Program starts there will be a slightdelay a s th e firmwa re is loaded onto the 1553 card,during this t ime the screen will display the mes-sage CDU PROGRAM LOADING. This is normaland may take as long as 1 minute. The screen will

then come up with the Situation Page Screen dis-played and the programmable pushbuttons will beilluminated.

The rest of this section deals with the different op-tions a va ilable t o the EW Officer.

The CDU Display has some fundamental conceptstha t need t o be understood in order to gain full useof the syst em. These ar e for genera l use thr oughoutthe display a nd can be used during a ll the functionsof the CDU . There may be some a ddit iona l featuresthat are dependent upon specific areas of the CDUDisplay a nd th ese will be handled separa tely.

COLORS

The most important item concerning the displaytest colors is green means no problem exists andred means there ma y be a problem. All failures areshown in red, normal conditional are shown ingreen. Yellow is also used throughout the program,sometimes it is used just to increase t he reada bility

of the display a nd other t imes as a w arn ing. On theSituat ion P age screen, threat s tha t a re red a re notbeing jammed, threats that are green are beingjammed. Threats displayed in yellow do not havevalid DF. On the Sta t us Pa ge screen LRU s tha t a rered have a ha rd fa i lure, LRUs t hat are yellow havea soft failure, LRUs th at are orange have a configu-ra tion failure and LRU s tha t a re green have no fail-ures.

SCRE EN SWITCH ING

Switching screens can be accomplished by using ei-ther t he pushbuttons or the touch screen. From the

Situation screen, the EW Officer can switch to theSt a tus screen, by pressing th e STATU S P AG E but -ton or by t ouching the s creen in the S YSTE M S TA-TU S box. In order to zoom in on a th rea t or a regionof the screen the EW Officer can touch theTH RE AT D ATA box on t he screen . Touchin g t his re-gion of the screen a gain w ill cause th e CDU displayto return to normal zoom. From any screen otherthen the Situation screen the EW Officer can re-turn to the situa tion screen by touching th e bott omright button marked SITUATION PAGE. In orderto return to the Situation screen from the Statusscreen the EW Officer can just touch the screen.The remainder of the screens are only available by

using the pushbuttons.

LAMP TEST

A lamp test feature in the CDU program allows theEW Officer to test the pixels on a programmablepushbutton. Pressing the LAMP TEST program-mable pushbutton on the Status Page lights all ofthe pixels on the pushbuttons. There is also a lamptest for just the non programmable pushbuttons aspart of the CDU hardware. These pushbuttons aretested by pressing the CDU Go indicator button.When this button is pressed, all of the bulbs insidethe fixed switches should light.



T.O. 1B-52H-1-13

Change 9 1-74A

HIGH LOW ALTITUDE MODE

The CD U P rogram is design to cont rol multiple AN/ALQ-172 syst ems. These syst ems a re designed t o beoperated in either high or low altitude modes. Sincethe threat priorit ies and lethality are alt itude de-pendent, the CDU comes with an option for chang-ing the a lt itude indication to the 172 system. In or-

der to change the alt itude sett ing the EW Officermust press the FILE SELECT button from the Sit-uation screen. This button will bring up a new setof buttons, including one that has a HIGH LOWdisplayed on it . Pr essing this button will cha nge thea lti tu de set tin g for t he AN/ALQ-172 sys tem s. TheSituation screen displays the alt itude in the top ofthe SYS TEM STATU S box. The a ltitu de is s hown inyellow i f the a l t i tude tha t the CDU Program issending agrees with the alt itude that the system isreporting, and red if they disagree. It is n ormal forthe color to change to red and then back to yellow as the system processes the pressing of the HIGHLOW button. It will a lso transit ion during 172 sys-

tem selftest . The CDU will alw ays r eport the actua lALQ-172 altitude mode. If the ALQ-172 AuxiliaryPanel CDU Altitude Override switch is set toOVRD LO with the CDU set to HIG H, the CDU wil ldisplay LOW in red to indicate the systems are inLOW and that a discrepancy between the CDUcommanded mode and the 172 system operationalmode has been detected.

E I D F I L E S

The ALQ-172 system is loaded with two databasefiles wh en the softw are is loaded. These sett ings a l-low t he operator to change t he para meters in w hich

threats are characterized. In order to change thedatabase sett ing the EW Officer must press theFILE SELECT button from the Situation screen.This button will bring up a new set of buttons, in-cluding one that has a FILE 1 FILE 2 displayed onit . Pressing this but ton wil l change the databasefile for t he AN/ALQ-172 syst ems. The S itu a tionscreen displays the file in the top of the SYSTEMSTATU S box. The file nu mber is sh own in y ellow.

CDU TIME

The CDU Hardware has no internal ba t tery andcan not keep time when the power is shut off on the

unit. Upon initial power-up, time will read00:00:00. In order to st ill be able t o ha ve the correcttime for recording purposes the EW Officer can setthe t ime using the programmable pushbuttons. In

order to access the t ime sett ing feature of the CD UProgram the EW Officer must switch to the Statusscreen and then press the MORE button repeat edlyuntil they see the TIME SET button. Pressing thisbutt on will then get t he EW Officer to the Time an dDate screen. The Time and Date may be set to somevery odd values or to the correct time depending onthe CPU BIOS. By us ing the CHANGE FIELD but

ton along with the -1 and + 1 buttons the EW Officer can set the t ime and date. When the t ime anddate are set properly, the EW Officer can press theSITUATION PAGE button to return to normal op-erations. Any power interruption will cause theCDU Hardware to lose track of the t ime and therefore the t ime must be reset after any power inter-ruption. The CDU will also obtain t ime from theOAS NAV bus. If time is a va ilable on t he NAV busthe CD U will display this t ime. The CD U will checkfor time from the OAS bus every 10 minutes andwill re-synchronize if required. However, once timeis set , either from opera tor sett ing or a utomat icallyvia OAS bus, the CDU will continue to increment

time a s long as power is a pplied. The dat e must a lwa ys be entered manua lly.

Threats

The purpose of the CDU Display is to provide theEW Officer with situation awareness about thethreats in the environment, threat parameters aswell as sta tus of the ALQ-172 systems.

SE LE CTING TH RE ATS AND TH RE AT HANDOF F

There are two ways to select a threat , the easiestan d most d irect method involves t ouching th e sym

bol on the screen of the threat you want to identifyWhen a threat is selected it will be surrounded by apurple diamond. The selected threat symbol is displayed under the corresponding frequency in thefrequency display field. The threats can also be selected using the handoff commands. The handofcomma nds go through the list of active threa ts a ndselects the next or last selected threat until t he endof the list is reached at which point it wrapsaround. The HANDOFF FWD and the HANDOFFREV buttons allow the EW Officer to go throughthe list in forward or reverse order. The threat in-forma tion for th e selected threat is displayed in thebox on the lower right s ide of the S itua tion screen.

If only one symbol is present on the display, thesymbol will aut omatically be selected a nd it s corresponding data display ed in the threat da ta field.



T.O. 1B-52H-1-13

1-74B Change 9

SYS TE M S TATU S B OX

In order to determine the number of threats in theenvironment and whether they are PR or PDthreats the EW Officer can look at the SYSTEMSTATUS box (2, figure 1-24B) on the upper rightcorner of the Situation screen. This box shows theforwa rd an d aft system followed by a green bar sep-

ara ted for PR and PD threats . For each threat tha tis being tracked by the system a yellow box isplaced in the green bar under the appropriatethreat type. The number of yellow boxes in thegreen bar indicates the number of tracked threats.For the P R subsyst em only, a red box will a ppear ifa channel has been disabled due to a self test faultdetect.

TH RE AT IN FOR MATION B OX

The CD U Displa y is designed to give much more de-tailed information about the threat environmentthan the Indicator Monitor. This information is ob-

ta ined by selecting a threa t a s described above. Thethrea t th at is selected will then ha ve deta iled infor-mation appear about it in the threat data field onthe lower right corner of the Situation screen (3,figure 1-24B ). Along w ith t he threa t da ta , informa -tion can be obtained about a threats frequency, itsrelative amplitude and the system frequency limits.This information is displayed along the bottom edgeof the screen. All of the threats are displayed alongthis bar graph of frequency with the height of thelines referring to their sign a l str ength . The selectedthreat will always have its symbol displayed below its frequency bar.

Record and Playback

The CDU Display is designed with record a nd play-back features to allow the EW Officer to record datafrom a f light and t hen la ter play back the data tha twas recorded. The CDU can also play files thatwere recorded using th e 50 series of the existing P Cba sed Forcing Function/St a tus D isplay/E nha ncedDia gnost ics (FF/SD /E D) progra m a nd t he FF /S D/ED program can playback files that were recordedwith the C DU P rogram. The CDU P rogram recordsinformation onto a PCMCIA card that must be in-serted into the PCMCIA slot on the front of theCDU hardware. In order to mainta in the compat i-

bility w ith t he FF/SD /E D progra m th e CDU doesnot record any information from the OAS 1553ABus.

In order to access the record feature of the CDUProgram the EW Officer must switch to the Statusscreen and then press the MORE button repeat edlyuntil they see the RECORD FUNCTIONS button.Pressing this button will allow the EW Officer toaccess the recording options. The EW Officer shouldthen press the NEW RUN button which will allow the EW Officer to select a file name that is not be-

ing used. This is done by pressing t he RU N # + 1,RU N # -1, MIS # + 1, and MIS # -1 buttons. Press-ing the MISSION RUN but ton wil l a l low the EWOfficer to switch between changing the missionnumber and the run number. The file name, e.g.,RU N01M02.DAT, w here 01 is the ru n nu mber a nd02 is the mission number, will be displayed in theFile stat us box on t he lower right corner of the Situ-at ion screen. B elow the file name w ill either be therecording t ime left on the drive, a warning that thefile name already exists, or a warning that there isnot enough room available on the drive to record. Ifthe file name exists the operator must change thename of the file, or else the recording will not be

started. Once the file name has been chosen, theEW Officer should press the OPEN FILE buttonwhich will bring the EW Officer back to the pre-vious button state. The CDU Program will not be-gin recording until after the RECORD ON buttonhas been pressed. After the recording has started,the bottom line of the Syst em St at us box on the Sit-uat ion page will show the current P C t ime in greenfollowed by the letters REC in red to show that thesystem is recording.

In order to access th e play back feature of the CD UProgram the EW Officer must switch to the Statusscreen and then press the MORE button repeat edly

until they see the PLAYBACK FUNCTIONS but-ton. P ressing this butt on w ill allow the E W Officerto access the playback options. The EW Officermust select a file name that exists in order to usethe playback feature. This is done by pressing theRU N # + 1, RUN # -1, MIS # + 1, an d MIS # -1 but-tons. Pressing the MISS ION RU N button will allow the E W Officer t o switch between changing the mis-sion number and the run number. The file name,e.g., RU N01M02.DAT, wh ere 01 is th e run n umb erand 02 is the mission number, will be displayed inthe File status box on the lower right corner of theSituation screen. Below the file name will be awarning that the file name does not exist if the file

is not found.



T.O. 1B-52H-1-13

Change 9 1-74C

After selecting a valid file name, the EW Officershould press t he P LAYB ACK START butt on wh ichwill allow the EW Officer to playback the file. Thetime tha t t he file wa s sta rted followed by th e lett ersPLY will appear in green on the bottom line of theSyst em St at us box on t he Situa tion page. The file iscurrently paused, in order to start the file playingthe EW Officer should first select the direction by

pressing either the STEP FWD or STEP REV but-ton. The EW Officer can then continue to stepthrough the file or press the RUN button to allow the file to run a utomat ically. U pon rea ching t he endof the file, the file will wrap around to the begin-ning. In order to stop playback the EW Officershould press the CLOSE FILE button. This willclose the playback file and return the CDU Pro-gram to normal operat ion.

NOTE

During playback there is no 1553 bus com-municat ion. The current signal environ-

ment , ALQ-172 sys tem st a tu s an d NAVdata will not be displayed. All non-program-mable switches are operational.

Entering Data Load Function

In order to exit the CDU Program the EW Officermust sw itch to the Sta tus screen and then press theMORE butt on repea tedly un til t hey see the DATALOAD but ton. The D ATA LOAD but ton w ill th enmove, and needs to be pressed again. This is to en-sure that the button was not accidentally pressed.If t he DATA LOAD bu tt on is pressed aga in dia logbox will appear on the screen prompting the EW

Officer to insert the PCMCIA card containing theCDUBURN program into the PCMCIA slot . Oncethis is done, the EW Officer should press the OKbutton or touch OK on the screen. Pressing this

button will allow the EW Officer to exit the program and sta r t the CDU BU RN Program for loadingthe ALQ-172 systems.

NOTE

Inser t the PCMCIA card par t number sideup into the slot before reboot begins. This

allows the CDU hardware to reboot to theCDUBURN program. I f the PCMCIA cardcontaining the CDUBURN program is notinser ted a t th is t ime the CDU hardwarewill reboot to the CDU Display.

Fail Safe Mode

If the CDU processor fails for any reason, the CDUHardware will default to a fail safe mode with onlythe four fail safe switches available. The defaultsta tes will be:

Alt i tude = HIG H

Data base F ile = FILE #1

STB Y/OP ER = OP ER ATE (The Ma ster STB YOPE R sw itch can override this default t o STB Y)

NOTE

The Ma ster S TB Y/OP ER sw itch mus t re-main in STBY until all systems t ime in toS T B Y m o d e a s d i s p l a y e d o n t h e C D Uscreen. Placing a subsystem into OPER be-fore the STBY time in occurs can result intransmitter self test errors.



T.O. 1B-52H-1-13

1-74D Change 9

Keyboard Commands And Screens

There are also keyboard commands that can beused on the CDU program when an external key-board is at tached to the CDU. The keys are ex-plained in the appendix.

KEYBOARD COMMANDS

Short-cut keys wh en CDU is being used with a key-board

S CRE E N S :

s S t a t us S creen

f Fw d S ystem D eta ils S creen

a Aft S yst em D et a ils S creen

d D ispla y S it ua tion S creen

h H elp S cr een - S how keyboa rd com ma nds

c CD U Fa ult Ma t r ix

u S how Fa ult Ana lysis screen

p Alignment P rocedures

q S how S ymbol Ta ble

E S C D is pla y S it ua t ion S cr een

RECORDING:

0 Choose Recording F ile Na me

Alt -R R ecor d S ta r t

1 New Run

PLAYBACK:

2 Forw a rd S t ep

3 Reverse S t ep

4 Run

– Choose P la yba ck File Na me

9 Open P la yba ck File

Ctr l-o Open File Dia log Box for select ing aplayback file

C t r l-f S h ow S t a t u s D ia l og B ox

Ct r l-c C lose f il e

C tr l-r Run

Al t -4 1/4 S p eed

Al t -2 1/2 S p eed

Alt -1 N or ma l S peed

Alt -D 2 * S peed

Al t-Q 4 * S peed

REC ORD and P LAYBACK:

5 Run Number + 1

6 Run Number - 1

7 Mission Number + 1

8 Mission Number - 1

OTHER:

Alt -Z Zoom

Alt -B S elect B a ck

Alt -G G e t D a t a F rom S ys tem

Al t -A D u m p ATF

Alt -S S elect N ext

Alt -x E xit

PG UP Pa ge up for fau l t ana lys is screenPG DN Pa ge down for f au lt ana lysis screen



T.O. 1B-52H-1-13

1-75

AN/ALQ-122/AN/ALT-16ACOUNTERMEASURES SYSTEM


The AN/ALQ-122 count ermea sur es set is a n a ir-borne receiver-processor system that is integratedw ith tw o AN/ALT-16A tr a nsm itt er set s t o ma ke up

the AN/ALQ -122/AN/ALT-16A coun t ermea sur essy st em. The sy st em in clud es one R-1787/ALQ-122receiver, one MX-9187/ ALQ-122 processor, oneC-9040/ALQ-122 cont rol-monit or, t w o C U -2030/ALQ-122 duplexers (aft and forward), one CU-2137A/ALQ-122 dir ect iona l coupler, t w o T-787A/ALT-16A rad io tra nsm itt ers (systems 9 a nd 21), t woAM-2714A/ALT-16A RF a mplif ier s, tw o C-3358/ALT-16 contr ol-indi cat ors, one a tt enua tor, oneban dpa ss filt er, t wo composite filt ers, one AS-3087Aantenna located in the nose radome, and twoAT-1102/A a nt enna s, one locat ed a t st a tion 1342 topcenterline and one at station 1374 bottomcent erline of t he section 47 fuselage.

The AN/ALQ-122 set is us ed w ith tw o slight ly m od-ified AN/ALT-16 tra nsm itt er set s w hich a re desig -na ted AN /ALT-16A. The AN/ALT-16A re t a in s a llth e capa bilit ies of t he AN/ALT-16, such a s t he 10channel selection in the barrage (backup) mode.H owev er, t he AN/ALT-16A ha s been mod ified toa ccept s elected dr ive sign a ls fr om th e AN/ALQ-122in t he AN/ALQ -122/AN/ALT-16A nor ma l m ode . I nth e norma l mode, t he AN/ALT-16A tr a nsm itt ers lin -early amplify the low level signals from the receiverto th e desired t ra nsm it power level. To utilize com-plete normal mode system operation, the AN/ALQ-122 control-monitor MODE switch must be

sw itch ed t o XMIT position, a nd th e t w o AN/ALT-16control-indicator function switches must be placedin TRANS MI T. The AN/ALT-16A ca nn ot be oper-ated in the barrage (backup) mode unless the AN/ALQ-122 system is turned off.


S ee figu re 1-25 for compon ent loca t ion. The T-787A/ALT-16A rad io tra nsm itt ers a re connected t o theAN/ALR-20A receiver t o provid e look th roug hoperation. During look through operation, the AN/ALR-20A receiver sends blanking pulses to thetransmitters which turns the transmitters off for

short dura tions of t ime.

Control-Monitor (C-9040/ALQ-122)

The control-monitor (figure 1-26) interfaces withthe processor and provides remote operator controan d surveillance of system operation during n ormaoperation and during self-test.

Duplexer (CU-2030/ALQ-122)

The AN/ALQ-122/AN/ALT-16A coun t ermea su res s etrequires two duplexers, one aft and one forwardB oth duplexers a re identical an d interchangeable.

Directional Coupler (CU-2137A/ALQ-122)

The directional coupler is used to combine andnormalize the received RF signals from t he forwa rdand aft duplexers. The combined signal from thedirectional coupler output port is routed to the RFinput of the receiver. The received signal from theforwa rd duplexer (nose antenna ), ha ving the grea test cable loss, is connected directly to the summing

port of the coupler. The signa l from t he a ft d uplexeris connected to the coupled port through an externa l fixed at tenuat or selected to bala nce the forwar dand aft signal levels to the receiver.

Radio Transmitter (T-787A/ALT-16A)

The transmitter is comprised of low-level circuitsthat generate broadband barrage noise, multipliercircuits that multiply the input signals from thelow-level circuits to the output frequency and thatalso provide channelization, and driver circuits inwh ich a tr a veling-wa ve tube (TWT) is used a s a lowpower a mplifier.

Radio Frequency Amplifier (AM-2714A/ALT-16A)

The solid state amplifier consists of a high powerRF a ssembly, a power supply, a nd a control assem-bly.

Control-Indicator (C-3358/ALT-16)

The cont rol-indi cat or (figure 1-26) provides th e necessary controls for activating the transmitter andamplifier from a remote location, and consists ofswitching circuitry, a relat ive power indicatingmeter, indicating lights for providing visual infor

ma tion as to sequences of tra nsmitt er and a mplifieroperation and panel lights for illuminating frontpanel ma rkings an d controls.



T.O. 1B-52H-1-13

1-76

System Signal Flow

In t he receive mode, RF signa ls a re routed from theantennas to the aft and forward duplexers throughconnectors J 7 and /or J 9 (a ft) or J 7 (fwd ), a nd a rerouted by internal switching circuits to duplexeroutput connectors J 5. The received RF signa ls fromthe J 5 connectors of the aft an d forwar d duplexers

are routed to the directional coupler where they arecombined to provide RF inputs to the receiver. RFsignals a re genera ted a t a low level by the receiveran d a re then routed to recepta cle J 111 on t heselected aft (system 9) or forward (system 21) AN/ALT-l6A tr a nsmit ter. The sign a l is a mplified by t hetransmitter, routed to the RF amplifier for furtherlinear am plificat ion, a nd is then coupled to J 4 ofthe aft or forward duplexers. The duplexers routethe RF to either connector J 7 or J 9 of the a ftduplexer, or J 7 of the forwa rd du plexer, wh ere it isfed out to the appropriate antenna. When the AN/ALT-16A is us ed w it h t he AN/ALQ-122 in off cond i-ti on, t he a ft AN/ALT-16A (sys tem 9) out put pow er

is fed to the section 47 bottom antenna while theforw a rd AN/ALT-16A (syst em 21) outpu t pow er isfed to the directional nose antenna in the noseradome.

BUILT-IN TEST EQUIPMENT (BITE) SELF-TEST

The AN/ALQ-122 set ha s a self-tes t ca pa bilit y

wh ich includes 1) a ma nua l control panel lamp t est ,an d 2) an aut omatic test sequence using BI TE. Thelamp test is used to verify proper operation of con-trol-monitor lamps and driver circuits. The auto-matic BITE self-test sequence provides an end-to-end checkout (except for antennas and their associ-ated RF transmission lines) of the entire counter-measures system. The self-test sequence comprises12 steps which test the system ability to acquireand t rack a test signal in each threat channel andoperate in both ECM modes, plus the capability ofautomatically selecting the optimum antenna foreach threat .



T.O. 1B-52H-1-13

Change 9 1-77

ALQ-122/ALT-16A Component Locations




T.O. 1B-52H-1-13

1-78

ALQ-122/ALT-16A Component Locations (Cont)




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1-79

AN/ALQ-122/AN/ALT-16A Controls and Indicators

C-9040/ALQ-122 CONTROL-MONITOR

1 SIGNAL ACTIVITY2 STATUS LIGHTS3 TEST NO-GO LIGHT

4 LAMP TEST SWITCH5 COVER SWITCH

6 PROGRAM SWITCH7 MODE SWITCH8 POWER SWITCH

9 TEST IN PROG SWITCH10 FAULT LIGHTS




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AN/ALQ-122/AN/ALT-16A Controls and Indicators(Cont)

C-3358/ALT-16 CONTROL-INDICATOR

11 CHANNEL SELECTOR BUTTONS (1-10)

12 POWER SWITCH13 FAULT LIGHT14 RADIATE LIGHT

15 STANDBY LIGHT

16 WARM UP LIGHT17 POWER MONITOR METER18 VSWR BUTTON




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1-81


C-9040/ALQ-122 CONTROL-MONITOR

1 SIGNAL ACTIVITY Lights A description of the function of these lights during normal operation iscontained in T.O. 1B-52H-1-13-1. During self-test sequence, these lightsprovide an indication of the test step being exercised. Steps above 8 areindicated by two indicators, e.g.. step 9 – 1 and 8 lights.

2 STATUS Lights The four green indicators provide indication of system status during nor-mal operation or self-test as follows:

RX Light Comes on when the receiver is generating an ECM drive signal to excitethe AN/ALT-16A transmitters.

DUP Light Comes on to indicate AN/ALT-16A transmitter RF power is being suppliedto the antenna(s) by one or more duplexer output ports. This indicatortherefore comes on whenever the system is transmitting against a threat

and when transmitting during steps 5 thru 8 of the BITE sequence.

16F and 16R Lights Come on to indicate the forward (16F) and the aft (16R) AN/ALT-16A setsare in TRANSMIT and ready to amplify the low level ECM drive from thereceiver.

3 TEST NO-GO Light This white light comes on to indicate a fail condition during the BITE auto-matic sequence. This indicator is automatically extinguished when theTEST IN PROG switch is momentarily depressed.

4 LAMP TEST Switch When held depressed, all control-monitor lights should be on verifyinglamp circuit operation.

5 COVER Switch Refer to T.O. 1B-52H-1-13-1 for a description of switch operation.

6 PROGRAM Switch Refer to T.O. 1B-52H-1-13-1 for a description of switch operation.

7 MODE Switch When momentarily depressed, switches set to either standby (STBY) ortransmit (XMIT) mode. In STBY (amber light), the set remains warmed upand ready for operation. In XMIT (green light), the set is enabled for fulloperation. At turn-on, the set always goes to STBY mode.

8 POWER Switch When momentarily depressed, alternately applies or removes power tothe AN/ALQ-122 set. Power on is indicated by the green ON indicatorcoming on. The blue WARM UP indicator is on during set warmup andgoes out after a 5-minute maximum warmup period.




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AN/ALQ-122/AN/ALT-16A Controls and Indicators(Cont)


9 TEST IN PROG Switch When momentarily depressed, switch initiates the automatic self-testsequence. Green TEST IN PROG light should be on during thissequence. Upon detection of a fail condition during self-test, thesequence will halt. When this occurs, depressing TEST IN PROG switchcauses test sequence to continue through remaining steps until anotherfailure is noted or test sequence is completed (TEST IN PROG light goesout).

10 FAULT Lights The four white indicators come on to indicate a fault in the receiver (RX),processor (PR), forward duplexer (DF), and aft duplexer (DR).

C-3358/ALT-16 CONTROL-INDICATOR

11 Channel Selector Buttons Used to select channels for jamming. When depressed, dc power is fed

to brightly illuminate the button light, and provides a ground for the powersupplied to the respective channel multiplier allowing it to function. Press-ing and releasing the button a second time deactivates the respectivechannel.

12 Power Selector Used to select the application of power to the transmitter. STANDBY posi-tion supplies power to illuminate the indicator lights. TRANSMIT positionsupplies power to place the transmitter in operation. OFF & RESET posi-tion disconnects all operating power and initiates a 3-minute coolingcycle.

13 Fault Light A white light, when illuminated, indicates that a malfunction has occurred.This light will not illuminate in event of a RF power output fault.

14 Radiate Light A green light, when illuminated, indicates that the system should beradiating.

15 Standby Light An amber light, when illuminated, indicates that the power selector is inSTANDBY and the system is ready to transmit.

16 Warmup Light Not Used

17 Power Monitor Meter Not Used

18 VSWR Button Not Used




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1-83

AN/ALQ-153(V) TAIL WARNING SYSTEM


The AN/ALQ-153 Ta il Wa rn ing S ys t em is a solidstate pulse Doppler radar consist ing of two anten-nas, a radar receiver-transmitter (RRT), a digitaldata signal processor (DDSP), an analog data sig-

nal processor (ADSP), and a control-indicator (fig-ure 1-28). The sy stem utilizes d igita l sign a l process-ing to detect a nd w arn aga inst missile and a ircra f tthreats to the rear of the aircraft . Threats are indi-cated by an audio warning tone as well as indicatorlights. When an aircraft is detected, a light on thecontrol-indicator (figure 1-28) comes on to indicatethe range window of the threat . When a missile isdetected, the left or right missile light (LMSL orRMSL) comes on to indicate the tail sector in whichthe missile is located. At the same time, the rangeindicat or comes on and the missile wa rning tone isheard through the aircraft interphone system.When the missile approaches a selected range or

time (whichever provides the least time remaining),a countermeasures trigger (CM TRIG) light comeson to indicate that a countermeasures dispense(CMD) pulse has been generated. The CMD pulsecan be utilized to init iate defensive action againstthe missile by releasing flares, chaff, or both flaresand chaff. A continuous built-in-test (BIT) is acti-va ted when the system is in OPER and wil l causethe malfunction (MALF) light to come on if a mal-function occurs. When the MALF light comes on,the RR T, ADS P, or DD SP light comes on to indicat ethe component in which the fault has occurred. AHOT or PWR light will come on if the system shutsdown due to overheat or power faults. An operator

initiated BIT procedure may be performed afterwarmup to provide limited verification of propersystem operation. The system receives three-phaseac power a nd 28 volt dc power from the a ircraft a nddirects it t o power supplies in the DD SP an d ADS P.


Antenna (AS-3193/ALQ-153(V))

Tw o a ntenn a s loca ted on the left an d right s ide ofthe vert ical st a bilizer (figure 1-27) look a ft a nd out -board. These antennas are alternately selected byth e RRT.

Radar Receiver-Transmitter (RT1239/ALQ-153(V))

The RRT (figure 1-27) is located forward of thean tenna s in the vertical st abilizer. It consists of two

solid state transmit modules, two low noise ampli-fier (LNA) modules, an input power splitter, and anoutput pow er combiner/left-right sw itch. The t ra nsmit modules serve as RF power a mplifiers in tran smit and the LNAs serve as receiver preamplifiers inreceive. The input power splitter splits drive powerto the two transmit modules and the output powercombiner combines the output of the transmit mod-

ules an d switches the tra nsmit energy for tra nsmission by the selected antenna. RF excitation, controsigna ls, an d power for th e receiver/tr a nsmit ter isfurnished by the ADSP. In receive, the LNA modules amplify the signals from the antennas andtransmit these received signals to the receiver inthe analog signal processor. A receiver multiplexerswitches the receive energy between the left andright L NA pairs. The receiver/tra nsmitt er also ha sa bu ilt-in test (B IT) a ssembly for detecting fau lts.

Digital Data Signal Processor (CV-3438/ALQ-153(V))

The DDSP (figure 1-27) is located in the aft

unpressurized section of the aircraft. The unit consists of a digital signal processor, a power supplyand a power contactor. The purpose of the digitadata signal processor is to discriminate betweenmissile and aircraft targets and to provide rangeinformation (missile targets only) to the ControlIndicator Panel. The DDSP provides the followingeight functions:

1. The synchronizer genera tes the precision t iming signals for a ll units in the system.

2. I t computes the Doppler of fset of main-beamclutter based on horizontal speed received from anexterna l source.

3. The Doppler f i lter resolut ion necessary to discriminate among returns from missiles, aircraftand clutter.

4. Const an t Fa lse Ala rm Ra te (CFAR) and postprocessing provide a “floating” or “adaptive” detection threshold which allows extremely low falsea larm ra tes.

5. I t p rovides t a rget iden t i fica t ion and measurement in which detected targets are centroided inrange and Doppler. Identification tests are made todiscriminate between aircraft and missile returnsTa rget a zimut h is calculat ed for missiles (left, rightdetermination) in which the amplitudes of the left

an d right sum channels ar e compared t o provide anindication of target location. A trigger pulse for theaircraft CMD is generated based on the presentcont rol pa nel set tings (ra nge a nd/or tim e-to-impa ccontrol) an d the syst em sta tus da ta for display.



T.O. 1B-52H-1-13

1-84

6. The Noise Automat ic Ga in Cont rol (NAGC )loop periodically samples the level of the detectednoise from the receiver and holds the noise levelconst a nt v ia g ain cont rol feed-ba ck to the receiver.

7. BIT con t rol and f au lt i sola t ion con t rols thetiming of system BIT and accumulates the resultsof independent BIT within each of the LineReplaceable Unit (LRU s) to output a signal indicat-ing overall system status as well as to throw faultf lags in the LRU s.

8. DDSP power supply accept s pr ime power(28-volt dc a nd 400 H z t hree-pha se a c) a nd cont rolspower distribution of the ALQ-153 via contactors,as well as providing regulated dc power for theDDSP.

Analog Data Signal Processor CV-3439/ALQ-153(V)

The ADSP (figure 1-27) consists of a dual channelreceiver, a sta ble loca l oscilla tor (STALO), four a na -log-t o-dig it a l (A/D ) conver ter s, (SAMP LE D ATAUNIT), and a power supply. The sample Data Unitconverts the four channels of video informationfrom the receiver-to digital information for the digi-ta l da ta signa l processor (DD SP ). The STALO pro-vides RF excita tion for th e receiver/tr a nsmit ter,local oscillator signals for the receiver in the ADSP,and clock signals for the DDSP. The power supply

supplies power to the ADSP and for the receiver/transmitter.

The ADSP performs th e followin g four functions:

1. The mult i frequency STALO provides the sta blesystem clock signal, the transmit RF drive signal,and the three Local Oscillator (LO) signals to the

two-channel receiver.2. The triple-conversion receiver provides amplifi-cation, filtering, and m ixing of the rada r return sig-nal down to baseband and produces I (in-phase)an d Q (qua dra ture) signals for each of the sum a nddifference inputs .

3. The sampled da t a a ssembly provides ana log-to-digital conversion of the four video channel sig-na ls from t he receiver.

4. The ADSP power supply provides regu la ted dcpower to other subassemblies within the ADSP aswell a s to the RR T a ssembly.

Control Indicator C-10259/ALQ-153(V)

The control-indicator (figure 1-28) interfaces thetail warning system with the operator and providessystem mode control, fault status, as well as coun-termeasures control and target display. See figure1-28 for control a nd indicat or functions.



T.O. 1B-52H-1-13

1-85

ALQ-153(V) Component Locations

Figure 1-27



T.O. 1B-52H-1-13

1-86

ALQ-153(V) Controls and Indicators

1 LEFT SECTOR INDICATOR2 TIME TO IMPACT (TTI) ROTARY SWITCH3 MISSILE RANGE INDICATOR4 COUNTERMEASURES TRIGGER INDICATOR5 RIGHT SECTOR INDICATOR6 RANGE INDICATOR 0-37 JAM INDICATOR8 MINIMUM RANGE THRESHOLD SELECTOR9 MINIMUM RANGE SELECTOR/SWITCH

10 HOMING DEFEAT SELECTOR PUSHBUTTON11 PUSH-TO-TEST LAMPS CONTROL12 ANALOG DATA SIGNAL PROCESSOR

MALFUNCTION INDICATOR

13 RECEIVER-TRANSMITTER/DIGITAL SIGNALPROCESSOR MALFUNCTION INDICATOR

14 PUSH-TO-TEST TONE CONTROL15 HIGH/LOW ALTITUDE SELECTOR SWITCH16 TEMPERATURE/POWER MALFUNCTION

INDICATOR & OVERRIDE SELECTOR SWITCH17 OPERATE/STANDBY SELECTOR PUSHBUTTON18 POWER PUSHBUTTON SWITCH19 TEST AND/OR MALFUNCTION SELECTOR

SWITCH/INDICATOR20 TIME TO IMPACT ENABLE-INHIBIT SELECT

SWITCH/INDICATOR21 RANGE INDICATOR 3-6




T.O. 1B-52H-1-13

1-87


1 Left Sector Indicator (Red) An illuminated L MSL lamp indicates a confirmed missile in the left tailsector.

2 Time-To-Impact (TTI) Rotary Switch A 10-position rotary switch for the selection of a TTI threshold. The settingof this switch is determined by mission requirements, In the event of amissile threat, when the time-to-impact is equal to or less than theselected time, a CM dispense pulse is automatically sent to the counter-measure dispenser (CMD) if the TTI ENAB lamp is illuminated. An illumi-nated CM TRIG lamp indicates that a CM dispense pulse has been initi-ated. Pressing the TTI ENAB/INHBT switch disables this function and illu-minates the INHBT lamp.

3 Missile RANGE Indicator A two digit readout provides missile range. The L MSL, R MSL, andRANGE is displayed only for the missile which presents the most immi-nent threat. If the system loses detection of a missile, the MSL lamp andthe last range readout holds for a 3 second period unless a new missilethreat is detected, at which time the CIP will update and display the newtarget information.

4 Countermeasures Trigger Indicator(Green)

When the ALQ-153 initiates a CM dispense pulse the CM TRIG lamp illu-minates for a 1 second period.

5 Right Sector Indicator (Red) An illuminated R MSL lamp indicates a confirmed missile in right tail sec-tor. Both L and R MSL lamps illuminated indicate detection of a missilewithin sector of the tail centerline.

6 Range Indicator (Green) 0-3 If illuminated indicates an aircraft or an unconfirmed missile within a givenrange.

7 JAM Indicator (Amber) This lamp illuminates when the system senses an increase in the receiver

noise level induced by external sources which significantly degrades thesystem performance.

8 Minimum Range Threshold Selector MIN RNG is a 10-position rotary switch for selection of a minimum rangethreshold. The setting of this switch is determined by mission require-ments. In the event of a missile threat, when the minimum range is equalto or less than the selected range, a CM dispense pulse is automaticallysent to the countermeasure dispenser (CMD) if the MIN RNG ENAB lampis illuminated. An illuminated CM TRIG lamp indicates that a CM dispensepulse has been initiated. Pressing the MIN RNG ENAB/INHBT switch dis-ables this function and illuminates the INHBT lamp.

9 Minimum Range Selector Switch Operation of this control described as part of Minimum Range ThresholdSelector (No. 8).

ENAB (Enable) (Green) The ENAB light is on when MIN RNG is enabled (see No.8)

INHBT (Inhibit) (Amber) The INHBT light is on when MIN RNG is inhibited (see No.8)




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1-88

ALQ-153(V) Controls and Indicators (Cont)


10 HOMING DEFEAT Selector Pushbutton When enabled, this mode automatically inhibits system RF radiation fora given period after a CM dispense pulse has been initiated. When defeat

mode is enabled, the HOMING DEFEAT lamp is illuminated. Pressing theHOMING DEFEAT lamp switch the second time disables this functionand extinguishes the HOMING DEFEAT lamp.

11 Push-To-Test LAMPS Control A push-to-test function for lamp checkout. In addition, provides rotarycontrol to adjust the intensity of all CIP lamps. Lamp test does not inter-rupt normal system operation or initiate any mode change.

12 Analog Data Signal Processor Malfunc-tion (ADSP) Indicator (White)

An illuminated ADSP lamp indicates a malfunction in the unit. When theHOT lamp is also illuminated this indicates a temperature problem in theLRU. If the MALF lamp is illuminated, the ADSP lamp indicates a unit fail-ure as detected by built-in-test (BIT). If the system has automaticallycycled into standby it can be reset by pressing the OPER switch.

13 Malfunction Indicators

Radar Receiver/Transmitter (R/T)(White)

An illuminated R/T lamp indicates a malfunction in the unit. When theHOT lamp is also illuminated this indicates a temperature problem in theLRU. If the MALF lamp is illuminated, the R/T lamp indicates a unit failureas detected by built-in-test (BIT). If the system has automatically cycledinto standby it can be reset by depressing the OPER switch.

Digital Signal Processor (DSP)Indicator (White)

An illuminated DSP lamp indicates a malfunction in the unit. When theHOT lamp is also illuminated this indicates a temperature problem in theLRU. If the MALF lamp is illuminated, the DDSP lamp indicates a unit fail-ure as detected by built-in-test (BIT). If the system has automaticallycycled into standby it can be reset by depressing the OPER switch.

14 Push-To-Test TONE Control A push-to-test function for tone checkout. In addition, provides rotary con-trol to adjust the tone volume. Tone should be present at EW, Gunner, andDl stations. Tone test does not interrupt normal system operation or initi-ate any mode change.

15 High/Low Altitude (HI ALT/LOW ALT)Selector Switch

This switch and lamp combination is a manual aircraft altitude input to theradar. HI ALT is selected when the aircraft is at 4000 feet AGL or above.




T.O. 1B-52H-1-13

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16 Temperature/Power MalfunctionIndicator & Override Selector Switch

Temperature Indicator (HOT)(White)

An illuminated HOT lamp indicates that one of the system thermal inter-locks is open (no-go condition). When the HOT lamp is illuminated theappropriate LRU lamp (ADSP, R/T, or DDSP} also illuminates, indicatingwhich unit is overheated. A “hot” condition automatically results in thesystem power contactor being deenergized, removing input power to allunits. Once the temperature problem has been corrected, the systemautomatically sequences into the standby mode if the power is on. In theevent of an emergency, this function can be disabled for the R/T andADSP by the OVRD, but cannot be disabled for the DDSP.

Power Malfunction Indicator (PWR)(White)

An illuminated PWR lamp indicates the input power to the system isunsatisfactory or not present. An absent phase or a voltage greater than130 vac phase to neutral, supplied via the three-phase power sourcewould illuminate the PWR lamp. When the PWR lamp is illuminated, thepower contactor is deenergized. In the event of an emergency this func-tion can be disabled by the OVRD switch.

Override Selector PushbuttonSwitch (OVRD) (Amber)

Pressing the OVRD switch disables the R/T and ADSP thermal inter-locks, but does not disable the DDSP thermal interlock. It also disablesthe input power monitor interlock, initiated BIT. lamp test, and tone testfunctions, and prevents reversion to STBY upon BIT fault. An illuminatedOVRD lamp indicates that the override function has been initiated. Press-ing the OVRD switch a second time extinguishes the OVRD lamp and dis-ables the override function. The switch inhibits the automatic sequencingfrom operate to standby mode in the event of a system malfunction.

17 Standby/(STBY) (Amber)Operate (OPER) (Green)

Pushbutton Switch

An illuminated STBY lamp indicates the system is ready to be placed intothe operate mode. When the STBY lamp is illuminated, pressing the

STBY/OPER switch automatically puts the system in the operate mode.The STBY lamp extinguishes and the OPER lamp illuminates. During thetransitions the MALF light will illuminate. When in the operate modedepressing the STBY/OPER switch returns the system to standby. Whenthe system is in the OPER mode it automatically goes to standby after theTEST switch is pressed and the test is performed or if a system malfunc-tion occurs, unless the OVRD button is depressed.

18 POWER Pushbutton Switch (White) The POWER switch controls system input power. Pressing the POWERswitch applies power to the CIP circuitry and energizes the powercontactor located in the DDSP. Once the power contactor has energizedthe POWER & MALF lamps illuminate. The POWER and MALF lampsremain illuminated during the warmup period. The warmup cycle requires130 seconds if the system is turned on cold or 42 seconds if the systemhas been off a short time. After the warmup cycle is completed, the

POWER and MALF lamps automatically extinguish and the STBY lampilluminates.




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ALQ-153(V) Controls and Indicators (Cont)


19 Test and/or Malfunction SelectorSwitch/Indicator

TEST (Green) Pressing the TEST switch initiates an operator confidence test of the sys-tem countermeasures (CM) pulse. The TEST and OPER lamp illumi-nates and the system automatically cycles into the standby (non-radiat-ing) mode. During this test the CM pulse to the aircraft is disabled. Missilerange is counted down until the preselected minimum range (MIN RNG)and time-to-impact (TTI) is reached. When this occurs the CM TRIG lampilluminates for a 1 second period. This is a test of the DDSP and DDSP/ CIP interfaces.

System Malfunction Indicator(White)

An illuminated MALF lamp indicates a system malfunction as detected bybuilt -in-test (BIT). When the MALF lamp illuminates, the system automat-ically cycles into the standby mode unless it is in OVRD.

20 Time-To-Impact Enable-Inhibit SelectSwitch/Indicator Operation of this control described as part of Time-To-Impact (TTI) RotarySwitch (No. 2).

ENAB (Enable) (Green) The ENAB light is on when TTI is enabled (see No.2)

INHBT (inhibit) (Amber) The INHBT light is on when TTI is inhibited (see No.2)

21 Range Indicator (Green) 3-6 If illuminated indicates an aircraft or missile within a given range.




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NORMAL OPERATION (ALQ-153(V))

Turn-On Procedures

Press POWER pushbutton, POWER light (green)comes on a nd th e system is in the w ar mup mode ofoperation. The POWER light will go out and theSTBY light (amber) will come on when the system

is ready for normal operation (42 to 130 seconds).

The ALQ-153(V) system will not be oper-ated on the ground unless ground coolingequipment is used. Time, temperature, andcooling req uir ement s of T.O. 1B -52G-2-20must be complied with.

System Operation

Normal operation of the ALQ-153(V) consists ofoperating the system to detect threat aircraftan d/or missiles off t he t a il of th e a ircra ft. To placethe system into normal operation after a satisfac-tory turn-on or operator initiated BIT procedures,the follow ing st eps should be performed:

1. Press STBY/OPER pushbut ton (amber), OPE R(green) light should come on, and STBY (amber)light s hould go off.

2. Pos it ion MIN RNG and TTI con t rols to des iredsett ings a s directed by MAJC OM, or current ta cti-cal directives.

3. P r e ss MI N RNG a n d TTI E N AB /I N HB T

pushbut tons t o ENAB position (green) light on.

4. I f the ALQ-153(V) system detects an a ircra f t orunconfirmed missile, the aircraft detect light(green) will come on to indicate the approximateran ge of the a ircra ft missile.

5. I f a miss ile has been detected, the L MSL or RMSL light(s) (red) will come on, the range indicatorwill come on to indicat e missile ra nge, and the missile warn ing tone will be heard over the int erphonesystem. B oth L MSL a nd R MS L l ights i lluminat edindicates detection of a missile within 10 degrees ofthe tail centerline. When the missile reaches theminimu m ra nge selected or the TTI s elected, w hichever criterion is met first, the CM TRIG light(green) will come on generating a countermeasuresdispense (CMD) pulse.

Do not operate the ALQ-153 (V) system on theground w ith chaff or flares loaded on the a ircraft .

NOTE

I f a utoma t ic dispensing of f lar es an d/orchaff is desired, the flare (ALE-20) systema nd/or th e cha ff (ALE -24), mu st be on a ndin the automatic mode of operation.

6. I f CMD pulse genera t ion i s not desi red , pressthe MIN R NG an d TTI pushbutt ons and posit ion toINH B T (a mber) lights come on.

7. To turn off the ALQ-153(V) system, press thePOWER pushbutton and all indicator lights will gooff.



T.O. 1B-52H-1-13

1-92 Change 1

AN/ALQ-155(V) POWER MANAGEMENTSYSTEM


The AN/ALQ-155(V) sy st em is ca pa ble of provid ingvarious types of RF power output covering a widefrequency ra nge by using intercha ngeable trans mit-

ter groups. Each transmitter group has a specificfrequency range and power output which is desig-na ted a s a band .

Band 12 systems are installed in posit ions 1 and 2;band 9 system in posit ion 6; band 9S systems in po-sitions 3 and 4; ba nd 10 system in position 13; ban d10S systems in positions 5 and 8; and band 11 sys-tems in positions 7 an d 14.

Each system consists of an ALQ-155(V) receiver-tr a ns mi t ter, on e-ha lf of a n H D -766A/ALT-28(V)dual electronic equipment liquid cooler, one-half ofa flow protect valve, antenna system, one-half of aC-10130/ALQ-155(V) cont rol-indica t or/progr a mm er,a nd CM-465A/ALQ-155(V) processor. Loca t ion ofsystem components is shown in figure 1-29. TheT-1150C or D /ALT-28(V) tr a ns mit t er ha s a nR-2050/ALQ-155(V) receiver m ount ed on it s f ron tpa nel. Together th ey form a n ALQ-155(V) receiver-transmitter unit . The transmitter contains an M-type backward wave oscillator (BWO) and most ofthe functional circuits of the sy stem. The tra nsmit-ter housing is a m agnesium cast ing wh ich providesmountin g for the B WO an d liquid-and a ir-cooled ca-vities in which modules containing the power sup-plies, regulators, and modulators associated withthe BWO are mounted. The receiver is tunable andcontrolled by the signal processor in the automaticmode of operation. The control signal from the ra-dar warning receiver and or SI is received throughthe ALQ-155 signal processor which consists ofthr ee functions: an in put/output int erface, a centra lprocessor, a nd a mem ory. The input /output int er-face circuits convert processor external signal in-puts into control and da ta inputs to the centra l pro-cessor circuits and reconverts central processorda ta into outputs from th e processor. When directedby the external control inputs, the central process-ing circuits perform programmed software opera-tions with the external dat a inputs. Microprocessorchips are utilized inside the central processor to ac-

complish t hese softw a re opera tions. Tw o memoriesare contained in the processor: one provides theprogrammable software routines and a random

memory scratch pad, and the other memory con-tains the threat data file. The interface processoroperates as an integral part of the ALQ-155(V) sys-tem providing interface between the control-indica-tor/program mers an d the receivers. Da ta a nd con-trol inputs from the aircraft ra dar wa rning receivera nd or S I a nd AN/ALQ-172(V)2 syst ems a re a lsorouted through the signal processor for system tie-

in. The liquid cooler comprises a reservoir for cool-ing fluid, a single motor which drives a pump, acooling coil, and circuitry for control of the systemtiming periods. The flow protect valve protects thesystem from major leaks by closing off the flow ofcoolan t t o eith er of t w o T-1150/ALT-28 tra ns mi t ter swhenever a leakage rate in excess of 0.2 gallon perminute (GPM) is detected. This prevents a loss ofcoolan t w hich could cause th e unimpaired syst em tofail . For leakage rates of 0.2 GPM or greater, thevalve closes, terminat ing power a nd coolant flow tothe leaky transmitter, and diverts all the coolant tothe operable transmitter. As a second independentfunction, the flow protect valve also senses whenev-

er the flow of coolan t t o either tra nsmitt er falls be-low 1.8 G P M. A signal is provided to the liqu id cool-er to shut down that transmitter before thermalda ma ge can occur. The control-indica tor/progra m-mer provides controls and indications required forremote control of the system and controls for initi-ating the jamming program desired. The C-9525/ALT-28(V) a nt enna select pan el drives a w av eguideswitch for systems No. 1 and 2 to transfer electro-magnetic energy from the transmitter to either theforward or omni antennas. Circuits within the pan-el control dc voltages used to disable the transmit-ters during wa veguide switching t ime.


Signal Processor (CM-465A/ALQ-155)

The signal processor (SP) (figure 1-30) controls thefunctioning of t he receiver-tra nsm itt ers (RTs) basedon the mode of operation. It does this by executinga set of softw are instr uctions conta ined in Program -mable Read Only Memory (PROM). This set ofinstructions is called the Opera tion Flight P rogram(OFP ). Also resident in th e PR OMs is a s et or repro-grammable threat parameters known as the Emit-ter Identification Data (EID). The major compo-nents of the ALQ-155 are controlled through four

interfa ces. These include th e Receiver Tra nsm itt er(RT), C ontrol I ndicat or/P rogra mmer (CI P ), AN/ALR-46, a nd t he AN/ALQ-172 int erfa ces.



T.O. 1B-52H-1-13

1-93

SIGNAL PROCESSOR CONTROL FUNCTIONS

The computer program contained in the SP consistsof an init ialization and self-test sequence and anexecut ive loop.

1. Init ia l iza t ion and self-test . When power is firstapplied to the SP, the OFP executes an init ializa-

tion a nd self-test sequence. This sequence performsthe follow ing st eps:

a . Verif ies proper insta l la t ion of the E IDPROMs by reading the f irst PROM word andcompa ring it t o the proper value st ored in the OFP.

b. Verif ies tha t a l l RAM locat ions can be writ-ten to and rea d from w ithout errors.

c. Verif ies the OFP P ROMs can be read a ndcontain the correct data. This is accomplished byforming a cumulative check of all OFP PROMmemory locations and comparing it to the correctvalue stored in the EID P ROMs.

d. Verif ies tha t opera t ional parameters/

constants, downloaded from PROM to RAM forOFP use, were downloaded properly by doing a one-to-one compa rison.

e . Verif ies the hardwa re long and shor t t imersused by the OFP are operating properly.

f . B l inks the ERR lamp on a l l a c t iva ted CIP sif th e sequence is successful.

2. Executive Loop. The executive loop repeat edlyperforms a number of sequential functions. Thesefunctions a re described below.

a . One rout ine per iodica l ly checks the sta tusof each RT to determine if a power failure hasoccurred. If a power fa ilure is detected, an internal

flag is set in RAM and the OFP attempts to reacti-va te th e RT. If rea ctiva tion is successful, no indica-tions are provided to the operator. If unsuccessful,the ERR la mp will illuminate.

b. Another rout ine handles CIP servicingwhenever a CIP request is received. It f irst deter-mines which CIP made the request and then deter-mines the ty pe of request (MODE switch, J OG/RE -SE T pushbutton, or DE S pushbutton). Fina lly, thisroutine services the request by executing the soft-ware sequences which apply to the switch orpushbutton.

c. Yet another routine controls operation of all

CIP lamps that are bl inking in a sof tware con-trolled blink table. It does this by inverting the

lamp state (i.e, on to off or off to on). If the blinkduration has expired, the lamp is turned off andremoved from the blink table. Timing for the blinkinterval is determined by a combinat ion of softw areand ha rdwa re t imers.

d. The final routine of the executive loopmaintains the accuracy of all designated transmitters which have previously locked to a signal. Onthe average, this is accomplished every 1.5 secondsBefore the receivers are checked for activity, altransmitters are blanked to avoid interferenceEa ch locked-on receiver is th en exam ined for signaactivity. If activity is found, the receiver is set sothe signal is in the middle of the search frequencyrange and the transmitter is tuned to the receiverfrequency. If a signal is no longer present, a reacquisition sequence is initiated. This routine alsoperforms the init ial acquisit ion for transmittersdesigna ted in the manua l mode.

CONTROL CIR CU ITS

The high volta ges, power levels, an d la rge hea t concentr a tions encount ered in th e AN/ALQ-155(Vrequire tha t w ar mup, sta ndby, a nd cooling off periods be provided before and after application of highvoltage in the system. The necessary protection isprovided by th e tur n on (cycle in) and tur n off (cycleout) procedures of the system. The turn on procedures energize relays in their proper sequence toallow system and backward wave oscillator filaments to warmup prior to application of high voltage. When the MODE switch is rotated from OFFto STBY 1, full filament voltage is applied to all butone filament in the system. Reduced filament volta ge is a pplied t o the B WO. The TU N light will come

on. The system will remain in this condition indefinitely or until the next step of turn on procedure isa ccomplished. To activa te th e normal fila ment v oltage to the BWO, the operator must rotate theMODE sw itch to STB Y 2, or pressing J OG /RE Sswitch with the MODE switch in STBY 1. At thist ime the TUN light will be on a nd num eral 5 will bedisplayed on the THREAT ENGAGED indicatorDuring the t ime that the TUN and 5 lights are onfull filament voltage is applied to the BWO for 60seconds. After the total cycle-in period has elapsedthe TUN light will go out, the 5 light will remainon, and the system is ready to t ransmit when theMODE switch is placed in a transmit posit ion sup

plying plat e volta ge to the tra nsmitter.



T.O. 1B-52H-1-13

1-94

System Cooling

If the coolant becomes overheated, ground isremoved from the cycle-in control circuits and thesystem operates as in the cycle-out period exceptthat control power has not been removed and thesystem will automatically begin to recycle aftercoolant temperature drops. No indication of this

fault is provided except that the TUN light willcome on.

Failure of one or two phases to the liquid coolermotor or the high voltage power supply trans-former, or failure of one or more legs of these com-ponents result ing in a high neutral current, or a

BWO filament overvoltage condition causes thephase protect relay to remove control voltage fromthe system thus removing all ac power. Operation ofthe phase fault relay causes the PHASE FAULTlight on the liquid cooler and the FAU light on thecontrol-indica tor/progra mm er to come on.

If coolant flow falls below 1.8 gpm, the flow switch

operates and applies 28volts dc to a 30 second timedelay relay and the NO FLOW light comes on. After30 seconds, the time delay relay opens, removingpower from the system. The 28volts dc from theflow swit ch is also applied to th e FAU light causinga fa ult in dicat ion on t he cont rol- indicat or/program -mer.



T.O. 1B-52H-1-13

1-95

AN/ALQ-155(V) Component Locations




T.O. 1B-52H-1-13

1-96

AN/ALQ-155(V) Component Locations (Cont)




T.O. 1B-52H-1-13

1-97




T.O. 1B-52H-1-13

1-98

ALQ-155(V) Signal Processor

Figure 1-30



T.O. 1B-52H-1-13

1-99

C-10130 (ALQ-155) Control Indicator Programmer

1 DESIGNATE SWITCH2 ERROR LIGHT3 LOCK-LIGHT4 AUTOMATIC LIGHT

5 SEMI-AUTOMATIC LIGHT6 STACK LIGHT7 TUNE (WARMUP) LIGHT8 TRANSMIT LIGHT

9 FAULT LIGHT10 JOG/RESET SWITCH11 MODE SELECTOR SWITCH12 THREAT ENGAGE INDICATOR

13 CENTER FREQUENCY CONTROL14 MANUAL SCAN RATE CONTROL15 PROGRAM SELECTOR SWITCH16 RF BANDWIDTH CONTROL

NOTE

Each ALQ-155 Control-Indicator/Programmer contains duplicate controls for twotransmitters with the exception of the MANUAL SCAN RATE CONTROL. TheMANUAL SCAN RATE CONTROL is shared by both transmitters.

Figure 1-31



T.O. 1B-52H-1-13

1-100

ALQ-155 Antenna Selector Panel

1 ANTENNA SELECTOR SWITCH (ALQ-155SYSTEM 1)

2 FWD ANTENNA LIGHT (ALQ-155 SYSTEM 1)3 CMNI ANTENNA LIGHT (ALQ-155 SYSTEM 1)4 MONITOR BUTTON (LOOK THRU)5 FWD ANTENNA LIGHT (ALQ-155 SYSTEM 2)6 OMNI ANTENNA LIGHT (ALQ-155 SYSTEM 2)7 ANTENNA SELECTOR SWITCH (ALQ-155

SYSTEM 2)8 LAMP TEST BUTTON

Figure 1-32



T.O. 1B-52H-1-13

1-101/(1-102 blank)

NORMAL OPERATION (ALQ-155)

Turn-On Procedures

1. Posit ion ing the MODE se lector to STBY 1places the system in warmup mode. During thismode of operation, full filament voltage is notapplied to the backward wave oscillator (BWO) and

only the TUN light will illuminate. The system can-not be placed into radiation directly from this mode.The upper THREAT ENGAGE indicator will dis-play a number and the lower THREAT ENGAGEindicat or will display a lett er on the first C IP set toSTBY 1 with all other MODE selectors set to OFF.This n umber/letter display represents th e version/revision of the installed software.

2. To place the system into standby mode, posi-tion the MOD E s elector to STB Y 2 or J OG /RE SE Tin WARMU P mode. Du ring th e 1-minut e cycle-inperiod when the transmitter is transit ioning from

warmup to standby, the TUN light is illuminatedand the number 5 is displayed in the THREATENGAGE display. After the 1 minute cycle-inperiod, th e TU N light will go out.

3. In the s t andby mode (STBY 2), the t r ansmit teris ready for immediate use and only the THREATENGAGE will continue to display the number 5 tosignify that t he system is in sta ndby mode.

4. To return the t r ansmit ter to WARMUP modeaf ter i t has been t ransmit t ing, ro ta te the MODEselector to t he st op at STB Y 2. Then pull out on t heknob an d rota te counterclockwise to OFF. The number 5 in the THREAT DISPLAY will blank outWhen the TUN light illuminates after 7 secondsrota te th e MODE selector clockwise to STB Y 1.

5. To turn the t r ansmit ter of f f rom the wa rmupmode (STBY 1), rotate MODE selector ccw fromSTBY 1 to OFF.



BL



T.O. 1B-52H-1-13

1-103

EXPENDABLE COUNTERMEASURES SYSTEMS

AN/ ALE-24 1-103


COMPON ENT DESCRIPTION 1-103


AN/ ALE-20 1-113


COMPON ENT DESCRIPTION 1-113NORMAL OPERATION 1-120

AN/ALE-24 DISPENSER SET


The AN/ALE-24 count ermea sur es equ ipment dis-pensing set provides a means of dispensing minia-ture chaff packages from the wings of aircraftwhich misleads or clouds distant investigativera da rs. The set consi st s of eight D-20/ALE-24 dis-pens ers , a C-4508/ALE -24 select or, a C-4507/ALE-24 progra mm er, an d a C9510/ALE M AEXPEN control panel (master expendables control)connected into the system for SPD dispensing. Theselector, programmer, and master expendables con-trol are located at the EW officer station. Four dis-pensers are installed in each wing and are num-bered 1 thru 8 sta rt ing a t t he left outboard posit ionand continuing to the right outboard posit ion. Seefigure 1-33 for further equipment location informa-tion. Locating t he dispensers in th e wings yields aneffective countermeasures capability due to thehigh air turbulence, a large lateral separation ofdispensers, an d simult a neous ejection of cha ff pack-ages from both wings in bursts of two, four, or sixpackages. The wing location also reduces chaff con-tamina t ion to the a ircra f t .

The AN/ALE-24 dispen sin g set is d esigned toaccommodate 900 packages of self-protection dis-pensing (SPD) chaff, 150 units of single unit dis-pensing (SUD) chaff, and 75 units of delayed open-

ing chaff (DOC). Dispensers No. 1, 3, 4, 5, 6, and 8are reserved for SPD chaff, dispenser No. 2 forDOC, and dispenser No. 7 for SUD chaff . Maga-

zines, mounted five to each dispenser, contain thechaff . SUD an d DOC cha ff are dispensed at selectedintervals. SPD chaff is dispensed at continuousrates or in bursts, programmed according to unitsper burst , interval between bursts, and bursts perprogr a m. The AN/ALQ-153(V)1 coun t erm ea su resset may dispense chaff as a counter to aircraft andmissiles approaching t he ta il of the B -52.

U NITS P E R B U RS T S E QU E NCE B YS WITCH S E TTING D IS P E NS E R NO.

2 1-5, 3-6, 4-84 1-4-5-8, 1-3-5-6, 3-4-6-86 1-3-4-5-6-8, 1-3-4-5-6-8,


Dispenser (D-20/ALE-24)

Eight identical dispensers (figure 1-33) are locatedin left and right wing section 11, four on each wingnumbered 1 to 8 from left outboard to right out-board position. Ea ch dispenser consist s of an ejectorassembly, five maga zine and feeder assemblies, andfive support fittings. The dispenser is capable ofha ndling the different thicknesses of cha ff units byadjustment of an ejector roller adjustment screwan d gat e in the ma gazine a nd feeder a ssembly. Thedispenser ha s a dispensing ra te of two packages persecond with a velocity of approximately 30 feet persecond. As ea ch pa ckage is ejected, a sleeve openerin the ma gazine opens the package.



T.O. 1B-52H-1-13

1-104

Selector Control Panel (C-4508/ALE-24)

The selector control panel (figure 1-34) contains thecontrols necessary to select operating modes andtypes of chaff to be dispensed. Located on the unitare the DOC, SUD, and SPD dispensing switches.the DOC or SU D dispensing switches will init iate acontinuous mode program. these modes are inde-

pendent of all other operating modes and can beoperated simult an eously w ith a ny other m ode. TheSPD dispensing switch controls mode of operationfor the SPD chaff. In CONT position, a continuousdispensing mode can be initiated; in BURST posi-tion, a burst dispensing mode can be init iat ed. Alsolocated on the unit are three subtractive counterunits, one for each type of chaff, which indicate thenumber of cha ff packages remaining in the dispens-ers. Each counter dial can be reset by pushing inan d rota ting t he reset control sha ft projecting fromunder each counter. Eight DISP FAULT lightslocated on the unit will light individually if theassociat ed dispenser fa ils to eject a package wit hin

approximately 100ms after receiving a dispensecomma nd pulse. DIS P FAULT lights w ill also lightindividually, indicating ma gazines a re empty.

Programmer Control Panel (C-4507/ALE-24)

The programmer control panel (figure 1-34) con-tains the necessary controls to program differentmodes of chaff dispensing. Located on this unit isthe power switch for the dispensing set and an

AUTO-OFF switch. The AUTO-OFF switch allowsthe init iat ion of an SPD burst program by the AN/ALQ-153 Ta il Wa rn ing S yst em, t his S ection. ThePROGRAM indicator light will come on when theburst program is in progress. Also contained on theunit a re five rota ry sw itches.

Master Expendables Control Panel

The circuitry in the master expendables controlpanel (figure 1-34) related to SPD chaff dispensingis electrically connected to the selector and pro-gra mmer units. Only tw o of the controls on the unitar e used in conjunction w ith t he SP D cha ff dispens-ing system. The SPD CHAFF pushbutton indicatoris used to ini t ia te a SPD burst program and theSPD TERM pushbutton is used to terminate theprogram. The remaining controls are used in con-junction w ith th e ALE -20 flar e ejection syst em.

Gunner’s Chaff Deactivate Switch

A foot-operate momentary switch is located at thegunner’s sta t ion. This sw itch enables the gunner toterminate a chaff program in progress init iated bythe EW officer. When this switch is actuated, thechaff program must be reinitiated by the EW officerin order to resum e chaff dispensing. The cha ff deac-tivate switch receives TR power through a circuitbreaker marked CHAFF DISP DEACTIVATElocated on the ECM circuit breaker panel.



T.O. 1B-52H-1-13

1-105

AN/ALE-24 Component Locations

Figure 1-33



T.O. 1B-52H-1-13

1-106 Change 9

ALE-24 Controls and Indicators

1 SPD CONTINUOUS UNITS PER MINUTESELECTOR

2 PROGRAM IN PROGRESS INDICATOR3 DOC-SUD MINUTES PER UNIT SELECTOR4 BURSTS PER PROGRAM SELECTOR

5 POWER SWITCH6 AUTOMATIC DISPENSE SWITCH7 UNITS PER BURST SELECTOR8 BURST INTERVAL SELECTOR




T.O. 1B-52H-1-13

Change 9 1-107

9 SPD DISPENSER FAULT INDICATORLIGHTS

10 SPD CHAFF COUNTER11 SPD CHAFF COUNTER RESET

CONTROL12 SUD CHAFF COUNTER13 SUD CHAFF COUNTER RESET

CONTROL14 SUD DISPENSER FAULT INDICATOR

LIGHT15 SUD DISPENSE SWITCH16 SPD DISPENSE SWITCH17 DOC DISPENSE SWITCH18 DOC DISPENSER FAULT INDICATOR

LIGHT19 DOC CHAFF COUNTER RESET

CONTROL20 DOC CHAFF COUNTER

B ALE-24 SELECTOR CONTROL PANEL

21 FLARE PROGRAM INITIATE SWITCH22 SPD CHAFF PROGRAM IN

PROGRESS LIGHT23 SPD CHAFF PROGRAM INITIATE

SWITCH24 FLARE BURST INTERVAL SWITCH25 ALE-20 BURST INTERVAL LIGHT26 SPD CHAFF PROGRAM TERMINATE

SWITCH27 FLARE BURST INTERVAL SELECTOR28 MEP BURST INTERVAL LIGHT29 SPD CHAFF STANDBY LIGHT30 LAMP TEST BUTTON31 FLARE STANDBY LIGHT32 FLARE PROGRAM IN PROGRESS

LIGHT

C MASTER EXPENDABLES PANEL (MEP)




T.O. 1B-52H-1-13

1-108

ALE-24 Controls and Indicators (Cont)


PROGRAMMER CONTROL PANELA

1 SPD Continuous Units-Per-MinuteSelector

Used with continuous program mode of operation to dispense SPD chaffpackages at rates of 60, 90, and 120 packages per minute. The continu-ous mode, when initiated from the programmer and selector units, over-rides the burst mode.

2 PROGRAM-in-Progress Indicator Light A green light indicates, when illuminated, that dispense pulses are beingprovided for SPD programmed dispensing.

NOTE

In the event of an empty dispenser or a malfunction, the count-ers may move without dispensing chaff.

3 DOC-SUD Minutes-Per-Unit Selector Controls the interval in minutes between dispense pulses provided to theDOC or SUD dispense clutch, in position 2, pulses will be provided at arandom interval of 1 to 3 minutes. In position 3, pulses will be providedat a random interval of 2 to 4 minutes. In position 4, pulses will be providedat a random interval of 3 to 5 minutes.

4 Bursts-Per-Program Selector Controls the number of chaff bursts to be dispensed to complete a burstprogram. A burst program is interrupted when a local continuous programis initiated.

5 Power Switch PWR position energizes the SPD dispenser power relays, supplying acpower to the SPD dispenser motors, and routes dc power through the3-second time delay to the other parts of the dispenser. OFF positionremoves all power from the dispenser system.

6 Automatic Dispense Switch The AUTO-OFF switch must be in AUTO position if automatic activationof chaff dispensing by the ALQ-153 is desired.

7 Units-Per-Burst Selector Used with burst program mode of operation to control the number of chaffpackages dispensed simultaneously in quantities of two, four, or six pack-ages.

8 BURST INTERVAL Selector Controls burst intervals from 1/2 second to 10 seconds.

ALE-24 SELECTOR CONTROL PANELB

9 SPD Dispenser Fault Indicator Light Amber lights indicate when illuminated, that a dispense signal has notbeen received at the malfunction circuit from that light’s respective dis-penser.

10 SPD Chaff Counter Subtractive type counter indicates the number of chaff packages remain-ing in their respective dispensers. A control is provided to adjust thecounter.

11 SPD Chaff Counter Reset Control The SPD chaff control counter can be reset by pressing and turning thereset knob in either direction.




T.O. 1B-52H-1-13

1-109


ALE-24 SELECTOR CONTROL PANEL (CONT)B

12 SUD Chaff Counter Subtractive type counter indicates the number of chaff packages remain-ing in their respective dispensers. A control is provided to adjust thecounter.

13 SUD Chaff Counter Reset Control The SUD chaff control counter can be reset by pressing and turning thereset knob in either direction.

14 SUD Dispenser Fault Indicator Light Amber lights indicate when illuminated, that a dispense signal has notbeen received at the malfunction circuit from that light’s respective dis-penser.

15 SUD Dispense Switch In DISP position, the dispense pulses will be provided to the SUD dis-penser at the continuous rate selected by the DOC-SUD minute-per-unitselector. In OFF position, no pulses will be provided to the SUD dis-

penser.

16 SPD Dispense Switch In CONT position, the SPD continuous units-per-minute selector is in thecircuit and dispense pulses will be provided to the SPD dispensers at thecontinuous rate selected. In BURST position, the burst interval, units-per-burst, and bursts-per-program selectors are in the circuit and dispensepulses will be provided to the SPD dispensers in bursts, for number ofbursts selected only. In OFF position, no dispense pulses will be providedto the SPD dispensers.

17 DOC Dispense Switch In DISP position, dispense pulses will be provided to the DOC dispenserat the continuous rate selected by the DOC-SUD minutes per unit selec-tor. In OFF position, no pulses will be provided to the DOC dispenser.

18 DOC Dispenser Fault Indicator Light Amber lights indicate when illuminated, that a dispense signal has notbeen received at the malfunction circuit from that light’s respective dis-penser.

19 DOC Chaff Counter Reset Control The DOC chaff control counter can be reset by pressing and turning thereset knob in either direction.

20 DOC Chaff Counter Subtractive type counter indicates the number of chaff packages remain-ing in their respective dispensers. A control is provided to adjust thecounter.

MASTER EXPENDABLES PANEL (MEP)C

21 FLARE Program Init iate Switch When pressed, this switch will initiate a flare burst program as set on the

flare programming control panel. This switch performs the same functionas the release switch on the flare programming panel.

22 SPD Chaff Program In Progress Light When illuminated, this light indicates that an SPD chaff program is inprogress as selected by either the ALE-24 programmer or the MEP. A pro-gram cannot be initiated by the MEP as long as this light is on.




T.O. 1B-52H-1-13

1-110



MASTER EXPENDABLES PANEL (MEP) (CONT)C

23 SPD CHAFF Program Initiate Switch When pressed, this switch will initiate an SPD chaff burst program as seton the programmer and selector control panels. This switch will not over-ride a program initiated by the ALE-24 control panels.

24 Flare Burst Interval Switch Pressing this switch will select either the flare burst interval set on the flareprogramming control panel or the flare burst interval set on the MEP.Successive pressing of the switch will alternately select either ALE-20panel setting or the MEP setting.

25 ALE 20 Burst Interval Light When illuminated, this light indicates that the burst interval setting on theflare programming control panel is selected.

26 SPD Chaff Program Terminate When pressed, this switch will terminate any SPD chaff burst program inprogress. After the switch has been pressed, the SPD burst program can

be reinitiated either by the chaff programming panel or by the MEP. If theSPD burst program is reinitiated, the program will start from the beginning(of the program setup on the ALE-24 programmer) and will not resumefrom the point at which the program was terminated. DOC, SUD, or SPDcontinuous programs are not affected by this switch.

27 FLARE BURST INTERVAL Selector This selector selects the desired interval in seconds between pro-grammed bursts.

28 MEP Burst Interval Light When illuminated, this light indicates that the burst interval setting on theMEP is selected.

29 SPD Chaff Standby Light When illuminated, this light indicates the ALE-24 system is in standby anda new SPD chaff program can be initiated.

30 LAMP TEST Button When pressed, all lights on the MEP should illuminate at full brilliance.

31 Flare Standby Light When illuminated, this light indicates the ALE-20 system is in standby anda new flare program can be initiated.

32 Flare Program in Progress Light When illuminated, this light indicates that a flare burst program is in prog-ress. A program cannot be initiated by the MEP as long as this light is on.




T.O. 1B-52H-1-13

1-111/(1-112 blank)

NORMAL OPERATION (ALE-24)

1. S PD CO N TI N U OU S M OD E . Th e sy st em isdesigned to dispense SPD chaff in the continuousmode at rates of 60, 90, or 120 packages per min-ute. P ackages a re dispensed sequentially from eachSP D d ispenser. To initia te continuous opera tion,place SPD dispense switch to CONT position; the

counter should decrease steadily and at a rate(determined by the sett ing of the SPD continuousunit s-per-min ut e selector. To stop contin uous opera -tion, return SPD dispense switch to OFF (centerposition).

2. S PD B U RS T M OD E . Th e bu r st m od e i s a ccom -plished by setting the package per burst control (2,4, or 6), t he bu rst int erva l selector (1/2 th ru 10),and the bursts-per-program selector (1 thru 10) tothe desired posit ion. P ackages a re dispensed simul-taneously to provide the desired number of pack-ag es per burst. To initiat e burst operat ion, firmlymove dispense switch to BURST position; thecounter should decrease a t int ervals a s determined

by burst interval selector setting The program-in-progress indicator will illuminate while an SPDburst program is in progress. The light will extin-guish and the counter will stop when the programis complete. To reinitia te a nother progra m, th e SP Ddispense switch must again be moved firmly toBURST position.

During SPD burst opera t ion, any changemade in programmer control sett ings while

a progra m is in progress ma y result in chaffbeing dispensed at an unknown rate andduration or possible system malfunction.

NOTE

When init iat ing a burst program, it is nec-essary to f irmly place the SPD dispense

switch to the BURST posit ion and releasethe switch slowly. Erratic operation mayresult if the SP D dispense switch is not pos-i t i v e l y a c t i v a t e d . T h i s s i t u a t i o n h a soccurred if the program light goes out priorto program completion. In this event, it willbe necessary to recycle the system beforeresuming the desired program. Merely reac-tivating the SPD dispense switch will causethe system to resume opera t ion but wil lresult in an incomplete chaff dispense.

3. To init ia te DOC and/or SUD dispensing, l ifgua rd(s) a nd place DOC a nd/or SU D dispense

switch(es) to DISP position. The counter(s) wildecrease as determined by the DOC-SUD minutes-per-unit selector sett ing. To stop DOC /S U D d ispens-ing, place dispense switch(es) OFF and closeguard(s).



BL



T.O. 1B-52H-1-13

Change 1 1-113

AN/ALE-20 FLARE EJECTOR SET


The AN/ALE-20 flar e ejector sys tem is a n a irborn ecountermeasure system designed to deceive in-frared guidance systems. Deception is accomplishedby ejecting flares having an infrared energy compo-

nent large in comparison to the aircraft infraredoutput so that the infrared guidance system willtra ck to the flar e instead of the a ircraft . The systemconsists of one flare programming control panel,one junction box, and 12 identica l stepping sw itcheswith their companion flare ejector cases. Equip-ment locations are shown in figures 1-36. The AN/ALE -20 flar e ejector sy stem provides a m ean s of se-lecting the number of flares to be fired, timing theinterval between bursts, and ignit ing and fir ing theflares from the aircraft. The flare ejector systemut ilizes 12 AN/ALA-17 flar e set s w ith 16 flar es perset , an d a ma ximum of 192 single flares per air-craft. The flares may be programmed to fire in

bursts of one, two, or three flares at intervals of 2 to20 seconds, between bursts. The flares may also besalvoed at a rate of one flare every 65 millisecondsby depressing the fast train switch. All flares maybe ejected from the aircraft in less than 20 seconds.A C 9510/ALE MA EXP E N control pa nel (ma st er ex-pendables control) provides the operator with anexterna l control to set the burst interval t ime of theflares from 2 to 20 seconds in 1-second increments.The AN/ALQ-153(V)1 count erm ea su res set m a y fir eflares as a counter to aircraft and missiles ap-proaching the tail of the B-52 provided the flaresyst em is on an d AUTO is selected on t he flar e con-trol panel.

A switch on the pilot side panel, a landing gearsquat switch, a door-actuated safety interlockswitch, a safety switch in each flare case, and a re-set power switch are provided to prevent firing ofthe flares w hile the aircraft is on the ground.


Flare Programming Control Panel

The primary function of the control panel is to pro-vide the ejector with dispense pulses at the desiredrate and interval. I t controls the selection of the

number of flares to be ejected in each burst, thenumber of bursts per program, the t iming of theinterval between bursts, and the ignit ion and ejec-tion of the flares from the aircraft. The controlpanel conta ins a progra m pulse generator, progra mpulse interval control circuits, pulse counting cir-cuits and indicators, and lights to provide indica-tions of the existing sta tus of the syst em.

Stepping Switch

Tw elve identical st epping sw itches, one mounted oneach flare ejector case (figure 1-35), are located inthe horizontal stabilizers, six on each side of thefuselage. Each stepping switch contains a motor

driven stepping type switch which advances onecontact each time a pulse is received from the junc-tion box.

Flare Ejector Case

One flare ejector case (figure 1-35) is used witheach st epping sw itch. th e flare ejector ca se providesa case to hold the flare set a nd th e stepping swit chelectrical connector which conducts the firing pulseto each flare. In addit ion, a safety switch isinstalled in each flare case. in the event a flare setis installed in the case, the switch inhibits groundtesting of the system.

Master Expendables Panel (C9510/ALE)

The master expendables panel located at the EWofficer’s station provides control for setting theburst interva l and init ia t ing flare ejecting progra msin a ddit ion t o the same capa bilit ies on t he flare progra mmin g control pan el. See figure 1-34 for locationof the controls on the master expendables contropanel.

Pilot’s Flare Ejector Set Power Switch

This sw itch is a n a dded sa fety device located on th e

pilot s ide pan el (figure 1-38) and a llows t he pilot tocontr ol applica tion of power to th e syst em.

System Safety Interlocks

The system safety interlocks consist of a door-actu-ated microswitch located on the bottom of the fuse-lage aft of the section 47 entry door and the squatswitch relay located in the left relay panel in theforward wheel well. These two switches are inseries with the flare ejector power relay solenoid insection 47 dc power box. The relay is a ctua ted by dcbus voltage applied through the flare ejector setpower switch on the pilot side panel and the power

switch on the flare programming control panelWhen the aircraft is in flight, the door-actuatedmicroswitch and the squat switch are normallyclosed and power can be applied to the system. Onthe ground, the squat switch relay is deenergizedand, for further safety, the door that actuates themicroswitch is opened. For ground testing, thispower is available through the ground test switchan d th rough closed conta cts of all safety switches inthe flare ejector cases indicating that all f lare sets



T.O. 1B-52H-1-13

1-114

have been removed. The reset power switch locatedon the junction box mount must be held in the ONposition to provide power to reset the steppingswitches.

GROUND TEST SWITCH

A ground test switch located on the left side of the

forward wheel well is used by ground maintenancepersonnel to route dc power around the landinggear safety switch. The switch is spring-loaded inthe OFF position.

SAFETY INTERLOCK SWITCH

A door-actuated safety switch located on the under-side of the fuselage just forward of the horizontalsta bilizer is used to interrupt dc power t o the flareejectors.

Power Distribution.

DC operating power is a pplied to the flare program -ming control panel through the pilot flare ejectorset power switch. AC power is applied directly tothe flare programming control panel.

Stepping Switch and Flare Ejector Case

Figure 1-35



T.O. 1B-52H-1-13

Change 9 1-115

ALE-20 Component Locations

Figure 1-36



T.O. 1B-52H-1-13

1-116 Change 9

ALE-20 Controls and Indicators

ALE-20 FLARE PROGRAMMING CONTROL PANEL

1 BURST REMAINING RESET CONTROL

2 BURST REMAINING INDICATOR3 FAST TRAIN BUTTON4 BURST COUNTER5 BURST SELECTOR THUMB WHEEL6 RIGHT HAND BANK EMPTY LIGHT7 AUTOMATIC RELEASE SWITCH

8 RELEASE BUTTON

9 POWER SWITCH10 PROGRAM IN PROGRESS LIGHT11 INTERVAL SELECTOR THUMB WHEEL12 INTERVAL INDICATOR13 TRANSFER SWITCH14 FLARES PER BURST SWITCH




T.O. 1B-52H-1-13

Change 10 1-117


1 Burst Remaining Reset Control A knurled knob used to reset the burst remaining indicate to any desirednumber. Its purpose is to set in the number of flares loaded before flight.

2 BURSTS REMAINING Indicator Indicates the total number of bursts (total number of flares divided byflares per bursts switch setting) remaining on board the aircraft. The indi-cator subtractively counts the bursts. The indicator will not count burstsdispensed by the fast train button.

3 FAST TRAIN Button A pushbutton switch used to initiate continuous dispensing. The fast trainbutton energizes the fast train relay forming a holding circuit, interruptingany program already initiated, illuminate the program in progress light,and start the fast train pulse generator which produces a dispense pulseto the ejectors every 65 milliseconds. With this button depressed, allflares will be ejected in less than 40 seconds. The fast-train relay willremain energized until the power switch is moved to OFF positionmomentarily.

4 Burst Counter Indicates the number of bursts selected for a program. When a programhas been initiated, the burst counter will count the pulse bursts and sub-tractively indicate the number of bursts remaining in the program. Aftera program has been completed, the counter will automatically reset to thepreviously selected number of bursts.

5 Burst Selector Thumbwheel A knurled wheel used to select the desired number of bursts per program.

6 Right Hand Bank Empty Light An amber or red indicator light indicates, when illuminated, that the lastflare in the right hand bank has been ejected. The light will remain illumi-nated until the power switch is moved to OFF position momentarily.

7 Automatic Release Switch The AUTO-OFF switch must be in AUTO position if automatic activationof flare dispensing by the ALQ-153 is desired.

8 RELEASE Button A pushbutton switch used to initiate a flare dispense program. Therelease button routes dc power to energize the release relay which willremain energized until the burst relay is opened by the burst limitswitches.

9 POWER Switch Used to control application of ac and dc power to the system. In POWERposition, ac power is connected to the program pulse generator motorand dc to the various control circuits.

10 PROGRAM IN PROGRESS Light An amber or red indicator light indicates, when illuminated, that the pro-gram in progress relay is energized and a dispense program should bein progress or the light will also illuminate when the fast train relay is ener-gized.




T.O. 1B-52H-1-13

1-118



11 INTERVAL SELECTOR Thumbwheel A knurled wheel used to select the desired interval in seconds betweenprogrammed bursts.

12 Interval Indicator Indicates the interval in seconds of programmed bursts. Interval range is2 to 20 seconds.

13 TRANSFER Switch In TRANSFER position, the transfer relay in the junction box is energizedand all dispense pulses will be routed to the right bank of flares only. InOFF position, the dispense pulses will be routed to the left bank, then tothe right bank through the normal transfer sequence. The switch must bein OFF position before flares can be dispensed from the left bank witheither programmed or fast train dispensing.

14 Flares Per Burst Switch Determines number of flares to be dispensed per burst. Located on theback side of the flare programming control unit. Will be preset by mainte-nance personnel.




T.O. 1B-52H-1-13

1-119

Pilot’s ALE-20 Flare Ejector Panel


Flare Ejector Set Power Switch Used to provide the pilot a means of assuring that flares will not be ejectedduring critical periods of flight. The switch must be in ON position to pro-

vide dc operating power. Three position ON–OFF–ON switch is used.The switch locks in the center or OFF position and must be pulled outbefore it can be moved up to ON position. The lower ON position is dis-connected and serves no function.

Figure 1-38



T.O. 1B-52H-1-13

1-120 Change 1

NORMAL OPERATION (ALE-20)

NOTE

Prior to any normal dispensing or emer-gency jettisoning of flares, the EW officerwill notify all crewmembers of his intendeda c t i o n . D u r i n g f l a r e d i s p e n s i n g ,

crewmembers can expect a br ight whiteflash visible within the crew compartmentaccompanied by a slight vibrat ion of the a ir-craft. These flashes will be most noticeableat night, in the vicinity of cloud format ions,or during IFR flight conditions; however,the flash es are discernible even during da y-time VFR flight conditions.

1. To init ia t e a f lare eject ion program, momen-tarily depress the release button; the program–progress light will illuminate and the flare(s) willbe ejected immediately as evidenced by the burstcounter decreasing one increment and the burst

remaining indicator decreasing one increment.Bursts will continue to be ejected at the intervalselected by the interval selector until the burstcounter counts down to 1. At this time, the pro-gram-in-progress light will go out and the burstcounter w ill automa tically reset to original sett ing.Additional programmed flare ejection can berepeated by again depressing the release button.Flare programs can be repeated at will until allflares are expended as evidenced by illumination of

the RH empty light . In the event a program is inprogress and power to the system is momentarilyinterrupted (such as power switch moved to OFFand then back to ON), the program-in-progresslight will go out and ejection of flares will termi-nate. The system should resume operation from thepoint in the program where power was lost ; how-ever, the program must be reinit iated by again

depressing the release button.

Removing power from the system while aprogram is in progress could result in theclutch coil cam being stuck in the detentposit ion, making program mode inopera-tive.

NOTE

To termina te a flar e progra m in progress

r o t a t e t h e b u r s t s e l e c t o r t h u m b w h e e lupward until the program in progress lightgoes out. The program will have stoppedand the bursts per program may be reset .

2. I f a p rog ra m m ed n u mb er of bu r st s i s n otdesired, the system can be operated manually withthe burst selector set on 1 position. Using thismethod, continuous burst releases can be obtainedby holding the release switch depressed.



T.O. 1B-52H-1-13

Change 9 2-1

Normal Procedures section II

NOTE

• This section contains text and an amplified checklist. The text is divid-ed into primary paragraphs which form the phases of a normal flight .Most of these para graphs ar e followed by an am plified checklist for t heparticular phase of the flight. The amplified checklist is presented ina chronological form that will enable the flightcrew to complete theirinspection, checks, and operation of the aircraft in an expedient yetthorough manner. The amplified checklist describes in detail the stepsto be completed. E ach m ajor part ha s been assigned t o be read by oneof crewmembers, and to be accomplished by others in the crew. Howev-er, there are exceptions as some of the checklists will be read and com-pleted silently. To show w hich crewm ember w ill a ccomplish certa insteps, the normal crew coding will be used and the code letters will

appear after the response to each step. The terms ‘‘as required,’’ ‘‘asdesired,’’ ‘‘climatic,’’ and ‘‘cross-checked’’ as used in the checklist indi-cate equipment operation or sett ings w hich may vary according to pre-vailing conditions. In practice, the response to these items will be therequired switch or control position or actual indicator reading. The am-plified checklist has also been designed to accommodate the productionof the abbreviated checklist to be used during aircraft operation.

• Some system control switches are provided with a guard. In practice,when guarded switches are actuated, the desired toggle posit ion willbe ascertained and then the guard posit ioned.


PREPARATION FOR FLIGHT 2-3

PREFLIGHT PROCEDURES 2-5

BEFORE EXTERIOR INSPECTION – SAFETY CHECK 2-5

EXTERIOR INSPECTION 2-7

INTERIOR INSPECTION 2-8

PRETAKEOFF PROCEDURES 2-21

STARTING ENGINES 2-21

TAXIING AND BEFORE LINEUP CHECKLIST (COPILOT/EW READS) 2-22



T.O. 1B-52H-1-13

2-2


INFLIGHT PROCEDURES 2-23

AFTER TAKEOFF/CLIMB 2-23

EW CALIBRATION AND INTERFERENCE 2-25

EW EQUIPMENT SET 2-37

PRELANDING OPERATIONAL CHECK 2-41

AIR REFUELING PROCEDURES 2-42

RENDEZVOUS 2-42

CONTACT 2-43

POST AIR REFUELING 2-43

POSTFLIGHT PROCEDURES 2-44

AFTER LANDING 2-44

POSTFLIGHT 2-46

NUCLEAR ALERT PROCEDURES 2-47



T.O. 1B-52H-1-13

2-3

PREPARATION FOR FLIGHT

ENTRANCE

One main entrance door provides normal crew access into the aircraft. The door is located on thelower centerline of the fuselage ahead of the for-ward landing gear wheel well. A flush-type handle

is pulled out to unlatch the door. An entrance lightswitch is locat ed directly forwa rd of the door a t t hehead of the ladder. The entrance light operates ondirect battery power.

CHECKLISTS

The flight manual checklists have been designed sotha t th ey may be used for tra ining missions wit h or

without a bomb, for alert posture, and for SIOPmissions which are launched from other than aground alert posture. Ground alert checklist imple-mentation and instructions are contained inALER T P ROCE DU RES , this section.

NOTE

When no bombs or missi les are loaded,safety wires and seals are not required onthe associated monitor control and releasesystem controls.



T.O. 1B-52H-1-13

2-4 Change 10

ECM Equipment Operation Requirements

SYSTEM RESTRICTIONS

Restrictions to operation of any system will be governed byexisting regulations and/or directives.

RADIATION RESTRICTIONS

• When ECM transmitters are operating, radiationhazardous to human life exists up to a 20-foot ra-dius of the antennas. During periods of ground ra-diation, ground crew will be notified of the aboverestrictions.

• Ground operation of ECM or radar transmitters isprohibited when the B-52 is within 200 feet of (1)weapons which are not fully assembled, (2) weap-

ons to which continuity testers are connected, or(3) weapons with open access doors.

• Do not operate the AN/ALQ-153(V) system on theground with chaff or flares loaded on the aircraft.

Do not operate the AN/ALQ-155 system using for-ward directional antennas for more than 5 minuteson the ground since damage to radome can result.A cooling period of 30 minutes must be observedbefore this operation may be resumed.

EQUIPMENT COOLING

Critical cooling requirements of ECM equipment demandprecautions during ground and inflight operations. Groundcooling must be supplied to the applicable ram air inlet oraircraft compartment when extended ground operation ofECM equipment is required. During inflight operations orground operations with ground cooling connected, any re-moved ECM equipment that was located within a coolingshroud must be replaced with a dummy box or equivalent.Failure to do so will result in the loss of cooling air; there-fore, operation of any equipment within that shroud is pro-hibited. Ground operation of ECM systems without coolingair is authorized provided the time and temperature limita-tions listed in the following table are observed. The RWRand SI have no time or temperature limitations.

• Due to probable equipment damage, operation ofECM equipment without complying with propercooling, time and/or temperature limitations is pro-hibited.

• The ALQ-153(V) and ALQ-172 systems will not beoperated on the ground unless ground coolingequipment is used. Time, temperature, and coolingrequirements of T.O. 1B-52H-2-20 must be com-plied with.

MAXIMUM GROUND TIME AND TEMPERATURELIMITATIONS WITHOUT GROUND COOLING

GROUP SYSTEMS TIME OAT TEMP

A 1, 3, 5, 7, & 20 10 min 60°F 1

B 2, 4, 6, 8, & 21 10 min 60°F 1

C 9, 11 & 13 10 min 60°F 1

D 12 & 14 10 min 60°F 1

E ALQ-153 & ALQ-172 NOT ALLOWED

ALR-20A NO TIME LIMIT NO TEMPERATURE LIMIT

RWR NO TIME LIMIT NO TEMPERATURE LIMIT

SI NO TIME LIMIT NO TEMPERATURE LIMIT

Provided no more than one system per group is transmitting, a system may be operated in transmit for thetime and outside air temperature (OAT) depicted. After transmitting, ECM equipment must cool for at least30 minutes before transmission can be resumed.

1 ECM systems may be operated AT OAT’S above 60°F provided requirements of T.O. 1B-52H-2-20 are met.

Figure 2-1



T.O. 1B-52H-1-13

Change 12 2-5

PREFLIGHT PROCEDURES

BEFORE EXTERIOR INSPECTION – SAFETY CHECK

Wearin g t he chemica l defense a ircrew ensemble, including pla stic boots

and overcape, can cause a buildup of static electricity. For this reason,aircrews will ground themselves on the aircraft grounding cable priorto entering the aircraft when t he aircrew ensemble is worn.

1. Form 781 – Checked

Check Form 781 for pertinent equipment writeups and chaff and flare loadings not specifically covered in the pilot’s review of the form. Ensure correct software versions of reprogrammable EC sys-tems are loaded for your specific mission. Confirm with groundcrew that any missing componenreceiving ram air cooling has been replaced by a dummy box to block ram air outlet. If any ECMequipment that receives air from a common cooling duct is removed and not replaced with a dummybox, none of the other equipment that receives cooling from that cooling duct can be operated sincecooling air will be lost through the open hole and adequate cooling will not be available for therema ining equ ipment. I f th is is a pplica ble, refer to AIRS P EE D LIMI TATIONS , S ection V of T.O1B -52H-1.

2. EW Officer ’s Sta t ion:

a . Arming Levers – Stowed, No. 1 safety pins insta l led and locked

If th e arming lever(s) ha s been rota ted on a st owed a rmrest, ra ising thearmrest wil l fire the arming initiator. If the arming lever(s) has beenrotated or the arming lever(s) safety pin is not instal led, cal l mainte-nan ce immediat ely and sta y clear of the seat .

b. Ground Emergency Egress Ha ndle – Stowed, No. 6 safety pin insta l led

If the ground emergency egress handle has been rotated or the No. 6safety pin is not insta l led, cal l ma intenan ce immediat ely and sta y clearof the seat .

c. ECM Equipment , Cha f f & Flare Power Swi tches – OFF

NOTE

ALQ-122, ALQ-153, and ALQ-172 system status cannot be determined

until power is available to the system(s). L ess DT An internalself-protection circuit will ensu re t he ALQ-172 will r emain off until th ePOWER switch is activated, following the application of external powerto the aircraft. The ALQ-122 and the ALQ-153 must be checked afterexterna l pow er is applied to aircra ft to ensure the systems a re off.



T.O. 1B-52H-1-13

2-6 Change 12

PREFLIGHT PROCEDURES (Cont)

d. Chaff , Flare & Rocket Circui t Breakers – Out

During this inspection, the EW officer wil l ensure tha t al l syst ems are

completely deactivated to prevent inadvertent jamming or dispensingof expendables w ith t he a pplicat ion of ground power.

e . WARNING RCVR AC Circui t Breaker – Out

The WARNIN G RCVR AC circuit br eaker on t he EC M circuit br eaker pa nel w ill be pulled t oassure deactivation of the warning receiver.

f. L ess DT SYS 15 & SYS 16 IND CONT Circuit Breaker – Out

The SYS 15 AND 16 IND CONT circuit breaker will be pulled to assure deactivation of theALQ-172 system.

f. DT ALQ-172(V) CDU Circuit Breaker – Out

g. SI Control & Display Circui t Breakers – Out

3. Gu n n er ’s S t a t i on :

a. Ejection Seat Arming Levers – St owed, No. 1 safety pins insta l led and locked.

If th e arming lever(s) ha s been rota ted on a st owed a rmrest ra ising thearmrest wil l fire the arming initiator. If the arming lever(s) has beenrotated or the arming lever(s) safety pin is not instal led, cal l mainte-na nce immediat ely and sta y clear of the seat .

b. Ground Emergency Egress Ha ndle – Stowed, No. 6 safety pin insta l led

If the ground emergency egress handle has been rotated or the No. 6safety pin is not insta l led, cal l ma intenan ce immediately and st ay clearof the seat .

c. H ot Cup – OF F

d. RWR In tens ity Cont rol – Minimum



T.O. 1B-52H-1-13

Change 8 2-7


EXTERIOR INSPECTION

1. Forwa rd/Center Exterior Antenna s – Checked

Check protruding EC M a ntenna an d a ntenna covers mounted on t he fuselage for condition, securityand cleanliness. The ALQ-155 antennas should not be painted.

The bomb door actuator struts will be disconnected before entering thebomb ba y if power is a pplied to the aircraft .

2. ALE-20 Ground Test Switch – OFF

Check that the ALE-20 ground test switch (in forward wheel well) has not been inadvertently leftpropped in the ON position. (Switch is spring-loaded to OFF position.)

On aircraft carrying the AGM-86 missile, flight control surfaces mayinadvertently deploy without warning. Remain clear of missile flightcontrol deployment a reas a fter sa fety restra ints ha ve been removed.

3. Left ALE-24 Wing Cha ff Dispenser Ports – Checked

Visually check th at exposed chaff packages conform with mission requirements. E nsure th at no chafpackages are engaged by the rollers.

4. Left Aft Exter ior Antennas – Checked

Check protruding antennas and antenna covers mounted on fuselage for condition, security, andcleanliness.

5. Left ALE-20 Fla re Ejectors – Checked

Visually check that ejector covers are secure (if flares are not loaded) or that openings are unob-structed (if flares are loaded).

6. Tail-Mounted Antenna s – Checked

Check protruding E CM a ntenna s a nd a ntenna covers mounted on t he fuselage for condition, securityan d clean liness. The ALQ-155 ant ennas a nd ra dar absorber pan els should not be paint ed.

7. Right ALE -20 Flar e Ejectors – Checked

Visually check that ejector covers are secure (if flares are not loaded) or that openings are unob-structed (if flares are loaded).



T.O. 1B-52H-1-13

2-8


8. ALE -20 Sa fety Int erlock Switch D oor – Ch eck open, remove streamer, and close

Check that the ALE-20 flare ejector safety interlock switch door is open, then remove streamer andclose the door. If the door is found closed, check with maintenance personnel on the status of theALE-20 equipment. When the aircraft is on ground alert in a cocked configuration, the streamer willbe removed and the door closed.

9. Right Aft Exter ior Antennas – Checked

Check protruding antennas and antenna covers mounted on fuselage for condition, security, andcleanliness.

10. Right ALE-24 Wing Cha ff Dispenser Ports – Checked

Visually check th at exposed chaff pa ckages conform with mission requirements. E nsure th at no chaffpackages are engaged by the rollers.

INTERIOR INSPECTION

1. E q u ipm en t – S t ow e d

Ensure that no equipment is stowed on or near heating ducts, outlets,electrical w iring, or electronic equipment.

2. E ject ion S ea t :

a . H a t ch Lin k – C h eck ed

Check link connecting escape hatch to catapult safety pin-pull initiator.

b . Maintenance Sa fety P ins No. 2, 3 & 5 – Checked removed

Ensure that no streamer has been torn from a maintenance safety pin,thus inadvertently leaving the pin installed. If a maintenance safetypin is installed, the status of the seat will be ascertained prior to re-moval of the pin.

c. Ca t a pul t In it i a tor Sa fe ty P in-Pul l Cy linder – P in in place

Catapult init iator safety pin should extend through the catapult init iator. If the pin is pulledout, the init iator may have been fired; call maintenance immediately.

d . Manua l Ca t apult P in-Pul l Lever – Checked

Lever latched, pin-pull cylinder secured.



T.O. 1B-52H-1-13

Change 14 2-9


e. Ini t ia tor Tube Runs – Checked connected

Check tubes for condition, and for proper and secure connections.

f. I n er t ia R eel – C h ecked

Check inertia reel lock for proper functioning.

g . Shoulder S t ra p At t achment Fi t t ings – Connected

3. Man-Sea t Separa t or – Checked

Ensure that the nylon man-seat separator straps are placed on the bare seat . Survival kit is thenplaced over man-seat separa tor straps. Ensure the J ack Sha ft Cotter P in is insta l led and t he retaining rod has no lateral movement.

Absence of the J ack Sha ft Cott er Pin wil l result in lat eral movement ofthe man seat separator retaining rod, resulting in fai lure of the manseat separ at or aft er ejection.

4. P a r a c hu t e P r ef li gh t :

e. I n spect i on R ecor d :

(1) Inspection & Repack Da te – Ch ecked

(2) Automa tic Releas e Time & Altit ude Set ting – C hecked

f . Personal Locat or Beacon Lanya rd – Snapped/Unsna pped (as required)

For peacetime operations, the personal locator beacon lanyard must be configured for automatic op-eration. When mission requirements dictate the necessity to avoid detection and automatic actuation of the beacon is not desired, th e lanya rd must be configured for nona utoma tic (ma nua l) operation.

g . Ba i lout Oxygen B ot t le Pressure & Hose Connector – Checked

h. Pa rachute Arming Lanyard Anchor – Ins t a l led

Be certain that the parachute arming lanyard anchor is securely fas-tened in the attachment fi t t ing on the seat . Failure to attach the lan-yard anchor to the seat wil l necessitate manual operation after ejec-tion.

i . Pa rachute St raps – Adjus ted (as required)

j. U WAR S – C h ecked

Check security of fittings.

NOTE

U WARS B IT is a ma intena nce function. D o not perform U WARS B ITsince excessive B IT checks will degra de ba tt ery life.

5. G l oba l Sur vi va l K it :3.

a . Ki t Insta l led & Plunger Depressed – Checked

b. Ki t Release Handle – Checked down



T.O. 1B-52H-1-13

2-10 Change 12


c. Mode Selector Lever – AUTO

d. Ki t S t r aps to Pa rachute – Checked and a t t ached

Check that the attachment fi t t ings are properly connected to the kit , the attachment strapsthrea ded through th e safety belt , a nd t he quick-disconnect fi t t ings a re properly a tta ched t o thepara chute (with release butt ons on outside). G ra sp each survival kit st ra p and perform a quickjerk to ensure a positive link between the D-Ring and the survival kit straps.

Care wil l be taken to ensure that the survival kit attachment strapsar e properly thr eaded through t he safety belt .

6. Sa fety B elt Release Fi t t ings – Connected

7. Ci rcuit Breakers – Se t

Check all circuit breakers set to IN position on the ECM circuit breaker panel except those for the

chaff dispenser, flare ejector, rocket pods, RWR warning receiver, and the ALQ-172 (L ess DT SYS

15 & 16 IND CONT or DT CDU). Chaff dispenser and flare ejector circuit breakers will be left OUT

until ready to dispense chaff or flares and OUT after activity is completed. The L ess DT ALQ-172

SYS 15 & 16 IND C ONT, DT ALQ-172(V) CD U , a nd RWR WARNING RC VR circuit brea kers w illbe left OUT until requir ed IN by th e AFTER TAKE OFF – CLI MB checklist.

8. Ai r Out let Knobs:4.

a . U p per – As des ir ed

b . Low e r – As des ir ed

NOTE

These knob sett ings a re approximat e settings only. After t he cabin t em-perature has stabil ized, knob adjustment may then be varied sl ightlyfor crew comfort.

9. In terphone – Moni tor

The EW officer will monitor the interphone at the station he is occupying.

10. PI HM Assembly – Connect (as required)5.

a . B l ow e r – At t a ch ed a n d s ecu r e

Atta ch the blower t o the blower mounting bra cket. Ensure t ha t t he blower is fa stened securely

in the mounting bracket.

Failure to configure the AERP System properly may result in injury ordeat h t o aircrew member while operat ing in a conta minated environment.



T.O. 1B-52H-1-13

2-11


NOTE

• When seated, the crew member should configure the AERP Systemwith the blower hose connected to ventilation inlet, aircraft oxygenhose connected to the chemical-biological canister and the crossovervalve in the vertical position.

• When not seated, the crew member should configure the AERP Systemwith aircraft oxygen hose disconnected, the blower hose connected tothe chemical-biological can ister, an d th e crossover va lve in th e horizon-tal position.

b. Blower Electr ica l Connector – Connected

Remove the dust cover from the blower electrical receptacle and connect the blower into theelectr ical recepta cle.

c. O xy gen Reg ul a t or – S et

While holding breath, position the supply lever to ON and the emergency oxygen toggle leverto EMERGENCY.

Hold breath until steps d. and e. are complete. This will preclude theinhaling of toxic chemicals during the changeover from blower air tothe a ircra ft oxygen syst em.

d . B lower Hose – Disconnect

Disconnect the blower hose from the quick disconnect (QD) pigtail adapter.

e . Aircra f t Oxygen – Connected

Connect the aircraft oxygen hose to the quick disconnect (QD). Resume breathing.

If signs of hypoxia occur at high att itudes, ensure the oxygen systemquick disconnect (QD) fittings are properly connected and descend to asafe alt it ude as required.

f . B low e r Hose – Con n ect ed

Connect the blower hose to the ventilat ion inlet hose on the PIHM manifold.

Crewm embers using upwa rd ejection seat s w ill ensure tha t blower hoseis under seat a rmrest before hooking it up to the P IH M ma nifold.

g . Crossover Valve – Vert ica l

Rotat e the valve to the vertical posit ion a nd check tha t oxygen from the a ircraft syst em is flowinginto the mask and that filtered ambient air from the blower is flowing through the defog tubes.



T.O. 1B-52H-1-13

2-12 Change 4


h. Oxygen Regulator Emergency Toggle Lever – NORMAL

i . I n t er com U n i t – D iscon n ect a n d s t ow

j. P I HM Co mm u nica t ion Cor d – Con n ect

Connect the PIHM communication cord to the aircraft communication cord.

k . P I HM M a n if old – Con n ect

Connect th e man ifold to the CRU -60/P bra cket locat ed on the par a chute ha rness.

l . Emergency Oxygen Hose – Connect

Connect the emergency oxygen hose to the fitting on the manifold.

11. Oxygen System – Checked6.

a . Regula to r Dilu ter Lever – 100% OXYGEN

b . S h ut off Lev er – OF F

c. Mask & Hose – Check disconnect , then reconnect ma sk and hose

Ensure that oxygen supply hose is under seat armrest before hookupwith oxygen mask hose.

d . Di lu ter Va lve – Checked

Attempt to draw air through the oxygen mask. Ability to draw air indicates a defective diluter

va lve, oxygen hose, an d/or conn ections or ma sk.

e . Regula to r Diluter Lever – NORMAL

Place the diluter valve to NORMAL posit ion and draw air through the mask; if unable, thisindicat es tha t only 100% oxygen is ava ilable.

When the oxygen supply shutoff lever is positioned OFF, on theCR U -73/A, the regula tor dilut er lever should aut omat ically move to100% OXYG EN posit ion or it may only move ha lfwa y between theNORMAL an d 100%OXYG EN positions. When t he supply shut off leveris positioned OFF, do not force regulator diluter lever to NORMAL asthis will break the diluter lever.



T.O. 1B-52H-1-13

Change 9 2-13


NOTE

• If the diluter valve is stuck in the 100%position, this will prohibit thedetection of smoke or fumes when use of normal oxygen is required.

• If t he CRU -73A regulat or is insta lled, the crewmember w ill not be able

to draw air t hrough the system w ith t he shutoff lever OFF. The diluterlever may be moved to NORMAL with the shutoff lever OFF on someCR U -73A regula tors. The dilut er va lve will be in t he 100%oxygen posi-tion when the shutoff lever is OFF on all CRU-73A regulators.

f. S hu toff Lev er – ON

g . P r es su re – C h eck ed

Pressure gage reads approximately 300 psi.

h. Emergency Toggle Lever – TES T MASK

With m a sk disconnected a t one side of helmet, th e flow in dicat or should indicate continuous flow

i. Ma sk – Test

Attach mask to helmet and hold breath; indicator should indicate no flow.

NOTE

Flow condition may be indicat ed by a s light leak a round the face form.If light hand pressure against the mask does not stop the flow, thema sk is una ccepta ble.

j. Emergency Toggle Lever – NORMAL

k. Regulator Diluter Lever – NORMAL/100% (as required)

12. P or table Oxygen B ot t le – Serviced and stowed

Pressure should read approximately 300 psi and altitude selector knob positioned to NORM.

Oxygen will rapidly accelerate any ignit ion source, such as a spark,into a flash fire. Dirt , grease, and hand lotion all can act as a fuel tothe fire. Therefore, when recharging a portable oxygen bottle, crew-members will wear Nomex flight gloves and the helmet with visordown. These gloves should be free of oil and grease.

13. L igh t s – Checked7.

a . ALQ-122 Power Swi t ch – OFF

Check all panel lights off.

b. ALQ-153(V) Control-Indicator P an el – Checked

Check all panel lights off.

c. ALQ-172 Waveguide Low P ressure Light – Press-to-test



T.O. 1B-52H-1-13

2-14 Change 9


14. ECM Equipment Cont rols Prese t :8.

a . DT ALQ-172 Auxiliary Panel Switches:

(1) FWD S ystem Power Switch – FWD

(2) AFT System P ower Sw itch – AFT

(3) CDU Alt i tude Overr ide Sw itch – CDU ALT

b. ALQ-172 B lanking Swi t ch – HIG H

c. SI Control Pa nel Dimming & Audio Controls – Minimum

Rotate intensity and audio control knobs fully ccw.

NOTE

SI audio is obta ined thru th e SI mixer switch a t t he EW, gunner, or DI

sta t ion.

d . S I P ow er S w it ch – ON

e. M FD – Ad ju st ed

Rotate the brightness and contrast knobs fully counterclockwise (ccw). Adjust the brightnessknob clockwise (cw) until MFD illumination is visible, then rotate it ccw until MFD illuminationjust disappears. Adjust contrast knob until optimum presentation is obtained.

f . M FD P r es en t a t ion – C hecked

If, after adjusting brightness and contrast , the MFD has no presentation call maintenance.

g . SI Control P anel Dimming & Audio Control – Minimum

Rotate intensity and audio control knobs full counterclockwise.

h . SI S YSTEM P ower But t on-Indica t or – Press and release , a l l panel l ights and MFD off

i . S I Cont rol & Display Circu it Breakers – OUT

j. RWR Intensity & Audio Controls – Minimum

k. Fla re & Cha f f Counters – Checked

Check all counters for correct loading (should agree with Form 781 entry).

15. Refuel Valve Emergency Control Lever – CE NTER

16. Defense Instructor ’s St a t ion Oxygen Syst em – OFF a nd 100%



T.O. 1B-52H-1-13

Change 5 2-15


17. IFF:

a . IFF Mode 4 Computer – Encoded

Load the cryptographic variables using an electronic fill device.

- - - - - - CYZ-10 Key Loading - - - - - -k.

For CYZ-10 key loading refer to the combat crew communications checklist.

- - - - - - KYK-13 Key Loading - - - - - -l.

(1) Mode Select S wit ch – OFF/CH EC K

(2) Fil l Cable – Connect

Remove the d ust cover from t he fill connector port of the K IT-1C a nd connect t he K YK-13to th e KI T-1C usin g t he fill cable.

NOTE

The KYK -13 ma y be conn ected dir ectly t o the KI T-1C fill port a nd keysloaded w ithout using t he fill cable.

(3) Address Select Sw itch – Set

Set the address select switch to the posit ion where the first key is stored.

(4) Mode Select S witch – ON

(5) Mode Select S witch – OFF/CH EC K

(6) Address Select Sw itch – Set

Set the address select switch to the position where the second key is stored.

(7) Mode Select S witch – ON

Observe tha t t he KI T-1C fill LE D fla shes once.

NOTE

If t he fill LED doesn’t f la sh a fter both keys are loaded, the keys did notload properly. Ch eck th e KYK-13 for serviceability a nd t ha t correct key-ta pes ha ve been loa ded. Repeat steps (1) and (3) th rough (7).

(8) Mode Select S wit ch – OFF/CH EC K

(9) Fill Cable – Disconnect

Disconnect t he K YK-13 from t he K IT-1C a nd replace th e fill connector port dust cover.



T.O. 1B-52H-1-13

2-16


- - - - - - KOI-18 Key Loading - - - - - -

(1) Fil l Ca ble – Connect

Remove the d ust cover from t he fill connector port of the K IT-1C a nd connect t he K OI-18to th e KI T-1C us ing t he fill cable.

(2) Fir st Key tape – Load

Insert the first keytape and slowly pull it through the KOI-18.

NOTE

• Ensure the tape is correctly inserted with the guide holes in the tapealigned with the dots on the flip-up cover of the KOI-18.

• Never pull the tape backwards through the KOI-18. Doing so couldcause dam age to or distortion of the ta pe, causing the t ape to be unus-able.

(3) Fill Ca ble – Disconnect, then reconnect

NOTE

The fill cable must be disconnected then reconnected in order to suc-cessfully loa d t he second key.

(4) Second Keytape – Load

Insert the second keytape and slowly pull it through the KOI-18 while observing that thefill LED flashes once.

NOTE

• Ensure the tape is correctly inserted with the guide holes in the tapealigned with the dots on the flip-up cover of the KOI-18.

• Never pull the tape backwards through the KOI-18. Doing so couldcause dam age to or distortion of the ta pe, causing the t ape to be unus-able.

• If the fill LED doesn’t f lash after both keys are loaded, the keys didnot load properly. Check the KOI-18 for serviceability and that correctkeytapes are being used. Repeat steps (2) through (4).

(5) Fill Ca ble – Disconnect

Disconnect t he K OI-18 from the KI T-1C a nd replace th e fill connector port d ust cover.



T.O. 1B-52H-1-13

Change 9 2-17


(6) Keytapes – Remove and stow

Return the keytapes to the appropriate storage location (Comm kit).

A keyta pe should not be left in t he KOI -18 read er head for an extend edperiod of time. This w ill shorten fill ba tt ery life.

b. I FF Mod e 2 – S et

Set to appropriate sett ing if required.

18. Bunk Oxygen System – OFF and 100%

19. Gunner ’s Sta t ion Oxygen System – OFF and 100%

20. Upper Deck Fire Ext inguisher – Checked a nd stowed

Ensure that appropriate safety device (safety wire seal or locking pin lever as applicable) is installed.Check for fully serviced pressure.

21. Gunner ’s Sta t ion P or table Oxygen B ot t le – Serviced and stowed

Pressure should read approximately 300 psi and altitude selector knob positioned to NORM.

Oxygen will rapidly accelerate any ignit ion source, such as a spark,into a flash fire. Dirt , grease, and hand lotion all can act as a fuel tothe fire. Therefore, when recharging a portable oxygen bottle, crew-

members will wear Nomex flight gloves and the helmet with visordown. These gloves should be free of oil and grease.

22. Sextant Mount P or t – Check closed

23. Upper Deck Sliding Ha tch – Open and locked

The upper deck sliding hatch will be opened and locked prior to start-ing engines, takeoff, air refueling, low level activity, planned unusualma neuvers, penetra tion, an d landings.



T.O. 1B-52H-1-13

2-18 Change 9


24. Crew Report – Completed9.

a . P i lot a ctuates the emergency a larm switch to AB ANDON, switches interphone to ca l l posit ion,and announces, ‘‘Crew report.’’

b. The sequence for crew reporting is: N, G , EW, RN, CP, P, IN, DI, 10TH, I P.

c. All crewm embers will press ca ll button a nd report ‘‘(crewmember ’s) check complete’’ in sequence.The check consists of abandon signal and call operation. The EW officer may report from theDI position. On return to the seat, the interphone call button will be checked with the pilot.

25. Oxygen Regulator – OFF a nd 100%OXYG EN (if leaving the aircraft for an extended period of t ime)

All data on pages 2-19 and 2-20 (Deleted)



T.O. 1B-52H-1-13

Change 10 2-21

PRETAKEOFF PROCEDURES

STARTING ENGINES

Whenever contamina tion is suspected, 100% OXYG EN will be used

during ground operat ion a nd t akeoff.

1. Interphone, UH F & V/UH F DJ Ra dios – Monitored

2. Sta nd By t o Taxi – Report i f not ready to taxi

3. Pa rachute & Sa fe ty Bel t – Fas tened

• Tighten the para chute-survival kit a t t achment st ra ps as t ightly as pos-sible to prevent the safety belt from inflicting facial injuries duringejection ba ilout.

• Ensure tha t the parachute arming lanyard is not entangled in theparachute harness. Lanyard entanglement could cause failure in seatseparation and failure of the automatic features of the parachute.

NOTE

• If it becomes necessary to leave the seat, the crewmember should openthe safety belt and unbuckle the parachute harness, leaving the para-chute and survival kit in the seat . If the parachute is worn when leav-ing the seat , upon returning to the seat , it will be necessary to takeit off in order to reinstall the parachute and safety belt in the seat .

• Steps 3 thru 5 may be accomplished during taxi.

4. Oxygen Hose & B ailout Oxygen Bottle – Connected to ma sk

En sure tha t oxygen supply hose is under t he seat ar mrest before hook-up with oxygen ma sk hose.

5. Oxygen Regula tor – As required

NOTE

For formation takeoffs, the warning receiver and SI may be turned ona nd checked ear ly I AW norma l procedures in the AFTER TAKE OFF/CLIMB and EW CALIBRATION AND INTERFERENCE checklists.This may be done any time after switching to aircraft power. After com-pleting the warning receiver and SI check, the systems may then beused as an aid to monitor t he posit ion of other a ircraft .



T.O. 1B-52H-1-13

2-22 Change 9

PRETAKEOFF PROCEDURES (Cont)

TAXIING AND BEFORE LINEUP CHECKLIST (Copilot/EW reads)

Checklist appears in EW officer’s abbreviated checklist and will be read on request of the pilot.



T.O. 1B-52H-1-13

Change 12 2-23

INFLIGHT PROCEDURES

AFTER TAKEOFF/CLIMB

1. E C M E qu ipm en t :

a . WARNING RCVR AC Ci rcuit B reaker – In

b. L ess DT SYS 15 & SYS 16 IND CONT Circuit Breaker – In

The SYS 15 AND 16 IND CONT circuit breaker will be pushed in to assure activation of theALQ-172 system.

b. DT ALQ-172(V) CDU Circuit Breaker – In

The ALQ-172(V) CD U circuit brea ker w ill be pushed in to a ssure a ctivat ion of the ALQ-172 system

c. SI Cont rol & Display C i rcuit B reakers – In

d. All ECM equipment power sw itches (except ALQ-122, cha ff, and flare) wil l be turned on duringclimbout a fter flaps up. Ca re should be exercised tha t E CM t ra nsmitters a re in sta ndby excep

when they are to be used.

To prevent accident a l actua tion of th e tra nsmit ter sw itches, extremecare will be exercised when leaving or return ing to the seat .

NOTE

• Tempora rily pla ce one AN/ALQ-155 tra nsm itt er t o STBY 1 t o check t hesoftware revision number in the threat engage windows. Then set al ltransmitters to STBY 2.

• All RWR indicator control panel lights should illuminate momentarilyand one burst of Launch Audio may be heard when system is turnedon .

• The AN/ALQ-153(V) STB Y/OP E R pus hbu t t on w ill be pla ced in t he op-erat e position only wh en aut horized by Air Force a nd MAJ COM direc-tives.

• When AN/ALQ-153(V) P OWER push but ton is pressed , t he P OWER a ndTES T/MALF light s come on for dura tion of w a rmu p period (minim umof 42 to a ma ximum of 130 seconds). Followin g w a rmup, t he P OWERa nd TES T/MALF ligh ts g o off a nd t he S TB Y/OP ER light comes on (a m-ber).

• The AN/ALQ-172 is capa ble of inter fering w ith precision appr oach r a -dar s. On tra ining sorties, the L ess DT S TAND B Y/OP ER ATE pushb ut -

tons; DT MASTER S TAND B Y/OP ER ATE pu shbu tt on w ill be pla ced inth e OPE RATE position, only w hen a uth orized by Air Force a nd MAJ -COM directives.



T.O. 1B-52H-1-13

2-24

INFLIGHT PROCEDURES (Cont)

2. Oxygen Check – Completed

a. During t he climb, copilot requests a n oxygen check a t 12,000 feet . The sequence for oxygen reportis E W officer, ra da r n a viga tor, pilot/copilot. The reporting crewmember will visua lly check othercrewmembers for alertness. He will report oxygen check for the compartment. Oxygen panel ateach occupied crew position will be checked on all oxygen checks for:

(1) Oxygen Supply Shutoff Lever – ON

(2) Regulator Diluter Lever – As required

(3) P ressure – 300 psi

(4) Flow Indicat or – Functions norma lly

(5) Em ergency Toggle Lever – NORMAL

b. EW officer, ra da r na viga tor, a nd pilot/copilot report ‘‘Oxygen panels checked.’’ In a ddition, pilot/copilot repor t s ‘‘Ca bin a lt it ud e ______________________ feet .’’

c. Copilot requests oxygen check at level-off and during cruise at 1-hour interva ls when cabin alt i-tude is below 12,000 feet, at 30-minute intervals when cabin altitude is 12,000 to 25,000 feet,a n d a t n o lo n g e r t h a n 1 0 - m in u t e in t e r va l s w h e n ca b in a l t i t u d e i s a b o ve 2 5 , 0 0 0 f e e t .Crewmembers will report when complete.

3. Level-Off Sta tion Check – Accomplished

Crewmembers will accomplish station checks at level-off, at approximately 30 minute intervals dur-ing cruise, and prior to leaving crew position during flight. A check for systems operation and properswitch sett ings for prevailing conditions will be ma de during each st at ion check. Sta tion checks w illinclude circuit breakers and equipment stowage.



T.O. 1B-52H-1-13

Change 5 2-25


EW CALIBRATION AND INTERFERENCE

The calibration of ECM equipment and interference to and from other aircraft systems will be determinedas soon as practical after takeoff. The purpose of this check is to determine whether the equipment meetsthe minimum requirements for dependable operation. If this abbreviated check reveals a malfunction orfa ilure a nd condi tions permit , refer to t he a pplicable port ion of T.O. 1B -52H-1-13 an d T.O. 1B -52H-1-13-1

Malfunction, Analysis, an d E mergency Operation Section. E ach t ra nsmitt er will be checked for norma l efficiency by comparing the output w ith like systems, ta king the an tenna posit ion int o consideration. Tra nsmitters will be momentarily activated in a clear band, consistent with clearance and operating restrict ions. Ontra ining missions only, wh en the miss ion profile precludes accomplishing t he entire check prior to th e HH CLHE W, only systems a nd frequ ency band s program med for use will be checked. Devia tions from checklissequence to comply with local area clearances are authorized. The entire crew must be alerted for coordina-tion during this check. UHF guard frequency must be monitored throughout the check.

NOTE

• Receivers and appropriate transmitters may be checked during climbcommensurate with clearance and crew coordination.

• ALQ-155 transmitters will be placed in STBY 2 mode no more than 30

minut es prior to EC M activit y a nd placed in STB Y 1/wa rmup modeafter completion of ECM activity unless scheduled for activity within30 minutes.

• Items t ha t a re circled w ill be repeated for each receiver band tra ce an dlike transmitter.

1. Mixer Switches – As required

2. ALR-20A Less DS :

a . Sweep Width Controls (7) – Full CW

b. RF Level Controls (7) – Checked, ad just for optimum signa l presentat ion

Check for a change in signal amplitude by varying each RF level control, then set to optimumlevel.

NOTE

Use RF t est if no signals a re ava ilable.

c. S ca le I llum in a t ion – O pt imu m

d. Scope P resen ta t ion – Checked

Check for presence of known signals and interference.

e . RF Test But ton – P ressed, signals checked

f . Expansion Trace Selectors A & B – Checked

Set expa nsion A selector on the desired t ra ce. Monitor expan sion tra ce A for display of this t ra ceRF test may be used. Repeat procedures for expansion trace B.



T.O. 1B-52H-1-13

2-26 Change 5


g . Righ t & Lef t Mark Cont rols – Checked

Vary the mark control. Mark should move across both expansion traces. Repeat procedure forleft mark control.

h . Sw eep Width Control – Checked, then full CCW

Rotate the sweep width control CCW from the full CW position to select a segment approximately1/4 of the tr a ce. Va ry t he ma nua l frequency contr ol a nd t he segment sh ould move a cross th etrace. Continue rotation of the sweep width control to the full CCW position (in detent).

i . Manua l Frequency Control – Adjust to signal frequency

NOTE

Use RF t est if no signals a re present.

j. Volume Cont rol – Adjusted

k . Sweep Width Cont rol – Fu ll CW

2. ALR-20A DS :

a . Sw eep Width Controls (7) – Full CW

b. RF Level Controls (7) – Checked, adjust for optimum signal presenta tion

Check for a change in signal amplitude by varying each RF level control, then set to optimumlevel.

NOTE

Use RF test if no signa ls are ava ilable.

c. M a s t er I llum in a t ion – Opt imu m

d . E d g e I l lu m in a t ion – Opt imu m

e. S ca le I llum in a t ion – O pt imu m

f . S cope P r esen t a t i on – Ch eck ed

Check for presence of known signals and interference.

g . Pers is tence – Checked and set

Check control of persistence levels P0 through P4 and set for optimum viewing of transmitter

operation and calibration.

h . RF Test B ut ton – P ressed, signals checked



T.O. 1B-52H-1-13



i Expansion Trace Se lector s A & B – Checked

Set expa nsion A selector on the desired t ra ce. Monitor expan sion tra ce A for display of this t ra ceRF test may be used. Repeat procedures for expansion trace B.

j. Righ t & Lef t Mark Cont rols – Checked

Vary the mark control. Mark should move across both expansion traces. Repeat procedure forleft mark control.

k . Sweep Width Control – Checked, then full CCW

Rotate the sweep width control CCW from the full CW position to select a segment approximately1/4 of the tr a ce. Va ry t he ma nua l frequency cont rol and t he segment sh ould move a cross th etrace. Continue rotation of the sweep width control to the full CCW position (in detent).

l . Manual Frequency Control – Adjust to signal frequency

NOTE

Use RF t est if no signals a re present.

m. Volume Control – Adjusted

n . Sweep Width Cont rol – Fu l l CW

o. BIT Se lect Swi t ch – BIT 1

BIT Status checked.

p. B I T S elect S w i t ch – OF F

3. RWR:

a . Warn ing Rece iver Mixer Swi t ch – Se t

b. Audio & Intensity Controls – Opt imum

Adjust intensity control clockwise until an optimum display of symbols is obtained on the RWRIt may be necessary to activate the test function for symbol presentation.

c . Self-Test – Accomplished

Any panel light that does not illuminate should be pressed to verify it comes on. Verify correctsoftware version is loaded as annotated in Form 781.

d. CRT Indica t or – Check for interference

NOTE

If interference is received, ha ve rada r na vigator place the OAS ra dar inSTAND B Y, a s n ecessa ry, to isolate interference source.



BL



T.O. 1B-52H-1-13

Change 12 2-27


4. ALQ-153(V):

a . ALQ-153 Mixer Swi t ch – Se t

b. LAMPS P US H TO TEST Control – P ressed, br ightness adjusted

All control indicator lights should come on and may be adjusted to desired brightness by rotatingthe control knob. Range indicator reads 8.8.

c . TONE P US H TO TES T Control – Pressed, volume adjusted

Missile warning tone should be audible (EW and G) for approximately 3 seconds. Adjust volumeas desired by rotating the control knob.

d . TTI E NAB/INHBT Pushbut ton – INHB T

e. MIN RNG ENAB/INHB T – ENAB , set to four th set t ing

f. TES T/MALF P ushbutton – P ressed, self-test accomplished

(1) TES T, MIN RNG ENAB, a nd 0-3 lights – ON

Lights remain on for duration of the test (approximately 15 seconds). Init ial reading in thera nge indicat or should be a pproxima tely equa l to the groundspeed read out (w ithin 5%) othe OAS ground speed.

(2) J AM Ligh t – On

It should remain on for approximately 4 seconds.

(3) LMSL & RMSL Lights – On

After a pproxima tely 8 1/2 seconds th ese lights come on, t he ra nge indica tor rea ds 1.0 an da 3 second tone burst sounds.

(4) Ra nge Indicat or – Decreases in steps to 0.5

The CM TRIG light should come on at the time specified and remains on until 0.5.

(5) 0-3, LMSL, RM SL & TES T Light s – Off, syst em to STB Y

After 15 seconds, these lights should go out and the range indicator is blank. STBY lightis on and the system is ready for normal operation.

g . STBY/OPE R Pushbut ton – OPE R (i f applicable)

Check receivers for presentation and interference. The MALF light will illuminate momentarilywhile transit ioning from standby to operate or operate to standby. Although the automatic BIToccurs every 1.5 seconds, it may take from 15 to 70 seconds before a BIT failure is displayed

on t he C /I.

NOTE

Before going back into the OPER mode after the test , the systemshould remain in STBY for approximately 3 seconds, otherwise a bit er-ror w ill occur.

h . STBY/OPER P ushbut ton – STBY



T.O. 1B-52H-1-13

2-28 Change 12


5. ALT-16A:

a . Channe l Se lector Bu t tons – Pressed a s desi red

b . Power Se lector – TRANSMIT

c. Signal Presenta t ion, Calibra t ion & Inter ference – Checked

d. Look-Thru Pa nel Controls – Checked

Check for proper operation of the Look-Thru buttons applicable to each transmitter.

e . Power Se lector – STANDBY

6. ALQ-122 Power Switch – ON

NOTE

ALT-16A tr an smit ters w ill not operat e in the norma l bar ra ge modewit h th e ALQ-122 system power t urned on.

7. ALT-32:

a . Spot A & B Ba ndwidth Cont rols – CCW to min imum

b. Spot A & B Frequency Controls – Set to clear frequencies

c. Transmit Channe l Se lector – A

d. Signal P resenta t ion, Calibra t ion & Inter ference – Checked

e . Spot A Ba ndwidth Cont rol – Checked and CCW

f . Tr a n smi t Ch a n nel S elect or – B

g. Signal Presenta t ion, Calibra t ion & Inter ference – Checked

h . Spot B Ba ndwidth Cont rol – Checked and CCW

i. Transmit Channe l Selector – A & B

Check that both A & B signals are present.

j. Transmit Cha nnel Se lector – BARRAGE 1, 2, 3, and 4

k. Signal P resenta t ion, Calibra t ion & Inter ference – Checked

l . Look-Thru Pa nel Cont rols – Checked

Check for operation of the Look-Thru Buttons applicable to each transmitter.

m. Transmit Cha nnel Selector – STBY1.2.3.4.5.6.7.



T.O. 1B-52H-1-13

Change 12 2-29

INFLIGHT PROCEDURES (Cont)a.b.c.d.e.

8. ALQ-155 D/E B and:

a . P r og ra m S elect or – B ARR

b . M a n ua l Ra t e Con t r ol – F u ll CW

c. R F B a n dw id t h C on t rol – F M OF F

d. Center Frequency Control – Set to clear frequency

e. J O G /RE S S w it ch – P r e ssed

Pressing the switch will ensure no ERR malfunction exists within the system.

f . M od e S e lect or – M AN

g. Signal Presenta t ion, Calibra t ion & Inter ference – Checked

h . RF Bandwid th Cont rol – Checked and FM OFF

Increasing RF bandwidth may cause the center frequency knob tomove. Do not use excessive force or damage to the geartrain will occur.Instead, rotate the center frequency knob to allow free movement of theRF bandwidth knob.

i . D E S S w i t ch – P r essed , si gn a l ch eck ed

Check for clear band ar ound system search w idth. The LOK light should not illuminate a nd th ecenter frequency control should operate normally.

j . ALR-20A Expansion Trace Selector – Set to required trace

k. ALR-20A Sweep Width Control – SetSelect approximat ely 1/4 of ma in tra ce. P osition selected segment a round tra nsmit ter signa l.

l . P r og ra m m er – C h eck ed

NOTE

Refer t o T.O. 1B -52H-1-13-1, ALQ-155 Norm a l Opera tion/E CIC , st eps 1th rough 3 for steps (1) th rough (3) below.

(1) P rogram Selector – 6

(2) RF Ba ndwidth – Se t a s required

Check visually for modulation.


(4) P rogra m Selector – MAN, check for coincidence a nd modula tion

(5) ALR-20A Sw eep Width C ontrol – Full CC W

Tune to tra nsmitt er signal.



T.O. 1B-52H-1-13

2-30 Change 12


(6) Manua l Rate Control – Checked a nd full CW

Ch eck for a udible increas e/decrease in pulse ra te.

(7) P rogram S elector – A2

Check audible change in pulse rate.


Check audible change in pulse rate.

m. Program Se lector – BARR

n. ALR-20A Sweep Width Control – Full CW

NOTE

St eps p an d q must be accomplished w ithin 30 seconds a fter init iat ingstep o.

o. Mode Selector – BIT, check for signal presence

Sw itch is sprin g-loa ded to t he AUTO position. If test is successful, all light s except FAU w ill comeon. If self-test is not successful, the ERR light will come on and the THREAT ENGAGED indica-tor will display a character relat ing to the specific malfunction.

p . DES S wi t ch – Pressed , s igna l checked

Signal frequency and bandwidth should increase.

q . J OG/RES S wi t ch – P ressed , s igna l checked

Signal should disappear.

r. Mode Selector – Warmup mode

9. ALQ-155 E/F B and:

a . P r og ra m S elect or – B ARR

b . M a n ua l Ra t e Con t r ol – F u ll CW

c. R F B a n dw i dt h C on t rol – F M OF F

d. Center Frequency Control – Set to clear frequency

e. J O G /RE S S w it ch – P r e ssed


f . M od e S elect or – M AN

g. Signal P resenta t ion, Calibra t ion, & Inter ference – Checked



T.O. 1B-52H-1-13

Change 10 2-31


h . RF Bandwid th Cont rol – Checked and FM OFF

Increasing RF bandwidth may cause the center frequency knob tomove. Do not use excessive force or damage to the geartrain will occur.Inst ead, rota te th e center frequency knob to a llow free movement of theRF ba ndwidth knob.

i . DES Switch – Pressed, signal checked; set signal to expected threat frequency

Check for clear band around system search width. The LOK light should not illuminate and thecenter frequency control should operate normally. Set to an expected threat frequency for thecoinciden ce check.

j. ALR-20A Expansion Tra ce Selector – Set to required trace

k. ALR-20A Sweep Width Control – Set

Select approximat ely 1/4 of ma in tra ce. P osition selected segment a round tra nsm itt er signa l.

l. (D elet ed)

m. Programmer – Checked

NOTE

Refer to T.O. 1B -52H-1-13-1, ALQ-155 Norma l Opera tion/E CI C, st eps 1th rough 3 for st eps (1) throug h (3) below.


(2) RF B andwid th – Set a s requ ired


(3) RF B andwid th – Set a s requ ired

(4) P rogram Selector – MAN, check for coincidence a nd modula tion

(5) ALR-20A Sw eep Width C ontrol – Full CC W


(6) Manua l Rate Control – Checked and full CW

Ch eck for a udible increa se/decrease of pulse r a te.


Check for audible change in pulse rate.



T.O. 1B-52H-1-13

2-32 Change 10




(9) P rogram Selector – A1


n . Slave Funct ion (Systems 5 & 8) – Checked

(1) P rogram Selector – Slave

(2) Master P rogram S elector – 2


o. Program Se lector (s) – BARR

p. ALR-20A Sw eep Width Control – Full CW

NOTE

Steps r and s must be accomplished within 30 seconds after init iat ingstep q.

q. Mode Selector – BIT, check for signal presence

Sw itch is spring -loaded t o the AUTO position. If test is successful, a ll lights except FAU w ill comeon. If self-test is not successful, the ERR light will come on and the THREAT ENGAGED indica-tor will display a character relat ing to the specific malfunction.

r. D E S S w i t ch – P r e ssed , si gn a l ch eck ed


s . J OG/RES S wi t ch – Pressed, s igna l checked


t . Mode Se lector – Warmup mode

10. ALQ-155 G /H /I B a nd:

a . Antenna Se lector – FWD (Sys tems 1 and 2)

b . P r og ra m S elect or – B ARR

c. M a n ua l Ra t e Con t r ol – F u ll CW

d . RF B a n d w id t h Con t r ol – F M O FF

e. Center Frequency Control – Set to clear frequency

f . J OG /R E S S w it ch – P r es sed




T.O. 1B-52H-1-13

Change 5 2-33

INFLIGHT PROCEDURES (Cont)11.a.b.c.d.e.f.

g. Mode Sw it ch :

(1) ALQ-172 FWD Wa veguide Light (Sy stem 1 an d 2) - Ch ecked OFF

(2) Mode Selector Sw itch - MAN

h. Signal P resenta t ion, Calibra t ion & Inter ference – Checked

NOTE

When th e ALQ-155 systems 1 a nd/or 2 tra nsm itt ers ar e tra nsmit tingwit h t he forwar d looking a ntenna selected, and the ALQ-172 FWD P Dis in OP ER , system 1 a nd/or 2 will be blanked at a low duty cycle atALQ-155 frequencies above approximately 1.73 GHz below the maxi-mum dial indication. This blanking also occurs with the ALQ-155 sys-tem 1 a nd/or 2 omni-directional a nt enna selected, a nd eith er th eALQ-172 FWD P D or AFT P D in OP ER .

i . RF B a n d w idt h Con t r ol – Ch eck ed a n d F M O FF

Increasing RF bandwidth may cause the center frequency knob tomove. Do not use excessive force or damage to the geartrain will occur.Inst ead, rota te th e center frequency knob to a llow free movement of theRF ba ndwidth knob.

j. DES SWITCH – Pressed, signal checked; set signal to expected threat frequency

Check for clear band around system search width. The LOK light should not illuminate and thecenter frequency control should operate normally. Set to an expected threat frequency for thecoinciden ce check.

k. ALR-20A Expansion Tra ce Selector – Set to required tra ce

l . ALR-20A Sw eep Width Control – Set

Select approximat ely 1/4 of ma in tra ce. P osition selected segment a round tra nsm itt er signa l.

m. P rogram S elector – MAN, check for coincidence and m odulat ion

Adjustments of manual rate control and RF level may be necessary to properly display coinci-dence of back and peak power levels. Check visually for modulation.

n . P r og r a m mer – Check ed (G b a n d)

(1) P rogrammer Selector – 2


(2) P rogram S elector (Systems 4 & 6) – Slave

(3) Master P rogram S elector – 2




T.O. 1B-52H-1-13

2-34


n . Programmer – Checked (H/I band)

(1) ALR-20A Sw eep Width Control – Full CC W


(2) Manual Ra te Control – Checked and F ull CW

Ch eck for a udible increa se/decrease of pulse r a te.

(3) ALR-20A Sw eep Width C ontrol – Set

Select approxima tely 1/4 of ma in tra ce. Position selected segment a round tra nsm itt er signal.

NOTE

Refer to T.O. 1B -52H-1-13-1, ALQ-155 Norm a l Oper a t ion/E C IC – H /Ifor st eps (4) th ru (7).







o. Program Se lector (s) – BARR

p. ALR-20A Sw eep Width Control – Full CW

q. Antenna Selector – Checked (Systems 1 & 2)

(1) OMNI – Pressed

(2) Signal P resenta t ion a nd Int er ference – Checked

r. Omni Antenna Monitor Switch – P ressed, signal presenta t ion checked

NOTE

Steps t and u must be accomplished within 30 seconds after init iat ingstep s.

s. Mode Selector – B IT, check for signal presence

Sw itch is spring -loaded t o the AUTO position. If test is successful, a ll lights except FAU w ill comeon. If self-test is not successful, the ERR light will come on and the THREAT ENGAGED indica-tor will display a character relat ing to the specific malfunction.



T.O. 1B-52H-1-13

Change 12 2-35


t . DES Swi tch – Pressed , s igna l checked


u. J OG/RES Sw i tch – Pressed, signal checked


v. Mode Selector – Warmup mode

11. ALQ-122:1.

a . Lamp Test – Accomplished

b . M od e S w it ch – XM IT

c. ALT-16A Power S electors – TRANSMIT

d. Test-in-P rogress Sw itch – P ressed, self-test a ccomplished

e. ALT-16A Power Selectors – STANDB Y

f. Mod e S w it ch – S TB Y

12. DT ALQ-172:2.

a. ALQ-172 Waveguide Low P ressure War ning Lights – P ress to test , ensure off

b. MASTER S TANDB Y/OPE RATE I ndicat or – Press, indicat or displays OPE R

c. C D U S t a t us P a g e – S el ect

d. CDU G o Indicator – Press, f ixed l ights and indicators checked

e. FWD & AFT STANDB Y/OPE RATE Indicators – P ress, unti l al l syst ems are in operat e

f . C D U TE S T S w it ch – P r es s

Press to accomplish self-test. Verify the correct software versions are loaded for the ALQ-172FWD, AFT, CD U , a nd H I/LO S ymbol files. Verify LRU sta tus.

g. FWD & AFT STANDB Y/OPE RATE I ndicators – Press, unti l a l l systems are in sta ndby

h. MASTER STANDB Y/OPE RATE Indicator – P ress, indicator displays STB Y



T.O. 1B-52H-1-13

2-36 Change 12


12. L ess

DT ALQ-172:3.

a . Lamp Test P ushbutton – Pressed, indicat ors checked

Press to test ALQ-172 indicator control panel, monitor and waveguide low pressure indicatorl ights.

b. Self-Test S elector – P ressed, self-test a ccomplished

Check for receiver interference during self-test cycle. Verify correct software version is loadedfor the ALQ-172 as annotated in AFTO Form 781.

NOTE

The ALQ-172 blanking switch will be in the high position to ensure avalid self-test.

13. S I S ys tem : 4.

a . Sy st em P ow e r – C h eck on

Check operational data and status appears on the SI MFD.

b . S I Mixer S w it ch – S et

c. Audio Cont rol s – Opt imum

d. System Test – Accomplished

P ress and release S YS TES T button. En sure missile launch t one is a udible and verify initiat edB IT display. Set a udio control to mid ra nge. Press a nd release SYS TES T button a gain to returnto the operational data and status presentation.

e . BI T Sta tus – Verif ied, note softwa re version

P ress and r elease B IT STATUS button a nd verify opera tional B IT sta tus on th e SI MFD. Notesoftware versions of respective sensors for optimum operational employment. Press and releaseB IT STATUS button a gain to return t o the operat iona l dat a an d sta tus display.



T.O. 1B-52H-1-13

Change 7 2-37


EW EQUIPMENT SET

Operational ECM equipment will be preset for use as soon as practical after completing the EQUIPMENTCALIBR ATION AND I NTER FE RE NCE CH EC K. Additiona lly, a pplicable portions of t his checklist ma y beused throughout penetration and withdrawal to verify equipment readiness and sett ings. On training mis-sions, applicable portions of this checklist will be used prior to and after all ECM activity. (Successive runs

ag a inst a single site do not require reaccomplishment of th is checklist.) Tra nsm itt ers will not be react ivat edAntenna locations, intelligence data, and the results of the calibration and interference check will be consid-ered when presett ing equipment.

NOTE

• ALQ-155 transmitters will be placed in STBY 2 mode no more than 30minutes prior to E CM a ctivity a nd placed in WARMU P mode aftercompletion of ECM activity unless scheduled for activity within 30 min-utes.

• Items t ha t a re circled w ill be repeated for each receiver band tra ce an dlike transmitter.

1. Mixer Switches – As required

2. ALR-20A:

a . C on t rols – Opt im um

b. Expansion Traces – Se t

Adjust the expansion traces to monitor a threat frequency band.

c. Pe r si st en ce – O pt im u m DS

3. RWR:

a . Audio Cont rol – Opt imum

b . D imm in g Con t r ol – Opt imu m

c. M od e B u t t on – As r eq u ir ed

d . Al t itude But ton – As requ ired

e. U n k now n B u t t on – As r eq u ir ed

f . Th r ea t F i le – As r eq u ir ed



T.O. 1B-52H-1-13

2-38


4. ALQ-122:

a . P r og ra m S w i t ch – As r eq u ir ed

b . Cover Swi t ch – As required

c. M od e S w i t ch – As r eq u ir ed

d. ALT-16A Power Selector – As required

NOTE

For proper opera tion of t he ALQ-122, both ALT-16A tr a nsm itt ers w illbe in radiate and should be placed in standby when operation is nolonger r equir ed t o conser ve TWT life.

5. ALT-16A:

a . Ch a n n el B u t t on s – P r e ssed a s r eq u ir ed

6. ALT-32:

a . Frequency & Ba ndwidth Controls – As required

7. ALQ-155:

a . Transmit ter Mode – As required

b . Ct r Freq & RF Ba ndwid th Cont rols – As requ ired

Increasing RF bandwidth may cause the center frequency knob tomove. Do not use excessive force or damage to the geartrain will occur.Instea d, rotat e the center frequency knob to allow free movement of theRF bandwidth knob.

c. Program Se lector – As requ ired

d . Manua l Ra te Cont rol – As requ ired

e. G/H Antenna S elector – As required

8. AL E -24:

a . P ow er Sw it ch – OF F

b. Programmer Se lector Sw i t ches – As requ ired

c. D i spen se S w i t ch es – O FF



T.O. 1B-52H-1-13

2-39


d . Circu it Breaker – In or a s d irected

NOTE

All chaff circuit breakers available to the EW officer will be pulled atall times except when accomplishing this checklist in preparation for

actual dispensing of chaff. The proper positioning of circuit breakersw ill then be governed by existing directives.

e . Power Swi t ch – ON or a s di rected

f . P ress-to-Test Lights – Tested

g . Auto Mode Swi t ch – As requ ired

9. AL E -20:

a . P ow er Sw it ch – OF F

b . F la r e P r og ra m – As r eq u ir ed

c. Transfer Swi t ch – Checked OFF

d. P i lot ’s F la re Set P ower Swi t ch – ON or a s d irected

NOTE

The pilot’s ALE-20 flare set power switch will be in the OFF positionan d fla re circuit brea kers pulled a t all t imes except w hen a ccomplish-ing this checklist in preparation for actual dispensing of flares or to dryfire the system. (This check is only necessary for initial accomplish-ment of this checklist unless flar es are a ctually programmed t o be dis-pensed.) The proper positioning of a ppropria te ALE -20 swit ches dur ingprepar at ion for a ctual d ispensing w ill then be governed by existing di-rectives.

e . Circu it Breakers – In or a s d irected

f . Po w er S w it ch – O N or a s di rect ed

Removing power from the system while a program is in progress canresult in the clutch coil cam being stuck in the detent position makingprogram mode inoperative.

g. P ress-to-Test Lights – Tested

h . Auto Mode Swi t ch – As required

i . Crew Not i fied – Accomplished

NOTE

Prior to any normal dispensing or emergency jett isoning of flares, theEW officer will notify a ll crew members of his intend ed a ction.



T.O. 1B-52H-1-13

2-40 Change 9


10. DT ALQ-172:10.

a . Al t it u de – As r eq u ir ed

b. FWD & AFT Syst ems Sta ndby/Operat e – As required

c. F i le Se lect – As requ ired

NOTE

The ALQ-172 blanking switch will be in HIGH position at all times ex-cept when excessive OAS interference is experienced.

10. Less DT ALQ-172:

d . Mode Selector – As required

e. Sta ndby/Operate Funct ion S elector – As required

f . S ecu r e S w i t ch – As r eq u ir ed

NOTE

The ALQ-172 blanking switch will be in HIGH position at all times ex-cept when excessive OAS interference is experienced.

11. ALQ-153(V):

a . TTI Cont rol – As required

b . MIN RNG Cont rol – As requ ired

c. TTI & MIN RNG ENAB /INHB T P ushbut ton – As required

d. HI/LO ALT P ushbut ton – As required

e. STBY/OPE R Pushbut ton – As required

12. Master E xpendables Cont rol P ane l:

a . F la r e B u r st I n t er va l S elect or – S et

b . F la re In terva l Se lector – As requ ired

13. S I S y s t em Con t r ol Pa n e l

a . Au dio Con t r ol – Op timu m

b . D imm in g Con t r ol – Op timu m

c. ALQ-155 MODE But ton-Indica t or – As required

d . U n k now n B u t t on – As r eq u ir ed



T.O. 1B-52H-1-13

Change 12 2-41


PRELANDING OPERATIONAL CHECK

1. P eriscopic Sexta nt – Stowed, port closed

2. Special Weapons Manua l Lock Ha ndle – Stowed, door closed

3. Prelanding Operat ional Check – Completed

All ECM equipment not used for ECM runs during the sortie or checked during the EW CALIBRA-TION AND INTERFERENCE CHECK will be checked for operation prior to landing in accordancewith procedures for the condensed check as outlined in the EW CALIBRATION AND INTERFER-ENCE checklist, consistent with clearance requirements and operating restrictions. Discrepancieswill be entered in the appropriate forms.

4. E C M E qu ipm en t :

a . ALQ-155 – WARMUP

b. ALQ-122 an d ALT-16/32A – STAND B Y

c. Cha f f & Flare Power Swi tches – OFF

d. Cha f f , F la re , and Rocket C i rcui t Breakers – Out

e . RWR In tens ity Cont rol – Minimum

f . RWR Power But ton – Pressed, POWER l igh t out

g. WARNING RCVR AC Circui t Breaker – Out

h. ALQ-153 Power Pushbutton – P ressed, a l l panel l ights off

i . ALR-20A Power Swi tch – OFF

j. DT ALQ-172 CDU P ower P ushbut ton – P ressed, G o Indicat or (FWD, AFT, CD U ) OFF

k. DT ALQ-172 Auxiliary P a nel Syst em Forwa rd P ower P ushbut ton/Ind icator – FWD OF F

l. DT ALQ-172 Auxiliary P a nel S ystem AFT Power P ushbut ton/Ind icator – AFT OFF

m. DT ALQ-172(V) CDU Circuit Breaker – Out

The ALQ-172(V) CD U circuit brea ker w ill be pulled to a ssur e dea ctiva tion of th e ALQ-172 system

n. L ess

DT ALQ-172 Power Pushbutton – Pressed, all panel lights off

o. L ess DT SYS 15 & 16 IND CONT Circuit Breaker – Out

The SYS 15 & 16 IND CONT circuit breaker will be pulled to assure deactivation of the ALQ-172system.

p. SI C ontrol Panel Intensity & Audio Controls – Minimum

q. SI S YSTEM P OWER B utton-Indicator – Press and release, a l l panel l ights off

r. SI Cont rol & Displ ay C i rcuit B reakers – Out

If one or more generators are off the line, all electronic warfare equip-ment not required for defense of the aircraft will be turned off prior todescent for landin g.

5. Sa fe ty Be lt & Pa rachute Harness – Fas tened



T.O. 1B-52H-1-13

2-42 Change 9

AIR REFUELING PROCEDURES

RENDEZVOUS

During air refueling, a possibility exists that fuel may enter the verti-

cal fin a ir scoop and form a combustible mixture in the a ft equipmentcompa rt men ts . P la cing t he ALT-16A, ALT-32A a nd AL Q-122 inSTANDB Y, a nd ALQ-155s in WARMU P, 15 min ut es prior t o initia l con-ta ct until 15 minutes after t erminat ion of final conta ct will a llow equip-ment to cool prior to refueling and ensure dissipation of combustiblemixtures after refueling. This procedure is applicable to all refuelingconta cts. Both forwa rd a nd a ft tra nsmitt ers will be placed in STAND-B Y to preclude the ina dvertent turning on of the aft tra nsmitt ers.

NOTE

• Normally, the rendezvous checklist will be started at least 30 minutesprior to the planned rendezvous control time.

• The EW officer should use all available ECM receivers to monitor theposition of the tanker throughout rendezvous. This is especially criticalduring an overrun condition when the tanker is aft of the four – eighto’clock position.

1. ALT-16A, ALT-32A & ALQ-122 – STAND B Y

Not later than 15 minutes prior to the first contact .

2. ALQ-172 FWD & AFT Syst ems – Sta ndby

3. ALQ-155s – WARMU P


4. ALQ-153 – OFF


Due to the high operating temperature of the ALQ-153 in the standbymode, the ALQ-153 will be turned OFF 15 minutes prior to initial con-ta ct until 15 minutes a fter termina tion of final contact . This w ill allow the equipment to cool prior to refueling and ensure dissipation of com-bustible mixtures after refueling. This procedure is applicable to all

contacts.

5. P er iscopic Sexta nt – Stowed, por t closed



T.O. 1B-52H-1-13

Change 9 2-43

AIR REFUELING PROCEDURES (Cont)

6. Upper Deck Sliding Ha tch – Open and locked

• Upper deck sliding hatch will be open and locked prior to air refueling.

• If the control cabin is not pressurized, all unnecessary electrical equip-ment should be turned off.

CONTACT

1. Fuel & Hydra ulic Lines – Check for leaks

Check visually from seat for evidence of fuel or hydraulic leaks. Report only if leaks occur.

Do not tr an smit on the HF r adio when in conta ct with or when in close

proximity to the K C-10 air refueling boom. Tra nsm itt ing on the H Fradio under these conditions may cause uncommanded movement ofthe KC-10 air refueling boom, endangering the tanker or receiver air-craft and crews.

POST AIR REFUELING

1. ALT-16A, ALT-32A & ALQ-122 – STAND B Y

Allow E CM t ran smitters a nd ALQ-122 to rema in in sta ndby not less tha n 15 minutes after termination of final contact.

2. ALQ-172 FWD & AFT Syst ems – Sta ndby

3. ALQ-155s – WARMU P

Allow ALQ-155 tra nsm itt ers to remain in WARMU P not less tha n 15 minut es aft er termina tion ofinal contact .

4. ALQ-153 – OFF

The ALQ-153 will remain off not less than 15 minutes after termination of final contact. After 15minut es t he ALQ-153 should be pla ced t o the STAND B Y mode.



T.O. 1B-52H-1-13

2-44 Change 1

POSTFLIGHT PROCEDURES

AFTER LANDING

NOTE

The AFTER LANDING checklist will be performed in the event themission is ground aborted after preflight has been init iated and afterall a lert exercises.

1. Arming Lever Sa fety P ins (No. 1) – Insta l led

2. Ar m res t s – S t ow e d

3. E CM Po w er S w i t ch es – OF F

Aircra ft electrical power must be maint ained for 5 minutes after t urn-ing off ECM equipment to allow cooling systems to cycle-out thus pre-

venting dama ge to the systems.

NOTE

• If cha nn el butt ons on ALT-16A cont rol-indica tors a re pressed a ndpow er selector sw itch is in TRANSMI T, power ca n be ra dia ted ifALQ-122 syst em is tu rned off before ALT-16A sys tem is t urn ed off.

• Check all ECM power switches OFF and recheck all chaff and flarepower switches OFF prior to leaving position to prevent inadvertentjamming or jettisoning of ECM expendables with the application ofground power.

• If taxi-back landings are accomplished, the ECM equipment will be

turned OFF on the first landing.

4. Eject ion Sea t – Down and forward

5. P IHM Assembly – Disconnect (as required)

a . P I HM M a n i fold – D iscon n ect

Disconnect the ma nifold from th e CRU -60/P bra cket locat ed on th e pa ra chute ha rness.

b. Emergency Oxygen Hose – Disconnect

Disconnect the emergency oxygen hose from the fitting on the manifold.



T.O. 1B-52H-1-13

Change 9 2-45

POSTFLIGHT PROCEDURES (Cont)

c. Aircra f t Oxygen Hose – Disconnect

While holding breath, disconnect the aircraft oxygen hose from the QD pigtail adapter.

Hold breath until steps d. and e. are complete. This will preclude theinhaling of toxic chemicals during the changeover from blower air tothe a ircra ft oxygen syst em.

d . B low er H os e:

Disconnect blower hose from the ventilation inlet hose on the PIHM manifold, remove fromunder right armrest and connect the QD on chemical-biological canister.

e . Crossover Va lve – Hor izon ta l

Rotate the valve to the horizontal posit ion. Resume breathing.

f . O xy gen Reg ul a t or – OF F a n d 1 00% O XYG E N

g. PIH M Communica t ion Cord – Disconnect

Disconnect P IH M communicat ion cord from th e a ircraft communication cord.

h . I n t er com U n i t – Con n ect

Connect the intercom unit to the PIHM communication cord.

i . B lower Elect r ica l Connector – Disconnect

Disconnect the blower fr om th e blower electrical r ecepta cle and r eplace the recepta cle dust cover

j. B low er – R em ove

Remove the blower from the aircraft mounting bracket.

6. Oxygen Regula to r – OFF a nd 100% OXYGEN

7. G u n ner S ta t ion :

a . Reg ul a t or – O FF a n d 100% O XYG E N

b. Supply Hose & Interphone Cord – Stowed

8. B u nk S ta t ion :

a . Oxygen Regula to r – OFF and 100% OXYGEN

b. Supply Hose and In terphone Cord – S towed

9. D I S ta t ion :

a . Reg ul a t or – O FF a n d 100% O XYG E N

b. Supply Hose & Interphone Cord – Stowed



T.O. 1B-52H-1-13

2-46 Change 9

POSTFLIGHT PROCEDURES (Cont)

POSTFLIGHT

1. ALE -20 Sa fety Interlock Sw itch Door – Open, streamer insta lled

The EW officer will ensure that the ALE-20 flare ejector safety interlock switch door is open andthe streamer is installed.

NOTE

Aircraft accepted for alert status will have the streamer removed andthe ALE -20 safety interlock swit ch door closed.

2. Required Forms – Completed

3. Crew Debriefing – Completed

Forms, logs, and classified material turned in as briefed.



T.O. 1B-52H-1-13

Change 1 2-47

ALERT PROCEDURES (SIOP)

The normal checklists in this section are designedto permit use during alert. The additional check-lists in this section are used in situations peculiaronly to t he a lert cycle. Any time bombs/missiles a reaboard, the normal two-man policy will be ob-served. After maintenance has declared an aircraft

read y for a lert a nd t he bombs/missiles ha ve beenloaded, the aircrew will conduct an init ial accep-tance check. When the aircrew declares the aircraftready for alert and the aircraft is on the alert line,it will be placed in a ‘‘cocked’’ configuration. Thedaily alert preflight will be accomplished once each24 hours, norma lly at a predesignated t ime.

A fully loaded CSRL mated to an aircraft does notprovide the crew the ability to accomplish a com-plete weapons preflight. Timers, baro settings, andother r equired preflight items a re not rea dily a cces-sible to the aircrew. As a result the following proce-dures will be used. The munitions maintenance

load team will load the weapons loaded CSRL andcomplete all required checks up to and includingthe post load check. During the post load check, thewing air weapons officer (must be certified), the al-ternate wing air weapons officer or a designatedrepresentative (must be certified by the air weap-ons officer) will be called to t he a ircra ft. These indi-viduals will perform a weapons preflight , examinethe general condition of the bomb bay, preflight theCSRL, its associated equipment and will verify thequantity of weapons and the launcher number. Af-ter completing checks and preflight, the individualaccomplishing the required checks will make thefollowing entry into the AFTO Form 781: A com-

plete weapons preflight has been accomplished.Weapons status and sett ings have been verified.Upon arriving at the aircraft , the aircraft com-mander will check the AFTO Form 781 to ensurethe required entry is in the forms. The aircrew willconduct a check of the general condition of thebomb bay, preflight the CSRL and validate thelauncher number, then va lidate t he correct numberand types of weapons. During engine runs, the ra-dar navigator will monitor the status of the weap-ons through Format 7. The command post will benotified that the aircraft is ready to be ‘‘cocked’’ onaler t .

During crew changeover, the radar navigator’s andnavigator’s BEFORE EXTERIOR (POWER OFF)checklist w ill be accomplished by the n ew crew. The

AGM-86B E XTE RI OR IN SP E C TION /AGM-129 E XTER IOR INSP E CTION/EXTER IOR INS P E CTION(BOMB BAY INTERIOR) checklists (as applicable)may be deferred until after an alert force exercisewhen engines are sta rted.

INSTRUCTIONS

Thermal Curtains

During init ial acceptance for an alert aircraft orprior to deploying to assume satellite alert, the pi-lots wil l ensure tha t a l l thermal cur ta ins a t t rans-parent openings in the cockpit are installedchecked for proper fit, and positioned as requiredCurtains for cockpit windows No. 6L&R, and the pilot/copilot escape ha tches w ill rema in closed w hilethe aircraft is on alert . Curtains for cockpit windows No. 1, 2L&R, 3L&R, 4L&R and 5L&R will beret ur ned t o the open/st owed p osit ion. The pilot /copilot flash d ivider curta ins w ill be positioned on top othe instrument panel cover with the lower tapes

fastened. For information regarding inspection accepta nce criteria , see THE RMAL CU RTAINS , Section I .

Thermal curtains will be kept free fromgrease, oil, and mold as any discolorationwill seriously impair the value of the cur-ta ins. Oil or grease base ma terial w ill igniteupon exposure to thermal radiation. Use ex-treme care when handling the curtains dur-ing installat ion. Dirty or cracked curtains

will be replaced.

All thermal and flash divider curtains will beplaced in th e open/stow ed position or a ppropria testorage containers when deploying to and from thesatellite alert base. When assuming init ial satellitea lert, therm a l/flas h divider curta ins need not be rechecked; however, they will be positioned in accordan ce with t he init ial a lert a ccepta nce procedures.

When assuming alert duty, the pilot and copilot wilcheck that the flash blindness goggle case seal isnot broken an d th e cases posit ioned wh ere they arereadily a vaila ble. Monocular eyeshields for r emain

ing crewmembers will be positioned where they arereadily available.



T.O. 1B-52H-1-13

2-48

Security

Entrance to the designated ‘‘No Lone Zone’’ of a‘‘cocked’’ configured aircraft will be in accordancewith comma nd directives.

Maintenance While On Alert

At any t ime while the aircraft is cocked, if a re-quirement exists to refuel (except wing tanks), theaircrew will uncock the aircraft using the UN-COCKING checklist . Normal servicing require-ments for oxygen, hydraulics, or pneumatics, whichdo not require access to the cockpit, may be accom-plished on a cocked aircraft . Maintenance may beperformed without uncocking provided force timingis not degraded, power is not placed on the a ircra ft ,access to the cockpit or bomb bay area is not re-quired, and no electrical component is involved.When t he a ircraft is uncocked for ma intena nce/re-fueling a nd th e ma intena nce/refueling is complete,the a ircraft w ill be recocked by th e alert crew using

the E XTER IOR INS P EC TION checklist as applica-ble, INTERIOR INSPECTION checklist , and BE-FORE STARTING ENG INE S checklist . If othertha n th e alert flightcrew personnel have ha d a ccessto the bomb ba y a nd/or missiles during t he requiredmaintenance, the navigator’s BEFORE EXTERIORINS P E CTION a nd th e bomb preflight a nd/or mis-sile preflight inspections m ust als o be completed.

NOTE

If the aircraft has been towed for t ire rota-tion, etc, ensure that the ground locks andbypass keys are removed upon completionof the towing operation.

EW Officer Procedures

1. AI RCRAF T ACCE PTAN CE

a. B efore Exter ior Inspect ion

b. Exter ior Inspect ion

c. In terior Inspect ion

d. ECM equipment opera t ional check, as re-quired

e. Af t er L a n d in g

2. S CRAMB LE

a . S t a r t in g E ng in es

b. Read over interphone the TAXIING check-list and BE FORE LINE UP checklist .

3. DAILY ALERT P REFLIGH T. There a re no spe-cific items that are to be accomplished by the EWofficer other than those called for by the copilot onhis DAILY ALERT PREFLIGHT checklist.

4. U N CO CK IN G . I t em s t o b e a ccom pl ish ed b ythe EW officer are on the pilot’s UNCOCKINGchecklist a nd w ill be a ccomplished at h is direction.



T.O. 1B-52H-1-13


Defensive Systems Abnormal Operationsand Malfunction Analysis section III


DESCRIPTION 3-3

RECEIVER SYSTEMS 3-3

AN/ALR-20A ABNORMAL OPERATION 3-3

AN/ALR-20A MALFUNCTION ANALYSIS CHECKLIST 3-4

RADAR WARNING RECEIVER ABNORMAL OPERATION 3-7

RADAR WARNING RECEIVER MALFUNCTION ANALYSIS CHECKLIST 3-8

SENSOR INTEGRATION ABNORMAL OPERATION 3-11

SENSOR INTEGRATION BIT ADVISORY MALFUNCTION ANALYSIS 3-12

TRANSMITTER SYSTEMS 3-15

AN/ALT-16A MALFUNCTION ANALYSIS CHECKLIST 3-15

AN/ALT-32A MALFUNCTION ANALYSIS CHECKLIST 3-15

RECEIVER-TRANSMITTER SYSTEMS 3-17

Less DT AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLIST 3-17

DT AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLIST 3-20D

AN/ALQ-122 MALFUNCTION ANALYSIS CHECKLIST 3-21

AN/ALQ-153(V) MALFUNCTION ANALYSIS CHECKLIST 3-22

AN/ALQ-155 MALFUNCTION ANALYSIS CHECKLIST 3-23

EXPENDABLE COUNTERMEASURES SYSTEMS 3-25

AN/ALE-24 MALFUNCTION ANALYSIS CHECKLIST 3-25

AN/ALE-20 MALFUNCTION ANALYSIS CHECKLIST 3-25

DEFENSIVE SYSTEMS CIRCUIT BREAKERS 3-27



BL



T.O. 1B-52H-1-13

Change 10 3-3

DESCRIPTION

Abnormal procedures and malfunction analysischecklists are presented in this section categorizedin the sam e order as in section I . Additiona l classi-fied informat ion for t he syst ems is conta ined in T.O.1B -52H -1-13-1.

The malfunction and analysis checklist should beperformed when the equipment is not functioningnormally. Effort should be made while still airborneto determine the nature of the malfunction to aidground maintenance efforts; and in certain tacticalsituations to investigate the possibility of emer-gency inflight use of equipment. In all malfunctionsinvolving apparent loss of equipment power, or sig-nal reception, accessible circuit breakers should bechecked and reset. Additionally, accessible cablingshould be checked for proper connection.

Due to the high voltages associated withmost ECM equipment, extreme care mustbe used when accomplishing inflight correc-tive action to ensure that applicable ECMequipment is placed to OFF before remov-ing and replacing the fuses.

Emergency opera t ion of ECM equipment

may result in damage to the equipment.

Inflight corrective action for systems malfunctionsconsists of the malfunction and analysis checklistand procedures for abnormal operation of theequipment. The malfunction and analysis checklistshould be performed for all specific systems mal-functions. Emergency operation procedures shouldbe accomplished only wh en dictat ed by th e ta cticalsituation.

RECEIVER SYSTEMS

AN/ALR-20A ABNORMAL OPERATION

The only emergency operation with the ALR-20Awould be with adjustments to the indicator. If oneor more traces jump halfway left or right of scope,adjust the horizontal position control for the traceIf one or more traces are positioned into or downinto the next trace, adjust the vertical position control for the trace.

Less DS Adjustm ents of th e intensit y, focus,HP, V, AST, a nd wid th contr ol should beaccomplished only by ground maintenancep e r so n n e l o r d u r in g S I O P /con t in g e n cyoperations. The use of extreme care and aninsulated screwdriver is recommended dueto the fragile potentiometers and possiblecontact with high voltages.



T.O. 1B-52H-1-13

3-4 Change 5

AN/ALR-20A MALFUNCTION ANALYSIS CHECKLIST

The following conditions are caused by blown fuses. These conditions require checking fuses in thepower supply located behind and left of the pilot’s seat. Power supply can be reached by openingthe sma ll panel with three spring latches. Blown fuses can be isolat ed by using the power indicat orand monitor switch located to the right of the indicator. The power selector must be ON when check-ing power supply voltage readings.

NOTE

U se the a ppropriat e type fuse. There ar e tw o types of fuses: 1) fas t blow fuses with single elements; and 2) slow blow fuses with glass envelopesand wire wound thermistor devices resembling springs. The fuse suffixwill aid in determining the difference between a fast blow (FB) and aslow blow (SB ) fuse. A FB fuse ha s a suffix of “A” (eg. F02A). A SB fuseha s a s uffix of “B ” (eg. F02B ).

1. No sca le il luminat ion and no t races.

a . Check three AC phase circuit breakers and one DC circuit breaker.

(1) Circuit Breakers Out – Reset

(2) Circuit Brea kers In – Proceed to step (1.b.)

b. Check fuses F-1, F-2, and F-3.

(1) One or More Illumina ted – Turn power off, repla ce illumina ted fuse(s)

(2) None Illumina ted – P roceed t o step (1.c.)

NOTE

SB denotes SLOW BLOW FUSE, FB denotes FAST BLOW FUSE.When replacing fuses turn off ALR-20A.

c. Check power supply voltage monitor meter readings.

Indica t ion Repla ce Fuses

All fuses ba d S B -4 (1A)All fuses ba d, except F-4, 7 S B -5 (10A)All fuses ba d, except F -4, 5, 7 S B -6 (5A)All fuses good, except F-7 S B -7 (2A)All fuses good, except F-12 S B -12 (2A)All fuses good, except F-19 S B -19 (1/4A)

2. Ha ve scale illumina tion, but no tra ce, no meter reading on F-10 only.

•Replace fuse FB-10 (2A).



T.O. 1B-52H-1-13


AN/ALR-20A MALFUNCTION ANALYSIS CHECKLIST (Cont)

3. No video or test signals on . . .

Tra ce No. C heck a nd Repla ce

1 FB -11 (1A)2 S B -13 (1/2A)3 S B -14 (1/2A)4 S B -15 (1/2A)5 S B -16 (1/2A)6 S B -8 (1/2A)7 S B -9 (1/2A)

4. No video or test signal on any tr ace, three strobes appear on right edge of tra ce 3.

• Check a nd repla ce SB -18 (1/2A).

5. No test s igna ls on any t r ace.

• Check a nd repla ce SB -20 (1/4A).

6. Tra ces 1-3-5-7 disa ppear complet ely, tr a ces 2-4-6 shri nk t o about 1/2 inch on righ t s ide of scope.

• Check and replace SB-17 (1A).

7. Loss of OAS blanking occurs for ALR-20A:

• Some trace 6 strobing and marker jittering is considered normal operation. The degree ofstrobing and jitter requiring maintenance will be determined by the EW officer in coordinationwith the maintenance technician.

• Check the BNS blanking amplifier circuit breaker is in.

• Check and replace fuse on front of BNS blanking amplifier.

Prior to removing fuse ensure that the BNS blanking amplifier circuitbreaker located on th e auxiliary B NS circuit breaker panel is pulled.

• May possibly be eliminated for one piece of ECM equipment by switching cables on the blank-ing amplifier . Interchange of cables will depend on the tactical situation.

J 2 (ALQ-172 SYS No. 15 & No. 16)J 3 (RWR)J 4 (ALR-20A)



BL



T.O. 1B-52H-1-13

Change 7 3-7

RADAR WARNING RECIEVER ABNORMALOPERATION

Inflight corrective action for systems malfunctionsconsists of the malfunction and analysis checklistand procedures for abnormal operation of theequipment. The malfunction and analysis checklistshould be performed for all specific systems mal-

functions. Abnormal operation procedures shouldbe accomplished only wh en dictat ed by th e ta cticalsituation.

Abnormal opera t ion o f ECM equipmentmay result in damage to the equipment.

Should loss of video display occur with the EW offi

cer’s indicator (scope), the gunner’s indicator maybe used. The indicator may be removed by use ofthe four screws on the face. Pull the indicator outand remove the cable attached at the rear. Replacewith gunner’s indicator.



T.O. 1B-52H-1-13

3-8 Change 7

RADAR WARNING RECEIVER MALFUNCTION ANALYSIS CHECKLIST

Due to the high voltages associated with most ECM equipment,extreme care must be used when accomplishing inflight correctiveaction. Ensure th at applicable EC M equipment is placed to OFF beforeremoving and replacing the fuses.

1. Syst em power light fa ils to illuminate, no audio, or no CRT display when power button is depressed.A 9 second delay occurs for the CRT display.

• P ull and reset WARNING RCVR AC on EC M circuit breaker pan el.

• Change ac fuse on front panel of signal processor with spare.

2. Will not resta r t a f ter momentary a c power f luctuat ion or loss.

• Recycle system power button manually.

3. Threshold bar flickering or missing.

• Check for presence of interference or known signals.

• Check that cable connectors are securely connected on processor front panel. This can bechecked by gently tugging on cannon plug.

Cannon plugs must not be forced on or pins will be bent causing thesyst em to be inopera tive. Ch eck tha t WARN RC VR circuit brea ker isout t o prevent blowing fus e before moving connectors.

NOTE

If J 1, J 2, or J 3 is found loose or disconnected, a lign cann on plug guidemarks (blue in color), hold the locking ring back, ensure pins arealigned, and gently insert plug. After plug is inserted, push lockingring full forwa rd.

4. System will not self-test .

• Hold in test button for approximately 2 seconds.

• Recycle system power switch.

• Check gunner’s indicator during test, EW indicator may be defective.



T.O. 1B-52H-1-13

Change 7 3-9

RADAR WARNING RECEIVER MALFUNCTION ANALYSIS CHECKLIST (Cont)

5. Test quadrant dots present , but not on third r ing.

• P rocessor or indicat or alignment fa ult . S ystem letha l ra nge, defined by dots, must be considered when evaluating threats.

6. Test quadrant dot or band symbol missing.

• Repeat test checking gunner’s indicator.

• Dot missing indicates processor failure. All threat s tha t sh ould appear on tha t h alf of indicat orwill now appear distorted or as flat lines on axis of missing dot .

• Symbol missing indicates amplifier-detector, test oscillator, or processor failure. Repeat self-test three t imes. Check for presence of known band radars in quadrant.

7. Ex t r a t est band symbols presen t .

• If radars are in area, no malfunction.

•No radars in area, check for interference from onboard systems.

8. Test band symbols present – no audio.

• Check audio volume adjustment.

• Ch eck WARNI NG RC VR interphone mixer swit ch position.

• Check for normal audio after self-test. Aircraft interphone or processor failure.

9. Flashing or missing version number in test .

• Processor memory failure, no inflight repair.

10. R appears on the CRT Less DZ

• Error in the processor ram memory has been detected.

11. M appears on the CRT Less DZ

• Error in the loader software exists. This error will not affect operation of the OFP but couldadversely affect the reprogramming process.



T.O. 1B-52H-1-13

3-10 Change 7

RADAR WARNING RECEIVER MALFUNCTION ANALYSIS CHECKLIST (Cont)

12. Selected indicat or control (IC) button legends will not illumina te.

• Check dim knob for adjustment.

• Replace bulbs in buttons that do not light from known good buttons.

• Check for proper system operation controlled by button as function within processor may bedefective.

13. Loss of OAS bla nking occurs for RWR:

• Check the BNS blanking amplifier circuit breaker is in.


Prior to removing fuse ensure that the BNS blanking amplifier circuitbreaker located on the auxiliary BNS circuit breaker panel is pulled.


J 2 – (ALQ -172 SYS No. 15 & No. 16)J 3 – (RWR)J 4 – (ALR -20A)



T.O. 1B-52H-1-13

3-11

SENSOR INTEGRATION ABNORMAL OPERATION

A built-in-test (BIT) function is provided to checkany failure of the Line Replaceable Units (LRUs).The BIT is initiated by pressing the SI control

panel SYS TEST and BIT button indicators. Therespective code of a failed LRU is displayed on theSI MFD init iated BIT display or the operationaB IT sta tus display. LRU failure codes are shown infigure 3-1.



T.O. 1B-52H-1-13

3-12 Change 7

Sensor Integration BIT AdvisoryMalfunction Analysis

FAULT INDICATION POSSIBLE CAUSES

SI BIT Error No.

01 – 03 (U) SP defective

04 OFP incorrectly loaded: SP defective

05 UDM incorrectly loaded: SP defective

06 – 19 SP defective


50 – 52 SP defective: SP-to-MFD wiring defective

60 SP defective, ALR-46-to-SP wiring defective

ALR-46 BIT Error No.

01 – 03 RWR SP defective

99 RWR SP defective: RWR-to-SP wiring defective

ALQ-155 BIT Error No.


04 OFP incorrectly loaded: SP defective

05 UDM incorrectly loaded: SP defective


30 – 86 Associated R/T defective: SP defective

99 SP defective




T.O. 1B-52H-1-13

3-13/(3-14 blank)

FAULT INDICATION POSSIBLE CAUSES

ALQ-172 BIT Error No. Forward and Aft

01 ALQ-172 LRU #1 defective; SP defective





8L ALQ-172 LRU #8L defective; SP defective

8R ALQ-172 LRU #8R defective; SP defective



12 ALQ-172 LRU # 12 defective; SP defective

99 SP defective; ALQ-172-to-SP wiring defective

0A SP defective; MIL-STD-1553 bus wiring defective

0B SP defective; MIL-STD-1553 bus wiring defective




BL



T.O. 1B-52H-1-13

3-15/(3-16 blank)

TRANSMITTER SYSTEMS

AN/ALT-16A MALFUNCTION ANALYSIS CHECKLIST

1. Fau l t l igh t i llumina tes .

• Place power selector switch to OFF and return to original posit ion.

AN/ALT-32A MALFUNCTION ANALYSIS CHECKLIST


• Place power selector switch to OFF and return to original posit ion.



BL



T.O. 1B-52H-1-13

Change 9 3-17

RECEIVER-TRANSMITTER SYSTEMS

Less AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLISTDT

1. Fa i l indica to r l igh t i l lumina tes .

•Depress applicable STB Y/OP ER pushbutton. If t he fault wa s t emporar y, th e system wilreturn to the operate mode.

2. Hot ind ica to r l igh t i l lumina tes .

• Allow applicable subset to cool until Hot indicator light goes out and then depress the applica-ble STB Y/OP ER pushbutton. If t he H ot indicat or light ha s not gone out with in 10 minutesturn the system off for the remainder of the flight .

• If imm ediat e syst em opera tion is requ ired, depress th e HOT/OVRD pushbu tt on. This a ctionplaces the system back into operation for 60 seconds. This action may be repeated as requiredwith the understanding tha t i t may cause damage to the system.

Forcing the system into operation with an overtemperature indicationma y cause da ma ge to the system. Norma lly this procedure will be con-fined to ta ctical situa tions.

3. Cold indica tor light il luminates.

• Allow applicable subset to warm up until cold indicator light goes out then press the applicableSTB Y/OP ER pushbut ton.

4. Test sta t us light i l luminates.

•Light illuminates for 5 to 10 seconds, then goes off (Soft Fault) – associated subsystem hasfault which may cause degraded operation.

• Light illuminat es an d rema ins on until syst em power is removed or a nother self-test is init iated (Hard Fault) – the associated subsystem is inoperative.



T.O. 1B-52H-1-13

3-18 Change 9

Less DT AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLIST (Cont)

5. Waveguide low pressure wa rning light(s) illumina ted.

• Pull and reset associated pressure pump circuit breaker(s) located on the overhead A117DECM CB pane l .

• If light(s) remain on, leave the associated pressure pump circuit breaker in for the remainderof the flig ht . Do not pla ce affect ed ALQ-172 FWD/AFT subs et(s) to opera te u nless use of th esystem is required for a tactical situation. The unaffected system may be operated normally.

• If the forward ALQ-172 low pressure light remains on do not transmit with ALQ-155 Systems1 and 2 unless barometric altitude is at or below 24,000 MSL (FL240), or use of the systemis required for a tactical situation.

• If the warning light(s) extinguish, the affected system may be operated normally.

• A continua lly lit low pressure war ning light normally indicates a wa ve-

guide leak. The corresponding pressure pump is continually operatingan d is not able to maint ain w aveguide pressure above the low pressureswitch sett ing. Allowing a waveguide pressurization pump to operatecontinuously may cause damage to the pump.

• Opera t in g ALQ-172 FWD or AFT t r a nsm it t e r subsys t ems w i t hunpressurized waveguides may cause damage to the transmitters. Op-erating the ALQ-155 Systems 1 and 2 transmitter subsystems trans-mitters w ith unpressurized wa veguides at alt itudes above 24,000 MSL(FL240) may cause damage to the transmitters

NOTE

• ALQ-155 Systems 1 and 2 waveguides are connected and pressurized

on the same line as FWD ALQ-172 System 16.

• Moisture saturation within waveguides may result in a reduction ofeffective radiated power for the associated transmitter subsystem. andwill hasten waveguide corrosion. The pressure pumps are left on withthe low pressure wa rning lights on to prevent w at er intrusion into thewaveguides.

• The wa rning light(s) ma y extinguish a fter descent into th e low alt itudeenvironment due to a decrease in the required pressure differential,be tween the ins ide and ou t s ide o f the waveguide . With a leakywa veguide, the pressure pump may be a ble to ma inta in pressure at low alt itude but not at high alt itudes. This condition does not necessarilyindicat e tha t a pressurizat ion ma lfunction has corrected itself . Mainte-

nance action should be taken.



T.O. 1B-52H-1-13

Change 9 3-19

Less DT AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLIST (Cont)

6. Loss of OAS blanking occurs for ALQ-172.

• Check the BNS blanking amplifier circuit breaker in.


P rior to removing fuse, ensure tha t t he BNS blanking a mplifier circuitbreaker on t he auxiliary B NS circuit brea ker panel is pulled.


J 2 (ALQ-172 Sys t em No. 15 & No. 16)J 3 (RWR)J 4 (ALR-20A)



T.O. 1B-52H-1-13

3-20 Change 9

AN/ALQ-172(V) Autonomous Self-TestFault Indications

Less DT

FAILURE DESCRIPTION WEDGE VALUE LRU

PR FAILURES: HI MODE (NOTE A)

EAROM Failure 1 1

Bit and Comm Fail (any LRU-1 Proc.) 2 1

Receiver Chan 1 Failure 4 1

PR Receiver Chan 2 Failure 8 1



PR Receiver Overflow Failure 64 1, 2

IFM Calibration Failure 128 1, 10

Amplitude Calibration Failure 256 1, 10PR ECM Failure 1 or 2 512 1, 2

PR ECM Failure 3 or 4 1024 1, 2

PR Overflow Jam Failure 2048 1, 2

PD FAILURES: LO MODE

EAROM Failure 1 10

PDSC Bit and Comm Fail 2 10

MRC Bit and Comm Fail 4 10

SRC Bit and Comm Fail 8 10

MRC Data Received Chan 1 Failed 16 10, 4

MRC Data Received Chan 2 Failed 32 10, 4

Short Path Calibration Path Failed 64 10, 4Long Path Calibration Path Failed 128 10, 4

SRC Calibration Failure 256 10

Discriminator Failure 512 10

FS-1 Phase Lock Failure 1024 10

FS-2 Phase Lock Failure 2048 10

NOTE A: These failures may illuminate on the LRU-6 without a corresponding PR RX or PR TX light illumi-nated on LRU-5 if a PD RX failure is reported.

NOTE B: If no self-test faults are detected, the LRU-6 C-11270/ALQ-172(V) control monitor will function asnormal and the LRU-5 C-11213/ALQ-172(V) control indicator TEST STATUS – FWD and/or AFT will not

flash.

Figure 3-2



T.O. 1B-52H-1-13

Change 13 3-20A

DT AN/ALQ-172 FAULTS

ALQ-172 CDU Failure

If the ALQ-172 fails, both FWD and AFT systemsdefault to the HIGH alti tude mode. LOW alti tudemode can be selected for both systems by selectingOVRD LO on the ALQ-172 Auxiliary Panel CDU

Altitude Override Switch.

[AMI] ALQ-172 Fault Status

ALQ-172 stat us is provided to the OAS via the Offen-sive/Defen sive In terfa ce softw a re a nd t he 1553A databus. The OAS displays the ALQ-172 status and itsbus B an d D communication sta tus on FRMT-6 on th eNavigator’s and Radar Navigator’s MFDs (Refer toth e F RMT-6 di spla y in T.O. 1B -52H-1-12).

ALQ-172 CDU Fault Display

In order to determine i f there are faults in the AN/ALQ-172 system there are many features built into

the CDU. On the Situation page, in the SYSTEMSTATU S box, th e user can look under t he a ctivethrea t ba rs. If there ar e numbers here displayed in

red, y ellow or ora nge, then th ere is a fa ult in t he corresponding LRU . The user can then sw itch to the Sta tusscreen a nd see a pictorial diagra m of the LRUs in thesystems and determine any fa ults based on the LRUcolors. For more information on the types of faultsth a t occurred, t he user ca n sw itch screens by pressingthe D ETAIL S but ton followed by the but ton for thesystem the user wants to obtain information. This

will bring up the D etails screen, wh ich indicat es whafaults have occurred by displaying an X in the appropriate area on the screen. The user then has theoption of switching to the number of the fault bypressing the NU MB ER /X butt on. This but ton w ilchang e the X’s on th e screen t o their correspondingnumbers. If th e user then wa nts t o know specificallywha t LRU or boards w ithin the LRU may be causingth e fault , the user can press the ANALYZE but ton forthe currently selected system. This will bring upan other screen tha t w ill describe to the user the typeof faults th a t ha ve occurred a long w ith t he most likelycause of t he problems. This list is in order of most likely fa ult t o lea st likely. The user can scroll down t hi

l ist i f i t is longer then one page using the PAG E U Pand PAG E D OWN buttons.

CDU Fault Display DT




T.O. 1B-52H-1-13

3-20B Change 9

CDU Fault Display (Cont)DT

NO. FAULT TYPE FAULT DESCRIPTION RESULT

1 PR Processor GlobalFault

PR PR Supervisor Processor Failed PR Subsystem inoperative.PD maybe inoperative.

AA Environment Processor Failed PR Subsystem partially inoperative.PR will not identify complex pulse trains.

2 PD Processor GlobalFault

PD (Supervisor) Processor Failed PD Subsystem inoperative.

SRC (Swept Receiver) ProcessorFailed

PD Subsystem inoperative.

MRC (Mod Recovery) ProcessorFailed PD Subsystem inoperative.

3 EID FAULT PR or PD EID failed software con-figuration.

PR Subsystem may be inoperative.PD Subsystem may be inoperative.

4 PR Receiver Fault No frequency report over part orall of PR frequency range.

No/wrong amplitude report overpart or all of PR frequency range.

PR Subsystem inoperative.

5 1553 Comm Fault No 1553 Communications PR Subsystem inoperative.

CDU (LRU-21) inoperative

6 LRU # Indicates which LRU is reportedfailed.

LRU inoperative:

LRU-1, 2 PR SubsystemLRU-4, 10 PD SubsystemLRU-7, 8R, 8L, 9 Antenna SubsystemLRU-12 PD Special Technique

7 BIT Type None Indicates whether self test was autono-mous or operator initiated.

8 EID Version Indicates mission database ver-sion loaded into system.

9 ECM CONFIG Fault Indicates if a software configura-tion error has been detected.

PR subsystem and/or PD subsystem maybe partially or completely inoperative.




T.O. 1B-52H-1-13

Change 9 3-20C

NO. FAULT TYPE FAULT DESCRIPTION RESULT

10 Configuration & Fault Indicates if a software configura-tion error has been detected.

PR Subsystem may be partially or com-pletely inoperative.

PD Subsystem may be partially or com-pletely inoperative.

Also indicates mission databaseversion loaded into the system.

None

11 PD Receiver GlobalFault

No frequency report over part orall of PD frequency range.

PD Subsystem inoperative.

12 PD Receiver & Trans-mitter ChannelizedFault

MRC, YIG, Long/Short indicatesno receive frequency or amplitudereport over part or all of PD fre-quency range by channel.

BRF FAIL indicates that the bandreject filter(s) protecting the PR re-ceiver are not tuning.

PD Subsystem partially inoperative (ifonly one channel failed).

PD Subsystem inoperative if both chan-nels.

PR Subsystem may be partially inopera-tive.

LRU-4 JAM – PD TransmitterFault

PD Subsystem partially inoperative (ifonly one channel failed).

PD Subsystem inoperative if both chan-nels.

LRU-12 JAM – PD Special Trans-mitter Fault

PD Special transmitter partially inopera-tive (if only one channel).

PD Special transmitter inoperative if bothchannels.

PD Fail – Digital Device Fault PD Subsystem partially inoperative someECM techniques inoperative.

13 PR ChannelizedFault

Indicated channel will not receive,identify, track or jam a signal.

Indicated PR channel(s) inoperative.

PR subsystem inoperative if all channels.

14 PR Processor Chan-nelized Fault

Indicated channel processor willnot receive, identify or track a sig-nal.

Indicated PR channel(s) inoperative.

PR subsystem inoperative if all channels.




T.O. 1B-52H-1-13

3-20D Change 9

AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLISTDT

1. Fa i l indica to r l igh t i l lumina tes .

• Depress applicable STB Y/OP ER pushbutton. If th e fault wa s temporary, the syst em willreturn to the operate mode.

2. Hot ind ica to r l igh t i l lumina tes .

• Allow applicable subset to cool until Hot indicator light goes out and then depress the applica-ble STB Y/OP ER pushbutton. If t he Hot indicat or light ha s not gone out wit hin 10 minutes,turn the system off for the remainder of the flight .

• If imm ediat e syst em opera tion is req uired, depress th e HOT/OVRD push butt on. This a ctionplaces the system back into operation for 60 seconds and can be reversed by pressing theHOT/OVRD pushbutton a gain. This a ction ma y be repeated a s required w ith t he understa nd-ing that it may cause damage to the system. The Override operation can be terminated ata ny t ime during th e 60 seconds by pressing t he HOT/OVRD pushbut ton.

Forcing the system into operation with an overtemperature indicationma y cause da ma ge to the syst em. Norma lly this procedure will be con-fined to ta ctical sit uat ions.

3. Cold indica t or l ight i lluminat es.

• Allow applicable subset to warm up until cold indicator light goes out then press the applicableSTB Y/OP ER pushbut ton.

4. Test sta t us light il luminates.

• Light/LRU number illuminates in yellow – associat ed subsystem ha s fault which ma y cause

degraded operation.

• Light /LRU num ber illumina tes in red unt il system power is removed or a nother self-test isinit iated – the associated subsystem is inoperative.

• Light/LRU number illuminates in ora nge – a softw ar e configurat ion fa ult ha s been detectedin t he LR U -1 an d/or LRU -10. The a ssocia ted su bsyst em a nd/or syst em ma y be degra ded ormay be inoperative.

NOTE

P lacing the Mast er STB Y/OP ER switch t o OPE R before all subsystemsha ve t imed in to STB Y as indicat ed on th e display will cause erroneousfail indicat ions.



T.O. 1B-52H-1-13

Change 9 3-20E

DT AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLIST (Cont)

5. Waveguide low pressure wa rning light(s) illuminated.

• Pull and reset associated pressure pump circuit breaker(s) located on the overhead A117DECM CB pane l .

• If light(s) remain on, leave the associated pressure pump circuit breaker in for the remainderof the flig ht . D o not pla ce affect ed ALQ-172 FWD/AFT subs et(s) to opera te un less us e of thesystem is required for a tactical situation. The unaffected system may be operated normally

• If the forward ALQ-172 low pressure light remains on do not transmit with ALQ-155 Systems1 and 2 unless barometric altitude is at or below 24,000 MSL (FL240), or use of the systemis required for a tactical situation.

• If the warning light(s) extinguish, the affected system may be operated normally.

• If th e light illumina tes a nd flash es continuously a softw are fa ult ha s been detected. The associated subsystem or the entire ALQ-172 system may be degraded or inoperative dependingon the configuration error detected (orange light).

• A continua lly lit low pressure wa rning light normally indicates a wa ve-guide leak. The corresponding pressure pump is continually operatingan d is not able to maint ain wa veguide pressure above the low pressureswitch sett ing. Allowing a waveguide pressurization pump to operatecontinuously may cause damage to the pump.

• Opera t in g ALQ-172 FWD or AFT t r a nsm it t e r subsys t ems w i t hunpressurized waveguides may cause damage to the transmitters. Op-erating the ALQ-155 Systems 1 and 2 transmitter subsystems trans-mitters w ith unpressurized wa veguides at alt itudes above 24,000 MSL(FL240) may cause damage to the transmitters

NOTE

• ALQ-155 Systems 1 and 2 waveguides are connected and pressurizedon the same line as FWD ALQ-172 System 16.

• Moisture saturation within waveguides may result in a reduction ofeffective radiated power for the associated transmitter subsystem. andwill hasten waveguide corrosion. The pressure pumps are left on withthe low pressure wa rning lights illuminat ed to prevent w at er intrusioninto the waveguides.

• The wa rning light(s) ma y extinguish a fter descent into th e low alt it udeenvironment due to a decrease in the required pressure differential,

be tween the ins ide and ou t s ide o f the waveguide . With a leakywa veguide, the pressure pump may be a ble to mainta in pressure at low alt itude but not at high alt itudes. This condition does not necessarilyindicat e tha t a pressurizat ion ma lfunction has corrected itself . Mainte-nance action should be taken.



T.O. 1B-52H-1-13

3-20F Change 9

DT AN/ALQ-172 MALFUNCTION ANALYSIS CHECKLIST (Cont)

6. Loss of OAS blanking occurs for ALQ-172.

• Check the BNS blanking amplifier circuit breaker in.


P rior to removing fuse, ensure tha t t he B NS bla nking a mplifier circuitbreaker on t he auxiliary B NS circuit brea ker panel is pulled.

• May possibly be eliminated for one piece of ECM equipment by switching cables on the blank-ing amplifier . Interchange of cables will depend on the tactical situation. J 2 (ALQ-172 Sy st em N o. 15 & No. 16)J 3 (RWR)J 4 (ALR -20A)

7. Fa ilure of ALQ-172 Control Display Un it .

• If th e ALQ-172 fails, both FWD a nd AFT systems default to the HI G H alt itude mode. If H IG Ha ltit ude mode is desired check tha t OVRD LO ha s not been selected on th e ALQ-172 AuxiliaryPanel CDU Altitude Override Switch.

• If LOW altitude mode is desired select OVRD LO on the ALQ-172 Auxiliary Panel CDU Alti-tude Override Switch.



T.O. 1B-52H-1-13

3-21

AN/ALQ-122 MALFUNCTION ANALYSIS CHECKLIST


• Depress power switch off momentarily and then back on. The POWER switch can be depressedfor a period of approximately 2 seconds or less without reinit iat ing the 5 minute warmupinterval.

• If fa ult ind icat or light st a ys on, check AN/ALR-20A to determine w hether s yst em is ra dia tingpower a gainst threa t(s). If no tra nsmission is observed, turn off ALQ-122 system a nd use tw oALT-16As (if opera tiv e) in t he norm a l ba rra ge mode.

2. Malfunct ion indica ted by B ITE self-test .

Re fer t o T.O. 1B -52H -1-13-1.



T.O. 1B-52H-1-13

3-22

AN/ALQ-153(V) MALFUNCTION ANALYSIS CHECKLIST

1. MALF light (wh ite) with R/T, ADSP, or DS P light(s) (wh ite) illumina tes.

• Reset sy stem by cycling OP E R/STANDB Y swit ch.

• If the MALF and LRU lights remain on, continued operation is possible by depressing the

OVRD pushbutton. System operation may be degraded.

2. HOT/P OWER light (wh ite) illuminates.

• Depress power switch off momentarily and then back on.

• If t he H OT/P OWER light r ema ins on, contin ued opera tion is possible by depressing the OVRDpushbutton. (Exception: DSP HOT light cannot be overridden).

Forcing the system into operation (OVRD MODE) with an overtemper-at ure indicat ion ma y cause da ma ge to the system. This procedure will

be confined to tactical situations.

• Depress power switch off for a short period of time.

3. Indicator light(s) fail to come on.

• Depress LAMPS PUSH TO TEST control to determine defective lamp(s).

• If lamp is defective, normal system operation can be expected.

4. Operat or init iated B IT check is satisfa ctory except C M TRIG light (green) does not come on.

• Reposition the appropriate MIN RNG or TTI controls.

• It may be possible to inhibit a malfunctioning MIN RNG or TTI control to permit the othercontrol to be utilized.



T.O. 1B-52H-1-13

3-23

AN/ALQ-155 MALFUNCTION ANALYSIS CHECKLIST

1. TUN light i l luminates but t ransmit ter does not t ime out .

• P ress J OG /RE SE T. “5” in TH RE AT E NG AG E a nd TU N lights w ill illumina te. TU N lightshould extinguish after 5 minutes. System has modified heat exchanger.

2. TUN light i l luminates in t ransmit mode and t ransmission stops.

• Coolant overtemperature condition. System will cool off and recycle automatically.

3. FAU and TUN lights i l luminate in t ransmit mode and t ra nsmission stops.

• Tra nsmit ter overload condition. P ress J OG /RE SE T. Sys tem should resume tr an smissionimmediately. If FAU and TUN lights again illuminate, turn set off for remainder of flight .

4. FAU light in STB Y 1 or STBY 2.

• FAU ligh t r ema ins on a fter pressing J OG /RE SE T. Turn s et off for rema inder of flight.

5. FAU light i l luminates in t ransmit mode, t ransmission stops.

• P ress J OG/RE SE T. If FAU light goes off an d sta ys off, the ma lfunction wa s a phase fault .

6. FAU light remains on in t ra nsmit mode a f ter J OG/RES ET has been pressed.

• P ha se fault is perma nent a nd is in h eat excha nger. Turn set off for rema inder of flight .

7. FAU light goes out a fter pressing J OG/RES ET but comes on a gain a fter set has recycled throughSTBY 1 and STBY 2.

• P ha se fault is permanent an d is in the tr an smitter. Turn set off for rema inder of flight .

8. FAU light remains on when mode switch is in MAN.

• No flow condit ion. Turn mode sw itch OF F u nt il fa ult goes off (a pproxima tely 30 seconds), thentur n mode sw itch to S TB Y. If FAU light comes back on, the condition is perma nent . Turn s eoff for remainder of flight . If FAU light stays out, resume normal use after t ime delay.

9. FAU light r emains on in tra nsmit m ode after J OG/RES ET ha s been pressed (center frequency is inlower or top quarter of frequency band).

• Move center frequency a wa y from previous set t ing . P ress J OG /RE SE T. I f t ra nsmissionreturns, use in MAN mode only. If no transmission, turn set off for remainder of night.

10. FAU light illuminat es every 5 or 6 seconds in tra nsmit mode and t ra nsmission stops while FAU ison .

•

Recycle Mode Switch to OFF for less than 2 seconds and see if FAU light remains off. If FAUlight and transmission return, use in MAN mode in tactical situations only.

• If not transmitt ing, turn off set for remainder of flight .



T.O. 1B-52H-1-13

3-24

AN/ALQ-155 MALFUNCTION ANALYSIS CHECKLIST (Cont)

11. FAU light bl inks in any posit ion.

• P ress J OG /RE SE T. If tra nsm ission is present, use in MAN mode in ta ctical situa tions only.

12. Sweeping Transmit ter s .

• If system sweeps only 8 times (a sweep is one cycle), perform BIT test. If “3” does not appearin Threat Engage window, system is useable. If package sweeps more than 8 t imes, turn setoff for remainder of flight.

13. PRO CE S S O R FAU L T

• Recycle power switch.

• If t he fault st ill exists, tur n off all power sw itches, then pull and reset circuit breakers simul-taneously.

14. E R R OR L IG H TS

•Refer t o T.O. 1B -52H -1-13-1.

15. BIT FAILURES – Dur ing BIT

If a ny of th e below error codes a re received, reat tempt B IT. Refer to the usa ble modes columnfor unsu ccessfu l BI T.

E rror Code P roblem U sa ble Modes

0 Memory Fa ilure (ROM or RAM) MAN

1 P a rty Line Fa ilure MAN

2 P arty Line Fa ilure (Wrong Receiver Responded) MAN

3 P RI F ilt er Fa ilure S E MI , MAN-D E S , MAN

4 Aut oma t ic Frequency C ont rol Fa ilure MAN

5 Not U sed for B IT (S TB Y) N/A

6 B IT Not C omplet ed Wit hin 30 S econds NONE – Rea ccomplish B IT

0, 1, 2, 4, 6 Reat tempt BIT – I f st i l l unsuccessful, system usable only in manua l mode.

3 R ea t t em pt B I T – If st ill un su cces sfu l, a ll mod es except AU TO a re us a ble.



T.O. 1B-52H-1-13

3-25/(3-26 blank)

EXPENDABLE COUNTERMEASURES SYSTEMS

AN/ALE-24 MALFUNCTION ANALYSIS CHECKLIST

1. Fault indica t or l ight(s) il luminate dur ing dispensing.

• Cycle power switch off and then back on to extinguish light(s). During subsequent dispensing,note if same light(s) illuminate, indicating permanent malfunction.

2. All (SU D) (DOC) (SP D) fault indicator lights illuminat e during program med dispensing.

• Check counters for system affected to assure all chaff has not been dispensed.

• (SPD) If counters indicate chaff remaining, revert to “continuous” operation.

• (DOC or SUD) If lights continue to light , change from SUD to DOC or vice versa.

• Check if gunner has actuated chaff deactivate switch. If the gunner does not have the deactivate switch depressed, pull the CHAFF DISP DEACTIVATE circuit breaker on the ECM cir-cuit breaker panel. This will disable the chaff deactivate switch.

AN/ALE-20 MALFUNCTION ANALYSIS CHECKLIST

1. Fir ing program does not sta r t w hen release but ton is depressed.

• Reset circuit breakers.

• Check with pilot to ensure flare ejector power switch on pilot’s auxiliary side panel is ON.

• Check fuses on flare programming control panel.

2. With an i lluminat ed RH Em pty l ight , the system is inoperat ive .



BL



T.O. 1B-52H-1-13

Change 7 3-27

Defensive Systems Circuit Protection and Location

EQUIPMENT

CIRCUITBREAKER

TITLE CB PANELPOWERSOURCE

Blanking System SYS 15 & 16 HTR & BLKG CON-TROLSYS 15 BLKG MDLSYS 16 BLKG MDLBLANKING AMP

ECM

ECMECMAUX BNS

Rt. TR

Left TRLeft TRLeft TR

ECM Systems Miscellaneous

Indicator Light Dimming Control ECM IND DIMMING ECM Left TR

Wave Guide PressurizationCompressor

ECM PRESS PUMP ECM AC Bus 5

ECM Test Receptacles

Nose Radome MISCELLANEOUS –NOSE ECM TEST RECP – ACNOSE ECM TEST RECP – DC

LLCLLC

AC Bus 3Left TR

Expendable CountermeasuresSystems

AN/ALE-20 Flare Ejector Set

AN/ALE-25 Rocket Pod

FLARE EJECTOR POWERFLARE EJECTOR PROGRAMPOWERROCKET POD – LHROCKET POD – RH

ECMECM

ECMECM

AC Bus 5Rt. TR

Rt. TRRt. TR

AN/ALE-24 Dispenser Set CHAFF DISP DEACTIVATEWING CHAFF CONT PWR

ECMECM

Rt. TRRt. TR

Receiver Systems

AN/ALR-20A Search Receiver AN/ALR-20 AC AAN/ALR-20 AC BAN/ALR-20 AC CAN/ALR-20 DC

ECMECMECMECM

AC Bus 5AC Bus 5AC Bus 5Rt. TR

Radar Warning Receiver (RWR) WARNING RCVR AC ECM AC Bus 5

Sensor Integration Systems SI CONTROL DCSI DISPLAY ACSI DISPLAY DC

ECMECMECM

Rt. TRAC Bus 5Rt. TR




T.O. 1B-52H-1-13

3-28 Change 9

Defensive Systems Circuit Protection and Location(Cont)

EQUIPMENT

CIRCUITBREAKER

TITLE CB PANELPOWERSOURCE

Receiver-Transmitter Systems

AN/ALQ-153 Tail WarningSystem

RIGHT ESSENTIAL DC POWER –CM SET RLC Rt. TR

AN/ALQ-155(V) PowerManagement System

MEMORY LOAD VERIFIERMEMORY LOAD VERIFIERMEMORY LOAD VERIFIER

MISCELLANEOUS – ECM PMS A

MISCELLANEOUS – ECM PMS B

MISCELLANEOUS – ECM PMS C

ECMECMECMRLCRLCRLC

AC Bus 5AC Bus 5AC Bus 5

AN/ALQ-172 Countermeasures

Set

PRESS PUMP IND

PRESSURE TEST

ECM

ECM

Left TR

Left TR

Less SYS 15 & 16 IND CONTDT ECM Left TR

Less SYS 15 & 16 MON CONTDT ECM Left TR

ALQ-172(V) CDUDT ECM Left TR

SYS 15 & 16 HTR & BLKGCONTROL

SYS 15 PRESS PUMPSYS 16 PRESS PUMP

ECM

ECMECM

Rt. TR

Left TRLeft TR

AN/ALT-28(V) JammingTransmitter

SYS NO.1 AN/ALT-28 ANT SELECTSYS NO.2

ECMECM

Left TRLeft TR

ECM ECM CIRCUIT BREAKER PANELLLC LEFT LOAD CENTRAL CIRCUIT BREAKER PANEL

RLC RIGHT LOAD CENTRAL CIRCUIT BREAKER PANELAUX BNS AUXILIARY BNS CIRCUIT BREAKER PANEL




T.O. 1B-52H-1-13

Change 10 Glossary-1/(Glossary-2 blank)

Glossary

AAA Ant i-Aircra ft Art illery. . . . . . . . . . . . . . . . . . . . . .AC Alt erna t ing Current. . . . . . . . . . . . . . . . . . . . . . . . .ACU Avionics Cont rol U nit. . . . . . . . . . . . . . . . . . . . . .AFSATCOM Air Force Sa te l li t e Communica t ions.AG C Automa t ic G a in Cont rol. . . . . . . . . . . . . . . . . . . .AJ Ant i-J a m. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANT Ant enna. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AOA Angle-of-At t a ck. . . . . . . . . . . . . . . . . . . . . . . . . . . .B IT B uilt -In-Test. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .B ITE B uilt -In-Test E quipment. . . . . . . . . . . . . . . . . . .B NS B omb Na viga t ion S yst em. . . . . . . . . . . . . . . . . . .B WO B a ckw a rd Wa ve Oscilla t ion. . . . . . . . . . . . . . . .CB Circuit B rea ker. . . . . . . . . . . . . . . . . . . . . . . . . . . . .CCA C ircuit ca rd Assembly. . . . . . . . . . . . . . . . . . . . . .

CD U Cont rol D ispla y U nit. . . . . . . . . . . . . . . . . . . . . .CFAR Const a nt Fa lse Ala rm Ra te. . . . . . . . . . . . . . .CMD Count ermea sures D ispenser. . . . . . . . . . . . . . .COMS E C Communica t ions S ecurit y. . . . . . . . . . . . . .CRT Ca thode Ra y Tube. . . . . . . . . . . . . . . . . . . . . . . . . .CS RL C ommon S t ra t egic Rot a ry La uncher. . . . . . . .CW Cont inuous Wa ve. . . . . . . . . . . . . . . . . . . . . . . . . . .D C D irect Current. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .E CM E lect ronic Counter Mea sures. . . . . . . . . . . . . . .E E ROM E lect ronica lly E ra sa ble Rea d. . . . . . . . . . . .

Only MemoryE ID E mit t er Ident ifica t ion D a ta. . . . . . . . . . . . . . . . .E MCON E mission Cont rol. . . . . . . . . . . . . . . . . . . . . . .E MI E lect roma gnet ic Int erference. . . . . . . . . . . . . . . .

E MP E lect roma gnet ic P ulse. . . . . . . . . . . . . . . . . . . . .E W E lect ronic Wa rfa re. . . . . . . . . . . . . . . . . . . . . . . . . .FD M Force D irect ion Messa ge. . . . . . . . . . . . . . . . . . .FP ROM Front -P a nel P rogra mma ble. . . . . . . . . . . . .

Rea d-Only Memory

G P S G loba l P osit ioning S yst em. . . . . . . . . . . . . . . . . .H S AB H ea vy S t ores Ada pt er B ea m. . . . . . . . . . . . . .ICS MS Int egra ted Convent iona l S t ores. . . . . . . . . .

Mana gement S ystemINS Iner t ia l Na viga t ion S et /S yst em. . . . . . . . . . . . . .IFF Ident ifica t ion Fr iend or Foe. . . . . . . . . . . . . . . . . .IF R Inst rument F light Rules. . . . . . . . . . . . . . . . . . . .LCD Liquid C ryst a l D ispla y. . . . . . . . . . . . . . . . . . . . .LF Low Frequency. . . . . . . . . . . . . . . . . . . . . . . . . . . . .LMS L Left Missile Light. . . . . . . . . . . . . . . . . . . . . . . .LNA Low Noise Amplifier. . . . . . . . . . . . . . . . . . . . . . . .LRU Line Repla cea ble U nit. . . . . . . . . . . . . . . . . . . . . .MFD Mult ifunct ion D ispla y. . . . . . . . . . . . . . . . . . . . .MRT Minia t ure Receive Termina. . . . . . . . . . . . . . . .

NAV Na viga t ion, Na viga tor. . . . . . . . . . . . . . . . . . . . . .OAS Offensive Avionics S yst em. . . . . . . . . . . . . . . . . .P D P ulse D oppler. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .P RF P ulse Recurrence Frequency. . . . . . . . . . . . . . . .P RI P ulse Recurrence Int erva. . . . . . . . . . . . . . . . . .P ROM P rogra mma ble Rea d-Only Memory. . . . . . . .RMS L Right Missile Light. . . . . . . . . . . . . . . . . . . . . . .RTM Ra da r-Tra nsmit ter Modula t or. . . . . . . . . . . . . .RWR Ra da r Wa rning Receiver. . . . . . . . . . . . . . . . . . .S AM S urfa ce t o Air Missile. . . . . . . . . . . . . . . . . . . . .S I S ensor Integra t ion. . . . . . . . . . . . . . . . . . . . . . . . . . .S IOP S ingle Integra t ed Opera t ions P la n. . . . . . . . . .S TALO S t a ble Loca l Oscilla t or. . . . . . . . . . . . . . . . . . .TRANS E C Tra nsmission S ecurit y. . . . . . . . . . . . . . . .

TH Tra ck While S ca n. . . . . . . . . . . . . . . . . . . . . . . . . . .TX Tra nsmi. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VLF Very Low Frequency. . . . . . . . . . . . . . . . . . . . . . . .



BL



T.O. 1B-52H-1-13

Change 9 Index-1

ALPHABETICAL INDEX

*DE NOTES ILL U STRATION

P a g e

A

Abnorma l Operation a nd MalfunctionAnalysis 1-5, S ection III

After Landing Checklist 2-44After Ta keoff/Clim b Ch ecklist 2-23Aircraft, The 1-3

Coding vDescription 1-3Dimensions 1-4Special Fea tures 1-3

Aircrew E mergency P rocedures 1-5Air Refueling P rocedures 2-42

Contact 2-43P ost Air Refueling 2-43Rendezvous 2-42

AN/ALE -20 Fla re E jector S et 1-113Component Description 1-113Component Locations 1-115*Controls an d Indicators 1-116*Functional Description 1-113Malfunction Analysis

Checklist 3-25Normal Opera tion 1-120P ilot’s ALE-20 Fla re Ejector P an el 1-119*Stepping Switch and Flare

Ejector Ca se 1-114*AN/ALE -24 Dis pens er S et 1-103

Component Description 1-103Component Locations 1-105*Controls an d Indicators 1-106*Functional Description 1-103Malfunction Analysis Checklist 3-25Normal Operat ion 1-111

AN/ALQ-172 Coun ter mea sur es S et 1-63Auxiliary P an el 1-72G , 1-72H*CDU Deta i led Sta tus Screen 1-72U *CDU Fault Display 3-20A*CDU Normal Operation 1-74CD U S elect Key Mat rix 1-72Q*CDU Situat ion Display 1-72K*

CDU Sta tus D isp lay 1-72P *CDU Symbol Set 1-72V*Component B lock Diagra m 1-66*Component Locations 1-67*Control Display U nit 1-65, 1-66A*,1-72B *Control Display Unit Operat ion 1-72JControls and Indicat ors 1-72*Contr ol Monitor 1-72A*Faults 3-20A

P a g e

Functional Description 1-63Keyboard Commands 1-74DMalfunction Analysis Checklist 3-17, 3-20DNormal Opera tion 1-73Wa veguide Low P ressure Wa rning

and Blanking Panel 1-72G *AN/AL Q-122/AN/ALT-16A

Countermeasures System 1-75B uilt-In-Test E quipment

(BI TE ) S elf-Test 1-76Component Description 1-75Component Locations 1-77*Controls and Indicat ors 1-79*Functional Description 1-75

Malfunction Analysis Checklist 3-21AN/ALQ-153(V) Ta il Wa rn in g S ys t em 1-83Component Description 1-83Component Locations 1-85*Controls and Indicat ors 1-86*Functional Description 1-83Malfunction Analysis Checklist 3-22Normal Opera tion 1-91

AN/ALQ-155(V) P ower Ma na gemen t Sy st em 1-92Antenna Selector P an el 1-100*Component Description 1-92Component Locations 1-95*Control Indicator P rogrammer 1-99*Functional Description 1-92

Malfunction Analysis Checklist 3-23Normal Opera tion 1-101Signa l P rocessor 1-98*

AN/ALR-20A S ea rch Receiver 1-13Abnormal Operation 3-3Blanking Amplifier 1-22*Component D escription 1-15Component Locations 1-17*Controls an d Indicators 1-23*, 1-26*Functional Description 1-13IP -1168B B it 1 S creen 1-26D, 1-26D*IP -1168B B it 2 S creen 1-26F, 1-26F*IP -1168B Ind icator Align S creen 1-26G *Look-Thru Panel 1-20*

Malfunction Analysis Checklist 3-4P ower Supply 1-21*Receiver-Cont rol, C-9449/ALR-20A 1-15, 1-19*RF Tuner s 1-21*

AN/ALT-16A 1-57AN/ALT-28(V) J a mm ing Tra ns mi tt er 1-57AN/ALT-32A J a mm ing Tra ns mi tt er 1-57

Component Locations 1-58*Controls and Indicat ors 1-60*



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Index-2 Change 12

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B efore Exterior Inspection – Sa fety Ch eck 2-5B la nkin g Amplifier, ALR -20A 1-22*

Bla nking System 1-55Equipment Locat ions 1-56*Fun ctiona l Description 1-55

C

C-9449/ALR-20A Receiver -Cont rol, 1-15, 1-19*Conta ct, Air Refueling P rocedures 2-43Coun t erm ea sur es Set , AN/ALQ-172 1-63

Component Loca tions 1-65*Controls an d Indicators 1-70*Contr ol Monitor 1-71*Fun ctiona l Description 1-63Normal Operation 1-73

Wa veguide Low P ressure Wa rningand Bla nking Panel 1-72G *

Countermeasures S ystemAN/ALQ-122/AN/ALT-16A 1-75

B uilt-In-Test Eq uipment(B ITE ) Self-Test 1-76

Component Description 1-75Component Loca tions 1-77*Controls an d Indicators 1-79*Fun ctiona l Description 1-75

D

Defensive Systems 1-4Circuit B reakers 3-27*

Dispen ser Set AN/ALE-24 1-103Component Description 1-103Component Loca tions 1-105*Controls an d Indicators 1-106*Fun ctiona l Description 1-103Normal Operation 1-111

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ECM Antenna s 1-5Antenna Locations 1-8*

Antenna P at t erns 1-5Tra nsmit ter Antenn a Types 1-5, 1-10*ECM Equipment Operation Requirements 2-4Equipment Circuit Pr otection and S ystem

Data Flow D iagrams 1-4EW Calibration and Interference Checklist 2-25EW Eq uipment S et Checklist 2-37EW Officers S ta tion 1-5, 1-6*Expenda ble Countermeasures S ystems 1-103

AN/ALE-20 Fl a re E jector S et 1-113Malfun ction Analysis C hecklist 3-25

AN/ALE-24 Dis pens er S et 1-103Malfun ction Analysis C hecklist 3-25

Ext erior I nspection C hecklist 2-7

F

Fl a re E jector Set , AN/ALE-20 1-113Component Description 1-113Component Loca tions 1-115*Controls an d Indicators 1-116*Fun ctiona l Description 1-113Normal Operation 1-120P ilot’s ALE-20 Fla re E jector P a nel 1-119*Stepping Swi tch and Flare

Ejector Case 1-114*

GGround Cooling 1-4

H I

Inflight Procedures 2-23After Ta keoff/Cl imb C hecklis t 2-23EW Calibrat ion a nd I nterference

Checklist 2-25EW Eq uipment Set C hecklist 2-37P relanding Operational Check

Checklist 2-41Int erior I nspection Ch ecklist 2-8



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Change 9 Index-3

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J K L

Look-Thr u P a nel, ALR-20A 1-20*

M NNuclear Alert P rocedures 2-47

O P

P ilot’s ALE-20 Fla re Ejector P a nel 1-119*P ost Air Refueling P rocedures 2-43P ostflight P rocedures 2-44

After Landing Checklist 2-44P ostflight Checklist 2-46

P ower Ma nagement System,AN/ALQ-155(V) 1-92

Antenna Selector P an el 1-100*Component Description 1-92Component Locations 1-95*Control Indicator P rogrammer 1-99*Functional Description 1-92Normal Opera tion 1-101Signa l P rocessor 1-98*

Power Supply, ALR-20A 1-21*P reflight a nd Operat ional C hecks 1-5P reflight P rocedures 2-5

Before Exterior Inspection – Safety Check 2-5Ext erior In spection Ch ecklist 2-7Int erior In spection Ch ecklist 2-8

P relanding Operational C heck Ch ecklist 2-41

Pretakeoff Procedures 2-21St art ing Engines Checklist 2-21Ta xiing a nd B efore Lineup C hecklist 2-22

P repar at ion for Flight 2-3Checklists 2-3Entrance 2-3

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Q R

Ra da r Wa rn ing R eceiver, (RWR) 1-27Component D escription 1-31

Component Locations 1-32*Controls and Indicat ors 1-36*Functional Description 1-27Gunner Sta t ion 1-31Indications 1-42*Normal Opera tion 1-42KOperational Modes 1-28Signa l P rocessor 1-34*

Receiver-Con t rol , C-9449/ALR-20A 1-15, 1-19*Receiver Systems 1-13

AN/ALR-20A Sea rch Receiver 1-13Abnormal Operation 3-3Malfunction Analysis Checklist 3-4

Ra da r Wa rning Receiver 1-27

Abnormal Operation 3-7Malfunction Analysis Checklist 3-8Sensor Integration System 1-43

Abnormal Operation 3-11B IT Advisory Ma lfunction Ana lysis 3-12

Receiver-Tra nsm itt er S yst ems 1-63AN/ALQ-172 (V) Count erm ea su res S et 1-63

Auton omous S elf-Test 1-73Malfunction Analysis Checklist 3-17

AN/ALQ-122/AN/ALT-16ACountermeasures System 1-75Malfunction Analysis Checklist 3-21

AN/ALQ-153(V) Ta il Wa rn in g S ys tem 1-83Malfunction Analysis Checklist 3-22

AN/ALQ-155(V) P ower M a na gem entSystem 1-92Malfunction Analysis Checklist 3-23

Rendezvous, Air Refueling P rocedures 2-42RF Tun ers ALR-20A 1-21*



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t.o. 1b-52h-1-13 - electronic warfare officers manual - b-52h (01!06!2006)

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