b717

TRAINING PURPOSES ONLY INTRO - 1 TECHNICAL DEVELOPMENT

BOEING 717MCDONNELL DOUGLAS CORPORATION - THIS INFORMATION IS SUBJECTTO DATA RIGHTS. LEGENDS ON TITLE PAGE OR FIRST PAGE.

BOEING 717 COCKPIT

FAMILIARIZATION

BOEING 717 COCKPIT EQUIPMENT LOCATION

BOEING 717

TECHNICAL DEVELOPMENT INTRO - 2 TRAINING PURPOSES ONLY

MCDONNELL DOUGLAS CORPORATION - THIS INFORMATION IS SUBJECTTO DATA RIGHTS. LEGENDS ON TITLE PAGE OR FIRST PAGE.

ContentsAFT OVERHEAD PANEL ............................................................................................................... 4FORWARD OVERHEAD PANEL ................................................................................................... 5GLARESHIELD AND OUTBOARD CONSOLE........................................................................... 6CENTER INSTRUMENT PANEL ................................................................................................... 7CAPTAINS INSTRUMENT PANEL ............................................................................................... 8FIRST OFFICERS INSTRUMENT PANEL ................................................................................ 9FORWARD PEDESTAL .................................................................................................................. 10AFT PEDESTAL .............................................................................................................................. 11OUTBOARD CONSOLE ................................................................................................................ 13SOURCE INPUT SELECT PANEL (SISP) ................................................................................... 15PRIMARY FLIGHT DISPLAY ...................................................................................................... 17NAV DISPLAY (ND)......................................................................................................................... 18EIS CONTROL PANEL .................................................................................................................. 19NAV INFORMATION CONTROL BUTTONS............................................................................ 19WEATHER RADAR DISPLAY KNOB ......................................................................................... 21MODE SELECT / DECLUTTER BUTTONS ............................................................................... 21NAV DISPLAY MAP MODE ...........................................................................................................22NAV DISPLAY PLAN MODE......................................................................................................... 22NAV DISPLAY VOR AND APPR MODE ...................................................................................... 23NAV DISPLAY TCAS MODE ......................................................................................................... 23ENGINE / ALERTS DISPLAY (EAD) ........................................................................................... 24ALERTS DISPLAY .......................................................................................................................... 26SYSTEM DISPLAY SECONDARY ENGINE DISPLAY............................................................ 27SYSTEM CONTROL PANEL (SCP) ............................................................................................. 30HYDRAULIC SYSTEM DISPLAY ................................................................................................ 31ELECTRICAL SYSTEM DISPLAY .............................................................................................. 32PNEUMATIC SYSTEM DISPLAY ................................................................................................ 33FUEL SYSTEM DISPLAY .............................................................................................................. 34CONFIGURATION DISPLAY ....................................................................................................... 35MISC DISPLAY................................................................................................................................ 36CONSEQUENCES DISPLAY ......................................................................................................... 36STATUS DISPLAY ........................................................................................................................... 37ELECTRONIC INSTRUMENT SYSTEM RECONFIGURATION........................................... 38THE ALERT SYSTEM .................................................................................................................... 39ENGINE FIRE PANEL.................................................................................................................... 43FLIGHT NUMBER PANEL............................................................................................................45GEAR HANDLE AND LIGHTS ..................................................................................................... 45GROUND SERVICE PANEL ......................................................................................................... 47AUDIO CONTROL PANEL ( 3 TOTAL)....................................................................................... 48FLIGHT RECORDER ..................................................................................................................... 51



WARNINGThis study guide is for training purposes only.

Information contained in this study guide is subject to change and may not be current. Wherever thistraining document and approved McDonnell Douglas documentation disagree, the approved docu-ments take precedence.

FIRE DETECTOR PANEL ............................................................................................................. 52IRS MODE SELECTOR ................................................................................................................. 53COCKPIT VOICE RECORDER .................................................................................................... 54ANTI-SKID PANEL ......................................................................................................................... 56APU PANEL...................................................................................................................................... 56HYDRAULIC PANEL ..................................................................................................................... 58ELECT PWR PANEL ..................................................................................................................... 60AIR CONDITIONING PANEL ...................................................................................................... 64ENGINE START PANEL / FUEL PANEL..................................................................................... 67FUEL PANEL ................................................................................................................................... 69GROUND PROX WARN PANEL................................................................................................... 71PRESSURIZATION PANEL...........................................................................................................72ICE PROTECT PANEL ................................................................................................................... 74ANNUN LT TEST, AND RESET PANEL ...................................................................................... 76CAPT & FO WINDSHIELD WIPER PANEL .............................................................................. 78LIGHT CONT PANEL .................................................................................................................... 79MCDU ................................................................................................................................................ 85STANDBY INSTRUMENTS ........................................................................................................... 86CENTER PEDESTAL..................................................................................................................... 87VHF COMMUNICATION RADIO PANEL (2EA) ...................................................................... 92SYSTEM CONTROL PANEL (SCP) ............................................................................................. 93WEATHER RADAR CONTROL PANEL ..................................................................................... 95ATC CONTROL PANEL ................................................................................................................. 98TRIM PANEL ................................................................................................................................... 99RED BOXED ALERTS (LEVEL 3) .............................................................................................. 112AMBER BOXED ALERTS (LEVEL 2) ...................................................................................... 112AMBER ALERTS (LEVEL 1) ..................................................................................................... 114CYAN ALERTS (LEVEL 0) ........................................................................................................122INDEX ............................................................................................................................................. 125

BOEING 717



AFT OVERHEAD PANEL

EV

EN

T

CC

CC

CC

C

1-V

OR

-21-

ILS

-2

1-A

DF

-2

1-D

ME

-2

VH

F1

VH

F2

VH

F3

HF

1H

F2

MIC

SE

LE

CTO

R /

CA

LL

CA

BID

EN

TPA

INT

RA

DIO

MK

R

INT

ON

ON

ON

OF

F

GR

OU

ND

SE

RV

ICE

EL

EC

PW

R

EN

G F

IRE

DE

T S

YS

AP

UL

OO

PS A B

OT

HB

R E

NG

LO

OP

S A BO

TH

B

L E

NG

LO

OP

S A BO

TH

B



FORWARD OVERHEAD PANEL

NAV OFF NAV OFF NAV OFF

1 AUX 2

OFFNAV

OFFNAV

OFFNAV

COCKPIT VOICE RECORDER MICROPHONE MONITOR

STATUS

ERASE TEST

HEADPHONE

OFF

ANTISKID

OFF

T/O

MEDMIN

MAX

AUTO BRAKE

HIGH

ON

R SYS

OFFL PUMP

AUX

HYDRAULICS

TRANS

R PUMP

L SYS

ON

OFFON

OFF

ON

OFFHYD CONTRUDDER

OFF

ON

L GEN

OFF

AUTO

OPEN

RBUSTIE

RESETEXT

AUTO

OPEN

LBUSTIE

ON

OFF

RESET

ON

OFF

RESET

ON

OFFR GEN

AUTO

OPENDC BUS TIE

GALLEY

ELECTRICALL DCBUS

R DCBUS

OFF

ON

BATT

ON

OFF

EMER PWR

ONOFFARM

EMER PWRIN USE

L ACBUS

AVAILEXT AVAIL

APU

R GEN

EXT

APU

L GEN

R ACBUS

APU

ON

OFFOFF

DISCH

APU

OFFMASTER

FIRE CONTNORM

FIRE AGENT AIRNO-1 NO-2

OFF&AGENT ARM

START

RUN

CKPT TEMPAUTO

HOTCOLDSTOPMAN

CABIN TEMPAUTO

HOTCOLDSTOPMAN

L PACK R PACKOFF

AUTO

OFF

AUTO

OFF

AUTO

OFF

AUTO

R BLEEDL BLEEDAUTO

CLSD

OPEN

AIR

ISOL

FLOWHIGH

NORM

PACKSHUTDOWN

OVRD

AUTO

OVRD

FAN

OFF

ON

AVIONICSCOOLING RAM AIR

AUTO

ON

STARTPUMP

ON

OFF

IGNITION

SELECT

ALTN

SELECT

ALTN

ENGINESFADEC MODE

L ENG R ENG

ENG STARTL R PULL TO DIM TEST

ENGEXCEEDANCE

RESET

FUELUSEDRESET

ANNUN LT

GPWS TERR OFF

GNDPROXWARN

FLAP OVRD

NORM

TEST

OFF

CABIN PRESS

MANUALMANUALLDG ALT

CLIMB

DESC DECR

INCR

OP

CL

CLOSED

VALVE

SCHED APL1000 FT CABIN

0 10 20 25 30 35

0 2 4 6 8

SELECT

MANUAL

SYSTEM

ICE PROTECTION

AIR DATA HEAT

AIR FOILWING TAIL

OFF

ON

WING ICE DET

RESET

TEST

L RENG

OFF

OFF

ON

ON

WINDSHLDANTI - FOG ANTI - ICE

OFF

FUEL SYSTEST

FUEL QTYA / B

OFF

OFF OFF OFF

OFF OFFOFF

ON

ON ON ON

ONON

LEFT CTR RIGHT

FUEL

AFT PUMPS

FWD PUMPS

AFT TANK XFER

A B

AUTO

OFF

FWD TANK XFER

A B

AUTO

OFF

STBYCOMP

DIM

BRT

PARK

FAST

SLOW

WINDSHLD WIPEROFF

CKPTDOOR

PARK

FAST

SLOW

WINDSHLD WIPEROFF

OFF

OFF

OFF

OFF

EXTOFF

OFF OFF

OFF OFF OFF

OFFOFF

OVHDPNL FLOOD

INSTR & PEDPNL FLOOD

DOME

THNDRSTRM

ON

EMERLT

ARM

ON ONON

LEFTON

RIGHTON

CKT BRKLT

NOSMOKE

SEATBELTS

DIM

BRTAUTO

LDG LTRET

EXT ON

NOSE LT

TAXI

LDGON

RONLY

WING/NACL

PA ATTND

CALL

GND FLOOD LTL R NAV

L R

CALLRESET

EXT

MECHMAINTINTPH

CALL ON

INOP BCN HI-INT

PAIN USE

VIDEOIN USE

INOP

BOEING 717



GLARESHIELD AND OUTBOARD CONSOLE

MAS

TER

CAUT

ION

MAS

TER

WAR

NING

STIC

KPU

SHER

PUSH

TO

INH

IBIT

STIC

KPU

SHER

PUSH

TO

INH

IBIT

MAS

TER

CAUT

ION

MAS

TER

WAR

NING

BA

RO

SET

QFE

QN

H

PULL

- ST

D

IN HP

VOR

1

AD

F1

INC

R

DEC

R

VOR

2

AD

F2

RA

NG

E

TRFC

DAT

AW

PTVO

RN

DB

AR

PT

MA

GTR

U

MA

PVO

RTC

AS

PLA

NA

PPR

MIN

IMU

MS

RA

BA

RO

PUSH

RES

ETW

X B

RT

PUSH

ON

/OFF

MIN

IMU

MS

RA

BA

RO

PUSH

RES

ETW

X B

RT

PUSH

ON

/OFF

MA

GTR

U

MA

PVO

RTC

AS

PLA

NA

PPR

TRFC

DAT

AW

PTVO

RN

DB

AR

PT

VOR

1

AD

F1

INC

R

DEC

R

VOR

2

AD

F2

RA

NG

E

IN HP

BA

RO

SET

QFE

QN

H

PULL

- ST

D

IAS

MA

CH

HD

G

TRK

FEET

MET

ER

V/S

FPA

MA

CH

.82

0H

DG

24

5A

PPR

/LA

ND

FT3

10

00

FPA

PRO

FN

AVFM

SSP

D

AFS 1

OVR

DO

FF 2

AU

TO F

LIG

HT

AU

TO5 10

152025

--.-

-

FLO

OR

LT

MA

P LT

TIM

ER

PUSH

UP

DO

WN

ON

OFF

OFF

BR

T

DIM

FLO

OR

LT

MA

P LT

TIM

ER

PUSH

UP

DO

WN

ON

OFF

OFF

BR

T

DIM



CENTER INSTRUMENT PANEL

FLIGHT NO

1 2 3 4

L

ENG

FIRE

PULL

R

ENG

FIRE

PULL

AGENTDISCH

AGENTDISCHAGENT 1

LOW

AGENT 2LOW

FIRETEST

FAULTTEST

LEFT

LEFT

NOSE

NOSE

RIGHT

RIGHT

GWFUEL

CABIN ALTCABIN RATE

STAB 3.0 ANU

ENG OIL

PRESS

TEMP

QTY

0.2 N1 VIB 0.20.3 N2 VIB 0.2

6

100

78

6

100

78

NL NR

RUDAIL

LWD RWD

APU%RPM

100

%EGT80

108500 LB18500 LB

5400120

1.04

80.0

390

90.02500

EPR

N1

TGT

N2

FF

1.04

80.0

390

90.02500

1.55 CRZ LIM TAT - 20°C

APU ONA-ICE ALL ON

BOEING 717



CAPTAINS INSTRUMENT PANEL

BE

LOW

GS

PU

SH

TO

INH

IBIT

GS

4

61TA

S

481

205°

/ 70

HD

GM

AG

270

HEC

71N

M/ 8

.5

PDZ

DA

GH

ECPS

P

TRM

TNP

PKE

BLH

EED

BLD

L

VOR

/ND

BR

/IN

AV

RN

G 1

60W

HT

TLT

-3.0

11:5

500

:15

22

23

2425

2627

2829

30

31

32

270°

/ 71N

M H

ECH

EC 2

70°/

71N

M

HD

GM

AG

270

2425

2627

2829

30

20 10 10 20

20 10 10 20

340

320

306

300

280

.820

3150

0

310

3050

020 00 80

4 3 2 1 0 1 2 3 4

.820

TH

RU

STN

AVH

OLD

31 0

00

API

BA

RO

200

29.9

2

EIS

SOU

RC

E

FLT

DIR

OFF

FLT

DIR

AIR

DAT

A

IRS

FLT

MG

T

VOR

APP

R

F/O

ON

1

CA

PTO

N2

OFF

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N A

UX

F/O

ON

AU

X



FIRST OFFICERS INSTRUMENT PANEL

BE

LOW

GS

PU

SH

TO

INH

IBIT

GS

4

61TA

S

481

205°

/ 70

HD

GM

AG

270

HEC

71N

M/ 8

.5

PDZ

DA

GH

ECPS

P

TRM

TNP

PKE

BLH

EED

BLD

L

VOR

/ND

BR

/IN

AV

RN

G 1

60W

HT

TLT

-3.0

11:5

500

:15

22

23

2425

2627

2829

30

31

32

270°

/ 71N

M H

ECH

EC 2

70°/

71N

M

HD

GM

AG

270

2425

2627

2829

30

20 10 10 20

20 10 10 20

340

320

306

300

280

.820

3150

0

310

3050

020 00 80

4 3 2 1 0 1 2 3 4

.820

TH

RU

STN

AVH

OLD

31 0

00

API

BA

RO

200

29.9

2

EIS

SOU

RC

E

FLT

DIR

OFF

FLT

DIR

AIR

DAT

A

IRS

FLT

MG

T

VOR

APP

R

F/O

ON

1

CA

PTO

N2

OFF

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N2

F/O

ON

1

CA

PTO

N A

UX

F/O

ON

AU

X

BOEING 717



FORWARD PEDESTAL

OFF

STABILIZER TRIM

SPDBRK

RET

EXT

FUELON

OFF

FUELON

OFFALTLONG TRIM

NOSEDN

NOSEUP

GEARHORN

OFF

FUELX

FEED

ON

UP

0

13

18

25

40

FLAP/SLAT

FLAP T.O.SEL

STOW

20

19

0

13

18

25

EXT

UP/RET

DIRINTC

NAVRAD PERF INIT TO/

APPR

F-PLN PROG FIX SECF-PLN REF ENG

OUT

ATC

MENU

PAGE

DSPY FAIL

MSG

OFST

A

F

K

P

U

Z

B

G

L

Q

V

-

C

H

M

R

W

D

I

N

S

X

E

J

O

T

Y

+

1

4

7

/

2

5

8

3

6

9

0

BRT

CLRSP

DIRINTC


APPR


OUT

ATC

MENU

PAGE

DSPY FAIL

MSG

OFST

A

F

K

P

U

Z

B

G

L

Q

V

-

C

H

M

R

W

D

I

N

S

X

E

J

O

T

Y

+

1

4

7

/

2

5

8

3

6

9

0

BRT

CLRSP

IAS FT360

340

306300

280

10

10

20 20

10

10 31100

31200

30900

30800

31000

29.92

BARO

ALIGN

101

ALIGN

IN Hg



AFT PEDESTAL

ACTIVE STANDBYTFR

COMM TEST

VHF

COMM

ACTIVE STANDBYTFR

COMM TEST

VHF

COMM

OFF

BRT1 2 3 4 5 6

ENG

HYD ELEC AIR FUEL CONFIG MISC

ND CONSEQ STATUS

OFF ONSTAB WX

TESTOFF

WX/TURBMAP

TILT

GAIN

AUTO MAX

UP

DN

WX RADAR

0

5 10

15

15

105

ATC

IDENT

ALT OFFSTBY

ALT ONTA

TA/RATEST

ATC

1

2

ATC 2 R

1234

AILERON TRIM RUDDER TRIM

LEFTWINGDOWN

RIGHTWINGDOWN

NOSEL

NOSER

RDRCTR

BOEING 717



TRAINING PURPOSES ONLY INST - 13 TECHNICAL DEVELOPMENT


FLOOR LIGHTS SWITCH (2)

FUNCTION -BRT- Illuminates cockpit floor lights at highest levelDIM- Illuminates cockpit floor lightsOFF- Extinguishes cockpit floor lights

PURPOSE - Control cockpit floor lights

FLOOR LT

FLOOR LT

MAP LT

MAP LT

TIMER

TIMER

PUSH

PUSH

UP

UP

DOWN

DOWN

ON

ON

OFF

OFF

OFF

OFF

BRT

BRT

DIM

DIM

OUTBOARD CONSOLE

FLOOR LT

OFF

BRT

DIM

BOEING 717

TECHNICAL DEVELOPMENT INST - 14 TRAINING PURPOSES ONLY


MAP LT

ON

OFF

MAP LIGHTS SWITCH (2)

FUNCTION -ON- Illuminates Map lightsOFF- Extinguishes Map lights

NOTE: Map light on overhead must be out of stowed position and on before this switch will work.

PURPOSE - Control map lights

TIMER

PUSHUP

DOWN

CHR (Chronograph) TIMER SWITCH (2)

FUNCTION -PUSH- Starts, Stops, and Resets chronograph time functions on the NAV display.UP- Causes the chronograph time functions to count upDOWN- Causes the chronograph time functions to count down ( down timer only works in flight )

PURPOSE - Used to Control CHR (Chronograph) time functions.



EIS SOURCE EIS SOURCE

FLT DIROFF

FLT DIR

AIR DATA

IRS

FLT MGT

VOR

APPR

FLT DIROFF

FLT DIR

AIR DATA

IRS

FLT MGT

VOR

APPR

F/OON1

F/OON1

CAPTON2

CAPTON2

OFF OFF

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON AUX

F/OON AUX

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON2F/OON1

CAPTON AUX

F/OON AUX

1

2 1

2

SOURCE INPUT SELECT PANEL (SISP)

EIS SOURCE SWITCH (2)

FUNCTION -Under normal conditions CAPT displays (1,2,3) are controlled by VIA 1 and FO displays (4,5,6) arecontrolled by VIA 2. If either VIA fails all displays can be controlled by one VIA. The source selec-tor allows the flight crew the option of selecting the alternate VIA. If the CAPT or FO selects theALT VIA, the appropriate light will be illuminated on both panels.

NOTE: EIS SOURCE SWITCH should never normally be used. VIA's will automaticallyreconfigure displays in the event of failure, as long as swithces are in "NORMAL" position.

PURPOSE - Manually Control VIA Source

EIS SOURCE

F/OON1

CAPTON2

1

2

EIS SOURCE

F/OON1

CAPTON2

1

2

BOEING 717



FLT DIROFF

OFF

FLT DIRCAPTON2F/OON1

AIR DATACAPTON2F/OON1

IRS INOPCAPT

ON AUXF/O

ON AUX

FLT MGTCAPTON2F/OON1

VORCAPTON2F/OON1

APPRCAPTON2F/OON1

Illuminates amber when flight director is selected off. Pushing switch whenilluminated will reengage the flight director.

Switch allows selection of flight director source displayed on PFD.

The AIR DATA switch allows selection of ADIRU air data output to the Captain's orFirst Officer's DUs. Under normal operation the Captain's DUs use Air Data 1 as asource, and the First Officer's DUs use Air Data 2 as a source. No light will illumi-nate if conditions are normal. CAPTAIN ON 2 or FIRST OFFICER ON 1 willilluminate amber to indicate respective condition. Pushing switch when illuminatedwill return DUs source to normal Air Data output.

IRS Switch - amberThe IRS switch will select other ADIRU IRS data ( offside if 2 installed, AUX ifthree are installed

The FLT MGT switch allows selection between normal in line operation of thefight management system or a transfer to a secondary flight management system.Captain may select First Officer's FMS (FMS-2) or First Officer may selectCaptain's FMS (FMS-1), but Captain or First Officer may not select each othersFMS simultaneously.

FLT DIR OFF Switch - amber

FLT DIR Switch - amber

AIR DATA Switch - amber

FLT MGT Switch - amber

The VOR switch allows selection of VOR display source to be transferred from analternate source. Normally the Captain's VOR display is controlled by the left radiosystems, and the First Officer's VOR display is controlled from the right radio sys-tems. CAPTAIN ON 2 or FIRST OFFICER ON 1 will illuminate amber to indicaterespective condition. Pushing switch while illuminated will return VOR source tonormal.

VOR Switch - amber

The APPR switch allows selection of approach data (ILS or MLS) to be transferredfrom an alternate source. Normally the Captain's APPR display is controlled by theleft radio systems, and the First Officer's APPR display is controlled from the rightradio systems. CAPTAIN ON 2 or FIRST OFFICER ON 1 will illuminate amber toindicate respective condition. Pushing switch while illuminated will return APPRsource to normal.

APPR Switch - amber



The primary flight display supplies flight data to the flight crew. The primary flight display showsaircraft attitude, altitude, airspeed, and heading data.The primary flight displays are on the captain's and the first officer's instrument panels. The primaryflight display is a combination of indicators, displays, and annunciators. The primary flight displaycan show:1. Attitude indicator2. Slip skid indicator3. Pitch limit indication4. Flight director5. Radio altitude indication6. Lateral (localizer) and vertical (glideslope) deviation display7. Marker beacon indication8. Airspeed/mach display9. Altitude indicator10. Vertical speed indicator11. Flight mode annunciator12. Heading indicator.

PRIMARY FLIGHT DISPLAY

MISCOMPAREANNUNCIATION

AREA

160 THRUST ALIGN DUAL LANDG/S

200

180

160

140

120

FLAPS 35IZH 16.0

20 20

1010

10 10

20 20

130

2000

161

16 171514

1318 19

HDG MAG

QNH 29.92

100RA

0.9432

1

150015 60

50

4000

0

1

234

F50FR

AP

PITCHINDICATORAND TAPE

ROLLLIMIT

INDICATORROLL

POINTERSLIP/SKID

INDICATORROLL

INDICESFLIGHT

DIRECTORFLIGHT MODEANNUNCIATOR

BUG (SELECT)

PRESELECTEDALTITUDE

ALTITUDESCALE

RADIO ALTITUDEBUG

PRECISIONALTITUDE

VERTICAL SPEEDSCALE

GLIDE SLOPESCALE

PRECISIONVERTICAL

SPEED

CURRENTALTIMETER

SETTING

RA/DH ORBARO SETALTITUDEMAGNETIC/TRUEPRECISION

HEADING/TRACKAIRCRAFT

TRACKBUG (SELECT)SCALE

DME

TUNEDILS

IDENT

AIRCRAFTCONFIGURATION

LOCALIZERSCALE

STICK SHAKER

VMIN FOOT

FMSPRESELECTSPEED BUG

PRECISIONAIRSPEED

FLAP50

RETRACTSPEED

MAX FOOT

AIRSPEEDSCALE

PITCHLIMIT

INDICATOR

BOEING 717



NAV DISPLAY (ND)PURPOSE - DISPLAY NAVIGATION INFORMATION

FUNCTION - NAVIGATION DISPLAYSThere are five modes of navigation display: MAP mode, TCAS mode, VOR mode, APPR mode and PLANmode. MAP mode shows the flight plan route related to aircraft heading. TCAS mode shows a partialcompass arc with proximity, traffic, and resolution advisories relative to the position of the aircraft. VORmode shows a compass rose and VOR course deviation. APPR mode shows a compass rose and ILS coursedeviation.PLAN mode shows the flight plan route related to true north.

You control the navigation display data from the electronic instrument system (EIS) control panel.

GS 461TAS 481

205°/ 70

HDG MAG270 HEC 71NM/ 8.5

PDZ

DAGHEC

HEC27

PSP

TRM

TNP

PKEBLH

EED

BLD

L

VOR/NDB R/INAV

RNG 160WHT

TLT -3.0

11:5500:15

22

23

2425

26 27 2829

30

31

32

270°/ 71NM HEC HEC 270°/ 71NM

TRUEAIRSPEED

GROUNDSPEED

HEADINGSCALE

AIRCRAFTTRACK

MAGNETICOR TRUE

PRECISIONHEADING/TRACK

FMS "TO"WAYPOINTDISTANCE

TIMECLOCK

DISPLAY

CURRENTTIME UTC

COUNTUP/DOWNCLOCK/

ELAPSEDFLIGHT TIME

DESTINATIONRUNWAY

FMSVERTICALDEVIATION

VERTICALDEVIATION

SCALE

AIRCRAFTVERTICALPOSITION

WEATHERRADAR

ANNUNCIATORDISPLAY

NAV 2RADIODATA

DISPLAY

NAV 1RADIODATA

DISPLAY

AIRPLANESYMBOL

FMSFROM

WAYPOINT

HALFRANGE

DISPLAYRING

FMSNAV

MODE

WINDDISPLAY

MISSEDAPPROACH

CDU MSG

TCASANNUNCIATIONS

DRAG MSG

ACTIVEMAP MODE

DISPLAYAREA

80

PRESELECTEDHEADING



MINIMUMSRA BARO

PUSH RESETWX BRT

PUSH ON/OFF

MAG TRU

MAP VOR TCAS

PLAN APPR

TRFC DATA WPT VORNDB ARPT

VOR1

ADF1

INCR

DECR

VOR2

ADF2

RANGE

IN

HP

BAROSETQFE QNH

PULL - STD

BAROSETQFE QNH

PULL - STD

IN

HP

VOR1

ADF1

INCR

DECR

VOR2

ADF2

RANGE


MAG TRU

MAP VOR TCAS

PLAN APPR

MINIMUMSRA BARO

PUSH RESETWX BRT

PUSH ON/OFF

EIS CONTROL PANEL

PURPOSE - Sets data on the primary flight display and navigation display.

FUNCTION - There are two EIS control panels. The EIS control panels are on the left and right side of theGLARESHIELD. The display control panel sets data on the primary flight display and navigation display.

VOR1

ADF1

INCR

DECR

VOR2

ADF2

RANGE

NAV INFORMATION CONTROL BUTTONS

PURPOSE - Select NAV Radios to display info on NAV Display, and to Adjust Range Displayed

FUNCTION - Bearing pointer control push buttons are used for selection of VOR 1 and VOR 2 or ADF 1and ADF 2 bearing pointers, and provide directional information to the radio station.

Range push buttons: INCR (Increase) and DECR (Decrease), allows range selection of 10, 20, 40, 80, 160,320, and 640 nautical miles.

BOEING 717



IN

HP

BAROSETQFE QNH

PULL - STD

MAG TRU

MINIMUMSRA BARO

PUSH RESET

PURPOSE - Set the altimeter

IN HP PUSH BUTTON

FUNCTION - Push the IN HP push button to set inches of mercury or hectopascals.

BAROSET KNOB

FUNCTION - The BAROSET knobs set the altimeter. The inner knob sets thebarometric pressure, and the outer knob sets QFE (altitude above the field) or QNH(altitude above sea level).Pull the knob to set a standard altimeter of 29.92 inches of mercury or 1013.2hectopascals.

MINIMUMS KNOB

PURPOSE - Set the minimum altitude

FUNCTION - The MINIMUMS knobs set the minimum altitude. The outer knob letsthe crew set RA (Radio Altitude) or BARO (barometric altitude) as the referencesource. The inner knob is for the selection of the minimums altitude. You can pushthe inner knob to set again the minimums alert after the aircraft reaches the setminimums.

MAG TRUE PUSH BUTTON

PURPOSE - Set magnetic or true heading

FUNCTION - The MAG (Magnetic) TRUE push button lets the crew set magnetic ortrue heading on the navigation display.




MAP VOR TCAS

PLAN APPR

WX BRT

PUSH ON/OFF

MODE SELECT / DECLUTTER BUTTONS

PURPOSE - Control format and declutter modes on the Navigation Display.

FUNCTION -Mode select push buttons to select: map mode (MAP), VOR, APPR ( ILS), plan mode (PLAN),TCAS mode (TCAS).

Declutter push buttons: control additional data on the navigation display. When set:TRFC (Traffic) push button shows other aircraft in the area.DATA push button shows flight plan cross track deviation.WPT push button shows additional non-flight plan waypoints.VOR/NDB (Non-Directional Beacon) push button shows non-tuned VOR and NDB stations.ARPT push button shows airports in the navigation data base that are in range that can handle theaircraft.

FUNCTION -WX BRT PUSH ON/OFF: rotating the knob controls the weather radar display brightness. Pushingthe knob selects between weather display and EGPWS.

WEATHER RADAR DISPLAY KNOB

PURPOSE - Control Weather / EGPWS information on Navigation Display.

BOEING 717



FUNCTION - PLAN mode shows the flight plan route related to true north.NAV DISPLAY PLAN MODE

NAV DISPLAY MAP MODE

FUNCTION - MAP mode shows the flight plan route related to aircraft heading.



NAV DISPLAY TCAS MODEFUNCTION - TCAS mode shows a partial compass arc with proximity, traffic, and resolutionadvisories relative to the position of the aircraft.

NAV DISPLAY VOR AND APPR MODE

FUNCTION - VOR and APPR mode shows a compass rose and VOR and APPR course deviation

BOEING 717



ENGINE / ALERTS DISPLAY (EAD)FUNCTION - The engine and alert display shows the engine parameters. The display also showsEPR limit, thrust rating mode, and TAT (Total Air Temperature) at the top of the display.The lower part of the display is the Alerting Section.

TOTAL AIR TEMP DISPLAY

PURPOSE - To display air temperature used to set engine thrust ratings.

THRUST LIMIT DISPLAY

PURPOSE - To display current calculated thrust limit.

EPR

N1

TGT

N2

FF

1.44

80.0

390

90.02500

1.44

80.0

390

90.02500


APU ON

HYD L PRES LO

HYD

A-ICE ALL ON

THROTTLESETTING

THRUST LIMIT

TOTAL AIRTEMPERATURE

ENGINEPRESSURERATIO

N1 % RPM (FAN/LPT SPEED

N2 % RPM (HPC/HPT SPEED

FUEL FLOW (LBS/HR OR KG/HR)

TAKEOFF/LANDINGESSENTIAL ITEMS

CHECKLIST

ALERT MESSAGES

TGT CAUTION

TGT RED LINE

TURBINERED LINE

N1 RED LINE

ADVISORIES (LEVEL 0, ALERTS)

REMINDER MESSAGES

TURBINE GAS TEMPERATURE(HP TURBINE OUTLET)

1.55 CRZ LIM



TURBINE GAS TEMPERATURE (TGT) DISPLAY

PURPOSE - Indicates the engine's turbine temperature in degrees Celsius.

N2 ROTOR SPEED DISPLAYS

PURPOSE - Indicates the current operating speed of the high pressure spool, in terms of percentageof maximum operating speed.

ENGINE PRESSURE RATIO (EPR) DISPLAY

PURPOSE - Shows the current measured engine thrust setting parameter.

N1 ROTOR SPEED DISPLAY

PURPOSE - Indicates the current operating speed of the low pressure spool, in terms of percentageof the maximum operating speed.

FUNCTION - To indicate the power output of an engine using the inlet pressure vs exhaust pressureat the tail pipe , to display the maximum EPR for current conditions ("V-bug"), to display TRAcommanded thrust from FADEC ("T-bug), and to display the engine power setting relative to thecommand (inside line).

BOEING 717



FUEL FLOW DISPLAY

PURPOSE - Indicates the current fuel flow in pounds or kilograms per hour

ALERTS DISPLAY

FUNCTION - DISPLAYAlerts Display shows:1. Alerts2. Takeoff essential item checklist:

a. Slats not extendedb. Flaps not in takeoff rangec. Stabilizer not set for takeoffd. Rudder Trim not centerede. Parking brake setf. Spoiler handle not full forward

3. A reminder message - A reminder annunciation shows to remind the pilot that an alert is presenton a system page

4. Landing essential item checklist:a. Landing gear not down and locked with flaps in the landing rangeb. Slats not extendedc. Flaps not extended in the landing range.



SYSTEM DISPLAY SECONDARY ENGINE DISPLAY

PURPOSE - Shows the pressure of the engine oil for each engine.

FUNCTION - The secondary engine display shows:1 Engine oil pressure2 Engine oil temperature3 Engine oil quantity4 Gross weight5 Stabilizer trim6 Total fuel7 Cabin altitude and cabin rate8 Auxiliary power unit parameters9 Engine vibration.

The lower section shows alerts and consequences.

GWFUEL

CABIN ALTCABIN RATE

STAB 4.0 ANU

ENG OIL

PRESS

TEMP

QTY

0.2 N1 VIB 0.20.3 N2 VIB 0.2

6

100

78

6

100

78

NL NR

RUDAIL

LWD RWD

APU%RPM

100

%EGT80

108500 LB18500 LB

5400100

AIRCRAFTGROSS WEIGHT

CABINALTITUDE

CABIN RATECLIMB/DESC

STABILIZERPOSITION

APU % RPM

APU % EGT

OIL TEMP

OIL QTY

ENGINEALERTS

OIL QTYSTART

HIGHLOW

EVM N1EVM N2

PRESSURENORMAL

LOW

RUDDERTRIMINDICATOR

AILERONTRIM

INDICATOR

OIL TEMPCAUTION

WARNING

TOTAL FUELON BOARD

ALERTCONSEQUENCES

OIL PRESSURE

BOEING 717



GROSS WEIGHT & FUEL DISPLAY

NL NR

RUD

AILLWD RWD

STABILIZER POSITION

RUDDER TRIM INDICATOR

AILERON TRIM INDICATOR

APU RPM% INDICATION

PURPOSE - Provides an indication of the operating speed of the APU.

• APU RPM indicated in % RPM.• Normal on-speed = 100%± 1%• APU generator coupled directly to gearbox, gen. RPM (frequency) controlled by

APU ECU/rpm.

APU EGT INDICATOR (%)

PURPOSE - Provides an indication of the operating Exhaust Gas Temperature of the APU.• Reads in % degrees C.• 100% = max. continuous temp. & start temp. limit.• APU protected by auto shut down for over temp.

APU%RPM

100

%EGT80

STAB 4.0 ANU



ENGINE OIL PRESS DISPLAY

PURPOSE - Shows the pressure of the engine oil for each engine.

ENGINE OIL TEMP DISPLAY

PURPOSE - Shows the temperature of the engine oil for each engine.

ENGINE OIL QTY DISPLAY

PURPOSE - Shows the quantity of the engine oil for each engine.

ENGINE VIB DISPLAY

PURPOSE - To shows the relative engine vibration level for each engine, in units, as detected by theengine vibration monitoring system (EVMS).

0.2 N1 VIB 0.20.3 N2 VIB 0.2

78

100

6

BOEING 717



SYSTEM CONTROL PANEL (SCP)

FUNCTION -Other synoptic page selections on the systems display are set from the systems control panel.

The selections are:

1 ENG (Secondary Engine) page

2 HYD (Hydraulic) page

3 ELEC (Electrical) page

4 AIR page

5 FUEL page

6 CONFIG (Configuration) page

7 MISC (Miscellaneous) page

8 STATUS page

9 CONSEQ (Consequence) page

10 Navigation Display (ND) can be set on the systems display with less than six display units in

operation.

OFF

BRT1 2 3 4 5 6

ENG


ND CONSEQ STATUS



HYDRAULIC SYSTEM DISPLAY

HYDRAULICS

13.8 12.4

2800 2300

P

ENGINEDRIVENPUMPS

REVERSIBLEMOTOR PUMPS

SYSTEMPRESSUREREADOUT

ALERTLIST

CONSEQUENCEAREA

SYSTEMRESERVOIR

SYSTEMRESERVOIRQUANTITY

ELECTRICAUXILIARY

PUMP

OIL QTY AT ENGINE

START

BOEING 717



ELECTRICAL SYSTEM DISPLAY

ELECTRICAL

L DC

L AC

R DC

R AC

EMER DC

EMER AC

280.48

280.49

280.52

3240

115/4001.00

115/4001.00

115/400 115/4001.00APUG EXT

GS

DC XFER

G

ALERTLIST

ENGINEDRIVEN

GENERATOR

GENERATORRELAY

AC BUSTIE RELAY

DC BUSTIE RELAYSDC TIE BUS

LEFTDC BUS

EMERGENCYDC BUS

DC TRANSFER

BUS

LEFTDC BUS

EMERGENCYPOWER RELAY

EMERGENCYAC BUS

RIGHTAC BUS

GROUNDSERVICEAC BUS

BATTERY

RIGHTDC BUS

TRANSFORMERRECTIFIER

APUDRIVEN

GENERATOR

VOLTAGE/FREQUENCYLOAD (IN%) EXTERNAL

POWER

CONSEQUENCEAREA



PNEUMATIC SYSTEM DISPLAY

AIR

APU89 º 74 º

67 º 67 º

70 º 70 º

70 º 70 º

HOTCOLD HOTCOLD

32 32

CABIN

CLSD

OUTFLO

ALT 5488DP 7.6RATE 500LAND 710

TAILA-ICE

ZONETEMP

ºF

WINGA-ICE

MANUAL TEMPCONTROL VALVE

POSITION INDICATOR

BLEED AIRPRESSURE

ANTI ICESHUTOFFVALVES

PACKFLOW

CONTROLVALVE

CONDITIONED AIRMANIFOLD

CABIN

ALTITUDE

DIFFERENTIALPRESSURE

RATECLIMB/DESCENT

LANDING ALT

ALERTLIST

ENGINEBLEED AIR

VALVE

APUBLEED AIR

VALVE

ISOLATIONVALVE

CONSEQUENCEAREA

OUTFLOWVALVE

POSITION

ACTUAL ZONEDUCT

TEMPERATURES

ACTUAL ZONE TEMPERATURES

ZONE SET TEMPERATURES

32

BLEED AIRTEMPERATURE

EXT

EXT AIRSUPPLY

BOEING 717



FUEL SYSTEM DISPLAY

FUEL

APU

+10º C +10º C

8250

GW 108 500 LBFUEL 18 500 LB

BALLAST 5 000 LB

AUX TANK

QTY CHAN A

FUELSYSTEM

TEST

9500 9500

5200

4950

3650

8250

AIRCRAFTGROSS WEIGHT

BALLASTFUEL

APU ONINDICATION

FUEL TEMP

FWD AUXTANK

AFT AUXTANK

ENGINEALERTS

28V DCSTART PUMP

TOTAL FUELON BOARD

ALERTCONSEQUENCES

AUX TANK FUEL TRANSFER VALVES

RIGHT FWDBOOST PUMP

RIGHT MAINTANK

CENTERTANK

FUEL SYSTEM

TEST INDICATION

RIGHT AFTBOOST PUMP

LEFT FWDBOOST PUMP

LEFT AFTBOOST PUMP

CENTERBOOST PUMPS CROSS FEED

VALVE



CONFIGURATION DISPLAY

CONFIGURATION

STAB 4.0 ANU

SLAT EXT15 15

NL NR

RUDAIL

LWD RWD

RUDDERTRIMINDICATOR

FLAPPOSITION

SLATPOSITION

SPOILERPOSITION

LANDINGGEARPOSITIONINDICATOR

BRAKETEMPERATURE

BRAKETEMPERATURE

BRAKE PRESSURELEFT / RIGHT SYSTEM

AILERONPOSITION

ELEVATORPOSITION

STABILIZERTRIM

RUDDERPOSITION

AILERONTRIM

INDICATOR

ALERTLIST

CONSEQUENCEAREA

BRAKE PRESS600 / 2600120º C 540º C 120º C 540º C

BOEING 717



MISC DISPLAY

CONSEQUENCES DISPLAY

MISC

ALERTLIST

CONSEQUENCEAREA

CONSEQUENCES

ALERTLIST CONSEQUENCE

AREA

WING A-ICE OFF DEPART ICING AREA



STATUS DISPLAY

STATUS

ALERTLIST

ENG

HYD

ELEC

AIR

FUEL

CONFIG

MISC

MAINT

BOEING 717



HDG MAG270

2425

26 27 28 2930

20

10

10

20

20

10

10

20

340

320

306

300

280

.820

31500

310

30500

200080

432

1

0

1

234

.820 THRUST NAV HOLD 31000

API

BARO 200

29.92

HDG MAG270

2425

26 27 28 2930

20

10

10

20

20

10

10

20

340

320

306

300

280

.820

31500

310

30500

200080

432

1

0

1

234

.820 THRUST NAV HOLD 31000

API

BARO 200

29.92

GS 461TAS 481

205°/ 70


PDZ

DAGHECPSP

TRM

TNP

PKEBLH

EED

BLD

L

VOR/NDB R/INAV

RNG 160WHT

TLT -3.0

11:5500:15

22

23

2425

26 27 2829

30

31

32

270°/ 71NM HEC HEC 270°/ 71NM

GS 461TAS 481

205°/ 70


PDZ

DAGHECPSP

TRM

TNP

PKEBLH

EED

BLD

L

VOR/NDB R/INAV

RNG 160WHT

TLT -3.0

11:5500:15

22

23

2425

26 27 2829

30

31

32

270°/ 71NM HEC HEC 270°/ 71NM

1.04

80.0

390

90.02500

EPR

N1

TGT

N2

FF

1.04

80.0

390

90.02500


APU ONA-ICE ALL ON

GWFUEL

CABIN ALTCABIN RATE

STAB 0.0 AND

ENG OIL

PRESS

TEMP

QTY

0.2 N1 VIB 0.20.3 N2 VIB 0.2

16

100

278

16

100

278

APU%RPM

100

%EGT80

108500 LB18500 LB

5400120

NL NR

RUDAIL

LWD RWD

OFF

BRT1 2 3 4 5 6

ENG


ND CONSEQ STATUS

ELECTRONIC INSTRUMENT SYSTEM RECONFIGURATION

With all six display units functional, there are two Primary Flight Displays (PFD), two NavigationDisplays (ND), one Engine and Alert Display (EAD), and one System Display (SD). If any displayunit fails the VIA to reconfigure the screens automatically.

The program in the versatile integrated avionics units contains a matrix of sixty-four separatereconfiguration options. The versatile integrated avionics units use the best configuration and movethe images on the display units to new positions.

If a display unit has a power loss, (or other detected failure) then the other display units reconfigureautomatically, with no manual input.

If an aircraft has one failed display unit, and it is not possible to replace the unit, the aircraft isdispatchable. All the display units are identical and interchangeable. For example, with the failedunit in the number four position, and the number four brightness control to off, the crew has:

1. Two primary flight displays (screens one and six)2. One navigation display (screen two)3. One engine and alerts display (screen three)4. One system or navigation display (screen five).

If a second display unit fails after takeoff and the flight crew turns the brightness control to OFF, thedisplay units will reconfigure. In the example, display unit number six fails.

With 2nd failed unit they will have:1. Two primary flight displays (screens one and five)2. One system or navigation display (screen two)3. One engine and alert display (screen three).



FUNCTION - The function of the alert system is to make the flight crew aware of aircraft operations. Itdoes this by visual indications on the instrument panel. The engine and alert display can show 18 alertsat the bottom of the screen. Each level of alerts is visually different so its priority is recognizable even ifthe display unit does not show colors.

Level 3 alerts have the highest priority and are at the top of the list. The alerts are red text, inside a redbox, with a red triangle on the left side. The alerts start at the top of the left column and go down andright. The master warning lights on the instrument panel and the applicable cue light on the systemscontrol panel illuminate when there is a level 3 alert.

Level 2 alerts are the subsequent highest priority. They are amber text, inside an amber box. These alertsare displayed below any level 3 alerts on the engine and alert display. They also go down and right fromthe upper left . The master caution lights on the instrument panel and the applicable cue light on thesystems control panel illuminate for level 2 alerts.

Level 1 alerts have the subsequent lower priority. They are amber text, with no box around them. Level1 alerts are displayed below any level 3 or 2 alerts. They also go from the upper left, and down to theright. The master caution lights on the instrument panel and the applicable cue light on the systemscontrol panel illuminate for some level 1 alerts.

Level 0 alerts are advisory messages. They are cyan text, with no box around them. Level 0 alerts aredisplayed in the right collum above the reminder messages. if there are more level 0 alerts than will fit inthe right collum they will start at the bottum of the center collum.

THE ALERT SYSTEM

BOEING 717



At the lower right corner of the engine and alert display is the reminder section. A reminder showswhen you reset an alert from the systems control panel. A cue light on the systems control panel forthe faulted system illuminate when a level 1 or 2 alert shows on the engine and alert display. Level 3alerts will not be displayed in the reminder section, but always indicates on the engine and alertdisplay. When you push a lighted cue switch the cue light extinguishes.

This can cause:1 The amber caution lights to reset off2 The associated synoptic page, with the alert, to display on the system display3 The alert on the engine and alert display to extinguish.4 A system reminder to show in the reminder section. The reminder will show the highest level of

alert that is currently active in that system.

There is a type of alert that does not display on the engine and alert display, or make the mastercaution lights illuminate. This type of alert is a reminder message. A reminder message will flash onthe engine and alert display and cause the applicable cue light to illuminate. No master caution lightor alert on the engine and alert display will illuminate. Push the applicable cue switch on the systemcontrol panel to view the synoptic page and alert message.

MASTER

CAUTION

MASTER

WARNING

STICKPUSHERPUSH TOINHIBIT

OUTBOARD GLARESHIELD

PURPOSE - Provides indication of Master Warning, Master Caution, And Stick Pusher

♦ Master Warning Illuminates when Level 3 Alert is present♦ Master Caution Illuminates when Level 2 Alerts and some Level 1 alerts are present♦ Stick Pusher Push to Inhibit is used to disable stick pusher at CAPT Or FO Command.



IAS

MACH

HDG

TRK

FEET

METER

V/S

FPAMACH .820 HDG 245 APPR/LAND FT 31000 FPA

PROFNAVFMSSPD

AFS1

OVRD OFF2

AUTO FLIGHTAUTO

5

1015

20

25

--.--

FLIGHT CONTROL PANEL

PURPOSE - Provides control over the Auto Flight System

SPEED CONTROL PANEL

PURPOSE - Provides lateral control over the Auto Flight System

LATERAL CONTROL PANEL

PURPOSE - Provides control over the Auto Flight System Speed and selection of speed

IAS

MACHMACH .820

FMSSPD

IAS/MACHCHANGE OVER

BUTTON

IAS/MACHSELECT KNOB

IAS/MACHDISPLAYWINDOW

FMS SPDSWITCH

HDG

TRK

HDG 245

NAV

AUTO5

1015

20

25

HDG/TRKCHANGE OVER

BUTTON

HDG/TRKSELECT KNOB

HDG/TRKDISPLAYWINDOW

NAVSWITCH

BOEING 717



PURPOSE - Provides vertical control over the Auto Flight System

VERTICAL (ALTITUDE) CONTROL PANEL

PURPOSE - Provides control over AutoPilot, AutoThrottle, and AFS Override.

AUTO FLIGHT CONTROL SWITCHES

APPR/LAND

AFS1

OVRD OFF2

AUTO FLIGHT

AFS OVRD OFFSWITCHES (2)

AUTO FLIGHT(AUTO PILOT/

AUTOTHROTTLE)SWITCH

APPR/LANDARM SWITCH

FEET

METER

V/S

FPA

FT 31000 FPA

PROF

--.--FEET/METER

CHANGE OVERBUTTON

FEET/METERDISPLAYWINDOW

FEET/METERSELECT KNOB

PROFSWITCH

VS/FPACHANGE OVER

BUTTON VS/FPADISPLAYWINDOW

VS/FPASELECT KNOB



ENGINE FIRE HANDLE (L&R)

PURPOSE - Use for fire warning indication and to initiate fire control.

FUNCTION -IN - Normal positionOUT AND NEUTRAL - Pulling the handle silences the aural warning, trips the generator controlrelay, shuts off the engine fuel, shuts off the supply of hydraulic fluid to the engine driven hydraulicpump, and energizes fuel cutoff on the respective engine.ROTATE RIGHT - discharges fire agent bottle #2ROTATE LEFT - discharges fire agent bottle #1

ADVISORY - Red warning lights within the handle are illuminated by the test circuit or the enginefire detection system.

ENGINE FIRE PANEL

L

ENG

FIRE

PULL

AGENTDISCH

1 2

L

ENG

FIRE

PULL

R

ENG

FIRE

PULL

AGENTDISCH

AGENTDISCHAGENT 1

LOW

AGENT 2LOW

FIRETEST

FAULTTEST

1 2 1 2

BOEING 717



FIRE TEST SWITCH (LEFT SW)

PURPOSE - Use to test fire detection and protection system and the Pneu-matic Overheat Detection System (PODS).

FUNCTION -FIRE TEST OFF - Normally spring loaded to off position.MOM - When moved to this position the following will illuminate:MASTER WARNING LIGHTS (2), ENGINE FIRE HANDLES (2), EAD Alerts ENGINE L FIRE,ENGINE R FIRE, APU FIRE. PODS Test Pass, AURAL WARNING (fire bell sounds then "fire leftengine" then "fire right engine", then "apu fire"Note: If PODS test fails PODS test pass will not display and an alert will be displayed for each failedsensor .

.

FAULT TEST SWITCH (RIGHT SW)

PURPOSE - Use to test fire detection system for faults.

FUNCTION -FAULT TEST OFF - Normally spring loaded to off position.MOM - When moved to this position the following will illuminate:MASTER CAUTION LIGHTS (2), EAD Alerts FIRE DET L FAIL, FIRE DET R FAILSTATUS Page Messages FIRE DET L FAIL, FIRE DET R FAIL, APU FAIL

AGENT 1 & 2 LOW LIGHTS (2)

PURPOSE - Use to determine that an extinguisher bottle has been discharged.

ADVISORY - Amber illumination occurs when low pressure switch senses low pressure in the firebottle (fire agent has been discharged).

AGENT 1LOW

AGENT 2LOW

FIRETEST

FAULTTEST



FLIGHT NO

1 2 3 4

FLIGHT NUMBER PANEL

LEFT

LEFT

NOSE

NOSE

RIGHT

RIGHT

GEAR HANDLE AND LIGHTS

BOEING 717



TRAINING PURPOSES ONLY OVERHEAD - 47 TECHNICAL DEVELOPMENT


GROUND SERVICE SWITCH / LIGHT

PURPOSE - Use to selectively power the Ground Service AC, DC Transfer and EMER AC bus from anExturnal power source without having to energize the remainder of the electrical system. The Main Extpower switch must be in the off position.FUNCTION -OFF - Ground Service power supplied by normal power sources.ON - Supplies external power to the ground service AC, DC Transfer and EMER AC bus if external poweris available and the Main Ext power switch is in the Off position and no other source of power is present.Ctr DC bus tie and AC tie bus relays are commanded open if no engines are running.

ADVISORY - Blue, Ground power (ON) light will illuminate indicating EXT power is being supplied to theGround Service bus.

GROUND SERVICE PANEL

ONON

OFF

GROUND SERVICE ELEC PWR

ONON

OFF

TECHNICAL DEVELOPMENT OVERHEAD - 48 TRAINING PURPOSES ONLY


MICROPHONE SWITCH/LIGHTS

PURPOSE - Used to select desired transmission.

AUDIO CONTROL PANEL ( 3 TOTAL)

FUNCTION - Microphone select.PUSH - To select desired transmission for VHF 1, VHF 2, VHF3, HF1, HF2,or INTerphone.Integral light illuminates to indicate selection. Mechanical interlock allows only one switch/light to belatched down at a time.

(1) LOCATED ON AFT OVERHEAD FOR OBSERVER, AND (2) LOCATED ON OUTBOARD CONSOLEFOR CAPTAIN, AND FIRST OFFICER.

C C C C C C

C

1-VOR-2 1- ILS -2 1-ADF-2

1-DME-2

VHF1 VHF2 VHF3 HF1 HF2

MIC SELECTOR / CALL

CAB IDENT PA INT

RADIOMKR

INT

ON

C C C C C C

VHF1 VHF2 VHF3 HF1 HF2

MIC SELECTOR / CALL

INT



VHF -1, VHF-2, VHF-3, HF -1, HF-2 AND INT KNOBS

PURPOSE - Used to select and control the volume of the desired VHF and HF communications radios andthe Flight Interphone..

FUNCTION - POP OUT TO SELECT AUDIO, ROTATE TO CONTROL VOLUME.PUSH IN TO DESELECT AUDIO VHF - ROTATE CLOCKWISE - To increase volume. The audio of as many comm channels as desired maybe on simultaneously. An auto-listen feature in the audio control panel is on with the selection of eachmicrophone switch. The communication channel audio for the set microphone is automatically on even ifthe volume is not on.

HF - ROTATE CLOCKWISE - To increase volume. The audio of as many comm channels as desired maybe on simultaneously.

INT - ROTATE CLOCKWISE - To increase volume for communications between the flight crew and theground crew through the interphone jack at the external power panel.

VHF1 VHF2 VHF3 HF1 HF2 INT

FUNCTION - Microphone select. PUSH - To select Cabin Service INTerphone. Integral light illuminates toindicate selection.Volum Control Knob - Pop out to select audio, rotate to control volume. Push in to deselect audioCAB - ROTATE CLOCKWISE - To increase volume.

When the MAINTENANCE INTERPHONE SWITCH (Ext Power panel) is ON, the ten maintenancesystem jacks also couple into the interphone system.

PURPOSE - Used to select the mic and control the volume of audio communication heard in the headsetbetween the cockpit, the cabin attendant stations, and the maintenance jacks at the radio racks and externalpower panels.

CAB/SERV INT MIC AND VOLUME CONTROL KNOB

C

CAB



PA MIC AND VOLUME CONTROL KNOB

PURPOSE - Used to select and control the MIC and volume of the passengeraddress system. PA button controls microphone. Volume control only affects thecockpit sidetone, or volume of PA transmitions from the cabin as heard in thecockpit - not the transmission volume.

FUNCTION - pop out to select audio, rotate to control volume. Push in to deselect audioROTATE CLOCKWISE - To increase volume.

RADIO / INT SWITCH

PURPOSE - Used to transmit on the radio selected by the mic selector switch on theaudio control panel when using a boom or mask mike, and as an alternate means oftransmitting over the flight interphone system.

FUNCTION -Three position switch, momentary, spring loaded to the center (off) position.RADIO - Hold switch to transmit on the selected radio system. This switch has priority over the hand mic.INT - Hold switch to transmit over the flight interphone using boom or mask mics. Transmission will occurregardless of the setting of the INT mic select button. This function has priority over all other radio trans-missions.

ID FILTER BUTTON

PURPOSE - Use to hear the station identification tone.

FUNCTION -When you set the ID (Identification) push button switch, the ON light comes on. A 1,020 Hz filter is Deacti-vated so that the station identification tone is heard. In the normal cockpit condition its ID is not on and notones are heard.

IDENT

ON

PA

INT

RADIO



NAVIGATION RADIO VOLUME CONTROL KNOBS

PURPOSE - Used to select the audio and control the volume of the audio of the desired navigation radiosheard in the headset.

FUNCTION - Pop out to select audio, rotate to control volume. Push in to deselect audioROTATE CLOCKWISE - To increase volume. The audio of as many navigation channels as desiredmay be on simultaneously.

1-VOR-2 1- ILS -2 1-ADF-2

1-DME-2

MKRMKR KNOB

PURPOSE - To select the audio and control the volume of the audio of the marker beacons heard in theheadset.

FUNCTION - Pop out to select audio, rotate to control volume. Push in to deselect audioROTATE CLOCKWISE - To increase volume.

EVENT PUSHBUTTON

PURPOSE - Used to mark an event in Flight Recorder memory.

FUNCTION -PUSH - To mark an event on the system memory if an abnormal situation occurs during flight.

FLIGHT RECORDER

EVENT



ENG FIRE DET SYSAPU

LOOPSA BOTHB

R ENGLOOPS

A BOTHB

L ENGLOOPS

A BOTHB

APU / L&R ENG LOOPS SWITCH

PURPOSE - To select the normal operating mode of the fire detection system or to deactivate a faultysystem.

FUNCTION -BOTH - Normal position. Both A and B fire detector loops are active, allows either loop to operate andindicate a fire.LOOPS A - disconnects loop B from the fire warning system for the respective engine and makes loop A thesingle source of fire detection.LOOPS B - disconnects loop A from the fire warning system for the respective engine and makes loop B thesingle source of fire detection.

FIRE DETECTOR PANEL



NAV OFF NAV OFF NAV OFF

1 AUX 2

OFFNAV

OFFNAV

OFFNAV

IRS MODE SELECTOR

IRU MODE SELECTOR

PURPOSE - Used to Align IRU 1 , 2 , or aux (if installed) .

FUNCTION -OFF - De-energizes unit 10 .NAV - Normal "ON" position. IRU will automatically function through alignment mode and enter naviga-tion mode once position information has been entered.

AUX IRU Placarded INOP if not Currently Installed.

NAV OFF

1

OFFNAV



PURPOSE - Indicates proper function during test.

COCKPIT VOICE RECORDER

PURPOSE - Microphone records all audible sound in the flight compartment.

FUNCTION -Records 4 channels of audio when aircraft power is connected.The audio management unit supplies the captain's and first officer's hot microphone audio to thecockpit voice recorder. The cockpit area microphone output goes to the cockpit voice recorder. Theaft pedestal handset earphone audio from the passenger address system, (or cabin/maintenanceinterphone earphone audio if PA is not selected to the headset ) goes back to the cockpit voicerecorder.

COCKPIT AREA MICROPHONE

PURPOSE - Microphone records all audible sound in the flight compartment.

FUNCTION -Records when aircraft power is connected.

COCKPIT VOICE RECORDER STATUS

FUNCTION - Green light indicates proper function

COCKPIT VOICE RECORDER MICROPHONE MONITOR

STATUS

ERASE TEST

HEADPHONE



COCKPIT VOICE RECORDER ERASE SWITCH

PURPOSE - Used to erase the audio content of the cockpit voice recorder.

COCKPIT VOICE RECORDER TEST SWITCH

PURPOSE - To test the cockpit voice recorder.

FUNCTION - When pushed, enables test function. Illuminates the status light and provides a testtone to the headphone jack at completion of test.

COCKPIT VOICE RECORDER HEADSET JACK

PURPOSE - Use to plug in headset.

FUNCTION - When headset is plugged in and test switch is pushed, 600Hz tone (accompanied bystatus light) indicates that the cockpit voice recorder system is operational.



OFF

ANTISKID

OFF

T/O

MEDMIN

MAX

AUTO BRAKE

HIGH

ANTI-SKID SWITCH

PURPOSE - Used to select mode of anti-skid system.FUNCTION -OFF - Anti-skid system inoperative. Foot pressure on brake controls hydraulic pressure on the brakes.ON - After main wheel spinup, the anti-skid system will reduce pilot applied brake pressure as necessary toprevent tire skidding and obtain maximum available braking. The system is active down to approximately10 knots.

ANTI-SKID PANEL

APU PANEL

ON

OFFOFF

DISCH

APU

OFFMASTER

FIRE CONTNORM

FIRE AGENT AIRNO-1 NO-2

OFF&AGENT ARM

START

RUN



PURPOSE - Use to initiate APU fire control.

FUNCTION -NORM - position of switch for normal operation.OFF & AGENT ARM - Moving switch to this position shuts down the APU, closesthe APU fuel valve, trips the APU generator control relay, closes the APU bleed airvalve (load control valve) and arms the APU fire agent.

APU FIRE CONTROL SWITCH

APU FIRE AGENT NO 1 & NO 2 SWITCHESPURPOSE - Use to discharge fire agent bottle number 1 or 2 into the APUcompartment.FUNCTION - DISCH - push and hold (momentary), discharges respectivefire extinguishing agent into the APU compartment.ADVISORY - Discharging the bottle causes the respective AGENT LOW lightto illuminate. (on main instrument panel)

OFF

DISCH

FIRE AGENTNO-1 NO-2

FIRE CONTNORM

OFF&AGENT ARM

ON

OFFAIR

OFFMASTER

START

RUN

APU AIR SWITCH

PURPOSE - Use to control the pneumatic output of the APU for pneumatics or air-conditioning.

FUNCTION - Two position switch -OFF - Commands APU load bleed valve closed.ON - Commands APU load bleed valve to open if APU is available and there is adownstream pneumatic "user" ( pack or Engine start valve )

APU MASTER SWITCH

PURPOSE - To control the starting, operation and shutdown of the APU.

FUNCTION - Three position switch -OFF - Shuts down the APU.RUN - Allows for normal operation of the APU after the start sequence has beeninitiated.START (momentary) - Initiates the automatic start sequence.



ON

R SYS

OFFL PUMP

AUX

HYDRAULICS

TRANS

R PUMP

L SYS

ON

OFFON

OFF

ON

OFFHYD CONTRUDDER

OFF

HYDRAULIC PANEL

HYD CONT RUDDER SWITCH

PURPOSE - Used to select either powered or manual rudder operation.

FUNCTION -NOT ILLUMINATED - Rudder will operate hydraulically.OFF / ILLUMINATED - When pushed, deselects hydraulic operation of the rudderwith reversion to manual control of rudder tabs.

HYD CONTRUDDER

OFF

HYDRAULICS

13.8 12.4

2800 2300

P



TRANS HYD PUMP SWITCH

PURPOSE - To allow either hyd system to pressurize the other system.

FUNCTION - The XFER (Transfer) PUMP switch controls the motor operated shutoff valve for thepower transfer unit.ON - Mechanically connects RH and LH hydraulic systems by opening a motor operated shutoffvalve in the right wheel well.OFF - Removes power to the trans pump by closing a motor operated shutoff valve in the rightwheel well.

AUX HYD PUMP SWITCH

PURPOSE - Used to control the function of the AUX hydraulic pump.

FUNCTION -ON - Energizes the AUX HYD PUMP.OFF - De-energizes the AUX HYD PUMP

The auxiliary hydraulic pump operates when the AUX (Auxiliary) PUMP switch is ON and 115VAC power is available. The auxiliary pump pressurizes the right hydraulic system only.

ENG HYD PUMP SWITCH

PURPOSE - Used to control the engine driven hydraulic pump.

FUNCTION -ON - Allows the ENG HYD PUMP to pressurize the system.OFF (AC PWR NORMAL) - Electrically depressurizes the ENG HYD PUMP.

TRANS

ON

OFF

AUX

ON

OFF

ON

OFFL PUMP

L SYS



ON

L GEN

OFF

AUTO

OPEN

RBUSTIE

RESETEXT

AUTO

OPEN

LBUSTIE

ON

OFF

RESET

ON

OFF

RESET

ON

OFFR GEN

AUTO

OPENDC BUS TIE

GALLEY

ELECTRICALL DCBUS

R DCBUS

OFF

ON

BATT

ON

OFF

EMER PWR

ONOFFARM

EMER PWRIN USE

L ACBUS

AVAILEXT AVAIL

APU

R GEN

EXT

APU

L GEN

R ACBUS

APU

ELECT PWR PANEL

ELECTRICAL

L DC

L AC

R DC

R AC

EMER DC

EMER AC

280.48

280.49

280.52

3240

115/4001.00

115/4001.00

115/400 115/4001.00APUG EXT

GS

DC XFER

G



BATT

ON

OFF

EMER PWR

ONOFFARM

EMER PWRIN USE

AUTO

OPENDC BUS TIE

DC BUS TIE SWITCH

PURPOSE - Used to connect the left and right DC busses allowing DC power to besupplied from one side to the other.

FUNCTION -AUTO - Allows EPCU to control DC bus tie relays automatically

OPEN - Causes the DC bus tie relays to become de-energized, the left, center, and right DC buses cannot bejoined.

BATTERY SWITCH

PURPOSE - Used to connect battery power to the DC transfer bus, emergency powerswitch and battery charger, ready to activate mode.

FUNCTION -OFF - Disconnects the battery from the battery charger , and disconnects the DCtransfer bus from the battery, if it was receiving power from the battery.

ON - Connects the battery to the battery charger it also connects the DC transfer busto the battery. Places the battery charger in the charge mode.

EMER PWR SWITCH

PURPOSE - Used to connect battery power, automatically or manually, to the emer-gency AC bus (through the inverter), DC emergency bus and DC transfer bus.

FUNCTION -OFF - (RESET) - Causes the emergency power relay to trip and the emergency bussensing circuit is "RESET".NOTE: To reset the Electrical Power Control Unit EPCU automatic emergency circuitafter an EPCU initiated emergency power mode, the switch is moved to the "OFF"position.ARM - Causes the EPCU to energize the emergency power relay upon loss of normalpower to any one of the 3 emergency busses (AC, DC emergency and DC transfer)enabling the battery and inverter to power these busses.

ON - (Override) The emergency power relay is energized and connects the battery asthe power source for the AC emergency bus through the inverter, DC emergency andDC transfer bus.



EXT

APU

R GEN

AUTO

OPEN

LBUSTIE

ON

L GEN

OFF

RESET

L & R BUS CROSS TIE SWITCHES

PURPOSE - Used to control the appropriate bus tie relay and connect the left or rightAC bus to the TIE bus.

FUNCTION -OPEN - Causes the EPCU to isolate the TIE bus from the respective AC generator busby opening the respective bus tie relay.OPEN - RESET - (Bus tie lockout condition) If a bus tie lockout mode exists due to afault, the bus tie system will automatically reset when the airplane is on the groundprovided the fault no longer exists.AUTO - Allows the bus tie relays to close automatically connecting the TIE bus to therespective AC generator bus, providing all protection circuits are satisfied and the TIEbus has priority.

GENERATOR CONTROL SWITCHES

PURPOSE - Used to connect respective ac generator power to associated electri-cal busses or reset tripped generator control relays.

FUNCTION -RESET - Position is momentary and is used to reset the respective generator control relay (GCR).OFF - Causes the Electrical Power System (EPS) to disconnect the respective generator power relay fromthe respective bus.ON - Causes the EPS to close the respective generator relays which connect power to the respective genera-tor busses, providing all related protection circuits are satisfied and the respective engine is operating.

APU POWER IN USE LIGHTS

PURPOSE - Visual indication of APU power is supplying power to bus.

EXT PWR IN USE LIGHT

PURPOSE - Visual indication of external power is supplying power to bus.

ENG GEN IN USE LIGHT (AC X TIE)

PURPOSE - Visual indication of opposite engine driven generator is supplyingpower to bus.



GALLEYOFF

ON

APU PWR AVAIL LIGHT / APU POWER SWITCH

PURPOSE - Indicates APU generator power is available.

EXT PWR AVAIL LIGHT / EXT PWR SWITCH

PURPOSE - Used to supply external power to the TIE bus.

FUNCTION -ON - to select external power if it is available. External power will power bus if buscross tie is armed and power is not being provided by Engine Driven Generator orAPU.OFF - External power relay will be opened

PURPOSE - Used to supply APU power to the TIE bus.

PURPOSE - Indicates external generator power is available.

GALLEY POWER SWITCH

PURPOSE - Used to supply AC power to aircraft galleys.

FUNCTION -OFF - Causes the electrical power to be disconnected from the galleys.ON - Causes the Electrical Power System (EPS) to supply power to the aircraftgalleys by closing the galley power relay(s), providing one generator is not supplyingboth main generator busses except during ground operations with the APU generator.(Exception: System logic will cause the galleys to be "Shed" whenever only one mainpower source or only the APU, when airborne, is supplying electrical power.

FUNCTION -RESET - Position is momentary and is used to reset the respective generator controlrelay (GCR).OFF - Causes the Electrical Power System (EPS) to disconnect the respective genera-tor power relay from the respective bus.ON - Causes the EPS to close the respective generator relays which connect power tothe respective generator busses, providing all related protection circuits are satisfiedand the respective engine is operating.

ON

OFF

RESET

AVAIL

APU

EXT

ON

OFF

AVAIL



CKPT TEMPAUTO

HOTCOLDSTOPMAN

CABIN TEMPAUTO

HOTCOLDSTOPMAN

L PACK R PACKOFF

AUTO

OFF

AUTO

OFF

AUTO

OFF

AUTO

R BLEEDL BLEEDAUTO

CLSD

OPEN

AIR

ISOL

FLOWHIGH

NORM

PACKSHUTDOWN

OVRD

AUTO

OVRD

FAN

OFF

ON

AVIONICSCOOLING RAM AIR

AIR CONDITIONING PANEL

AIR

APU89 º 74 º

67 º 67 º

70 º 70 º

70 º 70 º

HOTCOLD HOTCOLD

32 32

CABIN

CLSD

OUTFLO


TAILA-ICE

ZONETEMP

ºF

WINGA-ICE

32

EXT



AIR COND AUTO SHUTOFF SWITCH

PURPOSE - Shuts off packs on ground for engine fail at Take off

FUNCTION -AUTO - Allows auto shutdown of packs at Take offOVRD - Overrides auto shutdown and keeps pack on

RAM AIR SWITCH

PURPOSE - Use to vent the airplane with unconditioned outside air.

FUNCTION -OFF - (Normal) Ram air valve is closed.ON - Opens ram air valve and allows unconditioned outside air to enter the right airconditioning system for aircraft ventilation.NOTE: The ram air switch may be used on the ground or in flight.

AVIONICS RACK FAN SWITCH

PURPOSE - Use to select the normal or alternate method of cooling the radio rackequipment.

FUNCTION -FAN - (Normal in flight) Activates the primary radio rack fan, arms the circuitry forautomatic actuation of the standby radio rack fan in case of primary failure, andcloses the venturi valve. Conditioned air from the radio rack is exhausted under theforward cargo compartment floor for heating.OVRD -In flight, deactivates the radio rack fans and opens the venturi valve.NOTE: On the ground, the switch position is overridden: both fans are on andventuri is closed regardless of switch position.

OVRD

FAN

AVIONICSCOOLING

OFF

ON

RAM AIR

PACKSHUTDOWN

OVRD

AUTO

FLOWHIGH

NORM

AIR FLOW CONTROL SWITCH

PURPOSE - Selects Air Flow Mode

FUNCTION -HIGH - Provides maximum airflow through the cabin (21 CFM per pessenger)NORM - Normal pack flow



CKPT TEMPAUTO

HOTCOLDSTOPMAN

L PACKOFF

AUTO

OFF

AUTO

L BLEED

AUTO

CLSD

OPEN

ISOL

CABIN / CKPT TEMP SELECTORS

PURPOSE - To adjust cockpit temperature automatically or manually.

FUNCTION -AUTO - Rotate selector left of index (colder) or right of index (warmer) to adjusttemperature and automatically maintain it.MANUAL - Rotate selector until index points at STOP; selector will go into adetent.COLD - Momentary; moves temperature control valve towards cold.HOT - Momentary; moves temperature control valve towards hot.STOP - Detent; when selector is in manual it is spring loaded to the STOP (off)position; any movement of the temp control valve is halted.

AIR CONDITIONING PACK SUPPLY SWITCHES (LEFT and RIGHT)

PURPOSE - To control the operation of the respective air conditioning pack.

FUNCTION -OFF - Shuts down the air conditioning pack.AUTO - Opens flow control valves, .

BLEED AIR SUPPLY SWITCHES (LEFT and RIGHT)

PURPOSE - To control the operation of the respective pressure regulating valve

FUNCTION -OFF - Shuts down the respective pressure regulating valve .AUTO - Allows Pneumatic System Controler to operate the respective pressureregulating valve

ISOLATION VALVE SWITCH

PURPOSE - To control the operation of the isolation valve

FUNCTION -CLSD - Closes the isolation valve .OPEN - Opens the isolation valve .AUTO - Allows Pneumatic System Controller to operate the isolation valve (Normally Closed)



AUTO

ON

STARTPUMP

ON

OFF

IGNITION

SELECT

ALTN

SELECT

ALTN

ENGINESFADEC MODE

L ENG R ENG

ENG STARTL R

START PUMP SWITCHPURPOSE - Provides 28 Volt DC power to the DC START PUMP to providefuel pressure to start the APU.

FUNCTION -OFF - Removes DC power from fuel pump.ON - Completes the circuit from the DC transfer bus to the start pump.

IGNITION SWITCH

PURPOSE - To select the ignition system mode of operation.

FUNCTION -ON - Both igniters of an engine are energized continuously when the engine'sfuel switch is placed on.AUTO - (autostart), one igniter A or B is energized. The EEC alternates whichigniter is energized from one start to the next. (Above-idle operation) -Therespective igniter is energized in "A" or "B" automatically during takeoffs,landings, sub-idle excursions, surges and when engine anti-icing is on. (AutoStart) - The EEC automatically energizes the A or B igniter selected duringengine start.

ENGINE START PANEL / FUEL PANEL

AUTO

ON

IGNITION

STARTPUMP

ON

OFF



SELECT

ALTN

SELECT

ALTN

FADEC MODEL ENG R ENG

ENG STARTL R

FADEC MODE SELECT SWITCH

PURPOSE - Use to command EEC to revert to the N1 mode ofthrust control.

FUNCTION -DARK - Engine operating in normal EPR modeSELECT and ALTN illuminated - Engine has automatically reverted to N1 modeALTN illuminated - Switch has been selected to N1 mode

ENGINE START SWITCH

PURPOSE - Use to open engine starter air valve.

FUNCTION -OUT AND LATCHED (ON) - Commands EEC to open the enginestarter air valve. The EEC will automatically close the valve andunlatch the start switch when the N2 reaches starter cutoff speed.IN AND UNLATCHED (OFF) - Commands the EEC to close theengine starter air valve.

INDICATION: - SELECT ALTN illuminates if reversion is for EEC control fault.



FUEL SYSTEST

FUEL QTYA / B

OFF

OFF OFF OFF

OFF OFFOFF

ON

ON ON ON

ONON

LEFT CTR RIGHT

FUEL

AFT PUMPS

FWD PUMPS

AFT TANK XFER

A B

AUTO

OFF

FWD TANK XFER

A B

AUTO

FUEL

APU

+10º C +10º C

8250

GW 108 500 LBFUEL 18 500 LB

BALLAST 5 000 LB

AUX TANK

QTY CHAN A

FUELSYSTEM

TEST

9500 9500

5200

4950

3650

8250

FUEL PANEL



FUEL SYSTEM TEST BUTTON

FUNCTION - The FUEL SYS (system) TEST is a push button that starts a test of thefuel system indication.

A/B QUANTITY CHANNEL BUTTON

PURPOSE - Use to select between two fuel quantity channels.

FUNCTION -Pressing button selects the opposite channel. When channel "B" is selected "B" isdisplayed "A" is blank when selected..

FUEL QTYA / B

FUEL SYSTEST

OFF

ON

AFT PUMPS

OFF

ON

FWD PUMPS

OFF

AFT TANK XFER

A B

AUTO

OFF

FWD TANK XFER

A B

AUTO

AFT BOOST PUMP SWITCHES (3 EA, LEFT CENTER RIGHT)

PURPOSE - Provide electrical power to the AFT fuel pump(s).

FUNCTION -OFF - Removes AC power from fuel pump.ON - Completes the circuit enabling pump operation.

FWD BOOST PUMP SWITCHES (3 EA, LEFT CENTER RIGHT)

PURPOSE - Provide electrical power to the FWD fuel pump(s).

FUNCTION -OFF - Removes AC power from fuel pump.ON - Completes the circuit enabling pump operation.

PURPOSE - Use to test fuel system.

AUX TANK TRANSFER VALVE SWITCHES

PURPOSE - Provide electrical power to the aux tank fuel transfer valves.

FUNCTION -OFF - Removes electrical power from the aux tank fuel transfer valves.AUTO - Completes the circuit enabling valve operation.



GPWS TERR OFF

GNDPROXWARN

FLAP OVRD

NORM

TEST

OFF

GROUND PROX WARN SWITCH

PURPOSE - Used to test and inhibit ground proximity warning system.

FUNCTION -FLAP OVRD - Inhibits warning when landing is made with less thannormal landing flap configuration.NORM - System annunciates dangerous situations while remaining silentduring normal flight operations.TEST - (Momentary) Provides system integrity tests.

GNDPROXWARN

FLAP OVRD

NORM

TEST

INOP

GPWS TERR OFF

OFF

GROUND PROX WARN PANEL

GROUND PROX WARN TERR SWITCH

PURPOSE - Inhibits terrain warning of enhanced GPWS

FUNCTION -OFF - Disables EGPWS Terrain WarningDARK - Normal Mode



CABIN PRESS

MANUALMANUALLDG ALT

CLIMB

DESC DECR

INCR

OP

CL

CLOSED

VALVE


0 10 20 25 30 35

0 2 4 6 8

SELECT

MANUAL

SYSTEM

PRESSURIZATION PANEL

AIR

APU89 º 74 º

67 º 67 º

70 º 70 º

70 º 70 º

HOTCOLD HOTCOLD

32 32

CABIN

CLSD

OUTFLO


TAILA-ICE

ZONETEMP

ºF

WINGA-ICE

32

EXT




0 10 20 25 30 35

0 2 4 6 8

OP

CL

CLOSED

VALVE

MANUAL

CLIMB

DESC

SELECT

MANUAL

SYSTEM

MANUALLDG ALT

DECR

INCR

LAND ALT switch

PURPOSE - Use to manually set cabin altitude.

FUNCTION -INCR - Increases landing altitude on air pageDECR - Decreases landing altitude on air page.

MANUAL CABIN ALT SCHEDULE

PURPOSE - Use to aid pilot in manually setting cabin altitude.

OUTFLOW VALVE POSITION INDICATOR

PURPOSE - Use to monitor outflow valve position

MANUAL CABIN ALTITUDE CONTROL SWITCH (MOM)

PURPOSE - Use to manually set landing altitude

FUNCTION -CLIMB - moves outflow valve in open direction, increases air outflow, decreases cabinpressure, increasing cabin altitude.DESC - moves outflow valve in closed direction, reduces air outflow, increases cabinpressure, decreasing cabin altitude.

PRESSURIZATION SYSTEM SELECTOR SWITCH

PURPOSE - Use to select manual system control

FUNCTION -SELECT - Illuminates when automatic system fails.MANUAL - When Manual control is selected, MANUAL light illuminates.



ICE PROTECTION

AIR DATA HEAT

AIR FOILWING TAIL

OFF

ON

WING ICE DET

RESET

TEST

L RENG

OFF

OFF

ON

ON


OFF

ICE PROTECT PANEL



PURPOSE - To energize all air data heaters

FUNCTION -

Normal (DARK) - Provides power to all air data probe heaters

OFF - Removes power from all air data probe heaters

AIR FOIL ANTI-ICE SWITCH

PURPOSE - Use to provide anti-ice capability for wing

FUNCTION -2 Position switchOFF - Pressure regulator closed, system deactivated.ON - Pressure regulator opens to provide temperature controlled air to the system. The system providesanti-icing to the wing.

TAIL ANTI-ICE SWITCH

AIR FOILWING

OFF

ON

AIR FOILTAIL

OFF

ON

PURPOSE - Use to provide anti-ice capability for horizontal stabilizerleading edges.

FUNCTION -2 Position switchOFF - Tail Anti Ice Pressure regulator closed, system deactivated.ON - Tail Anti Ice Pressure regulator opens to provide temperature controlled air to the system. The systemprovides anti-icing to the horizontal stabilizer leading edges.

AIR DATA HEATAIR DATA HEAT

OFF



PURPOSE - Use to provide anti-ice and bird strike protection for thethree windshields.

WINDSHIELD ANTI-ICE SWITCH.

FUNCTION - 2 position switchOFF - system deactivatedON - system activated.

PURPOSE - Use to provide anti-fog capabilities to the three wind-shields, both eyebrow and both clearview windows.

ENG L & R ANTI-ICE SWITCHES

PURPOSE - Use to provide anti-ice capabilities to the engines.

FUNCTION -OFF - all valves are closedON - Energizes electrical circuits, opens 1 valve per engine to pro-vide temperature controlled regulated air to the engine nose cowl.

WING ICE DETECT RESET / TEST

OFF

ON


WING ICE DET

RESET

TEST

L RENG

OFF

ON

PULL TO DIM TEST

ENGEXCEEDANCE

RESET

FUELUSEDRESET

ANNUN LT

ANNUN LT TEST, AND RESET PANEL



PULL TO DIM SWITCHPURPOSE - Used to dim annunciations and indicator lights.

FUNCTION -When pulled - Dims all annunciations and all dimmable warning, caution andadvisory lights on the instrument panel and overhead

ANNUN LTS TEST BUTTON

PURPOSE - Used to illuminate all annunciations and digital lights for testpurposes.

FUNCTION -TEST (momentary) - Push to test annunciations and the digital lights. PutsDisplays in test mode

FUEL USED RESET BUTTON

PURPOSE - Use to reset the fuel used values to zero.

FUNCTION -OUT (open) - normal position.Momentary On - Fuel used values are reset to zero.

ENG EXCEEDANCE RESET

FUNCTION - Resets Emer. Reverse, N1 Overspeed, TGT Exceedance, and N2Overspeed on EAD

PULL TO DIM

TEST

FUELUSED

RESET

ENGEXCEEDANCE

RESET



CKPTDOOR

PARK

FAST

SLOW

WINDSHLD WIPEROFF

OFF

STBYCOMP

DIM

BRT

PARK

FAST

SLOW

WINDSHLD WIPEROFF

CAPT & FO WINDSHIELD WIPER PANEL

WINDSHIELD WIPER SWITCH

PURPOSE - Used to operate the windshield wipers.

FUNCTION -ROTARY SELECT SWITCH.PARK - Places the wiper blades at the bottom of the windshield.OFF - Wiper motor de-energized.SLOW - Wiper motor operates at reduced rate.FAST - Wiper motor operates at fast rate.

COCKPIT DOOR SWITCH

PURPOSE - To UNLOCK COCKPIT DOOR

FUNCTION -Push to unlock cockpit door. Overrides manual locking latch

STBY COMP LT SWITCH

PURPOSE - Lighting for standby compass

FUNCTION -OFF - Extinguishes standby compass lights.DIM - Illuminates standby compass internal light.BRT - Illuminates standby compass floodlights and extinguishes internal standbycompass light .

PARK

FAST

SLOW

WINDSHLD WIPEROFF

CKPTDOOR

OFF

STBYCOMP

DIM

BRT



OFF

OFF

OFF

OFF

EXTOFF

OFF OFF

OFF OFF OFF

OFFOFF

OVHDPNL FLOOD


DOME

THNDRSTRM

ON

EMERLT

ARM

ON ONON

LEFTON

RIGHTON

CKT BRKLT

NOSMOKE

SEATBELTS

DIM

BRTAUTO

LDG LTRET

EXT ON

NOSE LT

TAXI

LDGON

RONLY

WING/NACL

PA ATTND

CALL

GND FLOOD LTL R NAV

L R

CALLRESET

EXT

MECHMAINTINTPH

CALL ON

INOP BCN HI-INT

PAIN USE

VIDEOIN USE

LIGHT CONT PANEL

DOME LIGHT

FUNCTION - Push to turn cockpit dome light on or off

OVHD PNL / FLOOD LT SWITCH

FUNCTION -OFF -Extinguishes Cockpit Overhead Floodlights and Overhead Panel lights.OUTER KNOB - Adjusts Overhead Panel lights.INNER KNOB - Adjusts Cockpit Overhead Floodlights.

DOME

OFF

OVHDPNL FLOOD

OFF

EMERLT

ARM

ON

EMER LTS SWITCH

PURPOSE - Used to control the emergency lights

FUNCTION-OFF- Prevents emergency lights from illuminating. Connects battery packs charg-ing circuits to DC TRANSFER BUS. EMER NOT ARMED alert is displayedandamber lamp in portable emergency light is extinguished.NOTE- OFF position of the EMER LTS switch can be overridden and emergencylights illuminated at the EMERGENCY LIGHT switch on the forward attendant'spanel.ARM - Normal flight position. Emergency lights are extinguished. Connectsbattery packs charging circuits to EMERGENCY DC BUS and illuminates amberlight in portable emergency light. Emergency lights illuminate automatically ifEMER DC BUS is interrupted.ON- Simulates loss of EMER DC BUS. All emergency lights illuminate.



FUNCTION -OFF - Extinguishes circuit breaker panel flood lights.DIM - Illuminates circuit breaker panel dim floodlights.BRT - Illuminates circuit breaker panel bright floodlights.

CKT BKR LT SWITCH

OFF

CKT BRKLT

DIM

BRT

NO SMOKE SWITCH

FUNCTION -AUTO - NO SMOKING signs illuminate when landing gear is extended. ChimesoundsOFF- Extinguishes NO SMOKING signs, Chime sounds.ON- Illuminates NO SMOKING signs. Chime sounds.NOTE: NO SMOKING signs illuminate whenever cabin altitude exceeds 10,000feet, regardless of switch position.

SEAT BELTS SWITCH

FUNCTION -AUTO - FASTEN SEAT BELT and RETURN TO CABIN signs illuminate whenleading edge slats are extended. Chime soundsOFF- Extinguishes FASTEN SEAT BELT and RETURN TO CABIN signs, Chimesounds.ON- Illuminates FASTEN SEAT BELT and RETURN TO CABIN signs. Chimesounds.NOTE: FASTEN SEAT BELT signs illuminate whenever cabin altitude exceeds10,000 feet, regardless of switch position.

PA BUTTON/LIGHT

FUNCTION -WHEN PUSHED - connects handset to the passenger address system (Handsetmust be off hanger prior to button being pushed).

PA / VIDEO IN USE LIGHT

PURPOSE - Indicates PA in use and Video in use

OFF

ON

NOSMOKE

AUTO

OFF

ON

SEATBELTS

AUTO

ON

PA

PAIN USE

VIDEOIN USE



ATTND

CALL

CALLRESET

MECH

CALL

MAINTINTPH

ON

OFFTHNDRSTRM

ATTENDANT CALL BUTTON

PURPOSE - When pushed, alerts the cabin attendant of a pending call from thecockpit. When lighted, alerts cockpit of pending call from cabin

FUNCTION -WHEN PUSHED - Activates a high-low (Bing-Bong) chime through the forward,mid, and aft cabin attendants speakers.CALL light illuminates when attendant calls from cabin.

ATTENDANT CALLING ANNUNCIATOR RESET

FUNCTION -RESET - Used to reset and extinguish the attendant calling annunciation.

EXT MECH CALL

EXT MAINT INTPH CALL

FUNCTION -PUSH TO CONNECT MAINT INTERPHONE TO CABIN INTERPHONE.

THNDRSTRM LT SWITCH

FUNCTION -OFF - Returns control of lighting to individual controls.ON - Overrides individual lighting controls and illuminates all cockpit floodlightsto full intensity.

PURPOSE - When Lighted used to alert cockpit of call from mechanic

FUNCTION -WHEN PUSHED - Activates the mechanic horn in the wheel well. (also used toreset warning horn if battery switch is left on )

PURPOSE - To brighten cockpit lighting to prevent flash blinding around thunder-storms.



INSTR & PED PNL / FLOOD LT SWITCH

FUNCTION -OFF -Extinguishes Cockpit Instrument Panel and Pedestal Floodlights andPanel lights.OUTER KNOB - Adjusts Instrument Panel and Pedestal Panel lights.INNER KNOB - Adjusts Instrument Panel and Pedestal Floodlights.

OFF


EXTOFF

LDG LTRET

EXT ON

L R

OFFNOSE LT

TAXI

LDG

OFF

ONR

ONLY

WING/NACL

LANDING GEAR LTS SWITCH (2) L, R

PURPOSE - Extend, Retract, Turn On, and Turn Off Respective landing gearlights

FUNCTION-RET - Retracts and extinguishes respective landing gear lightEXT OFF - Extends, does not illuminate respective landing gear lightEXT ON - Extends and illuminates respective landing gear light

NOSE GEAR LTS SWITCH

PURPOSE - Turn ON, and turn OFF nose gear taxi and landing lights

FUNCTION-OFF - Turn Off Nose Gear Taxi and Landing lightsTAXI - Turn On Nose Gear Taxi lightsLAND - Turn On Nose Gear Landing lights

WING NACELLE LTS SWITCH

FUNCTION-OFF - Turn Off Wing and Nacelle lightsON - Turn On Wing and Nacelle lightsR ONLY - Turn On Right Wing and Nacelle lights

PURPOSE - Turn ON, and turn OFF Wing and Nacelle lights



LEFTON

RIGHTON

GND FLOOD LTL R

OFF

NAV

OFF

BCN

OFF

HI-INT

FUNCTION-PUSH - Turn On orTurn Off Respective Ground Floodlights

GND FLOOD LTS SWITCH

PURPOSE - Turn On, and Turn Off Left and Right Ground Floodlights

FUNCTION-PUSH - Turn On or Turn Off Position Lights

POSITION LIGHTS SWITCH

The position lights are on the leading and trailing edges of both wing tips.

ANTI COLLISION LTS SWITCH

FUNCTION-PUSH - Turn On or Turn Off Anti-Collision Lights

FUNCTION-PUSH - Turn On or Turn Off Strobe Lights

STROBE LIGHTS

The strobe lights are on the leading and trailing edges of both wing tips. Thestrobe lights operate only when the aircraft is in-flight.

The anti-collision lights are on the top and bottom of the fuselage.

BOEING 717

TRAINING PURPOSES ONLY PEDESTAL - 85 TECHNICAL DEVELOPMENT


MCDU

DIRINTC


APPR


OUT

ATC

MENU

PAGE

DSPY FAIL

MSG

OFST

A

F

K

P

U

Z

B

G

L

Q

V

-

C

H

M

R

W

D

I

N

S

X

E

J

O

T

Y

+

1

4

7

/

2

5

8

3

6

9

0

BRT

CLRSP

MCDONNELL DOUGLAS CORPORATION - THIS INFORMATION IS SUBJECTTO DATA RIGHTS. LEGENDS ON TITLE PAGE OR FIRST PAGE. BOEING 717

TECHNICAL DEVELOPMENT PEDESTAL - 86 TRAINING PURPOSES ONLY

IAS FT360

340

306300

280

10

10

20 20

10

10 31100

31200

30900

30800

31000

29.92

BARO

ALIGN

1013 hPa

ALIGN

In Hg

STANDBY INSTRUMENTS

BOEING 717



CENTER PEDESTAL

OFF

STABILIZER TRIM

STABILIZER TRIM SWITCH

FUNCTION -Used to stop a primary trim runaway condition. Removes power and applies brake to stabilizer trimmotor. When the switch is returned to the normal position stabilizer trim power is restored.

GEARHORN

OFF

FUELX

FEED

ON

UP

0

13

18

25

40

FLAP/SLAT

FLAP T.O.SEL

STOW

20

19

0

13

18

25

EXT

UP/RET

FUELON

OFF

FUELON

OFFALTLONG TRIM

NOSEDN

NOSEUP

OFF

STABILIZER TRIM

SPDBRK

RET

EXT

STABILIZER TRIMEMERGENCY SHUTOFF

SPEED BRAKE/SPOILER CONTROL

FORWARD THROTTLE

STOP

THRUST REVERSECONTROL LEVERS THROTTLE

CONTROLLEVERS

AUTOTHROTTLEDISCONECT

BUTTONS

TO/GABUTTONS

FUELSWITCHES

LONG TRIMSWITCHES

GEAR HORNOFF SWITCH

TAKEOFFFLAP

SELECTOR

FLAPSLAT

HANDLE

FUELCROSS FEED

HANDLE



FUNCTION -MANUAL - In flight the lever is used to control the flight spoilers to act asspeed brakes by pulling the lever aft without arming to EXT position. Onground, lever may be used to deploy all spoilers during a rejected takeoffby pulling lever up-aft. Lever is also used to release AUTO GROUNDSPOILER by pushing down allowing it to move forward to RET position.ARMED - When armed prior to a takeoff and a rejected takeoff is initiated(nosewheel on ground and throttles retarded), flight and ground spoilerswill automatically extend to 60˚ upon actuation of reverse thrust levers.When armed prior to landing, flight and ground spoilers will automaticallyextend to 60˚, upon main wheel spinup or after nosegear ground shiftactuation. When spoilers extend fully to 60˚, spoiler lever will move fullyaft to EXT position. When armed (up), a red placard labeled ARM in whiteletters can be seen on both sides of lever.

PURPOSE - Used to position the SPOILER/SPEED BRAKES manually.

SPD BRK LEVER

SPDBRK

RET

EXT

THROTTLE LEVERS

PURPOSE - Use for setting forward thrust.

FUNCTION -Forward stop - The maximum takeoff thrust rating iscommanded when the throttles are at the forward stopand the airplane is within the takeoff envelope.Beyond the forward stop - When the throttles levers aremoved beyond the forward stop on the throttle module,the EEC reverts into the N1 mode of thrust control.

ADVISORY - SELECT and ALTN light on the N1 modeselect switch.

BOEING 717



THRUST REVERSE CONTROL LEVERS

PURPOSE - Use to command and set reverse thrust.

FUNCTION -FORWARD IDLE (TR control levers down) - Commands the EEC tosignal the directional control valve to reduce hydraulic pressure on thedeploy side of the thrust reverser, causing the actuators to move tostow.INTERLOCK DETENT - Thrust reverse control is limited to thisposition by EEC until the EEC is satisfied that there are no failures inthe reverser system that would prevent safe reverser deployment andthe doors are deployed 90%.REVERSE IDLE - Reverser is fully deployed, engine is operating atidle.MAXIMUM THRUST REVERSER CONTROL THROW - EECcommands maximum reverse thrust.EMERGENCY REVERSE - Levers moved aft beyond max reversedetent.

AUTOTHROTTLE DISCONNECT BUTTONS (2)

PURPOSE - Use either button to disconnect autothrottle. Use again to extinguishwarning lights.

FUNCTION -PUSH IN AND RELEASE - disconnects autothrottle.

GA BUTTONS (2)

PURPOSE - Use to initiate Go Around mode.

FUNCTION -PUSH IN AND RELEASE - Go Around mode.



FUELON

OFF

FUELON

OFF

ALTLONG TRIM

NOSEDN

NOSEUP

OFF

FUELX

FEED

ON

ALT LONG TRIM SWITCH

PURPOSE - Used to position the horizontal stabilizer using the Alternate (Slowrate) System (Electric motor)

FUNCTION -NOSE DN - When both momentary switches are moved to this position the stabilizer is trimmed nose down.NOSE UP - When both momentary switches are moved to this position the stabilizer is trimmed nose up.The left switch is the brake release switch.The right switch is the trim motor switch.

FUEL CROSS FEED HANDLE

PURPOSE - To balance fuel quantities.

FUNCTION -VALVE OPEN - Opens fuel cross feed valve to allow fuel burn of the tank withhigher quantity.VALVE CLOSED - Closes fuel cross feed valve.

FUEL SWITCH

PURPOSE - Use to open the Fuel Metering Unit (FMU) Fuel ON/OFF valve.

FUNCTION -ON - Commands the EEC to open the fuel on/off valve automatically when the correct N2 RPM is reachedduring auto start or at any N2 RPM during manual start.OFF - Energizes the ON/OFF solenoid to close the Fuel ON/OFF valve.

ADVISORY - In case of a fire warning the switch is illuminated with a red light as an aid to verify whichfuel switch to move to OFF, and will remain illuminated until the fire warning goes out, or the switch isplaced in the OFF position. The light is tested by pushing the annunciater lights test button on the overheadpanel.

BOEING 717



GEARHORN

OFF

STOW

20

19

GEAR HORN OFF BUTTON

PURPOSE - To cancel the "LANDING GEAR" aural warning, and landing gear horn.

FUNCTION -PUSHING the gear horn off button cancels the aural warning "LANDING GEAR" andthe warning horn except in flight when the landing gear is not down and locked and theflaps are extended more than 22.5 degrees.

FLAP SLAT HANDLE

PURPOSE - Used to select degree of trailing edge flaps. Leading edge slatsare automatically positioned.

FUNCTION -Provides takeoff flap settings between 0˚ to 20˚ and landing flap detents of25˚ and 40˚and optionally 50˚.SLAT RANGE - When flaps are 0˚ to 13˚ the slats are in the mid position.When the flaps are 0˚ to 50˚ the slats are in the extended position.

ADVISORY - Flap range from 0 to 40 or 50 degrees. Slat range RETRACT,and EXTEND.

FLAP TAKEOFF SELECTOR (DIAL A FLAP)

PURPOSE - Provides a moveable takeoff flap setting detent for any flap settingbetween zero and 20 degrees, in addition to the fixed 0, 13, and 18 degree flaptakeoff settings.

FUNCTION -STOW - The position selected to retract, the flap takeoff selector detent when theselector is not required.0 - 20 degrees - provides a flap takeoff setting between zero and 20 degrees in 1/2degree increments.

UP

0

13

18

25

40

FLAP/SLAT

0

13

18

25

EXT

UP/RET



VHF COMMUNICATION RADIO PANEL (2EA)

ACTIVE STANDBYTFR

COMM TEST

VHF

COMM

FUNCTION -The communication radio panel tunes one of two Very High Frequency (VHF) radios.There are two panelson the lower pedestal. Each communication radio panel has:1. An ACTIVE and STBY liquid crystal display2. A fine and coarse frequency tune knob3. A transfer switch

COMMUNICATION RADIO PANEL The ACTIVE display shows the tuned frequency and the set radio. The STBY display shows a presetfrequency. The fine and coarse frequency tune knobs let a person change the frequency in the STBY display.The transfer switch changes the frequency from STBY to ACTIVE and from ACTIVE to STBY.

THE STANDBY DISPLAY WINDOWThe standby display window shows the standby radio frequency.

THE ACTIVE DISPLAY WINDOWThe active display window shows the active radio frequency.

TRANSFER SWITCHPush the transfer push button and the ACTIVE and STBY displays change places. The frequency shown inthe STBY display is not active until a person pushes the transfer push button. The ACTIVE display andmemory contain the last frequency entered from a communication radio panel to the set radio.

FREQUENCY SELECTOR KNOBThe frequency selector knobs change the standby frequency only. When a person turns the knobs this causesthe STBY display and the frequency in standby memory to change. The inner knob sets the digits to the leftof the decimal and the outer knob sets the digits to the right.

PURPOSE - Used to tune VHF-1 of VHF-2 Radio Frequency. One panel for each Radio.

BOEING 717



SYSTEM CONTROL PANEL (SCP)

OFF

BRT1 2 3 4 5 6

ENG


ND CONSEQ STATUS

FUNCTION -The systems control panel is on the aft left side of the pedestal. The brightness adjust switches control thelevel of brightness and set the applicable display off. The lower portion of the panel has switch cue lightsthat set other synoptic pages on the systems display. The cue switches have white lights that illuminate whenlevel 3, 2, or 1 alerts occur. Pressing the cue switch when lit resets the light off.

The cue switch selections are:

1 HYD (Hydraulic) page2 ELEC (Electrical) page3 AIR page4 FUEL page5 CONFIG (Configuration) page6 MISC (Miscellaneous) page7 STATUS page8 CONSEQ (Consequence) page9 ND (Navigation Display) when there is less than six display units in operation.



FUEL SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW FUEL SYNOPTIC PAGE AND ALERTS

CONFIG SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW CONFIGURATION SYNOPTIC PAGE AND ALERTS

EIS DISPLAY CONTROL KNOB

FUNCTION -The brightness adjust switches control the level of brightness and set the applicable display off.

ENG SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW SECONDARY ENGINE DISPLAY (SED) AND ALERTS

HYD SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW HYDRAULIC SYNOPTIC PAGE AND ALERTS

ELEC SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW ELECTRICAL SYNOPTIC PAGE AND ALERTS

AIR SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW AIR SYNOPTIC PAGE AND ALERTS

OFF

1

ENG

HYD

ELEC

AIR

FUEL

CONFIG

BOEING 717



MISC SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW MISCELLANEOUS ALERTS PAGE

STATUS SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW SYSTEM STATUS PAGE AND ALERTS

CONSEQ SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW CONSEQUENCES PAGE AND ALERTS

ND SYSTEM DISPLAY SELECTOR BUTTON

FUNCTION -PUSH -TO SHOW NAVIGATION DISPLAY AND ALERTS IF LESS THAN SIXDISPLAYS OPERATIONAL.

MISC

STATUS

CONSEQ

ND

WEATHER RADAR CONTROL PANEL

OFF ONSTAB WX

TESTOFF

WX/TURBMAP

TILT

GAIN

AUTO MAX

UP

DN

WX RADAR

0

5 10

15

15

105



PREDICTIVE WINDSHEAR/WEATHER RADAR SYSTEM(predictive wind shear optional)

The main components of the Predictive Windshear (PWS)/weather radar system are the two weatherradar receiver transmitters, the weather radar control panel, the waveguide switch, the antenna pedestaland the flat plate antenna.The predictive windshear/weather radar system can show:1 Weather data display on the navigation displays2 Terrain display (ground map) on the navigation displays3 Predictive windshear condition on the navigation displays and alert messages on the primary flight

displays. The system supplies aural warnings to the audio management unit.

The weather radar control panel lets you set:1 One of the two weather radar receiver transmitters2 The tilt control (antenna)3 The gain control (display intensity)4 The mode of operation.

The captain's and first officer's mode select panels control the range of the applicable navigation display.Set the navigation display to the MAP, VOR/APPR, or TCAS mode to show the weather data.

The PUSH ON/OFF control on the EIS mode select panels can set the radar display and contrast on therelated navigation display.

The weather radar receiver transmitter sends weather mode data, precipitation, turbulence, and groundmapping data to the Versatile Integrated Avionics Units (VIA). The Versatile Integrated Avionics Units sendthe weather radar data to the Navigation Display (ND).

The antenna has an azimuth scan (side-to-side range) of 180 degrees and an elevation scan (up or downrange) of 43 degrees. The receiver transmitter units get attitude data from the inertial reference system. Thisdata keeps the antenna stable during attitude changes.

The weather radar receiver transmitters interface with:

1 The radio altimeters for radio altitude to let the predictive windshear mode operate2 The Air Data Inertial Reference Units (ADIRU) -1 and -2 to obtain airspeed3 The Flight Control Computer (FCC) to stop predictive windshear alerts while in a windshear condition4 The Traffic alert and Collision Avoidance System (TCAS) to stop the resolution advisory and aural

annunciations5 The Ground Proximity Warning System (GPWS) to stop the aural annunciations6 The air/ground relay, parking brake switch, engine fuel shutoff relays, and the landing gear lever control

relay input discretes. The inputs activate PWS operation automatically in air, and also set the takeoff andland mode of operation.

BOEING 717



WEATHER RADAR SYSTEM CONTROL SWITCH

FUNCTION -Stabilization

WEATHER RADAR GAIN CONTROL

FUNCTION -Adjusts weather radar display intensity on the navigation display

The system has a built-in-test function. The navigation displays show the test pattern when the mode selectswitch, on the weather radar control panel, is in the TEST position.

There is also a TEST button on the front of the receiver transmitter unit. The liquid crystal display on thefront panel shows the status of the system test.

OFF ONSTAB

GAIN

AUTO MAX

WXTEST

OFFWX/TURB

MAP

TILT

UP

DN

0

5 10

15

15

105

WEATHER RADAR MODE CONTROL

Function -USED TO SELECT WEATHER RADAR MODE OF OPERATION SELECTSBETWEEN: TEST, WX (Weather), TURB (Turbulence), and MAP MODE.The system has a built-in-test function. The navigation displays show the testpattern when the mode select switch is in the TEST position. During the test,PWS (Predictive Windshear) alert messages on PFDs and PWS aural alerts maysound depending on the aircraft condition.

WEATHER RADAR ANTENNA TILT CONTROL

FUNCTION -To set the degree of tilt for the weather radar antenna.



ATC

IDENT

ALT OFFSTBY

ALT ONTA

TA/RATEST

ATC

1

2

ATC 2 R

1234

ALT OFFSTBY

ALT ONTA

TA/RATEST

ATC

1

2

FUNCTION -STBY - Places both Mode-S transponders and TCAS system in standby.ALT OFF - Activates transponder without altitude reporting. TCAS system in standby.ALT ON - Activates transponder with altitude reporting. TCAS system in standby.TA - Traffic advisory mode. Presents traffic location on TA display but does not issue resolution advisories.TA/RA - Traffic advisory and resolution advisory mode. Presents traffic location on displays and issuesaudio and visual resolution advisories for traffic determined to be a threat.

TCAS/TRANSPONDER FUNCTION SELECTOR

FUNCTION -1/2 - Selects one of the two Mode-S transponders to be active. The remaining transponder is placed instandby.

TRANSPONDER SELECTOR SWITCH

ATC CONTROL PANEL

BOEING 717



TRIM PANEL

ATC 2 R

1234

ATC

IDENT

FUNCTION -Displays code selected with the code selectors. Also indicates whichof the two transponders is active.

CODE INDICATOR DISPLAY WINDOW

ATC / IDENT BUTTON

FUNCTION - Used to select transponder codes. There are twoouter knobs and two inner knobs. The left outer knob tunes thefirst digit on the left (shown as 1); left inner knob tunes thesecond digit from the left (shown as 2); right inner knob tunesthe third digit from the left (shown as 3); right outer knobtunes the fourth digit from the left (shown as 4)

CODE SELECTOR KNOBS

FUNCTION -Used to identify aircraft on interrogating ground radar systems.

AILERON TRIM RUDDER TRIM

LEFTWINGDOWN

RIGHTWINGDOWN

NOSEL

NOSER

RDRCTR



AILERON TRIM CONTROL

FUNCTION -Move both switches toward LEFT WING DOWN or RIGHT WING DOWN - Deflects an aerody-namic trim tab on each aileron.Aileron trim Indication on Secondary Eng Display , or Config Display.

PURPOSE - Trims the ailerons to provide roll trim of the aircraft.

RUDDER TRIM CONTROL

PURPOSE - To trim the rudder or rudder control tabfor yaw trim of the aircraft.

FUNCTION -Rotation of the knob towards NOSE LEFT orRIGHT - Trims rudder during power or manualoperation and trims rudder control tab during manualoperation.Rudder trim Indication on Secondary Eng Display ,or Config Display.

AILERON TRIM

LEFTWINGDOWN

RIGHTWINGDOWN

RUDDER TRIM

NOSEL

NOSER

RDRCTR

RUDDER TRIM CENTERING BUTTON

PURPOSE - To center rudder trim

FUNCTION -Pushing button automatically centers rudder trim.

BOEING 717

TRAINING PURPOSES ONLY GLOSS - 101 TECHNICAL DEVELOPMENT


ABBREVIATIONS GLOSSARY

AABS .............................................................. Auto Brake SystemAC ................................................................. Alternating CurrentACARSAircraft Communications Addressing and Reporting SystemACP ............................................................. Audio Control PanelADF ...................................................Automatic Direction FinderADIRU ....................................... Air Data Inertial Reference UnitADL ...........................................................Airborne Data LoaderADM .................................................................. Air Data ModuleADS ...................................... Automatic Dependent SurveillanceAFS ............................................................... Auto Flight SystemA-ICE............................................................................... Anti-IceAIL .................................................................................... AileronALN ..................................................................................... AlignALT .................................................................. Altitude; AlternateALTN .............................................................................AlternateAND............................................................ Airplane Nose DownANNUN .................................................................... AnnunciatorANP ........................................... Actual Navigation PerformanceANT ................................................................................AntennaANU................................................................. Airplane Nose UpAOC .........................Aeronautical Operational CommunicationsAP.................................................................................. AutopilotAPCDU APU .............. Power Conversion and Distribution UnitsAPU ............................................................. Auxiliary Power UnitAREU ......................................... Audio Remote Electronics UnitARPT................................................................................ AirportARR................................................................................... ArrivalA/S ................................................................................ AirspeedAT or A/T ...................................................................AutothrottleATC ................................................................. Air Traffic ControlATR ...............................................Automatic Thrust RestorationATS...............................................................Autothrottle SystemATT .................................................................Attitude, AttendantATTND..........................................................................AttendantAUTO .......................................................................... AutomaticAUX ............................................................................... AuxiliaryAVAIL .............................................................................Available

BOEING 717

TECHNICAL DEVELOPMENT GLOSS - 102 TRAINING PURPOSES ONLY


BBARO .........................................................................BarometricBATT ................................................................................BatteryBLS ............................................................... Bezel Light SensorBRT .................................................................Bright; Brightness

CC......................................................................... Celsius, CenterCAP ................................................................................ CaptureCAPT...............................................................................CaptainCAWS.......................................... Central Aural Warning SystemCG .................................................................... Center of GravityCH, CHAN ......................................................................ChannelCHR ....................................................................... ChronographCKPT............................................................................... CockpitCL ..................................................................................... ClosedCLB .................................................................................... ClimbCLMP ................................................................................ClampCLR .................................................................................... ClearCMD ........................................................................... CommandCMP,�<Ùo0TR ComputerCOMM ................................................................ CommunicationCONFIG .................................................................ConfigurationCONT .......................................................... Control; ContinuousCONSEQ............................................................... ConsequenceCPA ................................................... Closest Point of A`∑2oachC/PDLC ......................Controller/Pilot Datalink CommunicationsCRS................................................................................. CourseCRZ ...................................................................................CruiseCTR ......................................................... Center; Crosstie RelayCVR....................................................... Cockpit Voice Recorder

DDC .........................................................................Direct CurrentD/D ............................................................................... DriftdownDECR ...........................................................................DecreaseDEG ................................................................................ Degree

BOEING 717



DEP ............................................................................. DepartureDES, DESC .................................................................... DescentDEST......................................................................... DestinationDET .................................................. Detector; Detection, DetectDFDAU .................................. Digital Flight Data Acquisition UnitDFDR .............................................. Digital Flight Data RecorderDH ...................................................................... Decision HeightDIR INTC.............................................................Direct InterceptDISAG ...........................................................................DisagreeDME .......................................... Distance Measuring EquipmentDTG.....................................................................Distance To GoDTW ......................................................... Distance To WaypointDU ............................................................................ Display Unit

EEAD ...................................................... Engine and Alert DisplayECON ........................................................................... EconomyECP ...................................................... Electronic Control PanelECU......................................................... Electronic Control UnitE/D .....................................................................End Of DescentE/E ...............................................................Electrical/ElectronicEEC .................................................... Electronic Engine ControlEGT ................................................... Exhaust Gas TemperatureEIS ............................................... Electronic Instrument SystemELEC ...............................................................Electric; ElectricalEMER ........................................................................ EmergencyENG ................................................................................. EngineENG OUT D/D ........................................... Engine Out DriftdownE/O ............................................................................ Engine OutEPCU ............................................ Electrical Power Control UnitEPR ......................................................... Engine Pressure RatioET.......................................................................... Elapsed TimeETA..................................................... Estimated Time Of ArrivalETD .............................................. Estimated Time Of DepartureETE .................................................... Estimated Time En RouteEXEC ............................................................................. ExecuteEXT ...................................................................External; Extend

BOEING 717



FF ................................................................................. FahrenheitFADEC ........................... Full-authority Digital Electronic ControlFANS ............................................ Future Air Navigation SystemFCC ....................................................... Flight Control ComputerFCOM.......................................... Flight Crew Operating ManualFCP ............................................................. Flight Control PanelFD .........................................................................Flight DirectorFF .................................................................. Final Approach FixF-F............................................................................... Fuel FlowFGS ....................................................... Flight Guidance SystemFL ..............................................................................Flight LevelFLAR ................................................................................... FlareFLEX TO .................................................................. Flex TakeoffFLO ..................................................................................... FlowFLR ..................................................................................... FlareFLT ..................................................................................... FlightFLT DIR .................................................................Flight DirectorFLT RCDR .......................................................... Flight RecorderFMA ...................................................... Flight Mode AnnunciatorFMC ............................................ Flight Management ComputerFMS................................................. Flight Management SystemF/O ............................................................................First OfficerFPA ................................................................... Flight Path AngleFPM.......................................................................... Feet/MinuteFQS ...........................................................Fuel Quantity SystemFREQ ......................................................................... FrequencyFT ......................................................................................... FeetFWD ............................................................................... Forward

GG .......................................... Acceleration Of Gravity, GeneratorGA, G/A ..................................................................... Go-AroundGEN ............................................................................ GeneratorGMT ........................................................ Greenwich Mean TimeGNSSU ........................ Global Navigation System Sensor UnitsGPS................................................... Global Positioning SystemGPWS .................................. Ground Proximity Warning SystemGS .............................................Ground Speed; Ground Service

BOEING 717



GS or G/S................................................................... GlideslopeGW ........................................................................ Gross Weight

HHDG ...............................................................................HeadingHF ......................................................................High FrequencyHI ..........................................................................................HighHLD ......................................................................................HoldHP ........................................................................ High PressureHYD.............................................................................. Hydraulic

II/O ........................................................................... Input/OutputIAS ................................................................ Indicated AirspeedIDENT...................................................... Identifier; IdentificationIDG ................................................... Integrated Drive GeneratorILS ................................................... Instrument Landing SystemINCR ............................................................................. IncreaseIN HG ............................................................. Inches of MercuryINIT........................................................................... InitializationINOP.......................................................................... InoperativeINSTR ........................................................................ InstrumentINT............................................................. Intercom; IntermittentINTC .............................................................................. InterceptINTPH ........................................................................ InterphoneIRS ................................................... Internal Reference SystemIRU ......................................................... Internal Reference UnitISA....................................... International Standard AtmosphereISOL ............................................................................... Isolation

KKIAS .................................................... Knots Indicated Airspeed

LL ............................................................................................ LeftLAND.............................................................................. LandingLAT .................................................................... Lateral; LatitudeLBS ................................................................................. PoundsLCDU .............................................. Liquid-Crystal Display Units

BOEING 717



LDG ................................................................................ LandingLED ............................................................. Light Emitting DiodeLIM ...................................................................................... LimitLNAV .............................................................. Lateral NavigationLND ..................................................................................... LandLO ........................................................................................ LowLO?dÓø‘�alizerLONG .......................................................................... LongitudeLP .......................................................................... Low PressureLRC .............................................................. Long Range CruiseLSK .................................................................... Line Select KeyLT(S)................................................................................ Light(s)LWD....................................................................Left Wing Down

MM ........................................................................... Mach, MetersMAG ............................................................................. MagneticMAINT .................................................................... MaintenanceMAN ......................................................... Manual, ManeuveringMAX ............................................................................ MaximumMAX ALT ......................................Maximum Engine Out AltitudeMAX CLB .......................................................... Maximum ClimbMAX DES ...................................................... Maximum DescentMAX END .................................................. Maximum EnduranceMB .................................................................................. MillibarsMCDU .............................Multipurpose Control and Display UnitMCL ......................................... Maximum Climb (Engine Rating)MCT..................... Maximum Continuous Thrust (Engine Rating)MECH...........................................................................MechanicMED ............................................................................... MediumMIC........................................................................... MicrophoneMIN...................................................................Minimum; MinuteMISC .................................................................... MiscellaneousMKR ................................................................................. MarkerMLG ............................................................. Main Landing GearMLW ...................................................Maximum Landing WeightMMEL .......................................Master Minimum Equipment ListMMO ................................................. Maximum Operating MachMOM ......................................................................... Momentary

BOEING 717



MSG ............................................................................. MessageMSP............................................................... Mode Select PanelMTES ...................................... Maintenance Test Enable SwitchMTOGW ................................... Maximum Takeoff Gross WeightMU...................................................................Management Unit

NN/A ......................................................................... Not AvailableNACL ............................................................................... NacelleN1........................................... Engine Low Pressure Rotor RPMN2.......................................... Engine High Pressure Rotor RPMNAV ............................................................................ NavigationND ................................................................. Navigation DisplayNDB....................................................... Non-Directional BeaconNL .................................................................................Nose LeftNLG .............................................................. Nose Landing GearNR ............................................................................. Nose RightNORM ............................................................................. Normal

OOFST..................................................................................OffsetOP ...................................................................................... OpenOVHD .......................................................................... OverheadOVRD ............................................................................ OverrideOXY.................................................................................Oxygen

PPA ................................................................. Passenger AddressPBD ......................................................Place/ Bearing/ DistancePBE .......................................... Protective Breathing EquipmentPED ............................................................................... PedestalPERF PEN ................................................ Performance PenaltyPFD .......................................................... Primary Flight DisplayPLAN .......................................................................... Plan ModePLI ................................................................Pitch Limit IndicatorPMP....................................................................................PumpPNEU ......................................................................... PneumaticPNL .................................................................................... PanelPOS................................................................................ Position

BOEING 717



PPH ................................................................. Pounds Per HourPRAM ...............................Prerecorded Announcement MachinePRES, ............................................................. PRESS PressurePROF ................................................................................ ProfilePROG............................................................................ProgressPROX ........................................................................... ProximityPSEU ......................................Proximity Switch Electronics UnitPSI ....................................................... Pounds Per Square InchPSU .................................................. Passenger Service UtilitiesPTT.......................................................................... Push To TalkPTU ............................................................. Power Transfer UnitPWR .................................................................................. PowerPWS .......................................................... Predictive Windshear

QQFE ...................................................... Field Elevation PressureQNH .............................................................Sea Level PressureQTY ................................................................................Quantity

RR..........................................................................................RightRA ....................................... Radio Altitude, Resolution AdvisoryRAT ........................................................... Ram Air TemperatureRDR ................................................................................ RudderREF ............................................................................ ReferenceRET ................................................................................. RetractRETD ............................................................................... RetardREV .............................................................................. ReverserRHM .......................................................... Rudder Hook MonitorRLS ........................................................... Remote Light SensorRNAV................................................................. Area NavigationRNP....................................... Required Navigation PerformanceRPM ....................................................... Revolutions Per MinuteRSL ............................................................. Rudder Stop LimiterRTE ................................................................................... RouteRTO .................................................................. Rejected TakeoffRUD ................................................................................ RudderRWD................................................................ Right Wing Down

BOEING 717



RWY ............................................................................... Runway

SSAT...........................................................Static Air TemperatureSATCOM ................................. Satellite Communication SystemSCP .......................................................... System Control PanelS/C ............................................................................ Step ClimbS/D ........................................................................ Step DescentSD ...................................................................... System DisplaySDP .......................................................... System Display PanelSDCP .......................................... System Display Control PanelSEL..................................................... Select; Selector; SelectedSELCAL............................................................ Selective CallingSENS .......................................................................... SensitivitySID ............................................ Standard Instrument DepartureSMOK............................................................................ SmokingSPD BRK ............................................................... Speed BrakeSPD ...................................................................................SpeedSTAB ....................................................... Stabilizer; StabilizationSTAR ........................................ Standard Terminal Arrival RouteSTBY .............................................................................. StandbySTD .............................................................................. StandardSW ................................................................................... SwitchSYNC ..................................................................... SynchronizerSYS ................................................................................. System

TTA ........................................................................Traffic AdvisoryTAKOFF ...........................................................................TakeoffTAS...................................................................... True Air SpeedTAT ............................................................ Total Air TemperatureTBD ................................................................ To Be DeterminedTCAS............................ Traffic Alert Collision Avoidance SystemTD ........................................................................ Traffic DisplayTEMP ...................................................................... TemperatureTFR ................................................................................ TransferTGT .................................................... Turbine Gas TemperatureTHNDSTRM ..........................................................Thunderstorm

BOEING 717



THROT ............................................................................ ThrottleTO, T/O ............................................................................TakeoffTOC........................................................................ Top Of ClimbTOD.................................................................... Top Of DescentTO FLEX ................................................ Takeoff Flexible DerateTOGA ..................................................... Takeoff and Go-AroundTOGW ....................................................... Takeoff Gross WeightTR ............................................................. Transformer RectifierTRANS ......................................................... Transition; TransferTRFC................................................................................. TrafficTRK .................................................................................... TrackTRU ...................................................................................... TrueTURB ........................................................................ Turbulence

UU/L ................................................................................ UnlockedUNBAL ..................................................................... Unbalanced

VVapp ................................................................. Approach SpeedVDC.............................................................. Volts Direct CurrentVERT ............................................................................... VerticalVfe ................................................................ Flap Extend SpeedVfr ................................................................. Flap Retract SpeedVge .............................................................. Gear Entend SpeedVgr............................................................... Gear Retract SpeedVHF ........................................................... Very High FrequencyVIA.................................................. Versatile Integrated AvionicsVIB ................................................................................ VibrationVLV ..................................................................................... ValveVmax ............................. FMC Calculated Max Operating SpeedVmin ............................... FMC Calculated Min Operating SpeedVmo ................................................. Maximum Operating SpeedVNAV............................................................. Vertical NavigationVOL ................................................................................. VolumeVOR ............................................... VHF Omnidirectional RangeVref .................................................. Reference Approach SpeedVs ..............................................................................Stall SpeedVse ................................................................ Slat Extend Speed

BOEING 717



Vso ................................................................. Clean Stall SpeedVsr ................................................................. Slat Retract SpeedVss ................................................................ Stickshaker SpeedV/S ....................................................................... Vertical SpeedVSI ........................................................ Vertical Speed IndicatorV1 ...................... Critical Engine Failure Speed; Decision SpeedV2 .................................. Takeoff Safety Speed; Climbout SpeedV3 ................................................... Final Segment Climb Speed

WWAGS .................................. Windshear Alert Guidance SystemWARN ............................................................................ WarningWINDSHLD ............................................................... WindshieldWINDSHR, WNDSHR ................................................ WindshearWOW............................................................... Weight On WheelWPT ............................................................................. WaypointW/S ............................................................................ WindshearWSC .......................................................... Windshear ComputerWT.................................................................................... WeightWX, WXR ............................................................Weather RadarWXBRT .............................................Weather Radar BrightnessWX+T ...................................................Weather and Turbulence

XX FEED .......................................................................CrossfeedXFER, XFR .................................................................... TransferXPDR ...................................................................... Transponder

ZZFW .................................................................Zero Fuel WeightZFWCG ............................... Zero Fuel Weight Center of Gravity

BOEING 717



RED BOXEDALERTS (LEVEL 3)CABIN ALTITUDE (AIR) Cabin pressure altitude exceeds 10,000 feet.CARGO SMOKE FWD/AFT (AIR) Smoke has been detected in forward/aft cargo

compartment.NO MASKS (AIR) Cabin altitude exceeds 14,750 feet and passenger

oxygen masks have not automatically deployed.TAIL MANF FAIL (AIR) The pneumatic overheat detection system (PODS)

detects a manifold failure in the tail anti-ice manifoldand has not shut off tail ice protection.

TAIL TEMP L/R HI (AIR) PODS detects an overheat condition or manifoldfailure in the tail compartment.

WING MANF FAIL (AIR) PODS detects a manifold failure in the wing anti-ice manifold and has not shut off wing ice protec-tion.

APU FIRE (ENG) APU compartment fire detected. APU shuts downAPU FIRE (ENG) APU compartment fire is detected.ENGINE L/R FIRE (ENG) Engine fire detection system has detected a fire.

AVNCS AIR FLO OFF (AIR) On the ground, indicates the primary fan hasfailed. In flight, indicates both fans have failedwith fan cooling (AVIONICS COOLING switch inFAN) selected.

BLD AIR L/R TEMP HI (AIR) Pneumatic supply manifold temperature exceedslimits with bleed system in automatic (L/R BLEEDswitch in AUTO) for respective system.

BLD AIR L/R TEMP LO (AIR) Bleed air temperature is too low to provide airfoilanti-ice protection.

BLEED AIR L/R FAIL (AIR) The pressure regulator valve, or a channel of thepneumatic system controller has failed.

CABIN DUCT OVHT (AIR) Cabin duct temperature exceeds limit. Packshutdown could occur.

CABIN INFLO LO (AIR) Cabin pressure is low. Pack air flow insufficient tomaintain pressurization.

CABIN PRES HI (AIR) Cabin pressure exceeds limits.CABIN PRESSURIZED (AIR) The cabin is pressurized while air-plane is on the

ground.CKPT DUCT OVHT (AIR) Cockpit duct temperature exceeds limit. Pack

shutdown could occur.ENG L/R OIL PRES LO (AIR) Respective engine oil pressure is low.PACK L/R OVERHEAT (AIR) Respective air conditioning pack has shut down

due to high temperature.TAIL A-ICE DISAG (AIR) The tail anti-ice valve position disagrees with the

commanded position.

AMBER BOXED ALERTS (LEVEL 2)

BOEING 717



TAIL A-ICE OFF (AIR) The tail anti-ice system is shut down by PODSdue to an overheat or a manifold failure.

WING A-ICE DISAG (AIR) The wing anti-ice valve position disagrees withthe commanded position.

WING A-ICE OFF (AIR) The wing anti-ice system is shut down by PODSdue to an overheat or a manifold failure.

ANTISKID L/R FAIL (CONFIG) Respective antiskid system is inoperative.AUTOBRAKE FAIL (CONFIG) Autobrake system is inoperative.BRAKE OVERHEAT (CONFIG) Brake temperature exceeds 308° C. Resets when

temperature falls below 260 ° C.ELEVATOR SPLIT (CONFIG) A split between left and right elevator panels

exists, possibly indicating a jammed condition.FLAP DISAG (CONFIG) Left and right flap positions disagree with each

other or with commanded position.GEAR DOOR OPEN (CONFIG) One of the main landing gear doors is open.RUDDER LIM FAIL (CONFIG) Both primary and secondary rudder limiters failed

to unrestricted position.SLAT DISAG (CONFIG) Left and right slat positions disagree with each

other or with commanded position.BUS AC EMER OFF (ELEC) AC emergency bus is off.BUS DC EMER OFF (ELEC) DC emergency bus is off.BUS DC XFER OFF (ELEC) DC transfer bus has failed.GEN ALL OFF (ELEC) Left, Right, and APU generators are off due to

faults.GEN L/R/APU OFF (ELEC) Respective generator is off due to a fault.APU EGT HI (ENG) APU % EGT exceeds limitsAPU FAULT (ENG) The APU detects a fault which results in auto

shutdown on the ground, but prevents shutdownin flight.

ENG L/R BRG OVHT (ENG) Overheat detected in the aft bearing compart-ment.

ENG L/R OIL TEMP HI (ENG) Respective engine oil temperature exceedsamber limit.

ENG L/R RPM HI (ENG) Respective N1 has exceeded the red line limit.Respective EEC detects low pressure N1 speedbeyond maximum limit. EEC commands FMUoverspeed valve to mini-mum flow position.

ENG L/R RPM LO (ENG) Engine rpm has dropped below idle (flameout).ENG L/R TGT HI (ENG) Respective engine TGT exceeds red line limit or

exceeds amber line limit after 5 minutes.SELECT FADEC ALTN (ENG) FADEC N1 control mode has been selected by

pilot.START VLV L/R OPEN (ENG) Respective start valve is open during normal

start and N2 less than 50.2 percent.

AMBER BOXED ALERTS (LEVEL 2) continued

BOEING 717



BALST FUEL DISAG (FUEL) Fuel quantity in the center or for-ward auxiliaryfuel tank is less than the designated ballast fuelquantity.

CTR FWD/AFT PUMP LO (FUEL) A center tank fuel pump is not producing pressure. System must be reconfigured to ensurecenter fuel can be used.

FUEL OFF SCHEDULE (FUEL) Either the left or the right main tanks have lowfuel while the center tank has usable fuel.

FUEL QTY FAULT (FUEL) Loss of fuel gauging in one or more fuel tanks.FUEL QTY SYS FAIL (FUEL) Complete loss of fuel gauging on one channel.HYD L&R FAIL (HYD) Both left and right hydraulic systems have failed.HYD L/R PRES LO (HYD) Respective hydraulic system pressure is low.HYD L/R QTY LO (HYD) Respective hydraulic reservoir fluid quantity is

too low.HYD L/R TEMP HI (HYD) Respective hydraulic system fluid temperature is

too high.AIR DATA 1/2/ FAIL (MISC) Respective air data system has failed.DCU FAIL (MISC) Data concentrator unit (DCU) has lost data.IRS 1/2/AUX FAIL (MISC) Respective inertial navigation portion of the

ADIRU has failed.STICK PUSHER FAIL (MISC) The stick pusher system has failed or is one

failure away from an uncommanded push.TAILCONE UNLOCK (MISC) Tailcone is not locked.WSHLD HEAT FAIL (MISC) The windshield heater has over-temped.

AMBER BOXED ALERTS (LEVEL 2) continued

AIR ISOL DISAG (AIR) The pneumatic system isolation valve isnot in the commanded position

AIR SYS L/R NOT OFF (AIR) The respective bleed air system is still pressurized when commanded OFF.

AIR SYS L/R OFF (AIR) The respective bleed air system is off andthe isolation valve is closed.

AIR SYS L/R PRES LO (AIR) Respective system on with low pressure.APU VALVE DISAG (AIR) The APU valve position disagrees with the

APU AIR switch position.AVNCS COOL OVRD (AIR) The AVIONICS COOLING switch is in the

override (OVRD) position.BLEED AIR L/R OFF (AIR) The respective bleed air valve is closed.CABIN PRES HI (AIR) Cabin differential pressure is high.CABIN PRES MAN FAIL (AIR) The cabin pressure control panel or

manual control of the outflow valve actuatorhas failed. Manual control is not available.

AMBER ALERTS (LEVEL 1)

BOEING 717



CABIN PRES SYS MAN (AIR) The cabin pressurization control systemsselected to manual.

CABIN RATE (AIR) Cabin climb or descent rate exceeds com-fortable limits.

CABIN TEMP MANUAL (AIR) Cabin temperature control knob is selectedto manual.

CARGO AGENT 1/2 LO (AIR) Respective cargo compartment fire-extinguishing agent has been discharged.

CKPT TEMP MANUAL (AIR) Cockpit temperature control knob is selected to manual.

CRG SMK FWD/AFT FAIL (AIR) Respective forward/aft cargo compartmentsmoke detector test has failed.

CRG SMK FWD/AFT SGL (AIR) Respective cargo compartment smokedetection system is operating in singlemode.

DISCH CARGO AGENT (AIR) Flight crew must discharge cargo compartment fire-extinguishing agent.

ENG L/R A-ICE DISAG (AIR) The respective anti-ice valve positiondisagrees with commanded position.

ICE DETECT FAIL (AIR) The ice detection system has failed.ICE DETECT FAULT (AIR) The ice detection system has detected a

sensor and/or controller fault in one system.ICE DETECTED (AIR) The ice detection system detects ice and

the anti-ice system is not on.LAVATORY SMOKE (AIR) Smoke has been detected in a lavatory.LDG ALTITUDE MAN (AIR) The landing field altitude is manually se

lected.NO ICE DETECTED (AIR) The ice detection system no longer detects

ice and all anti-ice systems are on.PACK L/R FLO DISAG (AIR) Respective pack pneumatic flow disagrees

with switch position.PACK L/R OFF (AIR) Respective pack is commanded off. MAS-

TER CAUTION lights come on if both packsare off above 4000 feet AGL.

PACK OVRD (AIR) The PACK SHUTDOWN switch is in theOVRD position.

PODS FAIL (AIR) PODS has failed and cannot detect amanifold failure.

PODS TEST FAIL (AIR) The PODS system test has failed.SEL CAB PRES MAN (AIR) Both cabin pressure controllers have failed

and system only functions when set manu-ally.

SET LDG ALTITUDE (AIR) Cabin pressurization system landing fieldelevation data from the FMS is lost andmust be set manually.

AMBER ALERTS (LEVEL 1) continued

BOEING 717



START AIR PRES LO (AIR) Pressure in the manifold is insufficient forengine start.

WING ICE DETECTED (AIR) (Ground only) - Either wing ice detector hasdetected upper surface wing ice.

WING ICE L/R FAIL (AIR) (Ground only) - Respective wing ice detec-tion system is inoperative.

AGS FAIL (CONFIG) The Auto Ground Spoiler (AGS) systemdetects a failure which may cause the AGSto not deploy.

ANTISKID FAULT (CONFIG) (Ground only) Antiskid system has detected a fault. Antiskid is still fully functional.

PSEU FAULT (CONFIG) Fault detected or failure of a redundantsensor.

ANTISKID OFF (CONFIG) ANTISKID switch is OFF.AUTO TRIM FAIL (CONFIG) The FCC is unable to trim the stabilizer.AUTOBRAKE OFF (CONFIG) AUTOBRAKE switch is OFF.BRAKE PRES LO (CONFIG) One or both brake accumulator pressures

are low.DISARM SPOILERS (CONFIG) The Auto Ground Spoiler (AGS) system

has detected a failure which may cause theAGS to not deploy.

FCC 1/2 FAULT (CONFIG) Respective FCC has a fault.FCC1/2 FAIL (CONFIG) Respective FCC has failed.PSEU FAIL (CONFIG) The proximity sensor system has failed,

resulting in loss of gear, door, and slatposition information.

PSEU FAIL (CONFIG) The proximity sensor system has failed.RUDDER LIM FAULT (CONFIG) Either the primary or secondary rudder

limiter system has failed to the rudderunrestricted position.

RUDDER PWR OFF (CONFIG) The rudder is in manual mode either due tohydraulic failure, or pilot selection.

RUDDER RESTRICTED (CONFIG) The rudder is restricted more than it shouldbe for the flight condition.

SPEEDBRAKE DISAG (CONFIG) The speed brakes are extended withthrottles set at high power.

SPEEDBRAKE/FLAP (CONFIG) The speed brakes are extended with theflaps in the landing range.

SPOILER FAIL (CONFIG) The spoiler system detects a non-dispatchable fault.

SPOILER INBD/OTBD FAIL (CONFIG) The respective spoiler system has shutdown in response to a detected failure orSECU channel failure.

STAB OUT OF TRIM (CONFIG) The stabilizer is not responding to autopilottrim commands.


BOEING 717



STAB TRIM OFF (CONFIG) The STABILIZER TRIM shutoff switch is selected to OFF.

YAW DAMP FAIL (CONFIG) The yaw damper function has been shut off bythe FCC.

BATT CHARGER FAIL (ELEC) The battery charger is inoperative.BATT CHARGING (ELEC) The battery is being charged.BATT DISCHARGING (ELEC) The battery is discharging abnormally.BATT SWITCH OFF (ELEC) BATT switch is in OFF position.BUS AC GS OFF (ELEC) AC ground service bus is off.BUS AC L/R OFF (ELEC) Respective bus is off.BUS DC L/R OFF (ELEC) Respective DC bus is off.BUS TIE L/R LOCKOUT (ELEC) Respective bus tie is locked open due to a

fault.BUS TIE L/R OPEN (ELEC) Respective BUS TIE switch is in OPEN posi-

tion.DC TIE SW OPEN (ELEC) DC BUS TIE switch is in OPEN position.ELEC FAULT (ELEC) Electrical power system has detected an

internal fault.EMER PWR ON (ELEC) Emergency power is on.EMER PWR SW OFF (ELEC) EMER PWR switch is in OFF position.EMER PWR TST FAIL (ELEC) The emergency power test has failed.GEN L/R/APU OFF (ELEC) Respective generator switch has been se

lected OFF or ENG/APU FIRE switches havebeen activated.

TR L/C/R FAIL (ELEC) A fault exists in the respective TR.APU AUTO SHUTDOWN (ENG) APU detects a fault and automatically shuts

down.APU DOOR OPEN (ENG) The APU air inlet door is open with the APU

commanded off.APU FIRE AGENT LO (ENG) The APU fire agent has been discharged.APU FIRE LOOP A/B (ENG) One of the two APU fire detection loops is

inoperative.ENG L/R FADEC ALTN (ENG) Respective FADEC EPR control mode not

available and N1 mode has been selected.EEC has reverted to N1 control mode.

ENG L/R FUEL FILTER (ENG) Respective engine has high differential pressure across fuel filter indicating possible fuelfilter clog.

ENG L/R OIL FILTER (ENG) Respective engine has high differential pressure across oil filter. Oil temperature must begreater than 32 ° C.

ENG L/R START ABORT (ENG) Ground only. During engine start, an abnormalcondition is detected in the respective engineand autostart sequence is aborted.


BOEING 717



ENG L/R SURGE (ENG) Respective engine compressor surge orstarting stall.

ENG L/R SYS FAIL (ENG) Respective engine has a class 3 fault. Nodispatch until fault is fixed.

ENG VIB HI (ENG) Engine vibration exceeds acceptable limits.FIRE AGENT 1/2 LO (ENG) Respective engine fire-extinguishing agent

has been discharged.FIRE AGENT APU LO (ENG) Optional third APU fire-extinguishing agent

has been discharged.FIRE DET APU FAIL (ENG) Both APU detector loops are inoperative or

a fire/overheat is detected in one of twoactive loops.

FIRE DET L/R FAIL (ENG) Both detector loops are inoperative in therespective engine or a fire/overheat isdetected in one of two active loops.

REV L/R DEPLOYED (ENG) Thrust reverser doors are uncommandeddeployed.

REV L/R FAULT (ENG) Respective thrust reverser unlocked.CTR FWD/AFT PUMP OFF (FUEL) Respective pump is off with usable fuel in

center tank.TNK L/R FWD/AFT PMP OFF (FUEL) Respective pump is commanded off with

associated FUEL switch in ON.ENG L/R FUEL PRES (FUEL) Respective engine has low fuel pressure.FUEL LEVEL LO (FUEL) Either the left or right main tanks have low

fuel and the center tank has low fuel.FWD/AFT AUX PRES LO (FUEL) Aux tank transfer switches are in auto,

transfer valves are open but aux tank pressure is low.

LAT FUEL UNBAL (FUEL) Fuel quantities in the left and right maintanks differ by more than 1400 pounds.

SEL AUX XFER AUTO (FUEL) Aux tank transfer switches are off withusable fuel in the aux tanks.

SEL CTR PUMPS OFF (FUEL) Center tank has low fuel and either centerpump has low pressure or, center tankquantity is slightly greater than the ballastquantity with either pump on.

SEL CTR PUMPS ON (FUEL) Center pumps are off with usable fuel incenter tank.

SEL FWD/AFT XFER OFF (FUEL) Aux tanks are empty and aux tank transferswitches are in auto.

TANK L/R PUMPS LO (FUEL) Respective tank pump(s) have low pres-sure.

TANK L/R PUMPS OFF (FUEL) Both forward and aft main tank pumps arecommanded off with FUEL switch on.


BOEING 717



TNK L/R FWD/AFT PMP LO (FUEL) Respective pump pressure is low.HYD AUX PUMP FAIL (HYD) The auxiliary hydraulic pump is com

manded on, but is not producing pressure.HYD AUX PUMP OFF (HYD) The auxiliary hydraulic pump is not on with

the slats extended and at least one engineon.

HYD L/R OFF (HYD) Engine-driven pumps, hydraulic PowerTransfer Unit (PTU), and auxiliary pump(right system) are all commanded off.

HYD PUMP L/R FAIL (HYD) Respective hydraulic pump is commandedon but not producing pressure.

HYD PUMP L/R OFF (HYD) The respective hydraulic pump is com-manded off.

HYD TRANS DISAG (HYD) Hydraulic PTU commanded position disagrees with actual position.

HYD TRANS OFF (HYD) The hydraulic transfer pump is not on withslats extended and at least one enginerunning.

ACARS NO COMM (MISC) ACARS communication has been lost.ACCESS COMPT DOOR (MISC) Accessory compartment door is not closed

and locked.AFT BULKHEAD DOOR (MISC) Aft exit door is not closed and locked.AIR DATA HEAT OFF (MISC) The AIR DATA HEAT pushbutton is se

lected OFF (the air data probe heaterswitch is off) and illuminated amber.

AOA HEAT L/R FAIL (MISC) Respective angle-of-attack probe heaterhas failed with the AIR DATA HEATpushbutton selected on.

ATC XPDR 1/2 FAIL (MISC) Respective ATC transponder has failed.AUTOPILOT SINGLE (MISC) Only 1 autopilot is available.CABIN DOOR (MISC) Forward cabin door is not closed and

locked.CARGO DOOR FWD/AFT (MISC) Respective cargo door is not closed and

locked.CAWS FAIL (MISC) Central aural warning function in both VIAs

has failed.DCU FAULT (MISC) Data concentrator unit has lost data redun-

dancy.DOOR OPEN (MISC) One or more doors are not closed and

locked.DRAIN MAST HEAT (MISC) Drain mast heater has failed.DRAIN MAST HEAT (MISC) The drain mast heater is inoperative.EIS SINGLE SOURCE (MISC) A single VIA channel is driving all six dis-

plays. Cross comparison is not available.


BOEING 717



ELEC COMPT DOOR (MISC) Electrical/electronics compartment door isnot closed and locked.

EMER LTS DISARM (MISC) EMER LT switch is in OFF position.FD G/A ONLY (MISC) Autopilot go-around not available.FMS 1/2 FAIL (MISC) Respective flight management function

within VIA 1/2 has failed.GALLEY DOOR (MISC) Galley door is not closed and locked.GPWS FAIL (MISC) EGPWS computer has failed.GPWS FAULT (MISC) Displayed on SD when the ground proxim

ity function of EGPWS has failed. Terrainawareness function is still operative.

IRS 1/2/AUX NO ALIGN (MISC) Respective ADIRU has failed to completean alignment.

IRS 2/AUX ON BATT (MISC) ADIRU-2/AUX (optional) is powered bybackup battery.

IRS BATT FAIL (MISC) IDIRU-2 backup battery has failed.IRS BATT LO (MISC) ADIRU-2 backup battery is low.IRS OFF (MISC) One or more ADIRU’s have been selected

OFF.MANUAL G/A ONLY (MISC) Autopilot and flight director go around

modes are not available.NO AUTOLAND (MISC) Autoland mode is not available.OVERWING DOOR (MISC) One or more overwing emergency exit

doors is not closed and locked.PRED WSHEAR FAIL (MISC) Predictive windshear function of weather

radar is inoperative.PRED WSHEAR FAULT (MISC) Predictive windshear has detected a fault.RAT PROBE HEAT (MISC) The ram air probe heater has failed with

the AIR DATA HEAT pushbutton selectedon in flight.

RUD PITOT HEAT (MISC) The rudder limiter pitot tube heater hasfailed with the AIR DATA HEAT pushbuttonselected on.

SINGLE LAND (MISC) Autoland reduced from dual land to singleland.

STAIRWAY DOOR FWD/AFT (MISC) (Optional) Respective stair-way door is notstowed and locked.

STALL WARN FAIL (MISC) The stall warning system has failed.TERRAIN FAIL (MISC) Displayed on SD when the terrain aware-

ness function of EGPWS has failed. Theground proximity function is still operative.

TERRAIN NOT AVAIL (MISC) Displayed on SD when the terrain awareness function is not available.


BOEING 717



UNABLE RNP (MISC) Navigation system cannot meet requirednavigation performance (RNP) accuracy forthe selected phase of flight.

VIA CONFIG DISAG (MISC) VIA-1 and VIA-2 configurations do notagree.

VIA FAIL (MISC) VIA computer has failed.WSHEAR DET FAIL (MISC) Windshear detection is inoperative.WSHLD A-ICE OFF (MISC) Windshield anti-ice is selected off.ADIRU 1/2/AUX FAULT (STATUS) Respective ADIRU has detected a fault.AIL TRIM FAIL (STATUS) The aileron trim system has failed.APU SQB 1/2/3 FAIL (STATUS) Respective discharge cartridge has failed

the manual fire test.CPC 1/2 FAIL (STATUS) The respective cabin pressure controller

has failed.DME 1/2 FAIL (STATUS) Respective DME receiver has failed.ENG L/R SQB 1/2 FAIL (STATUS) Respective discharge cartridge has failed

the manual fire test.ENG L/R SYS FAULT (STATUS) Respective FADEC has detected an inter-

nal fault or loss of redundancy.FIRE APU A/B FAULT (STATUS) Respective APU detector loop has de-

tected a fault.FIRE L/R A/B FAULT (STATUS) Respective engine detector loop has de-

tected a fault.FIREX TEST FAIL (STATUS) Manual fire discharge test has failed.FLT REC FAIL (STATUS) Flight data recorder has failed.GPS 1/2 FAIL (STATUS) Respective GPS function of MMR has

failed.ILS 1/2/3 FAIL (STATUS) Respective ILS function of MMR has failed.PODS A-ICE FAULT (STATUS) The pneumatic overheat detection system

(PODS) has a fault in the wing or tail iceprotection system and cannot detect amanifold failure.

PODS FAULT (STATUS) One loop or controller channel of the pneu-matic overheat detection system (PODS)has failed. Manifold failure detection isoperable.

PSC FAULT (STATUS) The pneumatic system controller (PSC)has recorded a fault requiring maintenanceaction.

PSEU FAULT (STATUS) The proximity sensor system has loggedan internal fault, or detected a failure of aredundant sensor.

SPOILER FAULT (STATUS) The spoiler system detects a fault.


BOEING 717



STALL WARN FAULT (STATUS) The stall warning system has lost twochannels of stall warning and/or one chan-nel of stick pusher.

STATIC L/R HEAT (STATUS) The respective static plate heater hasfailed with the AIR DATA HEAT pushbuttonselected on.

STICK PUSHER FAIL (STATUS) The stick pusher system has failed, or isone failure away from an uncommandedpush.

VIA FAULT (STATUS) VIA computer has detected an internalfault.

VOR 1/2 FAIL (STATUS) Respective VOR receiver has failed.PITOT HEAT CAPT/FO/AUX (STATUS) The respective probe heater has failed.


ACARS MESSAGE ACARS has received an incoming message.A-ICE ALL ON All engine and airfoil ice protection is selected on.AIR ISOL OPEN The pneumatic isolation valve is commanded open.AIRFOIL A-ICE ON Both wing and tail anti-ice is selected on.APU AIR ON The APU is on and providing pneumatic power but not electrical

power.APU AIR/ELEC ON The APU is on and supplying both electrical and pneumatic power.APU ELEC ON The APU is on and providing electrical power, but not pneumatic

power.APU ON The APU is running without load.AUTOBRAKE HI Autobrake switch is selected on HIGH for landing.AUTOBRAKE MAX Autobrake switch is selected on MAX for landing.AUTOBRAKE MED Autobrake switch is selected on MED for landing.AUTOBRAKE MIN Autobrake switch is selected on MIN for landing.AUTOBRAKE T/O Autobrake switch is selected on T/O for takeoff.CDU 1/2 MENU REQ Respective MCDU is not displaying FMS pages.CRG SMK TEST PASS Smoke detection system test is passed.EMER POWER TEST Emergency power test is in progress.ENG A-ICE ON Both ENG ANTI-ICE switches are on.ENG IGN OVRD ON Engine ignition switch is in ON position.ENG L/R A-ICE ON Respective system engine anti-ice switch is on.ENG START PUMP ON Fuel start pump is commanded on.ENGINE COOL Engine has cooled sufficiently after landing to be shut down.EXT POWER AVAIL External power is available.EXT POWER ON External power is on.FIRE DET APU FAIL Both APU fire detection loops have failed and fire detection is inop-

erative.FIREX TEST PASS Manual firex discharge test has passed (all squibs indicated conti-

nuity).

CYAN ALERTS (LEVEL 0)

BOEING 717



FUEL SYS TEST Fuel system is in test mode.FUEL XFEED ON Fuel crossfeed open.GPWS FLAP OVRD GND PROX WARN switch is in FLAP OVRD position.ICE DETECT TEST The primary ice detection system test is in progress.IRS IN ALIGN IRS is in alignment mode.NO SMOKING NO SMOKING signs have been turned on, or NO SMOKE switch is

in AUTO with slats extended.PACKS ALL OFF Packs are off for takeoff as selected through the FMS, or packs are

switched off during engine failure on takeoff.PACKS HIGH FLOW HIGH pack flow is selected on the FLOW switch.PARK BRAKE ON (Ground only) Parking brakes are set. If parking brakes are not set,

indicates an antiskid malfunction.PODS TEST PASS The PODS preflight test is successful.PRED WSHEAR OFF Weather radar is off when it should be on.SEAT BELTS FASTEN SEAT BELTS signs have been turned on, or SEAT BELTS

switch is in AUTO when the airplane below 10,000 feet.SPEEDBRAKE The speed brakes are extended.TAIL A-ICE ON Tail anti-ice is selected on, or, wing and tail anti-ice are selected on

and the system is in alternating mode.TERRAIN OVRD EGPWS terrain mode is off.VHF-3 VOICE The third VHF radio is in voice mode rather than ACARS data mode.WING A-ICE ON Wing anti-ice is selected on, or, wing and tail anti-ice are selected

on and the system is in alternating mode.WING ICE DET PASS The upper wing surface ice detection system test is successful.WSHLD ANTI-FOG ON The WINDSHLD ANTI-FOG switch is selected ON. Anti-fog heat to

the windshields, the clearview and the overhead windows is on.

CYAN ALERTS (LEVEL 0) continued

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Index

A

A/B QUANTITY CHANNEL BUTTON 70AGENT 1 & 2 LOW LIGHTS 44AILERON TRIM CONTROL 100AIR COND AUTO SHUTOFF SWITCH 65AIR FOIL ANTI-ICE SWITCH 75AIR SYSTEM DISPLAY SELECTOR BUTTON 94ALT LONG TRIM SWITCH 90ANNUN LTS TEST BUTTON 77ANTI COLLISION LTS SWITCH 83ANTI-SKID SWITCH 56APU AIR SWITCH 57APU EGT INDICATOR (%) 28APU FIRE AGENT NO 1 & NO 2 SWITCHES 57APU FIRE CONTROL SWITCH 57APU MASTER SWITCH 57APU POWER IN USE LIGHTS 62APU PWR AVAIL LIGHT / APU POWER SWITCH 63ATTENDANT CALL BUTTON 81ATTENDANT CALLING ANNUNCIATOR RESET 81AUTOTHROTTLE DISCONNECT BUTTONS (2) 89AUX HYD PUMP SWITCH 59AVIONICS RACK FAN SWITCH 65

B

BAROSET KNOB 20BATTERY SWITCH 61

C

CAB/SERV INT KNOB 49CABIN / CKPT TEMP SELECTORS 66CKT BKR LT SWITCH 80COCKPIT DOOR SWITCH 78COCKPIT VOICE RECORDER MICROPHONE 54COCKPIT VOICE RECORDER ERASE SWITCH 55COCKPIT VOICE RECORDER HEADSET JACK 55COCKPIT VOICE RECORDER STATUS 54COCKPIT VOICE RECORDER TEST SWITCH 55CONFIG SYSTEM DISPLAY SELECTOR BUTTON 94

D

DC BUS X TIE SWITCH 61DOME LIGHT 79

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E

EIS DISPLAY CONTROL KNOB 94ELEC SYSTEM DISPLAY SELECTOR BUTTON 94EMER LTS SWITCH 79EMER PWR SWITCH 61ENG EXCEEDANCE RESET 77ENG GEN IN USE LIGHT (AC X TIE) 62ENG HYD PUMP SWITCH 59ENG L & R ANTI-ICE SWITCHES 76ENG SYSTEM DISPLAY SELECTOR BUTTON 94ENGINE FIRE HANDLE 43ENGINE FIRE PANEL 43ENGINE OIL PRESS DISPLAY 29ENGINE OIL QTY DISPLAY 29ENGINE OIL TEMP DISPLAY 29ENGINE PRESSURE RATIO (EPR) DISPLAY 25ENGINE START SWITCH 68ENGINE VIB DISPLAY 29EVENT PUSHBUTTON 51EXHAUST GAS TEMPERATURE (EGT) DISPLAY 25EXT MAINT INTPH CALL 81EXT MECH CALL 81EXT PWR AVAIL LIGHT / EXT PWR SWITCH 63EXT PWR IN USE LIGHT 62

F

FAULT TEST SWITCH 44FIRE DETECTOR PANEL 52FIRE TEST SWITCH 44FLAP SLAT HANDLE 91FLAP TAKEOFF SELECTOR 91FLIGHT RECORDER/MECH CALL 51FUEL CROSS FEED HANDLE 90FUEL FLOW USED DISPLAYS 26FUEL SWITCH 90FUEL SYSTEM DISPLAY SELECTOR BUTTON 94FUEL SYSTEM TEST BUTTON 70FUEL USED RESET BUTTON 77FUNCTION - DISPLAY 26

G

GALLEY POWER SWITCH 63GEAR HORN OFF BUTTON 91GENERATOR CONTROL SWITCHES 62GND FLOOD LTS SWITCH 83GROSS WEIGHT & FUEL DISPLAY 28GROUND PROX WARN SWITCH 71GROUND SERVICE PANEL 47GROUND SERVICE SWITCH 47

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H

HF -1, HF-2 KNOBS (2) 49HYD CONT ELEV SWITCH 58HYD SYSTEM DISPLAY SELECTOR BUTTON 94

I

ID FILTER BUTTON 50IGNITION SWITCH 67IN HP PUSH BUTTON 20INSTR & PED PNL / FLOOD LT SWITCH 82INT KNOB 49IRS MODE SELECTOR 53

L

L & R BUS CROSS TIE SWITCHES 62L&R ENG LOOPS SWITCH 52LAND ALT KNOB 73LANDING GEAR LTS SWITCH 82

M

MAG TRUE PUSH BUTTON 20MICROPHONE SWITCH/LIGHTS 48MINMUMS KNOB 20MISC SYSTEM DISPLAY SELECTOR BUTTON 95MKR KNOB 51

N

N1 ROTOR SPEED DISPLAY 25N2 ROTOR SPEED DISPLAYS 25ND SYSTEM DISPLAY SELECTOR BUTTON 95NO SMOKE SWITCH 80NOSE GEAR LTS SWITCH 82

O

OVHD PNL / FLOOD LT SWITCH 79

P

PA / VIDEO IN USE LIGHT 80PA BUTTON/LIGHT 80PA KNOB 50POSITION AND STROBE LIGHTS SWITCH 83PRESSURIZATION SYSTEM SELECTOR SWITCH 73PULL TO DIM SWITCH 77

R

RADIO / INT SWITCH 50RAM AIR SWITCH 65RUDDER TRIM CONTROL 100

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S

SEAT BELTS SWITCH 80SPD BRK LEVER 88STABILIZER TRIM SWITCH 87START PUMP SWITCHES 67STATUS SYSTEM DISPLAY SELECTOR BUTTON 95STBY COMP LT SWITCH 78SUPPLY SWITCHES 66

T

TAIL DE-ICE BUTTON 75THNDRSTRM LT SWITCH 81THROTTLE LEVERS 88THRUST REVERSE CONTROL LEVERS 89TO/GA BUTTONS 89TOTAL AIR TEMP DISPLAY 24TRANS HYD PUMP SWITCH 59

V

VHF -1, VHF-2, VHF-3 KNOBS (3) 49

W

WEATHER RADAR ANTENNA TILT CONTROL 97WEATHER RADAR GAIN CONTROL 97WEATHER RADAR MODE CONTROL 97WEATHER RADAR SYSTEM CONTROL SWITCH 97WINDSHIELD ANTI-ICE SWITCH. 76WINDSHIELD WIPER SWITCH 78WING ICE DETECT RESET / TEST 76WING NACEL LTS SWITCH 82

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