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FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

BIWEEKLY 2003-21

This electronic copy may be printed and used in lieu of the FAA biweekly paper copy.

U.S. Department of Transportation Federal Aviation Administration

Regulatory Support Division Delegation and Airworthiness Programs Branch, AIR-140

P. O. Box 26460 Oklahoma City, OK 73125-0460

FAX 405-954-4104


AD No. Information Manufacturer Applicability Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information;

3

Biweekly 2003-01 2002-26-02 Univair Alon A-2, A2-A, ERCO 415-C, 415-CD, 415-D, 415-E, 415-G,

Forney F-1, F-1A, and Mooney M10 2002-26-05 S 2002-11-03 Air Tractor AT-502, AT-502A, AT-502B, and AT-503A 2003-01-01 S 2000-26-16 Raytheon Aircraft A36, B36TC, 58, 36, A36TC, and 58A 2003-01-03 Hartzell Propeller Propeller: ( )HC-( )2Y( )-( ) Biweekly 2003-02 2002-13-05 R1 R MD Helicopters, Inc. Rotorcraft: 369D, 369E, 369F, 369FF 2003-01-04 Bell Helicopter Textron Rotorcraft: 205B, 212, 204B, 205A, and 205A-1 2003-02-03 Raytheon Aircraft 65-90, 65-A90, B90, C90, C90A, 65-A90-1 (U-21A), 65-A90-1

(U-21G), 65-A90-2 (RU-21B), 65-A90-3 (RU-21C), 65-A90-4 (RU-21E), E90, F90, H90 (T-44A), 99, 99A, A99A, B99, C99, 100, A100, A100 (U-21F), A100-1 (U-21J), A200 (C-12A), (C-12C), A200C (UC-12B), A200CT (C-12D), A200CT (C-12F), A200CT (FWC-12D), A200CT (RC-12D), A200CT (RC-12G), A200CT (RC-12H), A200CT (RC-12K), A200CT (RC-12P), A200CT (RC-12Q), B100, 200, B200, 200C, B200C, B200C (C-12F), B200C (C-12R), B200C (UC-12F), B200C (UC-12M), 200CT, B200CT, 200T, B200T, 300, B300, B300C, and 2000

2003-02-05 Eurocopter France Rotorcraft: AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N

2003-02-06 Bell Helicopter Textron Canada Rotorcraft: 407 Biweekly 2003-03 2003-01-01 COR,

S 2000-26-16 Raytheon Aircraft Company A36, B36TC, 58, 36, A36TC, and 58A

2003-03-11 Air Cruisers Company Appliance: Emergency Evacuation Slide/Raft System 2003-03-12 Turbomeca S.A Engine: Arriel 1 A2, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1 E2, 1 K, 1 K1,

1 S, 1 S1 and Arriel 2 B, 2 B1, 2 C, 2 C1, 2 S1 Series Turboshaft 2003-03-13 Moravan A.S. Z-242L 2003-03-14 Piaggio Aero Industries S.p.A. P-180 2003-03-18 E Raytheon Aircraft Company 1900, 1900C, and 1900D 2003-03-18 FR, COR Raytheon Aircraft Company 1900, 1900C, and 1900D 2003-03-20 Hartzell Propeller Inc. Propeller: HC-C2YR-4CF 2003-03-21 Pratt & Whitney Canada Engine: PW530A, PW535A, and PW545A Turbofan Biweekly 2003-04 2003-03-18 FR, COR Raytheon 1900, 1900C, and 1900D 2003-04-02 S 98-12-10

99-21-23 Apex Aircraft CAP 10B

2003-04-03 SOCATA TB 9, TB 10, TB 20, TB 21, and TB 200 2003-04-04 Robinson Helicopter Rotorcraft: R22 2003-04-05 Robinson Helicopter Rotorcraft: R44 2003-04-07 British Aerospace HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series

3101, and Jetstream 3201 2003-04-08 Piaggio Aero P-180 ERRATA Honeywell Appliance: Pages 3 & 4 of AD Summary Book 4



4

Biweekly 2003-05 2002-25-51 FR, COR, S

2002-17-51 Agusta S.p.A. Rotorcraft: A109E

2003-04-06 Honeywell Appliance: Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit

2003-04-12 Bell Helicopter Textron Canada Rotorcraft: 427 2003-04-13 Eurocopter France Rotorcraft: SA341G and SA342J 2003-04-14 Bell Helicopter Textron Canada Rotorcraft: 427 2003-04-15 Sikorsky Aircraft Corporation Rotorcraft: S-76A, B and C 2003-04-23 Hartzell Propeller Inc. Propeller: HC-B3TN-5() 2003-04-26 Raytheon Aircraft Company 1900D 2003-05-01 S 2002-18-51 Wytwornia Sprzetu

Komunikacyjnego PZL- Rzeszow

Engine: 6A-350-C1, -C1A, -C1L, -C1R, -C2, -C2A, and 4A-235 Series Reciprocating

Biweekly 2003-06 2003-05-02 Lindstrand Balloons Ltd. Appliance: Fuel Hoses 2003-05-03 COR, S 2000-06-

10 Bell Helicopter Textron Canada Rotorcraft: 407

2003-05-05 Robert E. Rust DH.C1 Chipmunk 21, 22, and 22A 2003-05-06 Robert E. Rust DH.C1 Chipmunk 21, 22, and 22A 2003-05-11 S 2002-23-51 Bell Helicopter Textron Canada Rotorcraft: 407 2003-06-01 S 2002-13-02 Air Tractor, Inc. AT-300, AT-301, AT-302, AT-400A, and AT-400 Biweekly 2003-07 2003-06-02 Hartzell Propeller Inc. Propeller: HC-C2Y(K,R)-1BF/F8477-4 2003-06-07 S 2002-05-04 Socata-Groupe Aerospatiale MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS

894E, Rallye 150T, and Rallye 150ST 2003-06-08 Dornier-Werke G.m.b.H. Do 27 Q-6 2003-07-01 S 2000-11-16 Quality Aerospace, Inc. S–2R, S2R-G1, S2R–R1820, S2R–T15, S2R–T34, S2R–G10,

S2R–G5, S2R–G6, S2RHG–T65, S2R–T34, S2R–T45, S2R–T65, 600 S2D, S2R–R1340, S2R–R3S, S2R–T11, S2RHG-T34

2003-07-03 Twin Commander Aircraft Corp. 690D, 695A, and 695B 2003-07-04 Air Tractor, Inc. AT-300, AT-400, AT-400A, AT-401, AT-401B, AT-402, AT-

402A, AT-402B, AT-501, AT-502, and AT-502B 2003-07-05 Stemme GmbH & Co. KG Sailplane: S10 and S10-V 2003-07-06 British Aerospace HP.137 Jetsream Mk.1, Jetstream Series 200, and Jetstream Series

3101, Jetstream 3201 2003-07-09 Raytheon Aircraft Company 390 Biweekly 2003-08 2003-07-10 Pilatus Aircraft Ltd. PC-12 and PC-12/45 2003-08-04 Eurocopter France Rotorcraft: EC120B 2003-08-05 Eurocopter France Rotorcraft: AS350B3 2003-08-06 Eurocopter France Rotorcraft: AS350B, B1, B2, BA, and D 2003-08-07 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, and 230 2003-08-51 E MD Helicopter, Inc Rotorcraft: 369A, D, E, H, HE, HM, HS, F, and FF Biweekly 2003-09 2001-13-03 R1 R Kaman Aerospace Corporation Rotorcraft: K-1200 2003-08-53 E, S 2000-10-08,

2000-10-08R1 Eurocopter France Rotorcraft: SA-365N1, AS365-N2, AS 365 N3, and SA-366G1

2003-09-01 Pilatus Aircraft PC-6 2003-09-05 Schweizer Aircraft Corporation Rotorcraft: 269D 2003-09-09 S 2002-09-13 Cessna Aircraft 441, F406 2003-09-11 Pilatus Aircraft PC-12 and PC-12/45



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Biweekly 2003-10 94-20-04 R2 R Raytheon Aircraft Company C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35,

V35, V35A, and V35B 2003-09-10 Raytheon Aircraft Company 390 2003-09-12 Raytheon Aircraft Company 1900D 2003-09-13 The New Piper Aircraft PA-23, PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 2003-10-05 Raytheon Aircraft Company 390

Biweekly 2003-11 2003-11-08 Turbomeca S.A. Engine: Arriel -1B, -1D, and -1D1 Series Turboshaft 2003-11-09 COR Turbomeca Engine: Turmo IV A and IV C Series Turboshaft 2003-11-10 Turbomeca S.A. Engine: Arrius -2F Turboshaft Biweekly 2003-12 2003-08-53 FR,

S 2000-10-08, 2000-10-08R1

Eurocopter France Rotorcraft: SA-365N1, AS365N-2, AS 365 N3, and SA-366G1

2003-11-09 COR Turbomeca Engine: Turmo IV A and IV C Series Turboshaft 2003-11-12 S 2003-03-13 Moravan A.S. Z-242L 2003-11-13 Eurocopter France Rotorcraft: AS332C, L, and L1 2003-11-14 The New Piper Aircraft, Inc. PA-34-200T, PA-34-220-T, PA-44-180, and PA-44-180T 2003-11-17 Pilatus Aircraft Company Ltd. PC-12 and PC-12/45 2003-11-21 Eurocopter France Rotorcraft: AS332 C, L, and L1 2003-12-05 S 97-06-16 McCauley Propeller Systems Propeller: 1A103/TCM Series Biweekly 2003-13 97-18-02 R1 R Hartzell Propeller Inc. Propeller: ( )HC-( )(2,3)(X,V)( ) - ( ), HA-A2V20-1B 2003-12-13 Agusta S.p.A. Rotorcraft: A109K2 2003-12-14 Turbomeca S.A. Engine: Arriel 1 A, 1 A1, 1 A2, 1 B, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1

E, 1 E2, 1 K, 1 K1, 1 S, and 1 S1 Turboshaft 2003-13-04 Pilatus Aircraft LTD. PC-6 2003-13-05 Iniziative Industriali Italiane

S.p.A. Sky Arrow 650 TC and 650 TCN

2003-13-06 Iniziative Industriali Italiane S.p.A

Sky Arrow 650 and Sky Arrow 650 TCN

2003-13-51 E MD Helicopter, Inc. Rotorcraft: MD900 Biweekly 2003-14 97-18-02R1 COR, R Hartzell Propeller Propeller: ( )HC-( )(2,3)(X,V)( )-( ) Series and HA-A2V20-1B Series 2003-08-51 FR MD Helicopters, Inc. Rotorcraft: 369A, D, E, H, HE, HM, HS, F, and FF 2003-13-07 Short Brothers and Harland Ltd. SC-7 Series 2 and SC-7 Series 3 2003-13-08 Goodrich Avionics Systems, Inc. Appliance: TAWS8000 Terrain Awareness Warning System

(TAWS) 2003-13-10 Rolls-Royce Corporation Engine:250-C30R/3, -C30R/3M, -C47B, and -C47M Turboshaft 2003-13-13 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, and 222U 2003-13-14 Bell Helicopter Textron Canada Rotorcraft: 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3,

and 206L-4 2003-13-15 S 2001-25-52 Schweizer Aircraft Corporation Rotorcraft: 269A, 269A-1, 269B, 269C, and TH-55A 2003-13-16 Raytheon Aircraft Company 65–90, 65–A90, B90, C90, C90A, E90, F90, H90 (T–44A), 100,

A100, A100 (U–21F), A100–1 (U–21J), A200 (C–12A) and (C-12C), A200C (UC–12B), A200CT (C–12D), A200CT (C–12F), B200C (C–12F), A200CT (FWC–12D), A200CT (RC–12D), A200CT (RC–12G), A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), A200CT (RC–12Q), B100, B200C, 200C, B200C (C–12F), B200C (C–12R), B200C (UC–12F), B200C (UC-12M)

2003-13-17 Hartzell Propeller, Inc., McCauley Propeller Systems, Sensenich Propeller Manufacturing Company, Inc., and Raytheon Aircraft Company

Propeller: See Ad



6

Propellers Biweekly 2003-14 continued 2003-14-03 S 98-18-12 Textron Lycoming Engine: IO-320, LIO-320, IO-360, HIO-360, TIO-360, LTIO-360,

GO-435, GO-480, IGO-480-A1B6, IO-540, IGO-540, AEIO-540, HIO-540, TIO-540, LTIO-540, TIGO-541, IO-720, and TIO-720 Reciprocating

2003-14-51 E, S 2003-13-51 MD Helicopters, Inc. Rotorcraft: MD900 Biweekly 2003-15 2003-11-14 COR The New Piper Aircraft, Inc. PA-34-200T, PA-34-220T, PA-44-180, PA-44-180T 2003-13-10 COR Rolls-Royce Corporation Engine: 250-C30R/3, -C30R/3M, -C47B, and -C47M Turboshaft 2003-14-07 Pilatus Aircraft Ltd. PC-12 and PC-12/45 2003-14-12 Eurocopter France Rotorcraft: SA330F, G, and J; AS332C, L, and L1; SA341G;

SA342J; AS350B, BA, B1, B2, B3, and D; AS355E, F, F1, F2, and N; SA-365C, C1, and C2; SA-365N and N1; and AS-365N2 and N3

2003-14-18 Sikorsky Aircraft Corporation Rotorcraft: S76A, B, and C 2003-14-19 Eurocopter France Rotorcraft: SA-365N, N1, AS-365N2, N3, SA-366 G1, AS355F, F1,

F2, N and EC130 B4 2003-14-20 S 82-12-06 Aerospace Technologies of

Australia PTY LTD N22B and N24A

2003-15-51 E Eurocopter France Rotorcraft: SE3160, SA315B, SA316B, SA316C, and SA319B Biweekly 2003-16 2003-14-51 FR, S 2003-13-51 MD Helicopters, Inc. Rotorcraft: MD900 2003-15-07 Honeywell International Inc. Appliance: RE220 (RJ) Auxiliary power units (APUs) 2003-15-08 Eurocopter France Rotorcraft: AS350B, B1, B2, B3, BA, and D 2003-16-03 S 95-11-01 Turbomeca Engine: Arriel 1 A, 1 A1, 1 A2, 1 B, 1 C, 1 C2, 1 D, 1 D1, 1 E2, 1 K,

1 K1, 1 S, and 1 S1 Turboshaft 2003-16-51 E Schempp-Hirth Flugzeugbau

GmbH Glider: Duo-Discus

Biweekly 2003-17 2003-08-51 FR, COR MD Helicopters, Inc. Rotorcraft: Model 369A, D, E, H, HE, HM, HS, F, and FF 2003-16-10 Pratt & Whitney Canada Engine: PW206A and PW206E Turboshaft 2003-16-17 Dornier Luftfahrt GMBH 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 2003-16-51 FR Schempp-Hirth Flugzeugbau


2003-17-02 Extra Flugzeugbau GmbH EA-300/200, EA-300L, and EA-300S 2003-17-03 S 2003-03-14 Piaggio Aero Industries S.p.A. P-180 2003-17-04 Mitsubishi Heavy Industries,

Ltd. MU–2B/–10/–15/–20/–25/–26, MU–2B–30/–35/–36, /–26A/–40, /–36A/–60

2003-17-05 Short Brothers and Harland Ltd. SC-7 Series 2 and SC-7 Series 3 Biweekly 2003-18 2003-15-51 FR Eurocopter France Rotorcraft: SE3160, SA315B, SA316B, SA316C, and SA319B 2003-16-11 MD Helicopters, Inc. Rotorcraft: 600N 2003-16-51 FR, COR Schempp-Hirth Flugzeugbau


2003-17-16 Robert E. Rust DeHavilland DH.C1 Chipmunk 21, 22, and 22A Biweekly 2003-19 2003-16-03 COR, S 95-11-01 Turbomeca Engine: Arriel 1 A, 1 A1, 1 A2, 1 B, 1 C, 1 C1, 1 C2, 1 D, 1 D1, 1

E2, 1 K, 1 K1, 1 S, and 1 S1 Turboshaft 2003-18-03 Eurocopter France Rotorcraft: EC 155B, SA-365N and N1, AS-365N2, and AS 365 N3 2003-18-04 Wytwornia Sprzetu

Komunikacyjnego Engine: PZL-10W Turboshaft

2003-19-01 Eurocopter France Rotorcraft: AS 365 N3 and EC 155B 2003-19-06 Turbomeca S.A. Engine: Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 Turboshaft



7

Biweekly 2003-20 2003-19-07 Eagle Aircraft (Malaysia) 150B 2003-19-10 Fairchild Aircraft, Inc. SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-

26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC(C-26B), SA227-PC, and SA227-TT.

2003-19-11 S 95-14-09 Learjet 60 2003-19-12 Eurocopter France Rotorcraft: EC 155B 2003-19-13 Grob-Werke G120A 2003-19-14 Burkhart Grob Luft-und

Raumfahrt Gmbh & Co KG G103 TWIN ASTIR, G103 TWIN II, G103A TWIN II ACRO, G103C TWIN III ACRO

2003-20-05 Pilatus Aircraft Ltd. PC-7 Biweekly 2003-21 2003-20-09 Stemme GmbH & Co. KG Sailplane: S10-VT 2003-20-10 Raytheon Aircraft Comapany Beech 1900, 1900C, and 1900D 2003-20-11 S 2001-18-13 Eurocopter Deutschland GmbH Rotorcraft: EC135 P1, P2, T1, and T2 2003-20-12 Eurocopter France Rotorcraft: AS 350B3, SA-365N, N1, AS-365N2, AS 365N3, and

EC 155B 2003-20-15 Pilatus Aircraft Ltd. PC-12 and PC-12/45 2003-21-01 S 94-18-04 R1 Univar Aircraft Corporation Alon A–2 and A2–A, ERCO 415–C, 415–CD, 415–D, 415–E, and

415–G, Forney F-1 and F1A, Mooney M10 2003-21-04 Cessna Aircraft Company 208 and 208B

8

BW 2003-21

STEMME GMBH & CO. KG AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2003-20-09 Stemme GmbH & Co. KG: Amendment 39-13327; Docket No. 2003-CE-36-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 20, 2003. Are Any Other ADs Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects all Model STEMME S10-VT sailplanes that: (1) Incorporate a part number (P/N) 11AG gear box (serial numbers 43YYQ001 through 43YYQ093); and (2) Are certificated in any category: What is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the potential for the lower cog wheel in the gear box to rupture, which could result in loss of power and possible loss of control of the sailplane. What Must I Do To Address This Problem? (e) To address this problem, you must accomplish the following:

2003-20-09 2

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Actions Compliance Procedures (1) Incorporate the following flight

restrictions into the Limitations Section of the flight manual:

(i) ‘‘The operation of the engine will be limited to maximum 100% power (max. continuous power).’’ And

(ii) ‘‘Hence the take-off procedure (take-off with take-off power 115%, see section 4.5.2.2, of the Flight Manual) must not be selectd. Alternative procedures (i.e., take-off with max. continuous power 100%) are published in the flight Manual.’’

Within the next 10 days after October 20, 2003 (the effective date of this AD), unless already accomplished.

Either insert a copy of this portion of the AD or Stemme Service Bulletin A31–10–065, Am.-Index: 02a, dated February 25, 2003, into the Limitations Section of this of the AFM. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 Federal Aviation Regulations (14 CFR 43.7) may do this flight manual insertion. Make an entry into the aircraft records showing compliance with these portions of the AD in accordance with section 43.9 of the Federal Aviation regulations (14 CFR 43.9).

(2) Fabricate a placard that incorporates the following words (using at least 1/8-inch letters) and install this placard close to the throttle lever: ‘‘Operation above 100% continuous power is not allowed! (see SB A31–10–1065).’’

Within the next 10 days after October 20, 2003 (the effective date of this AD), unless already accomplished.

No specific procedures are necessary for this action. Stemme Service Bulletin A31–10–065, Am.-Index: 02a, dated February 25, 2003, references this action. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR the throttle 43.7) may do the placard requirements. Make an entry into the aircraft records showing compliance with these portions of the AD in accordance with section 43.9 of the Federal Aviation (14 CFR 43.9).

(3) As an alternative method of compliance to this AD, replace the lower cog wheel (P/N: 43.15.0028) with a modified cog wheel (P/N: 43:15:0043).

At any time as terminating action for the limitations and placard requirements of this AD.

Use the instructions in Stemme Service Bulletin A31–10–065, Am.-Index: 02a, dated February 25, 2003.

Why Is the FAA Not Mandating the Cog Wheel Replacement? (f) We are not mandating the cog wheel replacement (as specified in the service information) in this AD action because of the ''bootstrapping requirement.'' When we issue an AD that involves requirements affecting flight safety where we do not first provide notice and an opportunity for public comment, then we are only able to include a short-term action that immediately corrects the unsafe condition. (1) The Administrative Procedures Act does not permit combining a long-term requirement with a short-term action when we do not provide prior public comment. The short-term action and the long-term action are analyzed separately for justification to bypass public notice.

2003-20-09 3

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(2) We may initiate future AD action with public comment to mandate the cog wheel replacement as terminating action for the AFM requirements of this AD. This cog wheel replacement is optional in this AD as terminating action. What About Alternative Methods of Compliance? (g) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.13. Send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Is There Material Incorporated by Reference? (h) If you choose to do the replacement required by this AD, then you must use Stemme Service Bulletin A31-10-065, Am.-Index: 02a, dated February 25, 2003. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Stemme GmbH & Co. KG, Gustav-Meyer-Allee 25, D-13355 Berlin, Germany; telephone: 49.33.41.31.11.70; facsimile: 49.33.41.31.11.73. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Is There Other Information That Relates to This Subject? (i) German AD Number 2002-389/2, Effective date: April 17, 2003, also addresses the subject of this AD. Issued in Kansas City, Missouri, on September 30, 2003. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-25330 Filed 10-8-03; 8:45 am] BILLING CODE 4910-13-P

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BW 2003-21

RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2003-20-10 Raytheon Aircraft Company: Amendment 39-13328; Docket No. 2003-CE-43-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 15, 2003. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models Beech 1900, 1900C, and 1900D airplanes, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of an analysis of the maintenance procedures of the elevator trim system. We are issuing this AD to detect and correct any maintenance-induced problems with the elevator trim system installation before problems occur during operation. Such a condition could lead to difficulties in controlling the airplane or a total loss of pitch control. What Must I Do To Address This Problem? (e) To address this problem, you must accomplish the following:

2003-20-10 2

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Actions Compliance Procedures (1) Using pen and ink, mark the applicable

figure in the maintenance manual as referenced below. The depiction in the referenced figures is incorrect for the elevator trim drum only and depicts the cable drum at 180 degrees from the installed position and shows the open, keyed side of the drum instead of the flat side of the drum. Insert corrected figure (Figure 1 of this AD) into the applicable maintenance manual and identify it accordingly:

(i) Figure 9 of Chapter 27–10–00 of the Model 1900/1900C Airliner Maintenance Manual (114–590021–7B) Clearly note in pen that existing portion of Figure 9 is correct for the aileron trim drum only and insert corrected figure (Figure 1 of this AD) marked in pen as correct for the elevator trim drum only; or

(ii) Mark out Figure 201 of Chapter 27–30–04 of the Model 1900D Airliner Maintenance Manual (125–590000–15). Insert corrected figure (Figure 1 of this AD)

Before the next time you have maintenance done on the elevator trim system.

As specified in Raytheon Safety Communiqué No. 234, dated September 2003.

(2) Incorporate the applicable temporary revision into the maintenance manuals as follows:

(i) Temporary Revision No. 27–5 to the Model 1900/1900C Airliner Maintenance Manual: Revised ELEVATOR TRIM OPERATIONAL CHECK; or

(ii) Temporary Revision No. 27–9 to the Model 1900D Airliner Maintenance Manual: Added MANUAL ELEVATOR TRIM OPERATIONAL CHECK.

Before the next time you have maintenance done on the elevator trim system.

As specified in Raytheon Safety Communiqué No. 234, dated September 2003.

(3) Do the elevator trim operational check that is specified in the applicable maintenance manual and temporary revisions to the maintenance manual as referenced in paragraph (e)(2) of this AD

Prior to further flight after each time you have maintenance done on the elevator trim system.

As specified in Raytheon Safety Communiqué No. 234, dated September 2003: and Temporary Revision No. 27–5 to the Model 1900/1900C Airliner Maintenance Manual: Revised ELEVATOR TRIM OPERATIONAL CHECK; or Temporary Revision No. 27–9 to the Model 1900D Airliner Maintenance Manual: Added MANUAL ELEVATOR TRIM OPERATIONAL CHECK, both dated September 12, 2003, as applicable.

2003-20-10 3

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What About Alternative Methods of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.13. Send your request to the Manager, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Chris B. Morgan, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4154; facsimile: (316) 946-4107.

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Is There Material Incorporated by Reference? (g) You must do the actions required by this AD per Raytheon Safety Communique No. 234, dated September 2003; and either Raytheon Temporary Revision No. 27-5 to the Model 1900/1900C Airliner Maintenance Manual: Revised ELEVATOR TRIM OPERATIONAL CHECK, or Raytheon Temporary Revision No. 27-9 to the Model 1900D Airliner Maintenance Manual: Added MANUAL ELEVATOR TRIM OPERATIONAL CHECK, both dated September 12, 2003. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Issued in Kansas City, Missouri, on October 2, 2003. Dorenda D. Baker, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-25591 Filed 10-9-03; 8:45 am] BILLING CODE 4910-13-P

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EUROCOPTER DEUTSCHLAND GMBH. AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: [The "effective date" paragraph is missing from the "Part 39 Amended" portion of this AD. The effective date is November 14, 2003. We will issue a correction to the Federal Register.] 2003-20-11 Eurocopter Deutschland GmbH: Amendment 39-13329, Docket No. 2003-SW-08-AD. Supersedes AD 2001-18-13, Amendment 39-12439, Docket No. 2001-SW-19-AD. Applicability: Model EC135 P1, P2, T1, and T2 helicopters, with main rotor drive torque strut assembly (strut), part number (P/N) L633M1001 103 or L633M1001 105, installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the strut and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, insert a copy of this AD or a statement into the Emergency Procedures Section of the Rotorcraft Flight Manual (RFM) to inform the pilot to reduce power and land as soon as practicable if a thump-like sound followed by unusual vibration occurs during flight. (b) Within 10 hours time-in-service (TIS), visually inspect each strut with 950 or more hours TIS for a crack or a break using a flashlight and a mirror in accordance with the Accomplishment Instructions, paragraph 3.B.(1) and 3.B.(2), of Eurocopter Alert Service Bulletin EC135-63A-002, Revision 2, dated June 26, 2002 (ASB). Replace any cracked or broken strut with an airworthy strut before further flight. (c) Inspect the following struts for a crack or a break, using a 6-power or higher magnifying glass, and re-mark and relocate each strut in accordance with the Accomplishment Instructions, paragraph 3.C., of the ASB. This AD does not require you to return any part to the manufacturer. (1) For a strut with less than 950 hours TIS, inspect before accumulating 1000 hours TIS. (2) For a strut with 950 or more hours TIS, inspect within 50 hours TIS. (3) Replace any cracked or broken strut with an airworthy strut before further flight. (d) This AD revises the Airworthiness Limitations section of the maintenance manual by establishing a life limit of 1000 hours TIS for each strut, P/N L633M1001 103 and L633M1001 105, in its original location, with an additional 1000 hours TIS if properly re-marked and relocated (2000 hours total TIS) in accordance with the Accomplishment Instructions, paragraph 3.C.(3) of the ASB. (e) Record details of the inspections in the historical or equivalent records in accordance with the Accomplishment Instructions, paragraph 3.C.(4) of the ASB.

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(f) When a strut, P/N L633M1001 103 or L633M1001 105, reaches its life limit, replace it with a titanium strut, P/N L633M1001 104, which must be used in pairs, one strut on each side of the transmission. The titanium struts have no life limit. After installing a strut, P/N L633M1001 104, adjust the weight and balance by using the weight and moment stated in the Planning Information, paragraph 1.H., of the ASB. (g) On or before December 31, 2004, replace each strut, P/N L633M1001 103 or L633M1001 105, with a strut, P/N L633M1001 104. (h) Replacing struts, P/N L633M1001 103 and L633M1001 105, with titanium struts, P/N L633M1001 104, constitutes terminating action for the requirements of this AD. (i) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group for information about previously approved alternative methods of compliance. (j) The inspections and replacement of the struts shall be done in accordance with Eurocopter Deutschland (GmbH) Alert Service Bulletin EC135-63A-002, Revision 2, dated June 26, 2002. The Director of the Federal Register approved the incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note: The subject of this AD is addressed in Luftfahrt-Bundesamt (Federal Republic of Germany) AD 2001-107/2, dated September 19, 2002. Issued in Fort Worth, Texas, on September 29, 2003. David A. Downey, Manager, Rotorcraft Directorate, , Aircraft Certification Service. [FR Doc. 03-25592 Filed 10-9-03; 8:45 am] BILLING CODE 4910-13-P

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EUROCOPTER FRANCE AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2003-20-12 Eurocopter France: Amendment 39-13330. Docket No. 2002-SW-17-AD. Applicability: Model AS 350B3, SA-365N, N1, AS-365N2, AS 365N3, and EC 155B helicopters, with an optional Siren load release unit cargo hook, part number (P/N) AS-21-5-7, installed, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To detect internal corrosion of the Siren cargo hook locking catch (locking catch), which can cause the locking catch to return to an incomplete locking position, undetectable by the operator, and result in an unexpected cargo load release, accomplish the following: (a) For cargo hook, P/N AS-21-5-7, with Amendment B incorporated, before the first use of the cargo hook on each day that the cargo hook is used, check for corrosion on the locking catch as follows. Amendment B has been incorporated if the letter ''B'' is marked on the amendment identification plate of the release unit of the cargo hook and placard ''G'' is installed on the release unit cover plate ''D'' and reference line ''B'' is marked over the nut and cover plate as depicted in Figure 1 of this AD. The identification plate ''A'' is located on cover plate ''D'', on the opposite side of the electrical connector. See Figure 1:

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(1) With the cargo hook installed, cycle the red manual release control lever several times over its travel range. (2) Return the red manual release control lever to the initial position. (3) Determine whether the section of reference line (B) marked on the bolt (A) and the section of reference line (B) marked on the cover plate (D) form a straight line. (i) If the reference line is straight, the cargo hook is considered airworthy. (ii) If the reference line is not straight, the cargo hook is unairworthy and may not be used. (b) The requirements of paragraph (a) may be performed by an owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with that paragraph of this AD in accordance with 14 CFR sections 43.11 and 91.417(a)(2)(v).

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(c) For cargo hook, P/N AS-21-5-7, without Amendment B, before the next sling load flight, incorporate Amendment B to the cargo hook in accordance with the Accomplishment Instructions, paragraphs 2.A.2.a) and 2.A.2.b), of Eurocopter Alert Telex No. 05.00.39, for Model AS 350B3 helicopters; No. 05.00.41, for Model SA-365N, N1, AS-365N2, and AS 365N3 helicopters; and No. 05A002, for Model EC 155B helicopters; all dated December 20, 2001, as applicable. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Safety Management Group, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Safety Management Group. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Safety Management Group. (e) Special flight permits will not be issued allowing use of the cargo hook until the requirements of this AD are accomplished. (f) The actions shall be done in accordance with Eurocopter Alert Telex No. 05.00.39, for Model AS 350B3 helicopters; No. 05.00.41, for Model SA-365N, N1, (AS-365N, N1) AS-365N2, and AS 365N3 helicopters; and No. 05A002, for Model EC 155B helicopters; all dated December 20, 2001. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on November 18, 2003. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 2002-044(A), dated January 23, 2002. Issued in Fort Worth, Texas, on September 29, 2003. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 03-25593 Filed 10-10-03; 8:45 am] BILLING CODE 4910-13-P

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PILATUS AIRCRAFT LTD. AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2003-20-15 Pilatus Aircraft Ltd.: Amendment 39-13333; Docket No. 2003-CE-42-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 10, 2003. Are Any Other ADs Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models PC-12 and PC-12/45 airplanes, serial numbers 101 through 520, with fuel booster pump (fuel pump) part number (P/N) 969.84.11.401, 968.84.11.403, or 968.84.11.404 installed, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any defective fuel booster pump, which could result in electrical arcing from the leads in an air/fuel mixture. Such electrical arcing could lead to a fire or explosion of a fuel tank. What Must I Do To Address This Problem? (e) To address this problem, you must accomplish the following unless already accomplished:

Actions Compliance Procedures (1) Replace any installed fuel booster

pump part number (P/N) 969.84.11.401 with a fuel pump that has the Pilatus PC12 Service Bulletin No. 28–011, Revision No. 1, dated July 11, 2003, modification incorporated.

Within the next 7 calendar days after October 10, 2003 (the effective date of this AD).

Per Pilatus PC12 Service Bulletin No. 28-011, Revision No. 1, dated July 11, 2003, Pilatus PC12 Maintenance Manual Temporary Revision No. 12–03 (12–10–01), dated June 6, 2003, and Pilatus PC12 Maintenance Manual Temporary Revision No. 28–02 (28–20–04), dated June 6, 2003.

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(2) Inspect the installed fuel booster pump P/N 968.84.11.403 or 968.84.11.404 for defects:

(i) If defects are found, replace the fuel booster pump with a fuel booster pump that has the modification referenced in Pilatus PC12 Service Bulletin No. 28–011, Revision No. 1, dated July 11, 2003.

(ii) If no defects are found: (B) Re-identify the fuel booster pump

P/N and 968.84.11.403 or 968.84.11.404 by adding the suffix letter ‘‘B’’ adjacent to the serial Maintenance number on the fuel pump identification plate.

Within the next 7 calendar days after October 10, 2003 (the effective date of this AD).

Per Pilatus PC12 Service Bulletin No. 28–011, Revision No. 1, dated July 11, 2003, Pilatus PC12 Maintenance Manual Temporary Revision No. 12–03 (12–10–01), dated June 6, 2003, and Pilatus PC12 Maintenance Manual Temporary Revision No. 28–02 (28–20–04), dated June 6, 2003, and Pilatus PC12 Maintenance Manual Temporary Revision No. 28–02 (28–20–04), dated June 6, 2003.

(3) Do not install any part referenced in paragraph (e)(1) or (e)(2) of this AD unless it has been modified per Pilatus PC12 Service Bulletin No. 28–011, Revision No. 1, dated July 11, 2003.

As of October 10, 2003 (the effective date of this AD).

Not applicable.

(4) If you have scheduled the replacement or installation required by paragraphs (e)(1) and (e)(2) of this AD, but the schedule puts you beyond the time to comply, you may insert Temporary Revision No. 7, dated June 6, 2003, or Temporary Revision No. 37, dated June 6, 2003, in the Section 2—Limitations section of the applicable pilot’s operating handbook (POH) and operate the aircraft according.

Prior to further flight after scheduling the replacement of installation. The replacement or installation of paragraphs (e)(1) and (e)(2) of this AD must be accomplished within 50 hours time-in-service after October 10, 2003 (the effective date of this AD). After compliance with paragraphs (e)(1) and (e)(2) of this AD, you may remove Temporary Revision No. 7, dated June 6, 2003, or Temporary Revision No. 37, dated June 6, 2003, from the POH.

Anyone who holds at least a private pilot certificate, as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7), may incorporate the POH revision required by this AD. You must make an entry into the aircraft records that shows compliance with this AD, per section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Send the following to the Small Airplane Directorate using the procedures described in paragraph (f) of this AD: the airplane model and serial number designation; the number of hours TIS on the airplane; the scheduled date for the replacement/installation; and the name and location of the authorized repair shop.

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What About Alternative Methods of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.13. Send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090. Is There Material Incorporated by Reference? (g) You must do the actions required by this AD per Pilatus PC12 Service Bulletin No. 28-011, Revision No. 1, dated July 11, 2003, Pilatus PC12 Maintenance Manual Temporary Revision No. 12-03 (12-10-01), dated June 6, 2003, and Pilatus PC12 Maintenance Manual Temporary Revision No. 28-02 (28-20-04), dated June 6, 2003. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-9099; facsimile: (303) 465-6040. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Is There Other Information That Relates to This Subject? (h) Swiss AD Number HB 2003-301, dated July 17, 2003, also addresses the subject of this AD. Issued in Kansas City, Missouri, on October 2, 2003. Dorenda D. Baker, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-25477 Filed 10-8-03; 8:45 am] BILLING CODE 4910-13-P

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UNIVAIR AIRCRAFT CORPORATION AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2003-21-01 Univair Aircraft Corporation: Amendment 39-13335; Docket No. 2002-CE-58-AD; Supersedes AD 94-18-04 R1, Amendment 39-9173. When Does This AD Become Effective? (a) This AD becomes effective on December 1, 2003. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 94-18-04 R1, Amendment 39-9173. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category:

Models Serial Nos. Alon A–2 and A2–A All. ERCO 415–C, 415–CD, 415–D, 415–E, and 415–G. All. Forney F–1 and F–1A All. Mooney M10 All.

What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of additional reports of corrosion on airplanes in compliance with AD 94-18-04 R1. The actions specified in this AD are intended to prevent wing damage caused by a corroded wing outer panel structural component, which, if not detected and corrected, could progress to the point of structural failure. What Must I Do To Address This Problem? (e) To address this problem, you must accomplish the following:

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Actions Compliance Procedures (1) Install inspection openings in the outer wing panels and inspect the wing outer panel internal structural components for corrosion and unrepaired corrosion damage.

Within the next 12 calendar months after March 24, 1995 (the effective date of AD 94–18–04 R1), unless already accomplished.

In accordance with Univair Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, and Advisory Circular 43–4A, Corrosion Control for Aircraft.

(2) If corrosion or corrosion damage is found during the inspection required in paragraph (e)(1) of this AD, repair or replace components of the wing outer panel structure.

Repair or replace prior to further flight after the inspection required in paragraph (e)(1) of this AD.

In accordance with Univair Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, the applicable maintenance manual, and Advisory Circular 43– 4A, Corrosion Control for Aircraft.

(3) Repetitively inspect the wing outer panel internal structural components for corrosion and unrepaired corrosion damage.

Initially inspect within the next 6 calendar months after December 1, 2003 (the effective date of this AD), unless the wing outer panel internal structure has been inspected for corrosion within the previous 6 calendar months immediately prior to December 1, 2003 (the effective date of this AD). Repetitively inspect thereafter at intervals not to exceed 12 calendar months after the last inspection.

In accordance with Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, and Advisory Circular 43–4A, Corrosion Control for Aircraft.

(4) At any time corrosion or corrosion damage is found, repair or replace components of the wing outer panel structure.

Repair or replace prior to further flight after the inspection in which the corrosion or corrosion damage is found. Continue with the repetitive inspection requirements of this AD.

In accordance with Univair Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, and Advisory Circular 43–4A, Corrosion Control for Aircraft.

Note: The compliance times specified in Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, are different from those required by this AD. The compliance times in this AD take precedence over those in the service bulletin. What About Alternative Methods of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.13.

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(1) Send your request to the Manager, Denver Aircraft Certification Office (ACO). For information on any already approved alternative methods of compliance, contact Roger Caldwell, Aerospace Engineer, FAA, Denver Aircraft Certification Office, 26805 East 68th Avenue, Room 214, Denver, Colorado 80249-6361; telephone: (303) 342-1086; facsimile: (303) 342-1088. (2) Alternative methods of compliance approved for the inspection required in AD 94-18-04 R1, which is superseded by this AD, are approved as alternative methods of compliance with this AD. Is There Material Incorporated by Reference? (g) You must do the actions required by this AD per Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, and Univair Service Bulletin No. 29, Revision C, dated July 8, 1999. (1) The Director of the Federal Register approved the incorporation by reference of Univair Aircraft Corporation Mandatory Service Bulletin No. 29, Revision C, dated July 8, 1999, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011, telephone: (303) 375-8882; facsimile: (303) 375-8888. (2) The Director of the Federal Register previously approved the incorporation by reference of Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, as of March 24, 1995 (60 FR 13626, March 14, 1995). (3) You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Issued in Kansas City, Missouri, on October 6, 2003. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-25699 Filed 10-10-03; 8:45 am] BILLING CODE 4910-13-P

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CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2003-21-04 Cessna Aircraft Company: Amendment 39-13339; Docket No. 2003-CE-41-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 21, 2003. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category:

Model Serial No. 208 20800001 through 20800369. 208B 208B0001 through 208B1014,

208B1017, 208B1018, 208B1020 through 208B1024, 208B1026, and 208B1029 through 208B1033.

What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of cracks and missing/ incomplete welds in the right inboard forward flap bell crank. We are issuing this AD to prevent failure of the right inboard forward flap bell crank due to cracks, deformation, or missing/incomplete welds. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must accomplish the following, unless already accomplished (compliance with Cessna Caravan Service Bulletin CAB03-11, Revision 1, dated September 24, 2003):

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Actions Compliance Procedures (1) Inspect the right inboard forward flap bell crank assembly for cracks, deformation, and missing/incomplete welds. The affected flap bell crank incorporates one of the following part numbers (P/N): (i) P/N 2622083–18; (ii) P/N 2622281–2; (iii) P/N 2692001–2; or (iv) P/N 2622281–12.

Within the next 25 landings after October 21, 2003 (the effective date of this AD). If landings are unknown, then you may multiply hours time-in-service (TIS) by 1.25. For the purposes of this AD, you may substitute 20 hours TIS for 25 landings.

Use a flashlight and a mirror as necessary to see if welds (1), (4), (5), and (6) exist and are at least 0.06-inch thick around the full circumference of the shaft. These welds and the inspection procedures are referenced in Figure 1, details A, B, and C; and Views A–A and B–B of Cessna Caravan Service Bulletin CAB03–11, Revision 1, dated September 24, 2003.

(2) If you find cracks, deformation, or missing/incomplete welds during the inspection required by paragraph (e)(1) of this AD, then accomplish one of the following: (i) Replace the flap bell crank with a P/N 2622311–7 flap bell crank; or (ii) Prohibit the use of flaps through the actions of paragraph (f) of this AD.

Replace or do the flap prohibition actions prior to further flight after the inspection required in paragraph (e)(1) of this AD. If you choose the flap prohibition, you must have the replacement done within 200 hours TIS after the inspection required by paragraph (e)(1) of this AD. After the new flap bell crank (2622311–7) is installed, the Temporary Revision 208PHTR02, dated September 23, 2003, should be removed.

Replacement: Use the Accomplishment Instructions of Cessna Caravan Service Bulletin No.: CAB02–12, Revision 1, dated January 27, 2003, and the Accomplishment Instructions of Cessna Caravan Service Kit No.: SK208–148A, dated January 27, 2003. Flap Prohibition: Use the information in the Temporary Revision 208PHTR02, dated September 23, 2003. The action is referenced in Cessna Caravan Service Bulletin CAB03–11, Revision 1, dated September 24, 2003.

What Are the Actions I Must Do if I Choose the Flap Prohibition Option? (f) Insert Temporary Revision, 208PHTR02, dated September 23, 2003, into the applicable pilot's operating handbook and FAA-approved airplane flight manual. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may incorporate this information into the AFM. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with § 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (1) This procedure applies to Cessna Models 208 and 208B landplanes. For other FAA-approved aircraft configurations (e.g., amphibian, floatplanes, etc.), you must operate with flaps up per the appropriate airplane flight manual supplement. (2) This procedure allows for applicable deviation from the Master Minimum Equipment List (MMEL) for these airplanes until the flap bell crank is replaced. The applicable MMEL requirements go back into effect at the time of flap bell crank replacement.

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Are There Differences Between the Service Information and This AD? (g) Yes. The service information requires an inspection on all flap bell cranks within the flap system. However, this AD only addresses the right inboard forward flap bell crank. To date, FAA has only received reports on the right inboard forward flap bell cranks, and we are addressing this issue through a final rule; request for comments (immediately adopted rule) AD action. After issuing this AD, we will evaluate the condition of the entire flap system and determine whether additional action is necessary. What About Alternative Methods of Compliance? (h) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.13. Send your request to the Manager, Wichita Aircraft Certification Office (ACO). For information on any already approved alternative methods of compliance, contact Paul Nguyen, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: 316-946-4125; facsimile: 816-946-4107. Is There Material Incorporated by Reference? (i) You must do the actions required by this AD per Cessna Caravan Service Bulletin CAB03-11, Revision 1, dated September 24, 2003; Cessna Caravan Service Bulletin No.: CAB02-12, Revision 1, dated January 27, 2003; and Cessna Caravan Service Kit No.: SK208-148A, dated January 27, 2003 (Original issue: October 21, 2002). The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Issued in Kansas City, Missouri, on October 8, 2003. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-26115 Filed 10-16-03; 8:45 am] BILLING CODE 4910-13-U

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