FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2004-16 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

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SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.

Information

Manufacturer

Applicability

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-01 2003-23-05 2003-24-13 2003-26-04 2003-26-06 2003-26-14 2004-01-09 2004-01-10 2004-01-14 2004-01-51

COR COR

E

Titeflex Corportation Cessna Aircraft Company Agusta S.p.A. Anjou Aeronautique Kiddie Aerospace Eurocopter France Eurocopter Deutschland Eurocopter France Eurocopter France

Appliance: Titeflex hoses 172R, 172S, 182S, 182T, T182T, 206H, and T206H Rotorcraft: A109E Appliance: Safety belts and restraint systems Appliance: Hand-held halon fire extinguishers Rotorcraft: AS355E, F, F1, F2, and N Rotorcraft: MBB-BK-117 A-1, A-3, A-4, B-1, B-2, and C-1 Rotorcraft: EC130B4 Rotorcraft: AS355E, F, F1, F2, and N

Cessna Aircraft Company Raytheon Aircraft Company

441 and F406 1900, 1900C, 1900 (C-12J), and 1900D

Agusta S.p.A. Air Cruisers Company

Rotorcraft: A109E Appliance: Emergency Evacuation Slide/Raft Systems

Learjet Eurocopter France Pacific Aerospace Corporation, Ltd. The New Piper Aircraft, Inc. Pilatus Aircraft LTD.

31, 31A, 35, 35A (C-21A), 36 and 36A Rotorcraft: AS332C, L, and L1 FU24-954 and FU24A-954

45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, MU-2B36A, MU-2B-40, and MU-2B-60 Rotorcraft: AS355E, F, F1, F2, and N Engine: CT58-100-2, CT58-140-1, -140-2, and T58-GE-1, -3, -5, 8E, -8F, -10, -100, and -402 Turboshaft Engine: JT15D-1, -1A, and -1B Turbofan Otter DHC-3 N22B, N22S, and N24A

Biweekly 2004-02 2003-09-09 R1 2004-01-13

R S 97-22-16

Biweekly 2004-03 2004-02-03 2004-03-01

S 2003-03-11

Biweekly 2004-04 2004-03-08 2004-03-27 2004-03-29 2004-03-32 2004-04-01

COR

S 2002-01-09

PA-46-500TP PC-7, PC-12, and PC-12/45

Biweekly 2004-05 2001-13-18 R1 2003-22-07 R1

R1, COR R

Raytheon Aircraft Company Mitsubishi Heavy Industries, Ltd

2004-01-51 2004-04-06

FR

Eurocopter France General Electric Company

2004-04-09 2004-05-01 2004-05-02

Pratt & Whitney Canada Bombardier Inc. Aerospace Technologies of Australia Pty Ltd.

Biweekly 2004-06 2004-03-01

Air Cruisers Company

Appliance: Emergency Evacuation Slide/Raft System

2004-05-23

COR, S 2003-0311 S 89-21-01

Eurocopter France

2004-05-24

S 2002-23-06

Lycoming Engines

2004-05-28 2004-05-29 2004-06-51

E

2004-06-52

E

Eurocopter France Eurocopter France Boeing Defense and Space Group Robinson Helicopter Company

Rotorcraft: AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N Engine: AEIO-540, IO-540, LTIO-540, O-540, and TIO-540 Series Reciprocating Rotorcraft: AS 365 N3 Rotorcraft: EC 155B Rotorcraft: 234

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Rotorcraft: R22, R22 Alpha, R22 Beta, and R22 Mariner

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.

Information

Manufacturer

Applicability

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-07 2004-06-04 2004-06-05 2004-06-09 2004-06-10

Sikorsky Aircraft Corporation Pilatus Aircraft Ltd. The Lancair Company Aerospace Technologies of Australia Pty Ltd.

Rotorcraft: S-76 A, B, and C PC-12 and PC-12/45 LC40-550FG and LC42-550FG N22B, N22S, and N24A

Eurocopter France

Rotorcraft: AS332C, L, and L1

Bombardier Inc. Engine Components Incorporated (ECi) Schempp-Hirth Flugzeugbau Gmbh Burkhardt Grob Luft-und Raumfahrt Gmbh Co & KG Glasflugel Goodrich Avionics Systems, Inc. NARCO Avionics Inc. Cessna Aircraft Company HPH s. r. o. Cessna Airplane Company

Otter DHC-3 Engine: Teledyne TSIO-520-NB, -VB, -WB, 520 and 550 Series Reciprocating Glider: Discus-2a, Discus-2b, Ventus-2a, and Ventus-2b

Biweekly 2004-08 2004-03-27

COR

Biweekly 2004-09 2004-05-01 R1 2004-08-10

R

2004-08-12 2004-08-13 2004-08-14 2004-08-15 2004-08-16 2004-08-17 2004-09-03 2004-09-05

S 2003-13-08

Glider: G103 Twin ASTIR, G103 Twin II, G103 Twin III ACRO, and G103 C Twin III SL Glider: Mosquito and Club Libelle 205 Appliance: Terrain Awareness Warning System (TAWS) Appliance: AT150 Transponders 208 amd 208B Glider: Glasflügel 304CZ, 304CZ-17, and 304C 500, 501, 550, and 551

Biweekly 2004-10 2004-08-17 2004-09-02 2004-09-07 2004-09-29

COR

2004-09-30

Cessna Aircraft Company Glasflugel-Ing. E. Hanle Raytheon Aircraft Company Honeywell International Inc.

Raytheon Aircraft Company

208 and 208B Glider: Kestrel 1900, 1900C, 1900C (C12J), and 1900D Engine: TPE331-10-501C, -10-511C, -10-501K, -10-511K, -10501M, -10-511M, -10AV-511B, -10AV-511M, -10GP-511D, 10GT-511D, -10N-511S, -10N-512S, -10N-513S, -10N-514S, 10N-515S, -10N-531S, -10N-532S, -10N-533S, -10N-534S, -10N535S, -10P-511D, -10R-501C, -10R-502C, -10R-511C, -10R512C, -10R-513C, -10T-511D, -10T-511K, -10T-511M, -10T512K, -10T-513K, -10T-515K, -10T-516K, -10T-517K, -10U501G, -10U-502G, -10U-511G, -10U-512G, -10U-503G, -10U513G, -10UA-511G, -10UF-501H, -10UF-511H, -10UF-512H,10UF-513H, -10UF-514H, -10UF-515H, -10UF-516H, -10UG513H, -10UG-514H, -10UG-515H, -10UG-516H, -10UGR-513H, -10UGR-514H, -10UGR-516H, -10UR-513H, -10UR-516H, -11U601G, -11U-602G, -11U-611G, and -11U-612G Turboprop 1900C

Goodrich Avionics Systems, Inc.

Appliance: Terrain Awareness Warning System (TAWS)

Bell Helicopter Textron Canada Alexander Schleicher GmbH & Co. Segelflugzeugbau Lycoming Engines Garmin International Inc. Eagle Aircraft (Malaysia) SDN. BHD

Rotorcraft: 407 Glider: ASH 25M

Biweekly 2004-11 2004-08-15 2004-10-07 2004-10-08 2004-10-14 2004-10-15 2004-11-04

COR S 2003-13-08 S 2002-06-52 S 91-14-22

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Engine: Direct-Drive Reciprocating Engines Appliance: Mode S transponders Eagle 150B

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.

Information

Manufacturer

Applicability

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-12 2004-06-51

FR

2004-11-05 2004-11-06 2004-11-10 2004-11-12

Boeing Defense And Space Group Eurocopter France Agusta S.p.A Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ''PZL-Bielsko'' Alexander Schleicher Gmbh & Co.

Rotorcraft: 234

Agusta S.p.A. Burkhart Grob Luft-Und Raumfahrt GmbH & Co KG Cessna Airplane Company Eurocopter France Pilatus Aircraft Ltd. Dowty Aerospace Propellers

Rotorcraft: A109C, A109E, and A109K2 Glider: G103 Twin Astir, G103A Twin II Acro, G103C Twin III Acro 500, 501, 550, and 551 Rotorcraft: EC 155 B and B1 PC-12 and PC-12/45 Propeller: R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4-82-F/13 Rotorcraft: MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1

Rotorcraft: EC 130 B4 and AS 350 B3 Rotorcraft: A109E Glider: SZD-50-3 ''Puchacz'' Glider: ASW 27

Biweekly 2004-13 2001-24-07 R1 2003-19-14 R1

R R

2004-09-05 2004-12-06 2004-12-11 2004-13-01

COR S 2002-01-28

2004-13-05

Eurocopter Deutschland

Biweekly 2004-14 96-26-05 R1 2003-13-15 R1 2004-10-14 2004-13-20 2004-13-26 2004-14-02 2004-14-12

Res. R COR, S 91-14-22

Robinson Helicopter Company Schweizer Aircraft Corporation Lycoming Engines Garmin AT Kaman Aerospace Corporation Rolls-Royce Corporation New Piper Aircraft, Inc.

Rotorcraft: R44 Rotorcraft: 269A, 269A-1, 269B, 269C, and TH-55A Engine: Direct-Drive Reciprocating Engines Appliance: Global positioning system (GPS) Rotorcraft: K-1200 Engine: 250-C28, -C28B and, -C28C Turboshaft PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R301T, PA-32-301T, PA-32-301FT, PA-32-301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP

The Cessna Aircraft Company

525

2004-14-21 2004-14-22

Stemme GmbH & Co. Pratt & Whitney Canada

2004-15-01

Raytheon Aircraft Company

Glider: S10-VT, S10-V, S10 Engine: PW206B, PW206C, PW206E, PW207D, and PW207E Turboshaft 390

Biweekly 2004-15 2004-14-20

COR S 2003-21-07

Biweekly 2004-16 2004-15-11 2004-15-15 2004-15-18 2004-15-19 2004-15-21 2004-15-22 2004-16-07

S 2002-19-10

Eurocopter France Air Tractor, Inc. Cessna Aircraft Company The New Piper Aircraft, Inc Agusta S.p.A. Sikorsky Aircraft Corp. General Electric Company

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Rotorcraft: EC155B and B1 AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501, AT-502, AT-502A, AT-502B, AT-503A, AT-602, AT-802 and AT-802A 172R, 172S, 182S, 182T, T182T, 206H, T206H PA-46-500TP Rotorcraft: A109K2 Rotorcraft: S-61L, S-61N, S-61-NM, and S-61R Engine: CT7-2D1 Turboshaft

BW 2004-16 EUROCOPTER FRANCE AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-15-11 Eurocopter France: Amendment 39-13745. Docket No. 2003-SW-40-AD. Applicability: Model EC155B and B1 helicopters with auxiliary system unit (ASU) board 10 Alpha 2, part number (P/N) SE07451, installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent an electrical short circuit, failure of landing gear to extend, and an emergency landing, accomplish the following: (a) Within 15 hours time-in-service (TIS), clean the auxiliary system unit (ASU) board 10 Alpha 2. Clean the ASU board by following the Accomplishment Instructions, paragraphs 2.B.1, and 2.B.2.a., of Eurocopter EC155 Alert Service Bulletin (ASB) No. 31A005, dated August 20, 2003 (ASB No. 31A005). (b) Within 30 days, modify the wiring and wiring harness permanently by complying with paragraph (c) of this AD or temporarily by following the Accomplishment Instructions, paragraphs 2.B.1. and 2.B.2.a. through 2.B.2.d. of ASB No. 31A005. If temporarily modified: (1) Install a self-adhesive placard of the size and in the location depicted in Figure 4 of ASB No. 31A005 with the following text in white letters on a red background: ''CAUTION: ON GROUND OPERATION OF EMERGENCY LANDING GEAR PUMP IS TIME LIMITED-SEE OPERATING LIMITATIONS'' and (2) Revise the Operating Limitations by inserting the following text into the Rotorcraft Flight Manual (RFM): ''(i) Limit the emergency landing gear pump (pump) to 10 minutes of continuous operation. (ii) When the pump is continuously operated from 1 to 5 minutes, allow it to cool for 15 minutes before further use. (iii) When the pump is continuously operated from 5 to 10 minutes, allow it to cool for 30 minutes before further use.'' Note 1: Modifying the electric wiring covered by Alert Telex No. 31A005R1, dated September 19, 2002, led to inhibiting the protective thermal switch of the electric pump. This resulted in the need for a limitation placard. The purpose of the limitation placard is to remind operators about the on-ground operating limitations that apply to the electric pump. (c) Within 10 months, modify the wiring and wiring harness by following the Accomplishment Instructions, paragraphs 2.A. and 2.B., of Eurocopter EC155 ASB No. 31A008, dated August 20, 2003 (ASB No. 31A008). If you made the temporary modifications described in paragraph (b) of this AD, remove the placard from the helicopter and the limitations inserted in the RFM as a result of paragraphs (b)(1) and (b)(2) of this AD.

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2004-15-11 2

(d) Permanently modifying the wiring and wiring harness following ASB No. 31A008 is terminating action for the requirements of this AD. (e) 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, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (f) Special flight permits will not be issued. (g) Cleaning the auxiliary system unit and modifying the wiring and wiring harness shall be done by following Eurocopter EC155 Alert Service Bulletin No. 31A005 and Alert Service Bulletin No. 31A008, both dated August 20, 2003, as applicable. The Director of the Federal Register approved this 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. (h) This amendment becomes effective on September 3, 2004. Note 2: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD Nos. 2002-515(A) R1 and 2003-323(A), both dated September 3, 2003. Issued in Fort Worth, Texas, on July 16, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-17219 Filed 7-29-04; 8:45 am] BILLING CODE 4910-13-P

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BW 2004-16 AIR TRACTOR, INC. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-15-15 Air Tractor, Inc.: Amendment 39-13749; Docket No. 2004-CE-05-AD; Supersedes AD 2002-19-10; Amendment 39-12890. When Does This AD Become Effective? (a) This AD becomes effective on September 7, 2004. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 2002-19-10. 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 AT-401, AT-401B, AT-402, AT-402A, and AT-402B. AT-501, AT-502, AT-502A, AT-502B, and AT-503A. AT-602 AT-802 and AT-802A

Serial Nos. 0716 through 1144 0037 through 0658 0337 through 0664 0001 through 0139

What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of cracks in the aft fuselage upper longeron, originally detected as excessive movement in the empennage due to the loss of fuselage torsional rigidity. The actions specified in this AD are intended to detect and correct cracks in the upper aft longeron, which could cause the fuselage to fail. Such failure could result in loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must inspect the upper longeron and upper diagonal tube (as applicable) on the left hand side of the fuselage frame just forward of the vertical fin front spar attachment for cracks at the times specified below. You must also replace and modify any cracked upper and diagonal longerons (as applicable) found during any inspection required by this AD before further flight after the inspection in which cracks are found.

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2004-15-15 2

Affected models and serial nos. (1) AT-401, AT401B, serial numbers (S/Ns) 0716 through 1144.

(2) AT-402, AT402A, and AT402B, S/Ns 0716 through 1144.

(3) AT-501, AT502, AT -502B, and AT-503A, S/Ns 0037 through 0658.

(4)AT-502A, S/Ns 0037 through 0658

Inspection compliance times

Procedures

Initially inspect upon the accumulation of 1,250 total hours time-in-service (TIS) or within the next 100 hours TIS after September 7, 2004 (the effective date of this AD), whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper and diagonal longerons are replaced and modified. Replacing and modifying the upper and diagonal longerons is the terminating action for the repetitive inspection requirement in this AD. Initially inspect upon the accumulation of 1,250 total hours TIS or within the next 100 hours TIS after the last inspection required by AD 2002-19-10, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper and diagonal longerons are replaced and modified. Replacing and modifying the upper and diagonal longerons is the terminating action for the repetitive inspection requirement in this AD. Initially inspect upon the accumulation of 4,800 total hours TIS or within the next 100 hours TIS after September 7, 2004 (the effective date of this AD), whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper longeron is replaced and modified. Replacing and modifying the upper longeron is the terminating action for the repetitive inspection requirement in this AD. Initially inspect upon the accumulation of 2,800 total hours TIS or within the next 100 hours TIS after September 7, 2004 (the effective date of this AD), whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper longeron is replaced and modified. Replacing and modifying the upper longeron is the terminating action for the repetitive inspection requirement in this AD.

Inspect following Snow Engineering Co. Service Letter #218A, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #218B, dated November 10, 2003.

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Inspect following Snow Engineering Co. Service Letter #218A, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #218B, dated November 10, 2003. Inspect following Snow Engineering Co. Service Letter #195B, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #195A, revised November 10, 2003. Inspect following Snow Engineering Co. Service Letter #195B, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #195A, revised November 10, 2003.

2004-15-15 3

(5) AT-602, S/Ns Initially inspect upon the accumulation of 0337 through 700 total hours TIS or within the next 100 0661 hours TIS after the last inspection required by AD 2002-19-10, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper longeron is replaced and modified. Replacing and modifying the upper longeron is the terminating action for the repetitive inspection requirement in this AD. (6) AT-602, S/Ns Initially inspect upon the accumulation of 0662 through 1,750 total hours TIS or within the next 100 0664 hours TIS after the last inspection required by AD 2002-19-10, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper longeron is replaced and modified. Replacing and modifying the upper longeron is the terminating action for the repetitive inspection requirement in this AD. (7) AT-802 And Initially inspect upon the accumulation of AT-802A, S/Ns 250 total hours TIS or within the next 100 0001 through hours TIS after the last inspection required 0004 and 0012 by AD 2002-19-10, whichever occurs later. through 0118. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper longeron is replaced and modified. Replacing and modifying the upper longeron is the terminating action for the repetitive inspection requirement in this AD. (8) AT-802 and Initially inspect upon the accumulation of AT-802A, S/Ns 900 total hours TIS or within the next 100 0005 through hours TIS after the last inspection required 0011. by AD 2002-19-10, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper longeron is replaced and modified. Replacing and modifying the upper longeron is the terminating action for the repetitive inspection requirement in this AD. (9) AT-802 And Initially inspect upon the accumulation of AT-802A, S/Ns 1,750 total hours TIS or within the next 100 0119 through hours TIS after the last inspection required 0139. by AD 2002-19-10, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 100 hours TIS until the upper longeron is replaced and modified. Replacing and modifying the upper longeron is the terminating action for the repetitive inspection requirement in this AD. 10

Inspect following Snow Engineering Co. Service Letter #213A, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #213B, revised November 10, 2003. Inspect following Snow Engineering Co. Service Letter #213A, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #213B, revised November 10, 2003. Inspect following Snow Engineering Co. Service Letter #217A, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #217B, revised November 10, 2003. Inspect following Snow Engineering Co. Service Letter #217A, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #217B, revised November 10, 2003. Inspect following Snow Engineering Co. Service Letter #217A, dated November 10, 2003, as specified in Snow Engineering Co. Service Letter #195, reissued November 10, 2003. Replace and modify following Snow Engineering Co. Service Letter #217B, revised November 10, 2003.

2004-15-15 4

(f) You may replace and modify the upper and diagonal longeron (as applicable) at any time as a terminating action for the repetitive inspection requirement in this AD. However, you must replace and modify the upper and diagonal longeron (as applicable) before further flight after any inspection in which cracks are found. May I Request an Alternative Method 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 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Fort Worth Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Andrew D. McAnaul, Aerospace Engineer, FAA, Fort Worth ACO, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. Current duty station: San Antonio Manufacturing Inspection District Office (MIDO), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Snow Engineering Co. Service Letter 195, reissued November 10, 2003; Snow Engineering Co. Service Letter 195A, revised November 10, 2003; Snow Engineering Co. Service Letter 195B, dated November 10, 2003; Snow Engineering Co. Service Letter 213A, dated November 10, 2003; Snow Engineering Co. Service Letter 213B, revised November 10, 2003; Snow Engineering Co. Service Letter 217A, dated November 10, 2003; Snow Engineering Co. Service Letter 217B, revised November 10, 2003; Snow Engineering Co. Service Letter 218A, dated November 10, 2003; and Snow Engineering Co. Service Letter 218B, dated November 10, 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 Air Tractor, Incorporated, P.O. Box 485, Olney, Texas 76374. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on July 20, 2004. Dorenda D. Baker, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-17119 Filed 7-29-04; 8:45 am] BILLING CODE 4910-13-P

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BW 2004-16 CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-15-18 Cessna Aircraft Company: Amendment 39-13752; Docket No. 2004-CE-03-AD. When Does This AD Become Effective? (a) This AD becomes effective on September 12, 2004. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 2003-24-13. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are: (1) equipped with a KAP 140 autopilot computer system, part number (P/N) 065-00176-2501, P/N 065-00176-2602 , P/N 065-00176-5001, P/N 065-00176-5101, P/N 06500176-5201, P/N 065-00176-5402, or P/N 065-00176-7702, all serial numbers; and (2) certificated in any category. Model 172R 172S 182S 182T T182T 206H T206H

Serial Nos. 17280001 through 17281073, 17281075 through 17281127, and 17281130. 172S8001 through 172S9195, 172S9197, 172S9198, and 172S9200 through 172S9203. 18280001 through 18280944. 18280945 through 18281065, 18281067 through 18281145, 18281147 through 18281163, 18281165 through 18281167, and 18281172. T18208001 through T18208109, and T18208111 through T18208177. 20608001 through 20608183, 20608185, 20608187, and 20608188. T20608001 through T20608039, T20608041 through T20608367, T20608369 through T20608379, T20608381, T20608382, and T20608385.

What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of inadvertent and undetected engagement of the autopilot system. The actions specified in this AD are intended to prevent unintentionally engaging the KAP 140 autopilot computer system, which could cause the pilot to take inappropriate actions. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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2004-15-18 2

Actions (1) For airplanes previously affected by AD 2003-24-13: install the update to the KC 140 autopilot computer system operating software.

Compliance Within the next 100 hours time-in-service (TIS) after January 20, 2004 (the effective date of AD 2003-24-13), unless already done.

(2) For airplanes previously affected by AD 2003- 24- 13: do the following: (i) Change the unit part number by attaching flavor sticker, part number (P/N) 057-02203-0003, on the unit’s serial tag; (ii) Attach an M decal, P/N 057-029840501, in front of the unit serial number (this indicates that the unit’s P/N has been changed); and (iii) Attach a software mod tag, P/N 057-05287-0301, in place of the old tag to indicate the software change to SW MOD 03/01. (3) For airplanes not affected by AD 2003- 24-13: install the update to the KC 140 autopilot computer system operating software.

Prior to further flight after installing the update to the KC 140 autopilot computer system operating software as specified in paragraph (e)(1) of this AD, unless already done.

Within the next 100 hours time-in-service (TIS) after September 12, 2004 (the effective date of this AD).

(4) For all affected airplanes: install As of September 12, only KC 140 autopilot computer 2004 (the effective date systems, part number (P/N) 065of this AD). 00176-2501, P/N 065-00176-2602 , P/N 065-00176-5001, P/N 065-001765101, P/N 065-00176-5201, P/N 06500176-5402, or P/N 065-00176-7702, that have been modified as specified in paragraphs (e)(1), (e)(2), and (e)(3) of this AD.

Procedures Follow Cessna Service Bulletin SB02-22-01, dated November 25, 2002, and Honeywell Service Bulletin No: KC 140-M1, dated August 2002, as specified in Honeywell Installation Bulletin No. 491, Rev. 3, dated April 2003. Follow Honeywell Service Bulletin No: KC 140-M1, dated August 2002, as specified in Cessna Service Bulletin SB0222-01, dated November 25, 2002.

Follow Honeywell Installation Bulletin No. 491, Rev. 3, dated April 2003; Cessna Service Bulletin SB02-22-01, dated November 25, 2002; Honeywell Service Bulletin No: KC 140M1, dated August 2002; and Cessna Single Engine Service Bulletin SB98-22-01, dated May 18, 1998, as applicable. Not applicable.

(f) You may request a revised flight manual supplement from Cessna at the address specified in paragraph (h) of this AD.

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May I Request an Alternative Method 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 39.19. (1) Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Wichita Aircraft Certification (ACO), FAA. For information on any already approved alternative methods of compliance, contact Dan Withers, Aerospace Engineer, Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 9464196; facsimile: (316) 946-4407. (2) Alternative methods of compliance approved in accordance with AD 2003-24-13, which is superseded by this AD, are approved as alternative methods of compliance with this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Cessna Single Engine Service Bulletin SB98-22-01, dated May 18, 1998; Cessna Single Engine Service Bulletin SB02-22-01, dated November 25, 2002; Honeywell Service Bulletin No: KC 140-M1, dated August 2002; and Honeywell Installation Bulletin No. 491, Rev. 3, dated April 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 Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 9429006 and Honeywell, Business, Regional, and General Aviation, 23500 W. 105th Street, Olathe, Kansas 66061. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on July 21, 2004. Dorenda D. Baker, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-17217 Filed 7-29-04; 8:45 am] BILLING CODE 4910-13-P

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BW 2004-16 THE NEW PIPER AIRCRAFT, INC. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-15-19 The New Piper Aircraft, Inc.: Amendment 39-13753; Docket No. 2003-CE-52-AD. When Does This AD Become Effective? (a) This AD becomes effective on September 13, 2004. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model PA-46-500TP airplanes, serial numbers 4697001 through 4697163, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of a protective cover installed over the percussion cap or a silicon tube installed over the end of the trigger mechanism pin, on the oxygen generator, rendering the emergency oxygen system inoperative. The actions specified in this AD are intended to detect and remove any protective cover over the percussion cap or any silicon tube over the end of the trigger mechanism pin, which could result in failure of the emergency oxygen system. This failure could lead to the crew or passengers not being able to get oxygen in an emergency situation. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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Actions

Compliance (1) Inspect: Within the next 50 hours time(i) the percussion cap of any oxygen in-service after September 13, generator (part number (P/N) 4712004 (the effective date of this 025) for the presence of any protective AD) or within the next 30 cover; and calendar days after September (ii) the end of the trigger mechanism of 13, 2004 (the effective date of any oxygen generator (P/N 471-025) this AD), whichever occurs for the presence of any silicon tube. first, unless already done. (2) If during the inspections required by Before further flight after the paragraphs (e)(1)(i) and (e)(1)(ii) of inspection required in this AD, you find any protective cover paragraph (e)(1) of this AD, over the percussion cap or any silicon unless already done. tube over the end of the trigger mechanism, remove any protective cover or silicon tube. (3) Do not operate the airplane after installation of any oxygen generator (P/N 471-025) referenced in this AD unless any protective cover of the percussion cap or any silicon tube over the end of the trigger mechanism has been removed.

Procedures Follow the INSTRUCTIONS paragraph in The New Piper Aircraft, Inc. Service Bulletin No. 1140, dated September 16, 2003, and the applicable airplane maintenance manual. Follow the INSTRUCTIONS paragraph in The New Piper Aircraft, Inc. Service Bulletin No. 1140, dated September 16, 2003, and the applicable airplane maintenance manual. As of September 13, 2004 (the Not applicable. effective date of this AD).

Note 1: Standard procedure is to remove the protective cover after installation. Refer to the applicable airplane maintenance manual for specific procedures for removing any protective cover of the percussion cap or any silicon tube over the end of the trigger mechanism. Note 2: The affected models in the service bulletin referenced in this AD include the Models PA-46-310P and PA-46-350P airplanes. However, these models are certificated at a lower service ceiling than the Model PA-46-500TP airplane. Since Piper has demonstrated an emergency descent to a lower altitude with no oxygen to the pilot, neither Model PA-46-310P nor PA-46-350P airplanes are affected by the identified condition. May I Request an Alternative Method 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 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Atlanta Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Hector Hernandez, Aerospace Engineer, FAA, Atlanta ACO, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone: (770) 703-6069; facsimile: (770) 703-6097.

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Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in The New Piper Aircraft, Inc. Service Bulletin No. 1140, dated September 16, 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 The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567-4361; facsimile: (772) 978-6584. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on July 22, 2004. Dorenda D. Baker, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-17218 Filed 7-29-04; 8:45 am] BILLING CODE 4910-13-P

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BW 2004-16 AGUSTA S.P.A. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-15-21 Agusta S.p.A.: Amendment 39-13755. Docket No. 2004-SW-14-AD. Applicability: Model A109K2 helicopters, with tail rotor trunnion assembly (trunnion), part number 109-0131-05 (all dash numbers), installed, certificated in any category. Compliance: Required as indicated. To detect a crack and prevent fatigue failure of the trunnion, loss of the tail rotor hub and blade assembly, and subsequent loss of control of the helicopter, do the following: (a) Using a qualified Level II Inspector and following the Compliance Instructions, paragraphs 1. through 8., of Agusta Bollettino Tecnico No. 109K-37, dated February 13, 2004, dye penetrant inspect the trunnion for a crack as follows: (1) Unless accomplished previously, within 10 hours time-in-service (TIS) for trunnions with 150 or more hours TIS; (2) Unless accomplished previously, on or before accumulating 150 hours TIS for trunnions with less than 150 hours TIS; and (3) Thereafter, at intervals not to exceed 150 hours TIS. (b) If a crack is found, before further flight, replace the cracked trunnion with an airworthy trunnion before further flight. (1) Within 5 days, report the part number, serial number, total hours TIS, and a description of the crack to Richard Monschke, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961. (2) Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (c) 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, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (d) Do the inspection following Agusta Bollettino Tecnico No. 109K-37, dated February 13, 2004. 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 Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. Copies may be inspected at the FAA, Office of the Regional Counsel,

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Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. (e) This amendment becomes effective on August 17, 2004. Note: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) AD No. 2004-068, dated February 18, 2004. Issued in Fort Worth, Texas, on July 22, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-17369 Filed 7-30-04; 8:45 am] BILLING CODE 4910-13-P

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BW 2004-16 SIKORSKY AIRCRAFT CORPORATION AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-15-22 Sikorsky Aircraft Corporation: Amendment 39-13756. Docket No. 2003-SW-35-AD. Applicability: Model S-61L, S-61N, S-61-NM, and S-61R helicopters, certificated in any category. Compliance: Required within 60 days, unless accomplished previously. To detect an impending engine bearing (bearing) failure, which, if undetected and not addressed by appropriate crew action, may result in oil leakage, severing of the shaft housing, an uncontained in-flight fire, and a subsequent emergency landing, accomplish the following: (a) Install an engine chip detector, part number 3049T42P01 or 3018T72P01, in the engine power turbine accessory drive assembly using the Accomplishment Instructions, paragraphs 3.A. and 3.B., in General Electric Aircraft Engines CT58 Service Bulletin Number 72-0195, dated May 1, 2003. (b) Install an on-board engine chip detector annunciation system using Sikorsky Aircraft Corporation Alert Service Bulletin No. 61B30-15, Revision A. dated October 20, 2003 (ASB). For helicopters with a master warning caution panel (MWCP) manufactured by United Controls or Sundstrand Data, install in accordance with paragraph 3.B. of the ASB. For helicopters with a MWCP manufactured by Grimes Mfg., install in accordance with paragraph 3.C. of the ASB. (c) After accomplishing paragraph (b) of this AD, before further flight, perform a functional test of the engine chip detector system and repeat the functional test at intervals not to exceed 150 hours TIS using the Accomplishment Instructions, paragraph 3.D., of the ASB. (d) Insert the emergency procedures for an on-board engine chip detector warning light illumination into the Emergency Procedures section of the applicable Rotorcraft Flight Manual using the Accomplishment Instructions, paragraph 3.E., of the ASB. (e) 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 Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, for information about previously approved alternative methods of compliance. (f) The actions, including installations, testing, and inserting information into the Rotorcraft Flight Manual, shall be done in accordance with General Electric Aircraft Engines CT58 Service Bulletin Number 72-0195, dated May 1, 2003; and Sikorsky Aircraft Corporation Alert Service Bulletin No. 61B30-15, Revision A. dated October 20, 2003. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

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Copies may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Tech Support, 6900 Main Street, Stratford, Connecticut 06614, phone (203) 386-3001, fax (203) 386-5983; and from GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513) 552-3272; fax (513) 552-3329, e-mail [email protected]. 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. (g) This amendment becomes effective on September 7, 2004. Issued in Fort Worth, Texas, on July 22, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-17370 Filed 7-30-04; 8:45 am] BILLING CODE 4910-13-P

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BW 2004-16 GENERAL ELECTRIC COMPANY AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-16-07 General Electric Company: Amendment 39-13763. Docket No. FAA-2004-18758; Directorate Identifier 2004-NE-24-AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 23, 2004. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CT7-2D1 turboshaft engines with turbine stage 2 aft cooling plates, part number (P/N) 6064T07P02, and serial numbers (SN) starting with GFFN****, GFFP****, GFFR0*** through GFFR7***, GFFR81** through GFFR89**, GFFR8A** through GFFR8G**, GFFR8H92 through GFFR8H99, and GFFR8H9A through GFFR8H9N installed. Asterisks represent any subsequent number or letter that follow the root SN. These engines are installed on, but not limited to, Sikorsky S-70 helicopters. Unsafe Condition (d) This AD results from an uncontained failure of a turbine stage 2 aft cooling plate in a GE CT7 turboprop engine. We are issuing this AD to prevent a similar uncontained failure of turbine stage 2 aft cooling plates in GE CT7-2D1 turboshaft engines. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Cooling Plate Removal (f) At the next disassembly of the gas generator turbine rotor assembly at an FAA-approved overhaul facility, but not later than 5,000 cycles-since-new, replace any turbine stage 2 aft cooling plate, P/N 6064T07P02, with SNs starting with GFFN****, GFFP****, GFFR0*** through GFFR7***, GFFR81** through GFFR89**, GFFR8A** through GFFR8G**, GFFR8H92 through GFFR8H99, and GFFR8H9A through GFFR8H9N, with a cooling plate that does not have a SN specified in this AD.

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(g) After the effective date of this AD, do not install stage 2 aft cooling plate, P/N 6064T07P02, SNs GFFN****, GFFP****, GFFR0*** through GFFR7***, GFFR81** through GFFR89**, GFFR8A** through GFFR8G**, GFFR8H92 through GFFR8H99, and GFFR8H9A through GFFR8H9N into any engine. Material Incorporated by Reference (h) None. Related Information (i) GE CT7-TS Alert Service Bulletin 72-A0032, dated June 11, 2003, provides additional information regarding the disassembly of the gas generator turbine rotor assembly. Issued in Burlington, Massachusetts, on July 29, 2004. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 04-17755 Filed 8-5-04; 8:45 am] BILLING CODE 4910-13-P

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