FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-03 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 2005-01 2004-26-09 2004-26-11 2005-01-04
2005-01-10 2005-01-11
Rolls-Royce Corporation
S 98-15-13
S 74-06-01
Bell Helicopter Textron Canada Raytheon Aircraft Company
The New Piper Aircraft, Inc Pilatus Aircraft Ltd.
Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft Rotorcraft: 222, 222B, 222U, 230, 430 65-90, 65-A90, B90, C90, C90A, C90B, E90, F90, H90, 100, A100, A100-1, (RU-21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99,, A99A, B99, C99 PA-23-235, PA-23-250, and PA-E23-250 PC-12 and PC-12/45
Biweekly 2005-02 98-20-38 R1
R
Raytheon Aircraft Company
2005-01-14 2005-01-17 2005-01-18
S 2002-21-16 S 98-03-14 S 93-25-07
Bombardier-Rotax GmbH EXTRA Flugzeugbau GmbH Raytheon Aircraft Company
2005-01-19
S 2004-10-15
GARMIN International Inc
2005-02-01
The Lancair Company
Beech 200 (A100-1 (U-21J)), Beech 200C, Beech 200CT, Beech 200T, Beech A200 (C-12A) or (C-12C), Beech A200C (UC-12B), Beech A200CT (C-12D), (FWC-12D), (RC-12D), (C-12F), (RC-12G), (RC-12H), (RC-12K), or (RC-12P), B200CT, and B200T Engine: 912 F, 912 S, and 914 F Series Reciprocating EA–300 and EA–300/S A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), A200CT (RC–12K), 200C, B200C, 200CT, 200T, B200C (C-12F), B200C (UC–12F), B200C (UC–12M), B200CT, 300, B300, B300C, and B300C Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders LC40–550FG and LC42–550FG
Biweekly 2005-03 2005-01-04
COR S 98-15-13
Raytheon Aircraft Company
2005-01-18
COR S 93-25-07
Raytheon Aircraft Company
2005-02-11 2005-03-04
COR
Gippsland Aeronautics Pty. Ltd. Pacific Aerospace Corp., Ltd.
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65–90, 65–A90, B90, C90, C90A, E90, F90, H90, 100, A100, A100–1 (RU–21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99, A99A, B99, and C99 A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), A200CT (RC–12K), 200C, B200C, 200CT, B200CT, 200T, B200T, B200C (C–12F), B200C (UC–12F), B200C (UC–12M), B200CT, 300, B300C, and B300C GA8 750XL
BW 2005-03 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: [Federal Register: January 27, 2005 (Volume 70, Number 17); Page 3871; www.access.gpo.gov/su_docs/aces/aces140.html] 2005-01-04 Raytheon Aircraft Company: Amendment 39-13928; Docket No. FAA-2004-19089; Directorate Identifier 2000-CE-38-AD. When Does This AD Become Effective? (a) This AD becomes effective on February 22, 2005. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 98-15-13, Amendment 39-10664. 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 (1) 65–90 (2) 65–A90 (3) B90 (4) C90 (5) C90A
Series LJ–1 through LJ–75, and LJ–77 through LJ–113. LJ–76, LJ–114 through LJ–317, and LJ–178A. LJ–318 through LJ–501. LJ–502 through LJ–1062. LJ–1063 through LJ–1287, LJ–1289 through LJ–1294, and LJ–1296 through LJ–1299. (6) C90A LJ–1288, LJ–1295, and LJ–1300 through LJ–1445. (7) E90 LW–1 through LW–347. (8) F90 LA–2 through LA–236. (9) H90 LL–1 through LL–61. (10) 100 B–2 through B–89, and B–93. (11) A100 B–1, B–90 through B–92, B–94 through B–204, and B–206 through B–247. (12) A100–1 (RU–21J) BB–3 through BB–5. (13) B100 BE–1 through BE–137.
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(14) 200
(15) 200C (16) 200CT (17) 200T (18) A200 (19) A200C (20) A200CT (21) B200
(22) B200C (23) B200CT (24) B200T (25) 300 (26) B300 (27) B300C (28) 99, 99A, A99, A99A (29) B99 (30) C99
BB–2, BB–6 through BB–185, BB–187 through BB–202, BB–204 through BB–269, BB–271 through BB–407, BB–409 through BB–468, BB–470 through BB–488, BB–490 through BB–509, BB–511 through BB–529, BB– 531 through BB–550, BB–552 through BB–562, BB–564 through BB–572, BB–574 through BB–590, BB–592 through BB–608, BB–610 through BB– 626, BB–628 through BB–646, BB–648 through BB–664, BB–735 through BB–792, BB–794 through BB–797, BB–799 through BB–822, BB–824 through BB–828, BB–830 through BB–853, BB–872, BB–873, BB–892, BB–893, and BB–912. BL–1 through BL–23, and BL–25 through BL–36. BN–1. BT–1 through BT–22, and BT–28. BC–1 through BC–75, and BD–1 through BD–30. BJ–1 through BJ–66. BP–1, BP–7 through BP–11, BP–22, BP–24 through BP–63, FC–1 through FC–3, FE–1 through FE–36, and GR–1 through GR–19. BB–829, BB–854 through BB–870, BB–874 through BB–891, BB–894, BB–896 through BB–911, BB–913 through BB–990, BB–992 through BB– 1051, BB–1053 through BB–1092, BB–1094, BB–1095, BB–1099 through BB–1104, BB–1106 through BB–1116, BB–1118 through BB–1184, BB– 1186 through BB–1263, BB–1265 through BB–1288, BB–1290 through BB–1300, BB–1302 through BB–1425, BB–1427 through BB–1447, BB– 1449, BB–1450, BB–1452, BB–1453, BB–1455, BB–1456, and BB–1458 through BB–1536. BL–37 through BL–57, BL–61 through BL–140, BU–1 through BU–10, BV–1 through BV–12, and BW–1 through BW–21. BN–2 through BN–4, BU–11, BU–12, FG–1, and FG–2. BT–23 through BT–27, and BT–29 through BT–38. FA–1 through BA–230, and FF–1 through FF–19. FL–1 through FL–141. FM–1 through FM–9, and FN–1. U–1 through U–49, U–51 through U–145, and U–147. U–146, and U–148 through U–164. U–50, and U–165 through U–239.
What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of blockage of fuel hose due to hose delamination. The actions specified in this AD are intended to prevent fuel flow interruption, which could lead to uncommanded loss of engine power and loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:
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Actions (1) For airplanes manufactured prior to January 1, 1994, check airplane maintenance records for any MIL-H–6000B fuel hose replacement from January 1, 1994, up to and including the effective date of this AD.
Compliance For all affected airplanes other than Models 99, 99A, A99, A99A, B99, and C99: Within 200 hours time-in-service (TIS) after August 28, 1998 (the effective date of AD 98–15– 13). For all affected Models 99, 99A, A99, A99A, B99, and C99 airplanes: Within the next 200 hours TIS after February 22, 2005 (the effective date of this AD).
Procedures Documented compliance with AD 98–15–13 or follow PART II of the ACCOMPLISHMENT INSTRUCTIONS section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. An owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations 914 CFR 43.7), and must be entered into the aircraft records showing compliance with this AD in accordance with section 43.7 of the Federal Aviation Regulations (14 CFR 43.9) can accomplish paragraph (e)(1) required by this AD. (2) If the airplane records For all affected airplanes other Documented compliance with AD show that a MIL–H–6000B than the Models 99, 99A, A99, 98–15–13 or follow PART II of the fuel hose has been replaced, A99A, B99, and C99: Within ACCOMPLISHMENT inspect the airplane fuel 200 hours TIS after August 28, INSTRUCTIONS Section in hoses for a 3/8-inch-wide red 1998 (the effective date of AD Raytheon Aircraft Mandatory or orange-red, length-wise 98–15–13). For all affected Service Bulletin SB 2718, Revision stripe, with manufacturer’s Models 99, 99A, A99, A99A, 1, dated June 1997; or Revision 2, code, 94519, printed B99, and C99 airplanes: Within dated April 2000. periodically along the line in the next 200 hours TIS after red letters on one side. The February 22, 2005 (the hoses have a spiral or effective date of this AD). diagonal outer wrap with a fabric-type texture on the rubber surface. (3) Replace any fuel hose For all affected airplanes other Documented compliance with AD that matches the description than the Models 99, 99A, A99, 98–15–13 or follow PART II of the in paragraph (e)(2) of this A99A, B99, and C99: Within ACCOMPLISHMENT AD with an FAA-approved 200 hours TIS after August 28, INSTRUCTIONS Section in MIL–H–6000B fuel hose 1998 (the effective date of AD Raytheon Aircraft Mandatory that has a criss-cross or 98–15–13). For all affected Service Bulletin SB 2718, Revision braided external wrap. Models 99, 99A, A99, A99A, 1, dated June 1997; or Revision 2, B99, and C99 airplanes: Within dated April 2000. the next 200 hours TIS after February 22, 2005 (the effective date of this AD).
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(4) For Raytheon Models C90A, B200, and B300 airplanes that were manufactured on January 1, 1994, and after, replace the MIL–H–6000B fuel hoses.
Within 200 hours TIS after August 28, 1998 (the effective date of AD 98–15–13).
(5) Do not install a rubber As of February 22, 2005 (the fuel hose having spiral or effective date of this AD). diagonal external wrap with a 3/8-inch-wide red or orange-red, length-wise stripe running down the side of the hose, with the manufacturer’s code, 94519, printed periodically along the line in red letters on any of the affected airplanes.
Documented compliance with AD 98–15–13 or follow PART I of the ACCOMPLISHMENT INSTRUCTIONS Section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. Not applicable.
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, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Jeffrey A. Pretz, Aerospace Engineer, ACE-116W, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4153; facsimile: (316) 946-4407. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. 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. To get a copy of this service information, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 625-7043. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA2004-19089. Issued in Kansas City, Missouri, on December 27, 2004. William J. Timberlake, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-35 Filed 1-5-05; 8:45 am] BILLING CODE 4910-13-P 7
BW 2005-03 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: [Federal Register: January 28, 2005 (Volume 70, Number 18); Page 4191] [Federal Register: February 2, 2005 (Volume 70, Number 21); Page 5515] [www.access.gpo.gov/su_docs/aces/aces140.html] 2005-01-18 Raytheon Aircraft Company: Amendment 39-13943; Docket No. 2004-CE-01-AD. When Does This AD Become Effective? (a) This AD becomes effective on March 1, 2005. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 93-25-07, Amendment 39-8773. What Airplanes Are Affected by This AD? (c) This AD affects the following Beech airplane models and serial numbers that are certificated in any category: Model (1) A100–1 (U–21J) (2) 200 and B200 (3) A200 (C–12A) and A200 (C–12C). (4) A200C (UC–12B) (5) A200CT (C–12D). (6) A200CT (FWC–12D). (7) A200CT (RC–12D). (8) A200CT (C–12F) (9) A200CT (RC–12G). (10) A200CT (RC–12H). (11) A200CT (RC–12K). (12) A200CT (RC–12P). (13) A200CT (RC–12K). (14) 200C and B200C (15) 200CT and B200CT. (16) 200T and B200T (17) B200C (C–12F)
Serial Nos. BB–3 through BB–5 BB–2 and BB–6 through BB–1462. BC–1 through BC–75 and BD–1 through BD–30. BJ–1 through BJ–66. BP–1, BP–22, and BP–24 through BP–51. BP–7 through BP–11. GR–1 through GR–13. BP–52 through BP–63. FC–1 and FC–3. GR–14 through GR–19. FE–1 through FE–9. FE–10 through FE–24. FE–25 through FE–31. BL–1 through BL–72 and BL–124 through BL–138. BN–1 through BN–4. BT–1 through BT–38. BL–73 through BL–112 and BL–118 through BL–123.
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(18) B200C (C–12F) (19) B200C (UC–12F) (20) B200C (UC–12M). (21) B200CT (22) 300 (23) 300 (24) B300 (25) B300C (26) B300C
BP–64 through BP–71. BU–1 through BU–10. BV–1 through BV–12. FG–1 and FG–2. FA–1 through FA–228. FF–1 through FF–19. FL–1 through FL–103. FM–1 through FM–8. FN–1.
What Is the Unsafe Condition Presented in This AD? (d) As currently written, AD 93-25-07 allows continued flight if cracks are found in less than five fuselage stringers in the area of the rear pressure bulkhead. In 1996, FAA developed policy to not allow airplane operation when known cracks exist in primary structure, unless the ability to sustain limit and ultimate load with these cracks is proven. The fuselage stringers in the area of the rear pressure bulkhead are considered primary structure. This AD will bring the actions of AD 93-2507 in compliance with current FAA policy. The actions specified in this AD are intended to detect and correct any cracked fuselage stringers in the rear pressure bulkhead area, which could result in structural damage to the fuselage. This damage could lead to failure of the fuselage with potential loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) For airplanes that have been known cracks that exist in any of the aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and right-hand sides). Either modify or incorporate repairs as specified below. These cracks could have been detected through compliance with AD 93–25–07 and/or Raytheon Mandatory Service Bulletin SB 53– 2472, any revision level: (i) Incorporate the applicable modification kit or kits as specified in Raytheon Mandatory Service Bulletin SB 53–2472, Rev. 4, Issued: June, 1993, Revised: July, 2003; or (ii) Incorporate external doubler repairs on all aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and right-hand sides)
Compliance If airplane has less than five known cracked stringers: Within 25 cycles after March 1, 2005 (the effective date of this AD), unless already done. If cycles are unknown, then you may divide hours time-in-service (TIS) by .75 (18.75 hours TIS ÷ .75 = 25 cycles). If airplane has five or more known cracked stringers: Before further flight after March 1, 2005 (the effective date of this AD), unless already done. AD 93– 25–07 already required this.
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Procedures Incorporate the modification kit(s) following The procedures in Raytheon Mandatory Service Bulletin SB 53–2472, Rev. 4, Issued: June, 1993, Revised: July, 2003. Incorporate the external doubler repairs following the procedures in the maintenance manual.
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(2) For all airplanes that do not have either themodifications or repairs specified in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD incorporated in all aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and right-hand sides): Inspect these aft fuselage stringers. If sealant covers the stringers, you must remove it to facilitate the required inspections and then reapplied. You may terminate the repetitive inspections when all aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and righthand sides) are modified.
For airplanes affected by AD 93– 25–07: Initially inspect at the next inspection interval required by AD 93–25–07. Repetitively inspect thereafter at intervals not to exceed 500 cycles. If cycles are unknown, then you may divide TIS by .75 (375 hours TIS ÷ .75 = 500 cycles). For airplanes not affected by AD 93–25–07: Initially inspect upon accumulating 2,500 cycles on the fuselage or within the next 25 cycles after March 1, 2005 (the effective date of this AD), whichever occurs later, unless already done. Repetitively inspect thereafter at intervals not to exceed 500 cycles. If cycles are unknown, then you may divide hours TIS by .75 (1,875 hours TIS ÷ .75 = 2,500 cycles; 375 hours TIS ÷.75 = 500 cycles; and 18.75 hours TIS ÷ .75 = 25 cycles). (3) If any cracks are found during any If less than five cracked stringers inspection required by this AD, do are found: Within 25 cycles after one of the following: March 1, 2005 (the effective date (i) Incorporate the applicable of this AD), unless already done. If modification kit or kits as specified cycles are unknown, then you may in Raytheon Mandatory Service divide hours TIS by .75 (18.75 Bulletin SB 53–2472, Rev. 4, Issued: hours TIS ÷ .75 = 25 cycles). If five June, 1993, Revised: July, 2003; or or more cracked stringers are (ii) Incorporate external doubler repairs found: Before further flight after on all aft fuselage stringer locations any inspection where five cracked (No. 5 through No. 22 on both the stringers are found, unless already left-hand and right-hand sides) done.
Inspect following the procedures in Raytheon Mandatory Service Bulletin SB 53–2472. Rev. 4, Issued: June, 1993, Revised: July, 2003.
Incorporate the modification kit(s) following The procedures in Raytheon Mandatory Service Bulletin SB 53–2472, Rev. 4, Issued: June, 1993, Revised: July, 2003. Incorporate the external doubler repairs following the procedures in the maintenance manual.
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, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Steven E. Potter, Aerospace Engineer, Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316) 946-4107. 10
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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 Raytheon Mandatory Service Bulletin SB 53-2472, Rev. 4, Issued: June, 1993, Revised: July, 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 Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 6763140. 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 http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on January 7, 2005. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-716 Filed 1-18-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-03 GIPPSLAND AERONAUTICS PTY. LTD. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: Today, 01/31/2005, there is a typo is the AD number of the Federal Register (FR), 2nd col., pg. 4761. The AD# should be 2005-02-11. Since Part 39.13, pg. 4762, of this AD is correct, we will not issue a correction to the FR. We've corrected this copy for clarity. 2005-02-11 Gippsland Aeronautics Pty. Ltd.: Amendment 39-13956; Docket No. FAA-200419442; Directorate Identifier 2004-CE-31-AD. When Does This AD Become Effective? (a) This AD becomes effective on March 4, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects model GA8 airplanes, serial numbers GA8-00-004 through GA8-04-056, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of rubbing between the control wheel shaft and the bush in the control column, which may cause wear or damage to the control wheel shaft where the shaft connects to the control column. This damage may lead to the aileron control becoming stiff or locking. The actions specified in this AD are intended to detect and correct damage of the pilot and co-pilot control wheels and aileron cable operating arm shafts that could result in the aileron controls becoming stiff or locking, which could lead to loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:
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Actions (1) Inspect the pilot and co-pilot control column wheel and aileron cable operating arm shafts for damage. (2) If no damage is found, continue repetitive inspections.
Compliance Perform the initial inspection within 50 hours time-in-service (TIS) after March 4, 2005 (the effective date of this AD).
Procedures Follow Gippsland Aeronautics Pty. Ltd. Service Bulletin SB– GA8–2004–11, Issue 2, dated August 25, 2004. Perform repetitive inspections every Follow Gippsland 300 hours TIS until steel operating Aeronautics Pty. Ltd. arm shafts are replaced with bronze Service Bulletin SB– operating arm shafts. Replacement GA8–2004–11, Issue of steel operating arm shafts with 2, dated August 25, bronze operating arm shafts is 2004. terminating action for this AD on the side that was replaced. If one steel shaft requires replacement, all of the shafts on that side (pilot or co-pilot) must be replaced with bronze shafts. If only one side (pilot or copilot) is replaced, repetitive inspections are still required for the side that was not replaced. If damage is found, repair or replace Follow Gippsland operating arm shafts prior to further Aeronautics Pty. Ltd. flight. If airplane is repaired, Service Bulletin SB– repetitively inspect every 300 hours GA8–2004–11, Issue TIS after repair until replacement of 2, dated August 25, the operating arm shafts. 2004. Replacement of the steel operating arm shafts with bronze operating arm shafts is terminating action for this AD. If only one side (pilot or co-pilot) is replaced with bronze shafts, you must still repetitively inspect the other side that was not replaced.
(3) For airplanes where damage is found: (i) If damage can be repaired by polishing out marks or scratches so that material removed does not exceed 0.005 inches, repair the shaft. You can not repair by polishing out marks or scratches more than one time. (ii) If damage can not be repaired by polishing out marks or scratches so that that material removed does not exceed 0.005 inches or you have already repaired the damage by polishing out marks or scratches previously, the damed steel operating arm shaft must be replaced with a bronze operating arm shaft. When a shaft (pilot or copilot) requires replacement, you must install new bronze shafts in all areas of the affected side (4) As of the effective date of this As of March 4, 2005 (the effective AD, do not install shafts that are not date of this AD). bronze on any affected Model GA8 airplane. 13
Follow Gippsland Aeronautics Pty. Ltd. Service Bulletin SB– GA8–2004–11, Issue 2, dated August 25, 2004.
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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, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 816-329-4059; facsimile: 816-329-4090. Is There Other Information That Relates to This Subject? (g) Australian Civil Aviation Safety Authority Airworthiness Directive AD/GA8/2, dated September 17, 2004, and Gippsland Aeronautics Pty., Ltd., Service Bulletin SB-GA8-2004-11, dated August 25, 2004, also address the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Gippsland Aeronautics Pty. Ltd. Service Bulletin SB-GA8-2004-11, Issue 2, dated August 25, 2004. 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. To get a copy of this service information, contact Gippsland Aeronautics Pty. Ltd., Latrobe Regional Airport, P.O. Box 881, Morwell, Victoria 3840, Australia; telephone: 61 (0) 3 5172 1200; facsimile: 61 (0) 3 5172 1201. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19442. Issued in Kansas City, Missouri, on January 20, 2005. David A. Downey, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-1511 Filed 1-28-05; 8:45 am] BILLING CODE 4910-13-P
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BW 2005-03 PACIFIC AEROSPACE CORPORATION, LTD. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-03-04 Pacific Aerospace Corporation, Ltd.: Amendment 39-13960; Docket No. FAA-200419444; Directorate Identifier 2004-CE-33-AD. When Does This AD Become Effective? (a) This AD becomes effective on March 21, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model 750XL 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 mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. The actions specified in this AD are intended to replace the above identified rivets on the aileron pushrod ends and elevator control pushrod ends, which, if not replaced, could result in loose mechanical elements in the control systems. This could lead to control anomalies and loss of airplane control. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Replace any type TLP–D or TLED rivets on the aileron pushrod ends and elevator control pushrod ends with a new Cherry Max 3213–4–2 or 3243– 4–2 (oversize nominal 1⁄8 inch) rivet.
Compliance With 50 hours timein-service (TIS) after March 21, 2005 (the effective date of this AD), unless already done.
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Procedures Follow the ACCOMPLISHMENT INSTRUCTIONS in Pacific Aerospace Corporation Mandatory Service Bulletin No. PACSB/XL/007, dated June 22, 2004.
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(2) Do not install: (i) Any type TLP–D or TLED rivets on the aileron pushrod ends and elevator control pushrod ends; or. (ii) Any aileron pushrods or elevator control pushrods with type TLP–D or TLED rivets on the ends..
As of March 21, 2005 (the effective date of this AD).
Not Applicable.
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, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Karl Schletzbaum, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 302, Kansas City, MO 64106; telephone: 816-3294146; facsimile: 816-329-4090. Is There Other Information That Relates to This Subject? (g) New Zealand Airworthiness Directive Number DCA/40XL/1, dated June 24, 2004, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Pacific Aerospace Corporation Mandatory Service Bulletin No. PACSB/XL/007, dated June 22, 2004. 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. To get a copy of this service information, contact Pacific Aerospace Corporation, Ltd., Hamilton Airport, Private Bag HN 3027, Hamilton, New Zealand; telephone: 64 7 843 6144; facsimile: 64 7 843 6134. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19444. Issued in Kansas City, Missouri, on January 24, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-1723 Filed 2-1-05; 8:45 am] BILLING CODE 4910-13-P
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