2013-10-04: Engine Exhaust

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD) AD 82-16-05 R1, Amendment 39-5278 (51 FR 11707, April 7, 1986) and adding the following new AD: 2013-10-04 Piper Aircraft, Ltd.: Amendment 39-17457; Docket No. FAA- 2012-0983; Directorate Identifier 2012-CE-001-AD. (a) Effective Date This AD is effective July 17, 2013. (b) Affected ADs This AD supersedes AD 82-16-05 R1, Amendment 39-5278 (51 FR 11707, April 7, 1986). (c) Applicability This AD applies to turbocharged Piper Aircraft, Inc. Models PA- 31, PA-31-325, and PA-31-350 airplanes, all serial numbers, certificated in any category.(d) Subject Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 78, Engine Exhaust. (e) Unsafe Condition This AD was prompted by the forced landings of aircraft due to exhaust system failures between recurring detailed inspections. We are issuing this AD to prevent the possibility of an in-flight powerplant fire due to an exhaust system failure. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Visual Inspection (1) Within the next 60 hours time-in-service (TIS) after July 17, 2013 (the effective date of this AD) or within the next 6 months after July 17, 2013 (the effective date of this AD), whichever occurs first, and repetitively thereafter at intervals not to exceed 60 hours TIS or 6 months, whichever occurs first, perform the inspections listed in table 1 of paragraph (g) of this AD upon the parts listed in the same table. Note 1 to paragraph (g)(1) ofthis AD: Inspection procedure references can be found in Section 2, Visual Inspection, Chapter 5, Nondestructive Inspection (NDI), FAA Advisory Circular 43.13-1 B, Change 1, dated September 27, 2001, Acceptable Methods, Techniques, And Practices--Aircraft Inspection and Repair (http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/0/99C827DB9BAAC81B86256B4500596C4E?OpenDocument&Highlight=ac43.13-1b). (2) Aircraft equipped with Supplemental Type Certificate (STC) SA240CH heat exchanger will not have all of the parts referenced in table 1 of paragraph (g). (Information on STC SA240CH may be found at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/30C512E870BE421D86257297005B6822?OpenDocument&Highlight=sa240ch.) The heat exchanger replaces some of those parts; therefore, this AD requires the visual inspection on only the remaining parts listed in table 1 of paragraph (g) of this AD after installation of STC SA240CH. Airplanes modified inaccordance with STC SA240CH will not require an Alternative Method of Compliance if the corrective actions in this AD are complied with. [[Page 35114]] Table 1 of Paragraph (g)--Recurring 60-Hour Inspections for Lycoming and Piper Exhaust System Parts -------------------------------------------------------------------------------------------------------------------------------------------------------- -------------------------------------------------------------------------------------------------------------------------------------------------------- Product/part nomenclature Make.................. Model/part number Inspect with light and mirror or other method capable of achieving an equivalent visual resolution: -------------------------------------------------------------------------------------------------------------------------------------------------------- Airplane........................... Piper................. PA-31................. PA-31-325............ PA-31-350............ ..................... Engine............................. Lycoming.............. TIO-540-A1A, -A1B, - TIO-540-A2C (wide TIO-540-J2B and -J2BD ..................... A2A, -A2B and -A2C cylinder flange; and LTIO-540-J2B and (standard cylinder aka, wide deck) and - -J2BD. flange; aka, narrow F2BD, and LTIO-540- deck). F2BD. Pipe, exhaust, right intermediate.. Lycoming.............. LW-15850.............. LW-15850............. LW-15849............. bulges, cracks and exhaust leak stains. Pipe, exhaust, right rear, Lycoming.............. LW-16792.............. LW-16792............. LW-16621............. bulges, cracks and intermediate. exhaust leak stains. Pipe, exhaust, right rear.......... Lycoming.............. LW-16793.............. LW-16793............. LW-16620............. bulges, cracks and exhaust leak stains. Pipe, exhaust, left, intermediate.. Lycoming.............. LW-15849.............. LW-15849............. LW-15849............. bulges, cracks and exhaust leak stains. Pipe, exhaust, left rear, Lycoming.............. LW-16789.............. LW-16789............. LW-16696............. bulges, cracks and intermediate. exhaust leak stains. Pipe, exhaust, left rear........... Lycoming.............. LW-16790.............. LW-16790............. LW-16697............. bulges, cracks and exhaust leak stains. Tail pipe assembly, bottom......... Piper................. 40310-09.............. 40310-09............. 40310-09............. bulges, cracks and exhaust leak stains. Tail pipe assembly, top............ Piper................. 40310-08 or 40310-10.. 40310-08 or 40310-10. 40319-10............. bulges, cracks and exhaust leak stains. v-band coupling.................... Lycoming.............. LW-12093-5............ LW-12093-5........... LW12093-5............ cracks and exhaust leak stains. v-band coupling.................... Piper................. 555-511 or 557-584.... 555-511 or 557-584... 555-366 or 557-369... cracks and exhaust leak stains. -------------------------------------------------------------------------------------------------------------------------------------------------------- (h) Corrective Actions (1) If any damage is found as a result of the inspections required in paragraph (g) of this AD, before further flight, do the following corrective actions: (i) Replace v-band couplings exhibiting cracks and/or exhaust leak stains with airworthy and replacement v-band couplings following the applicable instructions contained in Piper Aircraft Corporation Service Bulletin No. 644E, dated May 9, 2012, and/or Lycoming Service Instruction No. 1238B, dated January 6, 2010. (ii) Replace exhaust system parts exhibiting bulges, cracks and/ or exhaust leak stains with airworthy parts in accordance with Lycoming Service Information 1320, dated March 7, 1975, and Lycoming Service Information 1391, dated October 5, 1979, as applicable. Note 2 to paragraph (h) of this AD: During installation, we recommend not opening the v-band coupling more than the MINIMUM diameter necessary to clear coupled flanges. It is recommended to replace any locknuts and/or mating couplings with airworthy parts when locknuts do not exhibit a prevailing torque when installed. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (j) Related Information (1) For more information about this AD, contact Gary Wechsler, Aerospace Engineer, Atlanta ACO, FAA, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474-5575; fax: (404) 474-5606; email: gary.wechsler@faa.gov. (2) Section 2, Visual Inspection, Chapter 5, Nondestructive Inspection (NDI), FAA Advisory Circular 43.13-1 B, Change 1, dated September 27, 2001, Acceptable Methods, Techniques, And Practices-- Aircraft Inspection and Repair may be found at http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/0/99C827DB9BAAC81B86256B4500596C4E?OpenDocument&Highlight=ac43.13-1b. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise: (i) Piper Aircraft Corporation Service Bulletin No. 644E, dated May 9, 2012; (ii) Lycoming Service Instruction No. 1238B, dated January 6, 2010; (iii) Lycoming Service Instruction 1320, dated March 7, 1975; and (iv) Lycoming Service Instruction 1391, dated October 5, 1979. (3) For obtaining service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567-4361; fax: (772) 978-6573; Internet: www.piper.com/home/pages/Publications.cfm. (4) You may view this service information at FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. (5) You may view this service information that is incorporated by reference 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/cfr/ibr-locations.html.