2009-18-15: Landing gear

2009-18-15 Airbus: Amendment 39-16011. Docket No. FAA-2009-0292; Directorate Identifier 2008-NM-011-AD. \n\nEffective Date \n\n\t(a) This AD becomes effective October 27, 2009. \n\nAffected ADs \n\n\t(b) This AD supersedes AD 87-16-06. \n\nApplicability \n\n\t(c) This AD applies to all Airbus Model A300, A310, and A300-600 series airplanes, certificated in any category. \n\nSubject \n\n\t(d) Air Transport Association (ATA) of America Code 32: Landing Gear. \n\nUnsafe Condition \n\n\t(e) This AD results from revisions to the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to include new or more restrictive life limits and/or replacements. We are issuing this AD to ensure the continued structural integrity of these airplanes. \n\nCompliance \n\n\t(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. \n\n\tNote 1: This AD requires revisions to certain operator maintenance documents to include new replacements. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these replacements, the operator may not be able to accomplish the replacements described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (l) of this AD. The request should include a description of changes to the required replacements that will ensure the continued operational safety of the airplane. \n\nRestatement of the Requirements of AD 87-16-06 \n\n\t(g) For Model A300 and A310 series airplanes: Prior to the accumulation of 16,000 landings, or within the next 2,000 landings after September 3, 1987 (the effective date of AD 87-16-06), whichever occurs later, replace the nose landing gear drag strut upper attachment pin in accordance withAirbus Service Bulletin A300-32-374, Revision 1, dated July 15, 1986 (applicable to Model A300 airplanes); or A310-32-2023, Revision 2, dated November 14, 1986 (applicable to Model A310 airplanes). \n\nNew Requirements of This AD \n\nALS Revision \n\n\t(h) For Model A300, A310, and A300-600 series airplanes: Within 3 months after the effective date of this AD, revise the ALS of the ICA to incorporate the applicable document listed in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Accomplishing the actions specified in the applicable document satisfies the requirements of paragraph A. of AD 84-02-04, amendment 39-4795. \n\t(1) For Model A300 series airplanes: Incorporate the applicable document listed in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. \n\t(i) Section 05-10-00, Revision 28, dated February 27, 1998, of Chapter 05, "Service Life Limits and Maintenance Checks,'' of the Airbus A300 Aircraft Maintenance Manual, except that the parts listed in Table 1 of this AD are subject to the life limits defined in the document listed in paragraph (h)(1)(ii) of this AD. \n\t(ii) "Sub-part 1-2: Life Limits,'' and "Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, "Safe Life Airworthiness Limitation Items,'' dated September 6, 2007, of the Airbus A300 ALS. \n\n\tTable 1--Parts Subject to the Life Limits Specified in the Document Identified in Paragraph (h)(1)(ii) of This AD\n\n\n\nPart Number (P/N)\nPart Name\nP/N C61643-2, P/N C61643-4, P/N C61643-5\nMain landing gear (MLG) shock absorber end fitting\nP/N A32210001205xx\nNose landing gear (NLG) pintle pin\nP/N C62037-1 \nNLG shock absorber bottom \nP/N 196-0328-501\nCross beam (Pratt & Whitney forward engine mount)\n \n\t(2) For Model A310 series airplanes: Incorporate "Sub-part 1- 2: Life Limits,'' and "Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, "Safe Life Airworthiness Limitation Items,'' dated December 21, 2006, of the Airbus A310 ALS. \n\t(3) For Model A300-600 series airplanes: Incorporate "Sub-part 1-2: Life Limits,'' and "Sub-part 1-3: Demonstrated Fatigue Lives'' of Part 1, "Safe Life Airworthiness Limitation Items,'' dated December 21, 2006, of the Airbus A300-600 ALS. \n\nInitial Compliance Times and Repetitive Inspections \n\n\t(i) Do the replacement at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, except as provided by paragraph (j) of this AD. The replacement must be done thereafter within the interval specified in the applicable document identified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. \n\t(1) For any life limitation/task that has been complied with before the effective date of this AD in accordance with the applicable document listed in paragraph (h)(1), (h)(2), or (h)(3) of this AD, or in accordance with paragraph (g) of this AD, use the last accomplishment of each limitation/task as a starting point for accomplishing each corresponding limitation/task required by this AD. \n\t(2) For any life limitation/task that has not been complied withbefore the effective date of this AD in accordance with the applicable document listed in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, or in accordance with paragraph (g) of this AD, the initial compliance time starts from the date of initial entry into service as defined in the applicable document. \n\nSpecial Compliance Times \n\n\t(j) For any airplane on which the history of accumulated landings is partial or unknown, or where the history of application details (airplane type, model, weight variant, etc.) is partial or unknown, with or without using the information in Airbus Service Information Letter 32-118, Revision 02, dated October 24, 2007: Parts listed in Figure 1 of this AD must be replaced at the associated compliance time. The replacement must be done thereafter at the interval specified in the applicable document(s) specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. \n\n\tNote 2: Airbus Service Information Letter 32-118, Revision 02, dated October 24, 2007,provides operators with guidance on the means to assign a conservative calculated life to parts whose history of accumulated landings is partial or unknown; and to select the limitations applicable to parts whose history of application details (aircraft type, aircraft model, weight variant, etc.) is partial or unknown. \n\n\n\n\n\n\n\n\n\n\n\n\n(1) When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut's removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time in service during the period between the removal and reinstallation.\n(2) If the removal / installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months after the effective date of this AD.\n\n\nAlternative Intervals or Limits \n\n\t(k) Except as provided by paragraph (l) of this AD, after accomplishing the actions specified in paragraphs (h), (i), and (j) of this AD, no alternative replacements, replacement intervals, or limitations may be used. \n\nAlternative Methods of Compliance (AMOCs) \n\n\t(l)(1) The Manager, ANM-116, International Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Stafford, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. \n\t(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. \n\nRelated Information \n\n\t(m) European Aviation Safety Agency (EASA) Airworthiness Directive 2007-0293, dated November 29, 2007, also addresses the subject of this AD. \n\nMaterial Incorporated by Reference \n\n\t(n) You must use the service information contained in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. \n\n\tTable 2--Material Incorporated by Reference\n\n\n\nDocument\nRevision\nDate\nSection 05-10-00 of Chapter 05, "Service Life Limits and Maintenance Checks, " of the Airbus A300 Aircraft Maintenance Manual.\n28\nFebruary 27, 1998\nAirbus A300 Airworthiness Limitations Section, ALS Part 1, "Safe Life Airworthiness Limitations Items"\nOriginal\nSeptember 6, 2007\nAirbus A300-600 Airworthiness Limitations Section, ALS Part 1, "Safe Life Airworthiness Limitations Items"\nOriginal \nDecember 21, 2006\nAirbus A310 Airworthiness Limitations Section, ALS Part 1, "Safe Life Airworthiness Limitation Items"\nOriginal\nDecember 21, 2006\nAirbus Service Bulletin A300-32-374\n1\nJuly 15, 1986\nAirbus Service Bulletin A310-32-2023\n2\nNovember 14, 1986\n\n\n\n\tAirbus Service Bulletin A300-32-374, Revision 1, dated July 15, 1986, has the following effective pages: \n\n\nPage No. \nRevision level shown on page \nDate shown on page \n1, 5-9 \n2 \nNovember 14, 1986 \n2, 4 \n1 \nJuly 15, 1986 \n3 \nOriginal \nApril 16, 1986 \n\n\tChapter 05 of Airbus A300 Aircraft Maintenance Manual has the following effective pages: \n\n\tList of Effective Pages\n\n\nPage Title/Description \nPage Number(s) \nRevision Number \nDate Shown on Page(s) \nAMM Title Page \nNone shown \nNone shown* \nFebruary 27, 1998 \nChapter 05 Record of Revisions \n1-2 \n28 \nFebruary 27, 1998 \nChapter 05 Effective Pages \n1-4 \nNone shown* \nFebruary 27, 1998 \nChapter 05 Table of Contents \n1-4\nNone shown* \nFebruary 27, 1998\nSection 05-10-00 \n1\nNone shown* \nFebruary 27, 1998\n\n* The revisionnumber is indicated only in the Record of Revisions section of Chapter 05.\n\n\t(The List of Effective Pages (LOEP) for Chapter 05 of the Airbus A300 Aircraft Maintenance Manual contains the following errors: Transmittal Letter page, page 4 of the LOEP and Table of Contents sections, page 2 of Subsection 05-00-01, page 1 of Subsection 05-11- 11, and Subsection 05-10-00, are not listed in the LOEP; and the LOEP also does not specify a date for the Record of Revisions page. In addition, the LOEP identifies three pages for Subsection 05-11- 00, Configuration 5; however, only one page exists. The LOEP identifies three pages for Subsection 05-11-00, Configuration 9; however, those pages do not exist.) \n\t(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) For service information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: [email protected]; Internet http://www.airbus.com. \n\t(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. \n\t(4) You may also review copies of the 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/code_of_federal_regulations/ ibr_locations.html.