AD 2009-18-15

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Note 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.

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 with Airbus 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).

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.

(1) For Model A300 series airplanes: Incorporate the applicable document listed in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.

(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.

(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.

(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.

(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.

(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.

(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.

(2) For any life limitation/task that has not been complied with before 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.

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.

Note 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.

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.