AD 2007-11-11

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

The term “service information,” as used in this AD, means Airbus All Operators Telex (AOT) A320-32A1273, Revision 01, dated May 6, 2004; or the Accomplishment Instructions of Airbus Service Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May 26, 2005. After the effective date of this AD, only Airbus Service Bulletin A320-32A1273, Revision 02, may be used.

Note 1: Airbus AOT A320-32A1273, Revision 01, and Airbus Service Bulletin A320-32A1273, Revision 02, refer to Messier-Dowty Service Bulletin 201-32-43, Revision 1, dated May 1, 2005; and Messier-Dowty Service Bulletin 200-32-286, Revision 1, dated March 1, 2005, as additional sources of service information for accomplishing the detailed inspections and magnetic particle inspections (MPI).

For all airplanes: Within 30 days after June 23, 2004 (the effective date of AD 2004-11-13), do a one-time general visual inspection to determine the S/N of both MLG sliding tubes, in accordance with the service information. Instead of inspecting the MLG sliding tubes, reviewing the airplane maintenance records is acceptable if the S/N of the MLG sliding tubes can be positively determined from that review.

(1) If the S/N of the MLG sliding tube is not listed in the service information: No further action is required by this paragraph for that sliding tube.

(2) If the S/N of the MLG sliding tube is listed in the service information: Do the actions in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable.

(i) For any MLG not inspected before June 23, 2004: Before further flight, do a detailed inspection of the MLG for cracking in accordance with the service information.

(A) If no cracking is found in any MLG sliding tube: Repeat the detailed inspection thereafter at intervals not to exceed 10 days, until the MLG replacement specified by paragraph (g)(2)(i)(B), (h), or (i) of this AD has been accomplished.

(B) If any cracking is found in any MLG sliding tube: Before further flight replace the part with a new or serviceable part in accordance with a method approved by either the FAA or the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent). Chapter 32 of the Airbus A318/A319/A320/A321 Aircraft Maintenance Manual (AMM) is one approved method. Installing an MLG sliding tube having an S/N that is not listed in the service information terminates the repetitive inspections required by paragraph (h) of this AD for that MLG sliding tube only.

(ii) For any MLG that has been inspected before June 23, 2004: Within 10 days after that inspection, do the detailed inspection required by paragraph (g)(2)(i) of this AD.

For any airplane equipped with any MLG having a sliding tube installed that is identified with a S/N listed in the service information: Within 500 flight cycles after the effective date of this AD, perform a detailed inspection and an MPI of the MLG sliding tube for cracking in accordance with the service information. Repeat these inspections thereafter at intervals not to exceed 2,500 flight cycles or 21 months, whichever occurs earlier, until paragraph (i) of this AD has been accomplished. If any cracking is discovered during any inspection required by this paragraph, before further flight, replace the cracked sliding tube with a new or serviceable sliding tube in accordance with the service information. Replacing the MLG sliding tube with a sliding tube having a S/N not listed in the service information terminates the repetitive inspection requirements of this paragraph and paragraph (g)(2)(i)(A) of this AD for that sliding tube only.

(i) Within 41 months after the effective date of this AD, replace all MLG shock absorbers equipped with sliding tubes having S/Ns listed in the service information with new or serviceable MLG shock absorbers equipped with sliding tubes having S/Ns not listed in the service information, using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). Airbus A318/A319/A320/A321 AMM 32-11-13, page block 401, is one approved method. Replacing the MLG shock absorbers in accordance with this paragraph terminates all repetitive inspections required by this AD.

The service information has instructions to send any cracked part to Messier-Dowty. This AD does not include such a requirement.

Prepare a report of any crack found during any inspection required by paragraph (g) or (h) of this AD. Submit the report to Airbus Customer Services, Engineering and Technical Support, Attention: M.Y. Quimiou, SEE33, fax +33+ (0) 5.6193.32.73, at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. The report must include the MLG sliding tube P/N and S/N, date of inspection, a description of any cracking found, the airplane serial number, and the number of flight cycles on the MLG at the time of inspection. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.

(1) For any inspection done after June 23, 2004, but before the effective date of this AD: Within 30 days after the inspection or 30 days after the effective date of this AD, whichever comes first.

(2) For any inspection done after the effective date of this AD: Within 30 days after the inspection.

As of the effective date of this AD, no person may install, on any airplane, any sliding tube, or MLG shock absorber having a sliding tube installed, if the sliding tube has a S/N identified in the service information, unless the sliding tube has been inspected, and any applicable corrective actions have been done, in accordance with paragraph (g)(2)(i), (h), or (i) of this AD.