Airworthiness Directive · Amendment 39-15640 · Wings
Airbus Model A310 Airplanes
Superseded. A later AD replaced this one: AD 2015-02-24. Comply with the one in force.
This AD applies to Airbus Model A310 airplanes, certificated in any category, all certified models, all serial numbers; except for those where LH (left-hand) and RH (right-hand) wing MLG (main landing gear) rib 5 forward lugs have been repaired by installation of oversized interference fit bushes as per Airbus A310 Repair Instruction R572-49121, or which have had Airbus Service Bulletin A310-57-2090 (Airbus modification 13329) embodied in service.
We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD in accordance with the instructions defined in Airbus Service Bulletin A310-57A2088, dated November 6, 2006.
(1) Before the accumulation of 12,000 total flight cycles, or within 14 days after February 6, 2007 (the effective date of AD 2007-02-09), whichever occurs later: Perform a detailed visual inspection of the LH and RH wing MLG Rib 5 aft bearing forward lugs.
(2) If any crack is detected at LH and/or RH aft bearing forward lug, contact Airbus and proceed with the replacement before next flight.
(3) Repeat the inspection at intervals not exceeding 100 flight cycles.
Unless already done, before the accumulation of 12,000 total flight cycles or before the accumulation of 12,000 flight cycles on MLG Rib 5, or within 14 days after the effective date of this AD, whichever occurs latest: Perform either a detailed visual inspection (DVI) or an ultrasonic inspection of the LH and RH MLG Rib 5 aft bearing forward lug for cracks, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007. If a MLG Rib 5 has been replaced on one side only, then the RH and LH must be considered separately. Doing this inspection ends the requirements of paragraph (f) for that MLG Rib 5 only.
Note 1: The ultrasonic inspection will detect any crack at an early stage and will limit the risk of extensive repairs. This earlier crack detection is not possible with the DVI.
(1) If no crack is detected during any inspection required by paragraph (g) of this AD: Repeat the applicable inspection at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Repeat the DVI thereafter at intervals not to exceed 100 flight cycles.
(ii) Repeat the ultrasonic inspection thereafter at intervals not to exceed 825 flight cycles.
(2) Replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g)(1) of this AD for that MLG Rib 5 only.
(3) If any crack is detected during the DVI required by paragraph (g) of this AD: Before further flight, contact Airbus for replacement instructions and replace the MLG Rib 5 bushes before further flight. Repeat the applicable inspection in paragraph (g) of this AD at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Accomplishing the replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g)(1) of this AD for that MLG Rib 5 only.
(4) If any crack is detected during the ultrasonic inspection required by paragraph (g) of this AD, before further flight, accomplish the actions specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable.
(i) If any crack is not visible on MLG Rib 5: Before further flight, repair MLG Rib 5 using Airbus A310 Repair Instruction R572-49121, Issue C, dated May 2007. After embodiment of the repair instruction, no further actions are necessary as required by this AD and specified in Airbus Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007, for that MLG Rib 5 only.
(ii) If any crack is visible on MLG Rib 5: Before further flight, contact Airbus for rib replacement instructions, and replace before further flight. Repeat the applicable inspection in paragraph (g) of this AD at the time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Accomplishing the replacement of the MLG Rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG Rib 5, in accordance with the instructions defined in Airbus Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007, ends the repetitive inspections required by paragraph (g) of this AD for that MLG Rib 5 only.
Note 2: This AD differs from the MCAI and/or service information as follows: (1) Although the MCAI or service information allows flight with cracks on aft bearing forward lugs for a certain period of time, this AD requires replacing MLG Rib 5 before further flight if any crack is found. (2) Although the MCAI or service information specifies submitting an inspection report sheet to Airbus, this AD would not require that action.
