Airworthiness Directive · Amendment 39-14986 · Airbus Model A318, A319, A320 and A321 Airplanes
Airbus Model A318, A319, A320 and A321 Airplanes
This AD applies to Airbus Model A318-111 and -112; A319-111, -112, -113, -114, and -115; A320-111, -211, -212, and -214; and A321-111, -112, -211, -212, and -213 airplanes; certificated in any category; all serial numbers, which have CFM International CFM56-5A or CFM56-5B series engines installed.
We are adopting a new 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.
(1) As of the effective date of this AD:
(i) Any maintenance on the engine mounts must be performed in accordance with correct instructions as identified in the Airbus All Operators Telex (AOT) A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich All Operators Letter (AOL) CFM56-074, Revision 1, dated February 1, 2007; and
(ii) Any forward engine mount support assemblies fitted on an engine which is used as replacement must be fitted in accordance with correct instructions as identified in Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich AOL CFM56-074, Revision 1, dated February 1, 2007.
(2) For aircraft on which any forward engine mount support assembly has been installed or maintained since May 2006 using erroneous torque values given in the maintenance data identified in paragraph 1. of the Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007, or where the use of correct torque values cannot be established: Within 20 days after the effective date of this AD, accomplish the actions in paragraphs (f)(2)(i), (f)(2)(ii), (f)(2)(iii), and (f)(2)(iv) of this AD, as applicable, in accordance with the instructions of Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007. Aircraft on which no engine removal has been performed since aircraft delivery are not affected by this paragraph. The alternative procedure given in paragraph 4.2.3 of the AOT is acceptable, provided that the nominal torque values specified in paragraphs 4.2.1 and 4.2.2 are restored within 120 flight cycles after accomplishing paragraph 4.2.3 of the AOT.
(i) Remove and inspect the following forward engine mount bolts: 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85).
(ii) If any bolts, 77710-5H6 (AMM item 90), are found broken during the above inspection, before further flight, replace the affected forward engine mount support assembly (AMM item 75).
(iii) Replace bolts, 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85), with new items and torque them to the correct value.
(iv) Re-torque 77458-7H21 bolts (AMM item 95) and NAS2816C7H (AMM item 50) to the correct value.
(3) Actions done before the effective date of this AD in accordance with Airbus AOT A320-71A1042, dated February 5, 2007, are acceptable for compliance with the corresponding provisions of paragraph (f)(2) of this AD.
(4) Within 7 days after the inspection, report all findings to Airbus Customer Services, Engineering and Technical Support, Attention: Mr. J-P Pourtau SEE11; telephone +33 (0) 5 62 11 04 48; fax +33 (0) 5 61 93 36 14.
Note: This AD differs from the MCAI and/ or service information as follows: No differences.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
