Airworthiness Directive · Amendment 39-15995 · Flight controls
Airbus Model A318, A319, A320, and A321 Series Airplanes
Superseded. A later AD replaced this one: AD 2011-19-04. Comply with the one in force.
This AD applies to Airbus Model A318-111, -112, -121, and -122; A319-111, -112, -113, -114, -115, -131, -132, and -133; A320-111, -211, -212, -214, -231, -232, -233; and A321-111, -112, -131, -211, -212, -213, -231, and -232 series airplanes; certificated in any category; all manufacturer serial numbers.
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, after the accumulation of 10,000 total flight cycles since first flight of the airplane, do the following actions.
(1) Not before the accumulation of 10,000 total flight cycles since first flight of the airplane, and at the later of the times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD: Inspect both the left-hand and right-hand inboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus All Operators Telex (AOT) A320-27A1186, Revision 04, dated April 3, 2009.
(i) Within 1,500 flight cycles or 200 days after the effective date of this AD, whichever occurs first.
(ii) Within 1,500 flight cycles or 200 days after accumulating 10,000 total flight cycles since first flight of the airplane, whichever occurs first.
(2) Not before the accumulation of 10,000 total flight cycles since first flight of the airplane, and at the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD: Inspect both the left-hand and right-hand outboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009.
(i) Within 3,000 flight cycles or 400 days after the effective date of this AD, whichever occurs first.
(ii) Within 3,000 flight cycles or 400 days after accumulating 10,000 total flight cycles since first flight of the airplane, whichever occurs first.
(3) If any cracking is found during any inspection required by this AD, before further flight, accomplish all applicable corrective actions in accordance with the instructions of Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009.
(4) Submit a report of the findings of the inspection required by paragraphs (f)(1) and (f)(2) of this AD to Airbus in accordance with the instructions of Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009; at the applicable time specified in paragraph (f)(4)(i) or (f)(4)(ii) of this AD.
(i) If the inspection was done after the effective date of this AD: Submit the report within 40 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 40 days after the effective date of this AD.
(5) As of the effective date of this AD, no person may install on any airplane an elevator servo-control rod eye-end unless it has been inspected in accordance with the instructions of Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009.
(6) Actions done before the effective date of this AD in accordance with Airbus AOT A320-27A1186, dated June 23, 2008; Revision 01, dated August 11, 2008; Revision 02, dated March 30, 2009; or Revision 03, dated April 1, 2009; are acceptable for compliance with the corresponding actions required by this AD.
Note 1: 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
