Airworthiness Directive · Amendment 39-16675 · Nacelles/pylons
Airbus Model A340-200 and -300 Series Airplanes
This AD applies to Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; all serial numbers except those on which Airbus Modification 49203 has been incorporated in production.
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:
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the later of the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD, except as provided by paragraph (h) of this AD: Perform an ultrasonic inspection of pylon pyramid attachment areas at the aft end of the lower arms between Rib 1 and Rib 2 without fastener removal (2 fastener locations per pylon), in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A340-54-4010, dated July 21, 2008.
(1) Before the accumulation of the applicable total flight cycles or total flight hours, whichever occurs first, specified in table 1 of this AD.
(2) Within 90 days after the effective date of this AD.
| Weight variant | Total flight cycles | Total flight hours |
|---|---|---|
| 000 through 004 | 13,000 | 60,000 |
| 020, 021, 023 through 026, 028 through 030, Pre 49203 | 11,470 | 77,400 |
| 027 | 11,000 | 30,000 |
(h) For airplanes belonging to weight variant 000 through 004 inspected before the effective date of this AD in accordance with Airworthiness Limitations Items (ALI) Task 545104-01-01, as described in Airbus A340 Airworthiness Limitations Items Document Ref: AI/SE-M4/95A.0051/97, Issue 10, dated February 1, 2007: Perform the inspection required in paragraph (g) of this AD at the compliance times specified in paragraphs (h)(1) and (h)(2) of this AD, whichever occurs later.
(1) Within 90 days after the effective date of this AD.
(2) Within 2,680 flight cycles or 19,200 flight hours, whichever occurs first, after the most recent rototest inspection done in accordance with ALI task 545104-01-01, but not to exceed the accumulation of 15,280 total flight cycles or 76,400 total flight hours, whichever occurs first.
(i) If no cracking is detected during any inspection required by paragraph (g) of this AD: Repeat the inspection required in paragraph (g) of this AD thereafter at intervals not to exceed the earlier of the applicable flight cycles or flight hours interval specified in table 2 of this AD.
| Weight variant | Flight cycles | Flight hours |
|---|---|---|
| 000 through 004 | 1,900 | 9,500 |
| 020, 021, 023 through 026, 028 through 030, Pre 49203 | 1,700 | 8,500 |
| 027 | 1,700 | 8,500 |
(j) If any crack is detected during any inspection required by this AD: Before further flight, repair the cracking using a method approved by either the Manager, International Branch, ANM 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
Note 1: This AD differs from the MCAI and/or service information as follows: No differences.
