AD 2014-12-06 Airworthiness Directives; Airbus Airplanes

Models named: A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R, A300 F4-605R, F4-622R, A300 C4-605R Variant F, A310-203. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD, certificated in any category, all certified models, all manufacturer serial numbers on which Airbus Modification 05438 has been embodied in production, except those on which Modification 12046 has been embodied in production. (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (2) Airbus Model A300 B4-605R and B4-622R airplanes. (3) Airbus Model A300 F4-605R and F4-622R airplanes. (4) Airbus Model A300 C4-605R Variant F airplanes. (5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.

Comply with this AD within the compliance times specified, unless already done.

(1) Within the compliance time identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD, as applicable, do an ultrasonic inspection or detailed inspection of the aft cargo door sill beam external area for cracking, in accordance with Airbus Alert Operators Transmission (AOT) A53W005-14, dated April 22, 2014. Repeat the inspection thereafter at intervals not to exceed 275 flight cycles. (i) For airplanes that have accumulated 30,000 flight cycles or more since the airplane's first flight as of the effective date of this AD: Within 50 flight cycles after the effective date of this AD. (ii) For airplanes that have accumulated 18,000 flight cycles or more, but less than 30,000 flight cycles since the airplane's first flight as of the effective date of this AD: Within 275 flight cycles after the effective date of this AD. (iii) For airplanes that have accumulated less than 18,000 flight cycles since the airplane's first flight as of the effective date of this AD: Before exceeding 18,275 flight cycles since the airplane's first flight. (2) If any crack is found during any inspection required by paragraph (g)(1) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder (DAH) with EASA design organization approval).

This AD was prompted by reports of fatigue cracks on the cargo door sill beam, lock fitting, and torsion box plate. We are issuing this AD to detect and correct fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, which could result in the loss of the door locking function and subsequently, complete loss of the cargo door in flight with the risk of rapid decompression.

None.