Airworthiness Directive · Amendment 39-18604 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2022-25-03. Comply with the one in force.
This AD applies to Airbus Model A300 B4-603, A300 B4-605R, A300 B4-622R, A310-304, A310-324, and A310-325 airplanes; certificated in any category; all manufacturer serial numbers (MSNs) in post-modification (MOD) 06924 configuration, except MSNs 464, 477, 479, 481, 482, 483, 484, and 488.
Note 1 to paragraph (c) of this AD: MSNs 464, 477, 479, 481, 482, 483, 484 and 488 partially embodied MOD 06924 by means of modification proposal D05902.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-603, B4-605R, and B4-622R airplanes; and Model A310-304, -324, and -325 airplanes. This AD was prompted by a report of a crack found on door frame (FR) 73A between stringers 24 and 25. This AD requires inspections around the rivet heads of the seal retainer run-out holes at certain frames and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the door frame, which could result in reduced structural integrity of the airplane.
At the later of the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a high frequency eddy current (HFEC) inspection for any crack around the rivet heads of the seal retainer run-out holes at FR 56A, FR 57A, and FR 73A, left-hand (LH) and right-hand (RH) sides on Model A300-600 airplanes; and at FR 73A, LH and RH sides on Model A310 airplanes; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2138, dated May 28, 2014; or Airbus Service Bulletin A300-53-6175, dated May 28, 2014; as applicable. Repeat the HFEC inspection thereafter at intervals not to exceed 7,500 flight cycles.
(1) Before the accumulation of 32,000 total flight cycles.
(2) Within 36 months after the effective date of this AD, or before the accumulation of 36,000 total flight cycles, whichever occurs first.
If any crack is found during any inspection required by paragraph (g) of this AD, repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
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.
