Airworthiness Directive · Amendment 39-17244 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category; except those airplanes identified in paragraph (c)(1), (c)(2), (c)(3), and (c)(4) of this AD.
(1) Airplanes on which Airbus Service Bulletin A300-53-6166 (Airbus Modification 13434) has been embodied in service (for Model A300 B4-600 and A300 B4-600R series airplanes).
(2) Airplanes on which Airbus Service Bulletin A300-53-0389 (Airbus Modification 13434) has been embodied in service (for Model A300 series airplanes).
(3) Airplanes on which Airbus Service Bulletin A310-53-2133 (Airbus Modification 13434) has been embodied in service (for Model A310 series airplanes).
(4) Airplanes modified by FAA Supplemental Type Certificate (STC) ST01431NY, ST00177LA-D, or ST00100NY, as applicable.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600 and A300 B4-600R, Model A300, and Model A310 series airplanes. This AD was prompted by reports of fatigue cracking in the crossbeams at the junction of the actuator beam of the lower deck cargo door. This AD requires repetitive inspections of the crossbeams of certain fuselage frames, and repair if necessary. We are issuing this AD to detect and correct cracking of the crossbeams at the junction of the actuator beam of the lower deck cargo door, which could result in failure to withstand ultimate load conditions, and consequent reduced structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(1) For airplanes on which the crossbeams at frames (FR) 22/23 and FR 61/62 have not been repaired as specified in an Airbus structural repair manual or repair approval sheet as of the effective date of this AD: Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 600 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection for cracking of the crossbeam fuselage frame stations FR 22/23 and FR 61/62, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. Repeat the inspection thereafter at intervals not to exceed 600 flight cycles until the modification specified in paragraph (i) of this AD has been done.
(i) Airbus Mandatory Service Bulletin A300-53-0390, dated January 15, 2010 (for Model A300 series airplanes).
(ii) Airbus Mandatory Service Bulletin A310-53-2134, dated January 15, 2010 (for Model A310 series airplanes).
(iii) Airbus Mandatory Service Bulletin A300-53-6168, dated January 15, 2010 (for Model A300-600 series airplanes).
(2) For airplanes on which the crossbeams at FR 22/23 and FR 61/62 have been repaired as specified in an Airbus structural repair manual or repair approval sheet as of the effective date of this AD: Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 600 flight cycles after the effective date of this AD, whichever occurs later, repair in accordance with 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).
If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair any crack using a method approved by the Manager, International Branch, ANM-116; or EASA (or its delegated agent).
Modifying the crossbeam fuselage frame stations FR 22/23 and FR 61/62, including doing rotating probe inspections for cracks of fastener holes, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, and repairing any crack using a method approved by the Manager, International Branch, ANM-116; or EASA (or its delegated agent); terminates the repetitive inspections required by paragraph (g)(1) of this AD.
(1) Airbus Service Bulletin A300-53-0389, Revision 02, dated April 27, 2011 (for Model A300 series airplanes).
(2) Airbus Service Bulletin A310-53-2133, Revision 02, dated April 27, 2011 (for Model A310 series airplanes).
(3) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 21, 2010 (for Model A300-600 series airplanes).
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.
