Airworthiness Directive · Amendment 39-11862 · Airbus Industrie Model A300 B2 and B4 Series Airplanes
Airbus Industrie Model A300 B2 and B4 Series Airplanes
Model A300 B2 and B4 series airplanes, manufacturer serial numbers 003 through 156 inclusive; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300 B2 and B4 series airplanes, that currently requires inspection of the fuselage longitudinal lap joints and circumferential joints, and of the stringers and doublers for bonding delamination and cracks; and repairs, as necessary. This amendment requires expansions of certain inspection areas; revisions of certain inspection thresholds or intervals; changes in references to inspection methods; and the addition of a modification to certain longitudinal lap joints. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent delamination and cracking of the fuselage, which could result in rapid decompression of the airplane.
To prevent rapid decompression of the airplane due to bonding delamination and cracking of the fuselage, accomplish the following:
(a) Except as required by paragraph (d) of this AD: Prior to the threshold limits specified in Table 1 of Airbus Service Bulletin A300-53-148, Revision 6, dated October 10, 1984, or within 6 months after May 13, 1985 (the effective date of AD 85-07-09), whichever occurs later, inspect the fuselage longitudinal lap joints and circumferential joints for bonding delamination, in accordance with the service bulletin.
(1) If no delamination is detected, repeat these inspections in accordance with the schedule shown in Table 1 of the service bulletin.
(2) If delamination is detected during any inspection, prior to further flight, perform the actions indicated in Figure 3, “Follow-up Action,” of the service bulletin.
(b) Except as required by paragraph (d) of this AD: Prior to the threshold limits specified in Figure 1, “Inspection Program,” of Airbus Service Bulletin A300-53-178, Revision 4, dated October 10, 1984, or within 6 months after May 13, 1985, whichever occurs later, visually inspect for corrosion and cracks, and repair if necessary, the bonded longitudinal lap joints and circumferential joints specified in Figure 1 of the service bulletin, in accordance with the service bulletin. Repeat the inspections thereafter in accordance with the schedule shown in Figure 1 of the service bulletin.
(c) Except as required by paragraph (d) of this AD: Prior to the threshold limits specified in Figure 1, “Inspection Frequency,” of Airbus Service Bulletin A300-53-149, Revision 6, dated October 10, 1984, or within 6 months after May 13, 1985, whichever occurs later, inspect for debonding, and repair, if necessary, bonded stringers and bonded doublers in the area between frame 1 and frame 18 and between frame 40 and frame 80 on all airplanes up to and including serial number 156, and in the area between frame 18 and frame 40 on all airplanes up to and including serial number 104. Repeat the inspections thereafter at intervals specified in Figure 1 of the service bulletin, except for repaired areas. The inspections of stringers are divided into three areas, as indicated in Figure 2 of the service bulletin, with the following options:
(1) Inspection in Area 1 is not required if Modification No. 2904, described in Airbus Service Bulletin A300-53-146, dated November 28, 1980, has been incorporated.
(2) Preventive riveting of stringers located in Area 2 in accordance with Airbus Service Bulletin A300-53-197, dated October 10, 1984, allows for an extension of the interval of subsequent repetitive inspections to the interval required for Area 3.
(d) After the effective date of this new AD, only the following service bulletin revisions shall be used for compliance thresholds and intervals and for accomplishment instructions for the actions required by this AD, as specified in paragraphs (d)(1), (d)(2), and (d)(3) of this AD. For any airplane that, as of the effective date of this AD, has exceeded a revised threshold or interval for any specified action, accomplish that action within 6 months after the effective date of this AD.
(1) Airbus Service Bulletin A300-53-148, Revision 11, dated September 8, 1998, shall be used for the requirements of paragraph (a) of this AD. For corrective actions and follow-on inspections, Figure 5, “Follow-up Action,” of the service bulletin shall be used.
(2) Airbus Service Bulletin A300-53-178, Revision 10, dated September 8, 1998, shall be used for the requirements of paragraph (b) of this AD. For inspection thresholds and intervals, Paragraph C., “Description,” of the service bulletin shall be used.
(3) Airbus Service Bulletin A300-53-149, Revision 14, including Appendix 01, dated September 8, 1998, shall be used for the requirements of paragraph (c) of this AD. For inspection thresholds and intervals, Figure 1, Sheet 1, “Inspection Frequency,” of the service bulletin shall be used.
(e) Within 60 months after the effective date of this AD, modify the bonded longitudinal lap joints in accordance with Airbus Service Bulletin A300-53-0209, Revision 10, dated July 5, 1999. Accomplishment of the modification terminates the repetitive inspections required by paragraph (a) of this AD for stringers 29 and 35 in section 18 only.
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.
