AD 96-06-07

2. Section 39.13 is amended by removing amendment 39-6861 (56 FR 1569, January 16, 1991), and by adding a new airworthiness directive (AD), amendment 39-9544, to read as follows:

Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category.

Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (e) 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.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of the cockpit frame and the adjacent fuselage structure, accomplish the following:

(a) Prior to the accumulation of 30,000 total landings, or within 6 months after February 25, 1991 (the effective date of AD 91-02-12, amendment 39-6861), whichever occurs later; and thereafter at intervals not to exceed 5,000 landings: Perform a visual inspection to detect cracks of the flight deck canopy area, in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 2, dated June 5, 1990; or Issue 3, dated April 8, 1993. Pay particular attention to the top sill joint strap, the top sill intercostal, the frame at Station 113, and the top sill boom and web. Repeat this inspection until the inspections required by paragraph (c) of this AD are accomplished. After the effective date of this AD, the inspection shall be accomplished only in accordance with Issue 3 of the alert service bulletin.

(b) If any crack is found during the inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Following accomplishment of the repair, repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 5,000 landings until the inspections required by paragraph (c) of this AD are accomplished.

(c) Perform a detailed visual inspection to detect cracks of the top sill joint strap at station 82.5, of the frame at station 113, and of the frame at station 160.5 (left-hand side only) between stringers 13 and 15; and an eddy current inspection to detect cracks of the top sill members at station 82.5. Perform these inspections in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, at the time specified in paragraph (c)(1) or (c)(2) of this AD, as applicable. Accomplishment of these inspections terminates the repetitive inspection requirement of paragraph (a) of this AD.

(1) For airplanes operating at a maximum cabin differential pressure not exceeding 7.5 pounds per square inch (psi): Perform the inspections at the later of the times specified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD. Thereafter, repeat these inspections at intervals not to exceed 5,000 landings or 7,500 hours time-in-service, whichever occurs first.

(i) Prior to the accumulation of 20,000 total landings since date of entry into service; or

(ii) Within 1,200 landings or 12 months after the effective date of this AD, whichever occurs later.

(2) For airplanes operating at a maximum cabin differential pressure greater than 7.5 psi, but not exceeding 8.2 psi, including those airplanes having incorporated British Aerospace Airbus Limited Modification PM3187: Perform the inspections at the later of the times specified in paragraphs (c)(2)(i) and (c)(2)(ii) of this AD. Thereafter, repeat these inspections at intervals not to exceed 3,500 landings or 5,250 hours time-in-service, whichever occurs first.

(i) Prior to the accumulation of 14,000 total landings since date of entry into service; or

(ii) Within 800 landings or 12 months after the effective date of this AD, whichever occurs later.

Note 2: British Aerospace Airbus Limited Modification PM3187 increases the cabin differential pressure from the normal 7.5 psi to 8.2 psi. If Modification PM3187 has been incorporated on the airplane, that airplane is considered to be subject to the requirements of paragraph (c)(2) of this AD.

(d) If any crack is found during any inspection required by paragraph (c) of this AD, prior to further flight, accomplish the requirements of paragraph (d)(1), (d)(2), or (d)(3), as applicable.

(1) For cracking of the joint strap, doubler, or angle at the sill joint at station 82.5: Replace the cracked part with a new part in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993.

(2) For cracking of the frame at station 113: Repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.

(3) For cracking of the frame at station 160.5: Repair in accordance with the Structural Repair Manual, as specified in British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993.

(e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(g) The inspections shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 2, dated June 5, 1990; or British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993. The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 2, dated June 5, 1990, was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of February 25, 1991 (56 FR 1569, January 16, 1991). The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from British Aerospace, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(h) This amendment becomes effective on April 22, 1996.

Issued in Renton, Washington, on March 12, 1996. James V. Devany, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.