95-15-09 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-9312. Docket 94-NM-185-AD.
Applicability: Model BAC 1-11-200 and -400 series airplanes on which British Aerospace Modifications PM5445 and PM5713 have not been installed, 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 use the authority provided in paragraph (h) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To detect and prevent fatigue-related cracking in fuselage frames at stations 178 and 213.5 in the vicinity of the passenger door at floor level, which could result in reduced structural integrity of the fuselage pressure vessel and possible decompression of the pressurized cabin, accomplish the following:
(a) For airplanes unrepaired or not reinforced by repair on frames 178 and 213.5, in the area between stringers 25L and 27L: Accomplish paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD, in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
(1) Perform the initial inspection prior to the compliance time specified in paragraph 2.1 of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later. Repeat the inspection thereafter at intervals specified in paragraph 2.1 of the Accomplishment Instructions of the alert service bulletin.
(2) If any discrepancy is found during any inspection required by paragraph (a)(1) of this AD, prior to further flight, correct the discrepancy in accordance with paragraph 2.1 of the Accomplishment Instructions of the alert service bulletin.
(3) Prior to the accumulation of the total number of landings specified in paragraph 2.1.5 or 2.1.10, as applicable, of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later, modify the structure of the fuselage frame at stations 178 and 213.5 in accordance with paragraph 2.1.5 or 2.1.10, as applicable, of the Accomplishment Instructions of the alert service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of paragraphs (a)(1) and (a)(2) this AD.
(4) Prior to the accumulation of 55,000 total landings or within 12 months after the effective date of this AD, whichever occurs later, rework the cabin pressurization system to limit the maximum differential operating pressure of the fuselage to 7.5 pounds per square inch (psi), in accordance with the alert service bulletin.
(b) For airplanes on which Structural Repair Manual, figure 76, repair in-situ has been accomplished: Accomplish paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD, in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
(1) Perform the initial inspection prior to the compliance time specified in paragraph 2.2 of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later. Repeat the inspection thereafter at intervals specified in paragraph 2.2 of the Accomplishment Instructions of the alert service bulletin.
(2) If any discrepancy is found during any inspection required by paragraph (b)(1) of this AD, prior to further flight, correct the discrepancy in accordance with paragraph 2.2 of the Accomplishment Instructions of the alert service bulletin; or in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) Prior to the accumulation of the total number of landings specified in paragraph 2.2.6 or 2.2.9, as applicable, of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later, modify the structure of the fuselage frame at stations 178 and 213.5 in accordance with paragraph 2.2.6 or 2.2.9, as applicable, ofthe Accomplishment Instructions of the alert service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of paragraphs (b)(1) and (b)(2) of this AD.
(4) Prior to the accumulation of 55,000 total landings or within 12 months after the effective date of this AD, whichever occurs later, rework the cabin pressurization system to limit the maximum differential operating pressure of the fuselage to 7.5 psi, in accordance with the alert service bulletin.
(c) For airplanes on which Structural Repair Manual, figure 87, repair has been accomplished: Accomplish paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
(1) Perform the initial inspection prior to the compliance time specified in paragraph 2.3 of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later. Repeat the inspection thereafter at intervals specified in paragraph 2.3 of the Accomplishment Instructions of the alert service bulletin.
(2) If any discrepancy is found during any inspection required by paragraph (c)(1) of this AD, prior to further flight, correct the discrepancy in accordance with paragraph 2.3 of the Accomplishment Instructions of the alert service bulletin; or in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) Prior to the accumulation of the total number of landings specified in paragraph 2.3.5 or 2.3.8, as applicable, of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later, modify the structure of the fuselage frames at stations 178 and 213.5 in accordance with paragraph 2.3.5 or 2.3.8, as applicable, of the Accomplishment Instructions of the alert service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of paragraphs (c)(1) and (c)(2) of this AD.
(4) Prior to the accumulation of 55,000 total landings or within 12 months after the effective date of this AD, whichever occurs later, rework the cabin pressurization system to limit the maximum differential operating pressure of the fuselage to 7.5 psi, in accordance with the alert service bulletin.
(d) For airplanes on which Structural Repair Manual, figure 110 or 111, repair has been accomplished: Accomplish paragraphs (d)(1), (d)(2), (d)(3), and (d)(4) of this AD, in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
(1) Perform the initial inspection prior to the compliance time specified in paragraph 2.4 of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later. Repeat the inspection thereafter at intervals specified in paragraph 2.4 of the Accomplishment Instructions of the alert service bulletin.
(2) If any discrepancy is found during any inspection required by paragraph (d)(1) of this AD, prior to further flight, correct the discrepancy in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) Prior to the accumulation of the total number of landings specified in paragraph 2.4.5. or 2.4.8, as applicable, of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later, modify the structure of the fuselage frames at stations 178 and 213.5 in accordance with paragraph 2.4.5 or 2.4.8, as applicable, of the Accomplishment Instructions of the alert service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of paragraphs (d)(1) and (d)(2) of this AD.
(4) Prior to the accumulation of 55,000 total landings or within 12 months after the effective date of this AD, whichever occurs later, rework the cabin pressurization system to limit the maximum differential operating pressure of the fuselage to 7.5 psi, in accordance with the alert service bulletin.
(e) For airplanes on which Structural Repair Manual, figure 76, reinforcement has been accomplished: Accomplish paragraphs (e)(1), (e)(2), (e)(3), (e)(4), and (e)(5) of this AD, in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
(1) Perform the initial inspection prior to the compliance time specified in paragraph 2.5 of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later. Repeat the inspection thereafter at intervals specified in paragraph 2.5 of the Accomplishment Instructions of the alert service bulletin.
(2) If any discrepancy is found during any inspection required by paragraph (e)(1) of this AD, prior to further flight, correct the discrepancy in accordance with paragraph 2.5 of the Accomplishment Instructions of the alert service bulletin; or in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) Prior to the accumulation of the total number of landings specified in paragraph 2.5.5 or 2.5.10, as applicable, of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later, modify the structure of the fuselage frames at stations 178 and 213.5 in accordance with paragraph 2.5.5 or 2.5.10, as applicable, of the Accomplishment Instructions of the alert service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of paragraphs (e)(1) and (e)(2) of this AD.
(4) For airplanes operated at a cabin maximum pressure differential in excess of 7.5 psi, prior to the threshold times specified in Table C of the service bulletin, replace the reinforcements accomplished in accordance with the Structural Repair Manual, figure 76, with reinforcements accomplished in accordance with Structural Repair Manual 53-02-00, figure 110 or 111, as specified in the alert service bulletin.
(5) Prior to the accumulation of 55,000 total landings or within 12 months after the effective date of this AD, whichever occurs later, rework the cabin pressurization system to limit the maximum differential operating pressure of the fuselage to 7.5 psi, in accordance with the alert service bulletin.
(f) For airplanes on which Structural Repair Manual, figure 87, reinforcement has been accomplished: Accomplish paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of this AD, in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
(1) Perform the initial inspection prior to the compliance time specified in paragraph 2.6 of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later. Repeat the inspection thereafter at intervals specified in paragraph 2.6 of the Accomplishment Instructions of the alert service bulletin.
(2) If any discrepancy is found during any inspection required by paragraph (f)(1) of this AD, prior to further flight, correct the discrepancy in accordance with paragraph 2.6 of the Accomplishment Instructions of the alert service bulletin; or in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) Prior to the accumulation of the total number of landings specified in paragraph 2.6.6 or 2.6.9, as applicable, of the Accomplishment Instructions of the alert service bulletin or within 12 months after the effective date of this AD, whichever occurs later, modify the structure of the fuselage frames at stations 178 and 213.5 in accordance with paragraph 2.6.6 or 2.6.9, as applicable, of the Accomplishment Instructions of the alert service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of paragraphs (f)(1) and (f)(2) of this AD.
(4) Prior to the accumulation of 55,000 total landings or within 12 months after the effective date of this AD, whichever occurs later, rework the cabin pressurization system to limit the maximum differential operating pressure of the fuselage to 7.5 psi, in accordance with the alert service bulletin.
(g) For airplanes on which repairs other than those described in the Structural Repair Manual have been accomplished on frames 178 and 213.5, in the area between stringers 25L and 27L: Accomplish paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
(1) Within 6 months after the effective date of thisAD, submit the following for approval to the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate:
(i) Procedures and schedule for accomplishing the initial and repetitive inspections of the fuselage frames at stations 178 and 213.5; and
(ii) Schedule for installation of Modification PM5993 or Structural Repair Manual, figure 110 and 111, as applicable, at the fuselage frames at stations 178 and 213.5.
(2) Within 6 months after the procedures and schedules are approved, revise the FAA-approved maintenance program to include these procedures.
(3) Prior to the accumulation of 55,000 total landings or within 12 months after the effective date of this AD, whichever occurs later, rework the cabin pressurization system to limit the maximum differential operating pressure of the fuselage to 7.5 psi, in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
(h) 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, FAA, Transport Airplane Directorate. 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(i) 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.
(j) The actions shall be done in accordance with British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993. This incorporation by reference 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.
(k) This amendment becomes effective on August 23, 1995.