95-23-04: Inspection of Rod Ends

95-23-04 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-9424. Docket 95-NM-217-AD. Applicability: All Model BAC 1-11 400 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 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 (e) 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. NOTE 2: Inspections and replacement of the rod ends in accordance with British Aerospace Campaign Wire 27-CW-PM6034, dated May 18, 1995, are considered to be acceptable for compliance with the actions specified in this AD. To prevent asymmetric deployment and subsequent lateral control problems, particularly at low speeds with the flaps extended, due to cracking of either pair of aft rod ends of the lift dumper operating mechanism, accomplish the following: (a) Within 100 flight hours or 30 days after the effective date of this AD, whichever occurs first: Perform a visual inspection to detect drill holes for a grease nipple in the housing of the rod ends of the lift dumper, in accordance with British Aerospace Alert Service Bulletin 27-A-PM6034, Issue 1, dated October 6, 1995. (b) If no drill holes for a grease nipple are found, no further action is required by this AD. (c) If any drill hole for a grease nipple is found, prior to further flight, perform a dye penetrant inspection to detect cracking of the rod eye-end, in accordance with British Aerospace Alert Service Bulletin 27-A-PM6034, Issue 1, dated October 6, 1995. Pay particular attention to the area surrounding the grease nipple hole. (1) If no cracking is found, accomplish the requirements of paragraphs (c)(1)(i) and (c)(1)(ii) of this AD. (i) Repeat the inspection required by paragraph (c) of this AD thereafter at intervals not to exceed 100 flight hours until the rod ends are replaced in accordance with paragraph (c)(1)(ii) of this AD. (ii) Within 60 days after the effective date of this AD, replace the drilled rod end with an undrilled rod end, in accordance with the alert service bulletin. Accomplishment of this replacement constitutes terminating action for the inspections required by paragraph (c)(1)(i) of this AD. (2) If any cracking is found, prior to further flight, replace the rod end with an undrilled rod end, in accordance with British Aerospace Alert Service Bulletin 27-A-PM6034, Issue 1, dated October 6, 1995. (d) As of the effective date of this AD, no person shall install on any airplane a rod end, part number RMX 7GUE, having any holes drilled for a grease nipple; nor shall any person drill any holes for a grease nipple in a rod end having part number RMX 7GUE on any airplane. (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, 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 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 and replacement of the rod ends shall be done in accordance with British Aerospace Alert Service Bulletin 27-A-PM6034, Issue 1, dated October 6, 1995. 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 theOffice of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on November 28, 1995.