AD 2001-20-09 Airworthiness Directives; Boeing Model 727 Series Airplanes

Models named: 727 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model 727 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 request approval for an alternative method of compliance in accordance with paragraph (h) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair of 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.

Required as indicated, unless accomplished previously. To prevent failure of the bearing support fitting of the forward trunnion, which could result in collapse of the main landing gear during normal operations; consequent damage to the airplane structure; and injury to flight crew, passengers, or ground personnel; accomplish the following: Interim Inspections/Follow-On Actions (a) For airplanes having a bearing support fitting of the forward trunnion installed that has NOT been repaired/reworked in accordance with Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0179, dated March 8, 1990; Revision 1, dated June 13, 1991; Revision 2, dated April 30, 1992; Revision 3, dated September 2, 1999; or Revision 4, dated July 13, 2000: Within 1,500 flight cycles or 6 months after the effective date of this AD, whichever occurs first; perform an ultrasonic inspection of the bearing support fitting of the forward trunnion to detect corrosion and cracking in accordance with Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0179, Revision 3, dated September 2, 1999; Revision 4, dated July 13, 2000; or Boeing Service Bulletin 727-57A0179, Revision 5, dated December 20, 2000; and within 18 months after the effective date of this AD, accomplish the requirements in paragraph (e) or (f) of this AD. (b) For airplanes having a bearing support fitting of the forward trunnion installed that HAS been repaired/reworked in accordance with Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0179, dated March 8, 1990; Revision 1, dated June 13, 1991; Revision 2, dated April 30, 1992; Revision 3, dated September 2, 1999; or Revision 4, dated July 13, 2000: Perform an ultrasonic inspection of the bearing support fitting of the forward trunnion to detect corrosion and cracking in accordance with Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0179, Revision 3, dated September 2, 1999; Revision 4, dated July 13, 2000; or Boeing Service Bulletin 727-57A0179, Revision 5, dated December 20, 2000; at the latter of the times specified in paragraphs (b)(1) and (b)(2) of this AD. (1) Within 12,000 flight cycles or 10 years after repair/rework, whichever occurs first. (2) Within 1,500 flight cycles or 6 months after the effective date of this AD, whichever occurs first. Follow-On Actions/Repetitive Inspections (c) Accomplish the actions required by either paragraph (c)(1) or (c)(2) of this AD, as applicable, in accordance with Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0179, Revision 3, dated September 2, 1999; Revision 4, dated July 13, 2000; or Boeing Service Bulletin 727-57A0179, Revision 5, dated December 20, 2000. (1) If no corrosion or cracking is detected by the inspections required by paragraph (a) or (b) of this AD, prior to further flight, clean the fitting in accordance with the service bulletins. Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles or 6 months, whichever occurs first. (2) If any corrosion or cracking is detected by the inspections required by paragraph (a) or (b) of this AD, prior to further flight, accomplish the requirements in paragraph (e) or (f) of this AD. Inspections, Repair/Rework (d) For airplanes having a bearing support fitting of the forward trunnion installed that HAS been repaired/reworked in accordance with Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0179, dated March 8, 1990; Revision 1, dated June 13, 1991; Revision 2, dated April 30, 1992; Revision 3, dated September 2, 1999; Revision 4, dated July 13, 2000: Accomplish the requirements in paragraph (e) or (f) of this AD at the later of the times specified in paragraphs (d)(1) and (d)(2) of this AD. (1) Within 12,000 flight cycles or 10 years after rework, whichever occurs first. (2) Within 36 months after the effective date of this AD. Inspections, Repair/Rework (e) At the applicable time specified in paragraph (a), (c)(2), or (d) of this AD, as applicable: Perform detailed visual and magnetic particle inspections to detect corrosion and cracking of the fitting, in accordance with Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-57A0179, Revision 3, dated September 2, 1999; Revision 4, dated July 13, 2000; or Boeing Service Bulletin 727-57A0179, Revision 5, dated December 20, 2000; and repair/rework the support fitting in accordance with the service bulletins. Repeat the inspections at intervals not to exceed 12,000 flight cycles or 10 years, whichever occurs first, in accordance with the service bulletins. Accomplishment of the requirements in this paragraph constitutes terminating action for the requirements in paragraphs (a), (b), (c), and (d) of this AD. Note 2: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” Alternative Action (f) Accomplishment of the actions required by paragraphs (f)(1) and (f)(2) of this AD in accordance with Part II of the Accomplishment Instructions of Boeing Service Bulletin 72757A0179, Revision 5, dated December 20, 2000, is acceptable for compliance with the repair/rework requirements of paragraph (e) of this AD. (1) Replacement of the fitting with a new fitting, as specified in Part II of the Accomplishment Instructions of the service bulletin at the time specified in paragraph (e) of this AD. (2) Accomplishment of repetitive inspections of a new fitting thereafter at intervals not to exceed 12,000 flight cycles or 10 years, whichever occurs first, in accordance with the service bulletin. Spares (g) As of the effective date of this AD, no person shall install on any airplane any bearing support fitting of the forward trunnion identified in the “Existing Part Number” column of Paragraph 2.E. of Boeing Alert Service Bulletin 727-57A0179, Revision 3, dated September 2, 1999; Revision 4, dated July 13, 2000; or Boeing Service Bulletin 727-57A0179, Revision 5, dated December 20, 2000; unless that support fitting meets the criteria specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) The fitting has been repaired/reworked in accordance with Part II of the Accomplishment Instructions of Revisions 3, 4, or 5 of the service bulletins, or the new fitting has been received from the manufacturer and has not been previously installed on any airplane. (2) The part number of the fitting has been verified in accordance with Revisions 4 or 5 of the service bulletins. (3) The maximum taxi gross weight (MTGW) limit of the fitting is greater than or equal to the MTGW of the airplane in accordance with Revisions 4 or 5 of service bulletins. Alternative Methods of Compliance (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, Seattle Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permit (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. Incorporation by Reference (j) The actions shall be done in accordance with the service information included in Table 1, as follows: Table 1.—Service Bulletins Service bulletin Revision Date Boeing Alert Service Bulletin 727-57A0179 3 September 2, 1999. Boeing Alert Service Bulletin 727-57A0179 4 July 13, 2000. Boeing Service Bulletin 727-57A0179 5 December 20, 2000. This incorporation by reference is approved by the Director of the Federal Register in accordance with 5 U.S.C. 52(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. This information may be examined 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. Effective Date (k) This amendment becomes effective on November 15, 2001. Issued in Renton, Washington, on October 2, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-25184 Filed 10-10-01; 8:45 am] BILLING CODE 4910-13-U