AD 92-17-04

92-17-04 BOEING: Amendment 39-8333. Docket No. 91-NM-235-AD. Supersedes AD 91-18-09, Amendment 39-8012.

Applicability: Model 757 series airplanes, equipped with brake part numbers (P/N) identified in paragraphs (a) and (c) of this AD, certificated in any category.

Compliance required as indicated, unless accomplished previously.

To prevent loss of main landing gear braking effectiveness, accomplish the following:

(a) Within 180 days after November 12, 1991 (the effective date of Amendment 39-8012, AD 91-18-09), incorporate the maximum brake wear limits, shown below, into the FAA-approved maintenance inspection program.

Brake Mfr. Brake P/N Boeing P/N Max. Wear Limit Dunlop AHA 1301 S160N020-1 2.46 inches Dunlop AHA 1637 S160N020-5 2.46 inches Dunlop AHA 1676 S160N020-7 2.46 inches Dunlop AHA 1693 S160N020-8 2.46 inches Dunlop AHA 1884 S160N020-14 2.80 inches BFGoodrich 2-1510 S160N020-11 1.70 inches

(b) For BFGoodrich brake P/N 2-1510 (Boeing P/N S160N020-11), in lieu of the limit specified in paragraph (a) of this AD, the maximum allowable brake wear may be extended to 2.2 inches when it is placed into the FAA-approved maintenance inspection program.

(c) Within 180 days after the effective date of this AD, accomplish the following:

(1) For airplanes equipped with BFGoodrich Brake P/N's 2-1457 and 2-1457-1, (Boeing P/N S160N010-43 AND S160N010-45): Accomplish the procedures specified in Section 2.B.(1) of BFGoodrich Service Bulletin 2-1457-32-13, dated January 30, 1991, or Revision 1, dated December 16, 1991 (issued February 28, 1991). Brakes found worn more than the 1.4-inch allowable brake wear must be removed and replaced, prior to further flight, with either a brake built in accordance with Section 2.B.(1)c. of the service bulletin, or a brake with more than 1.4 inches of allowable wear remaining.

(2) For airplanes equipped with BFGoodrich Brake P/N's 2-1457, 2-1457-1,and 2-1457-2, (Boeing P/N S160N010-43, S160N010-45, and S160N010-46): Incorporate either Figure 1 and/or Figure 2 of Section 2.B.(1)c. of BFGoodrich Service Bulletin 2-1457-32-13, dated January 30, 1991, or Revision 1, dated December 16, 1991 (issued February 28, 1991), into the FAA-approved maintenance inspection program.

(d) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.

(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

(f) The procedures relative to BFGoodrich Brake P/N's 2-1457 and 2-1457-1, and 2-1457-2 shall be done in accordance with BFGoodrich Service Bulletin 2-1457-32-13, dated January 30, 1991; or BFGoodrich Service Bulletin 2-1457-32-13, Revision 1, dated December 16, 1991 (issued February 28, 1991). 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124; and BFGoodrich Aerospace, Aircraft Wheels and Brakes, P.O. Box 340, Troy, Ohio 45373. 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., 7th Floor, Suite 700, Washington, DC.

(g) This amendment becomes effective on September 28, 1992.