AD 92-17-07

92-17-07 BRITISH AEROSPACE: Amendment 39-8336. Docket No. 92-NM-53-AD. Supersedes AD 91-14-19, Amendment 39-7060. Applicability: All Model BAe 146-100A, -200A, and -300A series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent in-flight separation of a landing gear door from the airplane, accomplish the following:

(a) Prior to the accumulation of 9,000 landings, or within 30 days after the effective date of this AD; or if previously inspected in accordance with AD 91-14-19 (56 FR 30314, July 2, 1991), within 3,000 landings after the last inspection in accordance with that AD; whichever occurs later; and thereafter at intervals not to exceed 3,000 landings; accomplish the following:

(1) Perform a visual inspection of the left and right main landing gear (MLG) door rear hinge bracket assemblies to detect cracks and/or corrosion, in accordance with British Aerospace Inspection ServiceBulletin 32-A119, Revision 1, dated December 2, 1991.

(2) Prior to further flight, replace any cracked hinge bracket with a serviceable part, in accordance with British Aerospace Inspection Service Bulletin 32-A119, Revision 1, dated December 2, 1991; or temporarily repair cracked brackets in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(3) Prior to further flight, remove any corrosion found, in accordance with the British Aerospace Model 146 Structural Repair Manual, and accomplish the following:

(i) If less than 0.100 inch of corrosion was removed, re-protect the hinge bracket in accordance with the maintenance manual; and obtain a life limit for the hinge bracket from the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(ii) If 0.100 inch, but less than 0.150 inch, of corrosion was removed, re-protect the hinge bracket in accordance with the maintenance manual; and, within 300 landings after accomplishing the re-protection procedure, replace the hinge bracket with a new part.

(iii) If 0.150 inch or more of corrosion was removed, prior to further flight, replace the hinge bracket with a new part.

(b) 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.

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

(c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(d) The inspections shall be done in accordance with British Aerospace Inspection Service Bulletin 32-A119, Revision 1, dated December 2, 1991, which includes the following list of effective pages:

Pages Revision Level Date 1-4 1 December 2, 1991 5 Original November 14, 1990

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, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. 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.

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