88-20-03 BRITISH AEROSPACE: Amendment 39-6029. Applies to certain British Aerospace (BAe) Model 146 series airplanes, as listed in BAe 146 Service Bulletin 53-70, Revision 1, dated July 15, 1988 (hereinafter referred to as SB 53-70), certificated in any category.
Compliance required as indicated, unless previously accomplished.
To detect cracking of the rear fuselage skin, accomplish the following:
A. For Model BAe 146 200 and 200A series airplanes listed in paragraph 1.A.(1)(c) of SB 53-70: Prior to the accumulation of 18,000 landings, or within 30 days after the effective date of this AD, whichever occurs later and thereafter at intervals not to exceed 12,000 landings, inspect the lap joint at stringer 2 left, between fuselage stations 635.36 and 766.40, for cracks, in accordance with SB 53-70. If cracks are found which exceed the limits specified in SB 53-70, repair before further flight, in accordance with that service bulletin.
B. For Model BAe 146 100, 100A, 200, and 200A series airplanes listed in paragraphs 1.A(1)(a), 1.A(1)(b), and 1.A(1)(c) of SB 53-70: Prior to the accumulation of 12,000 landings, or within 30 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 9,000 landings, inspect lap joints at stringer 10 left and right between fuselage stations 541.0 and 672.04 for the Model BAe 146 100 series, and 635.36 and 766.40 for the Model BAe 146 200 series, for cracks, in accordance with SB 53-70. If cracks are found which exceed the specified limits specified in SB 53-70, repair before further flight, in accordance with that service bulletin.
NOTE: BAE 146 100 and 100A series airplanes that have previously complied with paragraph B. of AD 88-14-08, Amendment 39-5972, are considered to have complied with the initial inspection requirements of paragraph B. of this AD. The inspection is to be repeated in accordance with this AD at intervals not to exceed 9,000 landings, as indicated.
C. For Model BAe 146 200 and 200A series airplanes listed in paragraph 1.A.(1)(c) of SB 53-70: Prior to the accumulation of 12,000 landings, or within 30 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 9,000 landings, inspect the lap joint at stringer 19 left, between fuselage stations 635.36 and 766.40, for cracks in accordance with SB 53-70. If cracks are found which exceed the limits specified in SB 53-70, repair before further flight, in accordance with that service bulletin.
D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.
NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113.E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements of this AD.
All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.
This amendment supersedes AD 88-14-08, Amendment 39-5972.
This amendment, 39-6029, becomes effective October 13, 1988.