87-26-05 FOKKER B.V.: Amendment 39-5805. Applies to Model F-28 series airplanes, as listed in Fokker B.V. Service Bulletin F28/52-a/100, Revision 1, dated June 19, 1987, certificated in any category. Compliance required within 120 flight hours after the effective date of this AD, unless previously accomplished.
To prevent sudden decompression of the airplane as a result of failure of a cargo hinge lugs, accomplish the following:
A. Visually or dye penetrant inspect the cargo door hinge lugs for cracks, in accordance with Fokker Service Bulletin F28/52-a/100, Revision 1, dated June 19, 1987. Any lugs found to be cracked must be replaced with a serviceable part prior to further flight, in accordance with the limitations set forth in the service bulletin.
B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approvedby the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.
C. 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 modifications required by this AD.
All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Fokker Aircraft, 1199 North Fairfax Street, Alexandria, Virginia 22314. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East marginal Way South, Seattle, Washington.
This amendment becomes effective February 1, 1988.