AD 88-10-05 ACTIVE

88-10-05 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-5913. Applies to Model 382 series airplanes, Serial Numbers 3946 through 4250, and 4299 through 4303, except those having outer wings installed to a configuration equivalent to Serial Number 4542 or subsequent; certificated in any category. Compliance required as indicated, unless previously accomplished.

To prevent severe damage to the lower surface panels of the outer wings, accomplish the following:

A. Within the next 50 hours time-in-service after the effective date of this AD; or upon the accumulation of 11,000 flight hours total time-in-service for airplanes Serial Numbers 3946 through 4250, or 18,000 flight hours total time-in-service for airplanes Serial Numbers 4299 through 4303; whichever occurs later, perform an inspection of the outer wing lower surface panels 1, 2, 3, and 4, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987, to determine the existence of doublers on those panels between outer wing stations 161 and 195.

B. If doublers have been installed on panels 1, 2, 3, and 4, left and right, in accordance with Northwest Industries (NWI) Drawing 3609103, the airplane may be returned to normal service.

C. If doublers have been installed on panels 1 and 2 in accordance with Lockheed Service Bulletin 382-152 (382-57-35), dated September 2, 1987, or later FAA-approved revisions, prior to further flight, accomplish either of the following:

1. Inspect the heat shield and nacelle fairing attachment fastener holes from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987.

a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours.

b. If cracks are found, prior to further flight, repair in accordance with an FAA-approved method.

2. Modify the wing in accordance with Lockheed Service Bulletin 382-57- 73, dated January 28,1988. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph C.1.a., above.

D. If doublers have not been installed on panels 1, 2, 3, and 4, prior to further flight, accomplish either of the following:

1. Inspect the heat shield and nacelle fairing attachment fastener from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987.

a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours.

b. If cracks are found, prior to further flight, repair in accordance with an FAA approved method.

2. Modify the wing in accordance with Northwest Industries (NWI) Drawing 3609103. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph D.1.a., above.

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

F. 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, Atlanta Aircraft Certification Office, FAA, Central Region.

NOTE: The request for alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Atlanta Aircraft Certification Office.

All persons affected by this directive who have not already received the applicable service information from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company-Georgia, Attn: Commercial and Customer Support, Department 72-05, Zone 80, 86 South Cobb Drive, Marietta, Georgia 30063. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia.

This amendment becomes effective May 25, 1988.