AD 71-25-09

Active

Main Landing Gear Retract Strut

Key Information
71-25-09
Active
January 29, 1972
Not specified
Unknown
39-1384
Applicability
["Aircraft"]
["Large Airplane"]
The Boeing Company
DC-8-11 DC-8-12 DC-8-21 DC-8-31 DC-8-32 DC-8-33 DC-8-41 DC-8-42 DC-8-43 DC-8-51 DC-8-52 DC-8-53 DC-8-55 DC-8-61 DC-8-61F DC-8-62 DC-8-62F DC-8-63 DC-8-63F DC-8-71 DC-8-71F DC-8-72 DC-8-72F DC-8-73 DC-8-73F DC-8F-54 DC-8F-55
Regulatory Text

71-25-09 MCDONNELL DOUGLAS: Amendment 39-1358 as amended by Amendment 39-1384. Applies to all Model DC-8 Series Airplanes. \n\n\tCompliance required within the next 3,000 hours' time in service after the effective date of this AD, unless already accomplished within the last 17,000 hours' time in service, and thereafter at each FAA approved normal gear overhaul period, but not to exceed 20,000 hours' time in service from the last inspection. \n\n\tTo prevent failures of the main landing gear retract cylinder attach pin, accomplish the following in accordance with McDonnell Douglas DC-8 Service Bulletin No. 32-102, Revision 4, dated 4 May 1970, or later FAA approved revisions, or an equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(a)\tRemove the retract pin and inspect the retract pin lock bolt hole, the surface of retract pin, and the inner surface of the retract pin boss for corrosion and cracks. \n\n\t(b)\tIf corrosion is found, rework the affected areas to remove all traces of corrosion. If no more than .003 inches on the diameter is removed from the boss hole during rework, further shot peening of the reworked area is not required. If cracks or corrosion are found in the retract pin, discard the pin. \n\n\t(c)\tReinstall uncracked and uncorroded pins, with particular care being used in obtaining a moisture proof seal around the retract pin lock bolt. It is recommended that a beak of PR 1436G sealant or equivalent be applied around the boss lip, where the retract pin protrudes, to seal out moisture. If the boss is heated to facilitate installation of the retract pin, Parker-O-Lube or equivalent should be substituted for the 463-6-1 Cat-A-Lac primer. \n\n\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. \n\n\tAmendment 39-1358 became effective January 11, 1972. \n\n\tThis Amendment 39-1384 becomes effective January 29, 1972.

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References
This information is not available.
--- - Part 39
FAA Documents