AD 71-25-09

AD Final Rules - DRS_71-25-09.html
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AD Number:
71-25-09
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes
Subject:
Main Landing Gear Retract Strut
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/29/1972
Make:
The Boeing Company
Model:
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 | ...Show more
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 71-25-09
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1384

AD NUMBER:   71-25-09

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 29, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
71-25-09 MCDONNELL DOUGLAS: Amendment 39-1358 as amended by Amendment 39-1384. Applies to all Model DC-8 Series Airplanes.

Compliance 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.

To 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.

(a) Remove 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.

(b) If 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.

(c) Reinstall 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.

Upon 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.

Amendment 39-1358 became effective January 11, 1972.

This Amendment 39-1384 becomes effective January 29, 1972.


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