AD 79-25-02 R1

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AD Number:
79-25-02 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED-CALIFORNIA COMPANY Model L-1011-385 Series Airplanes
Subject:
Main Landing Gear Pistons
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/22/1981
Make:
Lockheed Martin Corporation
Model:
L-1011-385-1 | L-1011-385-1-14 | L-1011-385-1-15 | L-1011-385-3
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Superseded AD: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Superseded By: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: 79-25-02 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4098

AD NUMBER:   79-25-02 R1

SUBJECT HEADING:   LOCKHEED-CALIFORNIA COMPANY Model L-1011-385 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 22, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
79-25-02 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3629 as amended by amendment 39-4098. Applies to Lockheed-California Company L-1011-385 series airplanes certificated in all categories.

To preclude possible failure of the main landing gear pistons P/N 1523009 (-109, -113, - 117, -121), perform the following:

Compliance required as indicated.

(a) Within the next 48 hours after the effective date of the AD, unless already accomplished, conduct a visual inspection of the main landing gear piston clevis lugs including the web area directly above the lugs. If a crack is found, the piston must be replaced prior to further revenue flight.

(b) Repeat the visual inspection of paragraph (a), above, once per each day in which the aircraft is operated.

NOTE: The visual inspection of paragraphs (a) and (b), above, should be conducted with the piston clevis lugs and the web area directly above the lugs thoroughly cleaned of all accumulated dirt and grease. The conduct of this visual inspection is considered to constitute an interim safety action.

(c) Installation and/or modification of the main landing gear uplock snubber, truck pivot pin and bushings using Kits 1630462-101, -103, -105, and -107 or alternate Kits 1630462- 109, -111, -113, and -115 per Lockheed Service Bulletin 093-32-154 Revision #2 dated January 5, 1981, constitutes terminating action for this AD.

(d) 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 replacements required by this AD.

(e) Alternative inspections or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).

All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 92520, Attention: Commercial Support Contracts, Department 63-11, 033, B- 1.

These documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14.

Amendment 39-3629 became effective December 11, 1979.

This amendment 39-4098 becomes effective May 22, 1981.

FOOTER: