AD 80-02-03 R1

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AD Number:
80-02-03 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED-CALIFORNIA COMPANY Model L-1011-385 Series Airplanes
Subject:
MLG Fwd/Aft Trunnion Pins
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/06/1980
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Superseded AD: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Superseded By: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: 80-02-03 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3964

AD NUMBER:   80-02-03 R1

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

ACTION:  

SUMMARY:  

DATES:   Effective November 6, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-02-03 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3661 as amended by amendment 39-3964. Applies to Lockheed-California Company L-1011-385 series airplanes certificated in all categories.

To preclude possible failure of the main landing gear forward and aft trunnion pins P/Ns 1523068(-103), 1535918(-101) and 1523069(-101), respectively, perform the following:

Compliance required as indicated.

(a) Within the next 48 calendar days after January 17, 1980, unless already accomplished;

(1) Visually inspect the main landing gear forward and aft trunnion pins in accordance with the accomplishment instructions of paragraph 2B of Lockheed-California Company Alert Service Bulletin 093-32-A167, Revision 1, March 6, 1980. If a crack(s) or fracture is found, replace the trunnion pin(s) prior to further aircraft operation, or;

(2) Visually inspect the main landing gear forward and aft trunnion pins with retainers removed in accordance with paragraph 2A of Lockheed-California Company Service Bulletin 093-32-167, Revision 1, dated September 18, 1980 and install MLG forward and aft trunnion pin retainers per paragraphs 2B and 2C of Lockheed-California Service Bulletin 093-32- 167, Revision 1, dated September 18, 1980. If a crack(s) or fracture is found, replace the trunnion pin(s) prior to further aircraft operation, or;

(3) Remove the MLG forward and aft trunnion pins and retainers, if installed and inspect by visual and magnetic particle methods, and reidentify per paragraphs 2A, 2B, 2C, and 2D of Lockheed-California Service Bulletin 093-32-169, Revision 1 dated September 18, 1980. If a crack(s) or fracture is found, replace the trunnion pin(s) prior to further flight. Defects in chrome plating only may be repaired per paragraphs 2E and 2F of Lockheed-California Service Bulletin 093-32-169, Revision 1, dated September 18, 1980.

NOTE 1: The repetitive inspection requirements of paragraph (b) of this AD are not applicable to trunnion pins inspected per paragraph (a)(3).

(b) Repeat the visual inspections of paragraph (a) of this AD as specified:

(1) Within 50 hours' time in service since the last inspection conducted per paragraph (a)(1) of this AD and thereafter at intervals not to exceed 50 hours' additional time in service, repeat the visual inspections required by paragraph (a)(1) of this AD.

(2) Within 1500 hours' time in service since the inspection and retainer installation accomplished per paragraph (a)(2) of this AD and thereafter at intervals not to exceed 1500 hours' additional time in service, repeat the visual inspections required by paragraph (a)(2) of this AD.

(c) Once per each day in which the aircraft is operated following the accomplishment of the inspections of paragraph (a)(1) above, and excluding the days on which the inspection of paragraph (b), above, is accomplished, conduct visual check of the main landing gear forward and aft trunnion pins in accordance with the accomplishment instructions of paragraph 2A of Lockheed-California Company Alert Service Bulletin 093-32-A167, Revision 1. If an obvious migration of either or both of the pins exists relative to the normal installation configuration, perform the visual inspections of paragraph (a), above. If a crack(s) or fracture is found, replace the pin(s) prior to further aircraft operation.

NOTE 2: The daily check requirements are not applicable if paragraph (a)(2) or (a)(3) of this AD is accomplished.

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

Amendment 39-3661 became effective January 17, 1980.

This amendment 39-3964 becomes effective November 6, 1980.

FOOTER: