AD 67-18-03

AD Final Rules - DRS_67-18-03.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
67-18-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Model 382 and 382B Series Airplanes
Subject:
Engine Mount Truss
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/12/1973
Make:
Lockheed Martin Corporation
Model:
382 | 382B
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Superseded AD: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Superseded By: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: 67-18-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1601

AD NUMBER:   67-18-03

SUBJECT HEADING:   LOCKHEED Model 382 and 382B Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 12, 1973.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-18-03 LOCKHEED: Amendment 39-423 as amended by Amendment 39-1601. Applies to Model 382 and 382B series airplanes, serial numbers 3946 and 4101 through 4196.

Compliance as indicated.

(a) For airplanes with 2350 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection.

(b) For airplanes with less than 2350 hours' total time in service on the effective date of the AD comply with Paragraph (c) before the accumulation of 2400 hours' total time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection.

(c) Inspect all eight affected engine mount truss assemblies in accordance with the tooling and inspection instructions given in Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, Section 1f and 2a through 2e, respectively, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.

(1) Cracked parts shall be replaced with new parts having the same part number, or with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, or later FAA approved revision. Replacement truss assemblies shall be installed according to the replacement instructions given in Section 2h through 2aa in the above Service Bulletin, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region.

(2) Replacement of cracked trusses shall be accomplished before further flight, except that one flight may be made for the purpose of obtaining the necessary replacements in accordance with the provisions of FAR 21.197.

(d) When a particular truss assembly is replaced with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, or later FAA approved revision, the repetitive inspection of that truss as required by this AD may be discontinued.

Lockheed-Georgia Service Bulletin 82-153, dated December 1, 1966, covers this same subject.

Amendment 39-423 became effective June 25, 1967.

This Amendment 39-1601 becomes effective March 12, 1973.

FOOTER: