AD 66-05-03

AD Final Rules - DRS_66-05-03.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
66-05-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Models 188A and 188C Series Airplanes
Subject:
Outer Wing Cap Fittings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/19/1966
Make:
Lockheed Martin Corporation
Model:
188A | 188C
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Superseded AD: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Superseded By: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: 66-05-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-182

AD NUMBER:   66-05-03

SUBJECT HEADING:   LOCKHEED Models 188A and 188C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 19, 1966.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
66-05-03 LOCKHEED: Amdt. 39-182 Part 39 Federal Register January 19, 1966. Applies to Models 188A and 188C Series Airplanes.

Compliance required as indicated, unless already accomplished.

To detect fatigue cracks emanating from the barrel-nut access holes of the outer wing front cap fittings at the Wing Station 65 joint, accomplish the following:

(a) Inspect lower cap fittings, P/N's 807352-1 and -2, by visual means, for cracks emanating from the barrel-nut access holes within the next 1,100 hours' time in service after the effective date of this AD.

(b) Inspect lower and upper cap fittings, P/N's 807352-1 and -2 and P/N's 807354-1 and -2, by dye penetrant method or an FAA-approved equivalent, for cracks emanating from the barrel-nut access holes and by visual means for burrs at the forward edge of the access holes within the next 3,000 hours' time in service after compliance with (a).

(c) Replace any cracked fittings found during the inspections required by (a) or (b) before further flight, with new deburred fittings of the same part number, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be made.

(d) Deburr uncracked fittings on which burrs have been found during the inspection required by (b), before further flight, in accordance with Lockheed Service Bulletin 88/SB-633B, Section 2.D.(4) or later FAA-approved revision, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be made.

This directive effective February 19, 1966.

FOOTER: