AD 68-11-02

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AD Number:
68-11-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Model 188A and 188C Series Airplanes
Subject:
Upper & Lower Wing Planks
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/04/1969
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Superseded AD: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Superseded By: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: 68-11-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-701

AD NUMBER:   68-11-02

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

ACTION:  

SUMMARY:  

DATES:   Effective January 4, 1969.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-11-02 LOCKHEED: Amdt. 39-701. Applies to Lockheed Model 188A and 188C Series airplanes.

Compliance required as indicated.

To detect fatigue cracks in the upper planks at the fillet attachment holes, accomplish the following:

(a) Within the next 400 hours' time in service after the effective date of this AD, unless already accomplished within the last 1000 hours' time in service, and thereafter at intervals not to exceed 1400 hours' time in service from the last inspection, inspect visually the upper wing planks in the vicinity of the fillet attachment holes on both sides of the four nacelles in accordance with Paragraphs (2)(B) of Lockheed Service Bulletin No. 88/SB-649A dated June 14, 1968, (or later FAA approved revision), or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region, and if cracks are found, repair before further flight in accordance with Section (2)(C) or (2)(D) of Lockheed Service Bulletin No. 88/SB-649A dated June 14, 1968, (or later FAA approved revision,) or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(b) The repetitive inspection required by (a) may be discontinued in the respective affected areas upon completion of the repairs described in Section 2.C. of Lockheed Service Bulletin No. 88/SB-649A, dated June 14, 1968, (or later FAA approved revision), or upon completion of the appropriate preventive repair installation described in Section I.C.I. or preventive reinforcement of Section I.C.II. of Lockheed Service Bulletin No. 88/SB-665, dated November 11, 1968, (or later FAA approved revision).

(c) 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.

This Directive effective July 5, 1968.

Revised August 20, 1968.

Revised October 26, 1968.

Revised January 4, 1969.

FOOTER: