# AD 68-11-02: Upper & Lower Wing Planks

- Type: Airworthiness directive
- Status: Current
- Products: Lockheed Martin 188A and 188C
- Effective: January 4, 1969
- Superseded by: Nothing supersedes this AD
- Product type: Aircraft, Large airplane
- Amendment: 39-701
- Registered aircraft: 4 may be affected, by airframe or engine model (OpenAirDocs)
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/69D65B9854F2454086256E0100546B6A.0001
- DRS record last changed: May 30, 2024
- Page: https://openairdocs.org/ad/68-11-02

## The airworthiness directive

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.

## Affected data sheets (1) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS 4A22](https://openairdocs.org/tcds/4A22): Lockheed Martin Corporation; names 2 of 2 models: 188A, 188C

## Registered aircraft it may apply to (OpenAirDocs)

Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment.

- Aircraft: 4 (4 by airframe model, 0 by engine model)
- Makers: Lockheed 4

Models with the most aircraft:

- [Lockheed 188C](https://openairdocs.org/model/lockheed-188c): 3 aircraft (airframe model)
- [Lockheed 188A](https://openairdocs.org/model/lockheed-188a): 1 aircraft (airframe model)

All 2 models: https://openairdocs.org/ad/68-11-02/models.md
Every aircraft: https://openairdocs.org/ad/68-11-02/aircraft.md

Its text cites no advisory circulars or STCs.

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