- Effective
- March 29, 1973
- Model
- 22M
- Data sheet
- TCDS4A27
- Product
- Aircraft · Large airplane
- Amendment
- 39-1612
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
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On this page
The airworthiness directive
73-07-03 GENERAL DYNAMICS: Amdt. 39-1612. Applies to Model 22M Series airplanes certificated in all categories.
Compliance required as indicated.
To detect cracks and prevent further failures of the actuator fitting, accomplish the following:
(1) Within the next 150 hours' time in service after the effective date of this A.D., unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, inspect the rudder boost actuator fitting P/N 30-15701-1 in accordance with General Dynamics 880M S.B. No. A27-47 dated 1 March 1973, or later FAA-approved revision.
(2) If, as a result of the inspection required by paragraph (1), cracks are found, replace the defective fittings with an identical part.
This amendment becomes effective March 29, 1973.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.