- Effective
- August 18, 1962
- Models
- 22, 22M, 30, 30A
- Product
- Aircraft · Large airplane
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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| FAA DRS HTML | 21 KB | 805aa5d8…55d180a | FAA DRS (API key needed) |
On this page
The airworthiness directive
62-18-01 GENERAL DYNAMICS/CONVAIR: Amdt. 475 Part 507 Federal Register August 18, 1962. Applies to All Models 22, 22M, and 30 Series Aircraft.
Compliance required within 150 hours' time in service following the effective date of this AD, unless already accomplished.
To prevent loose rudder flight tab balance weights, the following shall be accomplished: Inspect the rudder flight tab balance weight attachments for looseness of the balance weight, missing weights, missing attachment nuts and/or bolts, and for elongation of the attachment bolt holes in the balance weights and attachment arms in accordance with General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, or A27-32, as appropriate. If any of the noted defects are found, they shall be corrected prior to the next flight, as specified in General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, or A27-32, as appropriate, or by an FAA engineering approved equivalent method.
(General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, and A27-32 for the Models 22, 22M, and 30 respectively cover this same subject.)
This directive effective August 18, 1962.
Affected TCDS · 2
The type certificate data sheets for the models this AD names, matched by model and maker.