- Effective
- November 2, 1966
- Models
- 707-300B Series, 707-300C Series
- Data sheet
- TCDS4A26
- Registered aircraft
- 6 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-297
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 |
|---|---|---|---|
| FAA DRS HTML | 20 KB | 46a042f6…198795f | FAA DRS (API key needed) |
On this page
The airworthiness directive
66-27-01 BOEING: Amdt. 39-297 Part 39 Federal Register November 2, 1966. Applies to Models 707-300B and -300C Series Airplanes, Serial Numbers 18922, 18926, 18937, 18953, 18960, 18964, 18975, 18976, 18977, and 18991.
Compliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished.
Visually inspect the inboard aileron center hinge clevis for cracks or evidence of hammer-peening using a glass of at least 5-power in accordance with Section 3 of Boeing Service Bulletin No. 2377 or later FAA-approved revision or an equivalent approved by the Chief, Aircraft Engineering Division: FAA Western Region. Replace cracked parts and parts showing evidence of hammer-peening before further flight with a new part of the same part number or a part inspected in accordance with this AD and found free of cracks and evidence of hammer-peening.
This directive effective November 2, 1966.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 6
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1968 | 1 |
|---|---|
| 1977 | 1 |
4 with no year recorded