- Effective
- November 16, 1968
- Model
- 177
- Data sheet
- TCDSA13CE
- Registered aircraft
- 446 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-682
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 | b5cf0316…0c2c94e | FAA DRS (API key needed) |
On this page
The airworthiness directive
68-07-09 CESSNA: Amdt. 39-682. Applies to Model 177, Serial Numbers 177-00001 through 177-01152, aircraft.
Compliance: Required as indicated, unless already accomplished.
To prevent oscillation in the longitudinal control system, accomplish the following:
(a) Within 10 hours' time in service after the effective date of this airworthiness directive, modify the flap system by the installation of Cessna P/N 170094-1, in accordance with the instructions contained in Cessna Service Letter No. SE68-13, dated March 30, 1968, or any other method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region.
(b) Cessna P/N 170094-1 referred to in paragraph (a) may be removed when Cessna P/N 1709007-1 is installed in accordance with Cessna Service Letter SE68-14, operation 23 and attachments, dated April 11, 1968, as revised April 22, 1968, or when any other modification is installed which has been approved by Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region.
This amendment becomes effective November 16, 1968.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 446
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1967 | 204 |
|---|---|
| 1968 | 171 |
71 with no year recorded