| AD Number | 68-07-07 | Status | Active |
| Effective Date | April 11, 1968 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-575 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Cessna Aircraft Company |
| Model(s) | 188 188A 188B A188 A188A A188B |
68-07-07 CESSNA: Amdt. 39-575. Applies to Models 188 and A188 aircraft up to and including Serial Number 188-0317, except Serial Numbers 188-0052, 188-0055, 188-0212, 188- 0215, 188-0217, 188-0219, 188-0220, 188-0225, 188-0246, 188-0263, 188-0279, 188-0287, 188- 0288, 188-0290, 188-0298, 188-0304, 188-0306, 188-0307, 188-0308, 188-0310, 188-0311, 188- 0312, and 188-0314.
Compliance: Required as indicated, unless already accomplished.
To prevent the separation of the rudder pedal assembly from the pedal shaft at the stub tube weld, accomplish the following:
Within the next 25 hours' time in service after the effective date of this airworthiness directive, modify the rudder pedal assembly in accordance with either of the 2 methods contained in Cessna Service Letter 67-47, dated August 22, 1967, or any other method approved as an equivalent by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region.
This amendment becomeseffective April 11, 1968.