| AD Number | 77-14-09 | Status | Active |
| Effective Date | July 18, 1977 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-2964 |
| 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) | 182P 182Q |
77-14-09 CESSNA: Amendment 39-2964. Applies to Models 182P (serial numbers 18262466 through 18264713, 18264715 through 18265081, 18265083 through 18265175) and 182Q (serial numbers 18265177 through 18265213, 18265215 through 18265222, 18265224 through 18265237, 18265239 through 18265305, 18265307 through 18265320, and 18265322 through 18265327) airplanes certificated in all categories.
Compliance: Required as indicated, unless already accomplished.
To assure aircraft controllability when operating at maximum gross weight and aft center of gravity location, accomplish the following:
A. Within 25 hours time-in-service after the effective date of this AD:
1. Fabricate a placard having 3/16 inch or larger letters reading "AFT C.G. LOCATION LIMITED TO 46.0 INCHES".
2. Install the placard fabricated in A.1. above in clear view of the pilot and operate the airplane in accordance with this limitation until paragraph B. of this AD is accomplished.
B. Within100 hours time-in-service after the effective date of this AD in accordance with Cessna Service Letter SE77-11, dated April 25, 1977, or later approved revisions:
1. Using a steel straight edge, visually inspect the right and left horizontal stabilizer upper skin immediately aft of the stabilizer rear spar upper flange rivet line for evenness along the entire span of the spar.
2. If the inspection required by paragraph B.1. of this AD shows that unevenness exists, support the right and left stabilizer tips and fuselage tail cone and, using a mallet and a 6" x 1" x 1" phenolic block, reform the stabilizer rear spar upper flange to eliminate any unevenness.
C. After complying with paragraphs B.1. and B.2. of this AD, the aft center of gravity location is no longer limited to 46.0 inches aft of the datum and the placard installed in accordance with paragraph A. of this AD may be removed.
D. The 100 hour compliance time in paragraph B. may be extended to a maximum of110 hours time-in-service when necessary to allow compliance at a regularly scheduled maintenance period.
E. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
This amendment becomes effective July 18, 1977.