AD 77-14-09
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Cessna Aircraft Company | 182P | Airworthiness Directives; CESSNA Models 182P and 182Q Airplanes |
| aircraft | Cessna Aircraft Company | 182Q | Airworthiness Directives; CESSNA Models 182P and 182Q Airplanes |
Unsafe Condition
Failure to limit the aft center of gravity location to 46.0 inches or failure to inspect and reform the horizontal stabilizer rear spar upper flange could result in reduced aircraft controllability when operating at maximum gross weight and aft center of gravity location.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Fabricate and install a placard limiting the aft C.G. location to 46.0 inches within 25 hours time-in-service. Inspect the horizontal stabilizer upper skin for unevenness and reform the spar flange if needed within 100 hours time-in-service. Compliance may be extended to 110 hours time-in-service if necessary for scheduled maintenance.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 25 hours time-in-service after the effective date of this AD for placard installation and within 100 hours time-in-service (extendable to 110 hours time-in-service) after the effective date for stabilizer inspection and repair.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Cessna 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)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Aircraft Controllability
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_77-14-09.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-14-09 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CESSNA Models 182P and 182Q Airplanes Subject: Aircraft Controllability Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/18/1977 Make: Cessna Aircraft Company Model: 182P | 182Q Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 77-14-09 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2964 AD NUMBER: 77-14-09 SUBJECT HEADING: Airworthiness Directives; CESSNA Models 182P and 182Q Airplanes ACTION: SUMMARY: DATES: Effective July 18, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. Within 100 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 of 110 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. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_77-14-09.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-14-09 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CESSNA Models 182P and 182Q Airplanes Subject: Aircraft Controllability Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/18/1977 Make: Cessna Aircraft Company Model: 182P | 182Q Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 77-14-09 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2964 AD NUMBER: 77-14-09 SUBJECT HEADING: Airworthiness Directives; CESSNA Models 182P and 182Q Airplanes ACTION: SUMMARY: DATES: Effective July 18, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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. Within 100 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 of 110 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. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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