AD 92-16-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Cessna Aircraft Company | 441 | Airworthiness Directives; CESSNA Model 441 Airplanes |
Unsafe Condition
Loss of horizontal stabilizer front spar structural support caused by cracks in the fuselage bulkhead at Fuselage Station (FS) 387.22.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Dye penetrant inspect the horizontal stabilizer forward attach bulkhead at FS 387.22 in accordance with Cessna Attachment to Service Bulletin CQB91-1R1. If cracks are found, replace the bulkhead and install Service Kit SK441-103A prior to further flight. The installation of SK441-103A terminates repetitive inspection requirements.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Initially upon the accumulation of 3,000 hours time-in-service (TIS) or within the next 200 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,000 hours TIS.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Cessna Model 441 airplanes (serial numbers 441-0001 through 441-0362), certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Horizontal Stabilizer Front Spar
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-16-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-16-07 Document Type: AD Final Rules Docket Number: 92-CE-16-AD Subject Heading: Airworthiness Directives; CESSNA Model 441 Airplanes Subject: Horizontal Stabilizer Front Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/30/1992 Make: Cessna Aircraft Company Model: 441 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 92-16-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-CE-16-AD AMENDMENT: 39-8316 AD NUMBER: 92-16-07 SUBJECT HEADING: Airworthiness Directives; CESSNA Model 441 Airplanes ACTION: SUMMARY: DATES: Effective August 30, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-16-07 CESSNA: Amendment 39-8316. Docket No. 92-CE-16-AD. Applicability: Model 441 airplanes (serial numbers 441-0001 through 441-0362), certificated in any category. Compliance: Required initially upon the accumulation of 3,000 hours time-in-service (TIS) or within the next 200 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,000 hours TIS, unless already accomplished. To prevent loss of horizontal stabilizer front spar structural support caused by cracks in the fuselage bulkhead, accomplish the following: (a) Gain access to and dye penetrant inspect the horizontal stabilizer forward attach bulkhead at Fuselage Station (FS) 387.22 in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Attachment to Service Bulletin CQB91-1R1, dated June 21, 1991. (b) If cracks are found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, replace the horizontal stabilizer forward attach bulkhead at FS 387.22 and install Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991. (c) The installation of Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991, is considered terminating action for the repetitive inspection requirements of this AD. Although not required, this installation may be accomplished at any time after the initial inspection. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (f) The inspections and possible installation required by this AD shall be done in accordance with Cessna Attachment to Service Bulletin CQB91-1R1, and Cessna Service Kit SK441-103A, both dated June 21, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (g) This amendment becomes effective on August 30, 1992. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_92-16-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-16-07 Document Type: AD Final Rules Docket Number: 92-CE-16-AD Subject Heading: Airworthiness Directives; CESSNA Model 441 Airplanes Subject: Horizontal Stabilizer Front Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/30/1992 Make: Cessna Aircraft Company Model: 441 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: 92-16-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-CE-16-AD AMENDMENT: 39-8316 AD NUMBER: 92-16-07 SUBJECT HEADING: Airworthiness Directives; CESSNA Model 441 Airplanes ACTION: SUMMARY: DATES: Effective August 30, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-16-07 CESSNA: Amendment 39-8316. Docket No. 92-CE-16-AD. Applicability: Model 441 airplanes (serial numbers 441-0001 through 441-0362), certificated in any category. Compliance: Required initially upon the accumulation of 3,000 hours time-in-service (TIS) or within the next 200 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,000 hours TIS, unless already accomplished. To prevent loss of horizontal stabilizer front spar structural support caused by cracks in the fuselage bulkhead, accomplish the following: (a) Gain access to and dye penetrant inspect the horizontal stabilizer forward attach bulkhead at Fuselage Station (FS) 387.22 in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Attachment to Service Bulletin CQB91-1R1, dated June 21, 1991. (b) If cracks are found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, replace the horizontal stabilizer forward attach bulkhead at FS 387.22 and install Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991. (c) The installation of Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991, is considered terminating action for the repetitive inspection requirements of this AD. Although not required, this installation may be accomplished at any time after the initial inspection. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (f) The inspections and possible installation required by this AD shall be done in accordance with Cessna Attachment to Service Bulletin CQB91-1R1, and Cessna Service Kit SK441-103A, both dated June 21, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (g) This amendment becomes effective on August 30, 1992. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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