AD 47-43-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Cessna Aircraft Company | 120 | Airworthiness Directives; CESSNA Model 120 and 140 Airplanes |
| aircraft | Cessna Aircraft Company | 140 | Airworthiness Directives; CESSNA Model 120 and 140 Airplanes |
Unsafe Condition
Fatigue cracks in the elevator spar web at the hinges, starting at rivets or fitting edges and progressing around the fitting, leading to elevator separation from the hinge fitting.
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Required Actions
Inspect for fatigue cracks in the elevator spar web at the hinges every 100 hours of operation. Install reinforcing channels (Cessna P/N 0434151 or 0434152) with specified rivets if cracks are less than 1/2 inch. Replace the spar and install reinforcing channels if cracks exceed 1/2 inch.
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Compliance Time
upon each 100 hours of operation until reinforcing channels are installed at all hinge fittings
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Affected Aircraft
Cessna Model 120 and 140 Aircraft, Serial Numbers 8001 to 13780, inclusive.
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Federal Register Abstract
Elevator Spar Web Reinforcement
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_47-43-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-43-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CESSNA Model 120 and 140 Airplanes Subject: Elevator Spar Web Reinforcement Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Cessna Aircraft Company Model: 120 | 140 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 47-43-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-43-05 SUBJECT HEADING: Airworthiness Directives; CESSNA Model 120 and 140 Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-43-05 CESSNA: (Was Service Note 3 of AD-768-5.) Applies to 120 and 140 Aircraft Serial Numbers 8001 to 13780, Inclusive. Inspection required upon each 100 hours of operation until reinforcing channels are installed at all hinge fittings. Inspect for fatigue cracks in the elevator spar web at the hinges. These cracks start either at the rivets or at an edge of the fitting and progress around the fitting until the elevator breaks loose from the hinge fitting. If cracks less than 1/2 inch in length are found a reinforcing channel, Cessna P/N 0434151 at the outboard hinge or 0434152 at the inboard hinge, should be installed on the aft side of the spar with the flanges riveted between the spar flanges and the skin with two AN 455AD3 rivets per flange. Four AN 442AD4 rivets should be used to attach each fitting to the spar web and reinforcing channel. If any cracks are longer than 1/2 inch the spar should be replaced and the reinforcing channels added. (Cessna Service Letter No. 46 dated July 31, 1947, covers this same subject.) FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_47-43-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-43-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CESSNA Model 120 and 140 Airplanes Subject: Elevator Spar Web Reinforcement Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Cessna Aircraft Company Model: 120 | 140 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: 47-43-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-43-05 SUBJECT HEADING: Airworthiness Directives; CESSNA Model 120 and 140 Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-43-05 CESSNA: (Was Service Note 3 of AD-768-5.) Applies to 120 and 140 Aircraft Serial Numbers 8001 to 13780, Inclusive. Inspection required upon each 100 hours of operation until reinforcing channels are installed at all hinge fittings. Inspect for fatigue cracks in the elevator spar web at the hinges. These cracks start either at the rivets or at an edge of the fitting and progress around the fitting until the elevator breaks loose from the hinge fitting. If cracks less than 1/2 inch in length are found a reinforcing channel, Cessna P/N 0434151 at the outboard hinge or 0434152 at the inboard hinge, should be installed on the aft side of the spar with the flanges riveted between the spar flanges and the skin with two AN 455AD3 rivets per flange. Four AN 442AD4 rivets should be used to attach each fitting to the spar web and reinforcing channel. If any cracks are longer than 1/2 inch the spar should be replaced and the reinforcing channels added. (Cessna Service Letter No. 46 dated July 31, 1947, covers this same subject.) FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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