AD 54-05-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Sensenich Propeller Manufacturing Company, Inc. | 76AM6-2 | SENSENICH Model M76AM-2 Propellers |
| propeller | Sensenich Propeller Manufacturing Company, Inc. | 76AM6-2 | SENSENICH Model M76AM-2 Propellers |
Unsafe Condition
Blade tip failures due to nicks, gouges, and scratches within 8 inches of the blade tip on Model M76AM-2 propellers installed on Lycoming O-290-D and O-290-D2 engines.
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Required Actions
Remove all nicks, gouges, and scratches within 8 inches of the blade tip, ensuring all traces of damage are eliminated. Use coarse emery cloth for minor damage and polish with fine emery cloth. Rebalancing is not required for minor repairs.
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Compliance Time
March 15, 1954, and at intervals not to exceed each 25 hours operation thereafter.
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Affected Aircraft
SENSENICH Model M76AM-2 Propellers installed on Lycoming Models O-290-D and O-290-D2 Engines.
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Federal Register Abstract
Blade Tip
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_54-05-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 54-05-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: SENSENICH Model M76AM-2 Propellers Subject: Blade Tip Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Sensenich Propeller Manufacturing Company, Inc. Model: 76AM6-2 Product Type: Propeller Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 54-05-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 54-05-02 SUBJECT HEADING: SENSENICH Model M76AM-2 Propellers ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 54-05-02 SENSENICH: Applies to All Model M76AM-2 Propellers Installed on Lycoming Models O-290-D and O-290-D2 Engines. Compliance required by March 15, 1954, and at intervals not to exceed each 25 hours operation thereafter. To eliminate the possibility of blade tip failures on Model M76AM-2 propellers installed on the above Lycoming engines, all nicks, gouges and scratches within 8 inches of the blade tip should be removed. Care should be taken to be sure all trace of the damage is removed. Minor damaged areas may be removed by using coarse emery cloth. The repaired area should then be polished with fine emery cloth. Rebalancing is not necessary when repairing minor damage areas as defined in Civil Aeronautics Manual 18 (18.30-15) (Sensenich Service Bulletin No. R-2 covers this same subject.) FOOTER:
Document Text
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AD Final Rules - DRS_54-05-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 54-05-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: SENSENICH Model M76AM-2 Propellers Subject: Blade Tip Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Sensenich Propeller Manufacturing Company, Inc. Model: 76AM6-2 Product Type: Propeller Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 54-05-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 54-05-02 SUBJECT HEADING: SENSENICH Model M76AM-2 Propellers ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 54-05-02 SENSENICH: Applies to All Model M76AM-2 Propellers Installed on Lycoming Models O-290-D and O-290-D2 Engines. Compliance required by March 15, 1954, and at intervals not to exceed each 25 hours operation thereafter. To eliminate the possibility of blade tip failures on Model M76AM-2 propellers installed on the above Lycoming engines, all nicks, gouges and scratches within 8 inches of the blade tip should be removed. Care should be taken to be sure all trace of the damage is removed. Minor damaged areas may be removed by using coarse emery cloth. The repaired area should then be polished with fine emery cloth. Rebalancing is not necessary when repairing minor damage areas as defined in Civil Aeronautics Manual 18 (18.30-15) (Sensenich Service Bulletin No. R-2 covers this same subject.) FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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