AD 91-15-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | McCauley Propeller Systems | 2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| aircraft | McCauley Propeller Systems | 2AF34C55 | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| aircraft | McCauley Propeller Systems | 2D34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| aircraft | McCauley Propeller Systems | B2D34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| aircraft | McCauley Propeller Systems | D2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| aircraft | McCauley Propeller Systems | D2AF34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| aircraft | McCauley Propeller Systems | E2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| aircraft | McCauley Propeller Systems | F2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | 2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | 2AF34C55 | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | 2D34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | B2D34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | D2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | D2AF34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | E2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
| propeller | McCauley Propeller Systems | F2A34C | MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers |
Unsafe Condition
Possible blade separation due to cracks in the propeller blade threaded retention area, hub blade socket threads, retention nut threads, or ferrule threads.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Disassemble the propeller, perform penetrant inspection for cracks, remove and replace cracked assemblies, modify hubs to contain oil with red dye, and report any cracks found. Ferrying is allowed under FAR 21.197/199.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 100 hours, next annual inspection, or within 12 calendar months after the effective date (August 7, 1991), whichever occurs first, for propellers with greater than 900 hours or 59 calendar months since last overhaul/penetrant inspection or installation. For others, prior to accumulating 1000 hours or 60 calendar months since last overhaul/penetrant inspection or installation.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McCauley Model ( )2( )34C( )-( ) Series propellers with threaded retention hubs, including feathering models, on listed aircraft such as Beech, Bellanca, Cessna models (e.g., 180, 182H, 185, 206, 210, 310, 337), Fuji FA-200-180, Interceptor 200A-C, Mooney M20C-G, Navion A/B/D-H, Reims F337E-F, Transavia PL-12/T-300, and Windecker AC-7.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Hub
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_91-15-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 91-15-04 Document Type: AD Final Rules Docket Number: 91-ANE-22 Subject Heading: MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers Subject: Hub Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/07/1991 Make: McCauley Propeller Systems Model: 2A34C | 2AF34C55 | 2D34C | B2D34C | D2A34C | D2AF34C | E2A34C | F2A34C 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 91-15-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-ANE-22 AMENDMENT: 39-7067 AD NUMBER: 91-15-04 SUBJECT HEADING: MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers ACTION: SUMMARY: DATES: Effective August 7, 1991. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 91-15-04 MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY: Amendment 39-7067. Docket No. 91-ANE-22. Applicability: McCauley Model ( )2( )34C( )-( ) Series two bladed constant speed propellers with threaded retention hubs, including those with feathering capabilities listed as follows: Affected Propeller Hub Models CONSTANT SPEED FEATHERING 2D34C8-( ) D2AF34C30-( ) 2D34C9-( ) 2AF34C55-( ) 2D34C53-( ) D2AF34C56-( ) B2D34C53-( ) D2AF34C61-( ) D2A34C58-( ) D2AF34C65-( ) F2A34C58-( ) D2AF34C81-( ) 2A34C66-( ) E2A34C70-( ) E2A34C73-( ) D2A34C78-( ) D2A34C98-( ) The parentheses used in the above list indicate the presence or absence of an additional letter(s) which vary the basic hub model designation. These letter(s) define minor changes that do not affect interchangeability or eligibility, and therefore, this AD still applies regardless of whether these letters are present or absent on the hub model designation. The above listed McCauley propeller hubs are found on, but not limited to, the following aircraft certificated in any category: Beech A23-24, A24, A24R, 58, 58A; 95-55, -A55, -B55,-B55A, -B55B, -C55, -C55A; D55, D55A, E55, E55A. Bellanca 17-30, 17-30A Cessna 180, 182H, 185, 185A thru D, A185E, A185F, 188, 188A, 188B, A188, A188A, A188B, 206, P206, P206A thru E, TP206A thru E, TU206A thru G, U206, U206A thru G, 207, T207, 210, 210A thru H, 210J thru L, 210-5, 210-5A, T210F thru H, T210J thru L, 305B, 305E, 310J, E310J, 310K, 310L, 310N, 336, 337, 337A thru F, M337B, T337B thru F. Fuji FA-200-180 Interceptor (AeroCommander/Meyers) 200A thru C Mooney M20C, M20D, M20G Navion A, B, D thru H Procaer F15/C Reims F337E, F337F, FT337E, FT337F Transavia PL-12/T-300 Windecker AC-7 Compliance: Required as indicated, unless previously accomplished. To prevent possible blade separation, which could result in the loss of the engine and subsequent loss of aircraft control, accomplish the following in accordance with the compliance schedule as indicated: PRIOR PROPELLER UTILIZATION (Hours/calendar months given as time-in-service) COMPLIANCE SCHEDULE OF PROPELLER INSPECTION AND MODIFICATION Greater than 900 hours, or 59 calendar months since last overhaul/penetrant inspection or installed new, or prior time-in-service unknown. Within the next 100 hours, or at the next annual inspection, or within 12 calendar months after the effective date of this AD, whichever occurs first. Less than or equal to both 900 hours and 59 calendar months since last overhaul/penetrant inspection or installed new. Prior to the accumulation of 1000 hours or 60 calendar months since last overhaul/penetrant inspection, or installed new, whichever occurs first. (a) For propellers which have incorporated a hub containing oil with red dye and have been designated at initial production as a hub model number listed in the Appendix to this AD, or prior manufactured propellers whose hubs have been modified to contain oil with a red dye and reidentified as a hub model number listed in the Appendix to this AD, compliance is required only with paragraphs (f) and (h) of this AD. (b) Perform propeller disassembly in accordance with the procedures specified for the affected hub model number listed in Paragraph 1 on page 4 of McCauley Service Bulletin (SB) 184, dated March 15, 1991. (c) Penetrant inspect the propeller assembly for cracks in the propeller blade threaded retention area, the hub blade socket threads, the retention nut threads, and the ferrule threads in accordance with the procedures specified for the affected hub model number listed in Paragraph 2 on page 5 of McCauley SB 184, dated March 15, 1991. (d) Remove from service, prior to further flight, propeller assemblies which exhibit cracks and replace with a serviceable unit, modified in accordance with paragraph (e) of this AD, or with an equivalent initial production propeller which has incorporated a hub with oil containing red dye. (e) Modify the affected propeller hub assembly to contain oil with a red dye and reidentify in accordance with the procedures specified for the affected hub model number listed in Paragraph 3 on page 6 of McCauley SB 184, dated March 15, 1991. NOTE: The modification of the propeller hub assembly to contain oil with a red dye provides an "on-condition" (in-service) means of early crack detection to prevent blade separation and also improves lubrication and corrosion protection. The oil will add approximately 2.8 lbs. to the weight of the propeller assembly. (f) If leakage of oil containing red dye is detected in service (whether during flight or while on the ground), determine prior to further flight, the source of leakage in accordance with the procedures specified for the affected hub model number listed in Paragraph 4 on page 7 of McCauley SB 184, dated March 15, 1991. If the inspection reveals a crack, compliance with Paragraph (d) of this AD is required. (g) The "calendar month" compliance times stated in this AD allow the performance of the required action prior to the last day of the month in which compliance is required. NOTE: For example, a required inspection and modification 60 months from last overhaul/penetrant inspection that was performed on December 15, 1986, would allow the penetrant inspection and modification to be performed no later than December 31, 1991. (h) Report in writing any cracks found during inspections accomplished in accordance with paragraphs (c) or (f) of this AD to the Manager, Chicago Aircraft Certification Office, within ten (10) days of the inspection. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and has been assigned OMB Control Number 2120-0056. (i) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. (j) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate) an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Chicago Aircraft Certification Office, Small Airplane Certification Directorate, Aircraft Certification Service, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. The disassembly, inspection, and modification shall be done in accordance with the procedures listed in McCauley SB 184, dated March 15, 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 McCauley Accessory Division, The Cessna Aircraft Company, 3535 McCauley Drive, Vandalia, Ohio 45377. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. Airworthiness Directive 91-15-04, Amendment 39-7067, supersedes, AD 77-17-09, Amendment 39-3020, AD 77-20-03, Amendment 39-3044, AD 77-23-01, Amendment 39-3073, AD 77-24-04, Amendment 39-3086, AD 78-20-01, Amendment 39-3304. This amendment (39-7067, AD 91-15-04) becomes effective on August 7, 1991. AD 91-15-04 APPENDIX OIL-FILLED PROPELLER HUB COMPLIANCE INDICATOR TABLE Propeller Hub Model Compliance Indicator Propeller Hub Model Compliance Indicator + 2D34C8 2D34C8-()P and/or oil-fill plug in side of hub F2A34C58 F2A34C58-()0 and/or oil-fill plug in side of hub 2D34C9 2D34C9-()P and/or oil-fill plug in side of hub D2AF34C61 D2AF34C61-()0 and/or oil-fill plug in side of hub D2AF34C30 D2AF34C30-()P and/or oil-fill plug in side of hub D2AF34C65 D2AF34C65-()0 and/or oil-fill plug in side of hub B2D34C53 B2D34C53-()0 and/or oil-fill plug in side of hub 2A34C66 2A34C66-()P and/or oil-fill plug in side of hub 2D34C53 2D34C53-()0 and/or oil-fill plug in side of hub E2A34C70 E2A34C70-()P and/or oil-fill plug in side of hub 2AF34C55 2AF34C55-()0 and/or oil-fill plug in side of hub E2A34C73 E2A34C73-()P and/or oil-fill plug in side of hub D2AF34C56 D2AF34C56-()0 and/or oil-fill plug in side of hub D2A34C78 D2A34C78-()P and/or oil-fill plug in side of hub D2A34C58 D2A34C58-()0 and/or oil-fill plug in side of hub D2AF34C81 D2AF34C81-()0 and/or oil-fill plug in side of hub D2A34C98 D2A34C98-()0 and/or oil-fill plug in side of hub +Propeller models are listed in numerical sequence following the letter C in the model designation. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_91-15-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 91-15-04 Document Type: AD Final Rules Docket Number: 91-ANE-22 Subject Heading: MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers Subject: Hub Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/07/1991 Make: McCauley Propeller Systems Model: 2A34C | 2AF34C55 | 2D34C | B2D34C | D2A34C | D2AF34C | E2A34C | F2A34C 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 91-15-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-ANE-22 AMENDMENT: 39-7067 AD NUMBER: 91-15-04 SUBJECT HEADING: MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY Model ( )2( )34C( )-( ) Series Propellers ACTION: SUMMARY: DATES: Effective August 7, 1991. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 91-15-04 MCCAULEY ACCESSORY DIVISION, CESSNA AIRCRAFT COMPANY: Amendment 39-7067. Docket No. 91-ANE-22. Applicability: McCauley Model ( )2( )34C( )-( ) Series two bladed constant speed propellers with threaded retention hubs, including those with feathering capabilities listed as follows: Affected Propeller Hub Models CONSTANT SPEED FEATHERING 2D34C8-( ) D2AF34C30-( ) 2D34C9-( ) 2AF34C55-( ) 2D34C53-( ) D2AF34C56-( ) B2D34C53-( ) D2AF34C61-( ) D2A34C58-( ) D2AF34C65-( ) F2A34C58-( ) D2AF34C81-( ) 2A34C66-( ) E2A34C70-( ) E2A34C73-( ) D2A34C78-( ) D2A34C98-( ) The parentheses used in the above list indicate the presence or absence of an additional letter(s) which vary the basic hub model designation. These letter(s) define minor changes that do not affect interchangeability or eligibility, and therefore, this AD still applies regardless of whether these letters are present or absent on the hub model designation. The above listed McCauley propeller hubs are found on, but not limited to, the following aircraft certificated in any category: Beech A23-24, A24, A24R, 58, 58A; 95-55, -A55, -B55,-B55A, -B55B, -C55, -C55A; D55, D55A, E55, E55A. Bellanca 17-30, 17-30A Cessna 180, 182H, 185, 185A thru D, A185E, A185F, 188, 188A, 188B, A188, A188A, A188B, 206, P206, P206A thru E, TP206A thru E, TU206A thru G, U206, U206A thru G, 207, T207, 210, 210A thru H, 210J thru L, 210-5, 210-5A, T210F thru H, T210J thru L, 305B, 305E, 310J, E310J, 310K, 310L, 310N, 336, 337, 337A thru F, M337B, T337B thru F. Fuji FA-200-180 Interceptor (AeroCommander/Meyers) 200A thru C Mooney M20C, M20D, M20G Navion A, B, D thru H Procaer F15/C Reims F337E, F337F, FT337E, FT337F Transavia PL-12/T-300 Windecker AC-7 Compliance: Required as indicated, unless previously accomplished. To prevent possible blade separation, which could result in the loss of the engine and subsequent loss of aircraft control, accomplish the following in accordance with the compliance schedule as indicated: PRIOR PROPELLER UTILIZATION (Hours/calendar months given as time-in-service) COMPLIANCE SCHEDULE OF PROPELLER INSPECTION AND MODIFICATION Greater than 900 hours, or 59 calendar months since last overhaul/penetrant inspection or installed new, or prior time-in-service unknown. Within the next 100 hours, or at the next annual inspection, or within 12 calendar months after the effective date of this AD, whichever occurs first. Less than or equal to both 900 hours and 59 calendar months since last overhaul/penetrant inspection or installed new. Prior to the accumulation of 1000 hours or 60 calendar months since last overhaul/penetrant inspection, or installed new, whichever occurs first. (a) For propellers which have incorporated a hub containing oil with red dye and have been designated at initial production as a hub model number listed in the Appendix to this AD, or prior manufactured propellers whose hubs have been modified to contain oil with a red dye and reidentified as a hub model number listed in the Appendix to this AD, compliance is required only with paragraphs (f) and (h) of this AD. (b) Perform propeller disassembly in accordance with the procedures specified for the affected hub model number listed in Paragraph 1 on page 4 of McCauley Service Bulletin (SB) 184, dated March 15, 1991. (c) Penetrant inspect the propeller assembly for cracks in the propeller blade threaded retention area, the hub blade socket threads, the retention nut threads, and the ferrule threads in accordance with the procedures specified for the affected hub model number listed in Paragraph 2 on page 5 of McCauley SB 184, dated March 15, 1991. (d) Remove from service, prior to further flight, propeller assemblies which exhibit cracks and replace with a serviceable unit, modified in accordance with paragraph (e) of this AD, or with an equivalent initial production propeller which has incorporated a hub with oil containing red dye. (e) Modify the affected propeller hub assembly to contain oil with a red dye and reidentify in accordance with the procedures specified for the affected hub model number listed in Paragraph 3 on page 6 of McCauley SB 184, dated March 15, 1991. NOTE: The modification of the propeller hub assembly to contain oil with a red dye provides an "on-condition" (in-service) means of early crack detection to prevent blade separation and also improves lubrication and corrosion protection. The oil will add approximately 2.8 lbs. to the weight of the propeller assembly. (f) If leakage of oil containing red dye is detected in service (whether during flight or while on the ground), determine prior to further flight, the source of leakage in accordance with the procedures specified for the affected hub model number listed in Paragraph 4 on page 7 of McCauley SB 184, dated March 15, 1991. If the inspection reveals a crack, compliance with Paragraph (d) of this AD is required. (g) The "calendar month" compliance times stated in this AD allow the performance of the required action prior to the last day of the month in which compliance is required. NOTE: For example, a required inspection and modification 60 months from last overhaul/penetrant inspection that was performed on December 15, 1986, would allow the penetrant inspection and modification to be performed no later than December 31, 1991. (h) Report in writing any cracks found during inspections accomplished in accordance with paragraphs (c) or (f) of this AD to the Manager, Chicago Aircraft Certification Office, within ten (10) days of the inspection. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and has been assigned OMB Control Number 2120-0056. (i) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. (j) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate) an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Chicago Aircraft Certification Office, Small Airplane Certification Directorate, Aircraft Certification Service, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. The disassembly, inspection, and modification shall be done in accordance with the procedures listed in McCauley SB 184, dated March 15, 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 McCauley Accessory Division, The Cessna Aircraft Company, 3535 McCauley Drive, Vandalia, Ohio 45377. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. Airworthiness Directive 91-15-04, Amendment 39-7067, supersedes, AD 77-17-09, Amendment 39-3020, AD 77-20-03, Amendment 39-3044, AD 77-23-01, Amendment 39-3073, AD 77-24-04, Amendment 39-3086, AD 78-20-01, Amendment 39-3304. This amendment (39-7067, AD 91-15-04) becomes effective on August 7, 1991. AD 91-15-04 APPENDIX OIL-FILLED PROPELLER HUB COMPLIANCE INDICATOR TABLE Propeller Hub Model Compliance Indicator Propeller Hub Model Compliance Indicator + 2D34C8 2D34C8-()P and/or oil-fill plug in side of hub F2A34C58 F2A34C58-()0 and/or oil-fill plug in side of hub 2D34C9 2D34C9-()P and/or oil-fill plug in side of hub D2AF34C61 D2AF34C61-()0 and/or oil-fill plug in side of hub D2AF34C30 D2AF34C30-()P and/or oil-fill plug in side of hub D2AF34C65 D2AF34C65-()0 and/or oil-fill plug in side of hub B2D34C53 B2D34C53-()0 and/or oil-fill plug in side of hub 2A34C66 2A34C66-()P and/or oil-fill plug in side of hub 2D34C53 2D34C53-()0 and/or oil-fill plug in side of hub E2A34C70 E2A34C70-()P and/or oil-fill plug in side of hub 2AF34C55 2AF34C55-()0 and/or oil-fill plug in side of hub E2A34C73 E2A34C73-()P and/or oil-fill plug in side of hub D2AF34C56 D2AF34C56-()0 and/or oil-fill plug in side of hub D2A34C78 D2A34C78-()P and/or oil-fill plug in side of hub D2A34C58 D2A34C58-()0 and/or oil-fill plug in side of hub D2AF34C81 D2AF34C81-()0 and/or oil-fill plug in side of hub D2A34C98 D2A34C98-()0 and/or oil-fill plug in side of hub +Propeller models are listed in numerical sequence following the letter C in the model designation. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2005-24-09
final ruleAirworthiness Directives; McCauley Propeller Systems Propeller Assemblies Models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X; D3AF32C87/82NC-X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/90LF-X.
Unsafe Condition: Propeller hubs with improperly machined socket retention threads could cause concentrated loading on the threads, resulting in cracking of the hub and blade separation, which could lead to failure ...
2005-14-11
final ruleAirworthiness Directives; Hartzell Propeller, Inc., McCauley Propeller Systems, and Sensenich Propeller Manufacturing Company, Inc. Propellers
Unsafe Condition: Failed propeller blade leading to separation and potential loss of control of the airplane.
2003-13-17
final ruleAirworthiness Directives; Hartzell Propeller, Inc., McCauley Propeller Systems, Sensenich Propeller Manufacturing Company, Inc., and Raytheon Aircraft Company Propellers
Unsafe Condition: Extensive corrosion in the internal bearing bore of the blade, absence of corrosion protection in the internal bearing bore area, cadmium plating on top of deep corrosion pits, poor cadmium plating...
83-24-11 R1
final ruleMCCAULEY ACCESSORY DIVISION Models 2A34C66/90AT-2, E2A34C73/90AT- 8, and 2A36C23/84B-0 Propellers
Unsafe Condition: Propeller blade failure due to scratch(es) within the first four outboard threads or other unairworthy conditions in the retention threads of McCauley Models 2A34C66/90AT-2, E2A34C73/90AT-8, and 2A...