AD 68-06-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. | 42A | Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters |
| aircraft | Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. | 42B | Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters |
| aircraft | Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. | 44A | Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters |
| aircraft | Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. | 44B | Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters |
| aircraft | Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. | H21A | Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters |
| aircraft | Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. | H-21B | Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters |
Unsafe Condition
Fatigue failures of the attaching lugs on transmission drive shaft flex coupling adapter P/N 22D3047-1.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Remove the shaft assembly from the helicopter within 15 hours' time in service after the effective date and strip all paint from the exposed portion of the adapter. Perform a dye penetrant inspection for crack indications. Any P/N 22D3047-1 adapter re-installed must be inspected with a ten power magnifying glass within 10 hours' time in service and every 10 hours thereafter until P/N 22D3047-3 is installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 15 hours' time in service after the effective date of this AD
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 series helicopters with transmission drive shaft assemblies (P/N 22D3046, 22D3057, 22D3066 or 22D2172) incorporating P/N 22D3047-1 adapters.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Transmission Drive Shaft
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_68-06-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 68-06-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters Subject: Transmission Drive Shaft Status: Current Citation: This information is not available. Citation Publish Date: 03/21/1968 Effective Date: 03/21/1968 Make: Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. Model: 42A | 42B | 44A | 44B | H21A | H-21B Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 68-06-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-563 AD NUMBER: 68-06-01 SUBJECT HEADING: Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters ACTION: SUMMARY: DATES: Effective March 21, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 68-06-01 BOEING - VERTOL: Amendment 39-563. Applies to Helicopter Type 42A, 42B, 44A, 44B and Military H-21 series certificated under Part 21 (CAR Part 8 or 9). Compliance required as indicated. As a result of fatigue failures of the attacking lugs on transmission drive shaft flex coupling adapter P/N 22D3047-1, accomplish the following: (1) Unless already accomplished on helicopters which incorporate P/N 22D3047-1 adapters on transmission drive shaft assemblies (P/N 22D3046, 22D3057, 22D3066 or 22D2172) remove the shaft assembly from the helicopter within 15 hours' time in service after the effective date of this AD and strip all paint from the exposed portion of the adapter. Particular attention should be given to removal of all paint on both sides of the adapter lugs including the fillet area around the bosses where the adapter mates with the Thomas coupling plates. Do not allow paint remover to seep into the riveted joint. Perform a dye penetrant inspection of the exposed portion of the adapter and inspect for crack indications, paying particular attention to both sides of the adapter lugs and fillet areas. Any adapter with crack indications must be removed from service. (2) Any P/N 22D3047-1 new or used adapter re-installed in the helicopter after completing the above dye penetrant inspection must be inspected using a ten power magnifying glass within 10 hours' time in service and every 10 hours thereafter until an improved type adapter P/N 22D3047-3 is installed. Upon installation of the -3 adapter, the above paragraphs 1 and 2 inspections are no longer required. (Vertol Telex Communication No. 8-2300-2-59 dated January 17, 1968, covers this subject.) This amendment effective March 21, 1968. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_68-06-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 68-06-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters Subject: Transmission Drive Shaft Status: Current Citation: This information is not available. Citation Publish Date: 03/21/1968 Effective Date: 03/21/1968 Make: Boeing Defense & Space Group | Heli-Crane Corporation | Wright Kevin | Marrs Joe G. | Risley Lester W. Model: 42A | 42B | 44A | 44B | H21A | H-21B Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 68-06-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-563 AD NUMBER: 68-06-01 SUBJECT HEADING: Airworthiness Directives; BOEING - VERTOL Type 42A, 42B, 44A, 44B and Military H-21 Series Helicopters ACTION: SUMMARY: DATES: Effective March 21, 1968. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 68-06-01 BOEING - VERTOL: Amendment 39-563. Applies to Helicopter Type 42A, 42B, 44A, 44B and Military H-21 series certificated under Part 21 (CAR Part 8 or 9). Compliance required as indicated. As a result of fatigue failures of the attacking lugs on transmission drive shaft flex coupling adapter P/N 22D3047-1, accomplish the following: (1) Unless already accomplished on helicopters which incorporate P/N 22D3047-1 adapters on transmission drive shaft assemblies (P/N 22D3046, 22D3057, 22D3066 or 22D2172) remove the shaft assembly from the helicopter within 15 hours' time in service after the effective date of this AD and strip all paint from the exposed portion of the adapter. Particular attention should be given to removal of all paint on both sides of the adapter lugs including the fillet area around the bosses where the adapter mates with the Thomas coupling plates. Do not allow paint remover to seep into the riveted joint. Perform a dye penetrant inspection of the exposed portion of the adapter and inspect for crack indications, paying particular attention to both sides of the adapter lugs and fillet areas. Any adapter with crack indications must be removed from service. (2) Any P/N 22D3047-1 new or used adapter re-installed in the helicopter after completing the above dye penetrant inspection must be inspected using a ten power magnifying glass within 10 hours' time in service and every 10 hours thereafter until an improved type adapter P/N 22D3047-3 is installed. Upon installation of the -3 adapter, the above paragraphs 1 and 2 inspections are no longer required. (Vertol Telex Communication No. 8-2300-2-59 dated January 17, 1968, covers this subject.) This amendment effective March 21, 1968. FOOTER:
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