AD 61-08-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Vickers-Armstrongs (Aircraft Limited) | Viscount 744 | Airworthiness Directives; VICKERS Models 744 and 745D Series Airplanes |
| aircraft | Vickers-Armstrongs (Aircraft Limited) | Viscount 745D | Airworthiness Directives; VICKERS Models 744 and 745D Series Airplanes |
Unsafe Condition
Failure of bolt P/N 80216-627 or P/N 70116-9 forming the forward attachment of the outboard diagonal strut on the inboard engine nacelle structure due to cracks at the junction of the head and shank and thread undercut areas.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect bolts P/N 80216-627 or P/N 70116-9 with 4,000 or more hours' time in service for cracks via magnetic particle inspection or FAA-approved equivalent method by the next 600 landings. Replace cracked bolts prior to further flight. Comply with British Aircraft Corporation PTL 228 Issue 2 when inspecting.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Not later than the next 600 landings for inspection; replace cracked bolts prior to further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Vickers-Armstrongs (Aircraft Limited) Viscount Models 744 and 745D Series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Nacelle Bolts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_61-08-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 61-08-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; VICKERS Models 744 and 745D Series Airplanes Subject: Nacelle Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/09/1961 Make: Vickers-Armstrongs (Aircraft Limited) Model: Viscount 744 | Viscount 745D Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 61-08-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 61-08-03 SUBJECT HEADING: Airworthiness Directives; VICKERS Models 744 and 745D Series Airplanes ACTION: SUMMARY: DATES: Effective May 9, 1961. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 61-08-03 VICKERS: Amdt. 274 Part 507 Federal Register April 8, 1961. Applies to Viscount Models 744 and 745D Series Airplanes. Compliance required as indicated, unless already accomplished. As a result of reported failures of the bolt, P/N 80216-627, forming the forward attachment of the outboard diagonal strut on the inboard engine nacelle structure the following must be accomplished on the structure of both inboard engine nacelles. (a) Bolts P/N 80216-627 or bolts P/N 70116-9*, as applicable, having 4,000 or more hours' time in service must be removed not later than the next 600 landings and inspected for cracks by magnetic particle inspection or FAA approved equivalent method. Particular attention should be given to the area at the junction of the head and shank and also to the thread undercut. (b) Bolts found cracked must be replaced prior to further flight. (c) Compliance with "The Action" paragraphs of British Aircraft Corporation (Operating) Limited, Preliminary Technical Leaflet (PTL 228), Issue 2 (700 Series) is required when accomplishing the inspection of paragraph (a). (d) After compliance with (a), (b), and (c) no further inspection is necessary. (e) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each aircraft's hours' time in service by the operator's fleet average time from takeoff to landing for the aircraft type. Model 745D operators who have kept a record of flights prior to the effective date of this AD may account for them in complying with this AD by counting each flight as one landing. (British Aircraft Corporation (Operating) Limited, PTL No.228, Issue 2, (700 Series) covers this subject. This directive effective May 9, 1961. Revised September 28, 1965. *Bolts P/N 80216-627 were incorporated by Mod. 1306 and on later production aircraft. Pre-mod. standard bolts P/N 70116-9 are identical except 1/32-inch less in diameter. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_61-08-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 61-08-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; VICKERS Models 744 and 745D Series Airplanes Subject: Nacelle Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/09/1961 Make: Vickers-Armstrongs (Aircraft Limited) Model: Viscount 744 | Viscount 745D Product Type: Aircraft Product Subtype: Large 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: 61-08-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 61-08-03 SUBJECT HEADING: Airworthiness Directives; VICKERS Models 744 and 745D Series Airplanes ACTION: SUMMARY: DATES: Effective May 9, 1961. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 61-08-03 VICKERS: Amdt. 274 Part 507 Federal Register April 8, 1961. Applies to Viscount Models 744 and 745D Series Airplanes. Compliance required as indicated, unless already accomplished. As a result of reported failures of the bolt, P/N 80216-627, forming the forward attachment of the outboard diagonal strut on the inboard engine nacelle structure the following must be accomplished on the structure of both inboard engine nacelles. (a) Bolts P/N 80216-627 or bolts P/N 70116-9*, as applicable, having 4,000 or more hours' time in service must be removed not later than the next 600 landings and inspected for cracks by magnetic particle inspection or FAA approved equivalent method. Particular attention should be given to the area at the junction of the head and shank and also to the thread undercut. (b) Bolts found cracked must be replaced prior to further flight. (c) Compliance with "The Action" paragraphs of British Aircraft Corporation (Operating) Limited, Preliminary Technical Leaflet (PTL 228), Issue 2 (700 Series) is required when accomplishing the inspection of paragraph (a). (d) After compliance with (a), (b), and (c) no further inspection is necessary. (e) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each aircraft's hours' time in service by the operator's fleet average time from takeoff to landing for the aircraft type. Model 745D operators who have kept a record of flights prior to the effective date of this AD may account for them in complying with this AD by counting each flight as one landing. (British Aircraft Corporation (Operating) Limited, PTL No.228, Issue 2, (700 Series) covers this subject. This directive effective May 9, 1961. Revised September 28, 1965. *Bolts P/N 80216-627 were incorporated by Mod. 1306 and on later production aircraft. Pre-mod. standard bolts P/N 70116-9 are identical except 1/32-inch less in diameter. FOOTER:
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Retrieved: Apr 8, 2026
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