AD 65-22-04

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AD Number:
65-22-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Vickers Model Viscount Models 744, 745D and 810 Series Airplanes
Subject:
Main Landing Gear Retraction Jack Attachment Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/25/1965
Make:
Vickers-Armstrongs (Aircraft Limited)
Model:
Viscount 744 | Viscount 745D | Viscount 810
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Superseded AD: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Superseded By: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: 65-22-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-141

AD NUMBER:   65-22-04

SUBJECT HEADING:   Airworthiness Directives; Vickers Model Viscount Models 744, 745D and 810 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 25, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-22-04 VICKERS: Amdt. 39-141 Part 39 Federal Register September 28, 1965. Applies to Viscount Models 744, 745D and 810 Series Airplanes.

Compliance required as indicated.

To prevent failure of the main landing gear retraction jack attachment bolt, accomplish the following:

(a) For Models 744 and 745D Series airplanes with attachment bolts, P/N's 70150-495, 74450-103, 72450-275, or 74550-51, and Model 810 Series airplanes with attachment bolts, P/N's 74450-103 or 74550-51, comply with (c) within the next 350 hours' time in service after the effective date of this AD, unless already accomplished.

(b) For Models 744 and 745D Series airplanes with attachment bolts, P/N's 72450-291 or 74550-67, and Model 810 Series airplanes with attachment bolts, P/N's 74550-67 comply with (c) within the next 1,300 hours' time in service after the effective date of this AD unless already accomplished.

(c) Remove and inspect attachment bolts, P/N's 70150-495, 72450-275, 74450-103, 74550-51, 72450-291, or 74550-67, in accordance with B.A.C. Ltd. PTL No. 259 (744 and 745D) and PTL No. 123 (810) or FAA-approved equivalent. Replace bolts having helical markings or surface cracks in accordance with PTL No. 259 or No. 123 as applicable. If a bolt is found to be completely broken through, inspect the associated trunnion or eye end for cracks. Replace any cracked trunnions or eye ends before further flight with a part of the same part number or an FAA-approved equivalent.

This directive effective September 25, 1965.


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