AD 67-02-05

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AD Number:
67-02-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; VICKERS Models 744 and 745D Airplanes
Subject:
Control Rod Guide Beams
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/19/1967
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Superseded AD: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Superseded By: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: 67-02-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-323

AD NUMBER:   67-02-05

SUBJECT HEADING:   Airworthiness Directives; VICKERS Models 744 and 745D Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 19, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-02-05 VICKERS: Amdt. 39-323 Part 39 Federal Register December 20, 1966. Applies to Viscount Models 744 and 745D airplanes.

Compliance required as indicated.

To prevent further failures of the flying control rod guide beam at Fuselage Station 399.25, accomplish the following:

(a) Within the next 25 landings after the effective date of this AD, unless already accomplished within the last 225 landings, and thereafter at intervals not to exceed 250 landings from the last inspection until modified in accordance with (c) or repaired in accordance with (b), visually inspect the control rod guide beam attached to the bottom of the floor beam at Fuselage Station 399.25 for cracks at the top and bottom extremities of the vertical slot for the trim chains.

(b) Repair cracked beams before further flight in accordance with British Aircraft Corporation PTL 261, Issue 1, or later ARB-approved issue, or an FAA-approved equivalent, and either inspect as specified in (a) at intervals not to exceed 500 landings from the last inspection until modified in accordance with (c) and repair in accordance with this paragraph if applicable, or modify cracked beams before further flight in accordance with (c).

(c) Modify beams in accordance with British Aircraft Corporation Modification D.3179 within the next 1500 landings after the effective date of this AD.

(d) 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 airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type.

(e) Upon request of the operator, and FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, Europe, Africa, Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

This directive effective January 19, 1967.

FOOTER: