AD 61-16-02

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AD Number:
61-16-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
ARMSTRONG-WHITWORTH Model AW-65O Argosy Series Aircraft
Subject:
Elevators, Rudders, Fins, and Flaps
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/03/1961
Make:
British Aerospace (Commercial Aircraft) Ltd
Model:
Argosy AW.650 Series 101
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Superseded AD: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Superseded By: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: 61-16-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   61-16-02

SUBJECT HEADING:   ARMSTRONG-WHITWORTH Model AW-65O Argosy Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective August 3, 1961.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   61-16-02 ARMSTRONG-WHITWORTH: Amdt. 315, Part 507 Federal Register August 3, 1961. Applies to the following Model AW-65O Argosy Series 101 aircraft only: Serial Numbers 6655, 6656, 6657, 6659, and 6660.
Compliance required as indicated.
Because of service defects found on the elevators, rudders, fins and flaps, the following is required:
(a) Prior to every flight, visually inspect the following areas for loose rivets, cracks and damaged skin:
(1) Top and bottom surface of both elevators including horn balances.
(2) Inboard and outboard sides of left and right fins.
(3) Entire surface of left and right rudders including tabs.
(4) Undersurface of inboard flaps.
(b) If loose rivets or damaged skin is found an FAA approved repair must be accomplished prior to further flight.
(c) If cracks are found, the following action must be taken:
(1) If cracks between adjacent rivets or cracks at least one inch long are found, the internal structure in that location must be inspected. If no internal damage is found, an FAA approved repair must be made to the skin prior to the next flight. If any internal damage is found the component must either be replaced or an FAA approved repair incorporated prior to next flight.
(2) If cracks less than one inch long and less than twelve inches apart are found, they must be repaired prior to the next flight. Cracks less than one inch long which are twelve inches or more apart must either be stopped by drilling or repaired prior to next flight.
(d) The special inspections in (a), (b), and (c) are no longer required when AWA modifications 650/686, 650/687, 650/688, 650/689, and 650/690 are all incorporated.
This supersedes AD 61-05-01.
This directive effective August 3, 1961.

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