AD 66-17-02

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AD Number:
66-17-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; de Havilland Model DHC-2 Series (Mk 1, 2, and 3) Airplanes
Subject:
Front and Rear Spars
Status:
Current
Citation:
Federal Register: July 12, 1966
Citation Publish Date:
07/12/1966
Effective Date:
07/22/1966
Make:
Viking Air Limited
Model:
DHC-2 Mk.I | DHC-2 Mk.II | DHC-2 Mk.III
Product Type:
Aircraft
Product Subtype:
Small 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Superseded AD: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Superseded By: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: 66-17-02
CITATION:   [Federal Register: July 12, 1966]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-259

AD NUMBER:   66-17-02

SUBJECT HEADING:   Airworthiness Directives; de Havilland Model DHC-2 Series (Mk 1, 2, and 3) Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 22, 1966.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
66-17-02 de HAVILLAND: Amdt. 39-259, Part 39, Federal Register July 12, 1966. Applies to Model DHC-2 Series (Mk 1, 2, and 3) Airplanes.

Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 400 hours' time in service, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection until the incorporation of Modification 2/1497, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

To detect cracks in the wing ribs, accomplish the following:

(a) Inspect by radiographic technique or by incorporating a special inspection panel in the wing bottom skin and inspecting visually or with dye penetrant or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, the wing ribs at Stations 15.50, 29.00 and 42.50 for cracks in the rib web in the upper and lower rib flanges between the front and rear spars in accordance with de Havilland Engineering Bulletin, Series "B", No. 35, Modification 2/1497, dated March 18, 1966, for Mk 1 and 2 airplanes; de Havilland Engineering Bulletin Series "T.B.", No. 3, Modification 2/1497, dated March 18, 1966, for Mk 3 airplanes; or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(b) Repair cracks before further flight in accordance with the applicable Engineering Bulletin specified in (a) or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

This directive effective July 22, 1966.

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