AD 68-26-02

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AD Number:
68-26-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DE HAVILLAND Model DHC-6 Airplanes
Subject:
Wing Strut Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/20/1968
Make:
Viking Air Limited
Model:
DHC-6-1 | DHC-6-100 | DHC-6-200 | DHC-6-300
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Superseded AD: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Superseded By: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: 68-26-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-694

AD NUMBER:   68-26-02

SUBJECT HEADING:   Airworthiness Directives; DE HAVILLAND Model DHC-6 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 20, 1968.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-26-02 DE HAVILLAND: Amdt. 39-694. Applies to DHC-6 Type Airplanes.

To detect loose or missing jo-bolts in wing struts which have accumulated 150 or more hours time in service as of the effective date of this A.D., accomplish the following:

(a) Within the next 50 hours time in service, unless already accomplished, visually inspect the top and bottom of the right and left wing struts, P/N C6W1005-3, -4, for loose or missing jo-bolts in accordance with the procedure described in deHavilland Service Bulletin No. 6/166, or an FAA approved equivalent procedure.

(b) Identical inspections must be conducted at subsequent times in service of 450 to 550 hours, 2450 to 2550 hours and 7450 to 7550 hours after the inspection required by (a) and thereafter at intervals not to exceed 5000 hours time in service.

(c) Prior to further flight, missing jo-bolts must be replaced with jo-bolts of the same part number or an FAA approved equivalent part; but a maximum of four (4) missing in any strut may be replaced within the next 250 hours time in service provided:

(1) they are not all next to each other in the same row of twelve (12); or

(2) they do not include more than two (2) which are next to each other in the same row of twelve (12) within six (6) inches of the strut end.

(d) Equivalent parts and inspection procedures must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(e) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector.

This amendment is effective December 20, 1968.

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