AD 65-09-02

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AD Number:
65-09-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS DC-6 Series Aircraft
Subject:
Main Gear Torque Links
Status:
Current
Citation:
(Federal Register: April 21, 1965)
Citation Publish Date:
04/21/1965
Effective Date:
05/21/1965
Make:
The Boeing Company
Model:
DC-6 | DC-6A | DC-6B
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Superseded AD: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Superseded By: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: 65-09-02
CITATION:   [Federal Register: April 21, 1965]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-56

AD NUMBER:   65-09-02

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS DC-6 Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective May 21, 1965

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-09-02 DOUGLAS: Amdt. 39-56 Part 39 Federal Register April 21, 1965. Applies to Model DC-6 Series Aircraft.

Compliance required as indicated.

Due to the failure of a main gear torque link, P/N 8065-46, the wheels and axle of the main gear rotated 180 degrees. To correct this condition, accomplish the following on torque links, Douglas P/N 8065-46, which have not been reworked in accordance with Douglas Service Engineering Letters C1-78-133/DJW dated January 28, 1964, C1-78-977/DJW dated June 22, 1964, or C1-78-1311/DJW dated August 11, 1964, and attached service sketches:

(a) Within 600 hours' time in service after the effective date of this AD for torque links which have been installed on aircraft for 20,000 or more hours' time in service on the effective date of this AD, and prior to the accumulation of 20,600 hours' time in service for torque links which have been installed on aircraft for less than 20,000 hours' time in service on the effective date of this AD -

(1) Inspect for cracks in the area of the vertical webs adjacent to the trunnion holes, using a 10-power glass or an equivalent method approved by the Aircraft Engineering Division, FAA Western Region.

(2) Torque links with cracks greater than 0.170 inch in depth shall be replaced before further flight with torque links reworked in accordance with Douglas Service Engineering Letters C1-78-133/DJW dated January 28, 1964, C1-78-977/DJW dated June 22, 1964, or C1-78-1311/DJW dated August 11, 1964.

(3) Torque links with cracks 0.170 inch in depth or less shall be:

(i) Reworked before further flight in accordance with Douglas Service Engineering Letter C1-78-1311/DJW dated August 11, 1964, and Douglas Service Sketch No. 608-A attached thereto, or an equivalent method approved by the Aircraft Engineering Division, FAA Western Region; or

(ii) Replaced before further flight with torque links reworked in accordance with Douglas Service Engineering Letters C1-78-133/DJW dated January 28, 1964, C1-78-977/DJW dated June 22, 1964, or C1-78-1311/DJW dated August 11, 1964.

(4) If no cracks are found, repeat the inspection described in subparagraph (1) at intervals not to exceed 600 hours' time in Service from the last inspection.

(b) The repetitive inspections required by (a)(4) may be discontinued on torque links reworked in accordance with (a)(3).

(c) Operators who have not kept records of hours' time in service on individual torque links shall substitute airplane hours' time in service in lieu thereof.

(d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western 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 such operator.

(Douglas Service Engineering Letter C1-78-1311/DJW dated August 11, 1964, and Service Sketch No. 608-A attached thereto, cover this same subject.)

This directive effective May 21, 1965.


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