AD 66-05-01

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AD Number:
66-05-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
CURTISS-WRIGHT Model C-46 Series Airplanes
Subject:
Main Landing Gear Drag Struts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/25/1966
Make:
Airlift International, Inc. | Curtiss-Wright Corporation | Flying Tiger Line, Inc. | L. B. Smith Air...Show more
Model:
C-46A | C-46D | C-46F | C-46R | C-46E | C-46/CW20-T | Super C-46/CW20-T
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Superseded AD: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Superseded By: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: 66-05-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-183

AD NUMBER:   66-05-01

SUBJECT HEADING:   CURTISS-WRIGHT Model C-46 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 25, 1966.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
66-05-01 CURTISS-WRIGHT: Amdt. 39-183 Part 39 Federal Register January 26, 1966. Applies to Model C-46 Series airplanes.

Compliance required as indicated.

To prevent failure of the main landing gear drag struts, accomplish the following, unless already accomplished:

(a) Within the next 200 hours' time in service after the effective date of this AD, inspect the weld in the main landing gear drag strut that joins the lower end fittings, P/N 20-310- 1018-2, to the drag strut tubes, P/N's 20-310-1017-7 and -8, for the presence of a space or notch formed by the filleted shoulder on the end fitting and the weld. If the weld bead does not extend from the strut to the outer edge on the shoulder of the fitting, completely filling the area between the tube and the shoulder, this area must be inspected for external and internal cracks using X-ray or an FAA-approved equivalent. If cracks are found, the drag strut must be replaced before further flight.

(b) When inspected in accordance with (a), if the weld bead extends from the drag strut tube, P/N's 20-310-1017-7 and -8, to the outer edge on the shoulder of the lower end fitting, P/N 20-310-1018-2, completely filling the area between the tube and the shoulder, no further inspections are required by this AD.

(c) When inspected in accordance with (a), if the weld bead does not extend from the drag strut tube, P/N's 20-310-1017-7 and -8, to the outer edge on the shoulder of the lower end fitting, P/N 20-310-1018-2, completely filling the area between the tube and the shoulder, compliance with (c)(1) or (2) is required.

(1) Reinspect struts, inspected in accordance with (a) at intervals not exceeding 400 hours' time in service from the last inspection. Replace cracked parts before further flight.

(2) Fill in the space or notch between the tube and the shoulder using an FAA-approved method or replace the affected assembly with an assembly on which the space or notch does not exist. If the space or notch is filled in or if the affected part is replaced with an assembly on which the space or notch does not exist, no further inspections are required by this AD.

(d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern 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.

This supersedes AD 61-22-5.

This directive effective February 25, 1966.

FOOTER: