66-05-01: Main Landing Gear Drag Struts
FAA order 66-05-01 is an airworthiness directive in force since February 25, 1966. The FAA's subject line: Main Landing Gear Drag Struts. It names Curtiss Wright C-46: about 8 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: landing gear.
What it applies to as the FAA lists it
- Kind of product
- Aircraft
- Makes
- Airlift International, Inc.; Curtiss-Wright Corporation; Flying Tiger Line, Inc.; L. B. Smith Aircraft Corporation; Skyways International Trading and Transport Co.; Tempo Design Corporation
- Models
- C-46A, C-46D, C-46F, C-46R, C-46E, C-46A, C-46D, C-46E, C-46F, C-46A, C-46D, C-46F, C-46F, C-46/CW20-T, Super C-46/CW20-T
- On this site
- Curtiss Wright C-46 8 registered
Dates and paperwork
- In force since
- February 25, 1966
- Docket
- Unknown
- Status
- Current
- The FAA's document
- Read the order on the FAA's site
The order itself the regulatory text, as published
Show the full text (2,622 characters)
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 inaccordance 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.
Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 7, 2026. Connections as data: /graph/directive/66-05-01.json · aircraft systems.