The U.S. aircraft register, updated daily
FAA orders · airworthiness directive · current

2005-24-05: Quill shaft

FAA order 2005-24-05 is an airworthiness directive in force since December 8, 2005. The FAA's subject line: Quill shaft. It names Boeing-Vertol 107: about 7 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: rotorcraft systems.

What it applies to as the FAA lists it

Kind of product
Aircraft
Makes
Columbia Helicopters, Inc.
Models
107-II
On this site
Boeing-Vertol 107 7 registered

Dates and paperwork

In force since
December 8, 2005
Published
November 23, 2005 (signed November 16, 2005)
Docket
FAA-2005-23085
Status
Current
The FAA's document
Read the order on the FAA's site

The FAA's summary their words, unchanged

This amendment adopts a new airworthiness directive (AD) for Boeing Vertol (Boeing) Model 107-II helicopters. This action requires a visual and magnetic particle inspection of the quill shaft. This amendment is prompted by the discovery of cracks in a quill shaft during a routine inspection. The actions specified in this AD are intended to detect a fatigue crack in a quill shaft and prevent separation of the quill shaft between the aft transmission and the mix box assembly, loss of rotor synchronization, and subsequent loss of control of the helicopter.

The order itself the regulatory text, as published

Show the full text (2,212 characters)
2005-24-05 Boeing Vertol (Boeing): Amendment 39-14385. Docket No. FAA-2005-23085; Directorate Identifier 2005-SW-25-AD. Applicability: Model 107-II helicopters, all serial numbers, with a quill shaft, part number (P/N) 107D2067, all dash numbers, and a spiral bevel pinion gear (pinion gear), P/N 107D2215, installed, certificated in any category. Compliance: Required as indicated. To detect a fatigue crack in a quill shaft to prevent separation of the quill shaft between the aft transmission and the mix box assembly, loss of rotor synchronization, and subsequent loss of control of the helicopter, accomplish the following: (a) For a helicopter with a pinion gear installed with the following hours time-in-service (TIS): Pinion gear hours TIS Compliance time 700 or more hours TIS Within 50 hours TIS, unless accomplished within the previous 350 hours TIS. Less than 700 hours TIS On or before reaching 750 hours TIS. (1) Remove the aft transmission assembly, separate the mix box assembly from the aft transmission, and remove the quill shaft from the pinion gear assembly; (2) Visually inspect the external spline of the quill shaft for a chipped or cracked tooth around the pinhole; and (3) Magnetic particle inspect the quill shaft for a crack. (b) Before further flight, replace any quill shaft that has a crack or a chipped or cracked tooth with an airworthy quill shaft. Note 1: Boeing Service Bulletin No. 107-63-1005, Revision 1, dated April 27, 2005, pertains to the subject of this AD. Note 2: Replacement quill shafts manufactured by Kawasaki Heavy Industries (KHI) for use on their Model KV107-II helicopters must be approved by the geographic Aircraft Certification Office (ACO) on a case-by-case basis for installation on a Boeing Model 107-II helicopter. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, New York ACO, Engine and Propeller Directorate, FAA, for information about previously approved alternative methods of compliance. (d) Special flight permits will not be issued. (e) This amendment becomes effective on December 8, 2005.

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 5, 2026. Connections as data: /graph/directive/2005-24-05.json · aircraft systems.