AD/Beech 200/73 Main Landing Gear Actuator Nut (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Beechcraft 200 (Super King Air) Series Aeroplanes

AD/BEECH 200/73 Main Landing Gear Actuator Nut 9/2006

Applicability:

Main Landing Gear (MLG) Actuator nut assembly, part number (P/N)
GMD115-810029-17 or P/N GMD115-810029-23, for the right MLG actuator installed on, but not limited to, the following Raytheon Aircraft Company (Raytheon) (formerly Beech) aeroplanes that are not equipped with a hydraulic MLG or modified to a hydraulic MLG.

Models	Serial Nos.
200	BB-2, BB-6 through BB-733, BB-735 through BB-792, BB-794 through BB-828, BB-830 through BB-853, BB-872, BB-873, BB-892, BB-893, and BB-912 (except aircraft that incorporate Beech Kit No. 101-8018).
		B200	BB-734, BB-793, BB-829, BB-854 through BB-870, BB-874 through BB-891, BB-894, BB-896 through BB-911, BB-913 through BB-1157, BB–1159 through BB-1166, and BB-1168 through BB-1192 (except aircraft that incorporate Beech Kit No. 101-8018).
				200T and B200T	BT-1 through BT-30 (except aircraft that incorporate Beech Kit No. 101-8018).
200C and B200C	BL-1 through BL-72 (except aircraft that incorporate Beech Kit No. 101-8018).
200CT and B200CT	BN-1 through BN-4 (except aircraft that incorporate Beech Kit No. 101-8018).
A200CT (FWC–12D)	FG-1 and FG-2 (except aircraft that incorporate Beech Kit No. 101-8018).

Requirement:

1.    Check the maintenance records to determine whether the following replacements have been made:

a)    Actuator nut assembly, P/N GMD115-810029-17, for the right MLG actuator; or

b)    Actuator nut assembly, P/N GMD115-810029-23, for the right MLG actuator.

2.    If you find as a result of the check required by requirement 1 of this AD that there is no record of the specified assembly replacement, inspect the aeroplane, in accordance with General Machine Diecron Inc. Service Bulletin GM-D
32-30-01/102505 dated 21 November 2005, for installation of the following:

a)    Actuator nut assembly, P/N GMD115-810029-17, for the right MLG actuator; or

b)    Actuator nut assembly, P/N GMD115-810029-23, for the right MLG actuator.

You may choose to do the inspection detailed in requirement 2 of this AD without doing the maintenance records check detailed in requirement 1 of this AD.

3.    If during the check required by requirement 1 or the inspection required by requirement 2 of this AD, you find either actuator nut assembly, P/N
GMD115-810029-17 or P/N GMD115-810029-23, for the right MLG actuator, replace the specific assembly, with a new actuator nut assembly, P/N
GMD115-810029-23B or approved equivalent P/N in accordance with General Machine Diecron, Inc. Service Bulletin GM-D 32-30-01/102505.

4.    Do not install any actuator nut assembly, P/N GMD115-810029-17 or P/N GMD115-810029-23, for the right MLG actuator.

Note:  FAA AD2006-12-25Amdt 39-14651 dated 9 June 2006 refers.

Compliance:

1.    Within the next 50 hours time-in-service (TIS) or 30 calendar days after the effective date of this AD, whichever occurs first, unless already done.

2.    Within the next 50 hours TIS or 30 calendar days after the effective date of this AD, whichever occurs first, unless already done.

3.    Before further flight after the check required by requirement 1 or the inspection required by requirement 2 of this AD.

4.    From the effective date of this AD.

This Airworthiness Directive becomes effective on 31 August 2006.
Background:	This AD results from several reports of failures of the actuator nut assembly, P/N GMD115-810029-17 and P/N GMD115-810029-23, on the right MLG actuator.  The actions specified in this AD are intended to prevent failure of the actuator nut assembly for the right MLG actuator, which could result in failure of the MLG.  This failure could prevent the extension or retraction of the MLG.

James Coyne
Delegate of the Civil Aviation Safety Authority

21 July 2006