AD/DO 228/15 - Aileron Trim Actuator and Rod Spring Lever Attachment Bracket (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.

Dornier 228 Series Aeroplanes AD/DO 228/15 Aileron Trim Actuator and Rod 2/2009 DM Spring Lever Attachment Bracket

Applicability: Model 228-100, -101, -200, -201, -202, and -212 aircraft, all serial numbers. Requirement: 1. Accomplish inspection for "unequal aileron steering wheel force" in accordance with paragraphs A(1) through A(3) of the Accomplishment Instructions of RUAG Aerospace Service Bulletin (SB) No. SB-228-275 original issue, or later EASA approved revision.

If a defect is evident or suspected, before further flight, modify the attachment bracket riveting in accordance with paragraph B of the Accomplishment Instructions of SB No. SB-228-275 original issue, or later EASA approved revision.

2. Modify the attachment bracket riveting in accordance with paragraph B of the Accomplishment Instructions of SB No. SB-228-275 original issue, or later EASA approved revision.

Note: EASA AD 2008-0217 refers. Compliance: 1. Within 10 flight hours after 24 December 2008.

2. Unless already accomplished, within 300 flight hours after 24 December 2008. This Airworthiness Directive becomes effective on 24 December 2008. Background: Reports were received of loose rivets on the aileron trim actuator and rod spring lever attachment bracket between frame 18 and 19 left hand. This condition, unless detected and corrected, could lead to separation of the attachment bracket which could result in loss of aileron trim and loss of artificial force feedback; and consequent reduced controllability of the aircraft.