AD/F100/81 - Autopilot Disconnect Unit (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.

Fokker F100 (F28 Mk 100) Series Aeroplanes AD/F100/81 Autopilot Disconnect Unit 9/2006

Applicability: F28 Mark 0070 and 0100 aeroplanes. Requirement: Modify the aeroplane in accordance with Section 3 - Accomplishment Instructions of Fokker Service Bulletin SBF100-22-050 dated 25 April 2006 or later EASA approved revision. Note: CAA-NL AD NL-2006-010 (EASA Approval 2006-0195) refers. Compliance: Within 36 months after the effective date of this Directive. This Airworthiness Directive becomes effective on 31 August 2006. Background: The Netherlands Civil Aviation Authority (CAA-NL) has advised that to date, there have been at least 10 reported events on Fokker 70 (F28 Mark 0070) and Fokker 100 (F28 Mark 0100) aircraft where the flight crew manually overpowered the autopilot, inadvertently neglecting to disengage the autopilot. Detailed investigation of these incidents has shown that this usually occurs in a high workload environment that demands immediate manual control of the aircraft by the pilot flying, eg terrain warning. When the autopilot is not disengaged, the elevator servomotor is overpowered and the horizontal stabilizer is moved by the Automatic Flight Control & Augmentation System (AFCAS) auto-trim in a direction opposite to the (manual) deflection of the elevator, causing high elevator control forces. This condition, if not corrected, could cause the stabilizer to move to an extreme out-of-trim position, creating the (remote) possibility of loss of control of the aircraft, due to the extreme control loads.