AD/EMB-110/16 Amdt 2 - Control Column P/N 4A-500-10-01-20 - Inspection (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/EMB- 110/16 Amdt 1 and issues the following AD under subregulation 39.1 (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.

Embraer EMB-110 (Bandeirante) Series Aeroplanes

AD/EMB-110/16 Amdt 2

Control Column P/N 4A-500-10-01-20 - Inspection

12/2003

DM

Applicability: All models of EMB-110.

Requirement: To prevent failure of the control column assembly in flight, perform the following:

1. With the aid of a 4X-6X magnifying glass, visually inspect the control column walls, and the region adjacent to the two sharp corner of the aileron control chain access trim cover.

(a) If any cracks less than 10mm in length are detected, they shall be stop drilled using a 2 (two) mm diameter drill bit.

(b) If any cracks greater than 10mm in length are detected, repair them by manufacturing and installing a reinforcement plate in accordance with the instructions contained in Embraer Alert S/B 110-27-A59.

2. If a permanent repair (reinforcement patch) has been performed in accordance with Embraer Alert S/B 110-27-A59, inspect the condition of the repair for cracks in the weld, reinforcement patch or control column walls. Compliance: 1. Before further flight and thereafter at 250 hour intervals (if no cracks were found in the initial inspection), until the permanent repair (reinforcement patch) is incorporated per Embraer Alert S/B 110-27-A59. Installation of the reinforcement patch is terminating action for Requirement 1 of this AD. (a) The crack shall be stop drilled before further flight in accordance with requirement 1a of this AD, and then permanently repaired in accordance with requirement 1b of this AD, within 50 hours time in service after stop drilling the crack. The inspection per Requirement 1 shall be carried out daily/overnight until the permanent repair is carried out. If, during the daily inspection, the crack is found to extend beyond the stop drill, perform the permanent repair in accordance with requirement 1(b), before further flight. (b) The crack shall be permanently repaired in accordance with requirement 1(b) of this AD, before further flight.