Document ID: chunk:federal_register_of_legislation:F2007L01729:body:0:p3
Version: federal_register_of_legislation:F2007L01729
Segment Type: other
Provision Reference: 
Character Range: 9337–12752

- Engine start selector (ATA 24, 80)
   F-2001-214-084     30 May 2001        Propeller feathering -ATPCS test selector switch (ATA 24, 61)
   F-2001-387-085     5 September 2001   Flight controls - Normal pitch trim switches
   F-2001-554-087 R1  2 October 2002     Wing to fuselage fairing panel (ATA 53)
   F-2002-071-091     23 January 2002    Engines - High pressure oil pump - Pressure Regulating Valve (PRV) (ATA 79)
   F-2002-090-092     20 February 2002   Electrical rack 90VU - Wire bundle routing on 93, 94 and 95VU carbon shelves (ATA 92)
   F-2002-431         21 August 2002     Flight controls - Pitch control interface
   F-2002-539         30 October 2002    Forward attendant seat (ATA 25)
   F-2003-106 R1      16 April 2003      Flight controls - Stand by pitch trim switch (ATA 92)
   F-2003-376         1 October 2003     Main Landing Gear - Swinging lever (ATA 32)
   F-2004-191         22 December 2004   Wings - Outer wing boxes - Upper skin and ribs
   F-2005-160         12 October 2005    Fuel - Fuel quantity indicators

             Table 2
             EASA AD                                                                                                                                                                                                                                                                                                                                        Issue Date         Title
             2006-0216-E                                                                                                                                                                                                                                                                                                                                    14 July 2006       Main Landing Gear - Shock absorber - Cross locking bolt of the attachment pin
             2006-0283                                                                                                                                                                                                                                                                                                                                      14 September 2006  Electrical Power - 120 VU Electrical Harness - Inspection
             Note:  EASA and DGAC ADs may be accessed via the internet at the following URLs:

                  http://ad.easa.europa.eu/

                 http://www.gsac.fr/php/P_ConsignesNav.php
Compliance:  For Requirements 1 and 2 - Within 30 days after the effective date of this Directive or prior to the issue of a Certificate of Airworthiness, whichever occurs first.
             This Airworthiness Directive becomes effective on 22 June 2007.
Background:  The DGAC and EASA ADs listed in Table 1 and 2 of this Directive require one time actions for which the compliance date and/or period has passed.  CASA has determined that these ADs may be applicable to recently registered or imported Australian aircraft.  This Directive is issued to ensure all State of Design ADs are complied with.
             CASA appreciates that, due to date of aircraft manufacture or aircraft configuration and modification status, not all the ADs listed in Table 1 and 2 will be applicable to all ATR 42 series aeroplanes.

David Punshon
Delegate of the Civil Aviation Safety Authority

8 June 2007