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. Avions de Transport Regional ATR 42 Series Aeroplanes AD/ATR 42/1 State of Design Airworthiness Directives 8/2007 DM Applicability: ATR 42 series aeroplanes, as identified in the individual Airworthiness Directive (AD) listed Tables 1 and 2. Requirement: 1. Determine the applicability of the ADs issued by the Direction Générale de l'Aviation Civile of France (DGAC), listed in Table 1, and the ADs issued by the European Aviation Safety Agency (EASA), listed in Table 2. 2. If it is determined that an DGAC or EASA AD listed in Table 1 or 2 is applicable and has not been previously accomplished, perform the actions required by that AD. Table 1 DGAC AD Issue Date Title F-1986-085-002 R1 28 May 1986 Oil cooling system F-1986-078-001 R1 23 July 1986 Ipeco pilot and copilot seats - ATR Airplanes F-1986-130-003 R1 26 March 1997 Flaps 45º Configuration F-1987-022-004 4 January 1987 Automatic stop of the flight and cockpit voice recorders F-1987-046-005 R1 10 June 1987 Attitude and heading system F-1987-155-007 10 November 1987 Elevator trims F-1987-156-008 R1 16 November 1988 Propeller brake control system F-1987-173-009 9 December 1987 Protection for auto pilot roll actuator F-1988-051-010 R2 21 February 1990 Fuel quantity indicators F-1988-070-011 11 May 1988 Rudder control channel cables F-1988-080-012 22 June 1988 Engine and propeller flexible control shafts F-1988-092-013 17 August 1988 Honeywell-Sperry navigation equipment F-1988-135-014 19 October 1988 Main gear wheel bearing F-1988-147-015 16 November 1988 Propeller brake control pushbutton F-1988-186-016 R1 31 May 1989 Test system of the smoke detectors in cargo compartment areas F-1989-033-019 R1 31 May 1989 Pitch trim F-1989-042-018 R1 5 April 1989 Oil pressure transmitter manifold F-1989-067-020 R2 20 March 1991 Main L/G retraction jacks fitting bolts F-1989-077-021 R2 19 July 1989 Aileron tab inboard hingepin F-1989-093-022 28 June 1989 Automatic cut-off of the voice recorders F-1989-197-025 R1 4 April 1990 Fire extinguishing system F-1990-028-026 21 February 1990 Nose landing gear retraction system F-1990-029-027 21 February 1990 Emergency lighting F-1990-030-028 R1 23 January 1991 Propeller brake F-1990-109-029 13 June 1990 Main frames F-1990-155-030 R1 27 November 1991 Emergency oxygen system for cabin attendants F-1990-163-031 3 October 1990 Structure modification resulting from fatigue tests landing gear bay area F-1990-193-032 R2 8 July 1992 Hydraulic system - Low pressure warning F-1990-201-033 R2 23 April 1997 Flight controls F-1991-005-036 9 January 1991 Nose landing gear F-1991-068-039 20 march 1991 Flight controls F-1991-081-040 R1 6 June 1991 Main landing gear F-1991-157-041 31 July 1991 Nose landing gear F-1991-214-042 2 October 1991 Flight controls F-1991-216-043 R1 22 January 1992 Engine and propeller flexible controls F-1991-237-044 30 October 1991 Auto pilot F-1992-043-045 19 February 1992 Commercial furnishing F-1992-122-047 27 May 1992 ECE push-button F-1992-133-048 R1 19 August 1992 Pitch control F-1992-197-049 30 September 1992 Autopilot F-1993-205-052 8 December 1993 Pitch trim controls F-1994-003-053 5 January 1994 Flight control rods F-1994-004-054 5 January 1994 Roll trim F-1994-005-055 5 January 1994 Nose Landing Gear Nardi hinge pins F-1994-162-056 6 July 1994 Karman fairing attachment clips F-1995-051-058 15 March 1995 Main landing gear side brace pin F-1995-103-059 24 May 1995 Protection of the electrical harness in front area F-1995-127-062 21 June 1995 Corrosion on wing rear spar (ATA 57) F-1996-109-063 5 June 1996 Engine nacelle drain system F-1996-131-064 3 July 1996 Main landing Gear - Pins Magnaghi F-1996-132-065 3 July 1996 Fuselage - Stringer 6 to frame 34 junction F-1996-208-067 R1 21 April 1999 De-icing procedures and protection improvements (ATA 30) F-1996-230-066 23 October 1996 Standby horizon - Power supply F-1996-256-068 6 November 1996 Stick shaker/pusher system F-1996-289-069 R1 18 December 1996 Forward cargo compartment nets F-1997-115-070 R1 11 February 1998 Fuselage - Main landing gear actuator fitting F-1997-159-071 16 July 1997 Karman fairing panel fasteners F-1997-328-072 R1 19 November 1997 Flight controls - Rudder F-1998-069-073 11 February 1998 Engine mount and upper engine fairing stiffener fouling F-1998-070-074 11 February 1998 Rotron recirculation fan F-1999-014-076 R2 10 December 2003 Icing conditions - Revise the Airplane Flight Manual (AFM) F-1999-165-077 R1 12 July 2000 Severe icing conditions - Implement aircraft design enhancements (ATA 30) F-2000-189-078 3 May 2000 Landing Gears - Install modified uplock boxes (ATA 32) F-2000-281-078 R1 19 September 2001 Fire protection - Fire handles (ATA 26) F-2000-449-082 R2 19 September 2001 Take-off after use of type II or IV fluids - Appendix to the Flight Manual (ATA 04) F-2000-454-081 15 November 2000 Electrical system - 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