DGAC-INDONESIA List of Airworthiness Directives 2001

Transcription

1 PAGE - 1 AIRBUS A300, A310 SERIES AIRBUS INDUSTRIE, A310 aircraft and A aircraft, all certified models, all serial numbers, on which Airbus Industrie modifications Nos and have not been embodied in production AIRBUS INDUSTRIE, A310 aircraft, all certified models and all serial numbers on which Airbus Industrie modification and have not been embodied in production AIRBUS INDUSTRIE, A300, A310 and A , all certified models, all serial numbers equipped with MESSIER carbon brakes except for aircraft entirely equipped with MESSIER carbon brakes MB M318 (8 brake assemblies per aircraft) AIRBUS INDUSTRIE, A310 and A aircraft, all certified models all serial numbers fitted with Inertial Unit (IRU) Honeywell 10 MCU P/N. HG 1050BD02 or HG 1050BD AIRBUS INDUSTRIE, A300, A310 and A aircraft, all certified models and all serial numbers AIRBUS INDUSTRIE, A300, A310, and A aircraft, all certified models and all serial numbers except as listed in paragraph applicability of the reference AD AIRBUS INDUSTRIE, A310 aircraft, all certified models AIRBUS INDUSTRIE, A300, A310 and A aircraft, all certified models all serial numbers AIRBUS INDUSTRIE, A310 aircraft, all certified models and all serial numbers. DGAC France AD (B)R2. Fire protection - engine aand auxiliary power unit (APU) fire detection system. DGAC France AD (B). Fuselage - chafing plates of wing root. DGAC France AD (B)R1. Brakes - Flight Manual. DGAC France AD (B). Inertial reference system - Unit alignment. DGAC France AD (B)R1. Door surrounding - corrosion and fatigue inspection. DGAC France AD (B). Fuel tanks - electrical connections of the fuel level sensors. DGAC France AD (B). Throttle control - Inspection and modifications. DGAC France AD (B). Fuselage - Inspection of skin lap joints at the passenger doors and emergency exit doors (ATA 53). DGAC France AD (B)R3. Loss of auto-trim function (ATA 22) DGAC France AD (B)R1. AIRBUS INDUSTRIE, A310 aircraft. Throttle control - Inspection and modifications (ATA 76).

2 PAGE AIRBUS INDUSTRIE, A310 and A aircraft, all certified models and all serial numbers AIRBUS INDUSTRIE, A310 aircraft, all certified models and all serial numbers AIRBUS INDUSTRIE, A310 aircraft, all certified models and all S/Ns. except for aircraft on which mod has been embodied in production (SB.A in service), or on which SB. A has been embodied in service AIRBUS INDUSTRIE, A310 aircraft, all certified models and all serial numbers except for in-service aircraft on which Airbus Industrie modification (Airbus Industrie SB. A Rev.5) has been embodied AIRBUS INDUSTRIE, A310 aircraft equipped with Pratt & Whitney engines, as follows -A , (PWJT9D-7R4D1); - A (PWJT9D-7R4E1); -A (PW4125) and -A (PW4156A) AIRBUS INDUSTRIE, A310 aircraft, all certified models, all serial numbers equipped with Messier Carbon brakes as indicated in the reference AD AIRBUS INDUSTRIE, A310 aircraft, all certified models and all serial numbers AIRBUS INDUSTRIE, A310 aircraft, all certified models and all serial numbers AIRBUS INDUSTRIE, A310 aircraft, all certified models and all serial numbers, fitted with Honeywell 10 MCU inertial reference units, P/N. HG1050BD02 or HG1050BD05. DGAC France AD (B). Trimmable Horizontal Stabilizer - THSA life limit (ATA 27). DGAC France AD (B). Slat and flap power control units - Life limit of the pressure - Off Brakes (POBs)(ATA 27). DGAC France AD (B). Navigation - Pitot probes (ATA 34). DGAC France AD (B). APU - Starter feeder line terminal blokcs (ATA 24). DGAC France AD (B). Pratt & Whitney forward engine mount (ATA 10, 71). DGAC France AD (B)R1. Brakes - Flight Manual (ATA 04, 32). DGAC France AD (B). Thrust reverser - "ENG REV UNLK" procedure (ATA 78) DGAC France AD (B). Airspeed indication - airspeed fluctuations in icing condition. DGAC France AD (B). Navigation - Inertial Units.

3 PAGE AIRBUS INDUSTRIE, A310 aircraft, all certified models, all serial numbers except for aircraft on which Airbus Industrie mod has been embodied in production (Airbus SB. A in service). AIRBUS A330 SERIES AIRBUS INDUSTRIE, A330 aircraft models -202, -223, -301, -321, -322, -341 and -342 MSN's 0012 up to 0244 inclusive AIRBUS INDUSTRIE, A330 aircraft models -301, -321, -322, -341 and -342 which have not received Airbus Industrie modification (or Airbus Industrie SB A at initial issue or any further approved revision) AIRBUS INDUSTRIE, A330 aircraft, certified in all models which have received embodiment as listed in the reference AD AIRBUS INDUSTRIE, A330 aircraft models -301, -321, -322, -341 and -342 which have not received Airbus Industrie modification (or Airbus Industrie SB. A at initial issue or any further approved revision) AIRBUS INDUSTRIE, A330 aircraft models as listed in the reference AD AIRBUS INDUSTRIE, A aircraft MSN 240, 247 to 251, 253 to 255, 258, 259, 261, 262, 265, 266, 269, 271, 272, 275, 276, 281, 283, 285 to 288, 290, 291 that have not received Airbus Industrie SB. A330-55A AIRBUS INDUSTRIE, A330 aircraft, models -301, -321, -322, -341, -342 which have not received either Airbus Industrie modification 42418(or Airbus Industrie SB A at original issue or any further approved revision). DGAC France AD (B)R1. Centre tank metallic vapor seal. DGAC France AD (B). Wing - Trailing edge - Drain hole in skin panel 3 (bottom). DGAC France AD (B). Wings - Replacement of reinforcing plate rear pick-up. DGAC France AD (B)R1. Mid, aft and emergency type A pax/crew doors (doors 2, 3 and 4) - Emergency operation cylinder. DGAC France AD (B). Wings - Stringers 13 and 20 lower between rib 1 and rib 2. DGAC France AD (B). Inspection of the drive assemblies on the low-pressure and crossfeed fuel valves. DGAC France AD (B). Vertical stabilizer - Inspection and modification of the composite spar box. DGAC France AD (B). Inspection of lower flange and radius of floor beam between FR47 and FR48.

4 PAGE AIRBUS INDUSTRIE, A , -301, - 321, -322, -341 and -342 model aircraft except for aircraft that have received Airbus Industrie modification or Airbus Industrie SB A at original issue or any further approved revision AIRBUS INDUSTRIE, A , -321, - 341, and -342 model aircraft except for aircraft which have received modification or Airbus Industrie SB as listed in the reference AD AIRBUS INDUSTRIE, A330 aircraft models -202, -223, -243, -301, -322, -323, and -342 fitted with Sundstrand ram air turbine (RAT) and which have not received Airbus Industrie modification nor SB A Rev AIRBUS INDUSTRIE, A330 aircraft, all certified models, all serial numbers fitted with an FMGEC as listed in the reference AD AIRBUS INDUSTRIE, main landing gear - doors serial numbers as listed in the reference AD, installed on Airbus Industrie A330 aircraft AIRBUS INDUSTRIE, all A330 aircraft models, that have neither received Airbus Industrie modification in production nor Airbus Industrie SB A in service AIRBUS INDUSTRIE, A330 aircraft certified in all models, all serial numbers AIRBUS INDUSTRIE, A330 aircraft models, -202, -223, -243, -301, -321, -322, - 323, -341, -342 and -343, all serial numbers AIRBUS INDUSTRIE, A330 aircraft models, -202, -223, -301, -302, -322, -341, and -342 which have not received Airbus Industrie modification (or Airbus Industrie SB.A Rev.4. DGAC France AD (B). Improve bracket of the Green hydraulic reservoir. DGAC France AD (B). Frame 48 to 53.2 lower section at passage areas. DGAC France AD (B)R2. Sundstrand ram air. DGAC France AD (B)R1. Aircraft Flight Manual Temporary Revision "Incorrect Nav. Guidance upon F-PLN Sequencing". DGAC France AD (B)R3. Main landing gear - doors. DGAC France AD (B). Main landing gear - restrain for the attachment pin of the brake torque rod. DGAC France AD (B). Pax/crew emergency exit doors - Girt bar slider mechsnism. DGAC France AD (B). Airspeed indication - Airspeed fluctuations in icing conditions. DGAC France AD (B). Reinforcement of frame 40 (ATA 53).

5 PAGE AIRBUS INDUSTRIE, A330 aircraft, models -202, -223, -243, -301, -321, -322, - 323, -341, -342, and -343 which have not received Airbus Industrie mod (or Airbus Industrie SB. A at initial issue or any further approved revision) AIRBUS INDUSTRIE, A330 aircraft, models -301, -321, -322, -341, and -342, all serial numbers which have received none of the following modifications or SB.: - Mod.460 (or SB.A ); - Mod.46900; -Mod (or SB.A AIRBUS INDUSTRIE, A330 aircraft, models -202, -223, -243, -301, -321, -322, - 323, -341, -342, and -343, all serial numbers fitted with Trimmable Horizontal Stabilizer Actuator (THSA) P/N R1 AIRBUS INDUSTRIE, A330 aircraft, models -202, -223, -243, -301, -321, -322, - 323, -342, and -343, all serial numbers fitted with Trimmable Horizontal Stabilizer Actuator (THSA) P/N AIRBUS INDUSTRIE, A330 aircraft, certified in all models, all manufacturer serial numbers fitted with retraction links with following P/Ns (LH), (RH), (RH), (LH) AIRBUS INDUSTRIE, A330 aircraft, models as listed in the reference AD AIRBUS INDUSTRIE, A330 aircraft, certified in all models, all serial numbers AIRBUS INDUSTRIE, A330 aircraft model 341 all serial numbers, which have received Airbus Industrie mod production. DGAC France AD (B). CLG rear fixed panels (ATA 52). DGAC France AD (B). Fuselage - VHF2 antenna - Inspection for cracks detection and modification (ATA 53). DGAC France AD (B). THSA - Inspection of the ball-nut transfer tubes (ATA 27). DGAC France AD (B)R1. THSA - Inspection of the ball-nut transfer tubes (ATA 27). DGAC France AD (B). Main Landing Gear (MLG) - Inspection and replacement of the retraction link (ATA 32). DGAC France AD (B). Reinforcement of fuselage between FR 31 and FR 37.1 (ATA 53). DGAC France AD (B). Electrical and electronic installation - circuit breakers "Texas Instrument" P/N.E DGAC France AD (B). Inboard flap - Introduce new connection bolts on track 1 assembly (ATA 27, 57).

6 PAGE AIRBUS INDUSTRIE, model 341 except for aircraft which have received Airbus Industrie mod. Airbus Industrie SB. - Airbus Industrie mod or - Airbus Industrie mod (or SB.A at original issue or any further approved revision) AIRBUS INDUSTRIE, A330 aircraft, all certified models, all serial numbers AIRBUS INDUSTRIE, Airbus A330, models -301, -321, -322, -341, and -342 except aircraft which have received mod in production or modified in service in accordance with SB.A at original issue or any further approved rev AIRBUS INDUSTRIE, A330, models -202, - 223, -243, -301, -321, -322, -323, -341, - 342, and -343, all serial numbers except aircraft modified in production by Airbus Industrie mod AIRBUS INDUSTRIE, A , -341, - 342, and -343 aircraft series, with Rolls- Royce (RR)T700 engines AIRBUS INDUSTRIE, A aircraft series, all certified models, all serial numbers equipped with Basic Main strut and dressing (P/N xxx to xxx) AIRBUS INDUSTRIE, A330 aircraft, models -202, -223, -243, -301, -321, -322, - 323, -341, -342, and -343, all serial numbers fitted with Trimmable Horizontal Stabilizer Actuator (THSA)P/N or AIRBUS INDUSTRIE, A330 aircraft, models -202, -223, -243, -301, -321, -322, - 323, -341, -342, and -343, all serial numbers equipped with escape slide P/N. 7A1509- XXX at the door 3 type 1. DGAC France AD (B). Aft cargo compartment door inspection (ATA 52). DGAC France AD (B). Flight control primary computer (FCPC) - MMEL Temporary Revision (ATA 27). DGAC France AD (B). Wing rear spar - Inspection of the upper build slot between rib 1 and 2 (ATA 57). DGAC France AD (B). Vertical stabilizer - Desynchronization of rudder servocontrol (ATA 27, 55). DGAC France AD (B). RR engine stall and shut down during acceleration from idle. DGAC France AD (B). Landing gear - life limits. DGAC France AD (B). THSA - Inspection of the ball-nut transfer tubes (ATA 27). DGAC France AD (B). Emergency door 3 Type 1 (LH & RH) - Escape slide parachute pin (ATA 25).

7 PAGE AIRBUS INDUSTRIE, A330 aircraft, models -301, -321, -341, and -342, which have not received in production any of Airbus Industrie mod or AIRBUS INDUSTRIE, A330 aircraft models -321, -322, -323, -341, -342 and which have not received Airbus Industrie mod.46902, or Airbus SB.A R1 and mod.46904, or Airbus SB.A R AIRBUS INDUSTRIE, A330 aircraft models -301, -321, -322, -341, and -342 all serial numbers except aircraft has been modified in accordance with the reference AD AIRBUS INDUSTRIE, A330 aircraft models -301, -321, -322, -341, and -342 all serial numbers except aircraft has been modified in accordance with the reference AD. BAe 146 and AVRO 146-RJ SERIES BRITISH AEROSPACE, BAe 146 and Avro 146RJ aircraft post mod. HCM50070A, B, C or D BRITISH AEROSPACE, Avro 146-RJ85 aircraft E2302, E2303, E2304, E2305 and E BRITISH AEROSPACE, Avro 146-RJ85 series aircraft with modification HCM1080W embodied BRITISH AEROSPACE, BAe , - 200, and -300 series aircraft with modification HCM50261X and (HCM01088L or HCM50273B) and HCM50040E or HCM50040N) embodied BRITISH AEROSPACE, BAe , - 200, and -300 series aircraft and Avro 146- RJ70, RJ85 and RJ100 series aircraft. DGAC France AD (B)R2. Yaw damper actuator "SAMM" and FCPC standard M12 (ATA 27). DGAC France AD (B)R2. Main Landing Gear - Replacement of pivot pins, bellcrank assemblies and miscellaneous pins (ATA 32). DGAC France AD (B). Navigation - Pitot probes (ATA 34). DGAC France AD (B). Navigation - Pitot probes (ATA 34). CAA AD Air conditioning - Environmental control system - To inspect part numbers on forward and aft pressurisation discharge valves and flight deck mounted pressure controller. CAA AD Wings - To replace bolts (left and right side) on wing rear spar at centre fuel tank. CAA AD Navigation - Pitot static system - To inspect S4 and S5 static pipes. CAA AD Navigation - To introduce diodes to prevent TCAS audio remaining inhibited following a GPWS warning. CAA AD Electrical power - To introduce a Vickers standby generator Part in lieu of the existing Vickers unit.

8 PAGE BRITISH AEROSPACE, BAe , - 200, and Avro RJ85 series aircraft. BELL 407 SERIES BELL HELICOPTER TEXTRON CANADA (BHTC), model 407 helicopters BELL HELICOPTER TEXTRON CANADA (BHTC), model 407 helicopters, S/Ns through BELL HELICOPTER TEXTRON CANADA (BHTC), model 407 helicopters, S/Ns through with tailbooms P/N , -105 and -107 installed. BELL 412 SERIES BELL HELICOPTER TEXTRON INC. (BHTI), model 412, 412CF, and 412EP helicopters, with tail rotor yoke assembly, P/N all fdash numbers. BELL 430 SERIES BELL HELICOPTER TEXTRON CANADA (BHTC), model 430 helicopters, S/Ns and prior BELL HELICOPTER TEXTRON CANADA (BHTC), model 430 helicopters. BOEING 737 SERIES R1 BOEING, model and -200C series airplanes, line numbers 6 thru 873 inclusive; Model , -200C, -300 and -400 series airplanes; line numbers 874 thru 1642 inclusive equipped with an aft cargo door having Boeing P/N or BOEING, all model B , -200C, - 300, -400, and -500 series airplanes, CAA AD Landing Gear - Nose landing gear - Inspection for correct torque tightening of cap screw. DOT Canada AD CF Never-Exceed Speed Reduction. Transport Canada AD CF K-Flex Shaft. Transport Canada AD CF R1. Tailboom inspection. FAA AD Prevent static and dynamic overload damage to the tail rotor yoke (yoke). DOT Canada AD CF To comply with IFR and Category A certification regulations. DOT Canada AD CF Prevent potential loss of control of the helicopter. FAA AD R1. To prevent fatigue cracking of the corners of the doorframe and the cross beams of the aft cargo door, which could result in rapid depressurization of the airplane. FAA AD To prevent fatigue cracking of the lower corners of the door frame and cross beam of the forward cargo door, which could result in rapid depressurization of the airplane.

9 PAGE BOEING, model and -200C series airplanes; on which the left-or right-hand inboard flap tracks of the wing outboard flap have a part number (P/N) as listed in the reference AD BOEING, all model B , -400, and series airplanes, certificated in any BOEING, model , -400, and -500 series airplanes, BOEING, model , -400, and -500 series airplanes, certificated in any category, as listed in Boeing ASB A1208, dated May 6, BOEING, model and -300 series airplanes, equipped with a main deck cargo door installed in accordance with Supplemental Type Certificate (STC) SA2969SO; BOEING, all model 737 series airplanes, BOEING, model and -300 series airplanes equipped with main deck cargo door installed in accordance with supplemental type certificate (STC)SA2969SO, certificated in any BOEING, model 737 and 747 series airplanes equyipped with chemical oxygen generator, certificate in any category; as listed in Boeing special attention SB.of the reference AD. FAA AD To detect and correct damage of the aft end of each inboard flap track of the wing outboard flap, which could result in loss of the outboard trailing edge flap and consequent loss of controllability of the airplane. FAA AD To prevent a severe asymmetric thrust condition during flight which could result in loss of control of the airplane. FAA AD To detect and correct chafing and to prevent electrical contact between the fuel quantiry indicating system (FQIS) wiring and the surrounding structure which, in conjunction with another wiring failure outside the fuel tank, could result in fire or explosion of the fuel tank. FAA AD To detect fatigue cracking of the forward pressure bulkhead, which could result inrapid decompression of the airplane fuselage. FAA AD To detect and correct cracking of the lower portion of the main deck cargo door frames, which could result in sudden depressurization, loss or opening of the main deck cargo door during flight, and loss of control of the airplane. FAA AD To prevent ignition of fuel vapors due to the generation of sparks and a potential ignition source inside the center tank caused by metal-to-metal contact during dry fuel pump operation, which could result in a fire or explosion of the fuel tank. FAA AD To prevent in-flight separation of the main deck cargo door from the airplane. FAA AD To find and fix incorrect installation of the release pin in the generator firing mechanism of the chemical oxygen generator, which could result in the unavailability of the supplemental oxygen and possible incapacitation of passengers and cabin crew during an in-flight decompression.

10 PAGE BOEING, model , -200, -300, -400 and -500 series airplanes BOEING, model 737 and 747 series airplanes certificated in any category, as specified in the Boeing SB as listed in the reference AD BOEING, all model , -400, and series airplanes, certificated in any BOEING, model series airplanes, modified by Supplemental Type Certificate (STC) ST00171SE, certificated in any BOEING, model , -200 series airplanes, as listed in Boeing SB , dated April 4, 1991; certificated in any BOEING, model airplanes without high gross weight flaps installed, certificated in any BOEING, model and -200C series airplanes; as listed in Boeing SB , Rev.4, dated April 16, 1992; BOEING, model , and -200 series airplanes, line numbers 1 through 310 inclusive, and 323; certificated in any FAA AD To prevent failure of the motor operated hydraulic shutoff valves, which could result in leakage of hydraulic fluid to the engine fire zone, reduced ability to retract the landing gear, loss of backup electrical power or other combinations of failures, and consequent reduced controllability of the airplane. FAA AD To prevent unrestrained movement of the passenger seats during high forward deceleration of the airplane, which could result in injury to the passengers or crew members during an emergency landing. FAA AD To detect and correct discrepancies of certain connectors located in the main wheel wells, which could result in electrical arcing of the connectors, uncommanded movement of the engine fuel shut-off valves to the close position, and consequent in-flight loss of thrust or engine shutdown from lack of fuel. FAA AD To ensure that the flight crew is able to remove electrical power from the in-flight entertainment (IFE) system when necessary and as advised of appropriate procedures for such action. FAA AD To prevent failure of the main deck floor beams at certain body station (BS) due to fatigue cracking, which could result in rapid decompression and consequent reduced controllability of the airplane. FAA AD To prevent severe flap asymmetry due to fractures of both carriage spindles at an outboard midflap, which could result in loss of controllability of the airplane. FAA AD To detect and correct cracks in the floor beams at the aileron control quadrant cutout and in the floor beams and pressure web transverse beams above the main wheel well, which could result in rapid loss of cabin pressure and reduced structural integriry of the airplane. FAA AD To detect and correct cracking or corrosion of the upper and lower chords of the front and rear spars of the wing, which could result in reduced structural integrity of the wing.

11 PAGE BOEING, all model , -300, -400, and -500 series airplanes line numbers 1 through 706 inclusive, certificated in any BOEING 747 SERIES BOEING, all model B , 747SP, and 747SR series airplanes, certificated in any category; equipped with Pratt & Whitney JT9D-7, -7A, -7F and -7J series engines BOEING, model 747 series airplanes, line numbers 1 through 685 inclusive, BOEING, model 747 series airplanes having the line numbers 1 through 1234 inclusive except line numbers 1174, BOEING, all model , -200B, - 200C, -200F, -400, -400D, -400F, and 747SR series airplanes, certificated in any BOEING, model 747 series airplanes, as listed in Boeing SB A2206, Revision 1, dated February 22, 2001, certificated in any BOEING, model , equipped with either a warning electronics unit (WEU) or a modular avionics warning electronic assembly (MAWEA) power supply having part number (P/N)285T ; BOEING, model series airplanes, certificated in any category, powered by General Electric CF6-45/50 series engines, or Pratt & Whitney JT9D-70 series engines. FAA AD To prevent chafing of wire bundles in four junction boxes in the main wheel well, which could result in arcing and consequent fire in the main wheel well or passenger cabin, or inability to stop the flow of fuel to an engine or to the auxilary power unit in the event of fire. FAA AD To prevent separation of the nose cowl from the engine, which could cause collateral damage to the airplane, and, possibly, reduced controllability of the airplane. FAA AD To prevent fatigue cracking of the frame web and doubler of the forward edge frame of main entry door number 1, which could result in inability of the dege frame to react door stop loads, and consequent rapid depressurization of the airplane. FAA AD To prevent potential ignition of the moisture barrier cover of the drip shield, which could propogate a small fire that result from an otherwise harmless electrical arc, leading to a large fire. FAA AD To prevent loss of a flap transmission, which could reduced lateral controllability of the airplane. FAA AD To find and fix discrepancies of the installation of the midspar fuse pins of the inboard and outboard strut, which could result in loss of the secondary retention capability of the fuse pins, and consequent loss of the strut and engine from the airplane. FAA AD To prevent failure of the WEU or MAWEA power supplies, which could result in loss of visual, aural, and tacticle alerts to the flightcrew (the absence of which could result in the flightcrew being unaware that an immediate or appropriate action should be taken in the event of an unsafe condition). FAA AD To detect and correct heat damage to the diagonal brace, which could cause cracking or fracture of the diagonal brace, and possible loss of the diagonal brace load path and consequent separation of the strut and engine from the airplane.

12 PAGE BOEING, model 747 series airplanes, line numbers (L/N) 1 through 1254 inclusive, BOEING, model 747 series airplanes, as listed in Boeing SB A2449, Rev.1, dated May 24, 2001, certificated in any BOEING, model and -200 series airplanes, modified by Supplemental Type Certificate (STC) SA8622SW, certificated in any BOEING, model 747 SP series airplanes, modified by Supplemental Type Certificate (STC) ST09097AC-D, certificated in any BOEING, model series airplanes, modified by Supplemental Type Certificate (STC) SAQ8843SW, certificate in any BOEING, model series airplanes, as listed in Boeing ASB A2451, including appendix A, dated October 5, 2000, BOEING, model 747 series airplanes line numbers 1 through 685 inclusive, certificated in any category; except as excluded in the table of the reference AD BOEING, model 747 series airplanes, certificated in any category, as listed in Boeing ASB A2203, dated August 31, 2000, except model 747 series airplanes having serial numbers and FAA AD To detect and correct fatigue cracking of the skin, splice fittings, bulkhead web, and outer chord of the body station (BS) 1480 bulkhead at the overwing longeron splice, which could result in reduced structural integrity of the fuselage and the inability to carry limit load. FAA AD To find and fix cracking in the bulkhead frame support at body station (BS) 2598 under the hinge support fitting of the horizontal stabilizer, which could result in inability of the structure to carry horizontal stabilizer flight loads and reduced controllability of the horizontal stabilizer. FAA AD To ensure that the flight crew is able to remove electrical power from the in-flight entertainment (IFE) system when necessary; which if not done during a non-normal or emergency situation, could resutlt in inability to control smoke or fumes in the airplane flight deck or cabin. FAA AD To ensure that the flight crew is able to remove electrical power from the passenger entertainment system (PES) when necessary and is advised of appropriate procedures for such action. FAA AD To ensure that the flight crew is able to remove electrical power from the entire passenger entertainment system (PES) when necessary and is advised of appropriate procedures for such action. FAA AD To find and fix fatigue cracks of the station 800 frame assembly that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. FAA AD To detect and correct fatigue cracking of nose wheel well (NWW) vertical beams and frames, which could result in collapse of the NWW pressure bulkhead and subsequent rapid decompression of the airplane. FAA AD To prevent loose fasteners and associated damage to the hanger fittings and strut forward bulkhead of the forward engine mount, which could result in separation of the engine from the airplane.

13 PAGE BOEING, model 747 series airplanes, line numbers 1 through 1307 inclusive, BOEING, model , and 747SP series airplanes powered by Pratt & Whitney JT9D- 7 series engines; as listed in Boeing ASB A2201, dated September 28, 2000; BOEING, model , and 747SP series airplanes equipped with titanium diagonal brace underwing fittings; as listed in Boeing ASB A2312, dated June 15, 2000, BOEING, model 747 series airplanes, as listed in Boeing SB A2310, Rev.2, dated February 22, 2001, certificated in any BOEING, model series airplanes, line numbers 1 through 1205 inclusive, certificated in any category and equipped with dual crown skin heat exchangers BOEING, model 747 series airplanes, BOEING, model 747 series airplanes, powered by Pratt & Whitney JT9D-7 series engines, as listed in Boeing ASB A2200, dated July 07, 2000, certificated in any BOEING, model series airplane, certificated in any category, equipped with General Electric (GE) CF6-80C series engines; as listed in Boeing SB , dated October 8, FAA AD To detect and correct cracking of the forward and aft inner chords, the frame support, and the splice fitting of the forward inner chord of the upper corner of the station 2598 bulkhead, which could result in reduced structural capability of the bulkhead and the inability of the structure to carry horizontal stabilizer flight loads. FAA AD To prevent cracking of the vertical chords adjacent to the lower spar fitting, which could result in separation of the diagonal brace load path and lead to separation of the strut and engine from the airplane. FAA AD To prevent loss of underwing fitting load path due to missing or damaged taperlock fasteners, which could result in separation of the engine and strut from the airplane. FAA AD To detect and correct cracking on the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and consequent reduced controllability of the airplane. FAA AD To detect and correct damage or deflection of the crew rest heat exchanger, which could result in jamming of the rudder or elevator control cables, and consequent reduced controllability of the airplane. FAA AD To find and fix cracking or corrosion of the aft trunnion of the wing landing gear, which could result in collapse of the wing landing gear and consequent reduced controllability of the airplane. FAA AD To detect and correct bushing migration, corrosion, or cracking of the lugs on the bulkhead fitting of the rear engine mount. FAA AD To prevent failure of the core cowl latches during an engine fire, and consequent in-flight separation of an engine core cowl and its strut fire barrier from the airplane.

14 PAGE BOEING, model , and -200 series airplanes, modified by supplemental type certificate (STC)ST00196SE, certificated in any BOEING, model 747 series airplanes, equipped with General Electric model CF6-45, or -50 series engines or Pratt&Whitney model JT9D-3, -7, or -70 series engines; BOEING, model 747 series airplanes, line numbers 1 through 685 inclusive certificated in any category, except as excluded in the table of the reference AD BOEING, model 747 series airplanes, line numbers 1 through 1251 inclusive, CESSNA AIRCRAFT CESSNA, model 172RG, with the S/Ns.691 and 172RG0001 through 172RG1191, CESSNA, models 172R, and 172S, all serial numbers, that are certificated in any CESSNA, 208 and 208B, Piper PA T and PA P; Raytheon (Beech) 58, 95-55, 95-C55, A36, B36TC, D55, and E55 series airplanes. DC-10 AND MD-11 SERIES McDONNELL DOUGLAS, DC-10 series airplanes McDONNELL DOUGLAS, DC-10 series airplanes, as listed in McDonnell Douglas ASB.DC10-29A142, Rev.01, dated October 21, FAA AD To ensure that the flight crew is able to remove electrical power from the in-flight entertainment (IFE) system when necessary and is advised of appropriate procedures for such action. FAA AD To prevent fatigue cracking or fracture of the steel attachment fittings of the diagonal brace to the nacelle struts, which could result in failure of a nacelle strut diagonal brace load path and possible separation of the nacelle from the wing. FAA AD To detect and correct fatigue cracking of the nose wheel well (NWW) vertical beams and frames, which could result in collapse of the NWW pressure bulkhead and consequent rapid decompression of the airplane. FAA AD To ensure that the flight crew is advised of the hazards of dry operation of the override/jettison pumps of the center wing fuel tank, and to prevent wear or damage to the inlet check valves and inlet adapters of the override/jettison pumps, which could result in a fire or explosion in the fuel tank during dry operation. FAA AD To detect, correct and prevent future cracks on the original design landing gear pivots, which could result in gear-up landings or loss of braking. FAA AD To detect and correct an over-rich fuelk mixture (improper fuel flow settings), which could result in rough engine operation or engine stoppage. FAA AD Intended to prevent an undesirable autotrim command that the autopilot cannot detect in the required time. FAA AD To prevent unwanted deployment of the thrust reverser, which could result in reduced controllability of the airplane. FAA AD To prevent various failures of the electric motors of the auxiliary hydraulic pump and associated wiring, which could result in fire at the auxiliary hydraulic pump and consequent damage to the adjacent electrical equipment and/or structure.

15 PAGE McDONNELL DOUGLAS, DC-10 series airplanes, as listed in McDonnell Douglas ASB.DC10-57A143, dated December 20, 1999, McDONNELL DOUGLAS, DC series airplanes, modified by Supplemental Tyupe Certificate (STC) ST00054SE, McDONNELL DOUGLAS, DC series airplanes, as listed in McDonnell Douglas ASB. DC10-24A147, Rev.03, dated April 30, 2001; certificated in any McDONNELL DOUGLAS, all model DC- 10 series airplanes, as listed in Boeing ASB.DC10-24A164, dated June 22, 2000; McDONNELL DOUGLAS, DC-10 series airplanes, McDONNELL DOUGLAS, DC series airplanes modified by supplemental type certificate (STC) SA8452SW; McDONNELL DOUGLAS, DC as listed in reference AD, certificated in any DE HAVILLAND DHC-7 SERIES BOMBARDIER, DHC-7. EUROCOPTER AS-332 SERIES EUROCOPTER, AS 332 helicopters, versions C, C1, L and L1 equipped with engine to main gear box "Bendix" coupling shafts, all part numbers. FAA AD To prevent in-flight loss of inboard and outboard flap assemblies due to failure of H-11 attaching bolts, which could result in reduced controllability of the airplane. FAA AD To prevent the inability of flight crew to remove power from the in-flight entertainment (IFE) system when necessary; which, during a non-normal or emergency situation, could result in inability to control smoke or fumes in the airplane flight deck or cabin. FAA AD To prevent chafing of the feeder cables during removal of the sump panels of the cargo floors, which could result in electrical arcing and damage to adjacent structure, and consequent smoke and/or fire in the forward cargo compartment. FAA AD To prevent fire and smoke in certain wire bundles that are routed to and from the main avionics compartment or center accessory compartment. FAA AD To prevent unwanted deployment of a thrust reverser, which could result significantly jeopardize continued safety of flight and landing of the airplane. FAA AD To ensure that the airplane crew is able to remove electrical power from the in-flight entertainment (IFE) system when necessary and is advised of appropriate procedures for such action. FAA AD To prevent broken lockwires, which could result in lossening of the engine mount bolts, and consequent separation of the engine from the airplane. Transport Canada AD CF R1. Baggage door stop fitting. DGAC France AD (A)R3. Engine to MGB coupling (ATA 63).

16 PAGE EUROCOPTER, AS 332 helicopters, versions C, C1, L, L1 and L2 equipped with adjustment lever P/N. 332A of the pilot's and copilot's cockpit pedal unit assemblies EUROCOPTER, AS332 helicopters versions C, C1, L and L1 post-mod EUROCOPTER, AS332 L2 helicopters equipped with Power Loss printed circuit boards P/Nos.: - SE01973 (704A ), - SE1958(704A Except aircraft modified per MOD or in compliance with EUROCOPTER AS332 SB EUROCOPTER, AS332 helicopters versions C, C1, L and L1 equipped with TGB P/Nos.332A , all dash numbers. DGAC France AD (A) and (A). Pilot's and copilot's pedal unit (ATA 67). DGAC France AD (A)R1. Fuselage - Main frame 5295 (ATA 53). DGAC France AD (A)R2. Power Loss Printed Circuit Boards (ATA 05, 31, 77). DGAC France AD (A)R2. Tail Gear Box (TGB)(ATA 05, 65) DGAC France AD (A)R1. EUROCOPTER, AS332 L2 helicopters. Fuselage - Main Frame 5295(ATA 53) EUROCOPTER, AS 332 helicopters versions C, C1, L and L1 on which the tail rotor pitch rod is fitted with a bearing P/N.330A EUROCOPTER, AS 332 helicopter versions C, C1, L and L2 that incorporate MOD or MOD (TU203) or MOD or MOD (TU023) and MOD DGAC France AD (A)R4. Tail rotor pitch change rod bearing (ATA 05, 67). DGAC France AD (A). Engine Indicating (ATA 77) DGAC France AD (A). EUROCOPTER, AS332-L2 helicopters, Main rotor shaft- Non - rotating scissors hinges (ATA 05,62) EUROCOPTER, AS 332 helicopters versions C, C1, L, and L1 post Mod DGAC France AD (A)R2. Fuselage - Main frame 5295 (ATA 53) DGAC France AD (A)R2. EUROCOPTER, AS 332 L2 helicopters. Fuselage - Main frame 5295 (ATA 53).

17 PAGE EUROCOPTER, AS332 helicopters, version L2 equipped with fuel filter P/Ns.-4020P25 (704A , -4020P25-1 (704A ), -4020P25-2 (704A ), -4020P25-3 (704A ), -4020P25-11 (704A ), -4020P25-4 (704A ) EUROCOPTER, AS 332 helicopters, versions C, C1, L and L1, equipped with engine-to-main gearbox "Bendix" coupling shafts, all part numbers EUROCOPTER, AS 332 L2 helicopters equipped with engine extinguishing bottles P/N (704A20028) delivered before amendment A The following Eurocopter helicopter types : - SA 330 F, G, and J. - AS 332 C, C1, L, L1, and L2. - AS 365 N; equipped with SIREN load release units EUROCOPTER, AS 332 helicopters, versions C, C1, L, and L1 equipped with fuel filter P/N: P25 (704A ); P25-1 (704A ); P25-2 (704A ); P25-3 (704A ); P25-11(704A ); P25 (704A ) EUROCOPTER AS-350 SERIES EUROCOPTER, AS 350 BA helicopters, fitted with tail rotor hub pitch-change plate SNR bearing P/N.6010F234M16 (704A ) EUROCOPTER, AS 350 helicopters, equipped with all rear bench models. DGAC France AD (A). Fuel filter by-pass valve (ATA 01, 28). DGAC France AD (A)R4. Engine-to-MGB Coupling. DGAC France AD T (A). Engine Fire Extinguishing Circuits. DGAC France AD (A). SIREN Load Release Units. DGAC France AD (A)R6. Fuel Filter By-Pass Valve (ATA 01, 28). DGAC France Telegraphic AD T (A). Tail rotor hub pitch-change plate bearing. DGAC France AD (A). Rear bench cushions (ATA 25).

18 PAGE EUROCOPTER, AS 350BA helicopters EUROCOPTER, AS 350 BA helicopters. EUROCOPTER AS-365 SERIES EUROCOPTER, AS365 N helicopters except aircraft delivered from January 31, EUROCOPTER, AS 365N helicopter that have been modified per MOD 0753B31 or in compliance with Eurocopter AS 365N SB EUROCOPTER SA-330 SERIES EUROCOPTER, SA330 helicopters version, F, G and J on which the tail rotor pitch change rod is fitted with a bearing P/N.330A EUROCOPTER, SA330 helicopters, versions F, G and J equipped with TGB P/Nos. -330A , all dsah numbers, - 330A , all dash numbers, - 330A , all dash numbers EUROCOPTER, SA 330 helicopters, version F, G, and J equipped with a tail gearbox (TGB) fitted with a tail rotor blade de-icing collector P/N.APCL FOKKER F.27 SERIES FOKKER, F.27 Mk.050 S/Ns , 20171, 20177, 20180, 20181, through 20188, through 20195, 20198, 20199, through 20209, through 20219, 20221, and DGAC France AD T (A). This AD is issued following several occurences of rapid bonding failure of the metal bush that is installed on the STARFLEX star arms ends. In some cases, these incidents caused the pilots to land quickly due to strong vibrations in the cabin. DGAC France AD T (A). This AD is issued following several occurences of rapid bonding failure of the metal bush that is installed on the STARFLEX star arms ends. In some cases, these incidents caused the pilots to land quickly due to strong vibrations in the cabin. DGAC France AD (A). Fuselage - 9 frame - Stretcher support (ATA 53). DGAC France AD (A). Fuselage - 9 frame - Reinforced latch support (ATA 53). DGAC France AD (A)R3. Tail rotor pitch change rod bearing (ATA 05, 67). DGAC France AD (A)R2. Tail Gear Box (TGB)(ATA 05, 65). DGAC France AD (A). De-iced tail rotor blades - Rotating collector. RLD AD Fuselage - TCAS antenna structural provisions - Reinforcement.

19 PAGE - 19 FOKKER, F.28 SERIES RLD AD FOKKER, F.28 Mk.100, all serial numbers. Landing gear - Anti skid control box - Modification/Replacement FOKKER, F.28 Mk.1000 through 4000 series, all serial numbers FOKKER, F.28 Mk.1000C, Mk.3000C, Mk.3000RC serial number as listed in the reference AD, if large cargo door hinges P/N. A , A , A , A , A , A or A , are installed FOKKER, F.28 Mk.1000 through Mk.4000 series, S/Ns through 11091, through 11171, and FOKKER, F.28 Mk.0100, S/Ns , thru 11257, 11262, 11266, 11267, 11287, 11288, 11292, 11294, 11298, 11299, 11302, 11309, and FOKKER, F.28 Mk.070 and Mk.0100 all serial numbers FOKKER, F.28 Mk.070 and Mk.0100 all serial numbers, if in post SB.F or post SB.F configuration (BLA issue 4 also refers) FOKKER, F.28 Mk.0100, all serial numbers, if equipped with Messier Dowty (formerly Dowty Rotol and Dowty Aerospace Gloucester) MLG. Units P/Ns. As listed in the reference AD FOKKER, F.28 Mk.1000 through Mk.4000 series aircraft, all serial numbers. RLD AD Fuselage - Butt Joint FWD of emergenct exit, at stringer 27/48 - Inspection. RLD AD /3(A). Doors - Main Deck Large Cargo Door Hinge - Inspection. RLD AD /2(A). Wings - Main Landing Gear Attachment Bracket - Inspection/repair. RLD AD (A). Placards & Markings -0 Cargo Compartment Loading Height Marking - Installation. RLD AD (A). Engine controls - Thrust reverser operating lever & selector switch - Inspection. RLD AD (A). Ice & Rain protection - 1 pitot tube AC sensing circuit - Check/Modification. BLA AD (A). Landing Gear - Main Landing Gear Main Fitting - One - Time Inspection. BLA AD (A). Fuselage - Stub wing (Engine Pylon) area skin panels - Inspection/Repair. GENERAL To all IFR operating aircraft for DGAC France Type Certificate or flying in airspace controlled by French authorities. DGAC France Telegraphic AD T (AB)R1. VHF radio navigation and landing receivers F.M immunity.

20 PAGE AIRBUS INDUSTRIE, all models aircraft equipped with powered cockpit seats manufactured by SOGERMA with P/N. as listed in the reference AD Rockwell Collins, Inc. CTL-92 transponder control panel P/Ns , , , , and (serial numbers as specified in Rockwell Collins SB.33(CTL ), dated April 5, Aircraft equipped with a JanAero Devices P/Ns. 14D11, A14D11, B14D11, C14D11, 23D04, B23D04, or C23D04 fuel regulator shutoff valve B1500, B2030, B2500, B3040, B3500, B4050, or B4500 B-series combustion heaters Innovit baby bassinets model basic PNR : 7250-XXA, 7250-XXB, 7253-XXB, all serial numbers, installed, but not limited to Airbus, Boeing, Douglas and Fokker aircrafts. OTHER AIRCRAFT BRITTEN-NORMAN, models BN2A, BN2B, and BN2T as listed in the reference AD BRITTEN-NORMAN, models BN-2, BN2A, BN2B, BN2T, BN2T-4R and BN2T- 4S and BN2A Mk.III as listed in the reference AD Learjet Inc. model 31 and 31A airplanes Beech 58 series, Cessna 208, Cessna 421 series and Piper PA-23, PA-31, PA-34 series aircraft equipped with JanAero series 14D11 or 23D04 fuel regulator and shutoff valves installed with B-Series combustion heaters as listed in the reference AD. DGAC France AD (B). Flight crew seats. FAA AD To prevent erroneous altitude interpretation, which could result in reduced vertical separation or unsafe traffic alert and collision avoidance system (TCAS) resolution advisories. FAA AD Intended to eliminate or severely reduce to potential for fuel leakage in aircraft with these combustion heaters, which could result in an aircraft fire with consequent damage or destruction. DGAC France AD (B). PIP pins protection flap assy installation and installation of a set screw (ATA 25). CAA AD To inspect wing access panels and as required, repair procedures. This action as required because incidents have been reported where severe corrosion has been found in the wing box. CAA AD To inspect oleo attachment brackets (NB ) at the bottom of the main landing gear tube. If the cracking is not detected early, failure of the bracket can occur which could result in detachment of the main landing gear. FAA AD To prevent separation of the tread of main landing gear tires, which could cause damage to the structure and major systems of the airplane, and consequent reduced controllability of the airplane on the ground during takeoff and landing. FAA AD To prevent fuel leakage into the combustion heater, which could result in a hazardous fire.

21 PAGE B-N group BN-2 series Islander and Trislander aircraft. OTHER BOEING AIRCRAFT BOEING, all model B707, 727C, and series airplanes, as listed in Boeing SB 2999, Revision 3, dated January 12, 1997 and , Revision 4, dated June 19, 1981, BOEING, model 727 series airplanes BOEING, model , -200 series; B , -300, -400, and -500 series airplanes, as listed in Boeing SB , dated May 25, 2000 for Boeing 727 and Boeing SDB , dated May 25, 2000 for Boeing up to -500 series airplanes BOEING, all model 727 series airplanes, BOEING, all model 727 series airplanes, BOEING, all model 727 series airplanes, OTHER BRITISH AEROSPACE AIRCRAFT BRITISH AEROSPACE, BAC One-Eleven Type 510ED aircraft fitted with Sperry attitude director indicator P/N CAA AD Windows - Emergency exit window sealant. FAA AD To detect and correct cracking of main cargo door skin and frames, which could result in failure of the door frame, and consequent rapid decompression of the airplane. FAA AD To prevent delamination of the cold-bonded doublers, which could resutlt in corrosion of the body skin and doublers, and consequent reduced structural capability of the fuselage circumferential skin joints. FAA AD To prevent failure of an escape slide to deploy or inflate correctly, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or airplane crewmembers. FAA AD To prevent failure of the bearing support fitting of the forward trunnion, which could result in collapse of the main landing gear during normal operations; consequent damage to the airplane structure; injury to flight crew, passengers, or ground personnel. FAA AD To find and fix corrosion or cracking in the hinge pins of the horizontal stabilizer, which could lead to structural degradation of the hinge of the horizontal stabilizer and result in loss of the horizontal stabilizer and consequent loss of controllability of the airplane. FAA AD To find fix corrosion or cracking in the hinge pins of the horizontal stabilizer, which could lead to structural degradation of the hinge of the horizontal stabilizer and result in loss of the horizontal stabilizer and consequent loss of controllability of the airplane. CAA AD Autopilot -Attitude director indicator - Sperry P/N