37 Airworthiness Directives: 27 airplane, 4 rotorcraft, 5 engine, 1 appliance.
AD 2003-26-10 · published Jan 7, 2004, effective Jan 22, 2004
Airbus Model A300 B2 and B4 Series Airplanes; and A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (Collectively Called A300-600) Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to the Airbus airplanes listed above. This action requires a one-time inspection for cracking of the lower outboard flange of gantry No. 4 in the main landing gear bay area, and repair if necessary. This action is necessary to find and fix such cracking, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-26-12 · published Jan 7, 2004, effective Feb 11, 2004
Boeing Model 737-600, 737-700, 737-800, 757-200, and 757-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, 737-700, 737-800, 757-200, and 757-300 series airplanes, that requires replacing existing video distribution unit (VDU) connectors with new, improved connectors or new wire assemblies (jumpers), and performing related actions, as applicable. This action is necessary to prevent a short circuit in a VDU connector and consequent arcing and damage to wiring within the connector, which could result in damage to adjacent systems or structure and possible smoke or fire in the airplane cabin. This action is intended to address the identified unsafe condition.
AD 2003-26-13 · published Jan 7, 2004, effective Feb 11, 2004
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires identification of the valves installed on the engine struts as hydraulic supply (fire) shutoff valves for the engine-driven pump, corrective action if necessary, and eventual replacement of discrepant valves with serviceable parts. This action is necessary to prevent leakage of hydraulic (flammable) fluid into an engine fire, which could result in an uncontrolled fire. This action is intended to address the identified unsafe condition.
AD 2004-01-07 · published Jan 7, 2004, effective Feb 11, 2004
BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. This AD requires one-time inspections of the inner webs and flanges at frames 15, 18, 41, and 43 for evidence of corrosion or cracking; and corrective actions if necessary. This action is necessary to detect and correct corrosion and cracking of the inner webs and flanges at frames 15, 18, 41, and 43, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-01-01 · published Jan 9, 2004, effective Feb 13, 2004
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes (Regional Jet Series 100 & 440), that requires a one-time inspection of the dust covers for the flight data recorder (FDR) and cockpit voice recorder (CVR) equipment for the presence of markings that indicate the presence of a chemical-resistant coating, and corrective actions if necessary. The actions specified by this AD are intended to prevent peeling of the paint and markings from the dust covers for FDR and CVR equipment due to hydraulic mist from the actuators, which could result in the inability to identify FDR and CVR equipment in the event of an accident-recovery mission. The lack of data from FDR and CVR equipment could hamper discovery of the unsafe condition that caused an accident or an incident and prevent the FAA from developing and mandating actions to prevent additional accidents or incidents caused by that same unsafe condition. This action is intended to address the identified unsafe condition.
AD 2004-01-02 · published Jan 9, 2004, effective Feb 13, 2004
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires modification of the aft pitch load fitting of the diagonal brace of the nacelle strut of each wing. This action is necessary to prevent loss of the fuse pin of the pitch load fitting due to fatigue caused by improper clearance between the fuse pin and bushing, which could result in increased loads in the wing-to- strut joints and consequent separation of the strut and engine from the wing. This action is intended to address the identified unsafe condition.
AD 2004-01-03 · published Jan 9, 2004, effective Feb 13, 2004
Airbus Model A319, A320, and A321 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires an inspection to detect moisture and migrated bushings of the guide fittings of the safety locking pins of the passenger doors, removal of any moisture, application of grease, and reinstallation of any migrated bushing. That AD also requires installation of a greasing nipple on the guide fitting of the locking pin and on three telescopic rods on the passenger doors. This amendment adds a requirement for modification of the upper guide fitting of the locking pin, and expands the applicability in the existing AD. The actions specified by this AD are intended to prevent jamming of the locking pin of the passenger door, which could result in inability to open the passenger door and delay of evacuation in an emergency, resulting in possible injury to passengers or crew. This action is intended to address the identified unsafe condition.
AD 2004-01-04 · published Jan 9, 2004, effective Feb 13, 2004
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that currently requires revising the airplane flight manual (AFM), and either installing hydraulic tube assemblies incorporating a check valve, or visually inspecting the check valve if already installed and performing corrective actions if necessary. This action adds airplanes to the applicability of the existing AD. The actions specified by this AD are intended to prevent the landing gear doors from becoming blocked from opening during application of emergency procedures in the event of a loss of hydraulics. This action is intended to address the identified unsafe condition.
AD 2004-01-05 · published Jan 9, 2004, effective Feb 13, 2004
Dassault Model Falcon 2000 and 900EX, and Dassault Model Mystere-Falcon 900 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 and 900EX, and Dassault Model Mystere-Falcon 900 series airplanes. This AD requires measuring the paint thickness on the upper and lower surfaces of the left and right sides of the horizontal stabilizer, performing corrective actions if necessary, and installing maintenance caution placards on the upper surface of the left and right sides of the horizontal stabilizer. This action is necessary to prevent structural damage to the horizontal stabilizer after a direct lightning strike, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-01-06 · published Jan 9, 2004, effective Feb 13, 2004
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes. This AD requires a one-time general visual inspection of the left and right sides of the pedestal side cover adjacent to the rudder pedal on the cockpit floor for proper installation of the attachment bracket, and corrective actions if necessary. This action is necessary to prevent restricted movement of the rudder pedal due to a loose pedestal side cover causing interference, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-01-11 · published Jan 9, 2004, effective Feb 13, 2004
Hamburger Flugzeugbau G.m.b.H. Model HFB 320 HANSA Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Hamburger Flugzeugbau G.m.b.H. Model HFB 320 HANSA airplanes, that requires replacement of the elevator trim control cable assemblies with new assemblies. This action is necessary to prevent loss of elevator trim and possible loss of rudder and/or elevator function due to stress-corrosion cracking of certain cable terminals. This action is intended to address the identified unsafe condition.
AD 2004-01-12 · published Jan 9, 2004, effective Feb 13, 2004
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that requires operators to inspect the pitot-true air temperature (TAT) relays and the full authority digital engine control (FADEC) electronic interface resistor modules to detect contamination. This AD also requires operators to perform corrective action if necessary, clean the relay/connector pins and sockets, modify the seal between the cockpit console panels and the storm window, and/or install a new protective frame (protective sheets) at the cockpit relay supports. This action is necessary to detect and correct oxidation of the pitot-TAT relay, which could result in increased resistance and overheating of the relay and consequent smoke in the cockpit; and to detect and correct oxidation of the FADEC electronic interface resistor modules, which could result in in-flight uncommanded engine power roll back to idle. This action is intended to address the identified unsafe condition.
AD 97-24-02 R1 · published Jan 9, 2004, effective Feb 13, 2004
Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL- 600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes, that currently requires repetitive inspections to find cracks of a certain bulkhead web of the fuselage at certain locations, and repair if necessary. The actions specified by that AD are intended to prevent cracking in the pressure bulkhead at frame station (FS) 409.00, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage. This amendment provides an optional terminating modification for certain airplanes. This action is intended to address the identified unsafe condition.
AD 2003-09-09 R1 · published Jan 12, 2004, effective Jan 22, 2004
Cessna Aircraft Company Models 441 and F406 Airplanes
This amendment revises Airworthiness Directive (AD) 2003-09- 09, which applies to certain Cessna Aircraft Company (Cessna) Models 441 and F406 airplanes. AD 2003-09-09 currently requires repetitively inspecting the fuel boost pump wiring inside and outside the boost pump reservoir and repair or replacement of the wiring as necessary. AD 2003-09-09 also requires eventual installation of an improved design wire harness and fuel boost pump as terminating action for the repetitive inspections. The way the compliance time is currently written puts certain airplane owners/operators in non-compliance with the AD. Also, the terminating action for the repetitive inspections did not provide the option of installing the protective sleeving modification for boost pump lead wires. This document clarifies and corrects the compliance time and provides the option of installing the protective sleeving modification for boost pump lead wires. The actions specified by this AD are intended to detect, correct, and prevent chafing and/or arcing of the fuel boost pump wiring, which could result in arcing within the wing fuel storage system. This condition could lead to ignition of explosive vapor within the fuel storage system.
AD 2004-01-15 · published Jan 12, 2004, effective Feb 17, 2004
McDonnell Douglas Model 717-200 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model 717-200 airplanes, that requires repetitive inspections of the electric motor of the auxiliary hydraulic pump for electrical resistance, continuity, mechanical rotation, and associated wiring resistance/voltage; and corrective actions, if necessary. This action is necessary to prevent various failures of the electric motor 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. This action is intended to address the identified unsafe condition.
AD 2004-01-13 · published Jan 14, 2004, effective Feb 19, 2004
Raytheon Aircraft Company Model 1900, 1900C, and 1900D Airplanes
The FAA supersedes Airworthiness Directive (AD) 97-22-16, which applies to certain Raytheon Model 1900, 1900C, and 1900D airplanes. AD 97-22-16 currently requires you to replace the bearings on the vent blower assemblies with improved design bearings and install a thermal protection device for the vent blowers. That AD resulted from reports of vent blower assembly bearings seizing and locking the blower motor on several of the affected airplanes. This AD retains the actions required in AD 97-22-16 for certain vent blower assemblies and requires you to incorporate further product improvement modifications on all affected vent blower assemblies. This AD is the result of reports that vent blower assemblies modified in accordance with AD 97-22-16 are still malfunctioning. We are issuing this AD to prevent smoke from entering the cockpit and cabin due to the current configuration of vent blower assemblies, which could result in the pilot becoming incapacitated or impairing her/his judgment. Such a condition could lead to the pilot not being able to make critical flight safety decisions and result in loss of control of the airplane.
AD 2004-01-16 · published Jan 20, 2004, effective Feb 24, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires revising the wire connection stackups for the terminal strip of the generator feeder tail compartment of the auxiliary power unit (APU), and removing a nameplate, as applicable. For certain airplanes, this AD also requires replacing the terminal strips and revising the terminal hardware stackup for the feeder of the center cargo loading system. This action is necessary to prevent arcing damage to the terminal strips and damage to the adjacent structure, which could result in smoke and/or fire in the center and/or aft cargo compartments. This action is intended to address the identified unsafe condition.
AD 2004-01-17 · published Jan 20, 2004, effective Feb 24, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an initial general visual inspection of the power feeder cables of the integrated drive generator (IDG) and the fuel feed lines of engine pylons No. 1 and No. 3 on the wings for proper clearance and damage; corrective actions if necessary; and repetitive general visual inspections and a terminating action for the repetitive inspections. This action is necessary to prevent potential chafing of the power feeder cables of the IDG in engine pylons No. 1 and No. 3 on the wings, and consequent arcing on the fuel lines in the engine pylons and possible fuel fire. This action is intended to address the identified unsafe condition.
AD 2004-01-18 · published Jan 20, 2004, effective Feb 24, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires revising the vent fan wiring in the right forward cabin drop ceiling, right mid cabin drop ceiling, and right forward cargo compartment, as applicable. This action is necessary to prevent fire and/or smoke in the right forward cabin drop ceiling, right mid cabin drop ceiling, or right forward cargo compartment. This action is intended to address the identified unsafe condition.
AD 2004-01-19 · published Jan 20, 2004, effective Feb 24, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires replacement of the wire assembly connectors of the bag rack lighting with new, moisture-resistant connectors and reidentification of the bag racks. This action is necessary to prevent arcing of the wire assembly connectors of the overhead storage bin, and service module and bin extension assemblies, and consequent smoke/fire in the cabin. This action is intended to address the identified unsafe condition.
AD 2004-02-01 · published Jan 22, 2004, effective Feb 6, 2004
Gulfstream Model G-V Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires a one-time inspection of the landing gear selector dump valve (LGSDV) to determine the serial number (S/N). For any part with an affected S/N, or for any part for which the S/N cannot be determined, this action requires replacing the LGSDV with a cleaned part having an S/N within the affected range; or replacing the LGSDV with a new or serviceable part that has an S/N outside the affected range. This action is necessary to prevent uncommanded unlocking of the landing gear, which could result in collapse of the landing gear. This action is intended to address the identified unsafe condition.
AD 2004-02-04 · published Jan 29, 2004, effective Feb 13, 2004
Dassault Model Falcon 900EX Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Falcon 900EX series airplanes. This action requires revising the airplane flight manual to advise the flightcrew about limitations on operating in icing conditions, and to require that the airplane be operated per these limitations. This action is necessary to ensure that the flightcrew is aware of the potential for reductions in climb performance in certain situations while operating in icing conditions, and the actions they must take to avoid this condition, which could result in an inability to avoid low- level obstacles during takeoff and consequent controlled flight into terrain. This action is intended to address the identified unsafe condition.
AD 2004-02-07 · published Jan 29, 2004, effective Feb 13, 2004
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This action requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the aircraft maintenance manual by incorporating procedures for a functional test of the pilot input lever of the pitch feel simulator unit. This action also requires a functional test of the pilot input lever of the pitch feel simulator unit, and corrective action if necessary. This action is necessary to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-02-05 · published Jan 30, 2004, effective Mar 5, 2004
Bombardier Model DHC-8-400, -401, and -402 Airplanes
This amendment adopts a new airworthiness directive (AD); applicable to certain Bombardier Model DHC-8-400, -401, and -402 airplanes; that requires replacing certain flight guidance modules with improved modules, and certain flight control electronic control units with improved units. This action is necessary to prevent loss of the autopilot or manual pitch trim, which may increase the workload of the flightcrew and, under certain conditions, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-02-06 · published Jan 30, 2004, effective Mar 5, 2004
McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC-10A- and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F Airplanes; and Model MD-11 and MD-11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas transport category airplanes. For certain airplanes, this amendment requires a general visual inspection to detect cracking in the nuts on the lower attach bolt assemblies of the forward attach bracket of the inboard flap outboard hinge, replacement of both upper and lower attach bolt assemblies with new bolts and nuts made from Inconel material, and replacement of certain preload-indicating (PLI) washers with new washers. For certain other airplanes, this amendment requires replacement of the lower attach bolt assemblies of the inboard forward attach bracket of the inboard flap outboard hinge with new bolts and nuts made from Inconel material, and replacement of PLI washers with new washers. This action is necessary to prevent separation of the inboard flap outboard hinge from the wing structure and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-02-08 · published Jan 30, 2004, effective Mar 5, 2004
Boeing Model 737-300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes. This amendment requires, for certain airplanes, replacement of the hinge assemblies on certain escape slide compartments of the forward doors with new, stronger hinge assemblies; and, for certain other airplanes, an inspection for incorrectly crimped hinge assemblies, and corrective action if necessary. The actions specified by this AD are intended to prevent forward door escape slides from falling out of their compartments into the airplane interior and inflating, which could impede an evacuation in the event of an emergency. This action is intended to address the identified unsafe condition.
AD 2004-02-09 · published Jan 30, 2004, effective Mar 5, 2004
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This action requires a one-time visual inspection to determine if discrepant circuit breakers are installed, and corrective action if necessary. This action is necessary to prevent internal overheating and arcing of circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin. This action is intended to address the identified unsafe condition.
AD 2004-01-10 · published Jan 7, 2004, effective Jan 22, 2004
Eurocopter Deutschland Model MBB-BK-117 A-1, A-3, A-4, B-1, B-2, and C-1 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland (Eurocopter) Model MBB-BK-117 A-1, A-3, A-4, B- 1, B-2, and C-1 helicopters with a certain tail rotor (TR) transmission or intermediate (INT) gearbox installed. This action requires inspecting the magnetic plug of the TR transmission and INT gearbox for metal particles before the first flight of each day. Replacing an unairworthy TR transmission, INT gearbox, or bearings with airworthy parts is also required within 30 days after the effective date of this AD. This amendment is prompted by a report of production-related cracks on the cage of bearings installed in certain TR transmissions and INT gearboxes. This condition, if not corrected, could result in cracking and separation of the bearing cage, failure of a bearing, failure of the TR transmission or INT gearbox, and subsequent loss of control of the helicopter.
AD 2004-01-09 · published Jan 9, 2004, effective Feb 13, 2004
Eurocopter France Model AS355E, F, F1, F2, and N Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires revising the Limitations section of the Rotorcraft Flight Manual (RFM) to prohibit using the landing light except for landing and takeoff until the 40 amp 10P1 and 10P2 contactors are replaced with 50 amp circuit breakers. Also, this amendment requires upgrading the electrical master boxes. This amendment is prompted by three reports of complete loss of electrical power generating systems, except for the direct battery power, due to a combination of high outside temperature and long flight duration with the landing light on that causes the nontemperature compensated trip switches to prematurely trip. The actions specified by this AD are intended to prevent failure of the helicopter power generator systems, loss of the use of flight instruments, and subsequent loss of control of the helicopter.
AD 2004-01-14 · published Jan 9, 2004, effective Jan 26, 2004
Eurocopter France Model EC130B4 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC130B4 helicopters with a certain air intake cowling attachment fitting (fitting) installed. This action requires inspecting for broken or cracked forward fittings. If a broken or cracked fitting is found, inspecting the four center and aft fittings for cracks is required. Replacing broken fittings or certain cracked fittings is also required. This amendment is prompted by reports of cracked and broken fittings; one fitting failed after only 418 hours time-in-service (TIS). This condition, if not corrected, could result in failure of a forward fitting, an excess load on the other fittings, which could cause them to crack and break, which could result in loss of the air intake cowling in flight, and subsequent damage or loss of control of the helicopter, or both.
AD 2004-02-03 · published Jan 29, 2004, effective Mar 4, 2004
Agusta S.p.A. Model A109E Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Agusta S.p.A. (Agusta) model helicopters that requires modifying each passenger compartment sliding door (door) by applying a kit to replace the levers and links. This amendment is prompted by instances of a door inadvertently opening during flight due to the unstable configuration of the door. The actions specified by this AD are intended to prevent the inadvertent opening of a door during flight and loss of a passenger or other objects from the cabin.
AD 2003-26-05 · published Jan 2, 2004, effective Jan 20, 2004
General Electric Company CF34-8C1 Series and CF34-8C5 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-8C1 series and CF34-8C5 series turbofan engines, with certain serial number (SN) master variable geometry (VG) actuators installed. This AD requires initial and repetitive reviews of the airplane Maintenance Data Computer (MDC) for master VG actuator fault messages, and if the MDC is inoperative, reviews of the Engine Indication and Crew Alerting System (EICAS) for fault messages. This AD also requires replacement of actuators reported faulty by the Full Authority Digital Engine Control (FADEC). This AD results from nine reports of master VG actuator electrical signal faults, one report of which was a dual-channel fault, resulting in the FADEC commanding the engine power to idle. We are issuing this AD to prevent VG master actuator dual-channel electrical signal faults: [sbull] Which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle; and [sbull] Could result in a multi-engine loss of thrust if dual- channel faults occur on more than one engine simultaneously.
AD 2003-26-11 · published Jan 6, 2004, effective Feb 5, 2004
General Electric Company (GE) CF6-80E1A2 and -80E1A4 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80E1A2 and -80E1A4 turbofan engines with left vertical link bolts part number (P/N) 1304M26P02 installed, and pylon attachment bolts originally torqued to 450-500 lb ft. This AD requires reducing the torque of pylon attachment bolts, and replacing left vertical link bolts with life-limited serialized bolts. This AD results from revised analyses by the airframe manufacturer of loads on the forward engine mount. We are issuing this AD to prevent engine separation that could result from a reduction of engine mount structural integrity due to failure of pylon attachment bolts or vertical link bolts.
AD 2004-01-08 · published Jan 6, 2004, effective Feb 10, 2004
Pratt & Whitney JT9D-7R4 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT9D-7R4 series turbofan engines. This amendment requires on JT9D-7R4 series turbofan engines with steel fan cases, replacement of the existing one-piece fan case shield with a thicker four-piece fan case shield and would add four fan case shield supports. This amendment results from two uncontained full fan blade fracture events that resulted in penetration of the steel fan case and fan case shield. We are issuing this AD to prevent uncontained fan blade failures, resulting in damage to the airplane.
AD 2004-01-20 · published Jan 20, 2004, effective Feb 24, 2004
Rolls-Royce plc RB211 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, -524D4, - 524G2, -524G3, and -524H series, and RB211-535C and -535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. This AD allows disc assemblies not modified by a certain RR service bulletin to reach their full life only after the disc assemblies are modified with anti-corrosion protection. This AD results from the manufacturer's reassessment of the corrosion risk on HPC stage 3 disc assemblies that have not yet been modified with sufficient application of anti- corrosion protection. We are issuing this AD to prevent corrosion- induced uncontained disc failure, resulting in damage to the airplane.
AD 2004-01-21 · published Jan 23, 2004, effective Feb 27, 2004
Rolls-Royce plc (RR) RB211-22B, RB211-524, and RB211-535 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B, RB211-524, and RB211-535 series turbofan engines. This AD requires the installation of a front engine mount housing and link support assembly that has a serialized, life limited, spherical bearing installed. This AD results from reports of corrosion and fatigue cracks in the mount pins, the spherical bearings, and the support links and their respective spherical bearings. We are issuing this AD to prevent failure of the front engine mount housing and link support assembly due to cracks that could result in loss of the engine.
AD 2003-26-14 · published Jan 7, 2004, effective Feb 20, 2004
Kidde Aerospace Part Number (P/N) 898052 Hand-Held Halon Fire Extinguishers
The FAA adopts a new airworthiness directive (AD) for certain Kidde Aerospace P/N 898052 hand-held halon fire extinguishers that are utilized on aircraft. This AD requires you to remove the affected fire extinguishers from service and would prevent you from using them in the future. This AD is the result of information that shows that the discharge time of the affected fire extinguishers exceeds the maximum allowable discharge time. The problem is due to incomplete crimping of the siphon tube. We are issuing this AD to remove from service fire extinguishers that had this incomplete crimping of the siphon tube. If not removed from service, these fire extinguishers could function at diminished levels and compromise the level of safety in an emergency situation.
