35 Airworthiness Directives: 27 airplane, 4 rotorcraft, 3 engine, 1 appliance.
AD 2003-24-04 · published Dec 1, 2003, effective Dec 16, 2003
Boeing Model 747-400 and -400F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and -400F series airplanes. This action requires replacing the rudder feel, centering, and trim mechanism with a new or serviceable rudder feel, centering, and trim mechanism. This action is necessary to prevent degradation/loss of rudder feel and centering, which could result in increased pilot workload and could lead to loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-24-05 · published Dec 1, 2003, effective Dec 16, 2003
McDonnell Douglas Model DC-9-31 and DC-9-32 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-31 and DC-9-32 airplanes. This action requires installation of ceiling panels and a protective pad in the tailcone emergency exit passageway. The actions specified by this AD are intended to prevent people on board the airplane from striking their heads on exposed metal frames in the tailcone area, which could cause injury and delay or impede their evacuation during an emergency. This action is intended to address the identified unsafe condition.
AD 2003-24-06 · published Dec 1, 2003, effective Dec 1, 2003
Dassault Model Mystere-Falcon 200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Mystere-Falcon 200 series airplanes. This action requires a one-time inspection of the fire extinguishing pipe for each engine to determine whether holes for dispersal of fire-extinguishing agent are present, and corrective action if necessary. This action is necessary to ensure that the flightcrew is able to extinguish an engine fire, should one occur. Inability to extinguish an engine fire could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-24-08 · published Dec 1, 2003, effective Dec 4, 2003
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that currently requires repetitive inspections to find cracks, fractures, or corrosion of each carriage spindle of the left and right outboard mid-flaps; and corrective action, if necessary. That AD also provides for an optional action of overhaul or replacement of the carriage spindles. This amendment requires repetitive gap checks of the inboard and outboard carriage of the outboard mid-flaps to detect fractured carriage spindles; and corrective actions, if necessary. This amendment also reduces the interval for the existing inspections and revises the overhaul procedures. The actions specified in this AD are intended to detect and correct cracked, corroded, or fractured carriage spindles and to prevent severe flap asymmetry, which could result in reduced control or loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-24-07 · published Dec 3, 2003, effective Feb 9, 2004
The New Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2, PA-31T3, and PA-31P-350 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. (Piper) Models PA-31, PA- 31-300, PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2, PA- 31T3, and PA-31P-350 airplanes. This AD requires you to install an inspection hole (or use for inspection the tooling hole in the rudder bottom rib), conduct a detailed visual inspection of the rudder torque tube and associated ribs for corrosion, and, if corrosion is found, replace or repair the rib/rudder torque tube assembly. This AD is the result of reports of rudder tube corrosion. The actions specified by this AD are intended to detect and correct corrosion in the rudder torque tube assembly and rudder rib, which could result in failure of the rudder torque tube. This failure could lead to loss of rudder control.
AD 2003-24-09 · published Dec 4, 2003, effective Jan 8, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires performing a general visual inspection to detect chafing or damage of the parallel power feeder cables of the number 2 integrated drive generator (IDG); repairing any chafed cable and damaged structure; and repositioning the parallel power feeder cables of the number 2 IDG. This amendment revises the applicability of the existing AD by adding certain airplanes and removing certain other airplanes. The actions specified by this AD are intended to prevent chafing and arcing of the parallel feeder cables of the number 2 IDG, which could result in smoke and/or fire in the right aft galley area. This action is intended to address the identified unsafe condition.
AD 2003-24-10 · published Dec 4, 2003, effective Jan 8, 2004
McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC- 10-15, DC-10-30, DC-10-30F, DC-10-30F (KC10A and KDC-10), DC-10-40, DC- 10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes, that requires a one-time inspection to determine the thickness of the walls of the rudder pedal arm assembly for the captain's and first officer's rudder pedals, and follow-on actions. This action is necessary to prevent failure of the rudder pedal arm assembly, which, under certain conditions, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-24-11 · published Dec 4, 2003, effective Jan 8, 2004
McDonnell Douglas Model MD-11 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center (EPC) to detect damage; and corrective actions, if necessary. For certain airplanes, this amendment requires replacement of the electrical wiring of the galley in the EPC. For certain other airplanes, this amendment requires an inspection to detect damage of the electrical wiring of the galley in the EPC; corrective actions if necessary; modification of the wiring support; and removal of spare fuses; as applicable. These new actions terminate the repetitive inspection requirements. This amendment also limits the applicability of the existing AD. This amendment is prompted by the FAA's determination that additional rulemaking is necessary. The actions specified by this AD are intended to prevent chafing damage to the wire assembly, and consequent arcing and smoke and fire in the EPC, and to prevent damage to the wire assembly terminal lugs and overheating of the power feeder cables on the No. 3 and No. 4 GLCU, which could result in smoke and fire in the center accessory compartment. This action is intended to address the identified unsafe condition.
AD 2003-24-13 · published Dec 4, 2003, effective Jan 20, 2004
Cessna Aircraft Company Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H airplanes that are equipped with a Honeywell KAP 140 autopilot computer system installed on the center instrument control panel near the throttle. This AD requires you to install an update to the operating software of the KAP 140 autopilot computer system, change the unit's part number, and change the software modification identification tag. This AD is the result of reports of inadvertent and undetected engagement of the autopilot system. We are issuing this AD to prevent unintentionally engaging the KAP 140 autopilot computer system, which could cause the pilot to take inappropriate actions.
AD 2003-24-14 · published Dec 4, 2003, effective Jan 8, 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 all 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 one-time inspections to detect discrepancies of electrical wiring installations in various areas of the airplane, and corrective action if necessary. The actions specified by this AD are intended to prevent smoke and fire in various areas of the airplane due to heat damage and/or electrical arcing of improperly installed wiring. This action is intended to address the identified unsafe condition.
AD 2003-25-02 · published Dec 18, 2003, effective Jan 22, 2004
Boeing Model 777-200 and 777-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and 777-300 series airplanes, that requires application of high-temperature sealant in designated areas of the strut aft dry bay. The actions specified by this AD are intended to prevent leakage of hydraulic fluid into the strut aft dry bay, where high temperatures associated with the adjacent primary exhaust nozzle may ignite the fluid, resulting in an uncontrolled fire in the strut aft dry bay. This action is intended to address the identified unsafe condition.
AD 2003-25-03 · published Dec 18, 2003, effective Jan 22, 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 a one-time inspection of the forward engine mount assemblies on the left and right engine nacelles for installation of pre-production engine mount assemblies, and follow-on corrective actions if necessary. This action is necessary to prevent failure of the forward engine mount, which could result in reduced structural integrity of the nacelle and engine support structure. This action is intended to address the identified unsafe condition.
AD 2003-25-05 · published Dec 18, 2003, effective Jan 22, 2004
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes, that currently requires inspections to detect breakage in the struts of the rear mount strut assemblies on the left and right engine nacelles, and replacement of any broken struts. The existing AD also requires eventual replacement of all currently installed struts with new and/or reworked struts, as terminating action for the inspections. The amendment requires new repetitive inspections of the strut assemblies for cracking of struts replaced per the existing AD, and replacement of any cracked strut with a new, machined strut. The amendment also changes the applicability of the existing AD by adding certain airplanes and removing certain other airplanes, and includes an optional terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent failure of the engine rear mount struts, which could result in reduced structural integrity of the nacelle and engine support structure. This action is intended to address the identified unsafe conditions.
AD 2003-25-06 · published Dec 18, 2003, effective Jan 22, 2004
Airbus Model A300 B4-622R and A300 F4-622R Airplanes, and Model A310-324 and -325 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-622R and A300 F4-622R airplanes, and Model A310-324 and -325 series airplanes, that are equipped with Pratt & Whitney PW4000 series engines. This AD requires replacement of the existing flexible hose assembly that connects the oil pressure transmitter to the main oil circuit, with a new improved tube assembly. This action is necessary to prevent failure of the oil pressure indicator and low-oil-pressure warning in the event of an engine fire, which could result in an unannounced shutdown of the engine. This action is intended to address the identified unsafe condition.
AD 2003-25-07 · published Dec 18, 2003, effective Jan 22, 2004
Airbus Model A319 and A320 Series Airplanes Equipped With Elevator and Aileron Computer (ELAC) L80 Standard
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319 and A320 series airplanes, that currently requires revising the airplane flight manual to specify procedures for landing under certain conditions of gusty winds and turbulence. This amendment requires replacement of both Elevator and Aileron Computers (ELACs) having L80 standards with new ELACs having L81 standards, which terminates the requirements of the existing AD. The actions specified by this AD are intended to prevent activation of the high angle-of-attack protection during final approach for landing, which could result in loss of ability to flare properly during landings. This action is intended to address the identified unsafe condition.
AD 2003-11-15 R1 · published Dec 23, 2003, effective Jan 27, 2004
McDonnell Douglas Model MD-90-30 Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-90-30 airplanes, that currently requires replacing the lanyards on the pressure relief door for the thrust reverser with new, improved lanyards, and doing associated modifications. The actions specified by that AD are intended to ensure that the lanyards on the pressure relief door have adequate strength. Lanyards of inadequate strength could allow the pressure relief door to detach from the thrust reverser in the event that an engine bleed air duct bursts, which could result in the detached door striking and damaging the horizontal stabilizer, and consequent reduced controllability of the airplane. This amendment is prompted by the fact that a certain paragraph of the existing AD prohibits installation of certain part numbers of lanyards; the numbers listed in that paragraph correspond to new, improved lanyards that are acceptable for installation. This amendment will correct these part numbers to prohibit installation of suspect lanyards while allowing installation of the new, improved lanyards. This action is intended to address the identified unsafe condition.
AD 2003-25-04 · published Dec 23, 2003, effective Jan 27, 2004
Airbus Model A319, A320, and A321 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires modifying the fuel pipe couplings and installing bonding leads in specified locations within the fuel tank. This amendment continues to require the modification and installation, but adds new modifications of the bonding leads for certain airplanes. This amendment also changes the applicability of the existing AD. The actions specified by this AD are intended to prevent ignition sources and consequent fire/explosion in the fuel tank. This action is intended to address the identified unsafe condition.
AD 2003-25-09 · published Dec 23, 2003, effective Jan 27, 2004
Airbus Model A300 B4-600 Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 C4-605R Variant F Airplanes, and Model A300 F4-605R Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-600 series airplanes, Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-605R airplanes. This AD requires modification of certain components of the 115 Volts Alternating Current (VAC) supply wiring and of the fuel gauging system. This action is necessary to prevent short circuits between 115 VAC wiring and certain fuel system electrical wire runs with subsequent overheating of the cadensicon sensor thermistor or fuel level sensor, which could be great enough to ignite fuel vapors in the fuel tank and cause an explosion. This action is intended to address the identified unsafe condition.
AD 2003-25-10 · published Dec 23, 2003, effective Jan 27, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires an inspection to detect chafing or damage of the electrical wires leading to the terminal strips in the center accessory compartment (CAC) area, and corrective actions if necessary. That AD also currently requires revising the wire connection stack up of certain cable terminals at the electrical power center bays in the CAC, and replacing certain terminal strips with new strips and removing applicable nameplates at electrical power center bays. This amendment requires additional actions for improving the terminal strips and revises the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent arcing and sparking damage to the power feeder cables, terminal strips, and adjacent structure, and consequent smoke and fire in the CAC. This action is intended to address the identified unsafe condition.
AD 2003-25-11 · published Dec 23, 2003, effective Jan 27, 2004
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing airplane models, that requires a one-time inspection to identify all H-11 steel bolts installed in the latch fittings of the cargo doors, repetitive inspections for cracked or broken H-11 steel bolts, and follow-on and corrective actions if necessary. This amendment also requires eventual replacement of all H- 11 steel bolts in the latch fittings of the cargo doors with Inconel bolts. This action is necessary to prevent broken bolts in the latch fittings, which could reduce the capability of the door latch to keep the door closed, and result in loss of a cargo door and consequent rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-25-12 · published Dec 23, 2003, effective Jan 27, 2004
Dassault Model Falcon 900 EX and Mystere-Falcon 900 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 900 EX and Mystere-Falcon 900 series airplanes. This action requires installing an attachment support assembly for the fire extinguishing piping in the baggage compartment. For certain airplanes this action also requires modifying the liner panel of the baggage compartment. The actions specified by this AD are intended to prevent distortion of the fire extinguishing discharge nozzle as a result of the nozzle not being secure, which could result in poor diffusion of the fire extinguishing agent in the event of a fire in the baggage compartment. This action is intended to address the identified unsafe condition.
AD 2003-25-13 · published Dec 23, 2003, effective Jan 27, 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, and DC-10-40F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires a one- time inspection for damage of the power feeder cables and surrounding structure, and repair if necessary. For certain airplanes, this amendment requires fabricating and installing a power feeder support bracket assembly and clamps at station Y=595.000, left side. For certain other airplanes, this amendment requires installing two power feeder support brackets and clamps at station Y=606.000, left side. This action is necessary to prevent chafing of the external ground power feeder cables against the adjacent structure, which could result in arcing and fire. This action is intended to address the identified unsafe condition.
AD 2003-26-01 · published Dec 23, 2003, effective Jan 7, 2004
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action requires a one-time general visual inspection to identify the material of the rudder assembly, and corrective actions, if necessary. For airplanes with a graphite assembly, this action requires repetitive general visual inspections of the flange bolts of the rudder front spar for any loose bolts, and corrective actions, if necessary. This action is necessary to detect and correct loose bolts common to the flange of the rudder front spar and main thrust hinge and actuator assembly, as well as the auxiliary actuator support fitting, which could cause the rudder actuator to separate from the rudder during certain flight conditions, resulting in loss of rudder control and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-26-02 · published Dec 23, 2003, effective Jan 27, 2004
Airbus Model A319-113 and -114 Series Airplanes; and Model A320-111, -211, and -212 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319-113 and -114 series airplanes; and Model A320-111, -211, and -212 series airplanes; that requires either a review of airplane maintenance or delivery records, or one-time inspection of the hydraulic actuators located in the pivot doors of both thrust reversers to identify the part number, and eventual replacement of certain actuators with modified or new actuators. This action is necessary to prevent jamming of a thrust reverser door during operation, or inadvertent deployment of a thrust reverser door in- flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-26-03 · published Dec 23, 2003, effective Jan 27, 2004
Airbus Model A319, A320, and A321 Series Airplanes Equipped With Certain Litton Air Data Inertial Reference Units
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes equipped with certain Litton air data inertial reference units (ADIRU). This AD requires modifying the shelf (floor panel) above ADIRU 3, and, for certain airplanes, modifying the polycarbonate guard that covers the ADIRUs, and the ladder located in the avionics compartment, as applicable. This action is necessary to prevent failure of ADIRU 3 during flight, which could result in loss of one source of critical attitude and airspeed data and reduce the ability of the flightcrew to control the airplane. This action is intended to address the identified unsafe condition.
AD 2003-26-07 · published Dec 31, 2003, effective Feb 4, 2004
McDonnell Douglas MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires a one-time general visual inspection of the circuit breakers 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 2003-26-08 · published Dec 31, 2003, effective Feb 4, 2004
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that requires replacing the existing pressure relief valve on the potable water tank with a new, improved pressure relief valve, which is made of stainless steel and is non- adjustable. For certain airplanes, this AD also requires modification of certain piping to re-locate the pressure relief valve. This action is necessary to prevent rupture of the potable water tank during flight of the airplane, which could result in structural damage to the airplane and its inability to sustain flight loads. This action is intended to address the identified unsafe condition.
AD 2003-22-15 · published Dec 1, 2003, effective Jan 5, 2004
Eurocopter France Model SA-365N, N1, AS-365N2, and AS 365 N3 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the fuel air vent hoses (air vent hoses) for chafing and fuel leakage in the interference areas, inspecting the length of the latch support attachment screws, installing spacers to prevent interference with the latch support attachment screws, and removing one tyrap clamp support. This amendment is prompted by a report of a fuel leak in the air vent hose at the 9[deg] frame on the pilot's side of the helicopter. The actions specified by this AD are intended to prevent fuel leakage, toxic fumes inside the cabin creating a fire hazard that could lead to a fire and smoke in the cabin, and subsequent loss of control of the helicopter.
AD 2003-24-02 · published Dec 1, 2003, effective Jan 5, 2004
Eurocopter France Model AS332C, L, L1, and L2 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the cockpit pedal unit (pedal unit) adjustment lever (lever) for a crack at specified time intervals by a dye- penetrant inspection and replacing any cracked lever with an airworthy lever before further flight. Modifying the pedal unit is also required and is a terminating action for the requirements of this AD. This amendment is prompted by cracks detected in the lever that creates an unsafe condition. The actions specified by this AD are intended to prevent failure of the lever, loss of access to the brake pedals on the ground or loss of yaw control in flight, and subsequent loss of control of the helicopter.
AD 2003-25-01 · published Dec 15, 2003, effective Jan 20, 2004
Eurocopter France Model AS332C, C1, L, L1, AS350B, BA, B1, B2, B3 and D, and AS355E, F, F1, F2 and N Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters with a Breeze 300-pound electric hoist (hoist) installed that requires modifying and re-identifying the hoist operator control unit and replacing certain fuses. This amendment is prompted by a test of a hoist that revealed an anomaly in the electrical control circuit. The actions specified by this AD are intended to prevent failure of the hoist pyrotechnic squib electrical control unit, lack of adequate current to activate the hoist pyrotechnic squib, an inability of the pilot to cut the rescue hoist cable in the event of cable entanglement or other emergency, and subsequent loss of control of the helicopter.
AD 2003-26-04 · published Dec 31, 2003, effective Jan 15, 2004
Agusta S.p.A. Model A109E Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires certain inspections of the rod-end of the main rotor head damper for freedom of movement, and depending on the torque required to move the rod-end, either further inspection for a crack or replacing the rod- end. This amendment is prompted by reports of rod-end fractures due to fatigue failure resulting in increased helicopter vibrations. This condition, if not corrected, could result in failure of the rod-end, extreme vibrations, and a subsequent forced landing or loss of control of the helicopter.
AD 2003-24-12 · published Dec 3, 2003, effective Dec 18, 2003
Pratt & Whitney JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, part number (P/N) 697896, and No. 4 bearing front pressure manifold, P/N 670663, installed. This AD requires a one-time visual inspection of the gearbox pressure tube and No. 4 bearing front pressure manifold and the attaching clamp assemblies for correct positioning and for wear and damage, and replacement if necessary. This AD is prompted by a report of a failed gearbox pressure tube that resulted in an engine fire. We are issuing this AD to prevent engine fires caused by failed gearbox pressure tubes or failed No. 4 bearing front pressure manifolds.
AD 2003-25-08 · published Dec 17, 2003, effective Jan 21, 2004
Rolls-Royce Corporation (Formerly Allison Engine Company) AE 3007A1, AE 3007A1/1, AE 3007A1/3, AE 3007A3, AE 3007A1E, and AE 3007A1P Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007A1, AE 3007A1/1, AE 3007A1/3, AE 3007A3, AE 3007A1E, and AE 3007A1P turbofan engines, with 1st to 2nd stage turbine spacers, part number (P/N) 23069627, 23070989, 23072849, or 23075364 installed. This AD reduces the life limit for 1st to 2nd stage turbine spacers, P/N 23072849, to a certain lower life limit, based on engine model. This AD also requires a one-time fluorescent penetrant inspection (FPI) of 1st to 2nd stage turbine spacers P/Ns 23069627, 23070989, 23072849, and 23075364 before reaching the spacer life limit, within specified cycles-since-new (CSN), and requires replacement of the spacer if found cracked, or with bent or missing aft tangs. This AD is prompted by a report that during a scheduled inspection, aft pilot tangs on a 1st to 2nd stage turbine spacer were found bent and cracked. We are issuing this AD to prevent 1st to 2nd stage turbine spacer failure, leading to uncontained turbine failure, engine shutdown, and damage to the airplane.
AD 2003-26-09 · published Dec 31, 2003, effective Dec 3, 2003
Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW4090-3, and PW4098 Turbofan Engines
The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW4090-3, and PW4098 turbofan engines. That AD requires initial and repetitive visual and borescope inspections of the No. 3 bearing weep tube and turbine exhaust case (TEC), and removal of the high pressure turbine (HPT) assembly and replacement of any heat distressed HPT assembly hardware if oil wetting or staining is found. This ad requires the same actions. This AD results from the finding of a significant reference error in one of the borescope inspection compliance paragraphs. We are issuing this AD to prevent thermal distressed HPT assembly hardware from remaining in service, which could result in a cracked HPT stage 1 disk or HPT stage 1-2 air seal and an uncontained engine failure.
AD 2003-26-06 · published Dec 31, 2003, effective Feb 17, 2004
Anjou Aeronautique Safety Belts and Restraint Systems
The FAA adopts a new airworthiness directive (AD) for certain Anjou Aeronautique (ANJOU) (formerly TRW Repa S.A., formerly L'AIGLON) safety belts and restraint systems that are installed in aircraft. This AD requires you to inspect safety belts and restraint systems for defects and service life limits, and, if necessary, repair safety belts and restraint systems that have not reached service life limits; and replace safety belts and restraint systems that have reached service life limits. This AD is the result of reports of inadvertent unbuckling of the ANJOU seat belts and two safety recommendations to take AD action. We are issuing this AD to detect and correct defective safety belts and restraint systems, which could result in failure of the safety belts and restraint systems. This failure could lead to lack of occupant restraint during normal or crash loads.
