35 Airworthiness Directives: 22 airplane, 7 rotorcraft, 3 engine, 2 propeller, 1 appliance.
AD 2003-13-16 · published Jul 8, 2003, effective Aug 25, 2003
Raytheon Aircraft Company 90, 100, and 200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 90, 100, and 200 series airplanes. This AD requires you to inspect the forward side of the aft pressure bulkhead for scoring damage and repair, if necessary. This AD is the result of reports of the aft pressure bulkhead being damaged by scoring during manufacture. The actions specified by this AD are intended to detect and correct damage to the aft pressure bulkhead of the fuselage. Such damage could lead to fatigue failure of the bulkhead.
AD 2003-14-01 · published Jul 10, 2003, effective Aug 14, 2003
Airbus Model A300 B2, A300 B4, A300 B4-600, A300 B4-600R, A300 F4-600R, A310, A330, and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus airplanes, that requires repetitive inspections for foreign objects between the slider and the girt bar attachment fittings of the emergency escape slides; a one-time inspection for correct adjustment of the slide release mechanism and the girt bar attachment fittings, which would terminate the repetitive inspections; a one-time test for correct extension of the girt bar through the sliders; and corrective action, if necessary. The actions specified by this AD are intended to prevent failure of an emergency escape slide, which could result in a delayed evacuation in an emergency and consequent injury to passengers or crew. This action is intended to address the identified unsafe condition.
AD 2003-14-04 · published Jul 10, 2003, effective Jul 25, 2003
Boeing Model 737-200, 737-300, 737-400, 737-500, 737-600, 737-700, 737-800, 737-900, 757-200, and 757-300 Series Airplanes; and McDonnell Douglas Model DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-30F, MD-11, and MD-11F Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain transport category airplanes as listed above. This action requires modification of the reinforced flight deck door installed on the airplane. This action is necessary to prevent inadvertent release of the decompression latch and consequent opening of the decompression panel in the flight deck door. If an airplane crewmember is in close proximity to the flight deck door when the decompression panel opens, the decompression panel could hit and injure the crewmember. This action is intended to address the identified unsafe condition.
AD 2003-14-08 · published Jul 14, 2003, effective Aug 18, 2003
Boeing Model 737-600, 737-700, 737-700C, 737-800, 737-900, 757, and 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD); applicable to all Boeing Model 737-600, 737-700, 737-700C, 737-800, 737-900, 757, and 767 series airplanes; that requires revising the Airplane Flight Manual (AFM) to advise the flightcrew to don oxygen masks as a first and immediate step when a cabin altitude warning occurs. This action is necessary to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-14-11 · published Jul 14, 2003, effective Aug 18, 2003
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for the servo-controls located on the ailerons and replacement of the servo-controls with new servo-controls when they have reached their operational life limits. This action is necessary to prevent hydraulic leakage and failure of the servo-controls due to cracks in the end caps and along the barrel, which could result in loss of the ailerons and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-14-05 · published Jul 16, 2003, effective Jul 31, 2003
McDonnell Douglas Model 717-200 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model 717 airplanes. This action requires repetitive inspections for cracking of the support fitting assemblies and stop pads of the main spoiler actuators, and follow-on actions. This action is necessary to find and correct cracking of the support fitting assemblies of the main spoiler actuators, which could result in damage of adjacent structure such as the rear spar or upper skin panel, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-14-07 · published Jul 16, 2003, effective Sep 5, 2003
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/ 45 airplanes. This AD requires you to repetitively replace the nose landing gear (NLG) drag link right-hand part every 4,000 landings until an improved design NLG drag link right-hand part is installed. This AD also requires you to install an improved design NLG drag link right- hand part as terminating action for the repetitive replacements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent structural failure of the nose landing gear (NLG) caused by fatigue damage to the NLG drag link right-hand part that develops over time. Such failure could result in either an unintended NLG extension during flight or the NLG not properly locking upon extension, which could lead to loss of airplane control during landing operations.
AD 2003-14-09 · published Jul 18, 2003, effective Aug 22, 2003
Boeing Model 767 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires repetitive detailed inspections to detect cracked, corroded, or stained collar fittings on both inboard trailing edge flaps; and follow-on corrective actions, if necessary. This amendment expands the applicability in the existing AD, and adds repetitive inspections for discrepancies of the collar fittings, torque tube, and splined bushings on both inboard trailing edge flaps; and follow-on and corrective actions, if necessary. The actions specified by this AD are intended to prevent failure of the collar fittings, which could result in separation of the inboard trailing edge flap and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-14-10 · published Jul 18, 2003, effective Aug 4, 2003
Boeing Model 767-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes. This action requires modification of the wire bundles of the video control center (VCC) of the passenger address and entertainment system, and an operational test if necessary. This action is necessary to prevent chafing of the wire bundles of the VCC against the rudder and/ or elevator control cables, which could result in arcing of the wires in the wire bundles and severing of the cables. Severed cables, if combined with an engine-out during takeoff, or a high crosswind during takeoff or landing, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-14-13 · published Jul 18, 2003, effective Aug 22, 2003
Aerospatiale Model ATR42 Series Airplanes and Model ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, -320, and - 500 series airplanes; and Model ATR72 series airplanes; that requires replacement of a certain Automatic Takeoff Power Control System (ATPCS) test selector switch with a different test selector switch. This action is necessary to prevent shorting of a contact in the ATPCS test selector switch due to abnormal wear of contact surfaces, which could result in dual engine power drop with associated loss of both alternating current wild and main hydraulic power during ground maneuvers, and consequent reduced controllability of the airplane and increased flightcrew workload. This action is intended to address the identified unsafe condition.
AD 2003-14-14 · published Jul 18, 2003, effective Aug 22, 2003
Aerospatiale Model ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires installing brackets and ramps under floor panels between frames 23C and 23D and installing wire bundles on the ramps. The actions specified by this AD are intended to prevent chafing damage to the electrical wire cables, which could lead to an electrical short circuit and potential for a fire under the floor panels. This action is intended to address the identified unsafe condition.
AD 2003-14-17 · published Jul 18, 2003, effective Aug 22, 2003
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 (Regional Jet Series 100 & 440) airplanes, that requires the installation of protective tape on the fire and overheat control unit located in the flight compartment. The actions specified by this AD are intended to prevent fluid contamination inside the fire and overheat control unit, which could result in a false fire alarm and consequent emergency landing. This action is intended to address the identified unsafe condition.
AD 2003-14-22 · published Jul 18, 2003, effective Aug 22, 2003
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes. This AD requires modification of the No. 3 electrical equipment panel behind the avionics rack, and modification of the No. 2 propeller de-ice timer. This action is necessary to prevent incorrect altitude information transmitted by the Mode S transponder and simultaneous loss of the Traffic Alert and Collision Avoidance System (TCAS), and increasing the possibility of an air traffic conflict. This action is intended to address the identified unsafe condition.
AD 2003-14-06 · published Jul 21, 2003, effective Jul 14, 2003
Boeing Model 737-200, -200C, -300, -400, and -500 Series Airplanes
This document corrects a typographical error that appeared in airworthiness directive (AD) 2003-14-06 that was published in the Federal Register on July 9, 2003 (68 FR 40759). The typographical error resulted in an incorrect AD number in one location of the document. This AD is applicable to certain Boeing Model 737-200, -200C, -300, - 400, and -500 series airplanes. This AD requires repetitive inspections for cracking of certain lap splices, and corrective action if necessary.
AD 2003-14-15 · published Jul 21, 2003, effective Aug 25, 2003
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200F, 747-200C, 747-300, 747-400, 747-400D, 747-400F, and 747SR Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections for cracking of the forward end clevis lugs of the flap track, and replacement of the flap track with a new flap track if necessary. That AD also currently provides for an optional modification of the forward end clevis lugs, which terminates the required inspections. This amendment expands the applicability of the existing AD, and requires new repetitive inspections for evidence of rotation or migration of the bushings or cracking of the lugs of the forward end clevis of the flap tracks that support the wing trailing edge flaps, corrective actions if necessary, and eventual accomplishment of a terminating action. These actions are necessary to prevent cracking and fracture of the forward end clevis of the flap track, which could result in reduced structural capability of the flap and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-14-16 · published Jul 21, 2003, effective Aug 25, 2003
Lockheed Model 382G Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 382G series airplanes, that requires repetitive general visual inspections of certain bearings located in the emergency exit door for evidence of excessive wear; and repair of certain bearings, which would terminate the repetitive inspections. This action is necessary to prevent failure of the latch mechanism, which could result in the inability to open the emergency exit door in an emergency. This action is intended to address the identified unsafe condition.
AD 2003-14-20 · published Jul 21, 2003, effective Sep 8, 2003
AeroSpace Technologies of Australia Pty Ltd. Models N22B and N24A Airplanes
This amendment supersedes Airworthiness Directive (AD) 82-12- 06, which applies to certain AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 82-12-06 currently requires repetitive visual inspections of all rudder control lever shaft assemblies for cracks and discrepancies, and, if cracks or discrepancies are found, it requires replacement with new or serviceable rudder control shafts, and a check of the fit of all rod end bearings in lever shafts. AD 82-12-06 also allows you to inspect all lever shafts by magnetic particle inspection or dye penetrant methods as terminating action for the repetitive visual inspections. This AD is the result of recent reports of failures of the upper control lever torque shaft due to fatigue loading on the affected airplanes, including those that included the terminating actions. This AD requires more detailed repetitive inspections (than there are in AD 82-12-06) of the upper and lower rudder pedal torque shafts and a one- time inspection for discrepancies in the thickness of the lever shaft side plates with appropriate follow-up action. The actions specified by this AD are intended to detect and correct cracks in the rudder control lever torque shafts and discrepancies in the thickness of the lever shaft side plates, which could result in failure of the rudder control lever torque shaft. Such failure could lead to reduced controllability of the airplane.
AD 2003-14-21 · published Jul 21, 2003, effective Aug 25, 2003
Lockheed Martin Models L-1011 Airplanes and Rolls-Royce plc RB211 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD) that is applicable to Lockheed Martin L-1011-385 series airplanes. That AD currently requires modifications of the engine turbine cooling air overheat monitoring panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and the installation of a high speed gearbox (HSGB) overheat detector system into the monitoring system for the engine turbine air temperature. This amendment requires the same modifications. In addition, this amendment adds Lockheed Martin L-1011-385 series airplanes with RB211-22B-02 series engines to the applicability, requires installation of a revised engine front bearing housing assembly, installation of a revised speed probe loom electrical support assembly, and installation of a low pressure (LP) compressor shaft extreme axial movement detector system. Also, this amendment requires additional modifications to the engine turbine cooling air overheat monitoring panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel. The actions specified by this AD are intended to prevent undetected fires originating within the HSGB from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire, and to prevent undetected LP compressor shaft location bearing failure, which could result in LP compressor and turbine shaft assembly failure, turbine overspeed, and possible uncontained engine failure.
AD 2003-15-02 · published Jul 24, 2003, effective Aug 28, 2003
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all EMBRAER Model EMB-145 series airplanes, that currently requires repetitive replacement of the bleed-air check valve and associated gaskets on the bleed low-pressure lines of the engines with new parts. This amendment continues to require repetitive replacement of the bleed-air check valves and associated gaskets. Additionally, this amendment provides for optional terminating action for the repetitive replacement of bleed-air check valves by installing new improved check valves, and adds airplanes to the applicability of the existing AD. This amendment also clarifies that the replacement and follow-on actions are required for the left- and right-hand engines. The actions specified by this AD are intended to prevent failure of the bleed-air check valves on the bleed low-pressure lines of the engines, which could result in engine compressor stall and consequent flameout of the affected engines. This action is intended to address the identified unsafe condition.
AD 2003-15-03 · published Jul 28, 2003, effective Sep 2, 2003
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires replacement of the aileron control override quadrant with a modified unit. The actions specified by this AD are intended to prevent corrosion of the input override mechanism bearings of the lateral central control actuator, which, in the event of a subsequent jam in the pilot's aileron control system, could result in failure of the aileron override system and consequent reduced lateral controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-15-04 · published Jul 28, 2003, effective Sep 2, 2003
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires inspection of the drive trunnion pins for the main landing gear (MLG) doors to determine the part number of the pins and corrective action if necessary. The actions specified by this AD are intended to prevent failure of the MLG and consequent reduced controllability of the airplane during takeoff or landing.
AD 2003-15-05 · published Jul 31, 2003, effective Sep 4, 2003
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 repetitive visual checks or inspections to verify that the flight idle stop system circuit breakers are closed, and functional tests to determine if the backup flight idle stop system is operative. This amendment requires modification of the secondary flight idle stop system (SFISS), which terminates the repetitive actions. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent inadvertent or intentional operation with the power levers below the flight idle stop during flight for airplanes that are not certificated for in-flight operation, which could result in engine overspeed and consequent loss of controllability of the airplane.
AD 2003-08-51 · published Jul 2, 2003, effective Jul 17, 2003
MD Helicopters, Inc. Model 369A, D, E, H, HE, HM, HS, F, and FF Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2003-08-51, which was sent previously to all known U.S. owners and operators of the specified model MD Helicopters, Inc. helicopters by individual letters. This AD requires reducing the retirement life of certain tail rotor blades, performing a one-time visual inspection of each tail rotor blade pitch horn (pitch horn) for a crack or corrosion, and replacing unairworthy tail rotor blades with airworthy tail rotor blades. This AD also requires revising the Airworthiness Limitations section of the helicopter maintenance manual to reflect the reduced retirement life, and reporting information to the FAA within 24 hours following the one- time inspection. The actions specified by this AD are intended to prevent a pitch horn from separating from the tail rotor blade, leading to an unbalanced condition, vibration, loss of tail rotor pitch control, and loss of directional control of the helicopter.
AD 2003-13-13 · published Jul 8, 2003, effective Aug 12, 2003
Bell Helicopter Textron Canada Model 222, 222B, and 222U Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires a one-time inspection of the adjustable stop screws of the magnetic brake assembly; repairing, as appropriate, certain mechanical damage to the cyclic and collective flight control magnetic brake arm assembly (arm assembly), if necessary; and installing the stop screw with the proper adhesive, adjusting the arm assembly travel, and applying slippage marks. This amendment is prompted by reports that the magnetic brake adjustable screws have backed out, which limited travel of the arm assembly. The actions specified by this AD are intended to detect loose adjustable stop screws that could result in limiting the travel of the cyclic and collective arm assembly, and subsequent loss of control of the helicopter.
AD 2003-13-14 · published Jul 8, 2003, effective Aug 12, 2003
Bell Helicopter Textron Canada Model 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters that requires performing a continuity test, temporarily repairing any unairworthy chip detector, and replacing any repaired chip detectors. This amendment is prompted by reports of poor or no continuity between the insert and the chip detector housing on certain chip detectors. The actions specified by this AD are intended to prevent failure of a chip detector indication, loss of a critical component, and subsequent loss of control of the helicopter.
AD 2003-13-15 · published Jul 8, 2003, effective Aug 12, 2003
Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, and TH-55A Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation (Schweizer) Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters, that currently requires inspecting the lugs on certain aft cluster fittings and each aluminum end fitting on certain tailboom struts. Modifying or replacing each strut assembly within a specified time period and serializing certain strut assemblies are also required by the existing AD. This amendment requires the same actions as the existing AD, and also requires a one-time inspection and repair, if necessary, of certain additional cluster fittings, and replacement and modification of certain cluster fittings within 150 hours time-in-service (TIS) or 6 months, whichever occurs first. This amendment is prompted by the need to expand the applicability to include certain Hughes-manufactured cluster fittings and to provide a terminating action for the repetitive dye-penetrant inspections of the cluster fittings. The actions specified by this AD are intended to prevent failure of a tailboom support strut or a cluster fitting, which could cause rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter.
AD 2003-14-19 · published Jul 17, 2003, effective Aug 21, 2003
Eurocopter France Model SA-365N, N1, AS-365N2, AS 365 N3, SA-366G1, AS355F, F1, F2, N, and EC130 B4 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires removing certain main servocontrols and replacing them with servocontrols that do not fall within the "Applicability" of this AD at specified intervals. This amendment is prompted by the discovery of an incorrect tightening torque load found on servocontrols that were overhauled by Hawker Pacific Aerospace. The actions specified by this AD are intended to prevent thread failure, separation of the upper end fitting that attaches the servocontrol cylinder to the upper ball end- fitting, and subsequent loss of control of the helicopter.
AD 2003-14-12 · published Jul 21, 2003, effective Aug 25, 2003
Eurocopter France Model SA330F, G, and J; AS332C, L, and L1; SA341G; SA342J; AS350B, BA, B1, B2, B3, and D; AS355E, F, F1, F2 and N; SA-365C, C1, and C2; SA-365N and N1; and AS-365N2 and N3 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires determining whether specified main or tail rotor (rotor) parts are installed and, if so, updating and recording the correct hours time-in- service (TIS) or cycles of each part. If the hours TIS or cycles of any rotor part exceed its life limit, this AD also requires replacing that part with an airworthy part within 50 hours TIS. This amendment is prompted by the need to correct the Equipment Log Card (FME) to accurately reflect the total hours TIS and cycles of certain repaired or overhauled rotor parts. The actions specified by this AD are intended to prevent failure of a life limited rotor part, loss of a rotor, and subsequent loss of control of the helicopter.
AD 2003-14-18 · published Jul 21, 2003, effective Aug 25, 2003
Sikorsky Aircraft Corporation Model S76A, B, and C Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters that requires removing non-conforming main landing gear brake discs (discs) and replacing them with different part-numbered airworthy discs. It also requires revising the Rotorcraft Flight Manual (RFM) to adjust takeoff and landing distances until the discs are replaced. This amendment is prompted by the manufacture of some discs using inferior materials. The actions specified by this AD are intended to prevent reduced braking performance and subsequent loss of control of the helicopter.
AD 2003-14-03 · published Jul 10, 2003, effective Aug 14, 2003
Textron Lycoming Fuel Injected Reciprocating Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Textron Lycoming reciprocating engines with certain Crane/Lear Romec "AN" rotary fuel pumps installed. That AD currently requires initial and follow-up torque check inspections of pump relief valve attaching screws. This amendment requires the same initial and follow-up torque check inspections of relief valve attaching screws, and adds as a terminating action, replacement of the affected fuel pump at or before the overhaul interval, with a fuel pump having a new design valve housing. This amendment is prompted by the introduction of a new design pump relief valve housing and associated parts that provide enhanced resistance to fuel leakage, and the need for clarification of the requirements of the current AD. The actions specified by this AD are intended to prevent rotary fuel pump leaks, which could result in an engine failure, engine fire, and damage to or loss of aircraft.
AD 2003-14-23 · published Jul 17, 2003, effective Aug 1, 2003
Rolls-Royce plc RB211-524G2, -524G2-T, -524G3, -524G3-T, -524H, -524H-T, -524H2, and -524H2-T Series, and Models RB211 Trent 768-60, 772-60, and 772B-60 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-524G2, -524G2-T, -524G3, -524G3-T, -524H, - 524H-T, -524H2, and -524H2-T series, and models RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines with high pressure compressor (HPC) rotor stage 1 through stage 6 drums, part numbers (P/Ns) FK25502 and FW20195 installed. This AD is prompted by reports of cracks found in loading slots of HPC rotor stage 1 through stage 6 drums. We are issuing this AD to prevent crack initiation and propagation leading to uncontained failure of the HPC rotor stage 1 through stage 6 drum, and damage to the airplane.
AD 2003-15-06 · published Jul 30, 2003, effective Sep 3, 2003
Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that applies to Rolls-Royce plc (RR) RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with high pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers (P/Ns) FK25230 and FK27899 installed. This amendment requires removal from service of these HP compressor rotor rear stage 5 and 6 discs and cone shafts, before reaching newly reduced life limits. This amendment is prompted by three reports of crack indications in the stage 5 and stage 6 blade loading slots, found during engine overhaul. We are issuing this AD to prevent stage 5 and 6 disc crack initiation and propagation leading to uncontained disc failure and damage to the airplane.
AD 2003-13-17 · published Jul 3, 2003, effective Jul 18, 2003
Hartzell Propeller, Inc., McCauley Propeller Systems, Sensenich Propeller Manufacturing Company, Inc., and Raytheon Aircraft Company Propellers
The FAA is adopting a new airworthiness directive (AD) for certain Hartzell Propeller, Inc., McCauley Propeller Systems, Sensenich Propeller Manufacturing Company, Inc., and Raytheon Aircraft Company (formerly Beech Aircraft Corporation) propellers returned to service by T and W Propellers, Inc., of Chino, CA. This AD requires maintenance actions amounting to an overhaul of the affected propellers. This AD is prompted by the results of a National Transportation Safety Board (NTSB) investigation of a failed propeller blade and subsequent inspections of various propeller models returned to service by T and W Propellers, Inc. We are issuing this AD to detect unsafe conditions that could result in separation of a propeller blade and loss of control of the airplane.
AD 2003-15-01 · published Jul 17, 2003, effective Jul 17, 2003
McCauley Propeller Systems, Inc. Propeller Hub Models B5JFR36C1101, C5JFR36C1102, B5JFR36C1103, and C5JFR36C1104
The FAA is adopting a new airworthiness directive (AD) for certain McCauley Systems, Inc. propellers that are installed on BAE Systems (Operations) Limited Jetstream Model 4101 airplanes. This AD requires a fluorescent penetrant inspection (FPI) of the propeller blades for cracks. This AD is prompted by a report of a significant crack in a propeller blade shank and two reports of cracks in the hubs of the same propeller model. We are issuing this AD to detect cracks in the propeller blade shank that could cause a failure of the propeller blade and loss of control of the airplane.
AD 2003-15-07 · published Jul 30, 2003, effective Sep 3, 2003
Honeywell International Inc. (Formerly AlliedSignal) Model RE220 (RJ) Auxiliary Power Units
This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International Inc. (formerly AlliedSignal) model RE220 (RJ) auxiliary power units (APUs) part number (P/N) WE3800770-2. This amendment requires replacing the existing fuel nozzles with new design fuel nozzles, making reidentification updates to the APU identification plate, and operating the APU to perform a visual inspection for fuel leaks. This amendment is prompted by reports received by the FAA of cracks occurring in the existing APU fuel nozzles leading to fuel leaks. The actions specified by the AD are intended to prevent APU compartment fires and fuel vapor explosion.
