40 Airworthiness Directives: 28 airplane, 5 rotorcraft, 5 engine, 1 glider, 1 various.
AD 2003-07-01 · published Apr 1, 2003, effective May 20, 2003
Quality Aerospace, Inc. S2R Series and Model 600 S2D Airplanes
This amendment supersedes Airworthiness Directive (AD) 2000- 11-16, which currently applies to certain Quality Aerospace, Inc. (Quality Aerospace) (formerly Ayres Corporation) S2R series and Model 600 S2D airplanes. AD 2000-11-16 requires you to repetitively inspect the \1/4\-inch and \5/16\-inch bolt hole areas on the lower spar caps for fatigue cracking; replace or repair any lower spar cap where fatigue cracking is found; and report any fatigue cracking found. AD 2000-11-16 resulted from an accident of an Ayres S2R series airplane where the wing separated from the airplane in flight. Since AD 2000-11- 16, additional airplanes have been identified that were manufactured with a similar design to those affected by the AD and a third repair option has been developed. This AD retains the repetitive inspections and replacement (if necessary) requirements of the lower spar caps that are currently required in AD 2000-11-16, adds additional airplanes to the Applicability of the AD, and adds a third repair option. The actions specified by this AD are intended to detect and correct fatigue cracking of the lower spar caps, which could result in the wing separating from the airplane with consequent loss of control of the airplane.
AD 2003-07-03 · published Apr 3, 2003, effective May 16, 2003
Twin Commander Aircraft Corporation Models 690D, 695A, and 695B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Twin Commander Aircraft Corporation (TCAC) Models 690D, 695A, and 695B airplanes. This AD requires you to initially inspect and modify and repetitively inspect areas of the wing and fuselage structure for fatigue damage and modify or replace any damaged parts. This AD is the result of tests that show that the service life of certain airplane parts cannot be reached unless an inspection and modification program (with any necessary replacements or modifications if fatigue damage is found) is incorporated. The actions specified by this AD are intended to detect and correct fatigue damage in the wing and fuselage areas without reducing the service life of the airplane. Such undetected and uncorrected damage could result in structural failure with consequent loss of control of the airplane.
AD 2003-07-04 · published Apr 3, 2003, effective May 22, 2003
Air Tractor, Inc. Models AT-300, AT-400, AT-400A, AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501, AT-502, and AT-502B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-300, AT- 400, AT-400A, AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501, AT- 502, and AT-502B airplanes. This AD requires you to repetitively inspect the vertical fin front spar fitting for cracks and replace any cracked fitting found. This AD also requires you to install a steel doubler as a terminating action for the repetitive inspections. This AD is the result of a report of failure of a \1/4\-inch thick vertical fin front spar fitting. The actions specified by this AD are intended to prevent failure of the vertical fin front spar fitting, which could result in failure of the rear spar fitting. Such failures could lead to loss of directional control of the airplane.
AD 2003-07-06 · published Apr 3, 2003, effective May 22, 2003
British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes. This AD requires you to inspect the steering jack piston rod for cracks and replace if necessary; measure the torque setting of the steering jack piston rod end fitting and stop bolt; and measure the thickness of the tab washers. This AD also requires you to calculate a new safe life limit for the steering jack piston rod based on the results of the inspection and the measurements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect, correct, and prevent cracks in the steering jack piston rod, which could result in failure of the steering jack piston rod. Such failure could lead to loss of steering control of the airplane during takeoff, landing, and taxi operations.
AD 2003-07-07 · published Apr 3, 2003, effective May 8, 2003
Raytheon Model BAe.125 Series 800A, 800A (C-29A), 800A (U-125), and 800B Airplanes; Model BH.125 Series 400A Airplanes; Model DH.125 Series Airplanes; Model Hawker 800, 800 (U-125A), and 800XP Airplanes; and Model HS.125 Series F3B, F3B/RA, F400B, F403B, 1B, 1B-522, 1B/R-522, 1B/S-522, 3B, 3B/R, 3B/RA, 3B/RB, 3B/RC, 400B, 400B/1, 401B, 403A(C), and 403B Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon airplanes, that requires inspection of the main landing gear (MLG) wheels to determine the part numbers of the tie-bolt nuts, and replacement of nuts that have the incorrect part number with nuts that have the correct part number. The actions specified by this AD are intended to prevent separation of an MLG wheel due to loose or missing tie-bolts or tie-bolt nuts, with consequent damage to airplane structure or systems, decompression, loss of full braking ability, or injury to personnel on the ground. This action is intended to address the identified unsafe condition.
AD 2003-07-08 · published Apr 3, 2003, effective Apr 18, 2003
Boeing Model 757-200, 757-200CB, and 757-200PF Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200, 757-200CB, and 757-200PF series airplanes. This action requires repetitive detailed inspections to detect horizontal or vertical movement of the shims at the joint of the mid-bulkhead and the upper link fittings, and corrective action if necessary; or certain alternative actions that will terminate the requirement for the repetitive inspections. This action is necessary to detect and correct migration of shims at the joint of the mid-bulkhead and the upper link fittings, which could result in cracking of the strut and consequent loss of the strut and engine.
AD 2003-07-09 · published Apr 3, 2003, effective Apr 7, 2003
Raytheon Aircraft Company Model 390 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to incorporate information into the FAA-approved Airplane Flight Manual (AFM) that would add requirements for "Landing Performance for Operation of the Airplane with Lift Dump Inoperative." This AD is the result of two accidents on the affected airplanes where a contributing factor was the lift dump spoilers failing to deploy when commanded after the initial landing. The actions specified by this AD are intended to require the use of necessary flight information to prevent runway overruns based on insufficient aerodynamic and wheel braking if the lift dump spoilers do not operate after landing touchdown. This could result in reduced or loss of control of the airplane.
AD 2003-07-10 · published Apr 8, 2003, effective May 12, 2003
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC- 12/45 airplanes. This AD requires you to replace certain push switch caps on the electrical power management overhead panel with parts of improved design. 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 the inability to operate the switch, which could result in failure to activate the related operational system. Such failure could adversely affect the operation and control of the airplane.
AD 2003-07-14 · published Apr 10, 2003, effective May 15, 2003
McDonnell Douglas DC-10-30 Airplane
This amendment adopts a new airworthiness directive (AD), applicable to a single McDonnell Douglas Model DC-10-30 airplane, that requires repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/ transfer pump connectors; and corrective actions, if necessary. This action is necessary to prevent arcing of connectors in the fuel boost/ transfer pump circuit, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
AD 2003-07-12 · published Apr 15, 2003, effective May 20, 2003
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 inspection of landing gear parts and/or their records to see that parts have serial numbers and that each part's number of flight cycles has been tracked; assignment of serial numbers and flight cycle use numbers if necessary; and removal of individual landing gear components from service when they reach their life limit. This amendment also requires adding landing gear parts to the lists of safe-life components, and assigning life limits to landing gear parts already in service. The actions specified by this AD are intended to prevent failure of landing gear parts, which could lead to landing gear collapse. This action is intended to address the identified unsafe condition.
AD 2003-07-13 · published Apr 15, 2003, effective May 20, 2003
Boeing Model 757-200, -200CB, and -200PF Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires repetitive inspections for excessive wear of the internal and external splines of the torque tube couplings of the trailing edge flaps, and replacement of the couplings, if necessary. That AD also provides an optional modification that, if installed, constitutes terminating action for the inspection requirements. This amendment expands the applicability of the existing AD and requires new inspections of the torque tube assemblies and certain gearbox assemblies and universal joints in the drive system for the inboard trailing edge flaps, and follow-on actions if necessary. For certain airplanes, this amendment also adds a new optional modification, which, if installed, terminates certain inspections. The actions specified by this AD are intended to prevent separations in the drive system for the inboard trailing edge flaps, which could cause a flap skew condition that could result in damage to the flaps or fuselage, and consequent reduced controllability of the airplane.
AD 2003-08-02 · published Apr 15, 2003, effective Apr 30, 2003
McDonnell Douglas Model MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes. This action requires a one-time inspection for chafing or damage of the cable assemblies and follow-on modification of the cable assemblies of the powered seats located in the first-class cabin. This action is necessary to prevent chafing and damage of the cable assemblies due to contact between the cable and the metal retaining clip on the seat leg, which could result in electrical arcing and consequent smoke and/or fire in the cabin. This action is intended to address the identified unsafe condition.
AD 2003-07-15 · published Apr 16, 2003, effective May 21, 2003
Boeing Model 767-300 Series Airplanes Modified by Supplemental Type Certificate ST01783AT-D
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-300 series airplanes modified by Supplemental Type Certificate ST01783AT-D, that requires modifying the in-flight entertainment (IFE) system and revising the airplane flight manual. The actions specified by this AD are intended to ensure that the flight crew is able to remove electrical power from the IFE system when necessary and is advised of appropriate procedures for such action. Inability to remove power from the IFE system during a non- normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
AD 2003-08-03 · published Apr 17, 2003, effective May 22, 2003
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, and MD-10-30F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models. This amendment requires repetitive inspections for chafing or potential chafing of the wiring for the throttle control module (TCM) on the center pedestal in the flight deck compartment, corrective actions if necessary, an inspection of the TCM to determine its part number and configuration, and modification of the TCM. Doing this modification terminates the repetitive inspections. The actions specified by this AD are intended to prevent chafing of wiring inside the TCM, fuel shutoff lever lights, and/or aft pedestal lightplates due to degradation of protective sleeving, which could result in electrical arcing and failure of the auto throttle/ speed control system and consequent smoke and/or fire in the cockpit.
AD 2003-04-16 · published Apr 21, 2003, effective May 27, 2003
McDonnell Douglas Model MD-11 and MD-11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes that requires an inspection to detect chafed wires in the avionics equipment compartment, and repair, if necessary. This amendment also requires replacement of the existing cover of the avionics cooling fan with a new cover, and installation of a new placard on the cover. Additionally, this amendment specifies which previously accomplished actions are acceptable for compliance with certain requirements of this AD; and clarifies the applicability, a part number, and the inspection definition. The actions specified by this AD are intended to ensure that the cover of the avionics cooling fans is removed only for fan maintenance, and to prevent smoke and/or fire in the avionics equipment compartment due to chafing and arcing as a result of maintenance personnel lying against the removed cover and/ or insulation blankets that cover wire harnesses. This action is intended to address the identified unsafe condition.
AD 2003-04-17 · published Apr 21, 2003, effective May 27, 2003
McDonnell Douglas Model MD-11 and MD-11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that requires an inspection to detect damage of the wiring/ bundles routed to the wire support bar of the circuit breaker panel and to the circuit breakers, and an inspection of the wiring/bundles for correct routing. This amendment also requires installation of protective sleeving, spacers, and sta-straps; and corrective/follow-on actions, if necessary. The actions specified by this AD are necessary to prevent chafing and consequent arcing or loss of electrical power to associated avionics buses in the upper avionics circuit breaker panel of the main observer's station, which could result in smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2003-06-51 · published Apr 21, 2003, effective Apr 28, 2003
Learjet Model 45 Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-06-51 that was sent previously to all known U.S. owners and operators of certain Learjet Model 45 airplanes by individual notices. This AD requires an inspection to determine the part number of the horizontal stabilizer actuator assembly (A66), and replacement of any suspect horizontal stabilizer actuator assembly (A66) with a new or serviceable actuator assembly (A66). This action is prompted by a report of severe vibration followed by a rapid nose down pitch change on a Learjet Model 45 airplane. The actions specified by this AD are intended to prevent structural failure of the horizontal stabilizer actuator assembly, which could result in possible loss of control of the airplane.
AD 2003-08-08 · published Apr 21, 2003, effective May 27, 2003
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that currently requires, among other actions, a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors; repair, if necessary; and installation or modification of a flapper door ramp deflector on the forward entry drop ceiling structure. That AD also currently requires an inspection of the wire assembly support installation above the entry door (L1) sliding panel for chafing, and repair, if necessary. This amendment requires the existing requirements and requires replacing the wire support bracket with new support clip assemblies. The actions specified by this AD are intended to prevent chafing of electrical wire assemblies above the forward passenger doors and above the entry door (L1) sliding panel of the forward drop ceiling on the passenger compartment, which could result in electrical arcing, and consequent electrical fire in the passenger compartment. This action is intended to address the identified unsafe condition.
AD 2003-08-09 · published Apr 21, 2003, effective May 27, 2003
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that currently requires a one-time detailed inspection to detect discrepancies of all electrical wiring installations in various areas of the airplane; and corrective actions, if necessary. This amendment requires another identical inspection in additional fuselage stations, and corrective actions, if necessary. This amendment is prompted by a report from the airplane manufacturer that it failed to include 41 inches of fuselage in the previously required inspection. The actions specified by this AD are intended to prevent electrical arcing and/or heat damaged wires due to improper wire installations during manufacture and/or maintenance of the airplane, and consequent fire and smoke in various areas of the airplane.
AD 2003-08-10 · published Apr 21, 2003, effective May 27, 2003
Aerospatiale Model ATR42-500 Series Airplanes, and Model ATR72-102, -202, -212, and -212A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 series airplanes, and Model ATR72-102, -202, -212, and -212A series airplanes, that requires replacement of insulation blankets constructed of metallized polyethyleneteraphthalate (MPET) located from sections 11 through 16 of the fuselage with new insulation blankets constructed of Terul 18<SUP>TM</SUP>. This amendment is prompted by reports of in-flight and ground fires on certain airplanes manufactured with insulation blankets constructed of MPET, which may contribute to the spread of a fire when ignition occurs from small ignition sources such as electrical arcing or sparking. The actions specified by this AD are intended to ensure that insulation blankets constructed of MPET are removed from the fuselage. Such insulation blankets could propagate a small fire that is the result of an otherwise harmless electrical arc and could lead to a much larger fire. This action is intended to address the identified unsafe condition.
AD 2003-08-11 · published Apr 23, 2003, effective May 8, 2003
Boeing Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes; and Model 747SR Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F series airplanes; and Model 747SR series airplanes. This action requires repetitive inspections to detect discrepancies of the actuator attach fittings of the inboard and outboard flaps, and follow-on and corrective actions as necessary. This action is necessary to detect and correct cracking and other damage of the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and possible loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-08-12 · published Apr 23, 2003, effective May 8, 2003
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 adopts a new airworthiness directive (AD) that is 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. This action requires a detailed inspection to detect cracks of the vane brackets of the inboard flap actuator beam, and follow-on repetitive detailed inspections or corrective actions, as applicable. This action also provides for two optional terminating actions for the detailed inspection(s). This action is necessary to detect and correct gaps between the flap vane bracket and the adjacent lower skin and between the flap vane bracket and vane actuator beam of the wing flap systems, and premature cracking of the flap vane brackets, which could result in failure of the flap vane bracket(s) when the flaps are extended and the flap vane is aerodynamically loaded. Loss or warping of the flap vane in flight could decrease the lift on one side of the airplane, which could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-08-14 · published Apr 25, 2003, effective May 12, 2003
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) that is applicable to certain McDonnell Douglas airplane models. This action requires revising the airplane flight manual (AFM) to include new operating limitations, installing placards to advise the flightcrew of certain minimum fuel levels to be maintained in the fuel tanks, and deactivating certain auxiliary fuel tanks. For fuel tanks that are not deactivated, this AD also requires replacement of certain existing fuel boost/transfer pumps with pumps inspected--and modified, if necessary-- per certain procedures. Accomplishment of this replacement will allow operators to remove the operating limitations from the AFM, remove the placards, and reactivate the auxiliary fuel tanks (if deactivated). This action is necessary to prevent electrical arcing in the connector for a fuel boost/transfer pump, which could result in a fire or explosion of a fuel tank. This action is intended to address the identified unsafe condition.
AD 2003-08-15 · published Apr 25, 2003, effective May 12, 2003
Boeing Model 737-200, -200C, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200, -200C, -300, -400, and - 500 series airplanes. This action requires a one-time mid-frequency eddy current (MFEC), a low-frequency eddy current (LFEC), and a detailed inspection for damage or cracking of stringer S-4L and S-4R lap joints and stringer clips between body station (BS) 540 and BS 727, and follow-on inspections and repair if necessary. This action is necessary to find and fix cracking of the fuselage lap joints, which could result in sudden decompression of the airplane.
AD 2003-08-16 · published Apr 25, 2003, effective May 30, 2003
McDonnell Douglas Model 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 inspection for chafing of the RDB wire bundle against the No. 2 automatic direction finder (ADF) receiver located at the aft end of the forward right radio rack; repair or replacement, if necessary; and modification of the wire bundle. The actions specified by this AD are intended to prevent chafing of the RDB wire bundle against the No. 2 ADF receiver, which could result in electrical arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2003-09-01 · published Apr 29, 2003, effective Jun 17, 2003
Pilatus Aircraft Ltd. Model PC-6 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Model PC-6 airplanes. This AD requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. 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 detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight.
AD 2003-09-03 · published Apr 29, 2003, effective May 14, 2003
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires repetitive inspections of the spring cartridges of the elevator gust lock system to determine if the lock washer projection correctly fits the slots in the cartridge flange, and corrective action if necessary. This action also provides for optional terminating action for certain airplanes. This action is necessary to prevent the elevator from jamming due to the spring cartridges unscrewing in the gust lock system, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-09-04 · published Apr 29, 2003, effective May 14, 2003
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 by incorporating new structural inspection intervals for the pressure floor skin of the center fuselage at fuselage stations 460 and 513; repair if necessary; and submission of inspection findings to the airplane manufacturer. This action is necessary to detect and correct in a timely manner fatigue cracks of the pressure floor skin of the center fuselage at fuselage stations 460 and 513, which could result in failure of the pressure floor skin and consequent rapid decompression of the airplane during flight. This action is intended to address the identified unsafe condition.
AD 2003-08-05 · published Apr 14, 2003, effective May 19, 2003
Eurocopter France Model AS350B3 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the ASU No. 2 printed circuit board (PCB) to determine if the resistor R8 is installed, and if it is not installed, replacing the PCB with an airworthy PCB with that resistor installed. This amendment is prompted by the discovery of a PCB without a critical resistor that polarizes the voltage regulator that regulates electrical power to a critical warning light, a critical caution light, and the main rotor revolutions per minute (RPM) signal to the vehicle engine management display (VEMD). The actions specified by this AD are intended to prevent the malfunction of the two critical lights and the rotor RPM signal to the VEMD, failure of these components to timely alert the pilot to the associated malfunctions, further helicopter damage because of these malfunctions, and subsequent loss of control of the helicopter.
AD 2003-08-07 · published Apr 16, 2003, effective May 1, 2003
Bell Helicopter Textron Canada Model 222, 222B, 222U, and 230 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, and 230 helicopters. This action requires inspecting the main rotor pendulum weight support (pendulum weight support) for file or grinding marks, gouges, and appropriate edge breaks. It also requires, if necessary, reworking and remarking or replacing the pendulum weight support. Regardless, this AD requires a magnetic particle inspection for a crack and replacing the pendulum weight support if a crack is found. This amendment is prompted by a pendulum weight support failure and shedding of the pendulum weight set in flight and a subsequent determination of manufacturing defects on certain serial-numbered pendulum weight supports. This condition, if not corrected, could result in the pendulum weights separating from the pendulum weight support and striking the vertical fin or tail rotor, and subsequent loss of control of the helicopter.
AD 2003-08-04 · published Apr 17, 2003, effective May 22, 2003
Eurocopter France Model EC120B Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified model Eurocopter France (ECF) helicopters that requires inspecting the attachment of the bolted assemblies of the cyclic pitch flight control torque tube (torque tube) for an appropriate locking device. If a bolted assembly is single-locked, the AD requires, if necessary, tightening the self-locking nuts at certain intervals and modifying the torque tube after a certain time. This amendment is prompted by the discovery that some of the attachments of the torque tube were fastened with a single-locking device instead of the intended double-locking device. The actions specified by this AD are intended to prevent separation of the cyclic pitch stick yokes from the torque tube, loss of cyclic control, and subsequent loss of control of the helicopter.
AD 2003-08-06 · published Apr 17, 2003, effective May 22, 2003
Eurocopter France Model AS350B, B1, B2, BA, and D Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter model helicopters that requires fireproofing the engine oil tank breather pipe (breather pipe) where it passes through the firewall from the engine compartment to the main gearbox compartment. This amendment is prompted by the discovery of a design deficiency that permitted the installation of a non-fireproof breather pipe. The actions specified by this AD are intended to prevent the spread of fire between two designated fire zones of the helicopter, additional structural damage, and a decrease in the time available to execute an emergency landing.
AD 2001-13-03 R1 · published Apr 21, 2003, effective May 27, 2003
Kaman Aerospace Corporation Model K-1200 Helicopters
This amendment revises an existing airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters that currently requires reducing the life limit of the rotor shaft and teeter pin assembly and establishing a life limit for the flap clevis. This amendment retains those requirements but removes a flap clevis part number from the applicability and, as a result of a comment, changes the application of the life limit from the flap clevis to the flap clevis assembly. This amendment is prompted by the determination after an analysis of testing results that a certain flap clevis assembly should have an unlimited life. The actions specified by this revision are intended to remove the life limit for a specified flap clevis assembly. The actions specified by this AD are intended to prevent fatigue failure of the rotor shaft, teeter pin assembly, and flap clevis assembly, and subsequent loss of control of the helicopter.
AD 2003-07-02 · published Apr 2, 2003, effective May 7, 2003
Rolls-Royce Corporation (Formerly Allison Engine Company) 501-D Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) 501-D series turboprop engines. This amendment requires removal from service of certain turbine rotor components at reduced life limits. This amendment is prompted by the result of recalculated material properties by the manufacturer. The actions specified by this AD are intended to prevent uncontained turbine rotor failure resulting in in-flight engine shutdown and possible damage to the airplane.
AD 2003-07-11 · published Apr 11, 2003, effective Apr 28, 2003
Rolls-Royce Deutschland Ltd & Co KG Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) models BR700-710A1-10 turbofan engines with fan disc part numbers (P/ Ns) BRR18803, BRR19248, or BRR20791 installed, and BR700-710A2-20 turbofan engines with fan discs P/Ns BRR19248 or BRR20791 installed. That AD currently requires initial and repetitive inspections of these fan discs for cracks, and if necessary replacement with serviceable parts. This amendment requires the same inspections but with longer intervals between repetitive inspections under certain conditions, and requires removal of any dry film lubricant coating from the front face of the fan disc for visual inspections. This amendment is prompted by reevaluation by RRD of results from a fleet-wide inspection campaign, reevaluation of existing repetitive inspection interval requirements, and by a revised service bulletin (SB) that introduces improved inspection procedures. The actions specified by this AD are intended to detect cracks in the fan disc, that could result in an uncontained engine failure and damage to the airplane.
AD 2003-08-01 · published Apr 15, 2003, effective May 20, 2003
Rolls-Royce Deutschland Ltd & Co KG Engines
The FAA is adopting a new airworthiness directive (AD) for certain serial numbers (SNs) of Rolls-Royce Deutschland Ltd. & Co KG (RRD) Model Tay 650-15 turbofan engines. This action requires initial and repetitive visual inspections of low pressure (LP) turbine stage 2 rotor discs and LP turbine stage 3 rotor discs on certain SNs of engines, for corrosion. This AD is prompted by reports of excessive corrosion found during disc inspection. The actions specified in this AD are intended to prevent uncontained LP turbine stage 2 rotor disc or LP turbine stage 3 rotor disc failure due to excessive corrosion, and damage to the airplane.
AD 2003-09-02 · published Apr 29, 2003, effective Jun 3, 2003
Pratt and Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to certain serial number (SN) Pratt and Whitney (PW) models PW4164, PW4168, and PW4168A turbofan engines. This amendment requires operators to initially and repetitively borescope-inspect 14th and 15th stage rubstrips located on the 13th and 14th stage stator set for wear. This amendment is prompted by reports of high pressure compressor (HPC) surges during the takeoff phase of flight that have been attributed to increased stage 14 and stage 15 HPC blade tip clearances caused by excessive wear on the HPC inner rear case rear hook. The actions specified by this AD are intended to prevent engine power loss during takeoff due to HPC surge.
AD 2003-09-06 · published Apr 29, 2003, effective Jun 3, 2003
General Electric Company CF6-50 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-50 series turbofan engines. This amendment requires removal from service of eight serial number (SN) low-pressure turbine (LPT) stage 1 disks, part number (P/N) 9061M21P03, at the next engine shop visit. This amendment is prompted by a report of the potential for iron-rich inclusions introduced during manufacture in the affected disks. The actions specified by this AD are intended to prevent LPT stage 1 disk cracking, due to iron-rich inclusions introduced during manufacture, leading to uncontained disk failure.
AD 2003-07-05 · published Apr 3, 2003, effective May 22, 2003
Stemme GmbH & Co. KG Models S10 and S10-V Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Stemme GmbH & Co. KG (Stemme) Models S10 and S10-V sailplanes. This AD requires you to modify the engine compartment fuel and oil system and firewall. This AD is the result of FAA's determination that the actions required in AD 2002-22-04 should also be accomplished on other sailplanes of similar type design. The actions specified by this AD are intended to reduce the potential for a fire to ignite in the engine compartment and to increase the containment of an engine fire in the engine compartment. A fire in the engine compartment could lead to loss of control of the sailplane.
AD 2003-08-13 · published Apr 22, 2003, effective May 7, 2003
Various Surplus Military Airplanes Manufactured by Consolidated, Consolidated Vultee, and Convair
This amendment adopts a new airworthiness directive (AD) that is applicable to various surplus military airplanes manufactured by Consolidated, Consolidated Vultee, and Convair. This action requires repetitive inspections to find fatigue cracks in the lower rear cap of the wing front spar, front spar web, and lower skin of the wings; repair or replacement of any cracked part with a new part; and follow- on inspections at new intervals. This action is necessary to find and fix fatigue cracking, which could result in structural failure of the wings and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
