36 Airworthiness Directives: 27 airplane, 3 rotorcraft, 6 engine.
AD 2002-02-01 · published Feb 4, 2002, effective Mar 21, 2002
Eagle Aircraft Pty. Ltd. Model 150B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Eagle Aircraft Pty. Ltd. (Eagle) Model 150B airplanes. This AD requires you to modify the attachment of the port and starboard throttle arms, and the starboard bushing of the throttle torque tube. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The actions specified by this AD are intended to prevent failure of the throttle control assembly caused by rivets of the wrong size. Such failure could lead to reduced control of the airplane.
AD 2002-02-02 · published Feb 4, 2002, effective Mar 11, 2002
Boeing Model 707 and 720 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707 and 720 series airplanes, that requires installation of a new support structure for the trailing edge beam and main landing gear uplock mechanism. This action is necessary to prevent cracking in the frame and adjacent structure near the attach bolt of the main landing gear uplock mechanism, which could lead to compromised structural integrity. This action is intended to address the identified unsafe condition.
AD 2002-02-03 · published Feb 7, 2002, effective Mar 14, 2002
BAE Systems (Operations) Limited Model BAe 146 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 series airplanes, that requires repetitive inspections to detect cracking of the horizontal butt joint of the rear pressure bulkhead and repair, as necessary. This amendment also requires installation of new joint plates on the aft face of the rear pressure bulkhead, which terminates the requirements of this AD. This action is necessary to prevent cracking of the horizontal butt joint of the rear pressure bulkhead, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-02-04 · published Feb 12, 2002, effective Mar 19, 2002
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires a one-time inspection of a wire bundle in the left wing front spar for chafing and for proper installation of a Teflon sleeve; corrective action, if necessary; and installation of extra protection against chafing. This action is necessary to prevent chafing between the wire bundle and the left wing front spar, which could result in electrical arcing and subsequent ignition of flammable vapors and possible uncontrollable fire. This action is intended to address the identified unsafe condition.
AD 2002-02-05 · published Feb 12, 2002, effective Mar 19, 2002
Airbus Model A300 B2 and A300 B4; A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600); and Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600); and A310 series airplanes. This AD requires repetitive overhaul, including associated modifications, of the ram air turbine (RAT). This action is necessary to prevent failure of the RAT to deploy or operate properly in the event of an emergency, which could result in reduced hydraulic pressure or electrical power on the airplane. This action is intended to address the identified unsafe condition.
AD 2002-02-06 · published Feb 12, 2002, effective Feb 27, 2002
Airbus Model A330-243, -341, -342, and -343 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330-243, -341, -342, and -343 series airplanes. This action requires modifying the rear engine mount by replacing the existing fail-safe link with a new, improved fail-safe link. This action is necessary to prevent failure of the fail-safe link of the rear engine mount, which, in combination with failure of the primary load path for the engine, could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2002-02-07 · published Feb 12, 2002, effective Mar 19, 2002
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 repetitive inspections and operational checks of the spring function of the emergency exit door slider mechanism, and corrective action if necessary. This action is necessary to prevent failure of the spring locking function of the slider mechanism due to corrosion, which could result in the escape slide detaching from the airplane in an emergency evacuation. This action is intended to address the identified unsafe condition.
AD 2002-02-08 · published Feb 12, 2002, effective Mar 19, 2002
Boeing Model 737-200, -200C, -300, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-200, -200C, -300, and -500 series airplanes, that requires replacement of the bolt and self- locking nut on the primary support pin of the main landing gear (MLG) support beam with a new bolt, castellated nut, washer, and cotter pin. This action is necessary to prevent the loosening and loss of the support pin retaining bolt on the MLG, which could result in the loosening and movement of the support pin and consequent cracked support fittings and collapse of the MLG. This action is intended to address the identified unsafe condition.
AD 2002-02-10 · published Feb 12, 2002, effective Mar 25, 2002
Pilatus Britten-Norman Limited BN-2, BN-2A, BN-2B, and BN-2T Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Britten-Norman Limited (Pilatus Britten- Norman) BN-2, BN-2A, BN-2B, and BN-2T series airplanes. This AD requires you to repetitively inspect the inboard brackets of the elevator outboard hinge for loose rivets, structural damage, or cracks and replace any suspect bracket. This AD also requires you to replace the hinge bracket at a certain time period if no discrepancies are found. This replacement includes modifying this area and installing modified brackets. This replacement allows you to increase the time period between inspections (reduce the number of repetitive inspections). 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 and correct inboard brackets of the elevator outboard hinge with loose rivets, structural damage, or cracks. Such conditions could cause the outboard elevator to become loose with a consequent reduction in elevator and airplane control.
AD 2002-02-11 · published Feb 12, 2002, effective Mar 25, 2002
Pilatus Britten-Norman Limited BN-2, BN-2A, BN-2B, BN-2T, and BN2A MK. III Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman) BN-2, BN-2A, BN-2B, BN-2T, and BN2A MK. III series airplanes. This AD requires you to repetitively inspect certain oleo attachment brackets for cracks and replace any cracked bracket found during any inspection. In working with the United Kingdom, we have determined that the bracket may, as an option, be replaced with a newly designed steel bracket, increasing the length of time between the repetitive inspections. The actions specified by this AD are intended to detect and correct cracked oleo attachment brackets. Such a condition could cause the attachment bracket to fail, which could result in detachment of the main landing gear.
AD 2002-03-05 · published Feb 12, 2002, effective Mar 19, 2002
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires, among other things, repetitive leak tests of the lavatory drain systems and repair, if necessary; installation of a lever lock cap, vacuum breaker check valve, or flush/fill line ball valve on the flush/fill line; periodic seal changes; and replacement of "donut" type waste drain valves installed in the waste drain system. This amendment is prompted by continuing reports of damage to engines, airframes, and property on the ground, caused by "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent such damage associated with the problems of "blue ice."
AD 2002-03-11 · published Feb 12, 2002, effective Mar 19, 2002
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 a one-time ultrasonic inspection to detect disbonding of the skin attachments at the stringers and spars of the vertical stabilizer, repair, if necessary, and, for certain airplanes, prior or concurrent modification of the vertical stabilizer to ensure proper reinforcement of its attachment to the skin. This amendment adds repetitive ultrasonic inspections of the subject area, and repair, if necessary. It also adds installation of fasteners to reinforce the bonds to the skin, which terminates the repetitive inspections. 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 failure of the bonds of the vertical stabilizer spar boxes to the skin, which could lead to reduced structural integrity of the spar boxes.
AD 2002-03-02 · published Feb 14, 2002, effective Apr 2, 2002
British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, and Jetstream Series 3101 Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-13- 03, which currently requires repetitive inspections of the main landing gear (MLG) hinge fittings, support angles, and attachment bolts on British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, and Jetstream Series 3101 airplanes. AD 98-13-03 also requires eventual installation of improved design MLG hinge fittings as terminating action for the repetitive inspections of the hinge fittings and attachment bolts. AD 98-13-03 specifies repetitive inspections of the support angles for those airplanes with the improved design MLG hinge fittings installed and exempts from the applicability those airplanes with the improved design MLG hinge fittings installed. This AD retains the requirements of AD 98-13-03 and removes the applicability exemption of those Model HP.137 Jetstream Mk.1 and Jetstream Series 200 airplanes with the improved design MLG hinge fittings installed. The actions specified by this AD are intended to detect, correct, and prevent future fatigue cracking of the MLG, which could result in structural failure of the MLG and consequent loss of airplane control during takeoff, landing, or taxi operations.
AD 2002-03-03 · published Feb 14, 2002, effective Mar 29, 2002
SOCATA-Groupe AEROSPATIALE Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires you to install a new strainer draining system in the cabin fuselage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent water from accumulating in the fuselage, then freezing and interfering with or causing the elevator controls to seize. This could result in loss of elevator control with consequent loss of airplane control.
AD 2002-03-06 · published Feb 14, 2002, effective Mar 21, 2002
McDonnell Douglas Model DC-9-81, -82, -83, and -87 Series Airplanes, Model MD-88 Airplanes, and Model MD-90-30 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, Model MD-88 airplanes, and Model MD-90-30 series airplanes, that currently requires a revision to the applicable Airplane Flight Manual (AFM) to provide the flightcrew with the appropriate landing distance and flap positions, if applicable, for wet or icy runways. That AD also provides for an optional terminating action for the applicable AFM revision. For certain airplanes, this action requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent the flightcrew from performing a scheduled landing on a runway of potentially insufficient length due to failure of the weight-on-wheels spoiler lockout mechanism system and possible inactivation of the autospoiler actuator, which could result in the airplane overrunning the end of the runway during landing on a wet or icy runway.
AD 2002-03-07 · published Feb 14, 2002, effective Mar 21, 2002
BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that requires a one-time inspection to detect corrosion of the flap structure and machined ribs, corrective actions if necessary, and reprotection of the rib boss bores. This action is necessary to detect and correct corrosion in the flap structure and machined ribs, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-03-10 · published Feb 14, 2002, effective Mar 21, 2002
BAE Systems (Operations) Limited Model BAe 146 Series Airplanes and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that requires repetitive inspections to detect cracking of the oleo strut of the nose landing gear (NLG), and corrective actions if necessary. This AD also provides for optional terminating action for the repetitive inspections. This action is necessary to detect and correct fatigue cracking of the oleo strut of the NLG, which could result in failure of the NLG. This action is intended to address the identified unsafe condition.
AD 2002-03-04 · published Feb 15, 2002, effective Mar 29, 2002
Pilatus Britten-Norman Limited BN-2, BN-2A, BN-2B, BN-2T, and BN2A MK. III Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman) BN-2, BN-2A,BN-2B, BN-2T, and BN2A MK. III series airplanes. This AD requires you to replace the emergency exit window sealant. 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 correct the problems with emergency exit windows failing to open. Such failure could lead to the inability to exit the airplane in an emergency.
AD 2002-03-12 · published Feb 20, 2002, effective Mar 27, 2002
Bombardier Model DHC-8-400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-400 series airplanes, that requires a modification and a replacement affecting the fuel tanks in the wings. All affected airplanes require modification of the clearance of the fuel tank vent lines to the left and the right wing fuel tanks. Some affected airplanes also require replacement of three existing fuel probes from the center fuel tank on the left and right wings with new production fuel probes. This action is prompted by mandatory continuing airworthiness information from a foreign airworthiness authority. The actions specified by this AD are necessary to prevent inadequate clearance between the fuel tank vent lines and the adjacent rib structures of the wings or failure of certain temporary, reworked fuel probes in the center fuel tanks in the wings. Either condition could compromise the airplane's lightning protection system, possibly resulting in a fire or explosion if the airplane were hit by lightning. This action is intended to address the identified unsafe condition.
AD 2002-03-13 · published Feb 20, 2002, effective Mar 27, 2002
Short Brothers Model SD3-60, SD3-60 SHERPA, and SD3-SHERPA Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60, SD3-60 SHERPA, and SD3- SHERPA series airplanes, that requires a one-time inspection of the wiring harness and power cables of the heated windshield to detect inadequate clearance, inadequate support, or chafing. This amendment also requires corrective action (including re-routing for adequate clearance or replacing damaged cables, as applicable), if necessary. The actions specified by this AD are intended to prevent chafing or damage of the power cables of the heated windshield, which could cause arcing and result in smoke and fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2002-03-14 · published Feb 20, 2002, effective Mar 27, 2002
Bombardier Model CL-600-2B19 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that requires repetitive inspections for cracking of the left and right lower wing planks, and repair, if necessary. The actions specified by this AD are intended to find and fix such cracking, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
AD 2002-03-15 · published Feb 20, 2002, effective Mar 27, 2002
Dornier Model 328-100 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires testing of the left- and right-hand potentiometer levers of the aileron flight control system, and follow-on or corrective action, as applicable. This amendment is necessary to prevent detachment of an aileron potentiometer lever, which could result in jamming of the elevator and/or aileron flight control systems and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-04-01 · published Feb 21, 2002, effective Mar 28, 2002
McDonnell Douglas Model DC-9, DC-9-80, and C-9 Series Airplanes; Model MD-88 Airplanes; and Model MD-90 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 series airplanes; Model MD-88 airplanes; and Model MD-90 airplanes, that currently requires a visual check to determine the part and serial numbers of the upper lock link assembly of the nose landing gear (NLG); repetitive inspections of certain upper lock link assemblies to detect fatigue cracking; and modification of the NLG. The existing AD also provides for terminating action for the repetitive inspections. This amendment requires, among other actions, expanding the applicability of the existing AD, revising compliance times; and adding new inspection requirements. This amendment is prompted by a report indicating that an NLG upper lock link fractured prior to landing and jammed against the NLG shock strut, restricting the NLG from fully extending. The actions specified by this AD are intended to prevent the upper lock link assembly from fracturing due to fatigue cracking, and the NLG consequently failing to extend fully; this condition could result in injury to passengers and flight crew, and damage to the airplane.
AD 2002-04-02 · published Feb 21, 2002, effective Mar 28, 2002
Airbus Model A300 F4-605R Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 F4-605R airplanes, that requires installation of external doublers at frames 29 and 33. The actions specified by this AD are intended to prevent fatigue cracking of certain circumferential joints, which could result in reduced structural integrity of the fuselage in the vicinity of the upper deck cargo door.
AD 2002-04-03 · published Feb 21, 2002, effective Mar 8, 2002
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires reinforcement of the structural provisions for the Global Positioning System (GPS) antenna by replacement of existing fasteners with new fasteners, and installation of conical washers and a doubler plate at stringer 26, as applicable. This action is necessary to prevent cracking of the structure of the fuselage pressure vessel in the area of the GPS antenna, leading to reduced structural integrity of the fuselage pressure vessel, which could result in depressurization of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-04-06 · published Feb 25, 2002, effective Apr 1, 2002
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires repetitive inspections for cracking of the upper chord of the rear spar of the wing, and corrective action, if necessary. This action is necessary to find and fix such cracking, which could result in fuel leaking through the cracks, reduced structural integrity of the wing, and separation of the wing from the airplane. This action is intended to address the identified unsafe condition.
AD 2002-04-05 · published Feb 26, 2002, effective Apr 2, 2002
Airbus Model A300 B2 and A300 B4 Series Airplanes; Model A300 F4-605R Airplanes; Model A300 B4-600 and A300 B4-600R Series Airplanes; and Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4 series airplanes; certain Model A300 F4-605R airplanes and Model A300 B4-600 and A300 B4-600R series airplanes; and certain Model A310 series airplanes, that requires repetitive inspections to detect damage of the fillet seals and feeder cables, and of the wiring looms in the wing/ pylon interface area; and corrective action, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent wire chafing and short circuits in the wing leading edge/ pylon interface area, which could result in loss of the power supply generator and/or system functions. This action is intended to address the identified unsafe condition.
AD 2002-01-30 · published Feb 1, 2002, effective Feb 19, 2002
Eurocopter France Model SE 3130, SE 313B, SA 315B, SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model SE 3130, SE 313B, SA 315B, SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B helicopters with a certain main gearbox (MGB) installed. This action requires inspecting the magnetic plug for magnetic particles at specified intervals in addition to the MGB inspections currently required. This AD also requires, within 50 hours time-in-service (TIS), dye-penetrant inspecting the MGB bevel gear for a crack, and if a crack is found, replacing the cracked bevel gear with an airworthy bevel gear before further flight. This amendment is prompted by an MGB failure due to a cracked bevel gear. This condition, if not corrected, could result in failure of the MGB, loss of the main rotor drive, and subsequent loss of control of the helicopter.
AD 2001-26-55 · published Feb 11, 2002, effective Feb 26, 2002
Eurocopter France Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-26-55, which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters by individual letters. This AD requires, before further flight and thereafter at specified intervals, visually checking the tail rotor blade (blade) skin for a crack and replacing any cracked blade before further flight. This AD is prompted by the discovery of cracks in the skin of a blade. The actions specified by this AD are intended to prevent failure of the blade, which could result in severe vibration, loss of the tail rotor gearbox (TGB), and subsequent loss of control of the helicopter.
AD 2002-03-16 · published Feb 20, 2002
Bell Helicopter Textron, Inc.-Manufactured Model OH-13E, OH-13H, and OH-13S Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Model OH-13E, OH-13H, and OH-13S helicopters manufactured by Bell Helicopter Textron, Inc. (BHTI). That AD currently requires either recurring liquid penetrant or eddy current inspections of the main rotor blade grip (grip) threads for a crack. If a crack is detected, that AD requires, before further flight, replacing the cracked grip with an airworthy grip. That AD also establishes a retirement life of 1200 hours time-in-service (TIS) for each grip. This amendment adds two part numbers (P/N) to the applicability and requires only recurring eddy current inspections of the grip threads. This AD also requires reporting any results of the grip inspections to the FAA Rotorcraft Certification Office. This amendment is prompted by the issuance of an AD for the civil BHTI Model 47 helicopters and the results of an accident investigation, an operator survey conducted by a trade association, various comments concerning the subject of the current AD, and a further analysis of field service data related to the BHTI Model 47 helicopters. The actions specified by this AD are intended to prevent failure of a grip, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2002-02-09 · published Feb 8, 2002, effective Mar 15, 2002
General Electric Company (GE) CF6-45 and CF6-50 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to GE CF6-45 and CF6-50 series turbofan engines. This AD requires a reduction of the cyclic life limit for certain low pressure turbine rotor (LPTR) stage 2 disks, and requires removing certain LPTR stage 2 disks from service before exceeding the new, lower cyclic life limit. In addition, this amendment requires removing from service certain LPTR stage 2 disks that currently exceed, or will exceed, the new, lower cyclic life limit according to the compliance schedule described in this action. This amendment is prompted by a report of a cracked LPTR stage 2 disk found initially by flourescent penetrant inspection and later confirmed by a visual inspection. The actions specified by this AD are intended to prevent an uncontained engine failure and damage to the airplane, resulting from cracks in the LPTR stage 2 disk.
AD 2002-02-12 · published Feb 14, 2002, effective Mar 1, 2002
Rolls-Royce plc RB211-524G and -524H Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) RB211-524G and -524H series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and, if necessary, replacement with serviceable parts. That action also provides the options of installing improved design fan blades or reworking current fan blades to the improved configuration as terminating action for the inspections. This amendment requires initial inspection at lower thresholds, using either the blade root probe method or the surface wave probe method. This amendment also removes the option of reworking blades as terminating action for the inspections. Lastly, this amendment adds the model RB211-524H-T-36 engine to the applicability of this AD. This amendment is prompted by two additional reports of fan blade cracks found during inspections performed in accordance with the current AD. The actions specified in this AD are intended to detect cracked fan blades, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-02-13 · published Feb 14, 2002, effective Mar 21, 2002
CFM International, S.A. CFM56-5 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to CFM International, S.A. (CFMI) CFM56-5 series turbofan engines. This amendment requires replacement of the magnetic drain plug on certain part number (P/N) air turbine engine starters manufactured by Honeywell Engines & Systems. This amendment is prompted by three instances of uncontained air turbine engine starter failures, resulting in cowl damage. The actions specified by this AD are intended to prevent uncontained failure of the starter and possible damage to the airplane.
AD 2002-03-01 · published Feb 14, 2002, effective Mar 21, 2002
Honeywell International, Inc., (Formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-703 Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L- 703 series turboshaft engines. This amendment requires initial and repetitive special vibration tests of the engine, and if necessary replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This amendment is prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. The actions specified in this AD are intended to prevent excessive vibrations produced by the reduction gearbox assembly that could cause failure of the tachometer drive spur gear.
AD 2002-03-08 · published Feb 15, 2002, effective Apr 16, 2002
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney PW4000 series turbofan engines. That AD currently requires revisions to the Time Limits Section of the manufacturer's Engine Manuals (EM's) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-03-09 · published Feb 20, 2002, effective Mar 27, 2002
Honeywell International Inc. (Formerly AlliedSignal Inc. and Textron Lycoming) LTS101 Series Turboshaft and LTP101 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) LTS101 series turboshaft and LTP101 series turboprop engines. This amendment requires a one-time visual inspection for surface finish and a one-time fluorescent penetrant inspection for cracks of certain impellers installed on LTS101 series turboshaft and LTP101 series turboprop engines. This amendment is prompted by a report of a machining discrepancy that may have occurred during manufacture of the affected impellers. The actions specified by this AD are intended to prevent impeller failure from cracks in the impeller back face area, which could result in an uncontained engine failure.
