51 Airworthiness Directives: 37 airplane, 5 rotorcraft, 7 engine, 1 propeller, 1 glider.
AD 2001-26-19 · published Jan 3, 2002, effective Jan 18, 2002
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a one-time inspection for missing, damaged, or incorrectly installed parts in the separation link assembly on the deployment bar of the emergency escape system on the entry or service door, and installation of new parts, if necessary. This action is necessary to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers. This action is intended to address the identified unsafe condition.
AD 2001-23-12 R1 · published Jan 4, 2002, effective Dec 31, 2001
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This document revises an existing airworthiness directive (AD) that applies to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. That AD currently requires a one-time review of records to determine whether an airplane has been repainted since its delivery from the factory; and a one-time inspection to detect damage associated with improper preparation for the repainting, and corrective action if necessary. The actions specified in that AD are intended to detect and correct damage to the aluminum skin of the airplane, which could result in a weakening of the structure of the airplane. This document corrects certain conditional requirements of the existing AD.
AD 2001-23-15 · published Jan 4, 2002, effective Dec 31, 2001
Boeing Model 747 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain Boeing Model 747 series airplanes. That AD currently requires repetitive detailed visual inspections to find discrepancies of the installation of the midspar fuse pins of the inboard and outboard struts, and follow-on actions, if necessary. That AD also mandates accomplishment of a terminating modification. This document corrects the omission of the phrase "amendment 39-12514" from the first line of the AD. This correction is necessary to ensure that the amendment number is stated at the beginning of the AD.
AD 2001-26-14 · published Jan 4, 2002, effective Feb 8, 2002
Dornier Model 328 Series Airplanes Equipped With Honeywell GP-300 Guidance and Display Controller
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Dornier Model 328 series airplanes, that currently requires modification of certain Honeywell GP-300 guidance and display controllers. That AD was prompted by reports of smoke and fumes emitting from the Honeywell GP-300 guidance and display controller due to a defective light bulb; and a report of failure of the autopilot to disconnect manually. The actions specified by this AD are intended to prevent a defective light bulb from causing a short circuit that emits smoke and fumes into the cockpit; or causing damage to the circuit cards and various components, which may lock the autopilot into the engaged mode. Locking of the autopilot into the engaged mode could lead to the inability of the pilot to disconnect the autopilot, which could result in reduced controllability of the airplane. This amendment requires verification of proper installation of the modification, and repair, if necessary.
AD 2001-26-15 · published Jan 4, 2002, effective Feb 8, 2002
McDonnell Douglas Model DC-9-81, -82, -83, and -87 Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and - 87 series airplanes, and Model MD-88 airplanes, that requires a detailed visual inspection of certain wires to detect chafing and preload; repair, if necessary; and modification of certain wire assemblies. This action is necessary to prevent insufficient clearance between wire assemblies and the ice protection airduct and airstair door interlock rod; chafing; and consequent arcing of wire assemblies. Such arcing could result in damage to electronic equipment and adjacent structures, or cause the insulation blankets to ignite, which could result in smoke and fire in the flight deck and main cabin. This action is intended to address the identified unsafe condition.
AD 2001-26-16 · published Jan 4, 2002, effective Feb 8, 2002
McDonnell Douglas DC-9-81, -82, -83, and -87 Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires replacing the interface connectors of the cabin fluorescent lighting ballast in the wiring harness of the overhead stowage compartment with new connectors. In lieu of the required replacement, this AD requires adding interface seals to the existing interface connectors of the cabin fluorescent lighting ballast between certain stations and reidentifying the connector assemblies. This action is necessary to prevent electrical shorting and arcing due to the presence of water in the lighting ballast interface connectors, which could result in smoke in the main cabin. This action is intended to address the identified unsafe condition.
AD 2001-26-17 · published Jan 4, 2002, effective Feb 8, 2002
Airbus Model A330 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 series airplanes, that requires removal of the shear pins that keep the rear fixed panels on the center landing gear closed and installation of new solid shear pins. This amendment is prompted by issuance of mandatory continuing airworthiness information from a foreign airworthiness authority. This action is intended to prevent the shear pins on the rear fixed panels of the center landing gear from failing, which could result in loss of the panels during flight with consequent injury to people on the ground. This action is intended to address the identified unsafe condition.
AD 2001-26-18 · published Jan 4, 2002, effective Feb 8, 2002
Dornier Model 328-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires, for certain airplanes, a one-time torque test (inspection) of the attachment bolts of the forward engine mount vibration isolators to determine if the bolts are adequately torqued, and corrective action, if necessary. For all airplanes, this amendment prohibits installation of an attachment bolt on the forward engine mount vibration isolators, unless the attachment bolt is torqued within certain limits. These actions are necessary to prevent failure of the engine mount, which could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2001-26-20 · published Jan 4, 2002, effective Feb 8, 2002
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires a one-time inspection of the forward and aft lower bogies of the left- and right-hand sliding windows of the flightcrew compartment for the presence of a lock pin. If the lock pin is missing, this amendment requires corrective action. This action is necessary to prevent the inability of the flightcrew to open the left- or right-hand sliding window for evacuation in an emergency, due to a window jamming in the closed position. This action is intended to address the identified unsafe condition.
AD 2001-26-21 · published Jan 4, 2002, effective Feb 8, 2002
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires replacement of the low-pressure solenoid valve for the crew oxygen supply with a modified valve. This action is necessary to prevent faulty operation of the low-pressure solenoid valve for the crew oxygen supply, which could prevent oxygen from being supplied to the airplane crew when needed, such as in the event of smoke in the cabin or rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-26-22 · published Jan 4, 2002, effective Feb 8, 2002
BAE Systems (Operations) Limited Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model Avro 146- RJ series airplanes, that requires a one-time inspection of the S4 and S5 static pipes of the pitot static system for discrepancies, and follow-on corrective actions, if necessary. This action is necessary to prevent failure of the S4 and S5 static pipes and consequent failure of the maximum differential pressure protection for the airplane, which could lead to the fuselage of the airplane being overstressed and result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-26-23 · published Jan 4, 2002, effective Feb 8, 2002
Bombardier Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires replacement of the observer's seat latch assembly with a new, improved seat latch assembly. This action is necessary to prevent the observer's seat from separating from its attachment points in the event of an accident or emergency landing, due to an understrength seat latch assembly. This action is intended to address the identified unsafe condition.
AD 2001-26-24 · published Jan 4, 2002, effective Feb 8, 2002
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; and C-9 airplanes that requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition.
AD 2001-26-12 · published Jan 7, 2002, effective Feb 11, 2002
Boeing Model 747-100, 747-200, 747-300, and 747SR Series Airplanes Powered by General Electric CF6-45/50 or Pratt & Whitney JT9D-70 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200, 747-300, and 747SR series airplanes powered by General Electric CF6-45/50 or Pratt & Whitney JT9D-70 series engines, that currently requires a detailed visual inspection of the outboard diagonal brace for heat damage and cracking; and follow-on repetitive inspections and corrective actions, if necessary. This amendment requires accomplishment of the previously optional replacement of any existing sealant with heat-resistant sealant as terminating action for the repetitive inspections required by this AD. This amendment is prompted by reports of heat damage to the forward end of the diagonal brace after accomplishment of a previous strut and wing modification. The actions specified by this AD are intended to prevent heat damage to the diagonal brace, which could cause cracking, fracture, and possible loss of the diagonal brace load path and consequent separation of the strut and engine from the airplane.
AD 2001-26-51 · published Jan 8, 2002, effective Jan 14, 2002
Bombardier Model CL-600-2B19 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-26-51 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2B19 series airplanes by individual notices. This AD requires deactivation of the center tank fuel transfer shutoff valves by opening circuit breakers and installing a circuit breaker lock ring and disconnecting and stowing the electrical wiring, replacing certain valves with valves having a different part number, reconnecting certain circuit breaker wires, removing lock rings, and resetting the associated circuit breakers. For certain airplanes, this AD requires an AFM revision to prohibit operation with more than 200 pounds of fuel in the center fuel tank. This AD also has a provision for operating other airplanes with the center fuel tank full and with both fuel transfer shutoff valves inoperative. This action 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 ignition of fuel vapor in the center wing tank and consequent fire and explosion.
AD 2001-26-13 · published Jan 10, 2002, effective Feb 12, 2002
Pilatus Aircraft Ltd. Model PC-7 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to inspect the landing-gear emergency- extension cable for damage and replace if necessary; verify the correct installation of the bowden-cable conduit clamp and correct if necessary; and modify the temperature-control lever mechanism. 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 malfunction of the emergency landing-gear extension system. Insufficient clearance between the temperature-control lever mechanism and the landing-gear emergency- extension cable could result in damage to the emergency landing gear extension cable, or the cable could get caught on the temperature control lever. Damage to, or interference with, the landing-gear emergency-extension cable could lead to a malfunction of the emergency landing-gear extension system.
AD 2002-01-01 · published Jan 14, 2002, effective Feb 19, 2002
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 initial and repetitive inspections of the elevator tab assembly to find any damage or discrepancy; and corrective actions, if necessary. The actions specified by this AD are intended to prevent excessive in-flight vibrations of the elevator tab, which could lead to loss of the elevator tab and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-08 · published Jan 15, 2002, effective Jan 30, 2002
Israel Aircraft Industries, Ltd., Model Galaxy Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model Galaxy airplanes. This action requires disabling the baggage compartment heating blanket system. This action is necessary to prevent a short circuit between the baggage compartment heating blankets and the electrical connectors, which could result in fire and smoke in the baggage compartment. This action is intended to address the identified unsafe condition.
AD 2002-01-05 · published Jan 17, 2002, effective Feb 11, 2002
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 that are equipped with certain main landing gear (MLG) radius rods. This AD requires you to inspect the MLG radius rod cylinders for the required conductivity or hardness standard. This AD also requires you to replace any MLG radius rod cylinder that does not meet this standard. 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 prevent failure of the MLG due to incorrectly heat treated MLG radius rod cylinders. Such failure during takeoff, landing, or taxi operations, could lead to loss of airplane control.
AD 2002-01-09 · published Jan 17, 2002, effective Feb 28, 2002
Pilatus Aircraft Ltd. Models PC-7, PC-12, and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. Models PC-7, PC-12, and PC-12/45 airplanes that incorporate a certain engine-driven pump. This AD requires you to inspect the joints between the engine-driven pump housing, relief valve housing, and the relief-valve cover for signs of fuel leakage or extruding gasket material; replace any engine-driven pump with signs of fuel leakage or extruding gasket material; and inspect to ensure that the relief valve attachment screws are adequately torqued and re-torque as necessary. 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 gasket material extruding from the engine-driven pump housing and detect and correct relief valve attachment screws with inadequate torque. Such conditions could lead to fuel leakage and result in a fire in the engine compartment.
AD 2002-01-10 · published Jan 22, 2002, effective Feb 22, 2002
Raytheon Aircraft Company Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-4, B90, C90, C90A, E90, and H-90 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-4, B90, C90, C90A, E90, and H-90 airplanes. This AD requires you to repetitively inspect the main landing gear upper torque knees and lower torque knees for evidence of fatigue cracks; and replace any torque knee with evidence of fatigue cracks. This AD is the result of reports of many incidents of main landing gear torque knees cracking or breaking on the above-referenced airplanes. The actions specified by this AD are intended to detect and replace cracked main landing gear torque knees, which could result in failure of the main landing gear and consequent loss of control of the airplane during takeoff, landing, or other ground operations.
AD 2002-01-11 · published Jan 22, 2002, effective Feb 28, 2002
Pilatus Britten-Norman Ltd. BN-2, BN-2A, BN-2B, BN-2T, BN-2T-4, and BN2A MK. III Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN- 2, BN-2A, BN-2B, BN-2T, BN-2T-4, and BN2A MK. III series airplanes. This AD requires you to repetitively inspect the throttle friction- shaft and replace the shaft if damaged. 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 loosening of the throttle friction adjustment beyond its normal limits. Such a condition could lead to damage to the throttle friction-adjuster or the retaining washer and split pin. This could allow the throttle quadrant shaft to laterally shift and impede the operation of the engine controls.
AD 2002-01-14 · published Jan 22, 2002, effective Jan 22, 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 an in-situ one-time detailed visual inspection of Draeger Type I oxygen containers, located in the passenger service units, and Draeger Type II oxygen containers, located in the utility areas, for the presence of foam pads. That action also currently requires the installation of a new foam pad, if necessary; and other actions to ensure proper operation of the masks. This amendment retains those requirements and expands the applicability of the existing AD to include additional airplanes that were inadvertently excluded from that AD. The actions specified in this AD are intended to prevent failure of the oxygen containers to deliver oxygen to the passengers in the event of a rapid decompression or cabin depressurization. This action is intended to address the identified unsafe condition.
AD 2002-01-13 · published Jan 25, 2002, effective Mar 1, 2002
Boeing Model 767 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires inspections to detect cracking and corrosion of the aft trunnion of the outer cylinder of the main landing gear (MLG) and various follow-on actions. That AD also currently requires termination of the inspections by repairing the outer cylinder and installing new aft trunnion bushings. This amendment prohibits the use of a particular corrosion inhibiting compound during accomplishment of the terminating action. This action is necessary to prevent the collapse of the MLG due to stress corrosion cracking of the aft trunnion of the outer cylinder. This action is intended to address the identified unsafe condition.
AD 2001-17-26 R1 · published Jan 29, 2002, effective Oct 3, 2001
Raytheon Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) Series Airplanes; Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 Airplanes
This document corrects and clarifies information in an existing airworthiness directive (AD) that applies to certain Raytheon Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series airplanes; Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 airplanes. That AD currently requires an inspection for cracking or corrosion of the cylinder head lugs of the main landing gear actuator and follow-on/corrective actions. This document corrects and clarifies the affected airplane serial numbers. This correction is necessary to ensure that operators do not misinterpret which airplanes are subject to the requirements of this AD.
AD 2002-01-15 · published Jan 30, 2002, effective Feb 14, 2002
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires repetitive inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies, and corrective action, if necessary. This action is necessary to prevent failure of the bearings in the link assembly joint, which could result in separation of the outboard flap and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-16 · published Jan 30, 2002, effective Mar 11, 2002
Fairchild Aircraft, Inc. SA26, SA226, and SA227 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 86-24- 11 and AD 86-25-04, which require you to incorporate, into the Limitations Section of the pilot's operating handbook and airplane flight manual (POH/AFM) of Fairchild Aircraft, Inc. (Fairchild Aircraft) SA226 and SA227 series airplanes, procedures for preventing an engine flameout while in icing conditions. This AD retains the POH/ AFM requirements from the above-referenced AD's and requires a modification to the torque sensing system to allow the igniters to automatically turn on when an engine senses low torque. This AD is the result of two instances of a dual engine flameout on the affected airplanes. When the torque sensing system modification is incorporated, the POH/AFM requirements are no longer necessary. The actions specified by this AD are intended to prevent a dual engine flameout on the affected airplanes by providing a system that automatically turns on the engine igniters when low torque is sensed. A dual engine flameout could result in failure of both engines with consequent loss of control of the airplane.
AD 2002-01-17 · published Jan 30, 2002, effective Feb 14, 2002
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires revising the Airplane Flight Manual to provide the flight crew with the appropriate procedures necessary to verify correct operation of the primary alternating current (AC) pump of the main hydraulic system before takeoff. This action is necessary to prevent takeoff with an inoperative pump, which could result in an extended takeoff roll or a rejected takeoff, and consequent runway overrun, structural damage to the airplane, and possible injury to occupants. This action is intended to address the identified unsafe condition.
AD 2002-01-18 · published Jan 30, 2002, effective Mar 6, 2002
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires replacement of the trigger spring of the slide bar on each of the passenger doors with a new, stronger trigger spring. This action is necessary to prevent corrosion of the trigger spring on the slide bar of the passenger doors, which could result in incorrect locking of the slide bar and, during deployment of the escape slide, lead to a delay in evacuating passengers in an emergency. This action is intended to address the identified unsafe condition.
AD 2002-01-19 · published Jan 30, 2002, effective Mar 6, 2002
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires repetitive operational tests for discrepancies of the heating system of pitot tube #1, and replacement of the pitot tube, if necessary. This AD also requires eventual modification of the alternating current sensing circuit for pitot tube #1, which terminates the repetitive operational test requirement. This action is necessary to prevent failure of the heating system of pitot tube #1 due to a short circuit, which may go undetected and lead to the pilot receiving erroneous airspeed indications, resulting in reduced control of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-20 · published Jan 30, 2002, effective Mar 6, 2002
BAE Systems (Operations) Limited Model BAe 146-200A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146- 200A series airplanes, that requires replacement of the signal summing units (SSUs) for the stall identification system with new, improved parts. The actions specified by this AD are intended to prevent stall identification and stall warning signals from occurring at the same time, leading the flight crew to take action based on erroneous information, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-21 · published Jan 30, 2002, effective Mar 6, 2002
BAE Systems (Operations) Limited Model BAe 146 Series Airplanes and Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 series airplanes and Avro 146-RJ series airplanes, that requires replacement of the standby generator with a new, improved standby generator. This amendment is prompted by mandatory continuing airworthiness information from a foreign airworthiness authority. This action is necessary to prevent loss of the standby generator, which, in the event of an emergency involving the principal generator, could result in the loss of electrical power to the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-23 · published Jan 30, 2002, effective Feb 14, 2002
Raytheon Model Beech 400, 400A, and 400T Series Airplanes; Model Beech MU-300-10 Airplanes; and Model Mitsubishi MU-300 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Raytheon Model Beech 400, 400A, and 400T series airplanes; Model Beech MU-300-10 airplanes; and Model Mitsubishi MU-300 airplanes. This action requires repetitive inspections to detect cracking in the radius of the cutout of the aft flange of the left engine forward carry-through mount bracket, and replacement with a new bracket and fitting if necessary. This action is necessary to prevent failure of the engine mount and possible loss of the engine, and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-24 · published Jan 30, 2002, effective Mar 6, 2002
McDonnell Douglas Model DC-9-81, -82, -83, and -87 Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and - 87 series airplanes, and Model MD-88 airplanes, that requires replacing the dust seals of the passenger service unit (PSU) panels of the overhead stowage compartment with new dust seals. The AD provides two options to accomplish this. Operators can either replace the seals all at once or remove the seals and repetitively clean and inspect the area to defer the installation for an interim period. The actions specified by this AD are intended to ensure replacement of dust seals of the lower PSU panel that may contribute to the spread of a fire when ignition occurs from electrical arcing of a failed light holder assembly, which could cause damage to adjacent structure and smoke emitting from the PSU panel into the passenger cabin. This action is intended to address the identified unsafe condition.
AD 2002-01-25 · published Jan 30, 2002, effective Mar 6, 2002
Bombardier Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires repetitive inspections of the rudder pedal adjustment fittings for cracks and replacement of cracked fittings with new fittings. This amendment also provides an optional terminating action. This action is necessary to detect and correct cracking of the rudder pedal adjustment fittings, which could lead to deformation of the fittings, resulting in jammed rudder pedals and loss of rudder control, with consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-22 · published Jan 31, 2002, effective Mar 7, 2002
Short Brothers Model SD3 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires a one-time inspection of the installation of the bearing housings of the elevator torque shaft assembly, and corrective action if necessary. This action is necessary to prevent failure of the elevator torque shaft, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-01-26 · published Jan 31, 2002, effective Mar 7, 2002
Israel Aircraft Industries, Ltd., Model 1124 and 1124A, and Model 1125 Westwind Astra Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Israel Aircraft Industries, Ltd., Model 1124 and 1124A, and certain Model 1125 Westwind Astra series airplanes, that requires a one-time inspection of the attachment bolts installed on the engine inlet cowl and aft nacelle attachment flanges to verify correct part numbers of the bolts, and replacement of any discrepant/incorrect bolt with a correct attachment bolt. The actions specified by this AD are intended to prevent failure of attachment bolts due to fatigue, which could result in separation of the engine inlet cowl and aft nacelle, and consequent damage to the horizontal or vertical stabilizer. This action is intended to address the identified unsafe condition.
AD 2002-01-06 · published Jan 16, 2002, effective Jan 31, 2002
Eurocopter France Model AS332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model AS332L2 helicopters. This action requires inspecting the main frame for a crack and repairing any unairworthy frame before further flight. This amendment is prompted by a report of cracks on the right-hand (RH) side of a main frame. This condition, if not corrected, could result in failure of the main frame and subsequent loss of control of the helicopter.
AD 2001-25-51 · published Jan 17, 2002, effective Feb 1, 2002
MD Helicopters, Inc. Model MD900 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-25-51, which was sent previously to all known U.S. owners and operators of MD Helicopters, Inc. (MDHI) Model MD900 helicopters by individual letters. This AD requires performing a dual power confirmation test on the Integrated Instrument Display System (IIDS) and inserting a revision to the Rotorcraft Flight Manual (RFM), as applicable. If the IIDS fails the power test, replacing it is required before further flight. Removing the temporary revision when the IIDS is replaced and inserting the applicable revision into the RFM is also required. This AD is prompted by the failure of the IIDS during a helicopter hover operation. The actions specified by this AD are intended to prevent total power failure of the IIDS and the subsequent inability to monitor information and warning indications essential for the operation of the helicopter.
AD 2002-01-07 · published Jan 17, 2002, effective Feb 21, 2002
Bell Helicopter Textron Canada Model 430 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires changes to the electrical power distribution system. This amendment is prompted by design deficiencies in the electrical systems. The actions specified by this AD are intended to prevent failure of both generators, loss of primary electrical power, and subsequent loss of control of the helicopter.
AD 2001-26-52 · published Jan 22, 2002, effective Feb 6, 2002
Eurocopter Deutschland GmbH Model EC135 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-26-52, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (ECD) Model EC135 helicopters by individual letters. This AD requires, before further Instrument Flight Rule (IFR) flight, inserting a copy of the AD into the Limitations Section of the Rotorcraft Flight Manual (RFM) and replacing each affected Smart Multifunction Display (SMD45H) as specified. Removing the AD from the RFM is required after replacing each affected SMD45H. This AD is prompted by the discovery of an error in the assembly of an internal connector of the SMD45H that sometimes results in an inversion of the display information. The SMD45H provides the flightcrew with essential flight and navigation information. The actions specified by this AD are intended to prevent erroneous flight or navigation display information, produced by a faulty SMD45H, and subsequent loss of control of the helicopter.
AD 2001-26-53 · published Jan 22, 2002, effective Feb 6, 2002
Eurocopter France Model AS350B, B1, B2, B3, BA, D, and AS355E Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-26-53, which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model AS350B, B1, B2, B3, BA, D, and AS355E helicopters by individual letters. This AD requires, before further flight, removing certain serial-numbered servocontrols. This AD is prompted by a report of manufacturing defects in a batch of main servocontrol rods. The actions specified by this AD are intended to prevent failure of a main servocontrol in the flight control system and subsequent loss of control of the helicopter.
AD 2001-25-11 · published Jan 2, 2002, effective Jan 17, 2002
Pratt and Whitney PW4000 Series Turbofan Engines
This amendment supersedes two airworthiness directives (AD's), AD 99-17-16 and AD 2001-15-12. Those AD's both apply to Pratt and Whitney (PW) model PW4000 series turbofan engines. AD 99-17-16 generally requires that operators limit the number of PW4000 engines with potentially reduced stability margin to no more than one engine on each airplane, and requires initial and repetitive on-wing and test cell engine stability tests. It also establishes reporting requirements for stability testing data. AD 2001-15-12 also limits the number of PW4000 engines with potentially reduced stability on each airplane by applying rules based on airplane and engine configuration. In addition, AD 2001-15-12 also requires that engines that exceed high pressure compressor (HPC) cyclic limits based on cycles-since-overhaul (CSO) are removed from service, limits the number of engines with the HPC cutback stator (CBS) configuration to one on each airplane, and establishes a minimum rebuild standard for engines that are returned to service. These AD's were prompted by reports of surges during takeoff on airplanes equipped with PW4000 series turbofan engines. This amendment continues the limitation on the number of PW4000 engines with potentially reduced stability on each airplane to no more than one, and introduces a new cool engine fuel spike test to allow engines to be returned to service after having exceeded cyclic limits or undergone work in the shop. This AD also continues the limitation on the number of engines with HPC CBS configuration to one on each airplane, places a cyclic limit on how long a CBS engine may remain in service, and establishes a minimum rebuild standard for engines that are returned to service. This amendment is prompted by further analyses of compressor surges in PW4000 engines, and continuing reports of surges in the PW4000 fleet. The actions specified by this AD are intended to prevent engine power losses due to HPC surge.
AD 2002-01-02 · published Jan 7, 2002, effective Jan 22, 2002
Turbomeca S.A. Arrius 1A Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arrius 1A turboshaft engines. This action requires replacement of the 10 main fuel injectors in Arrius 1A engines with new or overhauled injectors. This amendment is prompted by routine inspections conducted in the repair workshop demonstrating that some main fuel injectors were partially or totally blocked. The actions specified in this AD are intended to prevent blocked main fuel injectors that could lead to engine flameout during engine deceleration or that could prevent the engine from obtaining the 2\1/2\ minute one engine inoperative (OEI) power.
AD 2002-01-03 · published Jan 8, 2002, effective Feb 12, 2002
GE Aircraft Engines CT7 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to GE Aircraft Engines (GE) CT7 series turboprop engines. This amendment requires removal of stage 2 turbine aft cooling plates of a certain part number (P/N) and installation of cooling plates of a new design. This amendment is prompted by a report of a stage 2 turbine aft cooling plate cracking, resulting in an uncontained engine failure. The actions specified by this AD are intended to prevent stage 2 turbine aft cooling plate cracking, which could result in uncontained engine failure, and damage to the airplane.
AD 2002-01-12 · published Jan 22, 2002, effective Feb 26, 2002
General Electric Company GE90 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Company (GE) GE90 series turbofan engines. This amendment requires removing from service high pressure turbine (HPT) interstage seals, identified by GE as the pre-life- improved rotor (pre-LIR) configuration, and installing a new design, identified by GE as the life improved rotor (LIR) configuration seal. This amendment also requires a new lower life limit for the LIR configuration seal. This amendment is prompted by an uncontained engine failure which occured during a factory development engine ground test. The actions specified by this AD are intended to prevent failure of the HPT interstage seal that could result in an uncontained engine failure and damage to the airplane.
AD 2002-01-04 · published Jan 30, 2002, effective Feb 14, 2002
General Electric Company CF6-80E1 Model Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-80E1 model turbofan engines. This action requires flex borescope inspections of high pressure turbine (HPT) stage two (S2) nozzle guide vanes (NGV) installed in CF6-80E1 model turbofan engines. This amendment is prompted by an uncontained engine failure attributed to HPT S2 NGV distress. The actions specified in this AD are intended to prevent blade failure from HPT S2 NGV distress, which could result in an uncontained engine failure.
AD 2002-01-27 · published Jan 30, 2002, effective Feb 14, 2002
General Electric Company GE90 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to General Electric Company (GE) GE90-76B, - 77B, -85B, -90B, and -92B model turbofan engines. That AD currently requires initial and repetitive eddy current inspections (ECI) for cracks in the high pressure compressor (HPC) stage 2-6 spool, and, if necessary, replacement with serviceable parts. That amendment was prompted by reports of cracks in the stage 3-4 and stage 4-5 interstage seal teeth and spacer arms. This amendment deletes reference to the GE90-92B engine model, deletes reference to HPC spool part number (P/N) 350-005-769-0 and directs the removal from service of affected part number spools by either engine cycles or calendar date, whichever occurs first. This amendment is prompted by the introduction of a new design HPC stage 2-6 spool and four additional HPC stage 2-6 spool P/N's that are terminating action for the repetitive inspection requirements for certain P/N spools. The actions specified by this AD are intended to prevent failure of the HPC stage 2-6 spool due to cracks, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-01-29 · published Jan 31, 2002, effective Feb 15, 2002
Rolls-Royce, plc. Models Tay 650-15 and 651-54 Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc (RR) models Tay 650-15 and 651-54 turbofan engines. This action requires borescope inspection of the high pressure compressor (HPC) stage 12 disc assembly to detect damage caused by HPC outlet guide vane (OGV) retaining bolt failure, and replacement of unserviceable parts with serviceable parts. This action also requires as terminating action, the incorporation of a new design retention arrangement for the HPC OGV, to prevent HPC OGV retaining bolt failure. This amendment is prompted by service reports of cracked HPC stage 11/12 disc spacers. The actions specified in this AD are intended to prevent an uncontained failure of the HPC stage 11/12 disc spacer, which could result in damage to the airplane.
AD 2002-01-28 · published Jan 30, 2002, effective Feb 14, 2002
Dowty Aerospace Propellers Type R334/4-82-F/13 Propeller Assemblies
This amendment adopts a new airworthiness directive (AD) that is applicable to Dowty Aerospace Propellers Type R334/4-82-F/13 with propeller hub assemblies, part number (P/N) 660709201. This action requires a one-time ultrasonic inspection of the propeller hub for cracks. This amendment is prompted by a report of an in-flight loss of a propeller. The actions specified in this AD are intended to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane.
AD 2001-26-25 · published Jan 8, 2002, effective Jan 31, 2002
Grob-Werke Gmbh & Co KG Models G102 Club Astir III, G102 Club Astir IIIb, and G102 Standard Astir III Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Grob-Werke Gmbh & Co KG (Grob) Models G102 Club Astir III, G102 Club Astir IIIb, and G102 Standard Astir III sailplanes. This AD requires you to apply a red mark and install a placard on the airspeed indicator to restrict the Vne airspeed. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent elevator flutter, which could cause structural damage. Such damage could result in loss of control of the sailplane.
