43 Airworthiness Directives: 29 airplane, 7 rotorcraft, 7 engine.
AD 2001-20-06 · published Oct 4, 2001
Airbus Model A300 B2 and B4 Series Airplane, and Model A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, and certain Model A300 B4-600, B4-60-R, and F4-600R (collectively called A300-600) series airplanes, that currently requires a one-time inspection to detect cracks in gear rib 5 (let and right) of the main landing gear (MLG) attachment fittings at the lower flange and vertical web, and repair if necessary. This amendment revises the applicability by including additional airplanes. The actions specified in this AD are intended to detect and correct fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane.
AD 2001-20-05 · published Oct 10, 2001, effective Nov 14, 2001
Fokker Model F.28 Mark 0100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0100 series airplanes, that currently requires replacement of the anti-skid control boxes with improved units. This amendment requires modification or replacement of the anti-skid control boxes with new, improved units, which render the skid control boxes even less susceptible to electromagnetic interference during power-up and power-down transients. This action is prompted by continuing mandatory airworthiness information from a foreign airworthiness authority. The actions specified by this AD are necessary to prevent electromagnetic interference with the anti-skid control system, which could result in reduced brake pressure during low-speed taxiing, and consequent reduced controllability and performance of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-20-07 · published Oct 11, 2001, effective Nov 15, 2001
Raytheon Model Beech 400A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A series airplanes, that requires replacement of certain bus bars connecting the battery and external power receptacle to the airframe ground with a new, improved bus bar. This amendment is prompted by reports of electrical arcing at the battery and external power receptacle of the airframe ground in the aft fuselage due to a deficiency in the bus bar and washer design. The actions specified by this AD are intended to prevent overheating or arcing of the ground connection in the aft fuselage area, which could result in a fire hazard due to ignition of fuel fumes during an engine start sequence.
AD 2001-20-08 · published Oct 11, 2001, effective Nov 15, 2001
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive eddy current inspections to detect cracks in the upper girder of the two main landing gear (MLG) brackets; and repair of a cracked bracket followed by repetitive inspections, or replacement of a cracked MLG bracket with an improved bracket, as applicable. This AD also provides for an optional terminating action for certain requirements of this AD. The actions specified by this AD are intended to detect and correct cracks in the upper girder of the MLG bracket, which could progress into the vertical stiffeners of the MLG bracket and result in reduced structural integrity of the landing gear. This action is intended to address the identified unsafe condition.
AD 2001-20-09 · published Oct 11, 2001, effective Nov 15, 2001
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 of the bearing support fitting of the forward trunnion on the main landing gear (MLG) to detect corrosion and cracking; follow-on actions, if necessary; and repair/rework of the support fitting, or replacement with a new or repaired/reworked fitting. The actions specified by this AD are intended to prevent failure of the support fitting, which could result in collapse of the MLG during normal operations; consequent damage to the airplane structure; and injury to flight crew, passengers, or ground personnel. This action is intended to address the identified unsafe condition.
AD 2001-20-11 · published Oct 11, 2001, effective Nov 15, 2001
Boeing Model 757 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires repetitive freeplay checks of the elevator, and replacement of worn elevator power control actuator (PCA) reaction link rod-end bearings and the PCA rod-end bearing, if necessary. That AD also provides for an optional terminating action for the repetitive checks. This amendment removes the optional terminating action provided by the existing AD, expands the applicability of the existing AD to include additional airplanes, and requires repetitive freeplay checks of the elevator at a revised repeat interval and repetitive lubrication of bearings of the elevator actuator load loop and hinge line. The actions specified by this AD are intended to prevent unacceptable airframe vibration during flight, which could lead to excessive wear of bearings of the elevator PCA load loop and hinge line and result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-20-15 · published Oct 11, 2001, effective Oct 26, 2001
McDonnell Douglas Model DC-9 Series Airplanes and MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9 series airplanes and MD-88 airplanes. This action requires an inspection to determine if a certain AC cross-tie relay is installed; replacement of a certain AC cross-tie relay with a new AC cross-tie relay; and repetitive cleaning, inspection, repair and testing of a certain AC cross-tie relay. This action is necessary to prevent AC cross-tie relay failures, which could result in internal arcing of the relay and smoke and/or fire in the cockpit and cabin. This action is intended to address the identified unsafe condition.
AD 2001-20-16 · published Oct 11, 2001, effective Oct 26, 2001
Airbus Model A319 and A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319 and A320 series airplanes. This action requires revising the Airplane Flight Manual to advise the flight crew of performance corrections necessary to ensure adequate runway lengths for certain takeoff and landing conditions. This action is necessary to prevent the airplane from departing the end of the runway during a landing or a rejected takeoff due to reduced braking performance.
AD 2001-20-14 · published Oct 12, 2001, effective Nov 21, 2001
Fairchild Aircraft, Inc., Models SA226 and SA227 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 and SA227 series airplanes. This AD requires you to replace the brake shuttle valves with parts of improved design and install a shield over the hydraulic lines. This AD also requires replacing the rubber fuel hose with a metal device for certain SA226 series airplanes. This AD is the result of a report of a wheel brake system malfunction caused by a faulty brake shuttle valve. The actions specified by this AD are intended to correct potential brake shuttle valve problems, which could cause the brake assembly to drag and overheat. Hydraulic or fuel line damage could then occur if the overheated brake assembly is retracted into the main wheel well, with a consequent fire if the hydraulic or fuel lines ruptured.
AD 2001-20-17 · published Oct 12, 2001, effective Oct 22, 2001
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that currently requires revising the Airplane Flight Manual, installing a placard on the main instrument panel, and removing the "LIGHT-HEAVY" inflation switch of the leading edge deicing boots. This amendment continues to require those actions and adds requirements to install a low speed alarm for icing conditions, to revise the AFM, and to replace an existing placard with a placard that directs the flightcrew to activate the deicing boots whenever ice is detected by visual cues or ice detector illumination. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This action is intended to ensure that the flightcrew is provided with accurate indications of the severity of ice accretion, clear indication of unintentional airplane speed reductions in icing conditions, and appropriate procedures to prevent reduced controllability of the aircraft due to accretion of ice on the airplane.
AD 2001-20-10 · published Oct 16, 2001, effective Nov 20, 2001
Boeing Model 737 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires inspection of wire bundles in certain junction boxes in the main wheel well to detect chafing or damage, and follow-on actions. The actions specified by this AD are intended to prevent wire damage, which could result in arcing and consequent fire in the main wheel well or passenger cabin, or inability to stop the flow of fuel to an engine or to the auxiliary power unit in the event of a fire. This action is intended to address the identified unsafe condition.
AD 2001-20-12 · published Oct 16, 2001, effective Nov 20, 2001
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires revising the Airworthiness Limitations Section of the maintenance manual (757 Airworthiness Limitations Instructions (ALI)). The revision will incorporate into the ALI certain inspections and compliance times to detect fatigue cracking of principal structural elements (PSE). This amendment is prompted by analysis of data that identified specific initial inspection thresholds and repetitive inspection intervals for certain PSEs to be added to the ALI. The actions specified by the proposed AD are intended to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2001-20-19 · published Oct 16, 2001, effective Oct 31, 2001
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-90-30 series airplanes. This action requires a visual inspection for heat damage, arcing, and loose terminal screws of the ground service electrical circuit breaker panel, and corrective actions, if necessary. This action is necessary to prevent overheating or arcing of circuit breakers in the ground service electrical circuit breaker panel, which could result in damage to the circuit breaker, wiring, or surrounding insulation blankets, and consequent smoke or fire in the flightdeck. This action is intended to address the identified unsafe condition.
AD 2001-20-20 · published Oct 17, 2001, effective Nov 1, 2001
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that currently requires replacement of certain ground block screws with new screws; and retermination of the circuit ground wires of the electrical power control unit (EPCU) to separate grounding points. This amendment removes certain airplanes and adds certain other airplanes to the applicability of the existing AD. The actions specified in this AD are intended to prevent a loose electrical ground block of the circuit ground wires of the EPCU, which could result in complete loss of the primary electrical power of an airplane during flight.
AD 2001-21-01 · published Oct 19, 2001, effective Nov 30, 2001
Dornier Luftfahrt GmbH Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Dornier Luftfahrt GmbH (Dornier) Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes. This AD requires you to repetitively inspect the horizontal stabilizer skin and ribs for damage and cracks and repair any damaged skin or cracked ribs. 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 detect and correct damage and fatigue cracks in the horizontal stabilizer skin and ribs. This condition could cause in-flight separation of the horizontal stabilizer skin with consequent loss of control of the airplane.
AD 2001-21-05 · published Oct 22, 2001, effective Nov 26, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a revision of the Airplane Flight Manual (AFM) to alert the flightcrew that both flight management computers (FMC) must be installed and operational. That AD also requires an inspection to determine the serial number of the FMC's; and follow-on corrective actions, if necessary, which terminate the AFM revision. This amendment requires an inspection to verify if a certain modification is on the front and rear identification plates of the FMC's; and applicable follow-on and corrective actions. This amendment is prompted by the FAA's determination that further rulemaking action is necessary to ensure that all affected airplanes are inspected for suspected defective multiplexers. The actions specified by this AD are intended to prevent loss of airspeed and altitude indications on both primary flight displays in the cockpit, and/or loss or degradation of the autopilot functionality, and consequent failure of the data busses.
AD 2001-21-06 · published Oct 22, 2001, effective Nov 6, 2001
Gulfstream Model G-V Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires an initial inspection of the electrical connections for the fire extinguisher bottles; an inspection after any subsequent maintenance affecting the fire extinguisher bottles; corrective action, if necessary; and reporting of the results of the inspection to the Federal Aviation Administration (FAA). This action is prompted by a report indicating that the electrical connections for the fire extinguisher bottle squibs had been improperly installed either during manufacturing or during subsequent maintenance. This action is necessary to prevent fire extinguishing agent from being discharged into the wrong location, which could result in failure to extinguish an in-flight fire on an affected engine and jeopardize operation of the opposite engine. This action is intended to address the identified unsafe condition.
AD 2001-12-08 R1 · published Oct 26, 2001, effective Jul 20, 2001
Boeing Model 767 Series Airplanes
This amendment corrects and clarifies information in an existing airworthiness directive (AD) that applies to certain Boeing Model 767 series airplanes. That AD currently requires removing the two existing escape ropes in the flight compartment; installing new escape ropes, bags, and placards; and replacing the nylon straps with new straps; as applicable. This document clarifies and corrects the affected airplane line numbers. This correction is necessary to ensure that operators do not misinterpret which airplanes are subject to the requirements of this AD.
AD 2001-22-06 · published Oct 26, 2001
Boeing Model B-17E, F, and G Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model B-17E, F, and G airplanes, that requires inspections to detect cracking and corrosion of the wing spar chords, bolts and bolt holes of the spar chords, and wing terminals; and correction of any discrepancy found during these inspections. This amendment is prompted by reports of cracking and corrosion of the wing spar. The actions specified by this AD are intended to prevent reduced structural integrity of the wing of the airplane due to the problems associated with corrosion and cracking of the wing spar.
AD 2001-22-02 · published Oct 29, 2001, effective Nov 13, 2001
Airbus Model A300 B2 and B4 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 B2 and B4 series airplanes. This action requires determining the part and amendment numbers of the variable lever arm (VLA) of the rudder control system to verify the parts were installed using the correct standard, and corrective actions, if necessary. This action is necessary to prevent failure of both spring boxes of the VLA due to corrosion damage, which could result in loss of rudder control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-22-03 · published Oct 29, 2001, effective Dec 3, 2001
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 series airplanes, that requires modifying the oxygen flow control valve. This action is necessary to ensure that proper oxygen flow will be available to passengers when needed. This action is intended to address the identified unsafe condition.
AD 2001-22-04 · published Oct 29, 2001, effective Dec 3, 2001
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires a one-time inspection of the fuselage skin adjacent to the drag splice fitting to detect cracking, and follow-on actions, if necessary. This amendment requires new repetitive inspections for cracking of the fuselage skin adjacent to the drag splice fitting. This amendment is prompted by reports of fatigue cracking in the fuselage skin and adjacent structure. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural integrity of the fuselage, and consequent rapid depressurization of the airplane.
AD 2001-22-10 · published Oct 29, 2001, effective Dec 3, 2001
Dassault Model Mystere-Falcon 50, Mystere-Falcon 900, and Falcon 900EX Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 50, Mystere-Falcon 900, and Falcon 900EX series airplanes, that requires revising the Emergency Procedures and Abnormal Procedures sections of the airplane flight manual to advise the flightcrew to immediately don oxygen masks in the event of significant pressurization or oxygen level changes. The actions specified by this AD are intended to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in their inability to continue to control the airplane. This action is intended to address the identified unsafe condition.
AD 2001-21-04 · published Oct 30, 2001, effective Dec 4, 2001
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. 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 ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes. This action is intended to address the identified unsafe condition.
AD 2001-21-07 · published Oct 30, 2001, effective Dec 4, 2001
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires, for certain airplanes, revising the Airplane Flight Manual, and, for all airplanes, performing repetitive inspections for wear or damage of the inlet check valves and inlet adapters of the override/jettison pumps, and corrective actions, if necessary. This amendment applies to fewer airplanes than the existing AD and requires rework of certain components, which ends the repetitive inspection requirement. These actions are necessary to ensure that the flight crew is advised of the hazards of dry operation of the override/jettison pumps of the center wing fuel tank, and to prevent wear or damage to the inlet check valves and inlet adapters of the override/jettison pumps, which could result in a fire or explosion in the fuel tank during dry (no fuel) operation. This action is intended to address the identified unsafe condition.
AD 2001-22-05 · published Oct 30, 2001, effective Dec 4, 2001
Short Brothers Model SD3 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3 series airplanes, that requires an inspection to find discrepancies of the hydraulic pipelines to the 7P panel and adjacent electrical wiring harnesses, and corrective action, if necessary. This action is necessary to find and fix such discrepancies, which could result in electrical arcing between the hydraulic lines and adjacent wiring, and a potential fire. This action is intended to address the identified unsafe condition.
AD 2001-22-08 · published Oct 30, 2001, effective Dec 4, 2001
Fokker Model F.28 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 series airplanes, that requires replacing the main landing gear (MLG) torque link dampers with modified and reidentified dampers. This action is necessary to prevent degradation of the dampers, which could result in MLG high amplitude oscillation in a lateral torsional mode, and consequent MLG damage or separation of the MLG from the airplane. This action is intended to address the identified unsafe condition.
AD 2001-21-51 · published Oct 31, 2001, effective Nov 5, 2001
Boeing Model 737-600, -700, and -800 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-21-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 737-600, -700, and -800 series airplanes by individual notices. This AD requires a detailed visual inspection for damage of the aft pressure bulkhead at body station (BS) 1016 and the forward attachment of the vertical fin at body section 48, and corrective action, if necessary. This action is prompted by a report of damage to the web of the aft pressure bulkhead at BS 1016. The actions specified by this AD are intended to find and fix damage of the aft pressure bulkhead at BS 1016 and the forward attachment of the vertical fin at body section 48, which could result in structural failure of the aft pressure bulkhead and consequent uncontrolled decompression, or loss of structural integrity of the forward support of the vertical fin, loss of the vertical fin, and consequent loss of control of the airplane.
AD 2001-22-12 · published Oct 31, 2001, effective Nov 15, 2001
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 727 series airplanes. This action requires repetitive inspections for migration or corrosion of the outer hinge pins that attach the horizontal stabilizer to the vertical fin, and various follow-on actions, if necessary. This action also provides other repetitive inspections for cracking or corrosion of the hinge pins, which terminate the required repetitive inspections for migration or corrosion; these inspections are optional for airplanes on which no migration or corrosion is found. This action is necessary to find and fix corrosion or cracking in the hinge pins of the horizontal stabilizer, which could lead to structural degradation of the hinge of the horizontal stabilizer and result in loss of the horizontal stabilizer and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-10-08 R1 · published Oct 3, 2001
Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 Helicopters
This amendment revises an existing airworthiness directive (AD) for Eurocopter France (ECF) Model SA-365N1, AS-365N2, and SA-366G1 helicopters. That AD currently requires inspecting each tail rotor blade for bonding separation, measuring the clearance between the tip of each tail rotor blade and the circumference of the air duct, and replacing the blade if necessary. This amendment requires the same actions but allows the pilot to perform the daily visual check and contains a damage allowance for certain blades. This amendment is prompted by FAA determination that the pilot can check for a cracked, blistered, or wrinkled blade and that some debonding of the blade is acceptable. The actions specified by this AD are intended to allow a pilot check, to prevent unacceptable damage to a tail rotor blade, and to prevent loss of tail rotor control and subsequent loss of control of the helicopter.
AD 2001-20-03 · published Oct 3, 2001, effective Nov 7, 2001
Bell Helicopter Textron Canada Model 206L-4 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206L-4 helicopters that requires installing a high altitude tail rotor static stop yield indicator (indicator) to allow operators to detect excessive bending loads sustained by the tail rotor yoke. A preflight check of the indicator is also required. This amendment is prompted by a determination that a tail rotor yoke with a high altitude rotor system is susceptible to a static and dynamic overload. Static overload could occur after the tail rotor yoke sustains an excessive bending load due to a strike from a ground vehicle. Dynamic overload could occur as a result of a hard landing. The actions specified by this AD are intended to prevent failure of the tail rotor yoke in flight and subsequent loss of control of the helicopter.
AD 2001-20-04 · published Oct 3, 2001, effective Nov 7, 2001
Agusta S.p.A. Model A109E Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that requires modifying the passenger compartment sliding doors by installing certain locking mechanism kits. This amendment is prompted by accidental opening of a passenger compartment sliding door (door) in flight due to a door locking mechanism that is too easy to accidentally open. The actions specified by this AD are intended to prevent accidental opening of a door in flight and subsequent loss of objects that could damage the rotor system.
AD 2001-19-52 · published Oct 15, 2001, effective Oct 30, 2001
Bell Helicopter Textron Canada Model 222, 222B, 222U, and 230 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-19-52 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, and 230 helicopters by individual letters. This AD requires removing certain serial-numbered main rotor pendulum weight supports from service and replacing with airworthy main rotor pendulum weight supports. This AD is prompted by the failure of a main rotor pendulum weight support (support) resulting in shedding of the weights and an increased level of main rotor vibration. The actions specified by this AD are intended to prevent failure of a support, loss of a weight set resulting in main rotor vibration, and subsequent loss of control of the helicopter.
AD 2001-20-18 · published Oct 15, 2001
Robinson Helicopter Company Model R44 Helicopters
This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (RHC) Model R44 helicopters that requires establishing a life limit of 2200 hours time-in-service (TIS) for affected horizontal stabilizers. This amendment is prompted by engineering analysis which indicates that certain vertical-to- horizontal stabilizer attach channels (channels) will crack sooner than the original life limit of the horizontal stabilizer. The actions specified by this AD are intended to prevent a crack through a channel, separation of the stabilizers, and subsequent loss of directional control of the helicopter.
AD 2001-18-51 · published Oct 16, 2001, effective Oct 31, 2001
Eurocopter France Model SA.315B, SA.316C, SA 3180, SA 318B, SA 318C, SA.319B, SE.3160, and SA.316B Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-18-51, which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model SA.315B, SA.316C, SA 3180, SA 318B, SA 318C, SA.319B, SE.3160, and SA.316B helicopters by individual letters. This AD requires, within 10 hours time-in-service (TIS), inspecting the magnetic drain plug and the main gear box (MGB) filter for a rust- colored deposit, inspecting the MGB to determine the angular displacement on the MGB output flange, and periodically examining oil samples. If a rust-colored deposit is found on the drain plug or filter, if the oil is rust-colored, or if the angular displacement is 1 millimeter (0.039 inch) or more, this AD requires replacing the MGB with an airworthy MGB before further flight. Repairing or overhauling the gearbox, or re-identifying certain gearboxes that have already been appropriately overhauled, is terminating action for the requirements of this AD. This AD is prompted by an accident of an ECF Model SA.315B helicopter that lost power to the tail rotor. The loss of power to the tail rotor was due to wear of the splines of the output bevel drive pinion in the MGB. The actions specified by this AD are intended to prevent a loose splined coupling, spline wear, loss of power to the tail rotor, and subsequent loss of control of the helicopter.
AD 2001-22-01 · published Oct 29, 2001, effective Nov 13, 2001
Enstrom Helicopter Corporation Model F-28, F-28A, F-28C, F-28F, 280, 280C, 280F and 280FX Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Enstrom Helicopter Corporation (EHC) Model F-28, F-28A, and 280 helicopters. That AD currently requires inspecting the main rotor shaft (shaft) for a crack or other evidence of damage until appropriately modifying or replacing the shaft with an airworthy shaft at specified time intervals. This amendment adds EHC Model F-28C, F- 28F, 280C, 280F, and 280FX helicopters and establishes life limits after which all unmodified shafts must be retired. This amendment requires determining the radius of the shaft fillet, certain visual and dye-penetrant inspections before further flight, and replacing certain main rotor transmissions. This amendment is prompted by the failure of a shaft on an EHC Model F-28A helicopter due to a fatigue crack. The actions specified by this AD are intended to prevent shaft failure and subsequent loss of control of the helicopter.
AD 2001-20-01 · published Oct 1, 2001, effective Nov 5, 2001
Pratt & Whitney Canada PT6A-25C and -114A Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney Canada (PWC) PT6A-25C and -114A turboprop engines. This amendment will require initial and repetitive visual inspections, and eventual replacement of the compressor bleed valve assembly, with a redesigned valve assembly for -114A and -25C engines. This amendment is prompted by reports of two occurrences of uncommanded engine power loss. The actions specified by this AD are intended to detect wear in the compressor bleed valve assembly which may cause valve orifice blockage, resulting in a loss of power, an inability to accelerate the engine, and an in-flight shutdown.
AD 2001-20-02 · published Oct 1, 2001, effective Nov 5, 2001
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) PW4000 series turbofan engines with 2nd stage high pressure turbine (HPT) air seal assembly part number (P/N) 50L976 or P/N 50L960 installed. This amendment requires operators to recalculate 2nd stage HPT air seal assembly cycles-in- service, based on flight hour-to-cycle ratio usage. This amendment also requires upon recalculation, initial and repetitive on-wing borescope inspections of 2nd stage HPT air seal assemblies for cracks based on the newly calculated service life. This amendment also requires the removal from service of any cracked seal assemblies, and the removal of seal assemblies at or before newly calculated service life limits. This amendment is prompted by reports that thirteen 2nd stage HPT air seal assemblies have been found cracked in the rim area. Although these thirteen air seals were operating in the hottest configuration design, which is no longer in service, the current design 2nd stage HPT air seal assemblies are still operating in a temperature environment that is hotter than anticipated. The actions specified by this AD are intended to prevent 2nd stage HPT air seal assembly fracture that could result in an uncontained engine failure.
AD 2001-20-13 · published Oct 12, 2001, effective Nov 16, 2001
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to certain models of Pratt & Whitney PW4000 series turbofan engines. This amendment requires operators to perform initial and repetitive inspections for cracking of high pressure compressor (HPC) front drum rotors based on cycle usage. This amendment also requires the removal from service of any cracked HPC front drum rotors. This amendment is prompted by reports that 11 HPC drum rotors have been found cracked on the spacer surface between the sixth and seventh stage disks. The actions specified by this AD are intended to detect premature cracking of the HPC drum rotor that could result in an uncontained engine failure and damage to the airplane.
AD 2001-21-02 · published Oct 19, 2001, effective Nov 19, 2001
Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-8, -10N, and -12B Turboprop Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-8, -10N, and -12B turboprop engines with certain electronic engine controls (EEC's) installed. This AD requires revising the Emergency and Normal Procedures section of the applicable Airplane Flight Manual (AFM) until the existing EEC's are replaced. This amendment is prompted by a report of an engine experiencing an uncommanded full power increase during an approach while both engine power levers were at the flight idle gate. The actions specified in this AD are intended to minimize exposure to flight and ground operations that could lead to the loss of control of the airplane due to asymmetric thrust and an uncommanded torque increase.
AD 2001-21-03 · published Oct 22, 2001, effective Nov 26, 2001
General Electric Company GE90 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain General Electric Company (GE) GE90 series turbofan engines. That AD currently requires inspecting and purging the P3B and Ps3 lines and associated fittings and ports of moisture. This amendment will allow the installation of improved hardware as terminating action to requirements of the AD, and remove the GE90-92B engine model from the AD applicability. This amendment is prompted by the recent FAA approval of redesigned P3B and Ps3 sense lines, and the removal of the GE90-92B engine from the applicability. The actions specified in this AD are intended to prevent corruption of Ps3 signals, which could result in simultaneous loss of thrust control of both engines.
AD 2001-22-07 · published Oct 26, 2001, effective Nov 30, 2001
Honeywell International, Inc. LTP 101 Series Turboprop and LTS101 Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to certain Honeywell International, Inc. (formerly AlliedSignal, Inc. and Textron Lycoming) LTP 101 series turboprop and LTS101 series turboshaft engines. This amendment requires a new life limitation and removal of rigid tube fuel manifold assemblies and replacement with serviceable assemblies. This amendment is prompted by reports of cracking and fuel leakage of rigid tube fuel manifolds. The actions specified by this AD are intended to prevent engine fuel leakage due to low-cycle fatigue (LCF) cracking of the rigid tube fuel manifold, which could result in an in-flight fire.
