37 Airworthiness Directives: 15 airplane, 9 rotorcraft, 7 engine, 2 propeller, 2 appliance, 1 glider, 1 balloon.
AD 2002-22-01 · published Nov 1, 2002, effective Dec 13, 2002
Zlin Aircraft a.s. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain MORAVAN a.s. (Moravan) Models Z-143L and Z-242L airplanes. This AD requires you to modify the engine secondary vent line. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to prevent the engine crankcase ventilation lines from freezing during flight in cold weather (winter) conditions, which could result in oil leaking from the engine. Such a condition could lead to engine failure.
AD 2002-22-02 · published Nov 1, 2002, effective Dec 20, 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 the bottom corner of the engine mount bracket for cracks and replace any cracked bracket with a new one. 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 cracks in the engine mount bracket. Such a condition could cause the engine mount assembly to fail, which could result in the engine separating from the airplane and lead to loss of control of the airplane.
AD 2002-22-03 · published Nov 1, 2002, effective Dec 20, 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 repetitively inspect the main landing gear front attachment brackets for cracks, and, if cracks are found, install improved-design brackets. Installing the improved-design brackets terminates the required inspections. 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 cracks in the main landing gear front attachment brackets, which could result in failure of the brackets. Such failure could lead to the main landing gear leg detaching from the wing main spar.
AD 2002-20-07 R1 · published Nov 6, 2002, effective Nov 12, 2002
Boeing Model 737 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that currently requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. That amendment would have superseded seven existing ADs; however, this new amendment removes any reference to superseding four of those seven ADs. This new amendment is prompted by an FAA determination that the requirements of those four ADs must remain in effect until installation of the new rudder control system and corresponding changes to the adjacent systems. The actions specified in this AD are intended to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam.
AD 2002-22-17 · published Nov 12, 2002, effective Dec 31, 2002
Cessna Aircraft Company Models 208 and 208B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to repetitively inspect the inboard forward flap bellcranks for cracks or replace bellcranks depending on the amount of usage. This AD is the result of Cessna re-evaluating the bellcrank life limit analysis and determining that the original estimate is too high. The actions specified by this AD are intended to detect, correct, and prevent future cracks in the bellcrank, which could result in failure of this part. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
AD 2002-23-01 · published Nov 13, 2002, effective Nov 29, 2002
Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 airplanes. This action requires a one-time inspection for evidence of damage to the forward engine cross spar assembly; and repair if necessary. This action is necessary to detect and correct damage to the forward engine cross spar assembly, which could result in reduced structural integrity of the forward engine cross spar assembly. This action is intended to address the identified unsafe condition.
AD 2002-23-05 · published Nov 20, 2002, effective Dec 26, 2002
Cessna Model 750 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 750 airplanes, that requires replacement of reset circuit breakers for the auxiliary hydraulic pump system and the King KHF 950 high frequency communication system(s) with new circuit breakers. This amendment is prompted by a report from the airplane manufacturer indicating that the trip levels for the reset circuit breakers installed in the auxiliary hydraulic pump system and the King KHF 950 high frequency system(s) are too high, which can prevent corresponding high current remote control circuit breakers from tripping when excessive electrical loads are present. The actions specified by this AD are intended to prevent overloading of the affected airplane electrical wiring and circuits, which could result in a fire.
AD 2002-23-10 · published Nov 20, 2002, effective Dec 17, 2002
Piaggio Aero Industries S.p.A. Model P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Piaggio Aero Industries S.p.A. Model P-180 airplanes. This AD requires you to inspect for proper clearance between the first outboard flap control rod and the bleed air duct for interference, replace worn or damaged parts or correct interference, and adjust clearance. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to detect and correct interference or damage of the first outboard flap control rod and bleed air duct, which could result in failure of the flap control rod. Such failure could lead to loss of airplane control.
AD 2002-23-11 · published Nov 20, 2002, effective Jan 10, 2003
Raytheon Aircraft Company 200, 300, and 1900 Series, and Models F90 and A100-1 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 200, 300, and 1900 series, and Models F90 and A100-1 airplanes. This AD requires you to check the airplane logbook to determine if the elevator(s) has/have been removed from the airplane. If the elevator(s) has/have been removed, this AD also requires you to inspect the elevator balance weight attachment screws for correct length, and, if necessary, install new bolts that are of improved design and rebalance the elevator, depending on the results of the inspection. This AD is the result of the elevator balance weight attachment screws and balance weights being improperly installed when balancing the elevator after it had been removed for repair or repainting. The actions specified by this AD are intended to prevent the balance weight attachment screws from becoming loose. Loose screws could come into contact and interfere with the horizontal stabilizer. This interference could restrict elevator movement and result in loss of elevator pitch control.
AD 2002-23-15 · published Nov 26, 2002, effective Dec 11, 2002
Boeing Model 747-100, -200B, -200C, -200F, -300, -400, -400F, and 747SR Series Airplanes, Equipped with a Main Deck Side Cargo Door (MDSCD) Manufactured by Boeing
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, -200B, -200C, -200F, - 300, -400, -400F, and 747SR series airplanes equipped with a MCSCD manufactured by Boeing. This action requires repetitive inspections for cracking of the lower lobe panel of the fuselage skin of the aft cargo bay, and repair if necessary. This action is necessary to find and fix cracking of the skin, which could lead to reduced structural integrity of the side cargo door cutout of the main deck, and result in rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-23-16 · published Nov 26, 2002, effective Dec 11, 2002
McDonnell Douglas Model MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes. This action requires replacement of the Captain's and First Officer's chart holder assemblies on the cockpit control columns with new, improved assemblies. This action is necessary to prevent interference between the cockpit control wheels and the chart holder assembly, which could result in restricted movement of the control wheel travel when rotating the right- and left-wing-down, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-23-17 · published Nov 26, 2002, effective Dec 31, 2002
McDonnell Douglas Model MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-90-30 airplanes, that requires one-time inspections to detect discrepancies of electrical wiring installations in various areas of the airplane; and corrective actions, if necessary. The actions specified by this AD are intended to prevent electrical arcing and/or heat-damaged wiring due to improper wire installations or maintenance practices, which could result in fire and smoke in various areas of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-23-18 · published Nov 26, 2002, effective Dec 31, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes Equipped with Collins LRA-900 Radio Altimeters
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes equipped with certain Collins LRA-900 radio altimeters, that currently requires a revision to the Airplane Flight Manual to prohibit autopilot coupled autoland operations in certain conditions; or, for certain airplanes, replacement of certain Collins LRA-900 radio altimeters with Collins LRA-700 radio altimeters. This amendment also requires a one-time inspection to determine whether a Collins LRA-900 radio altimeter receiver/transmitter with a certain part number is installed, and modification of such a radio altimeter. This amendment is prompted by reports indicating that a fault in Collins LRA-900 radio altimeters having a certain part number could result in an incorrect and unbounded output of radio altitude to other airplanes. The actions specified by this AD are intended to prevent an undetected anomalous radio altitude signal that is passed along to the flare control law of the flight control computer, which could cause the airplane to flare too high or too low during landing, and consequently result in a hard landing. This action is intended to address the identified unsafe condition.
AD 2002-23-20 · published Nov 29, 2002, effective Jan 3, 2003
Dassault Model Falcon 900EX and Mystere Falcon 900 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 900EX and Mystere Falcon 900 series airplanes, that requires repetitive operational tests of the flap asymmetry detection system to verify proper functioning, and repair, if necessary; repetitive replacement of the inboard flap jackscrews with new or reconditioned jackscrews; and repetitive measurement of the screw/nut play of the jackscrews on the inboard and outboard flaps to detect discrepancies, and corrective action, if necessary. This amendment also requires revision of the Airplane Flight Manual. 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 jamming of the flap jackscrews during the approach to landing, which could result in inability to move the flaps or an asymmetric flap condition, and consequent reduced controllability of the airplane.
AD 2002-24-01 · published Nov 29, 2002, effective Jan 21, 2003
Britten Norman (Bembridge) Limited BN2A Mk. III Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Britten Norman (Bembridge) Limited (Britten Norman) BN2A Mk. III series airplanes. This AD requires you to repetitively inspect the rear engine-mounting frame for cracks and replace the frame if cracks are found. 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 cracks in the rear engine-mounting frame, which could lead to engine mount failure. Such failure could result in separation of the engine from the airplane.
AD 2002-17-51 · published Nov 6, 2002, effective Nov 21, 2002
Agusta S.p.A. Model A109E Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-17-51, which was sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) helicopters by individual letters. This AD requires installing a placard in the helicopter and marking the airspeed indication at 140 knots indicated airspeed (KIAS) to indicate a reduction in the helicopter never-exceed speed (Vne) of 28 KIAS; visually checking the tail roter blades on both sides for a crack before each start of the helicopter engines; visually inspecting the tail rotor blades with a 5x or higher magnifying glass at certain time intervals and anytime an increase in vibration occurs, and conducting a dye-penetrant inspection if necessary; and replacing any cracked tail rotor blade with an airworthy tail roter blade. The actions specified by this AD are intended to prevent failure of the tail roter blade and subsequent loss of control of the helicopter.
AD 2002-22-09 · published Nov 6, 2002, effective Nov 21, 2002
Eurocopter France Model AS332C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. This action requires, before further flight, inserting statements into the Limitations section of the Rotorcraft Flight Manual (RFM) prohibiting flight under certain atmospheric conditions. Also, this AD requires inspecting the bullet seal on the multi-purpose air intake (MPAI) to determine the pressure and, if the pressure is less than 3 bars on one or both of the sides, replacing the P2 pipe with an airworthy P2 pipe within a specified time interval. This amendment is prompted by the discovery of unairworthy P2 pipes, which might cause insufficient inflation of the bullet seal on the MPAI. This condition, if not detected, could restrict airflow into the engine inlet during flight in icing conditions, resulting in loss of engine power and subsequent loss of control of the helicopter.
AD 2002-22-10 · published Nov 6, 2002, effective Nov 21, 2002
Bell Helicopter Textron Canada Limited Model 407 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTCL) Model 407 helicopters that requires visually inspecting the brackets that attach the horizontal stabilizer slat (slat) to the stabilizer for a crack. If a crack is found, that AD also requires replacing the slat assembly before further flight. Also, that AD requires installing airworthy, segmented slat assemblies by a specified date. Installing segmented slat assemblies was considered terminating action for the requirements of that AD. This amendment requires, initially and at certain time intervals, checking each slat assembly for a cracked bracket and, if a crack is found, replacing any unairworthy slat assembly with an improved, airworthy slat assembly. This amendment also requires replacing, modifying, and installing identification plates on slats on certain helicopters at specified time intervals. This amendment is prompted by two additional reports of cracked brackets. The actions specified by this AD are intended to prevent a slat from separating, contacting a rotor blade, and resulting in subsequent loss of control of the helicopter.
AD 2002-22-14 · published Nov 8, 2002, effective Dec 13, 2002
Bell Helicopter Textron, Inc. Model 204B, 205A, 205A-1, 205B, 212, 214B, and 214B-1 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for specified Bell Helicopter Textron, Inc. (BHTI) model helicopters that requires reducing the retirement time for certain main rotor tension-torsion (TT) straps on those models and on the Model UH-1 series helicopters. This document contains the same requirements as the existing AD but removes the Model UH-1 series restricted category helicopters and adds the BHTI Model 205A and 205B helicopters to the applicability. This amendment is prompted by the issuance of a separate AD for the Model UH-1 series helicopters and the need to add the BHTI Model 205A and 205B helicopters to the applicability because the affected straps are eligible for installation on these model helicopters. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2002-22-15 · published Nov 12, 2002, effective Dec 17, 2002
Eurocopter France Model EC 155B Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting and adjusting, if necessary, the position of the locking pins on each pilot, co-pilot, and passenger-hinged and sliding door (door) initially and each time a door is replaced. This amendment is prompted by two reports of inadvertent opening of the passenger-hinged doors in flight due to improper adjustment of the door-locking mechanism. The actions specified by this AD are intended to prevent loss of a door in flight, contact with the main rotor or tail rotor, and subsequent loss of helicopter control.
AD 2002-22-16 · published Nov 12, 2002, effective Dec 17, 2002
Eurocopter France Model AS355N Helicopters
This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters. The existing AD requires visually inspecting the four engine exhaust pipe ejector (ejector) attachment lugs (lugs), the starter-generator (S-G) attachment flange (flange) and attachment half-clamps (half-clamps) for cracks, and the S-G shaft for radial play. This amendment will retain the current requirements except will not require measuring the radial play. This amendment will also require measuring each S-G engine clamp torque and vibration level and recording the S-G vibration level on a component history card or equivalent record. If the S-G vibration level is equal to or higher than 0.5 inches per second (IPS), this superseding AD requires repairing or replacing the S-G, as necessary. This amendment is prompted by additional cases of S-G damage and the need for additional corrective actions. The actions specified by this AD are intended to prevent excessive S-G vibration, which could lead to separation of an ejector, impact with the main or tail rotor, and subsequent loss of control of the helicopter.
AD 2002-23-51 · published Nov 13, 2002
Bell Helicopter Textron (Canada) Helicopters
AD 2002-23-03 · published Nov 20, 2002, effective Dec 26, 2002
MD Helicopters, Inc. Model MD900 Helicopters
This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD900 helicopters that requires inspecting and, if necessary, repairing the longitudinal drive link (drive link) and modifying certain nonrotating swashplate (swashplate) assemblies. This AD also requires recording compliance with the AD on a component history card or equivalent record. This amendment is prompted by reports of damage to the drive link assembly caused by the sharp inner edge of the bushing in the swashplate assembly. The actions specified by this AD are intended to prevent damage to the drive link, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
AD 2002-23-04 · published Nov 29, 2002, effective Jan 3, 2003
Eurocopter France Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting the 9-degree frame (frame) for the correct edge distance of the two attachment holes for the reinforced latch support and for a crack and repairing the frame if necessary. This amendment is prompted by the detection of a fatigue crack on the left-hand (LH) side of the frame during maintenance. The actions specified by this AD are intended to prevent failure of the frame due to a crack at the latch support, loss of a passenger door, damage to the rotor system, and subsequent loss of control of the helicopter.
AD 2002-22-06 · published Nov 1, 2002, effective Nov 18, 2002
Honeywell International, Inc., (Formerly AlliedSignal, Inc. and Textron Lycoming) LF507 and ALF502R Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc. and Textron Lycoming) LF507 and ALF502R series turbofan engines with combustion chamber liner assembly part number (P/N) 2-131-520-03 installed. This action requires initial and repetitive borescope inspections of the combustion chamber liner assembly to determine if the combustion liner assembly condition is acceptable for continued operation, requires the removal from service of certain serial number (SN) combustion chamber liner assemblies, and provides an optional terminating action to the repetitive borescope inspections. This amendment is prompted by three reports of separation of the combustor dome baffle from the combustion chamber liner assembly resulting in engine combustion chamber liner assembly burn through. The actions specified in this AD are intended to prevent separation of the combustor dome baffle from the combustion chamber liner assembly and the flow of hot combustor gases on oil and fuel lines which could result in engine fire, in-flight shutdown, and damage to the airplane.
AD 2002-22-11 · published Nov 8, 2002, effective Dec 13, 2002
Turbomeca Artouste III Series Turboshaft Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Turbomeca Artouste III series turboshaft engines with injection wheels part numbers (P/N's) 218.25.700.0, 218.25.704.0, 243.25.709.0, 243.25.713.0, 0.218.27.705.0, 0.218.27.709.0, and 0.218.27.713.0 installed. That AD currently requires smoke emission checks after every ground engine shutdown. If smoke is detected, that AD requires inspecting for fuel flow. If fuel flow is not detected, the engine may have injection wheel cracks, which requires removing the engine from service for repair. If fuel flow is detected, the engine may have a malfunctioning electric fuel cock, which requires removing the electric fuel cock from service and replacing with a serviceable part. This amendment has similar requirements as the original AD, except that the smoke emissions are to be checked after the last flight of the day, as opposed to after every flight, as required by the original AD. This amendment also requires inspection of central labyrinths not previously inspected or not replaced after the engine logged 1,500 operating hours, and, replacement of these labyrinths if necessary. This amendment is prompted by reports and analyses of in-flight shutdowns (IFSD's) occurring since the issuance of AD 2000-06-12. The actions specified by this AD are intended to prevent injection wheel cracks and excessive central labyrinth wear, which could result in an IFSD.
AD 2002-23-06 · published Nov 14, 2002, effective Nov 19, 2002
Textron Lycoming, AVCO Corporation, Lycoming Engines Engines
This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of Textron Lycoming (T/L) AEIO-540, IO-540, LTIO-540, O-540, and TIO-540 series reciprocating engines. That action requires replacing certain zinc-plated crankshaft gear retaining bolts. This action still requires replacing certain zinc-plated crankshaft gear retaining bolts, but expands the population of affected engines. This amendment is prompted by two recent failures of zinc-plated crankshaft gear retaining bolts, and a reassessment of the extent to which the suspect bolts may still be present in the field. The actions specified by this AD are intended to prevent loss of all engine power and possible forced landing.
AD 2002-23-02 · published Nov 20, 2002, effective Dec 26, 2002
General Electric Company CF34-8C1 Turbofan Engines
This amendment adopts a new airworthiness (AD), that is applicable to General Electric Company CF34-8C1 turbofan engines. This amendment requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment also requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. Air carriers with an approved continuous airworthiness maintenance program will be allowed to either maintain the records showing the current status of the inspections using the record keeping system specified in the air carrier's maintenance manual, or establish an acceptable alternate method of record keeping. This amendment is prompted by the need to require enhanced inspection of selected critical life-limited parts of CF34-8C1 turbofan engines at each piece-part exposure. 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 2002-23-13 · published Nov 26, 2002, effective Dec 31, 2002
Pratt & Whitney Canada PT6A Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney Canada PT6A series turboprop engines that have certain turbine exhaust ducts that were modified by a number of different companies. This amendment requires inspections for low- quality welds and cracks of a large population of turbine exhaust ducts. This amendment is prompted by reports of cracks along the weld seams of certain turbine exhaust ducts. The actions specified by this AD are intended to prevent failure of the turbine exhaust duct due to cracking that could result in possible separation of the reduction gearbox and propeller from the engine, and possible loss of control of the airplane.
AD 2002-23-14 · published Nov 26, 2002, effective Dec 31, 2002
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT8D-200 series turbofan engines. This amendment requires initial and repetitive visual inspections, fluorescent magnetic particle inspections (FMPI), and fretting wear inspections of high pressure compressor (HPC) front hubs that have operated with PWA-110 coating in the interface between the hub and the stage 8-9 spacer. This amendment is prompted by the discovery of cracked tierod holes found during routine engine overhauls. The actions specified by this AD are intended to prevent a rupture of the HPC front hub that could result in an uncontained engine failure and damage to the airplane.
AD 2002-23-08 · published Nov 29, 2002, effective Dec 30, 2002
Rolls-Royce plc. RB211-535 Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) models RB211-535E4-37, RB211- 535E4-B-37, and RB211-535E4-B-75 turbofan engines, with certain part number (P/N) low pressure (LP) turbine stage 2 discs installed. This action requires establishing new reduced LP turbine stage 2 disc cyclic limits. This action also requires removing from service affected discs that already exceed the new reduced cyclic limit, and removing other affected discs before exceeding their cyclic limits, using a drawdown schedule. The actions specified in this AD are intended to prevent LP turbine stage 2 disc failure, which could result in uncontained engine failure and possible loss of the airplane.
AD 2002-22-08 · published Nov 4, 2002, effective Nov 19, 2002
Hartzell Propeller Inc., Model HD-E6C-3( ) Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. model HD-E6C-3( ) propellers. This action requires replacement of the current design propeller blade thrust bearing with a new design propeller blade thrust bearing and visual and eddy current inspection (ECI) of propeller hubs for cracks. This amendment is prompted by reports of fractured thrust bearings observed during disassembly, one or more blades becoming jammed in position during operation, pitch change fork fractures causing loss of blade pitch control, and excessive vibration. The actions specified in this AD are intended to prevent loss of aircraft control due to loss of blade pitch control, inability to fully feather the propeller, hub fracture, and blade release.
AD 2002-23-09 · published Nov 25, 2002, effective Dec 30, 2002
MT-Propeller Entwicklung GmbH Propellers
This amendment supersedes an existing airworthiness directive (AD), that is applicable to MT-Propeller Entwicklung GMBH Models MTV-9-B-C and MTV-3-B-C propellers. That AD currently requires initial and repetitive inspections of Torx head blade root lag screws that are used on certain serial number (SN) propellers and replacement of all lag screws on the propeller if any screws are found broken or with insufficient torque. In addition, that AD currently requires the replacement of certain part number (P/N) Torx head blade root lag screws with improved, hexagonal head blade root lag screws. This amendment requires the expansion of the applicability from certain SN propellers to all propellers with certain SN blades that may contain the suspect Torx head blade root lag screws. This amendment is prompted by FAA awareness that a propeller hub of an affected propeller could be changed, thereby changing the propeller serial number, creating a propeller that is not listed in the AD and that has affected blades and lag screws. The actions specified by this AD are intended to prevent failure of the blade root lag screw, which could result in propeller blade separation and loss of control of the airplane. DATES: Effective December 30, 2002. The incorporation by reference of certain publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of July 23, 1999 (64 FR 36777, July 8, 1999).
AD 2002-22-13 · published Nov 5, 2002, effective Dec 20, 2002
Rockwell Collins, Inc. FMC-4200, FMC-5000, and FMC-6000 Flight Management Computers
This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins, Inc. (Rockwell Collins) FMC-4200, FMC-5000, and FMC-6000 flight management computers (FMC) that are installed on airplanes. This AD requires you to remove the affected FMC unit and replace it with a new FMC unit or an FMC unit that has been modified to correct a problem with the flight management system (FMS) accepting new information when an existing procedure or flight plan is changed. This AD is the result of a report that an aircraft proceeded beyond the published altitude constraint on an arrival procedure. The actions specified by this AD are intended to prevent the FMC from retaining and displaying original altitude constraints when an edit or a replacement is made to a procedure or flight plan that shares a waypoint with another procedure or an airway, and there is an altitude constraint on the shared waypoint. Such a condition could cause the pilot to fly the airplane out of the range of the correct altitude constraint. This condition could result in air traffic control or the pilot making flight decisions that put the airplane in unsafe flight conditions.
AD 2002-22-12 · published Nov 8, 2002, effective Dec 13, 2002
Titeflex Corporation
This amendment adopts a new airworthiness directive (AD), that is applicable to certain Titeflex Corporation high-pressure and medium- pressure hoses. This amendment requires inspecting certain Titeflex hoses for a date of manufacture, and if necessary, replacing the hose with a serviceable part. This amendment is prompted by reports of hoses that failed to meet the fire test requirements during laboratory testing. The actions specified by this AD are intended to prevent failure of a hose when exposed to fire.
AD 2002-22-04 · published Nov 1, 2002, effective Dec 20, 2002
Stemme GmbH & Co. KG Model S10-VT Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Model S10-VT sailplanes. This AD requires you to modify the engine compartment fuel and oil system and firewall. 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 reduce the potential for a fire to ignite in the engine compartment and increase the containment of an engine fire in the engine compartment. A fire in the engine compartment could lead to loss of control of the sailplane.
AD 2002-23-07 · published Nov 20, 2002, effective Jan 7, 2003
Cameron Balloons Ltd. (Sky Balloons) Mk1 (BR1) & Mk2 (Mistral) Burners
This amendment adopts a new airworthiness directive (AD) that applies to all aircraft (specifically balloons) that incorporate certain Cameron Balloons Ltd. (Sky Balloons) Mk1 (BR1) & Mk2 (Mistral) burners. This AD requires you to replace the valve stems of the main blast, liquid fire, and pilot light valves. 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 mechanical failure of the valve stem/seat pinned joint, which could result in a propane vapor leak. Such failure could lead to a propane explosion and fire.
