38 Airworthiness Directives: 24 airplane, 4 rotorcraft, 9 engine, 1 propeller.
AD 2002-08-18 · published May 1, 2002, effective May 16, 2002
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires repetitive inspections (tests) of the actuator clutches of the primary and backup pitch trim systems of the horizontal stabilizer for proper pitch trim indications, and replacement of the actuator, if necessary. This action is necessary to prevent loss of pitch trim command during the takeoff and climb phase of flight due to improper set point of the actuator clutches, which could result in high pitch control forces and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-08-21 · published May 1, 2002, effective May 16, 2002
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135ER and "135LR series airplanes, and Model EMB-145, -145ER, -145MR, and -145LR series airplanes, that currently requires a one-time inspection to determine if the bonding jumpers that connect the horizontal stabilizer to the vertical stabilizer are properly installed, a one-time inspection to determine if the supports that connect the bonding jumpers to the horizontal stabilizer are deformed, and corrective actions if necessary. This amendment requires new repetitive inspections to detect discrepancies of both vertical-to-horizontal stabilizer bonding jumpers and the connecting support structure; and corrective action, if necessary. This amendment also revises the applicability to include additional airplanes. The actions specified in this AD are intended to prevent damaged or severed bonding jumpers, which, in the event of a lightning strike, could result in severed elevator control cables and consequent reduced elevator control capability and reduced controllability of the airplane. This AD is intended to address the identified unsafe condition.
AD 2002-08-51 · published May 1, 2002, effective May 6, 2002
Airbus Model A300 B2 and B4 Series Airplanes Equipped With General Electric CF6-50 Engines
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-08-51 that was sent previously to all known U.S. owners and operators of Airbus Model A300 B2 and B4 series airplanes equipped with General Electric CF6-50 engines by individual notices. This AD requires deactivating both thrust reversers and revising the airplane flight manual (AFM) to require performance penalties during certain takeoff conditions to ensure that safe and appropriate performance is achieved for airplanes on which both thrust reversers have been deactivated. 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 uncommanded in-flight deployment of a thrust reverser, which could result in reduced controllability of the airplane.
AD 2002-08-17 · published May 2, 2002, effective May 17, 2002
McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, and DC-10-30F (KC10A and KDC-10) Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, and DC-10-30F (KC10A and KDC-10) airplanes. This action requires revising the airplane flight manual to advise the flightcrew of necessary procedures if certain thrust reverser indicator lights illuminate or are inoperative, and locking out any affected thrust reverser under certain conditions. This action also provides for returning a thrust reverser to service after it has been locked out. This action is necessary to prevent an uncommanded in- flight deployment of a thrust reverser, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-09-05 · published May 2, 2002, effective Jun 6, 2002
Bombardier Model CL-600-2B19 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that requires a one-time inspection of the fuel-level sensing wires in the center fuel tank for damage and for clearance from the adjacent structure; and corrective action, if necessary. The actions specified by this AD are intended to detect and correct inadequate clearance between the fuel-level sensing wires in the center fuel tank and adjacent structures, which could lead to chafing of the wires, resulting in electrical arcing between the fuel-level sensing wires and the center fuel tank and a consequent fire or explosion in the center fuel tank. This action is intended to address the identified unsafe condition.
AD 2002-09-06 · published May 2, 2002, effective Jun 6, 2002
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 airplanes. This AD requires an inspection to verify proper installation of the support clamp of the alternating current (AC) power relay feeder cables at the aft inboard side of the electrical power center, and corrective actions, if necessary. This action is necessary to prevent the AC power relay feeder cables from chafing against the aft inboard side of the electrical power center due to improper installation, which could result in electrical arcing and damage to adjacent structures, and consequent smoke and/or fire in the electrical power center area. This action is intended to address the identified unsafe condition.
AD 2002-09-07 · published May 2, 2002, effective Jun 6, 2002
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 airplanes. This AD requires an inspection of the electrical power feeder cables in the aft cargo compartment sidewall for chafing and/or preloading, and corrective actions, if necessary. This action is necessary to prevent possible arcing of the electrical power cables in the aft cargo compartment sidewall and consequent damage to equipment and the adjacent structure, which could result in smoke and/or fire in the cargo compartment. This action is intended to address the identified unsafe condition.
AD 2002-09-11 · published May 7, 2002, effective Jun 20, 2002
SOCATA-Groupe AEROSPATIALE Model TBM 700 Airplanes
This amendment supersedes Airworthiness Directive (AD) 2001- 05-03, which applies to certain SOCATA--Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. AD 2001-05-03 currently requires you to apply Loctite on attaching bolt/screw threads of inboard, central, and outboard carriages; increase tightening torques of associated hardware; and replace central carriage attaching bolts. The French airworthiness authority has determined that certain service information referenced in AD 2001-05-03 be removed and additional inspection of the flap carriage attaching bolts, screws, and barrel nut be included. Therefore, this AD will retain the requirements of the current AD and will add the information communicated by the French airworthiness authority. The actions specified by this AD are intended to prevent the flap attaching bolts/screws from becoming loose and separating from the airplane, which could cause rough or irregular control. Such rough or irregular control could lead to the loss of control of the airplane.
AD 2002-09-12 · published May 9, 2002, effective Jun 21, 2002
Raytheon Aircraft Company Beech Model C90 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Model C90 airplanes. This AD requires you to inspect the left-hand (LH) and right-hand (RH) nacelle and spar assembly for the existence of rivets, and requires you to install rivets if they do not exist or are the wrong size or type. This AD is the result of Raytheon identifying several instances where rivets were either missing or were the wrong size or type on these airplanes. The actions specified by this AD are intended to correct the installation of rivets in the LH and RH nacelle and spar assembly. These rivets must be present and have the correct dimension in order to prevent reduced structural integrity, which could result in structural failure and possible loss of control of the airplane.
AD 2002-09-13 · published May 9, 2002, effective May 31, 2002
Cessna Aircraft Company Model CESSNA 441 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Model CESSNA 441 airplanes. This AD requires you to do a one-time inspection of the fuel boost pump wiring inside and outside the boost pump reservoir, and repair or replace the wiring as necessary. This AD is the result of several reports of chafing and/or arcing of the fuel boost pump wiring inside and outside the fuel pump reservoir. The actions specified by this AD are intended to detect and correct chafing and/or arcing boost pump wiring, which could result in arcing within the wing fuel storage system. Such failure could lead to ignition of explosive vapor within the fuel storage system.
AD 2002-07-09 · published May 13, 2002, effective May 17, 2002
Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F Series Airplanes
This document corrects information in an existing airworthiness directive (AD that applies to certain Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes. That AD currently requires repetitive inspections to find cracking of the lower skin panel at the lower row of fasteners in certain lap joints of the fuselage, and repair, if necessary. This document corrects a typographical error in the supplemental type certificate (STC) number specified in paragraph (i) of that AD. This correction is necessary to ensure that the correct STC number is specified and operators of affected airplanes are advised of all applicable actions.
AD 2002-08-19 · published May 13, 2002, effective May 28, 2002
Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes, that currently requires revising the Airplane Flight Manual to address uncommanded transfer of fuel between the wing fuel tanks and the center fuel tank; revising the Minimum Equipment List; limiting airplane operation; and increasing normal mission fuel requirements by 3,000 pounds. This amendment retains the requirements of the existing AD, and adds requirements for modification of the fuel distribution system for the center tank; and an inspection of that system for discrepancies, and corrective actions if necessary. This amendment is prompted by reports of uncommanded fuel transfer between wing fuel tanks and the center fuel tank, and reports of misaligned or damaged fuel tubes due to vibration. The actions specified in this AD are intended to ensure that the flight crew has the procedures necessary to address uncommanded fuel transfer; and to detect and correct discrepancies in the fuel distribution system, which could cause the center tank to overfill and fuel to leak from the center tank vent system or to become inaccessible, and could result in engine fuel starvation.
AD 2002-10-01 · published May 16, 2002, effective Jun 20, 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, that requires modification of the main battery ground stud and installation of a nameplate which indicates torque requirements for the ground stud nut. The actions specified by this AD are intended to prevent the ground stud nut from being inadequately tightened or becoming loose, which could result in electrical arcing between the ground stud and the adjacent structure, leading to damage to electrical or electronic equipment or possibly to fire in the airplane.
AD 2002-10-02 · published May 16, 2002, effective Jun 20, 2002
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires installation of an extender bracket for the compensator of the Simmonds fuel quantity indication system (FQIS) in the main fuel tanks. This action is necessary to prevent contact between the compensator for the Simmonds FQIS system and a flapper check valve on a baffle rib in the main fuel tanks, which--in conjunction with another wiring failure outside the fuel tank--could result in an electrical arc and a consequent potential source of ignition in the fuel tank. This action is intended to address the identified unsafe condition.
AD 2002-10-03 · published May 16, 2002, effective Jun 20, 2002
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes. This AD requires replacement of certain main landing gear (MLG) shock strut piston assemblies with new or serviceable, improved assemblies, which constitutes terminating action for the requirements of certain other ADs. This action is necessary to prevent fatigue cracking of the MLG shock strut pistons, which could result in failure of the MLG shock strut pistons during landing or jacking of the airplane, and consequent damage to the airplane structure and injury to the passengers, flightcrew, or ground personnel. This action is intended to address the identified unsafe condition.
AD 2002-10-06 · published May 20, 2002, effective Jun 24, 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 replacing certain flight warning computers (FWCs) with improved FWCs. 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 erroneous display of decision height information to the flightcrew during final approach, which could result in an increased risk of collision with terrain.
AD 2002-10-09 · published May 22, 2002, effective Jun 6, 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 repetitive inspections for evidence of fuel accumulation inside of the aft service compartment; and follow-on actions, if necessary. This AD also provides for an optional terminating modification. This action is necessary to prevent such fuel accumulation, which could result in fuel vapors coming into contact with ignition sources and consequent fire. This action is intended to address the identified unsafe condition.
AD 2002-10-10 · published May 23, 2002, effective Jun 27, 2002
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect cracks in various areas of the fuselage internal structure, and repair, if necessary. This amendment adds new repetitive inspections for cracking of certain areas of the upper chord of the upper deck floor beams, and repair, if necessary. This amendment is prompted by the results of fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. The actions specified by this AD are intended to prevent loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane.
AD 2002-10-11 · published May 23, 2002, effective Jun 27, 2002
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires repetitive inspections for cracking and corrosion of the pressure bulkhead at body station (BS) 1016, and follow-on actions. This amendment expands the applicability of the existing AD, and requires new repetitive inspections to detect cracking and corrosion of the aft pressure bulkhead at BS 1016, and follow-on actions. This action is necessary to detect and correct corrosion or cracking of the aft pressure bulkhead at BS 1016, which could result in loss of the aft pressure bulkhead web and stiffeners and consequent rapid decompression of the fuselage. This action is intended to address the identified unsafe condition.
AD 2002-10-12 · published May 23, 2002, effective Jun 27, 2002
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and - 500 series airplanes. For certain airplanes, this amendment requires a one-time inspection or a review of the maintenance records of the airplane to determine if a particular control rod barrel for the aileron tabs is installed, and follow-on repetitive inspections for cracking of the control rod barrels and replacement of the control rod barrels with new barrels, if necessary. Such replacement terminates the repetitive inspections. For all airplanes, this amendment prohibits installation of a certain control rod barrel for the aileron tabs. The actions specified by this AD are intended to prevent the disconnection of an aileron tab, which could lead to severe airframe vibrations; consequent damage to the aileron tab, aileron, and wing; and possible loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-10-13 · published May 24, 2002, effective Jul 8, 2002
Raytheon Aircraft Company Model 58P, 60, A60, B60, and 65-88 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 58P, 60, A60, B60, and 65-88 airplanes. This AD requires you to install new exterior operating instruction placards for the exit doors. This AD is the result of Raytheon improving the visibility and understandability of the door operating instruction placards. This was done as a result of difficulty opening the emergency exits of a similar type design airplane. The actions specified by this AD are intended to assure that clear and complete operating instructions are visible for opening the emergency exit doors. If not visible and understandable, this could result in the inability to open the exit door during an emergency situation.
AD 2002-11-02 · published May 29, 2002, effective Jun 14, 2002
Raytheon Aircraft Company Model 390 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to insert a temporary change into the FAA-approved Airplane Flight Manual (AFM) that adds a limitation for prohibiting flight into icing conditions and adds procedures for when an icing condition occurs. This AD is the result of reports of a manufacturing problem with the wing leading edge anti-ice system. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in icing conditions by providing procedures and limitations associated with such conditions.
AD 2002-08-06 · published May 31, 2002, effective May 3, 2002
Boeing Model 777-200 and -300 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain Boeing Model 777- 200 and -300 series airplanes. That AD currently requires a one-time torque check (inspection) of the bolts that attach the pivot fittings to the horizontal stabilizer through the upper and lower titanium straps, to determine if the bolts are adequately torqued, and follow-on actions. This document corrects the requirements of the existing AD by adding an option to allow operators a 30-day grace period for submission of the report required by paragraph (d) of the AD. This correction is prompted by communication received from the manufacturer that the current requirements of the AD could put operators out of compliance.
AD 2002-11-05 · published May 31, 2002, effective Jul 12, 2002
Air Tractor, Inc. Models AT-400, AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501, AT-802, and AT-802A Airplanes
This amendment supersedes Airworthiness Directive (AD) 2001- 10-04 R1, which lowered the safe life for the wing lower spar cap on certain Air Tractor, Inc. (Air Tractor) AT-400, AT-500, and AT-800 series airplanes. AD 2001-10-04 R1 resulted from numerous reports of cracks in the \3/8\-inch bolthole of the wing lower spar cap on the affected airplanes. This AD retains the safe life for the wing lower spar cap and requires you to eddy-current inspect the wing lower spar cap immediately prior to the replacement/modification in order to detect and correct any crack in a bolthole before it extends to the modified center section of the wing. This AD further reduces the safe life for certain Models AT-401, AT-401B, AT-402, AT-402A, AT-402B, and AT-501 airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets and removes the Models AT-502, AT-502A, AT- 502B, and AT-503A airplanes from the applicability. We are issuing another AD action to cover these airplanes. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in the wing separating from the airplane during flight.
AD 2002-09-03 · published May 2, 2002, effective May 17, 2002
Eurocopter France Model AS332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332L2 helicopters. This action requires, before further flight, verifying that the air vent is installed on the inflation cylinder of each life raft assembly. If the air vent is missing, this AD also requires replacing the cylinder head with an airworthy part before further flight. This amendment is prompted by the discovery that an inflation cylinder in the life raft did not have an air vent installed. This condition, if not corrected, could result in inadvertent life raft inflation, loss of the life raft, contact with the main or tail rotor, and subsequent loss of control of the helicopter.
AD 2002-09-04 · published May 3, 2002, effective Jun 7, 2002
Bell Helicopter Textron, Inc. Model 205A, 205A-1, 205B, 212, 412, 412EP, and 412CF Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 205A, 205A-1, 205B, 212, 412, 412EP, and 412CF helicopters, that requires inspecting each affected tail rotor blade forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids, and removing any tail rotor blade with an excessive void from service. This AD also requires modifying certain tail rotor blades by installing shear pins and tip closure rivets. This amendment is prompted by five occurrences of missing tip blocks or tip closures resulting in minor to substantial damage. The actions specified by this AD are intended to prevent loss of a tip block or tip closure, loss of a tail rotor blade, and subsequent loss of control of the helicopter.
AD 2002-10-05 · published May 15, 2002, effective Jun 19, 2002
MD Helicopters Inc. Model MD-900 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to MD Helicopters Inc. Model MD-900 helicopters, that currently requires inspecting the main rotor upper hub (hub) assembly drive plate attachment flange (flange), determining the torque of each flange nut (nut), and if a crack is found, before further flight, replacing the hub assembly. In addition to the current requirements, this action requires visually inspecting the outer surface of the flange at specified intervals, removing the drive plate and visually inspecting the flange for a crack at specified intervals, and replacing any unairworthy hub assembly. This amendment is prompted by reports that cracks starting at the drive plate attachment holes were found in the hub. The actions specified by this AD are intended to detect a crack in the flange and to prevent failure of the hub assembly, loss of drive to the main rotor, and subsequent loss of control of the helicopter.
AD 2002-11-01 · published May 30, 2002, effective Jun 14, 2002
Eurocopter Deutschland Model EC135 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland (Eurocopter) Model EC135 helicopters with Turbomeca Arrius 2B1 engines installed. This action requires modifying the engine electrical control unit (FADEC) software and the collective linear transducer (LVDT). This amendment is prompted by a parameter discrepancy within the engine fuel main metering unit that is transmitted to the FADEC. This condition, if not corrected, could result in deactivation of the engine main fuel-metering valve, loss of automatic control of the affected engine, and subsequent loss of control of the helicopter.
AD 2002-09-01 · published May 2, 2002, effective Jun 6, 2002
Pratt & Whitney 4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) PW4090, PW4090-3, PW4074D, PW4077D, PW4090D, and PW4098 turbofan engines with 15th stage high pressure compressor (HPC) disks having certain part numbers (P/N's). This amendment requires initial and repetitive borescope inspections of 15th stage HPC disks for cracks in the knife edges, eddy current inspections (ECI's) of blade loading slots if required, and removal of cracked disks. In addition, this amendment requires the removal from service of these P/N disks, at a new lower cyclic life limit. This amendment is prompted by two reports of 15th stage HPC disks with cracks in the outer rim front rail of the blade loading slots, and in the front forward and middle knife edges. The actions specified by this AD are intended to prevent 15th stage HPC disk failures from cracks, which could result in an uncontained engine failure.
AD 2002-09-02 · published May 2, 2002, effective Jun 6, 2002
Rolls-Royce plc. Tay Model 650-15 and 651-54 Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc. (RR) Tay model 650-15 and 651-54 turbofan engines. This amendment requires revisions to the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) in the Time Limits Section of the Engine Manual for Rolls-Royce plc. Tay model 650-15 and 651-54 series turbofan engines to include required enhanced inspection of selected critical life-limited parts 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 2002-09-10 · published May 8, 2002, effective Jun 12, 2002
CFE Company Model CFE738-1-1B Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to CFE Company Model CFE738-1-1B turbofan engines. This amendment requires replacing the high pressure turbine (HPT) stage 1 aft cooling plate and HPT stage 2 disk at or before they reach new reduced life cycle limits. This amendment is prompted by analysis of the existing life cycle limits by the engine manufacturer. The actions specified by this AD are intended to prevent failure of the HPT stage 1 aft cooling plate and HPT stage 2 disk, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-09-09 · published May 9, 2002, effective Jun 13, 2002
Honeywell International, Inc., (Formerly AlliedSignal, Inc., Textron Lycoming, Avco Lycoming, and Lycoming) Former Military T53 Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., Textron Lycoming, Avco Lycoming, and Lycoming) former military T53 series turboshaft engines. This amendment requires conducting a revised operating cycle count (prorate) and initial and repetitive inspections for cracks of centrifugal compressor impellers. This amendment is prompted by a report of a military surplus helicopter that experienced low-cycle fatigue failure of the centrifugal compressor impeller, resulting in an uncontained engine failure. The actions specified by this AD are intended to prevent centrifugal compressor impeller failure, which can result in an uncontained engine failure, in-flight engine shutdown, or damage to the helicopter.
AD 2002-10-04 · published May 16, 2002, effective Jun 20, 2002
General Electric Company CF6-80E1A2 Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1A2 turbofan engines. This action requires replacing a certain low pressure turbine rotor (LPTR) shaft at or before reaching a new reduced life cycle limit. This amendment is prompted by an updated low cycle fatigue (LCF) analysis of the LPTR shaft. The actions specified in this AD are intended to prevent LCF cracking and failure of the LPTR shaft due to exceeding the life limit, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-10-07 · published May 23, 2002, effective Jun 27, 2002
Pratt & Whitney JT9D-59A, -70A, -7Q, and -7Q3 Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines. This amendment requires fluorescent penetrant inspection of the high pressure turbine (HPT) second stage airseal knife edges for cracks, each time the airseal is accessible. This amendment is prompted by reports of cracks found in the knife edges of HPT second stage airseals during HPT disassembly. The actions specified by this AD are intended to prevent failure of HPT second stage airseals due to cracks in the knife edges, which if not detected could result in uncontained engine failure and damage to the airplane.
AD 2002-10-08 · published May 23, 2002, effective Jun 27, 2002
General Electric Company CF6-80E1 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1 series turbofan engines installed on Airbus Industrie A330 series airplanes. This action requires initial and repetitive thrust reverser inspections and checks, and allows extended threshold and repetitive inspection intervals for certain inspections if an optional double p-seal configuration is installed. This amendment is prompted by reports of service-induced hardware deterioration that reduces the overall thrust reverser system protection against inadvertent deployment, which can result in loss of control of the airplane. The actions specified in this AD are intended to prevent inadvertent in-flight thrust reverser deployment, which can result in loss of control of the airplane.
AD 2002-10-14 · published May 28, 2002, effective Jun 12, 2002
Bombardier-Rotax GmbH 914 F Series Reciprocating Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Bombardier-Rotax GmbH 914 F series reciprocating engines. This action requires initial and repetitive inspections of certain exhaust bend assemblies, which are located between the cylinder heads and exhaust manifold assembly. This amendment is prompted by reports of cracks found in exhaust bend assemblies. The actions specified in this AD are intended to prevent carbon monoxide from entering the cabin and also to prevent the possibility of an engine fire.
AD 2002-10-15 · published May 28, 2002, effective Jul 2, 2002
Rolls-Royce plc RB211 Trent 875, 877, 884, 892, 892B, and 895 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines. This amendment requires reapplication of dry film lubricant to low pressure compressor (LPC) fan blade roots. This amendment is prompted by an aborted take-off resulting from LPC fan blade loss. Since this event, four additional cracked LPC fan blade roots have been reported. The actions specified by this AD are intended to prevent LPC fan blade loss, which could result in an uncontained engine failure and possible aircraft damage.
AD 2002-09-08 · published May 9, 2002, effective Jun 13, 2002
Hartzell Propeller, Inc. Compact Series Propellers
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Hartzell models ( )HC-( )( )Y( )-( )( )( ) compact series, constant speed or feathering propellers with Hartzell manufactured "Y" shank blades. That AD currently requires initial and repetitive blade inspections; rework of all "Y" shank blades including cold rolling of the blade shank retention radius; blade replacement and modification of pitch change mechanisms for certain propeller models; and changing the airplane operating limitations with specific models of propellers installed. This amendment requires initial blade inspections, with no repetitive inspections; rework of all "Y" shank blades including cold rolling of the blade shank retention radius, blade replacement and modification of pitch change mechanisms for certain propeller models; and changing the airplane operating limitations with specific models of propellers installed. This amendment is prompted by FAA reviews of propeller service histories since the issuance of AD 77-12-06R2. The actions specified by this AD are intended to prevent failure of the propeller blade from fatigue cracks in the blade shank radius, which can result in damage to the airplane and loss of airplane control.
