29 Airworthiness Directives: 13 airplane, 7 rotorcraft, 8 engine, 1 appliance.
AD 2002-11-04 · published Jun 3, 2002, effective Jul 8, 2002
Airbus Model A300 B4-600 and A300 B4-600R Series Airplanes, and Model A300 F4-605R Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4-600, A300 B4-600R, and A300 F4-600R series airplanes (A300-600), that currently requires an inspection to detect cracks of certain attachment holes; and installation of new fasteners and follow-on inspections or repair if necessary. This amendment requires repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of frame FR47. This amendment revises the applicability of the existing AD. The actions specified by this AD are intended to prevent fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.
AD 2002-11-03 · published Jun 4, 2002, effective Jun 14, 2002
Air Tractor, Inc. Models AT-502, AT-502A, AT-502B, and AT-503A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-502, AT- 502A, AT-502B, and AT-503A airplanes. This AD lowers the safe life for the wing lower spar cap established in AD 2001-10-04 R1 and further reduces the safe life for airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets. This AD also requires you to eddy-current inspect the wing lower spar cap immediately prior to the replacement/modification to detect and correct any crack in a bolthole before it extends to the modified center section of the wing and report the results of this inspection to the Federal Aviation Administration (FAA). This AD is the result of reports of several cracks originating in the outboard \3/8\-inch hole of the main spar lower cap on Air Tractor Models AT-502, AT-502A, AT-502B, and AT-503A airplanes at times lower than the established safe life. 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 2002-11-06 · published Jun 5, 2002, effective Jul 10, 2002
Boeing Model 777 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that currently requires repetitive inspections to detect cracking of the cove skin on the outboard leading edge slats, and corrective actions, if necessary. The existing AD also provides for an optional modification that significantly increases the repetitive inspection interval. This amendment expands the applicability of the existing AD by mandating the currently required inspections, and corrective actions, if necessary, for additional airplanes. Also, for airplanes on which the optional modification has been accomplished, this action requires a new one-time inspection for undersized seal inserts in the spanwise bulb seals on certain slats, and replacement of seal assemblies with new assemblies, if necessary. The actions specified by this AD are intended to detect and correct cracking or missing pieces of the cove skin, or undersized seal inserts installed in the spanwise bulb seals, on the outboard leading edge slats on the wings, which could result in skin separation or structural damage to the leading edge slats and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-11-07 · published Jun 6, 2002, effective Jul 15, 2002
Raytheon Aircraft Company Models E55, E55A, A56TC, 58, 58A, 58P, 58PA, 58TC, and 58TCA Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models E55, E55A, A56TC, 58, 58A, 58P, 58PA, 58TC, and 58TCA airplanes. This AD requires you to inspect the Instrument Subpanel electroluminescent panel retaining screw for proper length and the rotating beacon circuit breaker switch (or any other switch in the same location) for damage and replace any screw or circuit breaker switch as necessary. This AD is the result of a report that an improper length electroluminescent panel retaining screw damaged the rotating beacon circuit breaker switch, which resulted in damaged wiring. The actions specified by this AD are intended to prevent damage to the rotating beacon circuit breaker switch or any other switch in the same location because of an incorrect length electroluminescent panel retaining screw. This condition could result in failure of the circuit breaker and lead to smoke and/or fire in the cockpit.
AD 2002-11-11 · published Jun 7, 2002, effective Jun 24, 2002
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires an inspection of visually accessible areas for indications of overheating of the heater tape attached to the potable water fill and drain lines in the forward and aft cargo compartments, exposed foam insulation or missing or damaged protective tape around the potable water fill and drain lines, and debris or contaminants on or near the potable water fill and drain lines. It also requires corrective action, as necessary. This action is necessary to prevent overheating of the heater tape on potable water fill and drain lines, which may ignite accumulated debris or contaminants on or near the potable water fill and drain lines, resulting in a fire in the airplane. This action is intended to address the identified unsafe condition.
AD 2002-12-01 · published Jun 11, 2002, effective Jul 16, 2002
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires a functional test of the shortening mechanism of the nose landing gear for free movement of the capsule in the upper and lower bearings, and corrective action, if necessary. This action is necessary to prevent damage to the capsule, which could result in inability to extend the nose landing gear in normal or emergency situations, and consequent injury to passengers and flight crew. This action is intended to address the identified unsafe condition.
AD 2002-12-05 · published Jun 13, 2002, effective Jul 18, 2002
Boeing Model 767-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 series airplanes, that requires repetitive inspections of the side panels of the nose wheel well for broken rivets and replacement of any broken rivets with bolts. This amendment also requires follow-on inspections of adjacent areas for cracks or broken rivets, whenever two or more adjacent broken rivets are found; repair of any cracks; and replacement of any broken rivets with bolts. Finally, this amendment provides for the optional replacement of all rivets in the affected areas with bolts, which terminates the repetitive inspections. The actions specified by this AD are intended to detect and correct broken rivets in the nose wheel well side panels and top panel, which could impair the function of the nose landing gear and cause fatigue cracks in the side panel and top panel webs of the nose wheel well, which could result in rapid cabin depressurization during flight. This action is intended to address the identified unsafe condition.
AD 2002-12-04 · published Jun 18, 2002, effective Jul 23, 2002
Boeing Model 757-200, -200CB, and -200PF; and 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200CB, and -200PF; and 767-200, -300, and -300F series airplanes; that requires modification of the right main landing gear and auto-speedbrake control system to provide an air/ground signal to the system. This action is necessary to prevent uncommanded deployment of the auto-speedbrake spoilers during flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-12-10 · published Jun 18, 2002, effective Jul 23, 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 installation of two arcing protection brackets below and behind the circuit breakers located in the generator control rack in the electrical/electronics compartment. The actions specified by this AD are intended to prevent arcing between circuit breaker terminals and adjacent equipment and structure located in the generator control rack in the electrical/electronics compartment, which, if not corrected, could result in possible electrical shock to maintenance personnel during maintenance operations. This action is intended to address the identified unsafe condition.
AD 2002-12-12 · published Jun 20, 2002, effective Jul 25, 2002
Bombardier Model CL-215-1A10 and CL-215-6B11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-215-1A10 and CL-215- 6B11 series airplanes, that currently requires repetitive inspections to detect cracking on certain wing-to-fuselage frame angles; and repair, if necessary. This amendment decreases the compliance time for the initial inspection to detect cracking on certain wing-to-fuselage frame angles and decreases the interval between repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking in the wing-to-fuselage frame angles, which could result in reduced structural integrity of the airframe.
AD 2002-12-11 · published Jun 26, 2002, effective Jul 31, 2002
Bombardier Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires revision of the applicable maintenance program manual, repetitive inspections for corrosion or cracking of the hook roller shafts of the flap carriage, and eventual replacement of the hook roller shafts with new or serviceable hook roller shafts. This replacement extends the interval for the repetitive inspections. This action is necessary to prevent cracking of the hook roller shafts of the flap carriage and consequent reduced structural integrity of the flap, which could result in jamming of the flap. This action is intended to address the identified unsafe condition.
AD 2002-12-13 · published Jun 26, 2002, effective Jul 31, 2002
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires a review of maintenance records or a one-time test to determine if elevator hinge support ribs on the trailing edge of the horizontal stabilizer are made from a certain material, and follow-on repetitive inspections for corrosion or cracking of the elevator hinge support ribs, if necessary. For airplanes with the affected ribs installed, this AD eventually requires replacement of all affected ribs with new, improved ribs. This action is necessary to prevent cracking of the elevator hinge support ribs, which could lead to vibration of the airframe during flight and consequent damage to the elevator and horizontal stabilizer, potentially resulting in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-13-01 · published Jun 26, 2002, effective Jul 31, 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 an inspection of the galley power feeder cable above the main cabin ceiling supports for damage caused by chafing. The amendment also requires repairing any damage on the outer cable jacket or primary insulation, installing a splice on the power feeder cable to remove damage, installing sleeving along a portion of the cable, installing standoffs for the cable, re-routing the galley power feeder cable, and testing the galley equipment, as applicable. The actions specified by this AD are intended to prevent future damage to the galley power feeder cable as well as to detect and correct existing damage to the galley power feeder cable, which could result in electrical arcing, possibly leading to damage to adjacent structures and to fire in the airplane. This action is intended to address the identified unsafe condition.
AD 2002-11-10 · published Jun 7, 2002, effective Jun 24, 2002
Sikorsky Model S-70A and S-70C Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Model S-70A and S-70C helicopters. That AD currently requires inspecting a certain part-numbered main landing gear drag beam (beam) for a crack, removing any cracked beam before further flight, and reducing the torque of the jackpad mounting bolt retention nut (nut) of each beam. This amendment contains the same actions but requires those actions for another beam part number (P/N). This amendment is prompted by the inadvertent omission in the current AD of the additional beam that is susceptible to failure due to stress corrosion resulting from sustained excessive tensile stress due to excessive torque of the nut. The actions specified by this AD are intended to prevent excessive torque of the nut, failure of a beam, and subsequent loss of control of the helicopter during takeoff or landing.
AD 2002-11-09 · published Jun 11, 2002, effective Jul 16, 2002
Bell Helicopter Textron Canada Model 407 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters that requires visually inspecting the forward hanger bearing bracket (bracket) for a crack. This amendment is prompted by reports of cracks in the bracket. The actions specified by this AD are intended to detect a crack in the bracket, to prevent loss of tail rotor drive or control and subsequent loss of control of the helicopter.
AD 2002-12-02 · published Jun 12, 2002, effective Jun 27, 2002
Eurocopter France Model AS332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332L2 helicopters. This action requires visually inspecting the engine compartment fire extinguisher bottle (bottle) for correct placement and installation of the percussion heads and attachment cartridges and if, incorrectly installed, making the necessary corrections. This action also requires marking the bottle's indicating label with "Amendment A" after making the necessary corrections. This amendment is prompted by the discovery that some of the spare bottles have interchanged percussion heads. The actions specified in this AD are intended to prevent release of the fire- extinguishing agent into the wrong engine compartment, failure to extinguish a fire, and subsequent loss of control of the helicopter.
AD 2002-12-03 · published Jun 12, 2002, effective Jun 27, 2002
Eurocopter France Model AS332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332L2 helicopters. This action requires removing the main rotor shaft non-rotating scissors (non- rotating scissors) from the swashplate balljoint and inspecting for friction or play in the hinges between the two links of the non- rotating scissors, or between the non-rotating scissors link and the flared housing, and replacing the non-rotating scissors, if necessary. This amendment is prompted by the discovery of in-service damage to main rotor shaft non-rotating scissors attachment hinges. The actions specified in this AD are intended to prevent friction on non-rotating scissors, failure of the swashplate, loss of main rotor pitch control, and subsequent loss of control of the helicopter.
AD 2002-12-14 · published Jun 21, 2002, effective Jul 8, 2002
Eurocopter France Model SA330F, G, J, and AS332C, L, and L1 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for specified Eurocopter France (ECF) model helicopters that currently requires inserting statements into the Limitations section of the Rotorcraft Flight Manual (RFM) prohibiting flight under certain atmospheric conditions. This amendment contains the same requirements but corrects, expands, and updates the applicability. This amendment is prompted by an incident in which a Multi-Purpose Air Intake (MPAI) inlet seal deflated after the P2 air system line, which feeds the seal, clogged due to the formation of ice. The actions specified by this AD are intended to prevent clogging of the MPAI seal P2 air system line due to ice formation, which could result in deflation of the MPAI seal, loss of engine power, and subsequent loss of control of the helicopter.
AD 2002-13-05 · published Jun 27, 2002, effective Aug 1, 2002
MD Helicopters, Inc. Model 369D, 369E, 369F, and 369FF Helicopters
This amendment adopts a new airworthiness directive (AD) for specified MD Helicopters, Inc. (MDHI) helicopters with a tailboom modified according to Aerometals Supplemental Type Certificate (STC) SH5055NM or SH4801NM. This AD requires an inspection to identify the part number (P/N) of the bolts that attach the tail rotor gearbox to the tailboom and replacing any bolt of inadequate grip length with an airworthy bolt. This AD also requires determining the number of bolt threads protruding from each nutplate and adding an additional washer if more than four threads protrude. This amendment is prompted by the discovery that bolts of inadequate grip length were specified to attach the tail rotor gearbox to the tailboom. The actions specified by this AD are intended to prevent loss of a tail rotor gearbox due to attaching bolts of inadequate grip length and subsequent loss of control of the helicopter.
AD 2002-13-06 · published Jun 28, 2002, effective Jul 15, 2002
Eurocopter Deutschland GmbH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS- 2, BO-105 CBS-4, and BO-105LS A-1 helicopters. This action requires creating a component log card or equivalent record and determining the calendar age, number of flights, and flight hours time-in-service (TIS) on two part-numbered tension-torsion (T-T) straps; inspecting and replacing certain T-T straps, as necessary; and modifying certain main rotor heads if alternate T-T straps are installed. This action also establishes an additional life limit for these two part-numbered T-T straps. This amendment is prompted by an accident in which a main rotor blade separated from a Eurocopter Model MBB-BK 117 helicopter due to fatigue failure of a T-T strap. The same part-numbered T-T strap is used on Eurocopter Model BO-105 helicopters. That accident indicated a need to establish an additional life limit for certain part-numbered T- T straps. The actions specified in this AD are intended to prevent fatigue failure of a T-T strap, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2002-11-08 · published Jun 6, 2002, effective Jun 21, 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 (RR) RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines with certain part number (P/N) low pressure compressor (LPC) fan blades installed. This action requires initial and repetitive ultrasonic inspection of the fan blade dovetail roots. This amendment is prompted by the loss of an LPC fan blade during takeoff. The actions specified in this AD are intended to prevent multiple LPC fan blade failures due to cracks, which could result in uncontained engine failure and possible damage to the airplane.
AD 2002-12-06 · published Jun 12, 2002, effective Jul 17, 2002
Pratt & Whitney (PW) PW2000 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Pratt & Whitney (PW) PW2000 series turbofan engines. That AD currently requires revisions to the engine manufacturer's Time Limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts that has indicated the need for mandatory inspections. 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 2002-12-08 · published Jun 12, 2002, effective Jul 17, 2002
Honeywell International, Inc. (formerly AlliedSignal Inc., and Textron Lycoming) ALF502 and LF507 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc. (formerly AlliedSignal Inc., and Textron Lycoming) ALF502 and LF507 series turbofan engines. This amendment requires removal from service of certain gas producer turbine (GPT) components prior to reaching new, lower cyclic life limits using drawdown plans and replacing with serviceable parts. This amendment is prompted by continuous analysis of field-returned hardware indicating smaller service life margins than originally expected. The actions specified by this AD are intended to prevent GPT component failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-12-07 · published Jun 18, 2002, effective Jul 3, 2002
Textron Lycoming Reciprocating Engines
This amendment supersedes emergency airworthiness directive (AD) 2000-18-53 that was sent previously to all known U.S. owners and operators of certain Textron Lycoming reciprocating engines. That action required before further flight after receipt of that emergency AD, replacement of the oil filter converter plate gasket or the converter plate kit. That action also required, within 10 hours time- in-service (TIS) or within 3 days after the effective date of that emergency AD, inspection of the oil filter base for signs of oil leakage and evidence of gasket extrusion. That action also required replacement of the converter plate gasket at intervals not to exceed 50 hours TIS since the last replacement of the gasket. This amendment requires the same replacements and inspection, and introduces the installation of an improved design gasket or converter plate kit as terminating action for the repetitive gasket replacements. The actions specified in this AD are intended to prevent complete loss of engine oil and subsequent seizing of the engine and possibility of fire, caused by oil leakage between the converter plate and accessory housing.
AD 2002-12-09 · published Jun 18, 2002, effective Jul 3, 2002
Honeywell International Inc. (Formerly AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-11U, -12B, -12JR, -12UA, -12UAR, and -12UHR Series 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) TPE331-11U, -12B, -12JR, - 12UA, -12UAR, and -12UHR series turboprop engines. This action requires repetitive Spectrometric Oil Analysis Program (SOAP) sampling, SOAP trend assessment, and inspections and replacement of certain gearbox components. This amendment is prompted by reports of spur gearshaft (bull gear) rim separations and high-speed pinion (HSP) assembly failures. The actions specified in this AD are intended to prevent bull gear rim separations and HSP assembly failures from abnormal gear wear, which could result in uncontained gearbox fragmentation, in-flight shutdowns, and engine rotor overspeed events.
AD 2002-12-15 · published Jun 26, 2002, effective Jul 31, 2002
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney PW4000 series turbofan engines. That AD requires operators to perform initial and repetitive inspections for cracking of high pressure compressor (HPC) front drum rotors based on cycle usage. That AD also requires the removal from service of any cracked HPC front drum rotors. This amendment clarifies inspection requirements for cracking of HPC front drum rotors that have fewer than 1,000 cycles-since-new (CSN). This amendment is prompted by comments from operators seeking more clarity about the inspection requirements of paragraph (a)(1) of that AD. The actions specified by this AD are intended to prevent HPC drum rotor failure from cracks that could result in an uncontained engine failure and damage to the airplane.
AD 2002-13-03 · published Jun 27, 2002, effective Aug 1, 2002
CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -5C, and -7B Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain CFM International (CFMI) CFM56 series turbofan engines. That AD currently requires revisions to the Airworthiness Limitations Section of applicable Engine Shop Manuals (ESM's) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment requires revisions to the Airworthiness Limitations Section of the applicable manufacturer's manuals and air carrier's approved continuous airworthiness maintenance program to incorporate additional inspections of selected critical life-limited parts at each piece-part exposure. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating parts. 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 99-27-16 R1 · published Jun 28, 2002, effective Aug 2, 2002
CFE Company Engines
This amendment revises an existing airworthiness directive (AD), that is applicable to CFE Company Model CFE738-1-1B turbofan engines. That AD currently requires a one-time visual inspection of stage 2 high pressure turbine (HPT) aft cooling plates for nicks, dents, raised metal, and scratches, and if necessary, repair of the cooling plates or replacement with serviceable parts. This amendment reduces the number of stage 2 HPT aft cooling plates affected by AD 99-27-16, and identifies the applicable engines by engine serial numbers (SN's). This amendment is prompted by an updated alert service bulletin (ASB) that reduces the number of stage 2 HPT aft cooling plates affected by AD 99-27-16 and identifies the applicable engines by engine SN's. The actions specified by this AD are intended to prevent stage 2 HPT aft cooling plate failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-13-04 · published Jun 27, 2002, effective Jul 12, 2002
Teledyne Continental Motors
This amendment supersedes emergency airworthiness directive (AD) 2000-11-51 that was sent previously to all known U.S. owners and operators of Teledyne Continental Motors (TCM) O-300, IO-360, TSIO-360, and LTSIO-520-AE series reciprocating engines. That action required within 10 flight hours after receipt of that AD, replacement of certain magnetos if they fall within the specified serial number range, inspection of the removed magneto to verify that the stop pin is still in place, and, if the stop pin is not in place, inspection of the engine gear train. This amendment requires the same replacement and inspections and adds TCM C-125 and C145 series reciprocating engines to the applicability, which were inadvertently omitted from the emergency AD. This amendment is prompted by reports of engine failures on certain TCM reciprocating engines. The actions specified by this AD are intended to prevent engine failure and loss of control of the airplane due to migration of the magneto impulse coupling stop pin out of the magneto frame and into the gear train of the engine.
