37 Airworthiness Directives: 25 airplane, 3 rotorcraft, 2 engine, 1 propeller, 4 appliance, 2 glider.
AD 2002-13-02 · published Jul 1, 2002, effective Jul 9, 2002
Air Tractor, Inc. Models AT-300, AT-301, AT-302, AT-400, and AT-400A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Air Tractor, Inc. (Air Tractor) Models AT-300, AT-301, AT-302, and AT-400A airplanes that have aluminum spar caps; certain Air Tractor Models AT-400 airplanes that have aluminum spar caps; and all Models AT-300 and AT-301 airplanes that have aluminum spar caps and are or have been converted to turbine power. This AD requires you to inspect (one-time) the wing centerline splice joint for cracks and, if any crack is found, replace the affected wing spar lower cap. This AD also requires you to report the results of the inspection to the Federal Aviation Administration (FAA) and replace the wing spar lower caps after a certain amount of usage. This AD is the result of an incident on one of the affected airplanes where the wing separated from the airplane. Preliminary reports indicate that fatigue caused the lower aluminum spar cap to fail across the \3/8\-inch bolt hole (6.5 inches outboard of the fuselage centerline in the centersplice connection). The actions specified by this AD are intended to detect and correct cracks in the wing centerline splice joint. If not detected and corrected, these cracks could eventually result in the wing separating from the airplane during flight.
AD 2002-13-08 · published Jul 1, 2002, effective Aug 13, 2002
de Havilland Inc. Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain de Havilland Inc. (de Havilland) Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. This AD requires you to modify the elevator tip rib on each elevator; repetitively inspect underneath the mass balance weights at each elevator tip rib for corrosion; and either remove the corrosion or replace a corroded elevator tip rib depending on the corrosion damage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. The actions specified by this AD are intended to detect and correct corrosion in the mass balance weights at the elevator tip ribs, which could result in loss of balance weight during flight and the elevator control surface separating from the airplane.
AD 2002-13-10 · published Jul 8, 2002, effective Aug 12, 2002
McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and KDC-10), -40, and -40F Airplanes; Model MD-10-10F and -30F Airplanes; and Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and KDC-10), -40, and -40F airplanes; Model MD- 10-10F and -30F airplanes; and Model MD-11 and -11F airplanes. This AD requires repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/ transfer pump connectors; and corrective actions, if necessary. This action is necessary to prevent arcing of connectors in the fuel boost/ transfer pump circuit, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
AD 2002-13-12 · published Jul 9, 2002, effective Aug 13, 2002
McDonnell Douglas Model DC-9-10, -30, -30F, and -40 Series Airplanes, and Model C-9 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and - 40 series airplanes and Model C-9 airplanes, that currently requires an inspection to detect chafing of the wiring of the attendants' work light of the aft cabin, and repair of chafed wiring. That AD also requires modification and reidentification of the attendants' work light assemblies of the aft cabin. This amendment revises the applicability of the existing AD. The actions specified by this AD are intended to prevent chafing of the ground wire against the positive contact of the lamp of the attendants' work light of the aft cabin, and consequent arcing or arcing damage to the wiring of the attendants' work light and transformer of the aft cabin. Such arcing or arcing damage could result in short circuits and consequent smoke and fire in the aft cabin area. The actions of this AD are intended to address the identified unsafe condition.
AD 2002-14-02 · published Jul 12, 2002, effective Jul 29, 2002
Boeing Model 767-300 Series Airplanes Equipped With Rolls Royce RB211-524H Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-300 series airplanes equipped with Rolls Royce RB211-524H series engines. This action requires re- routing a certain wire bundle containing control wiring for the thrust reverser actuation system. This action is necessary to ensure that control wiring for the thrust reverser actuation system is adequately separated. Inadequately separated wiring could allow a single failure to result in uncommanded deployment of a thrust reverser and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-14-16 · published Jul 12, 2002, effective Aug 16, 2002
McDonnell Douglas Model 717-200 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model 717-200 airplanes, that requires repetitive inspections for cracking of the spoiler hold-down actuator supports located on the left and right wing rear spars; adjustment of the spoiler hold-down actuators; and replacement of cracked spoiler hold-down actuator supports with new, improved supports. This AD also requires replacement of all spoiler hold-down actuator supports with new, improved supports, which terminates the repetitive inspections. The actions specified by this AD are intended to detect and correct as well as to prevent cracks in the spoiler hold- down actuator supports, which could lead to reduced spoiler hold-down capability, resulting in loss of the back-up protection of the spoiler float hold-down and unavailability of monitoring for an uncommanded spoiler movement.
AD 2002-14-20 · published Jul 16, 2002, effective Jul 31, 2002
Boeing Model 737-600, -700, -800, and -900 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -800, and -900 series airplanes. This action requires measuring the electrical voltage at the circuit breaker for a certain pitot heater to determine if the pitot heater is connected to the correct power supply bus, and performing corrective action, if necessary. This action is necessary to prevent ice from blocking the pitot tube that provides airspeed data to the captain. Such ice blockage could lead to the flightcrew receiving incorrect airspeed data, which could result in loss of control of the airplane if the flightcrew fails to recognize that the data are incorrect. This action is intended to address the identified unsafe condition.
AD 2002-14-21 · published Jul 17, 2002, effective Aug 21, 2002
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, and -800 series airplanes, that currently requires repetitive inspections to detect discrepancies of the quick-disconnect coupling on the fuel hose located at the fan case firewall; corrective action, if necessary; and installation of a clamp shell on the coupling to prevent separation of the coupling halves. This amendment limits the applicability of the existing requirements, clarifies certain existing requirements, and requires removal of the clamp shell installed previously and replacement of the existing quick-disconnect fuel supply hose, coupling, and strut fitting with new, fixed-B-nut-type parts. Such replacement ends the requirement for repetitive inspections. The actions specified by this AD are intended to prevent major fuel leakage due to excessive wear of the quick-disconnect coupling on the fuel hose, fire in the engine nacelle, and consequent loss of thrust from the affected engine, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-14-03 · published Jul 18, 2002, effective Aug 2, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 and 11F airplanes. This action requires a one-time inspection to detect loose preload-indicating (PLI) washers or cracked or corroded nuts of the lower bolts of the inboard flap outboard hinge, and replacement with new parts if necessary. This action is necessary to detect and correct loose PLI washers or cracked or corroded nuts of the lower bolts of the inboard flap outboard hinge, which could result in separation of the inboard flap outboard hinge from the wing structure and consequent reduced controllability of the airplane.
AD 2002-14-04 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires performing an inspection of the wiring of the Firex bottle discharge cartridge of the No. 2 engine at station Y=2163.00 bulkhead for chafing on adjacent structure and damaged wiring; repairing damaged wires; and repositioning wires, if necessary. This action is necessary to prevent chafing and possible damage to the wiring of the Firex bottle discharge cartridge of the No. 2 engine, which could result in improper distribution of the fire extinguishing agent within the No. 2 engine in the event of a fire. This action is intended to address the identified unsafe condition.
AD 2002-14-05 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center to detect damage; and corrective actions, if necessary. This amendment requires replacement of the electrical wiring of the galley in the electrical power center in bays 1, 2, and 3 with larger gage cable assemblies, which terminates the repetitive inspections. This amendment also expands the applicability of the existing AD to include two additional airplanes. This action is necessary to prevent damage to the wire assembly terminal lugs and overheating of the power feeder cables on the No. 3 and 4 GLCU, which could result in smoke and fire in the center accessory compartment. This action is intended to address the identified unsafe condition.
AD 2002-14-06 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires installation of protective sleeving on the right emergency alternating current (AC) wire assembly of the overhead switch panel. This action is necessary to ensure that protective sleeving is installed on the right emergency AC wire assembly of the overhead switch panel. Lack of such sleeving could result in loss of redundant electrical power during certain cockpit overhead wiring faults. This action is intended to address the identified unsafe condition.
AD 2002-14-07 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires relocation of the mod block tracks on the flight compartment floor beams in the avionics compartment beneath the Captain's and First Officer's seats. This action is necessary to prevent chafing and compression of electrical wiring at the upper track mod blocks on the flight compartment floor beams in the avionics compartment beneath the Captain's and First Officer's seats, which could result in electrical arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2002-14-08 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an inspection to detect discrepancies of the wire bundles in the avionics compartment in the vicinity of the pedestal extension area of the First Officer's seat; and corrective actions, if necessary. This action is necessary to prevent chafing of wiring in the avionics compartment, which could result in electrical arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2002-14-09 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and MD-11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that currently requires replacement of the existing terminal strips and supports above the main cabin area; and installation of spacers between terminal strips and mounting brackets in the avionics compartment; as applicable. This amendment requires replacing the applicable terminal strips in the avionics compartment with new terminal strips. This amendment also requires performing an inspection to detect arcing damage of the surrounding structure of the terminal strips and electrical cables in the avionics compartment, and repairing or replacing any damaged component with a new component. This amendment is prompted by reports of arcing between the power feeder cables and support brackets of the terminal strips on airplanes previously modified per the existing AD. The actions specified by this AD are intended to prevent electrical arcing caused by power feeder cable terminal lugs grounding against terminal strip support brackets, which could result in smoke and fire in the main cabin or avionics compartment.
AD 2002-14-10 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes Equipped With United Technologies Pratt & Whitney Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires replacing the wire harness support bracket of the integrated drive generator (IDG) of the forward engine mounts with a new support bracket, and modifying the angle of the bracket near the oil filter. The actions specified by this AD are intended to prevent arcing of the IDG wire harness, which could result in smoke and/or fire in the area of the forward engine mount bolt retainer and/or fire detector responder. This action is intended to address the identified unsafe condition.
AD 2002-14-11 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires replacing the ground support bracket(s); and rerouting the ground cables of the galley external power and main external power, or ground cables of the main external power; as applicable. This amendment requires a general visual inspection of the ground cables of the main external power and galley external power for excessive length, as applicable; and corrective actions, if necessary. This amendment is prompted by the FAA's determination that currently required actions may not adequately address the identified unsafe condition. The actions specified by this AD are intended to prevent arcing and heat damage to the attachment points of the main external and galley power receptacle ground wire, insulation blankets outboard and aft of the receptacle area, and adjacent power cables, which could result in smoke and fire in the forward cargo compartment.
AD 2002-14-12 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an inspection of the wiring in the fuel control panel of the wings for chafing damage and for proper routing of the wiring; and corrective action(s), if necessary. This action is necessary to prevent chafing of the wiring in a cutout area in the wing fuel control panel due to improperly routed wiring, which could result in electrical arcing in an abnormal fuel vapor zone and consequent possible ignition of the fuel vapor. This action is intended to address the identified unsafe condition.
AD 2002-14-13 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires installing a clipnut and bracket and revising the routing of the wire assembly of the forward lower cargo door. This action is necessary to prevent failure of the wire assemblies and damage of a ballast of a light fixture, and consequent smoke and/or fire in the forward cargo compartment. This action is intended to address the identified unsafe condition.
AD 2002-14-14 · published Jul 19, 2002, effective Aug 23, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes Equipped With General Electric Tail Engine Buildup Units (EBU)
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes that requires installation of a new support bracket with a clamp and screw to support the wire harness of the integrated drive generator (IDG). This action is necessary to prevent chafing and arcing of the wire harness of the IDG due to inadequate support, which could result in smoke and/or fire in the area of the forward engine mount. This action is intended to address the identified unsafe condition.
AD 2002-14-15 · published Jul 19, 2002, effective Aug 5, 2002
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires an inspection of the powered drive unit power wires within three feet of each affected powered drive unit termination for mechanical damage; and repair, if necessary. That AD also currently requires revising the wire harnesses; splicing any additional length wire; routing and installing parts; and replacing the floor panels with new and retained floor panels. This amendment revises the existing requirements by improving the routing of the wire harnesses. This amendment is prompted by the FAA's determination that the currently required modification does not adequately preclude the identified unsafe condition. The actions specified in this AD are intended to ensure that the powered roller pans are positioned properly. Improperly positioned powered roller pans could pierce a powered roller wire harness and cause sparking that could ignite adjacent insulation material, which could result in smoke and fire in the center cargo compartment of the airplane.
AD 2002-14-24 · published Jul 22, 2002, effective Aug 26, 2002
Cessna Model 650 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 650 airplanes, that requires a one- time inspection of the side brace mechanism assemblies of the left and right main landing gears (MLG) to detect any incorrect part number, and corrective actions if necessary. This action is necessary to prevent inadvertent disengagement of the locking mechanism of the side brace mechanism assembly, which could lead to collapse of the respective MLG, and result in a gear-up landing and possible injury to passengers and crew. This action is intended to address the identified unsafe condition.
AD 2002-14-28 · published Jul 22, 2002, effective Sep 6, 2002
de Havilland Inc. Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain de Havilland Inc. (de Havilland) Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. This AD establishes a life limit for the front fuselage struts and requires you to repetitively replace the front fuselage struts every 15 years or repetitively inspect the struts for corrosion or fatigue damage and replace when the damage exceeds a certain level. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. The actions specified by this AD are intended to prevent structural failure of the front fuselage caused by corrosion or fatigue damage to the struts that develops over time, which could result in reduced or loss of control of the airplane.
AD 2002-14-25 · published Jul 24, 2002, effective Aug 8, 2002
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment supersedes an existing airworthiness directives (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that currently 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 amendment expands the applicability in the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. The actions specified in this AD are intended 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 would result in high pitch control forces and consequent reduced controllability of the airplane. This action is needed to address the identified unsafe condition.
AD 2002-14-27 · published Jul 25, 2002, effective Aug 29, 2002
Fokker Model F.28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) that prohibits takeoff in certain icing conditions unless either a tactile inspection is performed or specific takeoff procedures are followed. This amendment requires adding a requirement, for certain airplanes, for modification of the wing leading edge ice protection system to include on-ground wing ice protection, and a new revision to the AFM. This amendment is prompted by the development of a modification that introduces a wing anti-icing system that will operate on the ground as well as in flight. The actions specified by this AD are intended to prevent takeoff with snow, ice, or frost on the critical surfaces of the airplane, which could result in reduced controllability of the airplane.
AD 2002-13-11 · published Jul 9, 2002, effective Aug 13, 2002
Eurocopter France Model EC120B Helicopters
This amendment adopts a new airworthiness directive (AD) for specified Eurocopter France (ECF) model helicopters that requires installing front and side covers to protect the yaw control. This amendment is prompted by a report of a mobile phone falling between the windshield canopy (canopy) and the cabin floor jamming the yaw control pedal. The actions specified by this AD are intended to prevent an object from sliding between the canopy and the cabin floor, loss of yaw control, and subsequent loss of control of the helicopter.
AD 2002-14-01 · published Jul 10, 2002, effective Aug 14, 2002
Eurocopter France Model AS332L and AS332L1 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters that requires adding a supplement to the Limitations section of the applicable Rotorcraft Flight Manual (RFM) for helicopters with "SEFA" skis installed. This amendment is prompted by the need to limit the taxi and Vne speed of those helicopters with skis. The actions specified by this AD are intended to prevent structural failure of a ski and subsequent loss of control of the helicopter.
AD 2002-14-17 · published Jul 11, 2002, effective Jul 26, 2002
Eurocopter Deutschland GmbH Model EC135 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model EC135 helicopters, that currently requires initial and repetitive visual inspections and a one-time dye-penetrant inspection of a certain main rotor hub shaft (shaft) for cracks, and replacement of any cracked shafts. This amendment requires the same actions as the existing AD, but corrects the shaft part number (P/N) in the current AD, includes additional P/N's, increases the area of inspection from a 40mm area to a 50mm area of the shaft, and provides an option for using either a visual or dye-penetrant inspection to satisfy the repetitive inspection requirement. This amendment is prompted by the need to correct the shaft part number and increase the area of inspection, as well as add additional affected shaft P/N's. The actions specified by this AD are intended to detect fatigue cracks in the shaft that could lead to shaft failure and subsequent loss of control of the helicopter.
AD 2002-13-09 · published Jul 3, 2002, effective Dec 30, 2002
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT8D-200 series turbofan engines, that currently requires revisions to the Time Limits Section (TLS) of the JT8D-200 Turbofan Engine Manual to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD adds additional critical life-limited parts for enhanced inspection. This AD is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this AD are intended to prevent the failure of critical, life-limited, rotating engine parts, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-14-26 · published Jul 22, 2002, effective Aug 6, 2002
Turbomeca S.A. Arriel Models 1A, 1A1, 1B, 1D, and 1D1 Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arriel models 1A, 1A1, 1B, 1D, and 1D1 turboshaft engines. This action requires installation of containment shield rings around the free turbine blade area, and installation of a double support around the gearbox free turbine bearing housing. This amendment is prompted by two reports of the cantilevered axis of the free turbine moving from its design position and inducing blade trajectories outside the current design free turbine containment area. This condition can lead to uncontainment of the free turbine during an overspeed event. The actions specified in this AD are intended to prevent uncontainment of the free turbine during an overspeed event, resulting in damage to the helicopter.
AD 2002-15-03 · published Jul 25, 2002, effective Aug 9, 2002
Hamilton Sundstrand Corporation Model 568F-1 Propellers.
This amendment supersedes an emergency airworthiness directive (AD) 2002-05-51 that was sent previously to all known U.S. owners and operators of Hamilton Sundstrand Corporation (formerly Hamilton Standard Division) model 568F-1 propellers. That AD requires replacement of propeller blades, part numbers (P/N's) R815505-2 and R815505-3, that have a serial number (SN) of FR1698 or lower, with serviceable propeller blades, a prohibition against installing any propeller blades, P/N's R815505-2 and R815505-3, that have a SN of FR428 or lower, that were previously installed on an ATR-42-400 or an ATR-72 airplane, on any other airplane, and initial and repetitive ultrasonic shear wave inspection of the blade tulip on installed blades P/N's R815505-2 and R815505-3, that have a SN of FR1698 or lower. This amendment requires those same actions, and also requires replacing certain SN blades before further flight. This amendment also requires initial and repetitive ultrasonic shear wave inspections of the blade tulip on installed blades, P/N's R815505-2 and R815505-3, that have a SN of FR1698 or lower until they are replaced. This amendment is prompted by a report of a blade failure that resulted in damage to the airplane. The actions specified in this AD are intended to prevent blade failure due to corrosion-induced fatigue, which could result in blade separation and possible loss of airplane control.
AD 2002-13-07 · published Jul 1, 2002, effective Aug 9, 2002
Honeywell, Inc. Part Number HG1075AB05 and HG1075GB05 Inertial Reference Units
This amendment adopts a new airworthiness directive (AD) that applies to certain Honeywell, Inc. part number (P/N) HG1075AB05 and HG1075GB05 inertial reference units (IRU) that are installed on aircraft. This AD requires you to inspect the affected IRU's for proper function and remove the IRU either immediately or at a certain time depending on the result of the inspection. This AD is the result of a report that these IRU's may not function when using backup battery power in certain installations. The actions specified by this AD are intended to ensure the correct transition of the IRU to backup battery power upon the loss of primary power. Failure of an IRU to transition to backup battery power could result in loss of attitude, heading, and position reference and lead to the pilot making flight decisions that put the aircraft in unsafe flight conditions.
AD 2002-14-19 · published Jul 15, 2002, effective Aug 23, 2002
Rockwell Collins, Inc. ADC-85, ADC-85A, ADC-850D, and ADC-850F Air Data Computers
This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins, Inc. (Rockwell Collins) ADC-85, ADC-85A, ADC-850D, and ADC-850F air data computers that are installed on airplanes. This AD requires you to replace any affected air data computer (ADC) with one that has a reprogrammed and tested central processing unit (CPU) circuit card and circuit card assembly. This AD is the result of a flight test that showed that these ADC's could display an unwarranted ADC flag in response to the airplane's "Normal/ Alternate Air" static source selection capability. The actions specified by this AD are intended to prevent an unwarranted display of the ADC flag when switching static air sources. This could cause the flight crew to react to this incorrect flight information and possibly result in an unsafe operating condition.
AD 2002-14-23 · published Jul 18, 2002, effective Aug 2, 2002
Empresa Brasileira de Aeronautica S.A.
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires a one-time inspection of the clutch assembly of the horizontal stabilizer actuator (HSA) to verify that at least one locking tab on the key washer is bent into the locking groove of the clutch nut, and follow-on actions. This action is necessary to prevent a loose or disengaged clutch nut on the HSA clutch assembly, which could result in loss of pitch trim and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-15-02 · published Jul 24, 2002, effective Aug 28, 2002
Hamilton Sundstrand Power Systems (Formerly Sundstrand Power Systems, Turbomach, and Solar) T-62T Series Auxiliary Power Units
This amendment adopts a new airworthiness directive (AD), that is applicable to Hamilton Sundstrand Power Systems (formerly Sundstrand Power Systems, Turbomach, and Solar) T-62T series auxiliary power units (APU's) with compressor wheel part number (P/N) 100636-1 installed. This amendment requires the replacement of compressor wheels P/N 100636-1. This amendment is prompted by a manufacturer's stress analysis that indicates stress levels high enough to initiate and drive crack growth in these compressor wheels. The actions specified by this AD are intended to mandate the replacement of the affected compressor wheels, which if not replaced, could result in uncontained compressor wheel failure and damage to the airplane.
AD 2002-14-18 · published Jul 12, 2002, effective Aug 23, 2002
Glaser-Dirks Flugzeugbau GmbH Models DG-400 and DG-800A Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (DG Flugzeugbau) Models DG-400 and DG-800A sailplanes. This AD requires you to inspect the rear plate of the propeller mount for marks and/or cracks and replace if necessary. This AD also requires you to inspect the mounting blocks for cracks and replace if necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct cracks in the propeller mount plate and mounting blocks, which could result in reduced structural integrity of the propeller mounting structure. This could lead to a hazardous flight condition or loss of control of the sailplane.
AD 2002-15-01 · published Jul 22, 2002, effective Sep 3, 2002
Diamond Aircraft Industries GmbH Models H-36 “Dimona”, HK 36 R “Super Dimona”, HK 36 TC, HK 36 TS, HK 36 TTC, HK 36 TTC-ECO, HK 36 TTC-ECO (Restricted Category), and HK 36 TTS Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Diamond Aircraft Industries GmbH (Diamond) Models H-36 "Dimona", HK 36 R "Super Dimona", HK 36 TC, HK 36 TS, HK 36 TTC, HK 36 TTC-ECO, HK 36 TTC-ECO (Restricted Category), and HK 36 TTS sailplanes. This AD requires you to inspect the long aileron push rods in both wings for damage and modify the push rods. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Austria. The actions specified by this AD are intended to detect and correct damage in the long aileron push control rods, which could result in failure of the aileron push rods and decreased control. Such failure could lead to aeroelastic flutter.
