55 Airworthiness Directives: 29 airplane, 11 rotorcraft, 11 engine, 1 appliance, 3 glider.
AD 99-07-13 · published Apr 1, 1999, effective May 6, 1999
Construcciones Aeronauticas, S.A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes. This amendment requires a one-time visual inspection to detect relative movement or deformation of the joint areas of the rear attaching supports and lower skin of the left and right outer flaps; repetitive borescopic inspections to detect cracking of the spar and of the rear internal support fittings of the outer flaps; and corrective actions, if necessary. This amendment also provides for optional terminating action for the 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 fatigue cracking of the rear internal support fittings of the outer flap structure, which could result in failure of the outer flaps, and consequent reduced controllability of the airplane.
AD 99-07-14 · published Apr 1, 1999, effective May 6, 1999
McDonnell Douglas Model DC-9-80 Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes, and Model MD-88 airplanes, that requires a one-time inspection to detect corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer; and corrective actions, if necessary. This amendment is prompted by reports of corrosion of the lug bores and the surface of the hinge plates of the vertical-to- horizontal stabilizer, apparently due to the improper brushing of cadmium on the hinge plates during manufacture. The actions specified by this AD are intended to detect and correct corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer, which could result in reduced structural integrity of the airplane.
AD 99-08-03 · published Apr 2, 1999, effective Apr 19, 1999
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-600, -700, and -800 series airplanes. This action requires an inspection of the power distribution panels (PDP) to verify proper installation of the power feeder terminals and associated hardware, and corrective actions, if necessary. This action also requires repetitive torque checks of the terminal attachment screws. This amendment is prompted by reports indicating the loss of electrical power from the engine-driven generators or the auxiliary power unit due to overheating, melting, and subsequent failure of the power feeder terminals. The actions specified in this AD are intended to prevent such conditions, which could result in increased risk of fire and the loss of electrical power from the associated alternating current power source.
AD 99-07-20 · published Apr 6, 1999, effective May 17, 1999
Avions Pierre Robin Model R2160 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R2160 airplanes. This AD requires repetitively inspecting the vertical stabilizer spar in the area of the lower fitting of the rudder for cracks, loose rivets, or spar web distortion; and modifying the vertical stabilizer spar either immediately or at a certain time period depending on whether discrepancies are found during the inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect defects (cracks, loose rivets, or spar web distortion) in the vertical stabilizer spar, which could result in structural failure of the vertical stabilizer with possible reduced or loss of control of the airplane.
AD 99-08-02 · published Apr 6, 1999, effective May 11, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes. The amendment requires a one-time inspection to detect discrepancies of the center fuel tank wiring and components, and corrective action, if necessary; and a one-time electrical bonding test of the center fuel tank components, and rework, if necessary. For certain airplanes, the amendment requires a one-time insulation resistance test and a one-time inspection to detect discrepancies of the wiring and components of the fuel quantity indication system (FQIS), and corrective actions, if necessary; replacement of certain FQIS probes with certain newer probes; a system adjustment and system operational test; and modification (installation of a flame arrestor) of the inlet line of the scavenge pump of the center fuel tank. This amendment is prompted by design review and testing results obtained in support of an accident investigation. The actions specified by this AD are intended to prevent ignition sources and consequent fire/explosion in the center fuel tank.
AD 99-08-01 · published Apr 7, 1999, effective May 12, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive detailed visual inspections for corrosion, and repetitive high frequency eddy current (HFEC) inspections for cracks, of the upper link assembly on the number 2 and number 3 engine struts, and corrective actions, if necessary. This amendment is prompted by reports of corrosion and cracks located at the four fasteners that attach to the aft end to the upper link assembly on the number 2 and number 3 engine struts. The actions specified by this AD are intended to prevent failure of the upper link due to cracking or corrosion, subsequent damage to other strut support structure, and in-flight separation of an engine from the airplane.
AD 99-08-04 · published Apr 7, 1999, effective May 12, 1999
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 modification of the flight compartment door; repetitive inspections for wear of the flight compartment door hinges following modification; and repair or replacement of the hinges with new hinges, if necessary. This amendment is prompted by a report that the door lock mechanism of the flight compartment door jammed and could not be opened using the alternate release mechanism. The actions specified by this AD are intended to prevent failure of the alternate release mechanism of the flight compartment door, which could delay or impede the evacuation of the flightcrew during an emergency. Such failure also could result in the flightcrew not being able to assist passengers in the event of an emergency.
AD 99-08-05 · published Apr 7, 1999, effective May 12, 1999
McDonnell Douglas Model DC-9 and C-9 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and C-9 (military) series airplanes. This amendment requires repetitive inspections to detect fatigue cracking of the fuselage frames and longerons 16R and 17R above the forward lower cargo door; repair, if necessary; and modification of the fuselage frames and longerons, if necessary, and follow-on repetitive inspections to detect fatigue cracking of the skin adjacent to the modification. This amendment is prompted by numerous instances of fatigue cracking of the fuselage frames and longerons. The actions specified by this AD are intended to prevent fatigue cracking of the fuselage frames and longerons 16R and 17R, which could result in reduced structural integrity of the airplane.
AD 99-08-08 · published Apr 12, 1999, effective May 17, 1999
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive lubrication of the engine control push-pull cables, and installation of heating tubes on the control cables in the cockpit area and in the left-hand and right-hand engine balconies, which terminates the repetitive lubrication requirement. 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 ice from building up on the engine control push- pull cables, which could result in friction or jamming of the engine controls, and consequent reduced controllability of the airplane.
AD 99-08-09 · published Apr 12, 1999, effective May 17, 1999
Aerospatiale Model ATR42 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and -320 series airplanes, that currently requires a one-time inspection of the main landing gear (MLG) actuator fitting bolt holes for correct alignment, and rework of the fitting surface and bolt replacement, if necessary. This amendment requires replacement of the MLG actuator fitting bolts with new, improved bolts. This amendment also revises the applicability of the existing AD. 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 failure of the MLG actuator fitting bolts, which could result in the inability to retract the MLG and attain an adequate climb gradient.
AD 99-08-10 · published Apr 12, 1999, effective May 17, 1999
Boeing Model 747-100, -200, -300, -SP, and -400F Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-100, -200, -300, -SP, and -400F series airplanes. Among other things, this amendment requires repetitive leak tests of the lavatory drain system and repair, if necessary; installation of a cap or flush/fill line ball valve on the flush/fill line; periodic seal changes; and replacement of any ``donut'' type valves installed in the waste drain system. This amendment is prompted by continuing reports of damage to airframes and damage to property on the ground, caused by ``blue ice'' that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent damage to airframes and property on the ground that is associated with the problems of ``blue ice'' that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage.
AD 99-08-19 · published Apr 12, 1999, effective Apr 27, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires replacement of the auxiliary power unit (APU) fuel boost pump with a serviceable pump. This amendment is prompted by findings from a design review and analysis, conducted as part of an accident investigation, of APU fuel boost pumps installed on certain Boeing Model 747 series airplanes. The actions specified in this AD are intended to prevent potential failures within the electrical motor assembly of the APU fuel boost pump (which could result in leakage of fuel from the electrical connector) or electrical arcing across the connector pins of the pump, and consequent fuel fire.
AD 99-08-20 · published Apr 14, 1999, effective May 19, 1999
Lockheed Model L-1011-385 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires a one-time inspection to detect cracking of the bulkhead at fuselage station (FS) 1363 at butt line 42.5, and repair or additional inspections, if necessary. This amendment adds repetitive inspections to detect cracking of the bulkhead web and bulkhead cap (frame cap) at FS 1363, and repair, if necessary. This amendment is prompted by reports that additional, more extensive, fatigue cracking was found in the bulkhead web and cap. The actions specified by this AD are intended to detect and correct cracking of the bulkhead web and cap, which could result in reduced structural integrity of the fuselage.
AD 97-15-13 R2 · published Apr 16, 1999, effective May 28, 1999
Raytheon Aircraft Company Beech Models 1900, 1900C, and 1900D Airplanes
This amendment revises Airworthiness Directive (AD) 97-15-13 R1, which currently requires installing lubrication fittings in the airstair door handle and latch housing mechanisms on certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. Since issuance of AD 97-15-13 R1, Raytheon has revised the applicable service information to correct the reference to the number of parts each owner/operator of the affected airplanes should order and to change an incorrect reference to a maintenance manual. This AD retains the actions of AD 97-15-13 R1, and incorporates the revised service bulletin into the AD. The actions specified by this AD are intended to continue to prevent moisture from accumulating and freezing in the airstair door handle and latch housing, which could result in the door freezing shut and passengers not being able to evacuate the airplane in an emergency situation.
AD 99-08-22 · published Apr 16, 1999, effective May 21, 1999
McDonnell Douglas Model DC-10 Series Airplanes and KC-10 (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10 (military) airplanes, that requires repetitive inspections to detect fatigue cracking of the rear spar cap of the horizontal stabilizer; and repair, if necessary. The amendment also would require a preventive modification of the rear spar cap of the horizontal stabilizer, which would constitute terminating action for the repetitive inspections. This amendment is prompted by reports of fatigue cracking of the rear spar cap of the horizontal stabilizer. The actions specified by this amendment are intended to prevent fatigue cracking of the rear spar cap of the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer, and consequent reduced controllability of the airplane.
AD 99-09-01 · published Apr 22, 1999, effective May 7, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires a visual inspection to verify that the channel flanges of the bracket installations are facing forward and to detect chafing or damage of the wire bundles of the center accessory compartment (CAC), and corrective actions, if necessary. This amendment also requires that operators submit a report of the inspection results to the FAA. This amendment is prompted by an incident in which sparks and smoke came out of the CAC during a functional test due to a wire bundle that had chafed against a support bracket installation, which was installed improperly during production of the airplane. The actions specified in this AD are intended to ensure that such bracket installations are installed properly. Improper installation of the brackets of the CAC could cause chafing of the wire bundles, which could result in sparks, smoke, and possible fire in the CAC.
AD 99-09-02 · published Apr 22, 1999, effective May 7, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires relocating the support bracket and rerouting the electrical wiring in the aft storage compartment drop ceiling structure. This amendment is prompted by an incident in which a burning odor was detected, and the rear galley power repeatedly tripped off line during flight of an in-service airplane, due to the sense wiring of the galley load control unit (GLCU) chafing against the support bracket. The actions specified in this AD are intended to prevent chafing of the sense wire of the GLCU due to the location of the support bracket of the aft drop ceiling, which could result in electrical arcing, smoke, and possible fire in the aft drop ceiling area of the passenger compartments.
AD 99-09-03 · published Apr 22, 1999, effective May 7, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection of the wiring and wire bundles of the aft main avionics rack (MAR) to determine if the wires are damaged, or riding or chafing on structure, clamps, braces, standoffs, or clips, and to detect damaged or out of alignment rubber cushions inserts of the wiring clamps; and corrective actions, if necessary. This amendment is prompted by an incident in which the automatic and manual cargo door test in the cockpit was inoperative during dispatch of the airplane, due to the wiring of the MAR chafing against clamps as a result of the wire bundles being installed improperly during production of the airplane. The actions specified in this AD are intended to ensure that the wires that route from the main wire bundles to the MAR and associated brackets, clamps, braces, standoffs, and clips are installed properly. Improper installation of such wiring and structure could cause chafing of the wire/wire bundles, which could result in electrical arcing, smoke, and possible fire in the MAR.
AD 99-09-04 · published Apr 22, 1999, effective May 7, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection to verify correct wire terminations of certain circuit breakers in the cockpit overhead switch panel; and correction of incorrect wire termination. This amendment also requires that operators submit a report of the inspection results to the FAA. This amendment is prompted by incidents in which the wiring of circuit breakers on the overhead switch panel lighting were found to be terminated improperly during production of the airplane, which bypassed the circuit breaker protection. The actions specified in this AD are intended to prevent smoke and possible fire in the overhead switch panel lighting circuitry due to an overload condition, as a result of lack of circuit breaker protection.
AD 99-08-23 · published Apr 23, 1999, effective May 10, 1999
Boeing Model 737-100, -200, -200C, - 300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action requires repetitive inspections to detect cracking in the web of the aft pressure bulkhead at body station 1016 at the aft fastener row attachment to the ``Y'' chord; and corrective actions, if necessary. This amendment is prompted by several reports of fatigue cracking found at that location on Model 737 series airplanes. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage.
AD 99-09-11 · published Apr 23, 1999, effective May 10, 1999
Boeing Model 747 Series Airplanes Equipped With General Electric Model CF6-45 or -50 Series Engines; or Pratt & Whitney Model JT9D-3, -7, or -70 Series Engines; and 747-E4B (Military) Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes and all 747- E4B (military) airplanes. This action requires repetitive inspections to detect cracking or fracture of the steel attachment fittings of the diagonal brace to the nacelle struts; and replacement of the attachment fittings with new steel fittings, if necessary. This amendment is prompted by a report indicating a fractured steel attachment fitting of a diagonal brace to the number 2 nacelle strut; such fracture has been attributed to fatigue cracking. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in failure of a nacelle strut diagonal brace load path and possible separation of the nacelle from the wing.
AD 99-09-08 · published Apr 26, 1999, effective Jun 7, 1999
Avions Pierre Robin Model R2160 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R2160 airplanes. This AD requires repetitively inspecting the aileron/flap common support bracket for cracks, loose rivets, or separation of the bracket from the skin, and reinforcing the bracket either immediately or at a certain time period depending on whether discrepancies are found during the inspections. Reinforcing the aileron/flap common support bracket terminates the repetitive inspection requirement. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect defects in the aileron/flap common support bracket (cracks, loose rivets, or separation of the bracket from the skin), which could result in reduced or loss of control of the airplane.
AD 99-09-10 · published Apr 26, 1999, effective Jun 7, 1999
Raytheon Aircraft Company Models C90A, B200, B200C, B200T, B200CT, 300, B300, B300C, and A200CT Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models C90A, B200, B200C, B200T, B200CT, 300, B300, B300C, and A200CT airplanes. This AD requires installing a filter element in the landing gear hand pump suction line. This AD is the result of reports of the potential for debris to enter the landing gear hand pump and interfere with its operation, which could prevent the nose landing gear from being extended manually. Two occurrences were reported of nose landing gear collapse after manual extension. The actions specified by this AD are intended to prevent the inability to extend the landing gear with the hand pump caused by debris entering the landing gear hand pump, which could result in passenger injury or damage to the airplane if manual operation of the landing gear failed.
AD 99-09-12 · published Apr 26, 1999, effective Jun 1, 1999
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 series airplanes, that requires repetitive inspections to detect damage of the structure associated with the engine nacelle fairing attached to the wing flaps, and repair of any damage found; drilling a new drain hole in each engine nacelle fairing; and applying a sealant to the gap between the wing flap and engine nacelle fairing. This amendment also requires correction of discrepancies, and modification of the wing flap structure, which terminates the repetitive inspections. This amendment is prompted by reports of fatigue cracks found in the structure that attaches the engine nacelle fairing to the wing flaps. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in the partial or complete separation of the fairing from the wing flap, and consequent additional structural damage to the airframe and/or reduced controllability of the airplane.
AD 99-09-13 · published Apr 26, 1999, effective Jun 1, 1999
Boeing Model 757-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires modifications to the attachment installation of the forward lavatory. This amendment is prompted by a stress analysis report indicating that the forward lavatory could break free from the upper and/or lower attachments during an emergency landing. The actions specified by this AD are intended to prevent failure of the attachment installation of the forward lavatory during an emergency landing, which could result in injury to the crew and passengers.
AD 99-09-14 · published Apr 26, 1999, effective Jun 1, 1999
Lockheed Model L-1011-385 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires inspections to detect cracking of fuselage station (FS) 983 main frame (left and right sides), and repair, if necessary. That AD was prompted by reports of cracks found in the left and right sides of the FS 983 main frame, below the level of the cabin floor. This amendment adds a new requirement to review the airplane maintenance records to determine if a crack within the FS 983 main frame web was detected previously, and if repair of any such crack was deferred; and repetitive inspections, if necessary, until accomplishment of a repair. This amendment also adds terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent cracking of the FS 983 frame, which could result in reduced structural integrity of the fuselage.
AD 99-08-51 · published Apr 27, 1999, effective May 3, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This document published in the Federal Register an amendment adopting airworthiness directive (AD) 99-08-51 that was sent previously to all known U.S. owners and operators of certain McDonnell Douglas Model MD-11 series airplanes by individual notices. This AD requires visual inspections under the floorboards in the lower center cargo compartment at frame 1681 to verify that a certain bracket and a certain open face nylon clamp are installed to a specific support wire bundle and to detect damage of the subject wire bundle; repair of damaged wiring; and installation of certain silicone rubber coated with a glass cloth protective wrap around the wire bundle, if necessary. This action is prompted by an incident in which the insulation blanket between frames 1661 and 1681 in the lower center cargo compartment was found to be burnt due to a missing wiring harness support bracket/clamp on the wire bundle at frame 1681. The actions specified by this AD are intended to ensure that such a wire harness support bracket/clamp is installed; a missing bracket/clamp could cause the wire bundle to chafe against the frame, which could result in sparks, smoke, and possible fire in the lower center cargo compartment.
AD 99-09-15 · published Apr 28, 1999, effective May 18, 1999
Raytheon Aircraft Company Beech Models A36, B36TC, 58, 58A, C90A, B200, B300, and 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models A36, B36TC, 58, 58A, C90A, B200, B300, and 1900D airplanes. This AD requires inspecting for interference or inadequate clearance between the flight control mechanism and any component located forward of the instrument panel. If interference or inadequate clearance is found, this AD requires securing all components so that they are clear of the flight control mechanism. This AD is the result of an incident where the electrical/avionics wires made contact with and restricted the control system of the affected airplanes. The actions specified by this AD are intended to prevent any component or wiring from interfering with the flight control mechanism caused by inadequate clearance, which could result in reduced or loss of aileron and/or elevator control.
AD 99-09-51 · published Apr 30, 1999, effective May 5, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 99-09-51 that was sent previously to all known U.S. owners and operators of certain McDonnell Douglas Model MD-11 series airplanes by individual notices. This AD requires visual inspections under the floorboards in the lower center cargo compartment at frame 1681 to verify that a certain bracket and a certain open face nylon clamp are installed to a specific support wire bundle and to detect damage of the subject wire bundle; repair of damaged wiring; and installation of certain silicone rubber coated with a glass cloth protective wrap around the wire bundle, if necessary. This action is prompted by an incident in which the insulation blanket between frames 1661 and 1681 in the lower center cargo compartment was found to be burnt due to a missing wiring harness support bracket/clamp on the wire bundle at frame 1681. The actions specified by this AD are intended to ensure that such a wire harness support bracket/clamp is installed; a missing bracket/clamp could cause the wire bundle to chafe against the frame, which could result in sparks, smoke, and possible fire in the lower center cargo compartment.
AD 99-07-15 · published Apr 1, 1999, effective May 3, 1999
Arrow Falcon Exporters, Inc., AST, Inc, Bell Helicopter Textron, Inc., California Department of Forestry, Hagglund Helicopters, LLC, International Helicopters, Inc., Overseas Aircraft Support Inc, Richards Heavylift Helo, Inc., Robinson Air Crane, Inc., Rotorcraft Development Corporation, San Joaquin Helicopters, Smith Helicopters, Southern Helicopter, Inc., Southwest Flo
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI)-manufactured Model HH-1K, SW204, SW204HP, SW205, SW205A-1, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters. This action requires inspecting the tail rotor yoke (yoke) assembly historical records to determine if the affected yoke assembly has been involved in any incidents that may have induced a bending load. It further requires replacement of the yoke assembly with a yoke assembly that has been x-ray diffraction inspected or has zero hours time-in-service (TIS); installing and inspecting an airworthy flapping stop or trunnion assembly to detect excessive bending loads; and revising the applicable Rotorcraft Flight Manual. This amendment is prompted by in-flight failures of yokes installed on civilian and military helicopters of similar type design, including three reported accidents. The actions specified in this AD are intended to detect static or dynamic overload on the yoke due to external bending forces, which could result in failure of the yoke, loss of the tail rotor, and subsequent loss of control of the helicopter.
AD 99-07-16 · published Apr 1, 1999, effective May 6, 1999
Sikorsky Aircraft-manufactured Model CH-54A Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft-manufactured Model CH-54A helicopters, that requires an initial and recurring inspections and rework or replacement, if necessary, of the second stage lower planetary plate (plate). This amendment is prompted by cracked plates that have been found during overhaul and inspections. The actions specified by this AD are intended to prevent failure of the plate due to fatigue cracking, which could result in failure of the main gearbox, failure of the drive system, and subsequent loss of control of the helicopter.
AD 99-08-07 · published Apr 6, 1999, effective Apr 21, 1999
MD Helicopters, Inc. Helicopters
This amendment supersedes an existing priority letter airworthiness directive (AD) 98-17-14, applicable to MDHS Model 369E, 369FF, 500N, and 600N helicopters, that currently requires, within the next 14 calendar days, inspecting each relay receptacle contact socket for correct size of the contact socket holes and replacing incorrectly-sized contact sockets with airworthy contact sockets. This amendment requires the same inspections and replacements as the existing priority letter AD, but changes the serial numbers affected for the MDHS Model 500N and 600N helicopters and changes a part number that was incorrectly referenced in the existing AD. This amendment is prompted by three incidences in which a MDHS Model 600 helicopter's Engine Control Unit (ECU) Fail light illuminated, even though the ECU continued to automatically control the engine. The cause of the ECU malfunction indication was determined to be contact sockets that did not properly fit the corresponding pins ofthe affected relay. Improperly sized contact sockets could create multiple unsafe conditions. These conditions, if not corrected, could result in the loss of various engine control or warning systems including the undetected loss of the auto-reignition function after an engine flameout, failure of an engine to reignite, and a subsequent forced landing and the inability to immediately detect an engine-out condition or to properly govern main rotor speed following loss of the Full Authority Digital Engine Control (FADEC), and subsequent loss of control of the helicopter.
AD 99-06-15 · published Apr 7, 1999, effective Apr 22, 1999
Bell Helicopter Textron Canada Model 407 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-06-15 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires installing a tail rotor pitch-limiting left-pedal stop, installing an airspeed limitation placard, marking a never-exceed velocity (Vne) placard on all airspeed indicators, and revising the Limitations section of the Rotorcraft Flight Manual (RFM). This amendment is prompted by three accidents involving inflight tail rotor blade strikes against the tailboom. The actions specified by this AD are intended to prevent the tail rotor blades from striking the tailboom, which could result in separation of the aft section of the tailboom with the tail rotor gearbox and vertical fin, and subsequent loss of control of the helicopter.
AD 99-08-06 · published Apr 7, 1999, effective Apr 22, 1999
Eurocopter France Model SA. 3160, SA. 316B, SA. 316C, and SA. 319B Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA. 3160, SA. 316B, SA. 316C, and SA. 319B helicopters. This action requires inspecting the spar skin and main rotor blade (blade) root reinforcement strip area for a bonding separation, corrosion, or a crack, and replacing the blade, if necessary. This amendment is prompted by the in-flight failure of a blade. The actions specified in this AD are intended to detect a bonding separation, corrosion, or a crack in the area of the blade root reinforcement strip, which could result in failure of the blade and subsequent loss of control of the helicopter.
AD 99-07-17 · published Apr 13, 1999, effective Apr 28, 1999
Robinson Helicopter Company Model R22 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-07-17 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R22 helicopters by individual letters. This AD requires, before further flight, inserting a Special Pilot Caution into the Normal Procedures section of the Rotorcraft Flight Manual (RFM). This amendment is prompted by several reports of sprag clutch assemblies with cracked or fractured sprag ends. The sprag clutch failures, determined to be due to a change in the manufacturing process, could result in loss of main rotor revolutions-per-minute (RPM) during autorotations. The intent of this AD is to alert pilots of the potential for the sprag clutch failing to overrun during autorotation, loss of main rotor RPM, and subsequent loss of control of the helicopter.
AD 99-07-18 · published Apr 13, 1999, effective Apr 28, 1999
Robinson Helicopter Company Model R44 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-07-18 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R44 helicopters by individual letters. This AD requires, before further flight, inserting a Special Pilot Caution into the Normal Procedures section of the Rotorcraft Flight Manual (RFM). This amendment is prompted by several reports of sprag clutch assemblies with cracked or fractured sprag ends. The sprag clutch failures, determined to be due to a change in the manufacturing process, could result in loss of main rotor revolutions-per-minute (RPM) during autorotations. The intent of this AD is to alert pilots of the potential for the sprag clutch failing to overrun during autorotation, loss of main rotor RPM, and subsequent loss of control of the helicopter.
AD 99-09-05 · published Apr 20, 1999, effective May 5, 1999
Bell Helicopter Textron Canada (BHTC) Model 230 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to BHTC Model 230 helicopters. This action requires initial and repetitive visual inspections and verification of the torque of the bolts on the main rotor hub. This amendment is prompted by a report of fatigue cracks around the bolt holes of the main rotor pitch horn (pitch horn) and a cracked main rotor flapping bearing assembly (flapping bearing assembly) on a similar model helicopter. This condition, if not corrected, could result in fretting-induced fatigue cracking of the flapping bearing assembly and around the bolt holes of the pitch horn, loss of the rotor system, and subsequent loss of control of the helicopter.
AD 99-09-06 · published Apr 23, 1999, effective May 10, 1999
Eurocopter France Model AS-350B, B1, B2, B3, BA, and D Helicopters, and Model AS 355E, F, F1, F2 and N Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS-350B, B1, B2, B3, BA, and D helicopters, and Model AS 355E, F, F1, F2 and N helicopters. This action requires inspecting the tail rotor spider plate bearing (bearing) for the proper bearing rotational torque, axial play, and for any brinelling of the bearing. This amendment is prompted by service difficulty reports citing the need to prematurely replace bearings due to wear, and by two in-flight incidents of increased tail rotor vibration levels due to bearing wear. This condition, if not corrected, could result in seizure of the bearing, loss of tail rotor control and subsequent loss of control of the helicopter.
AD 99-09-16 · published Apr 28, 1999, effective May 13, 1999
Eurocopter France (Eurocopter) Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C helicopters, that currently requires a visual inspection of the main rotor blade reinforcement strips for debonding between the reinforcement strips of the blade; and a visual inspection of the main rotor blade (blade) skin for cracks or corrosion, and replacement of the blade with an airworthy blade if certain debonding or a crack or corrosion is found. This amendment requires additional inspections using a tapping method, redefines the area to be inspected, and increases the repetitive inspection interval. This amendment is prompted by an in-flight failure of a main rotor blade on a Eurocopter SE 3130 helicopter. The actions specified by this AD are intended to detect bonding separation, cracks, or corrosion in the area of the blade root reinforcement strip, and to prevent failure of a blade and subsequent loss of control of the helicopter.
AD 99-09-20 · published Apr 29, 1999, effective May 14, 1999
Bell Helicopter Textron Canada (BHTC) Model 222, 222B, and 222U Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to BHTC Model 222, 222B, and 222U helicopters. This action requires initial and repetitive visual inspections and verification of the torque of the bolts on the main rotor hub. This amendment is prompted by a report of fatigue cracks around the bolt holes of the main rotor pitch horn (pitch horn) and a cracked main rotor flapping bearing assembly (flapping bearing assembly) on a BHTC Model 222 helicopter. This condition, if not corrected, could result in fretting-induced fatigue cracking of the flapping bearing assembly and around the bolt holes of the pitch horn, loss of the rotor system, and subsequent loss of control of the helicopter.
AD 99-02-51 · published Apr 5, 1999, effective Apr 20, 1999
Allison Engine Company, Inc. AE 3007A and AE 3007C Series Turbofan Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-02-51 that was sent previously to all known U.S. owners and operators of Allison Engine Company, Inc. AE 3007A and AE 3007C series turbofan engines by individual telegrams. This AD prohibits, prior to further flight, all engine ground starts at oil temperatures below 32 deg.F (0 deg.C) unless preflight operational procedures ensure that engine oil temperature is maintained at or above 32 deg.F (0 deg.C). This amendment is prompted by reports of in-flight engine shutdowns. The in-flight engine shutdowns have been attributed to loss of engine oil from the starter shaft seal. The actions specified by this AD are intended to prevent an in-flight engine shutdown due to loss of engine oil from the starter shaft seal.
AD 99-07-19 · published Apr 6, 1999, effective Apr 21, 1999
AlliedSignal Inc. TFE731-40R-200G Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to AlliedSignal Inc. TFE731-40R-200G turbofan engines. This action requires inspection of the fuel flow meter tube assembly part number (P/N) 3061157-2, which connects the fuel control to the fuel flow meter, and eventual replacement of the tube and fuel flow meter mounting bracket. This amendment is prompted by two in-flight shutdowns on two recently certified TFE731-40R turbofan engines within the last six months that resulted from fuel flow meter tube assembly failures. The actions specified in this AD are intended to prevent fuel from spraying on and around electrical components due to a cracked fuel line, which can result in an in-flight engine shutdown, and could possibly result in an engine fire.
AD 99-08-11 · published Apr 13, 1999, effective May 13, 1999
International Aero Engines AG (IAE) V2500-A1/-A5/-D5 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the Airworthiness Limitations Section (ALS) and Maintenance Scheduling Section (MSS) of the Instructions for Continued Airworthiness (ICA) in the Time Limits Manual (Chapter 05-10-00) of the Engine Manuals for International Aero Engines AG (IAE) V2500-A1/-A5/-D5 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. 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 99-08-12 · published Apr 13, 1999, effective May 13, 1999
Pratt & Whitney JT9D Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the Engine Time Limits section in the Engine Manual (EM) for Pratt & Whitney (PW) JT9D series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. The actions specified by this proposed 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 99-08-13 · published Apr 13, 1999, effective May 13, 1999
General Electric Company CF6-80A, CF6- 80C2, and CF6-80E1 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the Life Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF6-80A, CF6-80C2 and CF6-80E1 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. 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 99-08-14 · published Apr 13, 1999, effective May 13, 1999
Pratt & Whitney PW2000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) PW2000 series turbofan engines, that requires revisions to the engine manufacturers time limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that if allowed to continue in service, could result in uncontained failures. 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 99-08-15 · published Apr 13, 1999, effective May 13, 1999
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the Time Limits Section (TLS) of the manufacturer's Engine Manuals (EMs) for Pratt & Whitney (PW) PW4000 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that if allowed to continue in service, could result in uncontained failures. 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 99-08-16 · published Apr 13, 1999, effective May 13, 1999
CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, and -3C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the Engine Time Limits section in the Engine Shop Manual (ESM) for CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, and -3C series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. 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 99-08-17 · published Apr 13, 1999, effective May 13, 1999
General Electric Company GE90 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the manufacturer's Life Limits Section of the Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) GE90 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. 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 99-08-18 · published Apr 13, 1999, effective May 13, 1999
General Electric Company CF6-6, CF6-45, and CF6-50 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the Time Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF6-6, CF6-45, and CF6-50 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment also requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. The actions specified by this proposed 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 99-08-21 · published Apr 16, 1999, effective Jun 2, 1999
Puritan-Bennett Aero Systems Company C351-2000 Series Passenger Oxygen Masks and Portable Oxygen Masks
This amendment adopts a new airworthiness directive (AD) that applies to any aircraft equipped with Puritan-Bennett Aero Systems Company (Puritan-Bennett) C351-2000 series passenger oxygen masks and portable oxygen masks. This AD requires inspecting the passenger and portable oxygen masks for tears around the face cushion adjacent to the inner mask housing, and replacing or repairing any torn passenger or portable oxygen mask. This AD is the result of reports received from three airplane manufacturers of defective oxygen masks. The actions specified by this AD are intended to prevent reduced oxygen consumption when passengers are required to use defective oxygen masks, which could result in passenger injury.
AD 95-11-15 R1 · published Apr 26, 1999, effective Jul 25, 1999
Alexander Schleicher Segelflugzeugbau Model ASK 21 Gliders
This amendment revises Airworthiness Directive (AD) 95-11-15, which currently requires replacing the parallel rocker with a part of improved design and incorporating flight manual revisions on all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASK 21 gliders. AD 95-11-15 was the result of two incidents of the parallel rocker breaking at the elevator connection on the affected gliders. Since that time, the FAA has determined that the AD should only affect those Model ASK 21 gliders equipped with the automatic elevator connection. This AD retains the actions of AD 95-11-15, but only for those gliders with the automatic elevator connection incorporated. The actions specified in this AD are intended to continue to prevent possible loss of elevator control that could result from a broken parallel rocker.
AD 99-09-07 · published Apr 26, 1999, effective Jun 7, 1999
S.N. CENTRAIR 101 Series Gliders
This amendment adopts a new airworthiness directive (AD) that applies to all S.N. CENTRAIR (CENTRAIR) 101 series gliders that have modification 101-24 (major cockpit configuration equipped on all gliders manufactured since 1990) incorporated, and do not have modification 101-21 (minor modifications to this cockpit configuration) incorporated. This AD requires installing an attachment lug to the supporting bracket in order to secure the battery discharge warning device. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent elevator flight control interference caused by an unsecured battery discharge warning device, which could result in reduced or loss of glider control.
AD 99-09-09 · published Apr 28, 1999, effective Jun 7, 1999
Alexander Schleicher Segelflugzeugbau Model ASH 26E Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASH 26E sailplanes. This AD requires inspecting the red silicone tube of the rotor interior air cooling system (just in front of the carburetor ) for oil leaks and the heat damping layer of the lower exhaust damper fairing for oil contamination, and replacing the applicable parts where oil leakage or contamination is found. 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 any oil- contaminated exhaust damper fairing caused by oil leakage in the red silicone tube of the rotor interior air cooling system, which could result in an exhaust fire and/or an explosion.
