29 Airworthiness Directives: 24 airplane, 2 engine, 2 appliance, 1 glider.
AD 96-20-04 · published Nov 4, 1996, effective Nov 4, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires modification of the passenger door lock warning system. This amendment is prompted by reports that the passenger door opened during flight due to an improperly locked door; additionally, the door warning signal was not sufficiently visible to alert the flight crew of this condition. The actions specified by this AD are intended to ensure that the flight crew is aware of an unlocked passenger door prior to takeoff of the airplane. This condition, if not corrected, could result in inadvertent opening of the passenger door while the airplane is in flight.
AD 96-22-01 · published Nov 6, 1996, effective Dec 6, 1996
Boeing Model 747-200, -300, and -400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that requires modification of the left and right inboard elevator servo assemblies and the hydraulic routing of the right inboard elevator power control package (PCP). This amendment is prompted by a report of an uncommanded right elevator deflection after takeoff and reports of elevator/control column bumps during landing gear retraction on these airplanes. The actions specified by this AD are intended to prevent uncommanded elevator deflection, which could result in structural damage and reduced controllability of the airplane.
AD 96-22-03 · published Nov 6, 1996, effective Dec 11, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe series 1000A and Model Hawker 1000 airplanes, that requires modifications of the thrust reversers. This amendment is prompted by a review of the certification analysis of the thrust reversers and by testing of the thrust reversers, which indicated that additional design features are necessary to prevent failure of the driver link and the inadvertent deployment of a thrust reverser during flight. The actions specified by this AD are intended to prevent inadvertent deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.
AD 96-22-06 · published Nov 6, 1996, effective Dec 11, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10-15 airplanes, that requires, among other things, inspections to detect discrepancies at various locations of pylons 1 and 3, and correction of any discrepancy found. This amendment is prompted by a report of internal structural damage to the wing engine pylon that occurred during maintenance of a Model DC-10 series airplane. The actions specified by this AD are intended to ensure the integrity of the structure and attachment of the wing engine pylon.
AD 96-22-10 · published Nov 6, 1996, effective Dec 11, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas DC-9 and DC-9-80 series airplanes, and Model MD-88 airplanes, that requires repetitive leak checks of the lavatory drain system and repair, if necessary; provides for the option of revising the FAA-approved maintenance program to include a schedule of leak checks; requires the installation of a cap on the flush/fill line; and requires replacement or modification of the vent system piping. This amendment is prompted by continuing reports of damage to engines and airframes, separation of engines from airplanes, 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 such damage associated with the problems of "blue ice."
AD 96-22-11 · published Nov 6, 1996, effective Dec 11, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 and 747 series airplanes, that requires replacement of Waterman hydraulic fuse assemblies with modified assemblies. This amendment is prompted by reports of failure of hydraulic system A and the standby system, due to corrosion on the magnesium piston of the hydraulic fuse and consequent failure of the fuse to close sufficiently to prevent the loss of hydraulic fluid from the system. The actions specified by this AD are intended to prevent such failure of the fuse, which could result in the failure of one or more hydraulic systems and resultant reduced controllability of the airplane.
AD 96-22-13 · published Nov 6, 1996, effective Dec 27, 1996
Pilatus Aircraft Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus), Model PC-6 airplanes. This action requires inspecting for loose or sheared rivets in the hinge brackets on the horizontal stabilizer and inspecting for incorrect spacing tolerance of the hinge brackets. If the rivets are found loose or sheared, the AD requires replacing the rivets and also re-positioning the hinge brackets, if found incorrectly spaced. Several reports of rivets shearing on the hinge brackets prompted this action. The actions specified by this AD are intended to prevent structural failure of the hinge bracket on the horizontal stabilizer, which could result in partial or complete loss of control of the horizontal stabilizer and loss of control of the airplane.
AD 96-23-02 · published Nov 12, 1996, effective Nov 27, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires inspections to detect disbonding, corrosion, and cracking at the longitudinal rows of fasteners in the bonded skin panels in section 41 of the fuselage, and repair, if necessary. This amendment is prompted by a report of skin cracking due to disbonding of the internal doubler of the cracked skin panels. The actions specified in this AD are intended to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels.
AD 96-23-03 · published Nov 12, 1996, effective Dec 23, 1996
Aerospace Technologies of Australia Pty Ltd. (Formerly Government Aircraft Factory) Models N22B, N24A, and N22S Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N24A, and N22S airplanes that are not equipped with a part number (P/N) 1E/N-12-57 fuselage stub fin plate (MOD N759). This action requires replacing the existing fuselage stub fin plate with one of improved design, P/N 1E/N-12-57. This action results from several reports of cracks along the forward flange of the fuselage stub fin plate in the area of Rib Water Line (WL) 138.87. The actions specified by this AD are intended to prevent structural failure of the fuselage area caused by a cracked stub fin plate, which could result in loss of control of the airplane.
AD 96-23-18 · published Nov 12, 1996, effective Dec 23, 1996
Nomad TC Pty Ltd Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N24A, and N22S airplanes that are not equipped with a part number (P/N) 1E/N-12-57 fuselage stub fin plate (MOD N759). This action requires replacing the existing fuselage stub fin plate with one of improved design, P/N 1E/N-12-57. This action results from several reports of cracks along the forward flange of the fuselage stub fin plate in the area of Rib Water Line (WL) 138.87. The actions specified by this AD are intended to prevent structural failure of the fuselage area caused by a cracked stub fin plate, which could result in loss of control of the airplane.
AD 96-23-04 · published Nov 14, 1996, effective Dec 19, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires replacement of the 250 volt-ampere (VA) rated static inverters with 410 VA or 500 VA rated static inverters, and an operational test of the standby electrical power system. This amendment is prompted by a report that accomplishment of a certain modification could result in overload of the static inverter on these airplanes. The actions specified by this AD are intended to prevent overload of the static inverter, which could result in the loss of the 115 volt alternating current (VAC) standby bus and the associated flight instruments when the airplane is operating on standby electrical power.
AD 96-23-05 · published Nov 14, 1996, effective Dec 16, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect cracks and/or corrosion of the girt bar support fitting at certain main entry doors (MED); and repair or replacement of the support fitting. This amendment also provides for various terminating actions for the repetitive inspections. This amendment is prompted by reports that, during scheduled deployment tests of main entry door slides, corrosion was found on the floor structure supports for the escape slides of the main deck entry doors on these airplanes. The actions specified by this AD are intended to prevent such corrosion, which could result in separation of the escape slide from the lower door sill during deployment, and subsequently prevent proper operation of the escape slides at the main entry doors during an emergency.
AD 96-23-06 · published Nov 14, 1996, effective Dec 19, 1996
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of certain hydraulic fuses of the landing gear with improved fuses. This amendment is prompted by results of extended testing, which revealed that the hydraulic fuses of the landing gear failed to operate due to movement of the end of the spring within the fuses over the end of the flange of the spool. The actions specified by this AD are intended to prevent such failure, which could result in external leakage in the brake lines downstream of the respective fuse and consequent loss of hydraulic fluid; this condition, if not corrected, could result in partial loss of the main hydraulic power supply.
AD 96-23-17 · published Nov 20, 1996, effective Dec 26, 1996
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-102 and -103 series airplanes, that requires repetitive external inspections to detect cracks in the skin exterior of the fuselage at floor level, and repair, if necessary. This amendment also requires repetitive internal inspections to detect cracks of the subject area, which terminates the repetitive external inspections. This amendment is prompted by a report that one of the tasks in the Maintenance Program Airworthiness Limitations List inadvertently excluded certain airplanes from the instructions for the inspections. The actions specified by this AD are intended to prevent undetected cracking of the frames and skin panels of the fuselage, which could result in reduced structural integrity of the airplane.
AD 96-23-19 · published Nov 20, 1996, effective Dec 18, 1996
Air Tractor, Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-300, AT-400, and AT-500 series airplanes. This AD requires installing both a new flap actuator overtravel stop and a roll pin through the overtravel stop and jack screw. This AD results from incidents where the flap actuator overtravel stop nut disengaged from the jack screw. The flap pushrod pressed against the aileron pushrod, which caused difficulty in moving the ailerons. The actions specified by this AD are intended to prevent interference between the flap pushrod and the aileron pushrod caused by the flap actuator overtravel nut disengaging, which could result in loss of aileron control.
AD 96-23-09 · published Nov 22, 1996, effective Dec 27, 1996
de Havilland Model DHC-8-100 and -300 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 and -300 series airplanes, that currently requires repetitive inspections to detect cracks of the upper drag strut trunnion fittings of the nose landing gear (NLG) and to verify tightness of the fitting attachment bolts, and replacement of fittings or fasteners, if necessary. This amendment requires the installation of a modification to terminate the repetitive inspections. This amendment is prompted by the development of a modification that positively addresses the identified unsafe condition. The actions specified by this AD are intended to prevent failure of the upper drag strut trunnion fittings of the NLG, which could lead to collapse of the NLG.
AD 96-24-03 · published Nov 22, 1996, effective Dec 9, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing 747-400 series airplanes in the "combi" configuration. This action requires replacing the decompression panels that are located in the smoke barrier between the passenger and main deck cargo compartment, with new panels of an improved design. This amendment is prompted by reports indicating that normal pressurization cycles are causing premature tearing or opening of these decompression panels. The actions specified in this AD are intended to prevent increased airflow in the cargo compartment caused by the tearing or opening of these panels; this condition, if not corrected, could result in delayed fire detection and reduced effectiveness of the cargo compartment fire suppression system.
AD 96-24-04 · published Nov 22, 1996, effective Jan 17, 1997
Nomad TC Pty Ltd Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia (ASTA) Nomad Models N22B, N22S, and N24A airplanes. This action requires repetitively inspecting the tailplane stabilizer center section and repairing any cracked tailplane structure. This AD also provides an optional modification as a terminating action, after an inspection in which no cracks are found. A tailplane failure on one of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent cracking in the stabilizer center section, which, if not detected and corrected, could result in tailplane failure and loss of control of the airplane.
AD 96-24-05 · published Nov 22, 1996, effective Jan 17, 1997
Nomad TC Pty Ltd Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia (ASTA) Nomad Models N22B, N22S, and N24A airplanes. This action requires inspecting the flap and aileron control rod fork ends for water accumulation and corrosion inside the internally drilled holes, and replacing the control rod fork ends if there is visible corrosion, or sealing the hole if no corrosion is found. Reports of water entering the internal holes of the flap and aileron control rod fork ends, causing corrosion, prompted this AD action. The actions specified by this AD are intended to prevent corrosion and water accumulation in the flap and aileron control rod fork ends, which, if not detected and corrected, could cause loss of control of the flaps and aileron and possible loss of control of the airplane.
AD 96-24-07 · published Nov 22, 1996, effective Jan 17, 1997
HOAC-Austria Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain HOAC Austria Model DV-20 Katana airplanes. This action requires replacing the muffler with one of improved design, installing a heat shield around the exhaust system endpipe, and adjusting the airplane weight and balance. This AD results from reports of cracks in the welding joint that connects the exhaust system endpipe to the muffler on three of the affected airplanes. The actions specified by this AD are intended to prevent separation of the exhaust system endpipe from the muffler because of cracks in the welding that connects these parts, which could result in heat damage to the electrical system and engine controls.
AD 96-24-08 · published Nov 26, 1996, effective Dec 23, 1996
Air Tractor, Inc. Models AT-250, AT- 300, AT-301, AT-302, AT-400, AT-400A, AT-401, AT-402, AT-501, and AT- 502 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-250, AT- 300, AT-301, AT-302, AT-400, AT-400A, AT-401, AT-402, AT-501, and AT- 502 airplanes that are equipped with a Gerdes part number (P/N) A-850-5 or Cleveland P/N 60-9 parking brake valve. This action requires replacing the parking brake valve with a Scott P/N 4500A-2 parking brake valve. This AD results from several reports of the parking brake valve inadvertently slipping to the ``PARK'' position during flight, which causes constant pressure on the brakes. When the pilot applies the brake upon landing, this pressure causes the airplane to overturn. The actions specified by this AD are intended to prevent the airplane from overturning because of extreme pressure applied to the brake if the parking brake valve inadvertently slips to the ``PARK'' position during flight.
AD 96-24-13 · published Nov 26, 1996, effective Jan 17, 1997
Piper Aircraft Inc. Airplanes
This document supersedes AD 75-26-18, which currently requires modifying the landing gear selector cable forward attachment pin assembly by installing a safety lock wire on certain The New Piper Aircraft Inc., (Piper) PA-31, PA-31P, and PA-31T series airplanes. The action will require the same action as AD 75-26-18. An incorrect designation of Piper Model PA-31 airplanes as Piper Model PA-31-310 airplanes in AD 75-26-18 prompted the proposed AD action. The actions specified by this AD are intended to prevent the landing gear selector cable forward attachment pin assembly from becoming separated from the powerpack control arm, which, if not corrected, could cause loss of landing gear retraction or extension.
AD 96-21-09 · published Nov 29, 1996, effective Nov 29, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 series airplanes and certain Model Avro 146-RJ series airplanes, that requires a one-time inspection to detect corrosion of the direction link subassembly of the main landing gear (MLG) assembly, and repair or replacement of the direction link subassembly with a serviceable unit, if necessary. This amendment is prompted by a report of failure of the direction link subassembly due to corrosion. The actions specified by this AD are intended to prevent such failures, which can result in directional control problems of the airplane during landing.
AD 96-23-10 · published Nov 20, 1996, effective Jan 21, 1997
Pratt & Whitney Division Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT3D series turbofan engines, that requires inspection of steel high pressure compressor (HPC) disks for corrosion, recoating or replating those disks, or replacing those disks as necessary. This amendment is prompted by reports of a failure of a PW JT8D steel HPC disk, which is similar in design to the PW JT3D steel HPC disks. The actions specified by this AD are intended to prevent steel HPC disk failure due to corrosion, which could result in an uncontained engine failure and damage to the aircraft.
AD 96-24-09 · published Nov 25, 1996, effective Nov 25, 1996
Allison Engine Company Model 250-C47B Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company Model 250-C47B turboshaft engines. This action supersedes priority letter AD 96-21-12, applicable to Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 407 helicopters, that currently prohibits further flight, due to uncommanded inflight engine shutdowns. This action requires replacing the engine main electrical harness assembly with an improved assembly, disabling the overspeed solenoid, inspecting the engine control unit (ECU) internal PW10 voltage to determine electrical noise characteristics, and replacing units not considered serviceable. In addition, this AD requires adding a placard to the helicopter instrument panel notifying the pilot that the overspeed protection system is disabled and removes a placard which was required by priority letter AD 96-21-12; revises the BHTC Model 407 Rotorcraft Flight Manual (RFM); and requires maintenance actions to clear the engine electronic control unit (ECU) of faults prior to each flight. Accomplishment of these actions will enable operators to resume flight operations. This amendment is prompted by investigation into the causes of the inflight engine shutdowns. The actions specified by this AD are intended to prevent uncommanded inflight engine shutdowns, which can result in autorotation, forced landing, and possible loss of the helicopter.
AD 96-22-09 · published Nov 6, 1996, effective Dec 11, 1996
Short Brothers PLC Appliances
This amendment adopts a new airworthiness directive (AD), applicable to certain Shorts Model SD3-60 and SD3-SHERPA series airplanes, that requires a one-time inspection to detect cracks and/or corrosion of the gland nut on the shock absorber of the main landing gear (MLG), and follow-on actions. This amendment also requires repair or replacement of any cracked/corroded gland nut with a new nut. This amendment is prompted by a report indicating that, due to stress corrosion and cracking of the gland nut on the shock absorber, the MLG collapsed on an in-service airplane. The actions specified by this AD are intended to detect and correct such stress corrosion or cracking in a timely manner and consequent reduced structural integrity of the gland nut, which could result in separation of the shock absorber cylinder from the MLG shock absorber body and, consequently, lead to the collapse of the MLG during landing.
AD 95-26-15 R1 · published Nov 20, 1996, effective Dec 26, 1996
Airbus, Allied Signal Commercial Avionics Systems, ATR - GIE Avions de Transport Régional, The Boeing Company, Bombardier Inc., Embraer - Empresa Brasileira de Aeronautica S.A., Fokker Services, Gulfstream Aerospace Corporation, Textron Aviation Inc., Kelowna Flightcraft R & D Ltd., Lockheed Martin Corporation, Saab AB, Saab Aerosystems, Sabreliner Corporation, Viking Air
This amendment revises an existing airworthiness directive (AD), applicable to various transport category airplanes equipped with Allied Signal Commercial Avionics Systems CAS-81 TCAS, that currently requires a revision to the Airplane Flight Manual (AFM) to provide the flightcrew with procedures to cycle power to the TCAS processor via the circuit breaker or power bus, and to perform a TCAS functional test to verify proper operation of the TCAS. That AD was prompted by reports of failure of the audio output of the CAS-81 TCAS. The actions specified by that AD are intended to ensure that the flightcrew is advised of the potential hazard associated with failure of the audio output of the CAS-81 TCAS, and of the procedures necessary to address it. This amendment adds a revision of the AFM requirements that provides an alternative method of compliance with the currently required AFM revision; and provides for a modification to the TCAS processor, which, if accomplished, terminates the requirements of the AD.
AD 96-22-16 · published Nov 6, 1996, effective Dec 30, 1996
HB Aircraft Industries AG Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain HB Aircraft Industries AG HB-23 2400 Hobbyliner/Scanliner sailplanes. This action requires inspecting the rudder bearing support bracket for cracks, replacing the bracket if cracked, and modifying the bracket with a third bolt, if no cracks are found. Cracks found in the rudder bearing support brackets prompted this action. The actions specified by this AD are intended to prevent cracks in the rudder bearing support bracket, which could cause loss of control of the rudder and possible loss of the sailplane.
