28 Airworthiness Directives: 20 airplane, 5 engine, 3 glider.
AD 96-03-01 · published Feb 1, 1996, effective Feb 16, 1996
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 inspections of the lower engine mount to determine if the tangential link upper bolt and nut are oriented properly, and if the tangential link upper bolt nut is torqued within certain limits. This action also requires replacement of the bolt and nut with serviceable parts, if necessary, and requires certain follow-on actions for airplanes on which the upper bolt is missing. Terminating action is also provided by this AD. This amendment is prompted by reports of migration of bolts completely from the tangential link of the aft engine mount, a condition which would reduce the capability of the retention system for the engine. The actions specified in this AD are intended to prevent separation of the engine from the airplane due to migration of the tangential link upper bolt.
AD 96-03-09 · published Feb 2, 1996, effective Mar 4, 1996
De Havilland Model DHC-8-102, -103, - 106, -301, -311, -314, and -315 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8 series airplanes, that requires modification of a certain battery temperature monitor. This amendment is prompted by reports of failure of the battery temperature monitor, which resulted in smoke in the flight compartment. The actions specified by this AD are intended to prevent failure of the battery monitor, which could result in smoke in the flight compartment.
AD 96-03-10 · published Feb 2, 1996, effective Feb 20, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. This action requires an inspection for damage of the fuel tube located in the forward engine strut, and repair, if necessary; installation of a new support bracket and clamps on the power feeder conduit; and an inspection for proper positioning of the power feeder conduit in each engine strut, and adjustment, if necessary. This amendment is prompted by reports of worn fuel tubes that were caused by the power feeder conduit moving and touching the fuel tube. The actions specified in this AD are intended to prevent wear of the fuel tube, which could result in a fuel leak in the engine strut and a consequent fire hazard.
AD 96-02-02 · published Feb 12, 1996, effective Feb 12, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires installation of locking plates at the guide bushings in the area of the spigot bolt for certain aft flap track attachments. This amendment is prompted by reports of these guide bushings migrating out of position and resulting in a partial transfer of loads from the main attachment spigot bolt to two fail-safe bolts. Since the fail-safe bolts can withstand such loads for only a limited time, they can eventually fail and allow the wing flap to separate from the airplane. The actions specified in this AD are intended to prevent separation of the wing flap, which can lead to reduced controllability of the airplane and injury to persons or damage to property on the ground.
AD 96-03-03 · published Feb 12, 1996, effective Mar 15, 1996
M7 Aerospace LLC Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 and SA227 series airplanes. This action requires replacing the nuts that attach the power control cable to the lever attach point clevis with nuts that have safety wire holes, safety-wiring the power control cable to the lever attach point clevis, inspecting to assure that the power cable is securely attached to the power control cable bracket, and correcting any attachment problems. Reports of power control cable attaching hardware failure on two of the affected airplanes prompted this action. In one of these instances, the power control cable disconnected from the lever attach point clevis, resulting in engine shutdown. The actions specified by this AD are intended to prevent such power control cable disconnection, which could result in engine shutdown and subsequent loss of control of the airplane.
AD 96-03-05 · published Feb 12, 1996, effective Mar 13, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes and Model DC-10-30, DC-10-40, and KC-10A (military) airplanes. For Model MD-11 series airplanes, the AD requires an inspection to determine the serial number of the forward trunnion bolts on the main landing gear (MLG), and rework or replacement of the bolts, if necessary. For Model DC-10-30, DC-10-40, and KC-10A (military) airplanes, the AD requires an inspection for evidence of missing chrome and for corrosion on the chrome surfaces, or verification that the forward trunnion bolts have been chrome plated in a specific manner; and rework or replacement of the bolts, if necessary. This amendment is prompted by reports of chrome flaking on the bearing surface of the trunnion bolts due to improper cleaning of the base material prior to chrome plating. The actions specified by this AD are intended to prevent premature failure of the trunnion bolts and subsequent collapse of the MLG as a result of severe corrosion on the bearing surface and in the mechanical fuse due to chrome flaking.
AD 96-03-07 · published Feb 12, 1996, effective Mar 13, 1996
Beech Model 400, 400A, and MU-300-10 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400, 400A, and MU-300-10 airplanes, that requires installation of an improved adjustment mechanism on the flightcrew seats and replacement of the existing aluminum seat reinforcement assemblies with steel assemblies. This amendment is prompted by reports of incomplete latching of the existing adjustment mechanism and cracked reinforcement assemblies, which could result in sudden shifting of a flightcrew seat. The actions specified by this AD are intended to prevent such shifting of a flightcrew seat, which could impair the flightcrew's ability to control the airplane.
AD 96-03-08 · published Feb 12, 1996, effective Mar 13, 1996
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires repetitive operational tests of the valve limit switch of the propeller brake. This amendment also provides for an optional terminating action for the repetitive tests. This amendment is prompted by a report that when the propeller brake was not properly engaged the crew did not receive a "PROP BRAKE" warning due to a faulty valve limit switch. The actions specified by this AD are intended to prevent a valve limit switch from failing to send input to the warning system; absence of a "PROP BRAKE" warning could result in the crew being unaware that the propeller brake is not properly engaged and the propeller may turn without warning.
AD 96-03-11 · published Feb 13, 1996, effective Feb 26, 1996
American Champion Aircraft Corporation Models 8KCAB, 8GCBC, 7GCBC, and 7ECA Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to American Champion Aircraft Corporation (American Champion) Models 8KCAB, 8GCBC, 7GCBC, and 7ECA airplanes that are equipped with metal spar wings. This action requires inspecting (one time) the wing front strut fittings for cracks or scratches, replacing any wing front strut fittings found cracked or scratched, and reporting the inspection results to the Federal Aviation Administration (FAA). Fatigue cracks found on the wing front strut fittings on two Model 8KCAB airplanes prompted this action. The actions specified by this AD are intended to prevent structural failure of a wing assembly caused by cracked or scratched wing front strut fittings, which, if not detected and corrected, could result in loss of control of the airplane.
AD 94-07-10 R1 · published Feb 14, 1996, effective Mar 25, 1996
Fairchild Aircraft SA226 and SA227 Series Airplanes
This amendment revises AD 94-07-10, which currently requires the following on Fairchild Aircraft SA226 and SA227 series airplanes: Repetitively inspecting (visually) the wing skin for cracks; dye penetrant inspecting the rib straps if the wing skin is found cracked; and, if any crack is found in the rib straps, repairing the rib straps and modifying the wing skin. That AD references an incorrect dye penetrant inspection when the wing skin is found cracked. This action maintains the requirements of AD 94-07-10, but incorporates reference to the correct dye penetrant inspection for when the wing skin is found cracked. The actions specified by this AD are intended to prevent failure of the wing skin at the top aft outboard corner of the battery box, which could result in structural damage to the wing.
AD 96-03-01 R1 · published Feb 16, 1996, effective Feb 16, 1996
The Boeing Company Airplanes
AD 96-03-14 · published Feb 21, 1996, effective Mar 22, 1996
Boeing Model 747-400 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires replacement of electrical wiring to the fuel shutoff valve for each engine. This amendment requires replacement of the fuel shutoff valve wire and sleeve with a wire in two non-metallic sleeves in the conduit in the struts of each engine. This amendment is prompted by reports of additional occurrences of chafing and shorting of the wiring of the engine fuel shutoff valves. The actions specified by this AD are intended to prevent such chafing and shorting, which could result in the pilot's inability to shut off the supply of fuel in the event of an engine fire.
AD 96-04-03 · published Feb 21, 1996, effective Mar 22, 1996
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200 and -200C airplanes, that currently requires installation of fail-safe straps onto the engine inlet attach ring of the nose cowl. This amendment requires repetitive inspections to detect cracking of the attach ring of the nose cowl, and replacement of cracked attach rings. Replacement with an improved attach ring, if accomplished, would terminate the requirement to inspect the attach ring repetitively. This amendment is prompted by the development of an improved attach ring that eliminates the need for repetitive inspections. The actions specified by this AD are intended to prevent cracking of the attach ring of the nose cowl, which could result in separation of the nose cowl from the engine following failure of a turbine blade.
AD 96-03-13 · published Feb 22, 1996, effective Apr 1, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) 90, 99, 100, and 200 series airplanes. This action requires inspecting the main landing gear drag leg lock link to ensure that the hole for the roll pin is drilled completely through both walls of the main landing gear drag leg lock link and, if not drilled completely through both link walls, replacing any main landing gear drag leg lock link. An incident in which the left main landing gear collapsed on one of the affected airplanes prompted this action. Investigation revealed that the roll pin hole was not completely drilled through both walls of the drag leg lock link. The actions specified by this AD are intended to prevent main landing gear collapse caused by drag leg lock link failure, which could result in loss of control of the airplane.
AD 96-02-05 · published Feb 23, 1996, effective Mar 25, 1996
McDonnell Douglas Corporation Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes, that currently requires visual and eddy current inspections to detect cracking of the rudder pedals adjuster hub assembly, and replacement of the assembly, if necessary. That amendment was prompted by several occurrences of failure of the rudder pedals adjuster hub assembly due to broken detent lugs. This amendment provides an optional terminating action for the required inspections, and expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent loss of rudder pedals control and reduction of braking capability.
AD 96-04-08 · published Feb 23, 1996, effective Apr 12, 1996
Air Tractor, Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Air Tractor, Incorporated (Air Tractor) Models AT-802 and AT-802A airplanes. This action requires repetitively replacing the main landing gear legs. Failure of the main landing gear legs on an AT-802A prompted this action. The actions specified by this AD are intended to prevent possible failure of the main landing gear legs, which, if not detected and corrected, could result in loss of control of the airplane during landing operations.
AD 96-01-09 · published Feb 26, 1996, effective Feb 26, 1996
McDonnell Douglas Corporation 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 installation of hydraulic line restrictors in the main landing gear (MLG), and modification of the hydraulic damper assembly of the MLG. This amendment is prompted by reports of vibration occurring in the MLG during landing; in some cases, such vibration has led to the collapse of the MLG. The actions specified by this AD are intended to prevent incidents of vibration in the MLG, which can adversely affect the integrity of the MLG.
AD 96-02-03 · published Feb 26, 1996, effective Feb 26, 1996
Airbus SAS Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that currently requires inspections to detect cracks in the area of the shock absorber attachment at the top of the barrel at the main landing gear (MLG), a measurement of the gap between the barrel and the shock absorber attachment; and corrective action, if necessary. That AD was prompted by a report of the rupture of the aft hinge arm of the left MLG barrel. This amendment requires a measurement of the gap between the washer and barrel of the MLG, eddy current inspections to detect cracking of the MLG barrel, correction of any discrepancy, and accomplishment of certain other follow-on actions. Terminating actions are also provided by this AD. The actions specified by this AD are intended to prevent collapse of the MLG.
AD 96-02-06 · published Feb 26, 1996, effective Feb 26, 1996
BAE Systems (Operations) Limited, The Boeing Company, Lockheed Martin Corporation Airplanes
AD 96-03-04 · published Feb 28, 1996, effective Feb 28, 1996
Kelowna Flightcraft R & D Ltd. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to various General Dynamics (Convair) airplanes, that requires revising the Airplane Flight Manual to require that the flight crew limit the flap settings during certain icing conditions and air temperatures. This amendment is prompted by reports indicating that incidents involving uncommanded pitch excursions have occurred due to ice contaminated tailplane stall (ICTS) that occurred during or following flight in icing conditions. If flap settings are increased for landing when conditions for ICTS are present, elevator control could be affected adversely and the airplane could descend uncontrollably. The actions specified by this AD are intended to ensure that the flight crew is advised of the potential hazard related to increasing the flap settings when conditions for ICTS are present, and the procedures necessary to address it.
AD 94-05-05 R1 · published Feb 13, 1996, effective Feb 13, 1996
Continental Motors, Teledyne Continental Motors Engines
AD 94-14-10 · published Feb 13, 1996, effective Feb 13, 1996
Wright Aeronautical Division, Curtiss-Wright Corporation Engines
AD 95-26-01 · published Feb 22, 1996, effective Apr 22, 1996
AlliedSignal, Inc. (formerly Textron Lycoming) Models LTS101-650B1, -750B1, -650C, and -750C Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal, Inc. (formerly Textron Lycoming) Models LTS101-650B1, -750B1, -650C, and -750C turboshaft engines, that requires installation of an improved power turbine (PT) rotor and electronic PT rotor overspeed controller as a terminating action to the currently required inspections of AD 88-14-01. This amendment is prompted by reports of additional bearing failures since publication of AD 88-14-01, including one additional uncontained PT disk failure. The actions specified by this AD are intended to prevent PT overspeed and uncontained engine failure.
AD 96-04-01 · published Feb 29, 1996, effective Mar 15, 1996
AlliedSignal Inc. TFE731 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division) TFE731 series turbofan engines, that currently requires eddy current inspection of certain fan rotor disks for cracks, and replacement, if necessary, with serviceable parts. This amendment requires reinspection of 33 additional fan rotor disks, beyond the quantity of reinspections required by AD 93-25-16. This amendment is prompted by discrepancies in several magnetic tape records discovered as a result of recent improvements in the inspection tape review process. The actions specified by this AD are intended to prevent an uncontained failure of the fan rotor disk due to fatigue cracking in the dovetail slots, which can result in inflight engine shutdowns, severe secondary damage, and fan rotor assembly separation from the engine.
AD 96-04-02 · published Feb 29, 1996, effective Apr 29, 1996
Honeywell International Inc. Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming) ALF502L series turbofan engines, that establishes reduced retirement life limits for stage 1 and stage 3-7 compressors disks, and stage 2 turbine disks, and provides a drawdown schedule for disks already beyond the reduced retirement life limits. This amendment is prompted by new life analyses of these components. The actions specified by this AD are intended to prevent disk failure, which could result in an inflight engine shutdown and extensive engine damage.
AD 96-03-12 · published Feb 22, 1996, effective Apr 1, 1996
Glasflugel Gliders
This amendment adopts a new airworthiness directive (AD) that applies to Glasflugel Model Mosquito sailplanes. This action requires modifying the mounting studs on the lifting/tilting frame of the canopy system, repetitively inspecting the mounting stud, and incorporating flight manual revisions that specify a warning on emergency canopy deployment failure. Canopy system problems discovered during routine checks and periodic inspections of these sailplanes prompted the proposed action. The actions specified in this proposed AD are intended to prevent canopy system failure, which could result in loss of control of the sailplane.
AD 96-04-12 · published Feb 23, 1996, effective Mar 29, 1996
DG Flugzeugbau GmbH Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) DG-500M sailplanes. This action requires replacing the airbrake control hook-up shaft with a part of improved design. Reports of cracks in the welding of the lever to the torsion tube of the airbrake control prompted this action. The actions specified in this AD are intended to prevent an unintended extension of the airbrakes caused by failure of the lever to the torsion tube of the airbrake control, which could result in flutter, excessive rate of descent, and loss of control of the sailplane.
AD 96-02-01 · published Feb 29, 1996, effective Feb 29, 1996
Centrair Gliders
This amendment adopts a new airworthiness directive (AD) that applies to S.N. CentrAir Model 201 (all types) sailplanes. This action requires replacing all aileron balancing mass screws made of brass with screws made of steel, inspecting all steel screws for tightness, replacing any loose screws, and applying a normal screw thread safety bond. Incorrect fastening of the aileron balancing mass found on a Model 201 sailplane in France prompted this action. The actions specified in this AD are intended to prevent aileron failure and flutter caused by incorrect fastening of the aileron mass balance, which, if not detected and corrected, could result in loss of control of the sailplane.
