24 Airworthiness Directives: 18 airplane, 3 rotorcraft, 2 engine, 1 appliance.
AD 96-05-01 · published Mar 4, 1996, effective Apr 3, 1996
McDonnell Douglas Model DC-9-80 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes, that currently requires inspection and replacement of certain suspect horizontal stabilizer primary trim motors. That AD was prompted by an analysis which revealed that certain incorrectly manufactured motor shafts could fail prematurely and, in turn, cause the primary trim motor to fail. The actions specified in that AD are intended to prevent such failures of the primary trim motor, which could ultimately result in reduced controllability of the airplane. This amendment expands the applicability of the existing AD to include additional affected airplanes.
AD 95-13-12 R1 · published Mar 7, 1996, effective Jul 19, 1995
The Boeing Company Airplanes
This amendment clarifies information in an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires tests, inspections, and adjustments of the thrust reverser system. That AD also requires installation of a terminating modification and repetitive follow-on actions. The actions specified in that AD are intended to prevent possible discrepancies that exist in the current thrust reverser control system, which could result in inadvertent deployment of a thrust reverser during flight. This amendment clarifies the requirements of the current AD by specifying a revised number of pound-inches of torque operators should use when performing the torque check of the cone brake of the center drive unit (CDU). This amendment is prompted by information from the manufacturer that a current requirement of the AD requires clarification.
AD 96-05-04 · published Mar 7, 1996, effective Mar 22, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires the installation of a control cable guard to separate the flight control cables from the electrical wiring of the aft left cabin attendant console. This amendment is prompted by reports of burnt electrical wire cable in the cabin attendant console that was caused by chafing of the wire cable against certain flight control cables. The actions specified in this AD are intended to prevent chafing of these wire cables, which could result in a fire hazard or damage to critical flight control cables.
AD 96-05-06 · published Mar 7, 1996, effective Mar 22, 1996
Canadair Model CL-215-1A10 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Canadair Model CL-215-1A10 series airplanes. This action requires a one-time inspection of the main distribution center for loose or missing attachment hardware, and correction of any discrepancy identified. This amendment is prompted by a report of total loss of electrical power on one airplane during flight, which was caused by shorting out of the voltage regulator in the main distribution center. The actions specified in this AD are intended to prevent total electrical failure during flight, which could adversely affect the continued safe flight of the airplane.
AD 96-04-04 · published Mar 11, 1996, effective Mar 11, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires repetitive inspections to detect corrosion and cracking of the shortening mechanism pins in the main landing gear (MLG), and repair or replacement, if necessary. It also requires replacement of the shortening mechanism pin and retraction mechanism pins; the forward pintle pin; the shortening mechanism bellcrank pin; and the bellcrank subassembly of the shortening mechanism. This amendment is prompted by reports of failure of the shortening mechanism pins due to improper grinding of the chrome plating during manufacture, which led to the initiation of stress corrosion and cracks. The actions specified in this AD are intended to prevent failure of these pins, which could lead to a significant reduction of the shock absorber capability or damage to various components of the MLG, and eventually could lead to the failure of the MLG.
AD 96-05-07 · published Mar 11, 1996, effective Apr 10, 1996
Boeing Model 757 Series Airplanes Equipped with Pratt & Whitney Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires repetitive inspections to detect cracking in the midspar fuse pins and replacement of certain fuse pins. This amendment requires inspection of certain fuse pins, and replacement of certain fuse pins with certain other fuse pins. This amendment also requires inspections of refinished straight fuse pins and replacement of cracked refinished straight fuse pins with certain other straight fuse pins. This amendment is prompted by the development of new corrosion- resistant steel fuse pins. The actions specified by this AD are intended to prevent cracking of the midspar fuse pins, which may lead to separation of the strut and engine from the wing of the airplane.
AD 96-03-06 · published Mar 13, 1996, effective Mar 13, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream ATP airplanes, that requires inspections to detect fatigue cracking and corrosion in the gussets of the rear passenger door and rear baggage door apertures, and replacement of the gussets, if necessary. This amendment is prompted by fatigue tests which indicated that fatigue cracking and corrosion can occur in these gussets. The actions specified by this AD are intended to prevent degradation of the structural integrity of the fuselage pressure vessel due to the problems associated with cracking and corrosion in the gussets of the rear passenger door and rear baggage door apertures.
AD 96-06-06 · published Mar 21, 1996, effective Apr 22, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, -300, and SP series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit the use of the autoland function. This amendment also requires installation of a diode and a marker on certain shelves and making wiring changes to the flight mode annunciator of the autopilot/flight director system, which terminates the requirements for the AFM limitation. This amendment is prompted by a report that the flightcrew was unaware of the configuration of the autoland system during landing. The actions specified by this AD are intended to ensure flightcrew awareness of the configuration of the autoland system in the event of a change from fail-operational to fail-passive mode.
AD 96-06-08 · published Mar 21, 1996, effective Apr 22, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 series airplanes, and Model KC- 10A (military) airplanes. This amendment requires inspection(s) to detect cracks of the attach bolts of the front spar support fitting of each wing, and replacement of attach bolts with ones that are corrosion-resistant. This amendment is prompted by a report of failure of the attach bolts of the front spar fitting as a result of corrosion pitting. The actions specified by this AD are intended to prevent such stress corrosion, which could lead to the failure of the attach bolts of the front spar; this situation could result in reduced structural integrity of the wing.
AD 96-06-09 · published Mar 21, 1996, effective Apr 5, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to three Boeing Model 767 series airplanes, serial numbers 26847, 27048, and 27049. This action requires a functional check of the trailing edge flap drive bypass valve, and eventual replacement of the control valve module for the trailing edge flaps with an improved module. This amendment is prompted by reports of failure of the bypass valve motor in the control valve module of the trailing edge flaps due to hydraulic fluid contamination. The actions specified in this AD are intended to prevent such failure, which could result in loss of shutdown protection for the trailing edge flap drive; this condition could result in reduced controllability of the airplane in the event of uncommanded or asymmetrical flap motion.
AD 96-05-05 · published Mar 22, 1996, effective Mar 22, 1996
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires replacement of the inlet filter in the spoiler servo-controls and installation of a lockwire. This amendment is prompted by reports of leakage of hydraulic fluid at the inlet filter plug of the spoiler actuator as a result of inadequate torque of the filter plug, and reports of broken lockwires. The actions specified in this AD are intended to prevent loss of hydraulic fluid to the extent that a complete failure of the associated hydraulic system could occur. Such a loss, when combined with other hydraulic system failures, could reduce the controllability of the airplane.
AD 95-17-09 R1 · published Mar 25, 1996, effective May 13, 1996
M7 Aerospace LLC Airplanes
This amendment revises Airworthiness Directive (AD) 95-17-09, which requires relocating the left-hand (LH) and right-hand (RH) essential bus current limiters (225 amp) to the battery bus (main bus tie) on certain Fairchild Aircraft SA226 and SA227 series airplanes. The Federal Aviation Administration (FAA) has determined that the applicability of the current AD should be changed to reflect a different serial number range and model designation of certain SA227 series airplanes. This action retains the essential bus current limiter relocations required by AD 95-17-09, and revises the Applicability section of that AD. The actions specified by this AD are intended to prevent failure of the LH and RH essential bus when engine failure results in a blown generator current limiter, which could result in loss of airplane electrical power.
AD 96-04-06 · published Mar 25, 1996, effective Mar 25, 1996
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires replacement of the relays in the forward electronics rack of the braking system of the landing gear with new relays. This amendment is prompted by reports of loss of the systems of the braking/steering control unit (BSCU) on these airplanes due to electrical overvoltage of the relays. The actions specified by this AD are intended to prevent such electrical overvoltage of the relays, which could result in the loss of the BSCU systems, and subsequent loss of the antiskid functions and nose wheel steering of the airplane.
AD 96-04-07 · published Mar 25, 1996, effective Mar 25, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 and A300-600 series airplanes. This amendment requires repetitive inspections to detect distortion and/or cracks on the attachment brackets of the backrest recline control locks of certain seats. It also provides for an optional modification which, if accomplished, terminates the repetitive inspections. This amendment is prompted by a report of failure of the bracket of the backrest recline control lock on a seat due to fatigue-related cracking. The actions specified by this AD are intended to prevent fatigue-related cracking and/or distortion, which could result in failure of the seat backrest attach fitting, and the subsequent uncommanded 50 angle recline of the pilot or co-pilot seat; this situation could lead to the temporary inability of the pilots to control the airplane.
AD 96-04-09 · published Mar 25, 1996, effective Mar 25, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0100 series airplanes, that requires an inspection to detect the presence of a drain hole in certain mounting frames of the auxiliary power unit (APU). If a drain hole is present, the AD requires an inspection to detect corrosion of the mounting frame, and eventual replacement of the mounting frame. This amendment is prompted by a report indicating that corrosion was found on a number of mounting frames of the APU. The actions specified by this AD are intended to prevent such corrosion, which could lead to failure of the frame and consequently render the APU inoperative and/or create a potential fire hazard.
AD 96-04-10 · published Mar 25, 1996, effective Mar 25, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-231 series airplanes, that requires modification of the fire wall of each engine. This amendment is prompted by a report of a fire in the engine of an in-service airplane due to the fire wall being improperly sealed during production. The actions specified by this AD are intended to prevent propagation of a fire through a gap (opening) in the fire wall in the event of an engine fire, as a result of improperly sealed fire wall.
AD 96-07-01 · published Mar 25, 1996, effective Apr 24, 1996
McDonnell Douglas Model DC-10-10, -15, -30, and -40 Series Airplanes, and KC-10A (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires visual inspections to detect failure of the attachments located in the banjo No. 4 fitting of the vertical stabilizer. This amendment also requires an eddy current inspection to detect cracking of the flanges and bolt holes of that fitting, and repair or replacement of attachments. This amendment is prompted by reports of failed attachments of the vertical stabilizer; the failures are attributed to fatigue. The actions specified by this AD are intended to prevent loss of the fail safe capability of the vertical stabilizer due to cracking of its attachments.
AD 96-07-04 · published Mar 29, 1996, effective Apr 29, 1996
Fokker Model F27 Mark 050 and Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 and Model F28 Mark 0100 series airplanes, that requires an inspection to verify that adequate clearance exists between the insulation screen and the two adjacent terminal bolts, and replacement of the circuit breaker terminal bolts with new bolts, if necessary. This amendment is prompted by a report that circuit breaker terminal bolts that were too long were discovered installed in the circuit breaker panels. The actions specified by this AD are intended to prevent damage to the insulation screen between adjacent rows of circuit breakers, as the result of a circuit breaker terminal bolt being too long; this condition could lead to electrical arcing and loss of the associated electrical system, which could result in the potential for an electrical fire.
AD 96-06-03 · published Mar 19, 1996
The Enstrom Helicopter Corporation Model F-28, F-28A, F-28C, F-28C-2, F-28F, 280, 280C, 280F, and 280FX Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to The Enstrom Helicopter Corporation (Enstrom) Model F-28, F-28A, F-28C, F-28C-2, F-28F, 280, 280C, 280F, and 280FX helicopters, that currently requires initial and repetitive inspections of a certain main rotor transmission clutch assembly (clutch assembly) for bearing roughness, noise, lock-up, or improper oil level and, if necessary, replacement of the clutch assembly. The existing AD also requires replacement of the clutch assembly at certain time-in-service intervals. This amendment requires the same inspections and replacements as required by the existing AD, but would provide for installation of an additional approved replacement part number and provide a reference to three additional manufacturer service documents. This amendment is prompted by the approval of an additional replacement clutch assembly; the manufacturer's issuance of additional service information, and the need to correct a service information letter's number. The actions specified by this AD are intended to prevent failure of the clutch assembly, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
AD 96-06-10 · published Mar 26, 1996, effective May 28, 1996
AlliedSignal, Inc. LTS101 Series Turboshaft Engines Installed on Eurocopter France Model AS-350D and SA- 366G1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal, Inc. (formerly Textron Lycoming) LTS101 series turboshaft engines installed on Eurocopter France (formerly Aerospatiale) Model AS-350D and SA-366G1 helicopters, that requires incorporation of design modifications to the power turbine (PT) rotor. This amendment is prompted by reports of PT disk failures after No. 3 bearing failures. The actions specified by this AD are intended to prevent an uncontained engine failure due to a PT disk failure.
AD 96-07-03 · published Mar 28, 1996, effective May 2, 1996
Societe Nationale Industrielle Aerospatiale and Eurocopter France Model AS 350B, BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Societe Nationale Industrielle Aerospatiale and Eurocopter France (Eurocopter France) Model AS 350B, BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N helicopters, without an autopilot installed, that requires a visual inspection to determine whether the cyclic pitch change control rod (rod) end fittings were safetied, and removal and replacement of the rod if the rod end fittings were not safetied. This amendment is prompted by a manufacturer's report that some of the rod end fittings had not been safetied at the factory. The actions specified by this AD are intended to prevent loss of tightening torque on the adjustment nuts of the rod, shifting of the neutral point of the cyclic stick, reduction in the amount of available movement of the cyclic stick in the roll axis, and subsequent reduction in the controllability of the helicopter.
AD 96-05-03 · published Mar 18, 1996, effective Apr 2, 1996
AlliedSignal Inc. TFE731 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division) TFE731 SeriesTurbofan Engines, that currently requires inspection of fan rotor disks within certain schedules. This amendment requires initial and repetitive eddy current inspections using an improved, more definitive procedure for detecting fan rotor disk dovetail slot cracks. Also, this amendment adds additional engine models and fan rotor disk part numbers and disallows fluorescent penetrant inspection (FPI) as an alternative inspection method for detecting fan rotor disk dovetail slot cracks. This amendment is prompted after additional analyses revealed that stress levels in the fan rotor disk dovetail slots for the applicable engine models are higher than initially calculated. The actions specified by this AD are intended to prevent uncontained failure of fan rotor disks 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 96-06-11 · published Mar 26, 1996, effective May 28, 1996
Honeywell International Inc. Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain AlliedSignal Inc. (formerly Garrett Engine Division) TPE331 series turboprop engines, that establishes cyclic retirement lives for certain compressor components. This amendment is prompted by manufacturer's engine testing and analysis that indicate that if these compressor components continue in service without an established retirement life, accumulative cyclic effects may result in a fatigue failure. The actions specified by this AD are intended to prevent fatigue failure of engine compressor components and an inflight engine shutdown.
AD 95-25-08 · published Mar 21, 1996, effective May 20, 1996
Royal Inventum Company DR1 and DR6 Series Galley Water Heaters
This amendment adopts a new airworthiness directive (AD), applicable to Royal Inventum Company DR1 and DR6 Series Galley Water Heaters, that requires the installation of a pressure relief valve, and 3-phase safety devices on each Royal Inventum Company DR1 and DR6 series galley water heater. This amendment is prompted by a report of a Royal Inventum DR6 water heater explosion during an overheat test at a maintenance facility. The actions specified by this AD are intended to prevent explosions of Royal Inventum Company DR1 and DR6 series galley water heaters, which could cause personal injury or galley damage to the aircraft.
