28 Airworthiness Directives: 19 airplane, 7 rotorcraft, 2 engine.
AD 94-15-17 · published Aug 3, 1994, effective Sep 2, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of certain fuselage longitudinal lap joints, repair of any cracking found, and replacement of the countersunk fasteners in those lap joints with protruding head fasteners. This amendment is prompted by a structural reassessment of Model 747 series airplanes. The actions specified by this AD are intended to prevent skin cracking in the longitudinal lap joints of certain stringers, which can lead to rapid decompression of the airplane.
AD 94-14-15 · published Aug 5, 1994, effective Aug 5, 1994
Dassault Aviation Airplanes
AD 94-14-17 · published Aug 8, 1994, effective Aug 8, 1994
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires either the removal of the girt bar visual indicator brackets on passenger exit doors, or modification of the lanyard connecting the survival kit to the slide/raft. This amendment is prompted by a report that, during an emergency evacuation demonstration, the lanyard became entangled on the girt bar indicator mechanism, and subsequently prevented an exit door from opening fully to a locked position. The actions specified by this AD are intended to prevent the lanyard from becoming entangled and interfering with proper opening of the exit door, a situation which could impede the successful evacuation of passengers through the door during an over water operation where ditching is required.
AD 94-15-09 · published Aug 8, 1994, effective Aug 8, 1994
ATR - GIE Avions de Transport R gional Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Aerospatiale Model ATR72 series airplanes. This action requires inspections to detect damage, corrosion, or cracking of the hinge pin on each shock absorber on the main landing gear (MLG), and repair or replacement of the pins, if necessary. This amendment is prompted by reports of rupture of certain hinge pins due to stress corrosion of the pins in the shock absorber on the MLG on Model ATR72 series airplanes. The actions specified in this AD are intended to prevent loss of the MLG during a hard landing due to malfunction of the shock absorber on the MLG.
AD 94-14-05 · published Aug 10, 1994, effective Aug 10, 1994
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires removal of the actuator from the fuel-ballast transfer valve, and installation of a locking device on the fuel-ballast transfer valve. This amendment is prompted by a report that the fuel-ballast transfer valve on certain airplanes must be modified to ensure the valve is closed at all times. If the transfer valve is open during flight, the fuel supply to the engines may be reduced during cross-feed operation to the extent that fuel starvation could occur. The actions specified by this AD are intended to prevent engine flameout due to fuel starvation.
AD 94-14-08 · published Aug 10, 1994, effective Aug 10, 1994
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-600-2B16 series airplanes, that requires inspection to detect chafing of the wiring harness of the air driven generator (ADG), modification of the wiring harness, and repair of any chafed harness. This amendment is prompted by a report that the wiring harness on certain airplanes was produced in a configuration that is subject to chafing and electrical shorting. The actions specified by this AD are intended to prevent chafing or shorting of the wiring harness, which could result in loss of ADG power to the essential bus when the ADG is deployed during an emergency situation.
AD 94-15-10 · published Aug 11, 1994, effective Aug 11, 1994
ATR - GIE Avions de Transport R gional Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Aerospatiale Model ATR42-300 and -320 series airplanes. This action requires an inspection to verify that the cables supplying power to the aileron trim are adequately protected and to detect any damage to these cables. This amendment also requires installation of protective sleeves on unprotected cables, and replacement of damaged cables. This amendment is prompted by reports of a short circuit of these cables due to worn protective sleeves. The actions specified in this AD are intended to prevent short circuiting of the cables that supply power to the aileron trim, which could lead to loss of aileron trim control.
AD 94-15-18 · published Aug 11, 1994, effective Sep 12, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires that the FAA-approved maintenance inspection program include inspections which will give no less than the required damage tolerance rating (DTR) for each Structural Significant Item (SSI). This amendment requires the inclusion of additional airplanes to the candidate fleet. This amendment is prompted by a recommendation from the Airworthiness Assurance Working Group, Model 747 Structures Task Group. The actions specified by this AD are intended to ensure the continued structural integrity of the total Boeing Model 747 fleet.
AD 94-16-03 · published Aug 11, 1994, effective Jan 27, 1992
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires inspections, adjustments, and functional tests of the thrust reverser system. This amendment adds a requirement for installation of an additional thrust reverser system locking feature, periodic functional tests of that locking feature following its installation, and repair of any discrepancy found. This amendment is prompted by the identification of a modification that ensures that the level of safety inherent in the original type design of the thrust reverser system is further enhanced. The actions specified by this AD are intended to prevent possible discrepancies in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
AD 94-16-05 · published Aug 15, 1994, effective Sep 14, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections to detect cracking, corrosion, and wear of various components of the main landing gear (MLG) brake assembly, and correction of discrepancies. This amendment is prompted by reports indicating that components in the MLG assembly have been damaged due to the consequences of vibration in the brake assembly. The actions specified by this AD are intended to minimize the exposure of the brake assembly to the consequences of a vibratory condition that could ultimately lead to failure of components of the MLG; such failure could severely affect the braking capability of the airplane while on the ground.
AD 94-17-01 · published Aug 15, 1994, effective Sep 14, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking in the upper row of fasteners in the lower lobe of the fuselage skin lap joints, and repair, if necessary. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their design life goal. The actions specified by this AD are intended to prevent separation of the fuselage skin and rapid loss of pressure in the airplane. This AD also relates to the recommendations of the Airworthiness Assurance Working Group assigned to review Model 747 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.
AD 94-17-03 · published Aug 15, 1994, effective Sep 14, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires inspections, adjustments, and functional checks of the thrust reverser system; installation of a terminating modification; and repetitive operational checks of the gearbox locks and the air motor brake following accomplishment of the modification. This amendment is prompted by the identification of a modification that ensures that the level of safety inherent in the original type design of the thrust reverser system is further enhanced. The actions specified by this AD are intended to prevent possible discrepancies that exist in the current thrust reverser control system, which could result in an inadvertent deployment of a thrust reverser during flight.
AD 94-16-01 · published Aug 18, 1994, effective Aug 18, 1994
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A340-211 and -311 series airplanes. This action requires modifying the bonding leads on the fuel quantity indicating (FQI) probes or the temperature sensor, on the fuel low pressure inlet pipe next to the compensator, and on the jet pump. This amendment is prompted by results of a quality survey, which revealed that there may be insufficient clearance between several bonding leads and certain FQI system probes or the temperature sensor, and between the bonding leads and the FQI probes and the compensator. The actions specified in this AD are intended to eliminate such insufficient clearance, which could lead to electrical arcing and a resultant fire in the event of a lightning strike.
AD 94-17-08 · published Aug 22, 1994, effective Sep 21, 1994
Viking Air Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that requires removal of the aluminum or brass hardware in the firewall terminal block assembly and replacement with steel hardware. This amendment is prompted by the results of an investigation, which revealed that corroded aluminum washers in the DC firewall terminal block assembly may loosen the electrical connections. The actions specified by this AD are intended to prevent interruption of DC electrical power due to connections that may have loosened from corrosion.
AD 94-17-09 · published Aug 22, 1994, effective Sep 21, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, -300, and -400 series airplanes, that requires various modifications of certain evacuation ramp/slides. This amendment is prompted by reports of several evacuation ramp/slide malfunctions. The actions specified by this AD are intended to prevent delayed inflation of evacuation ramp/slides, which could delay or impede the evacuation of passengers during an emergency.
AD 94-17-10 · published Aug 22, 1994, effective Sep 21, 1994
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-8 series airplanes, that requires removal of the aluminum or brass hardware in the firewall terminal block and battery shunt cable assemblies and replacement with steel hardware. This amendment is prompted by the results of an investigation, which revealed that corroded aluminum washers in the DC firewall terminal block and battery shunt cable assemblies may loosen the electrical connections. The actions specified by this AD are intended to prevent interruption of DC electrical power due to connections that may have loosened from corrosion.
AD 94-15-11 · published Aug 29, 1994, effective Aug 29, 1994
Fokker Services Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F-27 series airplanes, that requires the implementation of a corrosion prevention and control program either by accomplishing specific tasks or by revising the maintenance inspection program to include such a program. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in transport category airplanes that are approaching or have exceeded their economic design goal; these incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the airplane due to the problems associated with corrosion.
AD 94-17-17 · published Aug 31, 1994, effective Sep 30, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections of the inboard and outboard strut chords, stiffeners, and web to detect cracks and loose fasteners; repair of the chords, stiffeners, or web, if necessary; and replacement of any loose fastener. This amendment is prompted by reports of fatigue cracks and loose fasteners found in the forward lower spar web of the inboard strut on Model 747 series airplanes equipped with Pratt & Whitney JT9D-3 and JT9D-7 series engines. The actions specified by this AD are intended to prevent separation of the strut from the wing of the airplane due to fatigue cracking.
AD 94-15-08 · published Aug 9, 1994, effective Aug 9, 1994
Robinson Helicopter Company Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company Model R22 helicopters. This action requires an initial inspection and repetitive checks and visual inspections for corrosion and cracks on certain main rotor blades. This amendment is prompted by reports of chordwise cracks found in the main rotor blades. The actions specified in this AD are intended to prevent abnormal in-flight vibrations, failure of the main rotor blade, and subsequent loss of control of the helicopter.
AD 94-14-20 · published Aug 11, 1994, effective Sep 15, 1994
Sikorsky Aircraft Corporation Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Sikorsky Aircraft Model S-76A series helicopters, that currently requires an initial and repetitive inspections of the tail rotor (T/R) blade spar elliptical centering plug (centering plug) for disbonding and adds a retaining pad between the T/R gearbox output shaft and the inboard T/R spar. This amendment requires the same design changes and procedures as the previous AD, except that it would eliminate the 500 hours' time-in-service repetitive inspections for centering plug disbonding. This amendment is prompted by an improved bonding and repair procedure and the lack of reports concerning the movement or disbonding of the centering plug. The actions specified by this AD are intended to prevent the centering plug from disbonding and moving out of position, which could result in loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 94-13-03 · published Aug 12, 1994, effective Aug 12, 1994
Enstrom Helicopter Corporation, The Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to The Enstrom Helicopter Corporation Model F-28C, F-28C-2, F-28F, 280C, 280F, and 280FX series helicopters. This action requires a visual inspection for cracks in the tail rotor spindle; a repetitive dye penetrant inspection for cracks; and removal and replacement of the tail rotor spindle upon reaching 1,200 hours' time-in-service (TIS). This amendment is prompted by five reports of cracked tail rotor spindles. The actions specified in this AD are intended to prevent failure of the tail rotor spindle, loss of directional control, and subsequent loss of control of the helicopter.
AD 94-12-06 · published Aug 15, 1994, effective Sep 19, 1994
Schweizer Aircraft Corporation Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A series helicopters, that currently requires repetitive inspections and replacement of certain lower belt drive pulley bearings (pulley bearings). This amendment retains the present AD requirements and adds an alternate pulley bearing to the requirements of the AD. This amendment is prompted by the introduction of an alternate pulley bearing into service by Schweizer Aircraft Corporation. The actions specified by this AD are intended to prevent failure of the pulley bearings, loss of power to the rotor systems, and subsequent loss of control of the helicopter.
AD 93-24-13 · published Aug 26, 1994, effective Aug 26, 1994
Enstrom Helicopter Corporation, The Helicopters
AD 94-15-07 · published Aug 26, 1994, effective Aug 26, 1994
Bell Helicopter Textron Canada Limited Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. Model 206A, 206B, 206L, 206L-1, 206L-3, and 206L-4 series helicopters. This action requires a one-time inspection for cracks in a portion of the main rotor blade (blade) trailing edge and the inboard trim tab, and replacement of the blade or trim tab as necessary. This amendment is prompted by reports of cracks in the blade trailing edge near the inboard trim tab. The actions specified in this AD are intended to prevent failure of a main rotor blade and subsequent loss of control of the helicopter.
AD 94-16-04 · published Aug 31, 1994, effective Oct 5, 1994
Schweizer Aircraft Corporation Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH55A series helicopters, that requires a one-time visual inspection to detect missing or damaged tail rotor pedal bulkhead gussets (gussets), loose or missing gusset rivets, and initial installation of missing gussets or replacement of damaged gussets and rivets, if necessary. This amendment is prompted by reports of missing or damaged tail rotor pedal bulkhead gussets and loose or missing gusset rivets. The actions specified by this AD are intended to prevent failure of the tail rotor pedal support structure that could result in loss of tail rotor control and subsequent loss of control of the helicopter.
AD 94-15-16 · published Aug 15, 1994, effective Oct 14, 1994
Pratt & Whitney Division Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT9D series turbofan engines, that requires a one-time modification and overhaul of engine control system accessories. This amendment is prompted by multiple engine surge and power loss events caused by deterioration of internal components of engine control system accessories. The actions specified by this AD are intended to prevent the loss of engine compressor surge margin caused by the deterioration of engine control system accessories, resulting in an engine surge, and subsequent power loss or inflight engine shutdown.
AD 94-17-16 · published Aug 31, 1994, effective Sep 15, 1994
General Electric Company Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Aircraft Engines (GEAE) CT7 series turboprop engines, that currently requires a one-time ultrasonic inspection of a suspect population of propeller shafts for metallurgical defects, and if necessary, replacement with a serviceable part. This amendment extends the compliance time for the required ultrasonic inspection on certain propeller shafts. This amendment is prompted by information indicating that the equipment necessary to perform the ultrasonic inspection is less available than originally assumed. The actions specified by this AD are intended to prevent failure of the propeller shaft, which can result in separation of the propeller from the propeller shaft and possible damage to the aircraft.
