23 Airworthiness Directives: 18 airplane, 1 rotorcraft, 4 engine.
AD 94-04-02 · published Apr 4, 1994, effective Apr 4, 1994
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-215-6B11 series airplanes, that requires inspections to detect cracking in the rear engine mount struts, and replacement of struts with new struts, if necessary; and the eventual replacement of all struts with new struts. This amendment is prompted by reports of failures of these rear engine mount struts due to cracking that was caused by rosette welds on the shank of the struts not achieving full weld penetration during manufacture. The actions specified by this AD are intended to prevent failure of the rear engine mount struts, which could subsequently result in reduced structural integrity of the nacelle and engine support structure.
AD 94-05-06 · published Apr 4, 1994, effective Apr 4, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires modification or replacement of designated passenger cabin floor panels. This amendment is prompted by a report that, during manufacture, the inserts that attach the floor panels to the seat tracks and floor beams were installed using sealant rather than required adhesive. The actions specified by this AD are intended to prevent loss of the passenger cabin floor capability to support the airplane interior inertia loads under emergency landing conditions.
AD 94-07-06 · published Apr 5, 1994, effective May 5, 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 cracked or fractured H-11 steel bolts, replacement of discrepant bolts with ones made of Inconel 718 material, and eventual replacement of all H-11 steel bolts installed at certain critical locations with Inconel 718 material bolts. This amendment is prompted by reports of cracked and fractured H-11 steel bolts installed at certain critical locations of the airframe structure. The actions specified by this AD are intended to prevent the failure of attachment bolts in critical locations, which could lead to severe airframe damage.
AD 94-06-07 · published Apr 6, 1994, effective Apr 6, 1994
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A310 series airplanes. This action requires modification of the evacuation system regulator assembly in certain escape slides and slide/rafts installed on these airplanes. This amendment is prompted by reports indicating that the evacuation system regulator assembly functioned inappropriately, and cases of the evacuation system inflating when the regulator safety pin was removed. The actions specified in this AD are intended to prevent delayed or inadvertent inflation of an evacuation system, which could delay or impede the evacuation of passengers during an emergency, and to prevent possible injury to ground personnel during installation of the evacuation system.
AD 94-04-11 · published Apr 11, 1994, effective Apr 11, 1994
Twin Commander Aircraft LLC Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Twin Commander Aircraft Corporation (Twin Commander) Models 500S and 690B airplanes. This action requires removing a sample of the wing front spar lower cap (spar cap) material for examination, and, depending upon the results of that examination, inspecting or replacing the Airworthiness Directives: Twin Commander Aircraft Corporation Models 500S and 690B Airplanes . Reports of cracks caused by stress corrosion in the spar cap on several of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent failure of the wing structure caused by cracks in the spar cap.
AD 94-06-01 · published Apr 11, 1994, effective Apr 11, 1994
The Boeing Company 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 inspection of the ceiling pressure relief panels in the cargo compartments to determine if slotted attach points are present and, if not, modification of the panels. This amendment is prompted by a report that certain panels were manufactured without the appropriate slotted attach points. The actions specified by this AD are intended to ensure that the action of the cargo compartment pressure relief panels will enable the airplane to withstand a rapid decompression caused by a hole below the compartment floor.
AD 94-04-18 · published Apr 12, 1994, effective Apr 12, 1994
Textron Aviation Inc. Airplanes
This amendment supersedes Airworthiness Directive (AD) 92-24-01, which currently requires inspecting the elevator balance arm assemblies of certain Beech Aircraft Corporation Models 34C and T34C-1 airplanes to ensure that sufficient welds exist to secure the balance weight tube to the attachment plate, and also requires replacing the assembly if insufficient welds are found. The Federal Aviation Administration (FAA) has determined that the existing AD should also apply to certain Beech Model T34C airplanes. This action retains the requirements of AD 92-24-01 and incorporates these Beech Model T34C airplanes. The actions specified by this AD are intended to prevent separation of an elevator balance arm assembly from the elevator because of an insufficient weld, which could result in loss of control of the airplane.
AD 94-06-02 · published Apr 14, 1994, effective May 16, 1994
Short Brothers PLC Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Short Brothers PLC Model SD3-30, SD3-60, and SD3-SHERPA series airplanes, that currently requires an inspection to detect corrosion on the distance piece associated with the wing strut pick up on the stub wing, and repair of corroded parts. This amendment requires repetitive inspections to detect corrosion of repaired or reworked distance pieces and adjacent side plates; and provides a terminating action for the repetitive inspections. This amendment is prompted by reports of corrosion on the distance pieces and adjacent side plates of the wing strut pick up. The actions specified by this AD are intended to prevent failure of the distance piece and adjacent side plates, which could result in reduced strength of the wing strut attachment to the stub wing on the fuselage and, subsequently, reduced structural strength of the main wing.
AD 94-08-10 · published Apr 14, 1994, effective Jun 13, 1994
Viking Air Limited Airplanes
This amendment supersedes Airworthiness Directive (AD) 88-13-11, which currently requires repetitively inspecting both wing main spar lower cap angles for corrosion, and repairing or replacing any corroded part. This action retains these inspection and possible repair or replacement requirements, but eliminates the dual compliance time of both hours time-in-service (TIS) and calendar time. The Federal Aviation Administration (FAA) has determined that, since corrosion occurs regardless of whether the airplane is in service, the best compliance method for the proposed action is calendar time. The actions specified by this AD are intended to prevent failure of the wing structure because of corroded wing main spar lower cap angles.
AD 94-06-10 · published Apr 15, 1994, effective Apr 15, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-8 series airplanes, that currently requires the incorporation of specific maximum brake wear limits into the maintenance inspection program. That action was prompted by an accident in which a transport category airplane executed a rejected takeoff (RTO) and was unable to stop on the runway due to worn brakes. The actions specified by that AD are intended to prevent loss of braking effectiveness during a high energy RTO. This amendment requires that a new part number be permanently marked on certain brakes when modified to meet the new brake wear limits.
AD 94-08-14 · published Apr 20, 1994, effective May 20, 1994
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Corporate Jets Model BAe 125-1000A series airplanes, that requires replacement of the white 'EMERG CONTCTRS' annunciator screen on roof panel 'CG' of the flight deck with an amber screen. This amendment is prompted by a report that the annunciator screen currently installed on these airplanes is not a color that would alert the flight crew that corrective action may be necessary. The actions specified by this AD are intended to ensure that the flight crew is alerted to conditions when standby electrical power is not available.
AD 94-09-02 · published Apr 20, 1994, effective May 20, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect damage of the auxiliary power unit (APU) power feeder cable installation, repair of damaged cables, and modification of the cable installation. This amendment requires an inspection of previously modified airplanes to determine whether a spacer or "stand off" has been installed, and installation of those items, if necessary. This amendment is prompted by reports of generator power feeder cables electrically shorting to the airplane structure due to chafing. The actions specified by this AD are intended to prevent the APU power feeder cable from chafing against adjacent structures, which could result in electrical shorting and arcing, and a fire below the cabin floor.
AD 94-08-03 · published Apr 21, 1994, effective May 23, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires visual inspection to detect inward buckling of the left and right main landing gear (MLG) pistons, and modification or replacement of the rebound check valves with new valves. If inward buckling is detected, this AD also requires replacement of the MLG piston with a serviceable piston. This amendment is prompted by failures of the MLG piston on Model DC-10 series airplanes. The actions specified by this AD are intended to prevent failure of the MLG piston and the subsequent reduced controllability of the airplane during landing.
AD 94-08-04 · published Apr 21, 1994, effective May 23, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes, and C-9 (military) airplanes, that currently requires inspections to detect cracking in the skin and doublers around the upper anticollision light cutout, and repair, if necessary. This amendment expands the applicability to include additional Model DC-9-80 series airplanes and Model MD-88 airplanes, and requires the performance of stress coining procedures on the plate nut clearance holes or installation of shims and an external doubler. This amendment is prompted by a report that stress coining procedures were not performed on the plate nut clearance holes of the upper anticollision light doublers during production of certain airplanes. The actions specified by this AD are intended to prevent crack growth in the doublers, which could result in damage to the adjacent structure, and subsequent loss of cabin structural integrity.
AD 94-05-08 · published Apr 22, 1994, effective Apr 22, 1994
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that requires modification of the electrical power supply system. This amendment is prompted by a report that a single phase fault current can cause sequential failure of all onboard main electrical generators. The actions specified by this AD are intended to prevent such failures and subsequent loss of electrical power sources onboard the airplane.
AD 94-09-10 · published Apr 26, 1994, effective May 11, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 757 series airplanes. This action requires revising the Non-Normal Procedures Section of the FAA-approved Airplane Flight Manual (AFM) to include procedures that will enable the flight crew to identify fuel system leaks and to take appropriate action to prevent further fuel loss. This amendment is prompted by reports that flight crew procedures related to fuel system leaks are not defined adequately in the FAA-approved AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard related to fuel exhaustion due to undetected leakage, and the procedures necessary to address it.
AD 94-08-08 · published Apr 29, 1994, effective Apr 29, 1994
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires installation of fusible trunnion pins in the shock struts and drag braces of the main landing gear (MLG). This amendment is prompted by a report of incorrectly manufactured trunnion pins that may cause the MLG to compromise the structural integrity of the wing fuel tanks. The actions specified in this AD are intended to prevent damage to the wing fuel tanks and the resultant fuel spillage and fire hazard when the maximum intended design load limits are exceeded during landing.
AD 94-09-11 · published Apr 29, 1994, effective May 16, 1994
Hawker Beechcraft Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Raytheon Corporate Jets Model BAe 125-1000A and Hawker 1000 series airplanes. This action requires inspections of the thrust reverser system for integrity, and correction of any discrepancy found. This amendment is prompted by a report that there is a possibility of failure of the drive links (or attachments) on the thrust reversers of these airplanes due to the single link design concept of the thrust reverser link and lock system. This condition, if not corrected, could result in inadvertent deployment of a thrust reverser during flight. The actions specified in this AD are intended to prevent a significant reduction in the controllability of the airplane due to an in-flight deployment of a thrust reverser. Comments for inclusion in the Rules Docket must be received on or before June 28, 1994.
AD 93-08-14 · published Apr 6, 1994, effective Apr 6, 1994
Bell Helicopter Textron, A Division of Textron Canada Helicopters
AD 94-07-05 · published Apr 19, 1994, effective Apr 19, 1994
General Electric Company Engines
AD 94-07-03 · published Apr 20, 1994, effective Jun 6, 1994
Honeywell International Inc. Engines
This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to certain AlliedSignal, Inc. TFE731-2A and -3 series turbofan engines, that currently requires a revision to the Limitations Section of the Airplane Flight Manual (AFM) to provide procedures for monitoring engine performance in order to detect A5 seal cracking and opening before first stage low pressure (LP) turbine disk failure. Additionally, the revision to the AFM requires a procedure for verification of LP rotor (N1) rotation during engine start to detect rotor lockup due to first stage LP turbine rotor creep. This amendment maintains those requirements for engine and flight data monitoring, adds a more stringent procedure for verifying rotor lockup during engine start and for detection of rubbing noises, and requires replacement of A5 seals with a redesigned seal. Replacement of A5 seals with a redesigned seal constitutes terminating action to the monitoring requirements.This amendment is prompted by reports of an additional first stage LP turbine disk failure due to A5 seal cracking. The actions specified by this AD are intended to prevent uncontained failure of the first stage LP turbine disk.
AD 94-07-04 · published Apr 21, 1994, effective May 23, 1994
General Electric Company Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80A series turbofan engines, that requires an inspection for cracks in the stage 1 high pressure turbine (HPT) disk rim bolt holes. This amendment is prompted by a report of an uncontained stage 1 HPT disk failure, which resulted in an aborted takeoff. The actions specified by this AD are intended to prevent an uncontained stage 1 HPT disk failure, which could result in an inflight engine shutdown, aborted takeoff, or damage to the aircraft.
AD 94-09-06 · published Apr 22, 1994, effective May 2, 1994
Hamilton Standard Division, Hamilton Sundstrand Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Hamilton Standard 14RF series, 14SF series, and Hamilton Standard/British Aerospace 6/5500/F series propellers. This action requires a one-time inspection for cracks in the propeller blade taper bore. This amendment is prompted by reports of two incidents where the incident aircraft lost a portion of a propeller blade inflight. The actions specified in this AD are intended to prevent loss of a propeller blade due to cracks initiating in the blade taper bore, that can result in possible aircraft damage, and possible loss of aircraft control.
