18 Airworthiness Directives: 16 airplane, 2 rotorcraft.
AD 91-25-08 R1 · published Nov 4, 1994, effective Nov 4, 1994
Cessna Aircraft Company Airplanes
AD 94-22-02 · published Nov 4, 1994, effective Nov 4, 1994
Revo, Incorporated Airplanes
AD 94-22-07 · published Nov 10, 1994, effective Dec 12, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-8-70 series airplanes, that currently requires replacement of all attachment screws at the exhaust nozzle plug splice, and a check of nut plates for running torque and replacement of nut plates, if necessary. This amendment requires modification of the engine exhaust plug assemblies as terminating action for the currently required replacement and check. This amendment is prompted by reports of loose or missing attachments at the splice joint of the engine forward and aft exhaust plugs, and loss of the rear exhaust plug following an engine bird strike. The actions specified by this AD are intended to prevent reduced integrity of the engine exhaust plug installation, which may lead to separation of exhaust plugs from the airplane, and create a hazard to persons and property on the ground.
AD 94-22-11 · published Nov 10, 1994, effective Dec 12, 1994
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model ATP airplanes, that requires modification of the power supply for the communications system. This amendment is prompted by reports of loss of power to the communications system due to an electrical fault in the ground crew jack box or the handset of the public address (PA) system. The actions specified by this AD are intended to prevent the inability of the flight crew to communicate with passengers via the PA system and with air traffic control due to loss of power to the communication system, which may lead to unsafe operation of the airplane.
AD 94-20-12 · published Nov 14, 1994, effective Nov 14, 1994
Gulfstream Aerospace LP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain IAI Model 1125 Westwind Astra airplanes, that requires relocation of the ground cable in the slat power drive unit. This amendment is prompted by a report that the drive system for the leading edge slat stopped in transit during flight on a Model 1125 Westwind Astra airplane. This incident was caused by an improper ground connection for the electric motor of the slat drive system, which resulted in arcing and an open electrical circuit. The actions specified by this AD are intended to prevent possible fuel vapor fire due to electrical arcing in an area where fuel vapors might be present and the inability to move the slats during flight due to an open electrical circuit.
AD 94-22-08 · published Nov 15, 1994, effective Dec 15, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections of the strut skin in the area of the precooler exhaust vent for cracks on the inboard and outboard struts, and repair, if necessary. This amendment requires inspections of an expanded area for certain airplanes, and inspections of airplanes on which a skin doubler has been installed as terminating action for the existing AD. This amendment is prompted by reports of strut skin fatigue cracks and heat damage found aft of the edges of skin doublers installed on certain Model 747 series airplanes. The actions specified by this AD are intended to prevent separation of an engine due to overheating and subsequent cracking of the engine strut.
AD 94-23-01 · published Nov 15, 1994, effective Dec 15, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes, that currently requires inspection of the wing rear spar lower cap aft tang fastener and the wing trailing edge access door sill to detect fatigue cracking, and repair, if necessary. This amendment requires installation of a crack preventative modification of the wing rear spar lower cap, and follow-on inspections. This amendment is prompted by reports of additional cracking found in the current inspection area. The actions specified by this AD are intended to prevent propagation of cracks in the subject area, which could compromise the structural integrity of the airplane.
AD 94-23-02 · published Nov 15, 1994, effective Dec 15, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-30 and -30F series airplanes, that requires replacement of cargo door latch spool fitting attach bolts fabricated from H-11 steel with Inconel bolts. This amendment is prompted by a report of a broken latch spool fitting attach bolt found on a cargo door on a Model DC-9 series freighter airplane. The actions specified by this AD are intended to prevent inadvertent opening of a cargo door while the airplane is in flight, and subsequent loss of pressurization and reduced controllability of the airplane.
AD 94-23-10 · published Nov 16, 1994, effective Dec 16, 1994
The Boeing Company Airplanes
This amendment supersedes an existing AD that currently requires periodic leak checks of the forward lavatory drain system and provides for the installation of a new drain valve as terminating action. This action continues to require various leak checks, but deletes a previously provided terminating action; adds requirements for leak checks of other lavatory drain systems; 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 either a periodic leak check of the flush/fill line cap or replacement of the seals on both that cap and the toilet tank anti-siphon (check) valve. This amendment was 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 had formed from leaking forward lavatory drain systems and subsequently had dislodged fromthe airplane. The actions specified by this AD are intended to prevent such damage associated with the problems of "blue ice."
AD 94-23-07 · published Nov 21, 1994, effective Dec 21, 1994
Lockheed Martin Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires various modifications and inspections of the flight controls, doors, and horizontal stabilizers. This amendment is prompted by a recommendation by the Systems Review Task Force (SRTF) for accomplishment of certain modifications and inspections that will enhance the controllability of these airplanes in the unlikely event of flight control malfunction or failure. The actions specified by this AD are intended to ensure airplane survivability in the event of damage to fully powered flight control systems.
AD 94-23-08 · published Nov 21, 1994, effective Dec 6, 1994
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Jetstream Model HS 748 Series 2A and 2B airplanes. This action requires repetitive replacement of the structurally significant items (SSI) on the nose landing gear (NLG) and main landing gear (MLG) with serviceable SSI's. This amendment is prompted by fatigue testing which revealed that the SSI's on the NLG and the MLG have a limited service life. The actions specified in this AD are intended to ensure the replacement of the SSI's that have reached the maximum life limit; SSI's that are not replaced could fail and lead to the failure of the NLG and MLG during taxi, take-off, or landing.
AD 94-21-03 · published Nov 25, 1994, effective Nov 25, 1994
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires installation of a placard near the decouple control handle for the elevator control system to ensure that the pilots are made aware that maintenance action is required to reset the disconnect unit once the decouple control handle has been pulled. This amendment is prompted by a report that, if the decouple control handle for the elevator control system is pulled, the lock linkage will remain unlocked until it is reset during maintenance. The actions specified by this AD are intended to prevent reduced controllability of the airplane due to loss of the mechanical linkage between the pilots' elevator controls, and each pilot having control authority over only one-half of the elevator control system.
AD 94-21-05 R1 · published Nov 25, 1994, effective Nov 25, 1994
The Boeing Company Airplanes
This amendment clarifies an existing airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that currently requires modification, adjustments, and tests of the thrust reverser system; and repair, if necessary. This amendment clarifies a requirement specified in the AD concerning the performance of the operational test of the system. This amendment is prompted by an inquiry from an operator of the affected airplanes concerning that aspect of the existing AD. \n\n\tThe incorporation by reference of certain publications listed in the regulations was approved by the Director of the Federal Register as of November 25, 1994 (59 FR 53573, October 25, 1994).
AD 94-20-04 · published Nov 28, 1994, effective Nov 28, 1994
KWAD Company, Raytheon Aircraft Company, Hawker Beechcraft Corporation Airplanes
This amendment supersedes Airworthiness Directive (AD) 57-18-01 and AD 87-20-02 R1, which currently require several ruddervator checks and modifications on certain Beech Aircraft Corporation (Beech) 35 series airplanes. This action maintains the requirements of each of the superseded AD's and requires rebalancing the ruddervators (off the airplane) anytime the ruddervator is repaired or repainted (even if stripes are added). The required action imposes no new speed restrictions. Several incidents where empennage flutter occurred on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent structural failure of the V-tail, which could result in loss of control of the airplane.
AD 94-21-04 · published Nov 28, 1994, effective Nov 28, 1994
ATR - GIE Avions de Transport R gional Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Model ATR42-200 and -300 series airplanes, that requires a one-time dye penetrant inspection to detect cracking in certain hinge pins of the nose landing gear (NLG), and replacement of cracked pins with crack-free pins. This amendment is prompted by reports of cracking of certain hinge pins in the NLG. The actions specified by this AD are intended to prevent collapse of the NLG due to cracking of the hinge pins.
AD 94-22-03 · published Nov 28, 1994, effective Nov 28, 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 modification of the power transfer unit (PTU). This amendment is prompted by reports of fatigue cracks found in the drain port housings of the PTU's on several airplanes. The actions specified by this AD are intended to prevent failure of the PTU housing due to fatigue cracking, which could result in the loss of both hydraulic systems (until the PTU is shut off).\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 28, 1994.
AD 94-22-09 · published Nov 7, 1994, effective Nov 22, 1994
Arrow Falcon Exporters, Inc., AST, Inc, Bell Helicopter Textron, Inc., California Department of Forestry, Global Helicopter Technology, Inc., Hagglund Helicopters, LLC, International Helicopters, Inc., Overseas Aircraft Support Inc, Richards Heavylift Helo, Inc., Robinson Air Crane, Inc., Rotorcraft Development Corporation, San Joaquin Helicopters, Smith Helicopters, Sout
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. restricted category military Model UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and TH-1L helicopters, that currently requires an inspection before the first flight of each day of certain tail rotor drive shafts and the tail rotor drive shaft hanger bearings (bearings) for grease leakage, security, overheat conditions, binding, or roughness until the bearings are replaced. This amendment requires the same inspection of the bearings, but also requires replacement of the affected bearings within the next 100 hours time-in-service and extends the requirements of this AD to the Model UH-1P and TH-1F helicopters that were recently type certificated. This amendment is prompted by an accident involving a bearing failure, and by the certification of two additional affected helicopter models. The actions specified by this AD are intended to prevent failure of the bearing, failure of the tail rotor drive shaft, and subsequent loss of control of the helicopter.
AD 94-24-04 · published Nov 28, 1994, effective Dec 13, 1994
MD Helicopters, Inc. Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems and Hughes Helicopters, Inc. Model 369D, E, F, and FF series helicopters. This action requires an initial inspection of the pitch control assembly lockwasher (lockwasher) for dents at the inner tang inside radius, application of a torque stripe on the tail rotor swashplate and locknut, and repetitive inspections of the torque stripe to detect any locknut slippage. This amendment is prompted by a report that a lockwasher failed in service and allowed a locknut to loosen. The actions specified in this AD are intended to prevent failure of the inner tang of the lockwasher, loss of the locknut, disengagement of the pitch control assembly, loss of tail rotor control, and subsequent loss of control of the helicopter.
