31 Airworthiness Directives: 23 airplane, 3 rotorcraft, 3 engine, 1 propeller, 1 appliance.
AD 95-19-16 · published Nov 2, 1995, effective Nov 2, 1995
Dassault Aviation Airplanes
AD 95-20-04 · published Nov 2, 1995, effective Nov 2, 1995
Lockheed Martin Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385-1 series airplanes, that requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair, if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This amendment is prompted by a structural re-evaluation by the manufacturer that identified certain structural details where fatigue damage is likely to occur. The actions specified by this AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes.
AD 95-20-04 R1 · published Nov 2, 1995, effective Nov 2, 1995
Lockheed Martin Corporation Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385-1 series airplanes, that currently requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair, if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. That AD originally was prompted by a structural re-evaluation by the manufacturer that identified certain structural details where fatigue damage is likely to occur. The actions specified in that AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes. This amendment corrects the compliance time for the initial inspection of each structurally significant detail (SSD). The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of November 2, 1995 (60 FR 51713, October 3, 1995).
AD 95-21-06 · published Nov 2, 1995, effective Nov 2, 1995
Airbus 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 fire extinguisher distribution pipe and attachments in the lower deck cargo compartment fire extinguishing system. This amendment is prompted by a report indicating that, in response to a smoke warning in the forward cargo compartment on one airplane, bottle 2 of the fire extinguishing system did not discharge extinguishing agent into the cargo compartment due to a blockage of the discharge pipe by debris within it. The actions specified in this AD are intended to ensure that, in the event of a fire, adequate fire extinguishing agent is discharged into the cargo compartment.
AD 95-21-13 · published Nov 2, 1995, effective Nov 2, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes. This action requires inspection(s) to detect damaged and missing surface protective finish, corrosion, and cracking on the servo tab brackets and the trim tab drive brackets of the aileron, and corrective actions, if necessary. This amendment is prompted by a report of corrosion on an aileron tab bracket between the two tab drive flanges in the area of the two attachment bolts, which resulted in cracking of the flanges at their base. The actions specified in this AD are intended to prevent the failure of the servo tab brackets and trim tab drive brackets of the aileron due to cracking associated with corrosion, which could result in reduced controllability of the airplane.
AD 95-20-01 R1 · published Nov 3, 1995, effective Nov 3, 1995
Textron Aviation Inc. Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-20-01 R1, which was sent previously to all known U.S. owners and operators of certain Beech Aircraft Corporation (Beech) Models 65 and L-23F (military conversion) airplanes. This AD requires fabricating and installing a placard that specifies not to operate the airplane with the cabin door removed, and incorporating a copy of the AD into the Limitations Section of the Airplane Flight Manual (AFM). A recent accident of one of the affected airplanes that was operating with the cabin door removed prompted the existing AD. The actions specified by this AD are intended to prevent the possibility of a reduction in stability, controllability, or airplane climb performance during operation, particularly in single-engine operations at high gross weights. Comments for inclusion in the Rules Docket must be received on or before December 27, 1995.
AD 95-22-13 · published Nov 3, 1995, effective Nov 20, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires an inspection to determine proper clamping and to detect damage of a wire bundle in the avionics compartment, and repair, if necessary. This amendment is prompted by a report of smoke and fire in the avionics compartment floor area that was caused by electrical arcing that occurred as the result of chafed wiring. The actions specified in this AD are intended to prevent smoke and fire in the avionics compartment due to such electrical arcing in the wire bundle; that condition could pose a hazard to the continued safe flight of the airplane.
AD 95-23-01 · published Nov 7, 1995, effective Nov 22, 1995
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires inspections to detect cracking, corrosion, and free play in the spherical washers located in certain assemblies where the aft flap track attaches to the wing trailing edge, and replacement of the washers, if necessary. This amendment is prompted by reports indicating that these washers can break under load. The actions specified in this AD are intended to prevent breakage of these washers, which could result in structural damage to the attachment assembly and eventually lead to separation of the flap from the airplane.
AD 95-22-04 · published Nov 8, 1995, effective Nov 8, 1995
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-215-1A10 and CL-215-6B11 series airplanes. This action requires inspections to detect cracking of main landing gear (MLG) axles that have been reworked by chromium plating, and replacement of cracked axles. This amendment is prompted by reports of fatigue cracking found on several MLG wheel axes that had been chromium-plated during rework. The actions specified in this AD are intended to prevent such cracking, which can result in failure of the axle, separation of the wheel from the aircraft, and consequent reduced controllability of the airplane during takeoff or landing.
AD 95-22-06 · published Nov 8, 1995, effective Nov 8, 1995
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. This action requires repetitive inspections to detect fatigue cracking of the shock strut cylinder of the main landing gear (MLG), and replacement of any cracked shock strut cylinder with a serviceable part. This action also provides for installation of brake line hydraulic restrictors on the MLG brake systems, which, if accomplished, terminates the repetitive inspection requirement. This amendment is prompted by a report indicating that fatigue cracking and subsequent fracturing of the shock strut cylinder of the MLG occurred due to high stress loads on the cylinder as a result of braking induced vibration. The actions specified in this AD are intended to prevent such fracturing, which could result in collapse of the MLG and consequent reduced controllability of the airplane during landing.
AD 95-22-11 · published Nov 9, 1995, effective Nov 24, 1995
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes. This action requires reinforcement of the fuselage frame (FR) 20 between stringer 30 and 32 in the forward fuselage. This amendment is prompted by the results of fatigue testing, which revealed that fatigue cracks can develop on the web and cap of lower left FR20. The actions specified in this AD are intended to prevent the initiation and propagation of such fatigue cracking, which could adversely affect the structural integrity of this area of the fuselage.
AD 95-23-10 · published Nov 13, 1995, effective Dec 13, 1995
Boeing Model 737 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that requires revising the FAA-approved Airplane Flight Manual (AFM) to provide the flightcrew with additional procedures for shutting down the auxiliary power unit (APU) when an APU fire is indicated. This amendment is prompted by reports indicating that a latent electrical failure exists in the fire extinguishing system for the APU; this failure could prevent the APU from shutting down and fire extinguishant from discharging into the APU compartment in the event of an APU fire. The actions specified by this AD are intended to ensure that the flightcrew is provided with procedures for shutting down the APU in the event of an APU fire.
AD 95-23-06 · published Nov 14, 1995, effective Nov 29, 1995
British Aerospace Model BAe 146-100A, - 200A, and -300A Airplanes and Model Avro 146-RJ70A, -RJ85A, and RJ-100A Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A airplanes and Model Avro 146-RJ70A, -RJ85A, and RJ-100A airplanes. This action requires inspections to detect cracking and evidence of exhaust leaks in the forward face of the central panel of the forward firewall of the auxiliary power unit (APU) bay, and replacement of the central panel with a new panel, if necessary. This amendment is prompted by a report indicating that cracking due to leakage of hot exhaust gases was found in the forward face of the forward firewall of the APU bay. The actions specified in this AD are intended to prevent such gas leakage and subsequent cracking, which could damage the wiring to the APU fire bottle; this condition could result in failure of the APU fire bottle to discharge in the event of an APU fire.
AD 95-23-11 · published Nov 16, 1995, effective Nov 30, 1995
Aerostar Aircraft Corporation PA-60-600 (Aerostar 600) Series (Formerly Piper Aircraft Corporation) Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) PA-60-600 series airplanes. This action requires repetitively inspecting the fuselage horizontal stabilizer attach fittings for cracks, and replacing any cracked fuselage horizontal stabilizer attach fitting. A report of several cracks found on the forward horizontal stabilizer attach spar fitting on an Aerostar Model PA-60-601P airplane prompted this action. The actions specified by this AD are intended to prevent undetected cracked fuselage horizontal attach fittings, which could result in the fuselage horizontal stabilizer separating from the airplane while in flight with subsequent loss of control of the airplane.
AD 95-21-18 · published Nov 17, 1995, effective Nov 17, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model ATP airplanes, that requires an inspection to ensure that various components of the retraction actuator of the nose landing gear (NLG) are secure, and an inspection of the bearing cap mounting holes for correct hole and thread length. This AD also requires a later inspection for certain discrepancies of the retraction actuator; installation of revised tolerance bushings; and correction of any discrepancy found. This amendment is prompted by reports of failure of the attachment bolts of the bearing cap of the retraction actuator of the NLG. The actions specified by this AD are intended to prevent the inability to raise or lower the NLG, or possible collapse of the NLG, due to failure of the attachment bolts of the bearing cap.
AD 95-21-20 · published Nov 17, 1995, effective Nov 17, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires a visual inspection to detect damage to the flexible fuel drain line of the auxiliary power unit (APU), and replacement of the drain line, if necessary. This amendment also requires installation of two additional clamps to secure the flexible fuel drain line to the fuel supply line of the APU. This amendment is prompted by reports of electrical arcing between the flexible fuel drain line and the APU starter motor. The actions specified by this AD are intended to prevent such electrical arcing, which could result in a fire in the APU.
AD 95-22-10 · published Nov 20, 1995, effective Nov 20, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes. This action requires replacement of the rear pintle pin of both main landing gears (MLG) with an improved pintle pin assembly. This amendment is prompted by the results of fatigue testing, which demonstrated that fatigue cracking can occur in the heads of these pintle pins. The actions specified in this AD are intended to prevent the initiation and propagation of such fatigue cracking, which could lead to the failure of the pintle pins and consequent collapse of the MLG.
AD 95-23-12 · published Nov 27, 1995, effective Jan 8, 1996
Piper Aircraft Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft, Inc. (Piper) Model PA-46-350P airplanes. This action requires installing a placard (to the right of the manifold pressure gauge in full view of the pilot) that specifies manifold pressure limits, and incorporating a revision into the Limitations section of the Pilot's Operating Handbook (POH). The actions specified by this AD are intended to prevent fatigue damage to the propeller caused by operating above certain manifold pressure limits.
AD 95-24-01 · published Nov 27, 1995, effective Dec 27, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-10-10 series airplanes, that requires inspections of the wings to detect cracks in the aft spar lower cap, in certain stringer butterfly clips on the bulkheads, and in certain fastener holes; and repair, if necessary. This amendment also requires modification of those areas of the wings, which terminates the repetitive inspection requirements. This amendment is prompted by reports indicating that, during fatigue testing of the wing structure, cracks developed in the aft spar lower cap, in certain stringer butterfly clips, and in certain fastener holes due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue- related cracking, which could lead to the failure of the aft spar cap and consequently could reduce the structural integrity of the wing.
AD 95-24-02 · published Nov 27, 1995, effective Dec 27, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747SP series airplanes, that requires modification of the escape slide/raft on Door 2 of the airplane. This amendment is prompted by reports indicating that the escape slide/raft on Door 2 deployed onto the wing of the airplane and did not inflate automatically. The actions specified by this AD are intended to ensure that the escape slide/raft on Door 2 inflates automatically so that passengers are able to exit the airplane through Door 2 in the event of an emergency evacuation.
AD 95-24-03 · published Nov 27, 1995, effective Dec 27, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10, -30, and -40 series airplanes, and KC-10 (military) airplanes, that requires inspections to detect corrosion or cracking of the lower front spar cap and the skin panel of the horizontal stabilizer, and repair of corroded or cracked parts. This amendment also requires eventual modification of the horizontal stabilizer, which terminates the inspection requirements. This action is prompted by reports indicating that corrosion, caused by water entrapment, was found on the horizontal stabilizer. The actions specified by this AD are intended to prevent water entrapment and subsequent damage to the horizontal stabilizer, which could result in reduced controllability of the airplane.
AD 95-24-11 · published Nov 27, 1995, effective Jan 3, 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 installing foreign object damage (FOD) barriers in the floorboards of the cockpit between the pedestal and floor from Fuselage Station (FS) 79.38 to FS 88.06 and on the outboard forward edge of the left-hand and right-hand cockpit forward floorboards at FS 79.38. Two incidents of objects falling through openings in the cockpit floor and jamming the elevator controls and the yoke prompted this action. The actions specified by this AD are intended to prevent airplane flight control jammings caused by objects falling through the cockpit floor openings.
AD 95-23-04 · published Nov 28, 1995, effective Nov 28, 1995
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all British Aerospace Model BAC 1-11 400 series airplanes. This action requires an inspection of the rod ends of the lift dumper to detect drill holes; a dye penetrant inspection to detect any cracking of drilled holes; and replacement of the rod end with an undrilled rod end, if necessary. This amendment is prompted by a report that, during a routine examination of the operating mechanism of the lift dumper, two cracked aft rod ends were found. Investigation revealed that holes had been drilled in the rod ends for grease nipples during manufacturing, and that cracking had developed at the holes. The actions specified in this AD are intended to prevent asymmetric deployment and subsequent lateral control problems due to cracking of either pair of aft rod ends of the operating mechanism of the lift dumper.
AD 95-22-09 · published Nov 1, 1995, effective Dec 6, 1995
Boeing Defense and Space Group Helicopter Division Model 234 Series Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Boeing Defense and Space Group Helicopter Division (Boeing) Model 234 series helicopters, that currently requires inspections of the forward and aft transmission first stage sun and spiral bevel ring gear bolted connection (bolted connection). This amendment requires a revision to the inspection intervals and criteria used during these inspections, as well as adds a visual inspection of the pinion and spiral bevel ring gear. This amendment is prompted by reports that certain of the affected helicopters have been discovered with loose nuts on the bolted connection more frequently than was anticipated in the previous AD. The actions specified by this AD are intended to prevent wear of the spiral bevel ring gear flange surface, failure of the bolted connection, transmission failure, and subsequent loss of control of the helicopter.
AD 95-23-05 · published Nov 22, 1995, effective Dec 27, 1995
Robinson Helicopter Company Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company Model R22 series helicopters, that currently requires an inspection and repetitive visual checks for slippage of the tail rotor (T/R) drive and replacement of the T/R gearbox, if necessary. This amendment requires disassembly of the T/R gearbox to verify the installation of the input and output shaft keys (keys) between the input and output pinions and their respective shafts. This amendment is prompted by two incidents in which the key was not installed between the output shaft and the output pinion during assembly of the T/R gearbox at Robinson Helicopter Company. The actions specified by this AD are intended to prevent slippage of the T/R drive, loss of directional control, and subsequent loss of control of the helicopter.
AD 95-24-06 · published Nov 22, 1995, effective Dec 27, 1995
Bell Helicopter Textron, a Division of Textron Canada, Model 206B and 206L Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, a Division of Textron Canada (BHT), Model 206B and 206L helicopters, that currently requires a revision to the Limitations section of the FAA-approved Supplemental Type Certificate (STC) Rotorcraft Flight Manual Supplement (RFMS) until replacement of the engine power-out warning sensor on BHT Model 206B and 206L helicopters equipped with Allison 250-C20R engines in accordance with certain supplemental type certificates. This amendment requires a revision to the Limitations section of the STC RFMS, but removes the requirement for replacement of the engine power-out warning sensor. This amendment is prompted by a reevaluation of the need for an engine power-out warning sensor based on the lack of reported operational occurrences of the false engine-out warnings. The actions specified by this AD are intended to maintain a heightened pilot awareness that false engine-out warnings may occur when practicing autorotations and could result in an unnecessary emergency autorotative landing.
AD 95-21-15 · published Nov 13, 1995, effective Nov 28, 1995
Continental Motors, Teledyne Continental Motors Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Teledyne Continental Motors (TCM) reciprocating engines installed on certain aircraft identified by registration numbers. This action supersedes priority letter AD 94-14-12 that currently requires engines certified to operate on 91 octane or higher aviation gasoline (avgas) to undergo a teardown and analytical inspection for detonation damage, and engines certified to operate on 80 octane avgas to undergo inspection for evidence of possible internal engine damage. This action revises incorrect engine model numbers and aircraft registration numbers listed in the priority letter AD. This amendment is prompted by the Federal Aviation Administration (FAA) receiving more accurate information concerning which aircraft were fueled with the contaminated mixture at the affected airports. The actions specified by this AD are intended to prevent detonation due to low octane, which can result in severe engine damage and subsequent failure.
AD 86-09-02 R2 · published Nov 17, 1995, effective Nov 17, 1995
Pratt & Whitney Division Engines
AD 95-23-03 · published Nov 21, 1995, effective Dec 6, 1995
General Electric Company CF6 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6 series turbofan engines, that currently requires initial and repetitive ultrasonic and eddy current inspections of a certain population of high pressure compressor rotor (HPCR) stage 3-9 spools for cracks. This amendment retains the inspection requirements of the current AD, but would accelerate the inspection schedule for parts affected by the current AD, require initial and repetitive inspections of an expanded population of HPCR stage 3-9 spools installed on GE CF6-45/-50/-80A engines, include HPCR stage 3-9 spools installed on GE CF6-80C2 series engines, and require reporting to the FAA the results of inspections that equal or exceed the reject criteria. This amendment is prompted by recent field experience and the associated engineering investigation, which indicate that cracks are likely to develop in a larger population of parts than previously thought. The actions specified by this AD are intended to prevent HPCR stage 3-9 spool cracking and separation, which can result in an uncontained engine failure and aircraft damage.
AD 95-22-12 · published Nov 8, 1995, effective May 6, 1996
Hamilton Standard Division, Hamilton Sundstrand Propellers
This amendment supersedes an existing airworthiness directive (AD), applicable to Hamilton Standard 14RF, 247F, 14SF, and 6/5500/F (formerly Hamilton Standard/British Aerospace 6/5500/F) series propellers, that currently requires initial and repetitive inspections of the propeller control unit (PCU) servo ballscrew internal spline (BIS) teeth for wear, and replacement, if necessary, of PCU servo BIS assemblies. This amendment increases the repetitive PCU servo BIS teeth inspection interval from 1,500 to 2,500 hours time in service (TIS) for propellers that have a ballscrew quill damper installed. In addition, the FAA has reevaluated the optional installation of the Secondary Drive Quill (SDQ), and has added a new compliance end-date of June 30, 1998, for the installation of the SDQ. This AD will also require initial and repetitive torque check inspections of the primary ballscrew quill once the SDQ is installed. This amendment is prompted by field service and laboratory test data that indicate that the repetitive inspection interval can be safely increased, and by the development and availability of the SDQ. The actions specified by this AD are intended to prevent inability to control the propeller blade angle due to tooth wear in the PCU servo BIS assembly.
AD 95-22-01 · published Nov 3, 1995, effective Dec 4, 1995
Aerospace Lighting Corporation Power Units and Power Supplies
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospace Lighting Corporation (ALC) lamp connectors and fluorescent lamps, that currently requires an inspection, and adjustment or replacement of improperly installed, damaged, or improperly configured lamp connectors and fluorescent lamps used in cabin fluorescent lighting systems. This amendment adds an optional replacement of certain power units and power supplies with new technology parts as terminating action to the repetitive inspections. This amendment is prompted by the availability of new technology components. The actions specified by this AD are intended to prevent smoke, fire, electrical shock, and possible electromagnetic interference caused by high voltage arcing in the cabin which, if undetected, could result in personal hazard or loss of the aircraft.
