22 Airworthiness Directives: 19 airplane, 1 rotorcraft, 1 engine, 1 propeller.
AD 95-01-03 · published Jan 3, 1995, effective Jan 18, 1995
Dassault Aviation Model Mystere-Falcon 50 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Aviation Model Mystere-Falcon 50 series airplanes. This action requires measurement of the clearance between the electrical bundles in the left-hand cabinet of the electrical panel and the counterbalancing actuator of the passenger door, and rerouting and clamping the wire bundles, if necessary. This amendment is prompted by a report of damage of the wire bundles between the actuator of the passenger door and the left-hand cabinet of the electrical panel. The actions specified in this AD are intended to prevent an electrical fire due to damage of the electrical wire bundles.
AD 94-26-09 · published Jan 4, 1995, effective Feb 3, 1995
Lockheed Martin Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires an initial servicing or overhaul of the ram air turbine (RAT), and incorporating repetitive overhaul actions into the FAA-approved maintenance program. This amendment is prompted by reports indicating that, during routine maintenance of the RAT, the turbine blade assembly separated during spin tests. The actions specified by this AD are intended to prevent separation of the turbine blade assembly, which could damage the airplane structure and systems, and, under certain circumstances, could lead to reduced controllability of the airplane. DATES: Effective February 3, 1995. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 3, 1995.
AD 94-26-15 · published Jan 4, 1995, effective Feb 3, 1995
Lockheed Martin Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 382 series airplanes, that requires inspection of a kingpin riser on the lower surface of the outer wing to determine fastener placement. This AD would also require repetitive inspections for fatigue cracks in the kingpin riser if the fasteners are positioned outside certain limits, and repair, if necessary. This amendment is prompted by reports of insufficient distance between the center of the outermost fastener on the kingpin riser and the edge of the riser, which can adversely affect the fatigue resistance of the outer wing assembly. The actions specified by this AD are intended to prevent structural failure of the lower surface of the outer wing due to fatigue cracks in the kingpin riser.
AD 94-24-07 · published Jan 6, 1995, effective Jan 6, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires modification of the brake steering control unit (BSCU). This amendment is prompted by reports that the BSCU on these airplanes allowed a 90-degree rotation of the nose gear after landing, which resulted in significant damage to the wheels. The actions specified by this AD are intended to prevent failure of the nose gear tires and wheels and the loss of directional control of the airplane while it is on the ground.
AD 95-01-04 · published Jan 6, 1995, effective Jan 23, 1995
Boeing Model 747-100 Series Airplanes Equipped With Freighter Conversion Modification Installed in Accordance With Supplemental Type Certificate (STC) SA2322SO
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 series airplanes. This action requires an inspection to detect discrepancies of the lap joint in certain fuselage stations, repair of any discrepancies, and modification of a certain lap joint. This amendment is prompted by reports of holes in the lap joints and longerons of these airplanes. The actions specified in this AD are intended to prevent reduced fatigue life of the fuselage in the areas in which holes are found.
AD 95-01-06 · published Jan 9, 1995, effective Jan 24, 1995
Boeing Model 737-200 and -300 Series Airplanes Equipped With Cargo Doors Installed in Accordance With Supplemental Type Certificate (STC) SA2969SO
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200 and -300 series airplanes. This action requires inspections to detect cracking in the radii on the support angles on the lower jamb (latch lug fittings) of the main deck cargo door, and replacement of cracked parts. This amendment is prompted by reports of premature fatigue cracking on the support angles on the lower jamb of the main deck cargo door. The actions specified in this AD are intended to prevent in-flight separation of the main deck cargo door from the airplane due to fatigue cracking on the support angles on the lower door jamb.
AD 95-01-07 · published Jan 10, 1995, effective Feb 17, 1995
M7 Aerospace LLC Airplanes
This amendment supersedes Airworthiness Directive (AD) 83-12-01, which currently requires repetitively inspecting the lower wing skin panel for cracks on certain Fairchild Aircraft Models SA227-AC and SA227-AT airplanes, and installing wing skin reinforcement doublers if any wing skin crack is found. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate, or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action requires installing wing skin reinforcement doublers or wing skin stringer ties as terminating action for the repetitive inspections that are currently required by AD 83-12-01. The actions specified by this AD are intended to prevent fatigue failure of the lower wing skin panels, which could result in loss of control of the airplane.
AD 95-01-08 · published Jan 10, 1995, effective Feb 20, 1995
Jetstream Aircraft Limited (Formerly British Aerospace, Regional Airlines Limited) HP137 Mk1 and Jetstream Series 200 Airplanes
This amendment supersedes AD 81-09-03 R1, which currently requires repetitively inspecting the rudder pedal adjusting mounting bracket for cracks on Jetstream Aircraft Limited (JAL) HP137 Mk1 and Jetstream Series 200 airplanes, and replacing any cracked bracket. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate, or in certain instances, reduce the number of repetitions of certain short-interval inspections when improved parts or modifications are available. This action requires replacing the mounting bracket with a new mounting bracket of improved design as terminating action for the repetitive inspections that are currently required by AD 81-09-03 R1. The actions specified by this AD are intended to prevent inadvertent rudder movement caused by a cracked rudder pedal adjusting bracket, which, if not detected and corrected, could result in loss of rudder control.
AD 94-25-11 · published Jan 17, 1995, effective Jan 17, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires installation of additional venting between the flight deck and the passenger compartment. This amendment is prompted by results of an engineering analysis that revealed there was insufficient venting in the forward stowage and wardrobe assembly. The actions specified by this AD are intended to prevent injury to the crew resulting from structural failure of the bulkhead between the flight deck and the passenger compartment in the event of windshield failure and subsequent rapid decompression.
AD 94-22-10 R1 · published Jan 19, 1995, effective Feb 3, 1995
De Havilland Model DHC-8-100 and DHC-8- 300 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain De Havilland Model DHC-8-100 and DHC-8-300 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to advise flight crew members that certain cockpit indications may reveal faulty anti-collision strobe light units, and to provide procedures for subsequent flight crew and maintenance action. That AD also requires a modification that eliminates the need for the AFM revision. That AD was prompted by reports that the function of the proximity switch electronics unit (PSEU) may be adversely affected during operation of the white anti-collision lights. The actions specified by that AD are intended to ensure correct operation of the PSEU and its associated systems. This amendment revises the applicability of the existing AD to add one model of affected airplanes.
AD 94-26-13 · published Jan 19, 1995, effective Feb 3, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes. This action requires modification of the leading edge slat access panel and internal structure at Front Spar Station (FSS) 250.663. This amendment is prompted by reports that fuel leaking from the fuel line at FSS 250.663 flowed through a drain hole in a slat access panel and leaked into the turbine exhaust area. The actions specified in this AD are intended to prevent drainage from such a fuel leak into the turbine exhaust area, which could cause an external fire under the wing.
AD 95-02-02 · published Jan 20, 1995, effective Feb 21, 1995
McDonnell Douglas Model DC-9 and DC-9- 80 Series Airplanes, Model MD-88 Airplanes, and Model C-9 (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and Model C-9 (military) airplanes, that requires inspection of the tailcone release locking cable fitting assembly, and replacement or modification of the assembly, if necessary. This amendment is prompted by reports of the inability of the tailcone to deploy because the swaged ball on the cable had jammed after passing into the release handle hole. The actions specified by this AD are intended to prevent the inability of the tailcone to deploy, which could impede the egress of passengers from the airplane during an emergency evacuation.
AD 94-26-03 · published Jan 26, 1995, effective Jan 26, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 series airplanes, that requires inspection to detect cracking in the area of the side stay attachment lugs of the fitting subassembly of the main landing gear (MLG), and replacement of cracked subassemblies with new or serviceable subassemblies. This amendment is prompted by reports of cracking in the subassembly of the MLG. The actions specified by this AD are intended to prevent damage to and/or failure of the support structure of the MLG.
AD 94-26-04 · published Jan 26, 1995, effective Jan 26, 1995
BAE Systems (Operations) Limited Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires inspections to detect damage of the ball bearings in the aileron quadrants, replacement of damaged ball bearings with new ball bearings, and adjustment to the secondary stops. This amendment requires installation of new swivel bearings in the aileron quadrants, which, when accomplished, will terminate the inspection requirement. This amendment is prompted by the development of a modification that eliminates the need to inspect repetitively. The actions specified by this AD are intended to prevent failure of the bearings in the aileron quadrants, which could result in reduced controllability of the airplane.
AD 95-01-51 · published Jan 30, 1995, effective Feb 14, 1995
Airbus Model A300, A300-600, A310, A330, and A340 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T95-01-51 that was sent previously to all known U.S. owners and operators of Airbus Model A300, A300-600, A310, A330, and A340 series airplanes by individual telegrams. This AD requires an inspection of the sliding side windows in the cockpit to identify the part number of the windows. For airplanes on which a certain suspect window is installed, this AD requires either deactivation of the sliding window defogging system; or installation of thermo-sensitive indicators, daily inspections of those indicators, and deactivation of the defogging system, if necessary; or replacement of the window with a serviceable window. This amendment is prompted by reports of fracture of the sliding side window in the cockpit, due to thermal stress created by overheating of the wires of the heating element in a localized area. The actions specified by this AD are intended to prevent such fractures, which could lead to rupture of a cockpit sliding window and subsequent rapid decompression of the fuselage.
AD 95-02-10 · published Jan 30, 1995, effective Feb 14, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires replacement of the bolts, nuts, and washers that attach the support bracket at the Number 4 and Number 5 transmissions to the wing flap structure. This amendment is prompted by a report of damage to the left inboard trailing edge flap. The actions specified in this AD are intended to prevent these airplanes from taking off with broken bolts that attach the transmission bracket to the wing flap track structure, which could result in the airplane rolling at liftoff.
AD 96-05-09 · published Jan 30, 1995, effective Jan 30, 1995
Airbus Airplanes
This amendment supersedes an existing airworthiness directive (AD), that is applicable to all Airbus Model A300, A300-600, A310, A330, and A340 series airplanes. The existing AD currently requires an inspection of the sliding side windows in the cockpit to identify suspect windows; and either deactivation of the sliding window defogging system; installation of thermo-sensitive indicators; or replacement of the window. This amendment adds a requirement to replace suspect windows with serviceable windows, which, when accomplished, terminates the requirements of the AD. The actions specified by this amendment are intended to prevent rupture of a cockpit sliding window and subsequent rapid decompression of the fuselage due to fracture of the window as a result of thermal stress created by overheating of the wires of the heating element in a localized area.
AD 94-24-11 · published Jan 6, 1995, effective Jan 6, 1995
Bell Helicopter Textron Canada Limited Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, that requires a one-time inspection for cracks in the tail rotor drive shaft hanger bearing support brackets (brackets), and repair or replacement, as necessary. This amendment is prompted by reports of cracks in the bend radius of the brackets. The actions specified by this AD are intended to prevent misalignment of the tail rotor drive shaft, failure of the tail rotor drive shaft system, loss of control of the tail rotor, and subsequent loss of control of the helicopter.
AD 95-01-05 · published Jan 5, 1995, effective Jan 20, 1995
Boeing Model 757 Equipped With Pratt & Whitney Model PW2000 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires a revision to the FAA-approved Airplane Flight Manual to include procedures to perform periodic engine run-ups during ground operation in icing conditions in order to shed ice before it accumulates, sheds, and is ingested into the engine, which could cause damage to the core of the engine. This action provides procedures for a visual check to detect ice build-up on the first stage of the low pressure compressor (LPC) stator and removal of any ice, as necessary. This amendment is prompted by reports of damage to the high pressure compressor of the engines due to ice ingestion. The actions specified in this AD are intended to prevent damage to engines due to the ingestion of ice into the compressor, which can result in the loss of power from the affected engine.
AD 95-01-02 · published Jan 12, 1995, effective Jan 27, 1995
Hartzell Model HC-B4 Series Propellers Installed on Mitsubishi MU-2 Series Aircraft
This amendment supersedes three existing airworthiness directives (AD), applicable to Hartzell Model HC-B4TN-5(D,G,J)L/ LT10282(B,K)-5.3R and HC-B4TN-5(D,G,J)L/LT10282N(B,K)-5.3R propellers installed on Mitsubishi MU-2 series aircraft. These AD's currently require replacement of existing LT10282(B,K)-5.3R propeller blades with LT10282N(B,K)-5.3R improved ``N'' configuration propeller blades, and repetitive inspection and rework when required of the inner hub arm bore. This amendment requires new repair limits, shot peening procedures, and retirement at 10,000 hours time in service for the ``N'' configuration blades. Additionally, this action requires replacement of existing propeller hubs with new improved fatigue strength steel hubs and requires inspection, and specified rework as necessary, of the new steel hubs at a repetitive interval of 3,000 hours time in service. This amendment is prompted by a determination that the current hub design and blade repair limits do not adequately protect against initiation of fatigue cracks in the propeller hub arm bore and do not prevent the resonant speed of the propeller from shifting into the permitted ground idle operating range. The actions specified by this AD are intended to prevent initiation of fatigue cracks in propeller assemblies and subsequent progression to propeller failure, with departure of the blade, or hub arm and blade, that may result in loss of aircraft control.
