35 Airworthiness Directives: 33 airplane, 2 rotorcraft.
AD 95-19-06 · published Oct 2, 1995, effective Nov 1, 1995
Jetstream Model ATP Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model ATP series airplanes, that currently requires inspections to detect cracking of the aft end of the wing rib boom angles on the left and right engine, and repair or replacement of the wing rib boom angle assemblies, if necessary. That AD was prompted by the detection of cracks in the engine outboard rib boom angles at the main landing gear (MLG) actuator attachment point. The actions specified by that AD are intended to prevent structural failure of the actuator attachment point, which could lead to collapse of the MLG. This amendment limits the applicability of the rule to only a certain number of airplanes; revises the initial inspection threshold, depending on whether or not certain modifications have been accomplished on the boom angles; and requires that modified boom angles be installed whenever replacement is necessary.
AD 95-19-01 · published Oct 3, 1995, effective Oct 18, 1995
Airbus Model A330 and A340 Series Airplanes Equipped With BFGoodrich Evacuation Slides and Slide/Rafts
This amendment adopts a new airworthiness directive (AD), applicable to Airbus Model A330 and A340 series airplanes equipped with certain BFGoodrich evacuation slides and slide/rafts. This action requires an inspection to detect the presence of certain discrepancies of the packboard associated with the evacuation slides and slide/rafts, and replacement or modification of the packboard unit, if necessary. It also requires the eventual modification of all affected packboard units. This amendment is prompted by reports indicating that these packboards have disengaged from the door mounting, due to cracking of the packboard and associated latch assembly that was incurred during hard landings. The actions specified in this AD are intended to prevent the packboard from disengaging from the door and restraining the door from fully opening, thereby preventing the evacuation slide from inflating and making both the slide and the door unusable during an emergency evacuation.
AD 95-20-03 · published Oct 3, 1995, effective Nov 2, 1995
Learjet Inc. Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Learjet Model 24, 25, 31, 35, and 36 series airplanes, and all Learjet Model 28, 29, and 55 series airplanes, that currently requires a revision to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to prohibit flight above an altitude of 41,000 feet. The actions specified by that AD are intended to limit the airplane operating altitude due to a possible failure of the outflow/safety valves, which could result in rapid decompression of the airplane. This amendment adds a requirement for replacement of certain outflow/safety valves, which, when accomplished, constitutes terminating action for the previously required AFM limitation.
AD 95-20-05 · published Oct 3, 1995, effective Nov 2, 1995
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections for cracking in the inboard strut-to-diagonal brace attach fittings, and repair or replacement, if necessary. This amendment requires an additional inspection of those attach fittings, and additional inspections in an area beyond that specified in the existing AD. This amendment also provides an optional terminating action for the required inspections, and expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by reports of cracking and severing of the attach fittings. The actions specified by this AD are intended to prevent failure of the strut and separation of an engine from the airplane due to cracking of the inboard strut-to-diagonal brace attach fittings.
AD 95-20-07 · published Oct 5, 1995
The New Piper Aircraft, Inc. (Formerly Piper Aircraft Corporation) PA24, PA28R, PA30, PA32R, PA34, and PA39 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) PA24, PA28R, PA30, PA32R, PA34, and PA39 series airplanes. This action requires repetitively inspecting the main gear side brace studs for cracks and replacing any cracked main gear side brace stud. Several reports of main gear side brace stud cracks on the affected airplanes, including seven incidents where the main landing gear (MLG) collapsed, prompted this action. The actions specified by this AD are intended to prevent a MLG collapse caused by main gear side brace stud cracks, which, if not detected and corrected, could result in loss of control of the airplane during landing operations.
AD 95-20-02 · published Oct 10, 1995, effective Nov 9, 1995
Airbus Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires inspections to detect cracks in bolt holes where parts of the main landing gear (MLG) are attached to the rear spar, and repair, if necessary. This amendment is prompted by a report that cracks emanating from bolt holes in the rear spar were found during full-scale fatigue testing. The actions specified by this AD are intended to prevent unnecessary degradation of the structural integrity of the airframe due to cracks in the rear spar.
AD 95-21-03 · published Oct 11, 1995, effective Oct 26, 1995
Learjet Model 31A and 60 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 31A and 60 airplanes. This action requires an inspection to identify the serial numbers of the engine fire pull switch assemblies, and replacement of the assembly with a serviceable assembly, if necessary. This amendment is prompted by a report indicating that certain engine fire pull switch assemblies may contain microswitches that were manufactured with internal defects. Such defects could result in electrical failure of the switch in the open or closed position. The actions specified in this AD are intended to prevent failure of the switch, which could result in the inability of the flight crew to shut down certain systems or to arm the fire extinguishers due to inoperation of the fire tee handle, or inadvertent shutdown of one or both engines due to fuel starvation.
AD 95-21-05 · published Oct 11, 1995, effective Oct 26, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires an inspection to detect damage of the wire bundles in the left side of the flight compartment in the vicinity of the stowage box for the captain's oxygen mask, and repair, if necessary; a continuity check on repaired wires; installation of sleeving over the wire bundles; and rerouting of the wire bundles. This amendment is prompted by reports of chafed wiring and minimal clearance between the oxygen connector and the adjacent wire bundles in the vicinity of the stowage box for the captain's oxygen mask. The actions specified in this AD are intended to prevent such chafing and inadequate clearance, which could result in electrical arcing and consequent oxygen leakage in the vicinity of the stowage box; these conditions, if not corrected, could result in a fire in the flight compartment.
AD 96-18-01 · published Oct 11, 1995, effective Oct 2, 1996
Learjet Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 60 airplanes, that requires modification of the aft core cowl nozzle of the engine nacelles. This amendment is prompted by a report that the sealant material in the aft core cowl nozzle of the engine nacelle was found to extend higher than the nozzle's forward flange, which can allow it to interfere with the proper operation of the emergency fuel shutoff actuating mechanism. The actions specified by this AD are intended to prevent physical interference of the emergency fuel shutoff actuating mechanism and resultant engine shutdown.
AD 95-20-51 · published Oct 12, 1995, effective Oct 17, 1995
Boeing Model 767-200 and -300 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T95-20-51 that was sent previously to all known U.S. owners and operators of Boeing Model 767- 200 and -300 series airplanes by individual telegrams. This AD requires inspections of the lower half of the aft trunnion of the main landing gear (MLG) to detect damage, cracking, missing pieces, or corrosion; and correction of discrepancies. This amendment is prompted by a report indicating that the MLG collapsed on an airplane due to fracture of the aft trunnion outer cylinder that was caused by stress corrosion cracking. The actions specified by this AD are intended to prevent the collapse of the MLG due to the problems associated with stress corrosion cracking in the aft trunnion assembly; collapse of the MLG could lead to loss of control of the airplane during landing, taxiing, and takeoff.
AD 95-21-04 · published Oct 12, 1995, effective Oct 27, 1995
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires modification of the support structure of the cargo liner. That AD was prompted by a report of chafing and arcing in the vacuum waste exhaust heater that caused a spark to ignite the surrounding insulation blankets. The actions specified in that AD are intended to prevent fire and/or smoke due to chafing and arcing of the vacuum waste exhaust port heater. This amendment expands the applicability of the existing rule to include additional affected airplanes. It also provides for an alternative method of modification.
AD 93-16-06 R2 · published Oct 15, 1995, effective Oct 15, 1995
Bombardier Inc. Airplanes
AD 95-18-09 · published Oct 16, 1995, effective Oct 16, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of the rear spar-to-fuselage attachment. This amendment is prompted by a report indicating that, during full-scale fatigue tests on a Model F28 Mark 0100 test article, cracking was found in the coupling plate and web plate of the rear spar end fitting at the attachment to the main frame at fuselage station 17011 due to fatigue-related stress. The actions specified by this AD are intended to prevent fatigue-related cracking in the rear spar-to-fuselage attachment which, if not detected and corrected in a timely manner, could result in reduced structural integrity of the wing.
AD 95-21-07 · published Oct 18, 1995, effective Nov 17, 1995
Lockheed Martin Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Lockheed Model L-1011-385 series airplanes, that requires modifications of various fluid drainage areas of the fuselage. This amendment is prompted by 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 affected airplanes due to problems associated with corrosion.
AD 95-21-08 · published Oct 18, 1995, effective Nov 17, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Boeing Model 757 series airplanes, that requires modification of the engine fuel indication circuits. This amendment is prompted by numerous reports of false indications of engine fuel valve faults, which have led to the flight crew conducting rejected takeoffs (RTO). The actions specified by this AD are intended to reduce such false indications and the flight crew's consequent execution of an RTO at high speed during takeoff roll, which could result in the airplane overrunning the runway, damage to the airplane, and injury to airplane occupants.
AD 95-21-09 · published Oct 18, 1995, effective Nov 17, 1995
Airbus Model A300 and A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 series airplanes, that currently requires repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary. That AD was prompted by reports of cracking of the No. 2 flap beams. This amendment provides optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. This amendment also expands the applicability of the existing AD to include Model A300-600 series airplanes. The actions specified by this AD are intended to prevent asymmetry of the flaps due to cracking of the No. 2 flap beams.
AD 95-21-11 · published Oct 18, 1995, effective Nov 2, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10 (military) series airplanes. This action requires inspections to detect cracking of the wing pylon aft bulkheads and upper spar webs, and replacement or repair, if necessary. This amendment is prompted by reports of fatigue cracking in the aft bulkhead and upper spar webs. The actions specified in this AD are intended to prevent failure of the wing pylon aft bulkhead due to fatigue cracking; such failure could lead to separation of the engine and pylon from the airplane.
AD 95-21-14 · published Oct 18, 1995, effective Dec 4, 1995
Viking Air Limited Airplanes
This amendment supersedes Airworthiness Directive (AD) 83-18-03, which currently requires repetitively inspecting the tailplane outboard hinge assembly on certain de Havilland DHC-6 series airplanes, and replacing any cracked tailplane outboard hinge assembly. 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 eventually modifying the tailplane outboard hinge arm and tailplane hinge plate with parts of improved design (Modification No. 6/1799) as terminating action for the currently required repetitive inspections. The actions specified by this AD are intended to prevent tailplane failure caused by cracks in either outboard hinge arm or the hinge plate, which, if not detected and corrected, could result in loss of control of the airplane.
AD 95-21-16 · published Oct 18, 1995, effective Nov 17, 1995
Lockheed Martin Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires an inspection to detect evidence of sealant around the lug bushing flanges of certain actuator attach pin assemblies of the main landing gear (MLG), and replacement of the pin assembly with a serviceable unit if no sealant is present. This amendment is prompted by reports of cracks emanating from corrosion pits of the lug bores on the actuator attach pin assemblies of two MLG's. The actions specified by this AD are intended to prevent failure of the actuator attach pins as a result of corrosion and subsequent cracking of the lug bores. Such failure could result in the MLG failing to extend completely or rapidly free-falling during extension and causing additional damage to the landing gear.
AD 95-21-17 · published Oct 18, 1995, effective Nov 17, 1995
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 1000 and BAe 125-1000A series airplanes, that requires an inspection to detect damage to an electrical cable loom (wire bundle). This amendment also requires tying back the loom with a cable tie to the cable loom support bracket, and repair, if necessary. This amendment is prompted by a report indicating that damage had occurred to the electrical cable loom. The actions specified by this AD are intended to prevent incorrect fault displays in the cockpit and possible electrical systems failures, as a result of damage to the electrical cable loom.
AD 95-21-19 · published Oct 18, 1995, effective Nov 17, 1995
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B airplanes, that requires inspections to detect cracking of the beams located over the overwing emergency exits, and replacement of the beam with a new beam, if necessary. This amendment is prompted by a report that a batch of beams with cracking may have been installed on these airplanes. The actions specified by this AD are intended to prevent cabin pressure leakage, consequent loss of cabin pressurization, and reduction of the load carrying capability of the associated structure, as a result of cracked beams.
AD 95-19-02 · published Oct 20, 1995, effective Oct 20, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of the flight control lock (FCL) handle and switch with a modified unit. This amendment is prompted by a report of sudden engagement of the FCL system during approach for landing. The actions specified by this AD are intended to prevent inadvertent engagement of the FCL system during flight and subsequent reduced controllability of the airplane.
AD 95-19-05 · published Oct 20, 1995, effective Oct 20, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A and -200A airplanes, that requires modification of the glareshield and certain electrical equipment of the airplane. This amendment is prompted by a report indicating that, if the lift spoilers fail to deploy on landing, the flight crew may not receive any indication that this situation exists. The actions specified by this AD are intended to ensure that the flight crew is advised when the lift spoilers fail to deploy on landing; such failure could result in the airplane overrunning the end of the runway during landing.
AD 95-19-11 · published Oct 20, 1995, effective Oct 20, 1995
Vickers-Armstrongs (Aircraft Limited) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 airplanes, that requires inspections to detect cracking of certain fittings of the tailplane spar, and replacement of the fittings with serviceable parts, if necessary. This amendment is prompted by reports of fatigue cracking of certain fittings in the tailplane spar. The actions specified by this AD are intended to prevent such cracking, which could result in structural degradation of the attachment of the horizontal stabilizer to the fuselage.
AD 95-19-12 · published Oct 20, 1995, effective Oct 20, 1995
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires various repetitive inspections to detect cracks in certain panels of the lower skin of the wing, and in certain fixed ribs of the leading edge of the wing. This amendment also requires repair or replacement of cracked parts, which would terminate certain repetitive inspections. This amendment is prompted by reports of cracking in certain panels of the lower skin of the wing, and in certain fixed ribs of the leading edge of the wing due to fatigue-related stress. The actions specified by this AD are intended to ensure the structural integrity of the wing by detecting fatigue-related cracking in a timely manner in the panels of the lower skin of the wing or in the fixed ribs of the leading edge of the wing.
AD 95-19-13 · published Oct 20, 1995, effective Oct 20, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A airplanes, that requires repetitive inspections for cracking of fuselage frame 29, and repair, if necessary. This amendment is prompted by testing that revealed fatigue cracking in the web and inboard flange of frame 29. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking in frame 29.
AD 95-19-14 · published Oct 20, 1995, effective Oct 20, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model ATP airplanes, that requires modification of certain doors. This amendment is prompted by a report that an operator was unable to unlock a Type I passenger door due to migration of a shootbolt bush. The actions specified by this AD are intended to prevent such migration, which could jam the Type I passenger door, and subsequently could delay or impede the evacuation of passengers during an emergency.
AD 95-22-03 · published Oct 24, 1995
Beech Aircraft Corporation Models 60 and A60 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) Models 60 and A60 airplanes. This action requires incorporating flight manual supplement revisions into the Airplane Flight Manual (AFM) that would specify a minimum airspeed for operating the affected airplanes in icing conditions. Reports of several incidents and accidents on the affected airplanes related to flight in icing conditions prompted the proposed action. The actions specified by the proposed AD are intended to prevent loss of control of the airplane because of the airplane traveling too slowly in icing conditions.
AD 95-22-05 · published Oct 24, 1995, effective Nov 8, 1995
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This action requires repetitive inspections to detect damage of the brake assembly and wheel assembly; repair, if necessary; and installation of a heat shield. This action also provides for an optional installation which, if accomplished, constitutes terminating action for the repetitive inspections. This amendment is prompted by reports of failure of the brake assembly due to separation of the stator clips from the stator disk. The actions specified in this AD are intended to prevent failure of the brake assembly, which could result in a brake fire.
AD 95-22-08 · published Oct 26, 1995, effective Nov 27, 1995
British Aerospace Model Viscount 744, 745D, and 810 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model Viscount 744, 745D, and 810 airplanes, that currently establishes time-in-service limits for components of the fuselage pressure vessel, and requires modifications and inspections of various fuselage components to assure the continued structural integrity of these airplanes through the manufacturer's design life goal. This amendment requires additional modifications and inspections of the fuselage pressure vessel to extend the fuselage pressure vessel life from 30 to 45 years since new. This amendment is prompted by results of a review of fatigue test findings, stress analysis, and in-service history associated with pressure vessel components. The actions specified by this AD are intended to prevent reduced structural capability of the fuselage pressure vessel.
AD 95-21-10 · published Oct 27, 1995, effective Oct 27, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Fokker Model F28 Mark 0100 and Model F28 Mark 0070 series airplanes. This action requires revising the Limitations Section of the Airplane Flight Manual to include information that will enable the flightcrew to identify failures of the emergency direct current (DC)/alternating current (AC) bus power supply and to take appropriate corrective actions. This amendment is prompted by one report indicating that a diode failed, which resulted in battery drain and loss of the emergency DC bus power supply; and another report indicating that the circuit breaker of the transformer rectifier unit No. 3 tripped, which resulted in the loss of the emergency DC/AC bus power supply. The actions specified in this AD are intended to ensure that the flightcrew is advised of the potential hazard related to failures of the emergency bus power supply, and the procedures necessary to address it.
AD 95-22-02 · published Oct 30, 1995, effective Nov 29, 1995
BAE Systems (Operations) Limited Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model ATP airplanes, that currently requires daily and/or pre-flight cleaning and inspections to detect damaged main landing gear (MLG) wheel bearings and replacement of discrepant parts. That AD was prompted by reports of failure of the MLG wheel bearings. This action requires an additional inspection, in lieu of the pre-flight inspection, for certain airplanes. This action also requires the accomplishment of a terminating modification that eliminates the need for daily and pre-flight inspections. The actions specified by this AD are intended to prevent failure of the MLG wheel bearing, which could result in detachment of a MLG wheel from the airplane.
AD 95-22-07 · published Oct 30, 1995, effective Dec 27, 1995
de Havilland DHC-6 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 83-26- 05 and AD 86-15-08, which currently require repetitively inspecting the horizontal stabilizer attachment fittings for cracks or looseness on certain de Havilland DHC-6 series airplanes, and, if a cracked or loose part is found, modifying the horizontal stabilizer. This action retains the repetitive inspection requirement of the existing AD's, requires incorporating an improved modification for airplanes with a certain modification design as terminating action for the repetitive inspections, and making these inspection-terminating modifications optional for other affected airplanes. Reports of loose horizontal stabilizer attachment fittings on airplanes incorporating the inspection-terminating modifications required by AD 83-26-05 prompted this action. The actions specified by this AD are intended to prevent separation of the horizontal stabilizer from the airplane caused by a cracked attachment fitting, and subsequent loss of control of the airplane.
AD 95-21-02 · published Oct 13, 1995, effective Nov 17, 1995
Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A 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 helicopters with certain main rotor (M/R) drive shafts installed, that currently requires a one-time radiographic inspection or other non- destructive inspection of certain M/R drive shafts for cracks, distortion, corrosion, or other surface damage, at specified time intervals or upon the occurrence of specified conditions. This amendment requires the same inspections as the previous AD, but expands the applicability of certain inspections to additional models of the affected helicopters, and excludes certain M/R drive shafts from certain inspections. This amendment is prompted by a reevaluation as a result of a comment to the previous AD suggesting the need to expand the applicability of certain inspections to additional models of the affected helicopters and to exclude certain M/R drive shafts from certain inspections. The actions specified by this AD are intended to prevent structural failure of the M/R drive shaft, separation of the M/ R from the helicopter, and subsequent loss of control of the helicopter.
AD 95-21-12 · published Oct 16, 1995, effective Nov 20, 1995
Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model MBB- BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, that requires initial and repetitive inspections of the main rotor (M/R) blade upper and lower surfaces for bulging. This amendment is prompted by two reported incidents in which a balance weight became detached from inside the M/R blade structure and migrated toward the tip of the M/R blade. The actions specified by this AD are intended to detect movement of a balance weight and to prevent severe vibrations and a subsequent precautionary landing.
