35 Airworthiness Directives: 30 airplane, 1 rotorcraft, 3 engine, 1 appliance.
AD 96-24-11 · published Dec 2, 1996, effective Jan 6, 1997
Israel Aircraft Industries (IAI), Ltd., Model 1123, 1124, and 1124A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all IAI, Ltd., Model 1123, 1124, and 1124A series airplanes, that requires repetitive inspections of the aileron push- pull tubes for excessive wear and the guide rollers for smooth rotation; and repair or replacement of worn parts with serviceable parts. This amendment is prompted by reports of excessive wear on the aileron push-pull tube in the area of the guide rollers. The actions specified by this AD are intended to prevent such wear, which could result in uneven movement of the control wheel, perforation of the aileron push-pull tube, and consequent reduced roll control of the airplane.
AD 96-25-02 · published Dec 4, 1996, effective Dec 27, 1996
Mitsubishi Heavy Industries, LTD. Models MU-2B-10, -15, -20, -25, -26, -26A, -30, -35, -36, -36A, -40, and -60 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Mitsubishi Heavy Industries, LTD. Models MU-2B-10, -15, -20, -25, -26, -26A, -30, -35, -36, -36A, -40, and -60 airplanes. This action requires revising the Limitations Section, the Procedures Section, and the Master Minimum Equipment List (MMEL) of the Airplane Flight Manual (AFM). These revisions require establishing a minimum airspeed for sustained level flight in icing conditions, limitations for the use of flaps for flight in icing conditions, cues for recognizing hazardous conditions, exiting procedures in icing conditions that are specific to Mitsubishi MU-2B series airplanes, and ensuring the wing illumination and taxi lights are operable prior to flight at night into known or forecast icing conditions. Several fatal accidents, involving certain Mitsubishi MU-2B series airplanes while flying in icing conditions, prompted this action. The actions specified by this AD are intended to prevent operating in conditions that are beyond the capability of the icing protection system, prevent aerodynamic stall at higher than normal airspeed because of icing conditions, and immediately provide the pilot with cues for recognizing hazardous conditions and exiting these conditions, which if not followed, could result in loss of the airplane.
AD 96-23-11 · published Dec 5, 1996, effective Dec 5, 1996
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 a one-time test to verify if the disconnect lock of the aileron disconnect control system functions properly, and follow-on actions, if necessary. This amendment is prompted by a report that a disconnect unit of the aileron control system was found to be jammed and unserviceable. The actions specified in this AD are intended to detect and correct such jamming, which could result in reduced controllability of the airplane.
AD 96-23-12 · published Dec 5, 1996, effective Dec 5, 1996
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 a one-time check of the left and right main landing gear leg assemblies to determine whether certain assemblies have been installed; and the replacement of certain discrepant retaining bolts on these assemblies with correctly manufactured bolts. This amendment is prompted by a report indicating that some of these retaining bolts have failed during the assembly and installation of a main landing gear unit, due to an incorrect process that was used during the manufacture of the bolts. The actions specified in this AD are intended to prevent structural damage to the main landing gear due to failure of the retaining bolts which, if not corrected, could result in reduced controllability of the airplane during takeoff, landing, and taxiing.
AD 96-23-13 · published Dec 5, 1996, effective Dec 5, 1996
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-215-1A10 series airplanes. This action requires a one-time inspection of the three DC generators to ensure that the extra unconnected bare copper wire is properly stowed. This amendment is prompted by reports indicating that unconnected bare copper wire, which was fitted inside of some DC generators installed on these airplanes, could cause a short circuit. The actions specified in this AD are intended to prevent a fire hazard that would be posed if a short circuit were to occur at this area in the presence of a combustible fuel-air mixture.
AD 96-24-06 · published Dec 5, 1996, effective Dec 10, 1996
Cessna Model 560 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-24-06 that was sent previously to all known U.S. owners and operators of certain Cessna Model 560 series airplanes by individual letters. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to provide the flightcrew with limitations, operational procedures, and performance information to be used during approach and landing when residual ice is present or can be expected. This amendment is prompted by reports indicating that, while operating in icing conditions or when ice is on the wings, some of these airplanes have experienced uncommanded roll at a speed at (or slightly higher than) the speed at which the stall warning system is activated. The actions specified by this AD are intended to prevent uncommanded roll of the airplane during approach and landing when residual ice is present or can be expected.
AD 96-22-02 · published Dec 11, 1996, effective Dec 11, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP airplanes, that requires repetitive inspections of the ram air inlet ducts for structural integrity and security of fasteners, and repairs, if necessary. This amendment also provides an optional terminating modification for the repetitive inspections. This amendment is prompted by a report of the separation of a ram air inlet duct from the airplane during flight. The actions specified by this AD are intended to prevent such separation, which could pose a hazard to persons or property on the ground.
AD 96-22-04 · published Dec 11, 1996, effective Dec 11, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model Avro 146-RJ70A, -RJ85A, and -RJ100A airplanes, that requires repetitive inspections for cracking of fuselage frame 29, and repair, if necessary. This amendment is prompted by results of fatigue testing, which 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 96-22-05 · published Dec 11, 1996, effective Dec 11, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes, that requires a one-time inspection of terminal block "D" to ensure that a two-way link is installed, and installation of a new link, if necessary. This amendment is prompted by a report indicating that a two-way link that should be installed on direct current (DC) panel No. 1 may be missing from certain airplanes. The actions specified by this AD are intended to ensure that a two-way link is installed. If the link is not installed, it could result in loss of the emergency electrical system and, consequently, increased pilot workload and possible reduced controllability of the airplane.
AD 96-22-07 · published Dec 11, 1996, effective Dec 11, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4100 series airplanes, that requires replacement of the existing decompression panel on the aft bulkhead of the toilet compartment with a modified decompression panel. This amendment is prompted by a report that a decompression panel that does not meet flammability requirements was installed on these airplanes during manufacture. The actions specified by this AD are intended to prevent injury to the crew and passengers and damage to the airplane structure due to the incapability of the decompression panel to contain a fire.
AD 96-22-15 · published Dec 11, 1996, effective Dec 11, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive Tap Test inspections to detect debonding of the elevator skins, and corrective actions, if necessary. This amendment is prompted by a report of a debonded area of the upper skin of an elevator that was discovered during a visual inspection. The actions specified by this AD are intended to prevent the presence of water in the elevator, which could cause debonding of the elevator skins and, consequently, adversely affect the structural integrity of the elevator.
AD 96-25-01 · published Dec 17, 1996, effective Jan 22, 1997
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires inspections to detect broken sealant common to the lower horizontal clevis of the inboard and outboard strut midspar fittings and of the fasteners, and various follow-on actions. This action also requires inspections to detect cracking, corrosion, and fracturing of the lower horizontal clevis, and replacement of discrepant parts with new or serviceable parts, or repair, if necessary. This action also provides for optional terminating action for the inspections. This amendment is prompted by reports of fatigue cracking, stress corrosion cracking, and fracturing of the horizontal clevis of the inboard midspar fitting of the number three strut. The actions specified in this AD are intended to detect and correct such cracking and fracturing, which could result in drooping of the strut at the strut- to-wing interface, and consequent separation of the engine and strut from the airplane.
AD 96-23-08 · published Dec 19, 1996, effective Dec 19, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes, that requires repetitive tests of the integrity of the electrical circuit between the windshear computer and the flap position sensor, and repair of the electrical wiring, if necessary. This amendment also requires replacement of certain windshear computers with new computers, which, when accomplished, terminates the repetitive tests. This amendment is prompted by a report indicating that the existing windshear computer is not capable of detecting a signal indicating loss of flap position; this could result in the flightcrew following erroneous computer-generated guidance. The actions specified by this AD are intended to prevent the incapability of the windshear computer to detect the true flap position, which, if not corrected, could result in the inability of the flightcrew to avoid a windshear encounter, and consequent reduced controllability of the airplane.
AD 96-24-14 · published Dec 19, 1996, effective Jan 27, 1997
Lockheed Martin Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model 382 series airplanes, that requires that all landing gear brakes be inspected for wear and replaced if the wear limits prescribed in this AD are not met, and that the new landing gear brake wear limits be incorporated into the FAA-approved maintenance inspection program. This amendment is 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; and the subsequent review of allowable brake wear limits for all transport category airplanes. The actions specified by this AD are intended to prevent loss of brake effectiveness during a high energy RTO.
AD 96-24-15 · published Dec 19, 1996, effective Jan 27, 1997
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes, and KC-10A (military) series airplanes, that requires high frequency eddy current inspections to detect cracks in the secondary pivot support of the horizontal stabilizer, and various follow-on actions, if necessary. This amendment is prompted by reports of crack development in the secondary pivot support of the horizontal stabilizer due to fatigue. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the horizontal stabilizer and, consequently, lead to reduced controllability of the airplane.
AD 96-24-16 · published Dec 19, 1996, effective Jan 27, 1997
Raytheon Model BAe 125-800A, Model Hawker 800, and Model Hawker 800XP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe 125-800A, Model Hawker 800, and Model Hawker 800XP series airplanes, that requires the filling of two tooling holes on the firewalls of the left and right engine pylons with sealant. This amendment is prompted by notification from the manufacturer that these holes were not sealed during production. The actions specified by this AD are intended to prevent an engine fire from moving to the fuselage and to the lines that carry flammable fluid that are located inboard of the firewall.
AD 96-25-07 · published Dec 19, 1996, effective Jan 27, 1997
Airbus Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires repetitive visual inspections and end-float checks of the ram air turbine (RAT), and replacement of the RAT, if necessary. This amendment requires installation of a modified RAT, which constitutes terminating action for the currently required inspections. This amendment is prompted by the development of a modification of the RAT that positively addresses the unsafe condition. The actions specified by this AD are intended to prevent the RAT from breaking away from its support leg, which could damage the airplane structure and systems, and could injure ground personnel.
AD 96-25-19 · published Dec 19, 1996, effective Jan 27, 1997
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 either the application of a vapor sealant on the back of the receptacle of the auxiliary power unit (APU) power feeder cable; or a one-time visual inspection for gold-plating and evidence of damage of the connector contacts of the power feeder cable of the APU generator, and various follow-on actions. This amendment adds a requirement for replacement of certain connector contacts (pins/sockets) with gold-plated contacts. This amendment is prompted by reports of burning and arcing of the connector contacts of the power feeder cable of the APU generator. The actions specified by this AD are intended to reduce the potential for a fire hazard as a result of such burning or arcing.
AD 96-25-03 · published Dec 20, 1996, effective Jan 24, 1997
Raytheon (Beech) Model 400A, 400T (Military T-1A), and 400T (Military TX) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A and 400T series airplanes, that currently requires an inspection of certain flap roller retention components to detect discrepant or missing parts; replacement of those parts; and installation of new washers on the roller attach bolts. This amendment requires the replacement of certain previously- installed washers with new and stronger washers. This amendment also expands the applicability of the rule to include additional airplanes. This amendment is prompted by reports indicating that some locking tab washers on the roller attach bolt could fail, due to the absence of an inner tang. The actions specified by this AD are intended to prevent the loss of roller attach nuts and the flap roller, which could result in the loss of a flap when the airplane is subject to load limit conditions, and consequently lead to reduced controllability of the airplane.
AD 96-24-01 · published Dec 27, 1996, effective Dec 27, 1996
Fokker Services Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires replacement of certain rudder horn assemblies with a new assembly. For certain airplanes, the amendment also requires replacement of certain rudder control rods with a new rod. This amendment is prompted by reports of cracked rudder horns and a cracked rudder control rod, caused by impact overload. The actions specified by this AD are intended to prevent such an overload and consequent cracking of the subject parts, which could result in reduced structural integrity of the rudder horn assembly or loss of rudder control; this condition could lead to reduced controllability of the airplane.
AD 96-24-02 · published Dec 27, 1996, effective Dec 27, 1996
328 Support Services GmbH Airplanes
AD 96-25-09 · published Dec 27, 1996, effective Jan 31, 1997
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of the thrust reverser doors, and replacement of the Collins multifunction display units (MFDU) with new MFDU's. This amendment also requires installation of a placard if the replacement of the MFDU is accomplished prior to modification of the thrust reverser door. This amendment is prompted by a report that cracks were found in the flanges of the main hinge fittings of the horizontal stabilizer, which were caused by higher than anticipated loads induced during thrust reverser operation. The actions specified by this AD are intended to ensure the structural integrity of the horizontal stabilizer by reducing the thrust reverser loads on the horizontal stabilizer.
AD 96-25-14 · published Dec 27, 1996, effective Jan 31, 1997
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -30, and -40 series airplanes, and KC-10 (military) series airplanes, that requires repetitive high frequency eddy current (HFEC) inspections to detect cracks in the number 4 banjo fitting on the rear spar of the vertical stabilizer, and repair and modification of the vertical stabilizer, if necessary. It also requires the installation of a modification as terminating action for the repetitive inspections. This amendment is prompted by reports of failed attach bolts and cracking found in the area of the number 4 banjo fitting, which were caused by higher than normal operating stresses. The actions specified by this AD are intended to prevent reduction in the structural integrity of this fitting due to failed bolts and cracking.
AD 96-25-18 · published Dec 27, 1996, effective Jan 31, 1997
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires inspections of the components of the leading edge outboard slat; replacement of the control rod end, if necessary; and various follow-on actions. This amendment is prompted by reports of skewed panels of the outboard leading edge slat due to failure of a corroded rotary actuator or the control rod. The actions specified by this AD are intended to prevent such conditions, which could result in reduced controllability of the airplane and damage to or cracking of the leading edge slats or the fixed leading edge of the wing.
AD 96-26-02 · published Dec 27, 1996, effective Jan 13, 1997
FLS Aerospace (Lovaux) Ltd. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain FLS Aerospace (Lovaux) Ltd. OA7 Optica series 300 airplanes equipped with a Hoffman fan, part number HO-E315/122EZ, and fan shaft extension. This AD requires replacing the fan shaft extension with one that incorporates Modification No. B2/MOD/047. The AD results from a quality control review that shows that the four counterbores on the fan shaft extension to engine attachment flange have excessive depths. The actions specified in this AD are intended to prevent cracks from forming in the fan shaft extension flange and subsequent structural failure of this area because of counterbores with excessive depth.
AD 96-25-08 · published Dec 30, 1996, effective Feb 3, 1997
de Havilland Model DHC-7 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that requires performing a review of the airplane maintenance records to determine if any insulation blankets have been repaired or changed during service, and various follow-on actions, if necessary. This amendment is prompted by reports of corrosion forming on areas of the airplane structure where black film thermal insulation blankets are used. The actions specified by this AD are intended to prevent such corrosion, which could result in degradation of the structural capability of the airplane fuselage and consequent sudden loss of cabin pressure.
AD 96-25-16 · published Dec 30, 1996, effective Feb 3, 1997
Viking Air Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-7 series airplanes, that requires modification of the power control relay installation of the emergency lights. This amendment also requires revising the FAA-approved Airplane Flight Manual to include procedures for turning off and on the emergency lights switch in certain conditions. This amendment is prompted by a report that the emergency lights do not automatically illuminate when all generated electrical power on the airplane is lost and the power to the left essential bus is maintained from the aircraft batteries. The actions specified by this AD are intended to ensure that the emergency lights illuminate when needed in an emergency situation.
AD 96-25-17 · published Dec 30, 1996, effective Feb 3, 1997
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires inspections to detect bent or damaged tie links and washers of the elevator feel and centering unit, and replacement of the centering unit with a new or serviceable unit, if necessary. This amendment also provides an optional replacement of the centering unit, which, if accomplished with the installation of supports and a stop bolt, constitutes terminating action for the repetitive inspections. This amendment is prompted by a report of high control column forces that occurred during takeoff and landing. The actions specified by this AD are intended to prevent such high forces, which could result in restriction of elevator control during takeoff, climbout, and landing.
AD 96-24-12 · published Dec 31, 1996, effective Dec 31, 1996
ATR - GIE Avions de Transport R gional Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires modification of the pitch uncoupling mechanism of both elevators. This amendment is prompted by reports of fatigue cracking of the pitch uncoupling mechanism and the torque tube of the elevator. Failure of the pitch uncoupling mechanism due to fatigue cracking could result in the uncommanded uncoupling of the elevators. The actions specified by this AD are intended to prevent such fatigue cracking and subsequent uncommanded uncoupling of the elevators, which could result in reduced controllability of the airplane.
AD 96-26-04 · published Dec 31, 1996, effective Jan 6, 1997
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires a one-time inspection to detect fatigue cracking of the vertical beam webs and chords of the nose wheel well (NWW) at body station (BS) 300 and BS 320, and repair, if necessary. This action also requires inspections to detect fatigue cracking of the inner chord and web of the fuselage frames at BS 300 and BS 320, and repair, if necessary. This amendment is prompted by a report indicating that the fuselage frames at BS 300 and BS 320 severed approximately 10 inches outboard of the NWW side panel and resulted in accelerated fatigue cracking and subsequent failure of the adjacent NWW vertical beams. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in collapse of the NWW pressure bulkhead and subsequent rapid decompression of the airplane.
AD 96-23-01 · published Dec 11, 1996, effective Dec 11, 1996
Bell Helicopter Textron Canada Limited Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada, Ltd. (BHTC) Model 206L-1 helicopters that have a Kratos turbine outlet temperature (TOT) indicator (Kratos indicator) installed, that requires replacing certain Kratos indicators. This amendment is prompted by manufacturer's tests and FAA analyses that show certain Kratos indicators may incorrectly provide low-temperature readings when the battery voltage is below 10 volts. The actions specified by this AD are intended to prevent false low-temperature indications, which could result in overheating of the engine turbine (turbine) and subsequent thermal fatigue damage to the turbine wheel.
AD 96-23-14 · published Dec 2, 1996, effective Jan 2, 1997
Pratt & Whitney Division Engines
This amendment supersedes two existing airworthiness directives (ADs), applicable to Pratt & Whitney (PW) JT8D series turbofan engines, that currently require repetitive eddy current, fluorescent penetrant, fluorescent magnetic penetrant, or visual inspections for cracks in the rear flange, and ultrasonic, fluorescent penetrant, or fluorescent magnetic penetrant inspections for cracks in the PS4 boss, and drain bosses of the combustion chamber outer case (CCOC); and an additional inspection of the CCOC rear flange for intergranular cracking. This amendment requires reducing the rear flange inspection interval for CCOCs when only the aft face of the rear flange has been inspected, and introducing an improved ultrasonic probe assembly. In addition, this amendment introduces a rotating eddy current probe for shop inspections in which the case is removed from the engine. Also, this amendment eliminates fluorescent penetrant inspection (FPI), fluorescent magnetic particle inspection (FMPI), and visual inspections from hot section disassembly level inspection procedures. This amendment is prompted by reports of crack origins in the forward face of the rear flange that could not be detected by the inspection methods for installed CCOC's that were mandated in the current ADs. The actions specified by this AD are intended to prevent uncontained engine failure, inflight engine shutdown, engine cowl release, and airframe damage.
AD 96-25-10 · published Dec 19, 1996, effective Feb 18, 1997
Pratt & Whitney Division Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT9D series turbofan engines, that requires installing an improved design turbine exhaust case (TEC) with a thicker containment wall, modifying the existing TEC to incorporate a containment shield, or modifying the existing TEC to replace the "P" flange and case wall. This amendment is prompted by reports of 64 uncontained engine failures since 1972. The actions specified by this AD are intended to prevent release of uncontained debris from the TEC following an internal engine failure, which can result in damage to the aircraft.
AD 96-25-11 · published Dec 30, 1996, effective Jan 29, 1997
CFM International, S.A. Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to all CFM International (CFMI) CFM56-3C-1 and certain CFM56-3B-2 engines, that currently requires the removal from service of certain fan disk and fan blade hardware, and limits the use of CFM56- 3C-1 thrust levels. This amendment requires removal of additional fan blade hardware, requires an Airplane Flight Manual (AFM) revision to impose thrust level limitations for airplanes equipped with affected engines, and requires the installation of redesigned fan blades as a terminating action to the thrust level limitations of this AD. The existing AD requirements for certain CFM56-3B-2 engines are unchanged and carried over into this final rule AD. This amendment is prompted by the availability of redesigned fan blades that are not subject to the thrust level limitations, and the need to clarify the AD requirements by deleting references to specific AFMs. The actions specified by this AD are intended to prevent a fan blade failure that can result in complete loss of engine power.
AD 96-25-12 · published Dec 27, 1996, effective Jan 13, 1997
BAE Systems (Operations) Limited, The Boeing Company, Bombardier Inc., Cessna Aircraft Company, Dassault Aviation, Embraer - Empresa Brasileira de Aeronautica S.A., Airbus Helicopters, Fokker Services, Gulfstream Aerospace Corporation, Textron Aviation Inc., Kelowna Flightcraft R & D Ltd., Lockheed Martin Corporation, Sabreliner Corporation, Sundstrand Aerospace, Viking A
This amendment adopts a new airworthiness directive (AD) that is applicable to Sundstrand T-62T-40C series auxiliary power units (APUs). This action requires removal from service of certain compressor wheels in accordance with a drawdown schedule, and replacement with serviceable parts, and establishes a new cyclic life limit for the existing compressor wheels. This amendment is prompted by reports of compressor wheel ruptures. The actions specified in this AD are intended to prevent compressor wheel rupture, which could result in an uncontained APU failure and damage to the aircraft.
