88 Airworthiness Directives: 61 airplane, 12 rotorcraft, 8 engine, 1 appliance, 6 glider.
AD 98-11-21 · published Jun 1, 1998, effective Jul 6, 1998
de Havilland Model DHC-8-102, -103, and -301 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-102, -103, and -301 series airplanes, that requires a one-time inspection for wear and breakage of wire segments of the individual lighting units of the ceiling and sidewall lights, and replacement of any damaged wiring. This amendment also requires installation of teflon spiral wrap on the wiring of the ceiling and sidewall lights. This amendment is prompted by reports of chafing found on the electrical wiring of the cabin ceiling lighting system. The actions specified by this AD are intended to prevent the possibility of a fire on an airplane due to such chafing and consequent short circuiting, overheating, and smoking of the wires on the aircraft structure.
AD 98-11-22 · published Jun 1, 1998, effective Jul 6, 1998
Short Brothers Model SD3-60 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes, that requires a one-time inspection to detect discrepancies of certain diode mounting assemblies on specified electrical panels; follow-on actions; and repair or replacement with serviceable components, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent overheating and possible failure of certain electrical diodes, which could result in loss of electrical service to one or more airplane electrical circuits.
AD 98-11-23 · published Jun 3, 1998, effective Jul 8, 1998
Construcciones Aeronauticas, S.A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires modification of certain fastener holes of the center wing. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking in this area, which could result in reduced structural integrity of the wing.
AD 98-11-25 · published Jun 3, 1998, effective Jul 8, 1998
de Havilland Model DHC-8-311 and -315 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-311 and -315 series airplanes, that requires replacement of the nitrogen cylinder assemblies that inflate the airplane's ditching dams with improved nitrogen cylinder assemblies. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the ditching dams to inflate fully during an emergency water landing, which could result in water entering the airplane.
AD 98-11-26 · published Jun 3, 1998, effective Jul 8, 1998
Saab Model SAAB 340B and SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B and SAAB 2000 series airplanes, that requires modification of the check valves of the airfoil de-icing system, or replacement of the check valves with improved valves. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the check valves, which could result in loss of airfoil de- icing capability during single engine operation, and consequent reduced controllability of the airplane.
AD 98-11-27 · published Jun 3, 1998, effective Jul 8, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of the existing pressure dump and relief valves in the main and auxiliary hydraulic systems with new valves. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the pressure dump and relief valves in the main and auxiliary hydraulic systems, which could cause a loss in hydraulic pressure for roll control spoilers and brakes, and consequent reduced controllability of the airplane.
AD 98-11-28 · published Jun 3, 1998, effective Jul 8, 1998
British Aerospace Model BAe Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe Avro 146-RJ series airplanes, that requires a one-time inspection of certain electrical wires in the electrical equipment bay to determine if ERMA terminal lugs are installed; and replacement with new parts, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the electrical circuit terminal lugs, which could result in electrical system failure, and consequent reduced controllability of the airplane.
AD 98-11-29 · published Jun 3, 1998, effective Jul 8, 1998
British Aerospace Model BAe 146 Series Airplanes and Model Avro 146-RJ Series 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 to detect corrosion of the threads of the eyebolt and piston rod on the retraction jack of the main landing gear (MLG); and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent corrosion of the threads of the eyebolt and piston rod on the retraction jack of the MLG, which may cause the eyebolt to detach from the jack, and consequent unrestrained MLG deployment or inability to retract the MLG.
AD 98-11-30 · published Jun 3, 1998, effective Jul 8, 1998
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires inspection of the main landing gear (MLG) bushing seats to detect cracks, and repair of the bushing hole or replacement of strut bushings with new bushings, if necessary. This amendment also requires replacement of the plain bearings of the MLG shock absorber with new bearings. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent structural failure of the MLG due to fatigue cracking of the strut bushing seat.
AD 98-11-31 · published Jun 3, 1998, effective Jul 17, 1998
British Aerospace Jetstream Model 3101 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace (BAe) Jetstream Model 3101 airplanes equipped with a certain autopilot. This AD requires modifying the autopilot elevator electric system relays by installing two additional relays and associated wiring changes in the relay box located under the right hand crew seat. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the autopilot elevator electric system relays for the up and down trim interlocks, which could result in uncommanded trim servo operation and possible loss of control of the airplane.
AD 98-12-01 · published Jun 4, 1998, effective Jul 13, 1998
Pilatus Aircraft Ltd. Models PC-6, PC- 6/A, PC-6/B, and PC-6/C Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-6, PC-6/A, PC-6/B, and PC-6/C series airplanes equipped with turbo-prop engines. This AD requires modifying the fuel system to improve the venting between the collector tank, the main wing tanks, and the engine. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent engine fuel starvation during maximum climb and descent caused by poor fuel tank venting with low fuel levels, which could result in a loss of engine power during critical phases of flight.
AD 98-12-02 · published Jun 4, 1998, effective Jul 17, 1998
SOCATA Groupe Aerospatiale Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA Groupe Aerospatiale (SOCATA) Model TBM 700 airplanes. This AD requires inspecting the elevator trim tab fittings for cracks, and replacing any elevator trim tab found to have cracks. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent cracks in the elevator trim tab fittings, which could result in separation of the elevator trim tab and loss of control of the airplane.
AD 98-12-11 · published Jun 5, 1998, effective Jul 24, 1998
British Aerospace Jetstream Model 3101 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3101 airplanes. This AD requires modifying the emergency hydraulic hand-pump by increasing the length of the access aperture. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent difficulty accessing the emergency hydraulic hand-pump because of the current design, which, in the event of a hydraulic system failure, could result in the inability to operate the flaps and landing gear.
AD 98-12-10 · published Jun 8, 1998, effective Jul 17, 1998
Avions Mudry et Cie Model CAP 10B Airplanes
This amendment supersedes Airworthiness Directive (AD) 93-10- 11, which currently requires installing an inspection opening in the wing, repetitively inspecting the upper wing spar cap for cracks, and repairing any cracks on all Avions Mudry et Cie (Avions) Model CAP 10B airplanes. This AD will retain the same actions already required by AD 93-10-11, and will add inspecting, and repairing if necessary, the lower surface of the wing spar. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural cracks in the wing spar, which could lead to loss of a wing and loss of control of the airplane.
AD 98-12-13 · published Jun 8, 1998, effective Jul 18, 1998
Industrie Aeronautiche e Meccaniche Model Piaggio P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires modifying the low pitch stop switch support. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent low pitch stop switch support displacement, which could result in an improper cockpit indication that the propeller is in the Beta range and cause loss of control of the airplane.
AD 98-12-14 · published Jun 8, 1998, effective Jul 18, 1998
AERMACCHI S.p.A. S.205 Series and Models S.208 and S.208A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain AERMACCHI S.p.A. (AERMACCHI) S.205 series and Models S.208 and S.208A airplanes. This AD requires inspecting the flap cable pulley bracket for correct alignment and correcting any misalignment; inspecting the flap control cable for wear (nicks, cuts, frays, etc.), and replacing the flap control pulley bracket and flap control cable if worn. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent flap control failure, which could result in loss of control of the airplane.
AD 98-12-18 · published Jun 9, 1998, effective Jul 14, 1998
Airbus Model A320-111, -211, and -231 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action, if necessary. This amendment also provides for an optional terminating modification for the repetitive inspection requirements. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel.
AD 98-12-24 · published Jun 10, 1998, effective Jun 25, 1998
Airbus Model A310 Series Airplanes Equipped With General Electric Model CF6-80A3 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 series airplanes. This action requires a one-time inspection to detect cracked or broken links of the aft engine mounts, and replacement of any cracked or broken link with a serviceable link. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking of the links of the aft engine mounts, which could result in failure of the aft engine attachment and consequent separation of the engine from the airplane.
AD 98-12-25 · published Jun 10, 1998, effective Jul 15, 1998
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires a one-time inspection to detect corrosion, wear, or damage of the operating mechanism of the forward door of the main landing gear (MLG); operational inspections to ensure smooth operation of the MLG operating mechanism; and follow-on actions. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent partial seizure of the forward door of the MLG operating mechanism, which could result in the inability to lower or retract the MLG.
AD 98-12-26 · published Jun 10, 1998, effective Jul 15, 1998
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time inspection to determine the torque values of the coupling fitting attachment bolts at fuselage station 10790, and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent loss of the coupling fitting attachment bolts between the center wing section and the fuselage, and consequent reduced structural integrity of the airplane.
AD 98-12-27 · published Jun 10, 1998, effective Jul 15, 1998
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive magnetic particle inspections to detect cracking of the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the splined operating shaft of the internal door handle, which could result in failure of the internal door handle, inability to operate the door during an emergency evacuation, and consequent injury to airplane occupants.
AD 98-12-28 · published Jun 10, 1998, effective Jul 15, 1998
CASA Model C-212 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires repetitive inspections for cracking in the false spar of the wing, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking in the false spar, which could result in reduced structural integrity of the wing.
AD 98-13-02 · published Jun 11, 1998, effective Jul 7, 1998
Raytheon Aircraft Company Models 35, A35, B35, and 35R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) Models 35, A35, B35, and 35R airplanes (commonly referred to as Beech Models 35, A35, B35, and 35R airplanes). This AD requires fabricating a placard that restricts the never exceed speed (Vne) to no more than 144 miles per hour (MPH) or 125 knots (KTS) indicated airspeed (IAS), and installing this placard on the instrument panel within the pilot's clear view. This AD also requires marking a red line on the airspeed indicator glass at 144 MPH (125 KTS), marking a white slippage mark on the outside surface of the airspeed indicator between the glass and case, and inserting a copy of this AD into the Limitations Section of the airplane flight manual (AFM). This AD is the result of several occurrences of in-flight vibration on the affected airplanes. The actions specified by this AD are intended to prevent in-flight vibrations caused by the affected airplanes operating at excessive speeds, which could result in airplane damage and possible loss of control of the airplane.
AD 98-12-23 · published Jun 12, 1998, effective Jul 28, 1998
British Aerospace Model H.P. 137 Jetstream Mk. 1, Jetstream Model 3101, Jetstream Model 3201, and Jetstream 200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace (BAe) Model H.P. 137 Jetstream Mk. 1, Jetstream Model 3101, Jetstream Model 3201, and Jetstream 200 series airplanes. This AD requires replacing the windshield wiper arm attachment bolts and windshield wiper arm on all of the affected airplanes; and measuring the material thickness of the upper and lower toggle attachment brackets on the nose landing gear of the affected airplanes, and replacing the toggle attachment bracket lugs. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the windshield wiper arm from corroding, detaching from the airplane during flight, and penetrating the fuselage, which could result in possible injury to the pilot and passengers; and to prevent collapse of the nose landing gear caused by design deficiency, which could result in loss of control of the airplane during landing operations.
AD 98-12-31 · published Jun 12, 1998, effective Sep 10, 1998
British Aerospace Jetstream Model 3101 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3101 airplanes. This AD requires repositioning the fuel cross feed pipes in the lower center fuselage to give an overall clearance of 2 inches when measuring from the bottom of Frame Station 223. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified in this AD are intended to prevent the fuel pipe from fracturing during a wheels up landing because of the positioning of the fuel cross feed pipes, which could result in an airplane fire.
AD 98-12-33 · published Jun 15, 1998, effective Jul 20, 1998
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking on the connecting angle between frame 56 and the right-hand frame support at stringer 38; and replacement of the connecting angle, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking on the connecting angle, which could result in reduced structural integrity of the airplane.
AD 98-12-34 · published Jun 15, 1998, effective Jul 20, 1998
Construcciones Aeronauticas, S.A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires modification of the forward beam of the vertical stabilizer by the installation of a structural reinforcement plate. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent in-flight structural deformation or failure of the vertical stabilizer, resulting in reduced controllability of the airplane.
AD 98-12-35 · published Jun 15, 1998, effective Jul 20, 1998
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires replacement of the actuating ram bobbin and O-ring seals of the main landing gear (MLG) with new bobbins and improved O-ring seals. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent loss of dampening of the MLG actuating ram, which could result in failure of the MLG lockstruts, and consequent structural damage to the airplane.
AD 98-13-01 · published Jun 15, 1998, effective Jul 20, 1998
Aerospatiale Model ATR42 and ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42 and ATR72 series airplanes, that requires replacement of the left longitudinal net of the forward cargo compartment with a new reinforced net. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent blockage of the access door, which could restrict access for crewmembers between the flight deck and the passenger compartment during normal operations or an emergency evacuation.
AD 98-13-08 · published Jun 17, 1998, effective Jul 31, 1998
Pilatus Aircraft Ltd. Model PC-12 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-12 airplanes. This AD requires replacing and re-routing the power return cables on the starter generator and generator 2, inserting a temporary revision to the pilot operating handbook (POH), and installing a placard near the standby magnetic compass. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent directional deviation on the standby magnetic compass caused by an overload of electrical current in the airplane structure, which could result in flight-path deviation during critical phases of flight in icing conditions and instrument meteorologic conditions (IMC).
AD 98-13-10 · published Jun 17, 1998, effective Jul 8, 1998
Cessna Aircraft Company Model 182S Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Model 182S airplanes. This AD requires repetitively inspecting all engine exhaust muffler end plates (four total) for cracks and replacing any muffler where an end plate is found cracked. The AD also requires fabricating and installing a placard that specifies immediately inspecting all engine exhaust muffler end plates any time the engine backfires upon start-up. This AD is the result of incidents where cracks were found in an engine exhaust muffler end plate on several of the affected airplanes. These cracks were caused by high stresses imposed on the attachment of the exhaust at the area of the firewall. The actions specified by this AD are intended to detect and correct damage to the engine exhaust mufflers caused by such high stress and cracking, which could result in exhaust gases entering the airplane cabin with consequent crew and passenger injury.
AD 98-13-12 · published Jun 18, 1998, effective Jul 6, 1998
Boeing Model 737, 747, 757, 767, and 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737, 747, 757, 767, and 777 series airplanes. This action requires a one-time inspection to detect discrepancies of the fasteners that connect the pushrods to the rudder pedal assemblies; and corrective actions, if necessary. This amendment is prompted by reports of loose and missing fasteners due to incorrect installation. The actions specified in this AD are intended to prevent loss of rudder control, jamming of the rudder system, uncommanded movement of the rudder system, and consequent reduced controllability of the airplane, due to loose or missing fasteners that connect the pushrods to the rudder pedal assemblies.
AD 98-13-13 · published Jun 18, 1998
Mitsubishi Heavy Industries Ltd. Model YS-11 and YS-11A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Mitsubishi Model YS-11 and YS-11A series airplanes. This amendment requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller beta was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 98-13-15 · published Jun 18, 1998
Dassault Model Mystere-Falcon 200, Fan Jet Falcon, and Mystere-Falcon 20 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 200, Fan Jet Falcon, and Mystere-Falcon 20 series airplanes, that requires repetitive inspections to detect cracks at the attaching holes of the wing-to- fuselage fairings and to ensure tightness of the attaching screws; and repair of any discrepancy. This amendment also requires installation of cupwashers under the vertical seams of the upper fairings. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent loss of the wing-to-fuselage upper fairings during flight, which could result in the fairings impacting the engines or tail sections, and consequent reduced controllability of the airplane.
AD 98-13-03 · published Jun 19, 1998, effective Aug 3, 1998
British Aerospace Model H.P. 137 Mk1, Jetstream Series 200, and Jetstream Model 3101 Airplanes.
This amendment supersedes Airworthiness Directive (AD) 82-20- 04 R1, which currently requires repetitively inspecting the main landing gear (MLG) hinge fitting, support angles, and attachment bolts on British Aerospace H.P. 137 Mk1 and Jetstream series 200 airplanes, and repairing or replacing any part that is cracked beyond certain limits. This AD requires installing improved design MLG fittings, as terminating action for the repetitive inspections that are currently required by AD 82-20-04 R1, and will incorporate the Jetstream Model 3101 airplanes into the Applicability of the AD. 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. The actions specified by this AD are intended to prevent structural failure of the MLG caused by fatigue cracking, which could result in loss of control of the airplane during landing operations.
AD 98-13-07 · published Jun 19, 1998, effective Aug 1, 1998
Industrie Aeronautiche e Meccaniche Model Piaggio P-180 Airplanes.
This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires accomplishing a leakage check of all lavatory water tube/hose connections, and correcting the installation of these connections if leakage is found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent water leakage from the lavatory water duct system, which could collect in the fuselage, freeze in cold weather conditions, and cause the rudder control system to jam.
AD 98-11-52 · published Jun 24, 1998, effective Jun 29, 1998
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) T98-11-52 that was sent previously to all known U.S. owners and operators of Boeing Model 737- 100, -200, -300, -400, and -500 series airplanes by individual telegrams. This AD requires removal of the fuel boost pump wiring in the conduits of the wing and center fuel tanks; an inspection to detect damage of the wiring, and corrective action, if necessary; and eventual installation of teflon sleeving over the electrical cable. This action is prompted by reports of severe wear of the fuel boost pump wiring due to chafing between the wiring and the surrounding conduit inside the fuel tank; pin-hole-sized holes in the conduit that appear to be the result of arc-through of the conduit; and exposure of the main tank boost pump wire conductor inside a conduit and signs of arcing to the wall of the conduit. The actions specified by this AD are intended to detect and correct chafing and electrical arcing between the fuel boost pump wiring and the surrounding conduit, which, if not corrected, could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank.
AD 98-13-29 · published Jun 24, 1998
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 98-13-30 · published Jun 24, 1998
Gulfstream Aerospace Corporation Model G-159 (G-I) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Gulfstream Aerospace Corporation Model G-159 (G-I) airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 98-13-34 · published Jun 24, 1998, effective Jul 9, 1998
Empresa Brasileira de Aeronautica, S.A. (EMBRAER), Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-145 series airplanes. This action requires repetitive emergency extension (free-fall) functional tests of the nose landing gear (NLG), and lubrication of all NLG hinge points, to ensure that the NLG extends and locks down properly; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the NLG to extend and lock down properly, which could result in damage to the airplane structure, and consequent reduced controllability of the airplane upon landing.
AD 98-11-01 R1 · published Jun 25, 1998, effective Sep 22, 1998
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment revises Airworthiness Directive (AD) 98-11-01, which currently requires replacing the fuel tank vent valves and drilling a 4.8 millimeter (0.1875 inch) hole in each fuel filler cap on certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 98-11-01 also requires inserting a temporary revision in the Pilot's Operating Handbook (POH) that specifies checking to assure that the fuel filler cap hole is clear of ice and foreign objects. This AD maintains the requirements of AD 98-11-01, and adds the option of modifying the fuel tank vent valves instead of the drilling and POH requirements carried over from AD 98-11-01. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to continue to prevent moisture from entering the fuel tank inward vent valve and then freezing after a cold soak at altitude, which could result in wing airfoil distortion and structural damage with consequent degradation of the airplane's handling qualities.
AD 98-13-09 · published Jun 25, 1998, effective Aug 1, 1998
AERMACCHI S.p.A. Models F.260, F.260B, F.260C, and F.260D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain AERMACCHI S.p.A. (AERMACCHI) Models F.260, F.260B, F.260C, and F.260D airplanes. This AD requires marking the airspeed indicator to indicate the correct flap operation range and stall speed of the airplane. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent the airplane from stalling at an airspeed higher than anticipated, which could result in loss of control of the airplane.
AD 98-13-11 · published Jun 25, 1998, effective Aug 3, 1998
Raytheon Aircraft Company Model 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This action requires modifying the airplane by incorporating Raytheon Kit No. 129-5200-1, ``Ground Fine Switch Installation Kit''. This action is the result of design analysis during certification of 5.5 degree approach landings of the Model 1900D airplanes. The actions specified by this AD are intended to prevent a loose or misrigged ground fine switch, which could result in very hard landings causing structural damage to the airplane and possible passenger injury.
AD 98-13-14 · published Jun 25, 1998, effective Jul 30, 1998
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive rotating probe inspections of fastener holes and/or the adjacent tooling hole of a former junction of the aft fuselage, and corrective action, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced structural integrity of the aft fuselage caused by fatigue cracking of the former junction at frame 68. DATES: Effective July 30, 1998. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 30, 1998.
AD 98-13-16 · published Jun 25, 1998, effective Jul 30, 1998
Empresa Brasileira de Aeronautica, S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires replacement of the horizontal stabilizer anti-icing valve with a new anti-icing valve. This amendment also requires reinforcement of the insulation over the anti-icing ducts of the horizontal stabilizer thermal anti-icing system. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the horizontal stabilizer anti-icing valve, which could cause the horizontal stabilizer thermal anti-icing system to be inoperative, and could result in reduced controllability of the airplane.
AD 98-13-17 · published Jun 25, 1998, effective Jul 30, 1998
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER EMB-145 series airplanes, that requires modification of the windshield heating system in the flight compartment. This amendment is prompted by reports of overheating and delamination of the windshield because the windshield heating system failed to shut off during flight. The action specified by this AD is intended to prevent failure of the windshield heating system, which could result in reduced pilot visibility, structural degradation of the windshield, and depressurization of the airplane during flight.
AD 98-13-18 · published Jun 25, 1998, effective Jul 30, 1998
Airbus Model A319 and A321-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A321-100 series airplanes, that requires adjustment of the landing gear unlocked-stop screw; replacement of the shear pins in the reduction gear box and the landing gear pulley assembly with new or serviceable shear pins; a one-time inspection to detect discrepancies of the landing gear cut-out valve; an operational test of the uplock mechanical control system; and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent non-extension of one or more landing gears, consequent damage to the airplane structure, and possible injury to passengers and crewmembers.
AD 98-13-19 · published Jun 25, 1998, effective Jul 30, 1998
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series 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 a one- time detailed visual inspection of the forward fuel feed lines in the left- and right-hand engine nacelles for chafing; replacement of damaged parts with serviceable parts; and modification of the supports and improved routing for the high- and low-tension leads of the inboard ignition units. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing on the forward fuel feed lines, which could result in fuel leakage and consequent increased risk of fire in the engine nacelles.
AD 98-13-23 · published Jun 25, 1998, effective Jul 30, 1998
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 corrosion and cracking of the lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap, and the outer skin; and repair, if necessary. This amendment is prompted by cracking found at the lower corner of the horizontal stabilizer cutout longeron during a full scale fatigue test. The actions specified by this AD are intended to prevent such cracking, which could result in reduced structural integrity of the horizontal- stabilizer cutout longeron.
AD 98-13-24 · published Jun 25, 1998, effective Jul 30, 1998
Bombardier Model CL-600-2B19 (Regional Jet Series 100) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to prohibit the use of mach trim and to add speed restrictions if the autopilot is disengaged or inoperative. That AD also requires installation of an associated placard. This amendment adds requirements for replacement of the horizontal stabilizer trim control unit (HSTCU) with a new HSTCU, and reactivation of the mach trim engage/disengage switch/light (if deactivated). Accomplishment of these actions terminates the requirements of the existing AD. This amendment also limits the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent deficiencies of the HSTCU, which could result in a nose-up trim runaway when a single component in the mach trim circuit fails.
AD 98-13-25 · published Jun 25, 1998, effective Jul 30, 1998
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that currently requires an inspection to detect free movement of the actuator servo-valve sub-assembly of the horizontal stabilizer actuator, and replacement, if necessary. This amendment adds a one-time inspection to determine the residual strength of the servo-valve sub-assembly of the horizontal stabilizer actuator, and replacement of the actuator with a new or serviceable actuator, if necessary; and eventual replacement of the horizontal stabilizer actuator with an improved actuator. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent uncommanded trimming or failure of the trim system of the horizontal stabilizer, and consequent reduced controllability of the airplane.
AD 98-13-26 · published Jun 25, 1998, effective Jul 30, 1998
British Aerospace Model BAC 1-11 200 and 400 Series 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 repetitive detailed visual inspections to detect cracking in the trunnion fittings located in the nose landing gear (NLG) bay of the forward fuselage; and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking in the trunnion fittings of the NLG, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flight crew and passengers.
AD 98-13-27 · published Jun 25, 1998, effective Jul 30, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection to detect discrepancies of circuit breaker panels 10VE and 11VE; follow-on corrective actions; modification of the contact points; and installation of a high capacity fuse. This amendment also requires replacement of power relays 32HB and 36HB on relay panel 22VE with new parts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent electrical short circuits of the contact points and power relays on the circuit breaker panels, which could result in increased risk of smoke and fire damage in the flight compartment.
AD 98-13-31 · published Jun 25, 1998, effective Jul 30, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires repetitive visual inspections to detect discrepancies of the bushing installation of the aileron actuation fitting, and eventual installation of staked bushings in the fitting. Accomplishment of such installation terminates the repetitive inspections. This amendment also provides for an optional temporary preventive action, which, if accomplished, would allow the repetitive inspection intervals to be extended until the terminating action is accomplished. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the fitting lugs due to vibration caused by loose bushings in the fittings, and consequent reduced controllability of the airplane.
AD 98-13-32 · published Jun 25, 1998, effective Jul 30, 1998
Fokker Model F.28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires interim inspections to detect discrepancies of the main fitting subassembly of the main landing gear, and follow-on corrective actions, if necessary. This amendment also requires a one-time inspection to detect discrepancies of the fitting, repair of the fitting, if necessary, and application of new surface protection on the fitting, which would terminate the interim inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the main fitting subassembly of the main landing gear, which could result in collapse of the main landing gear.
AD 98-13-33 · published Jun 25, 1998, effective Jul 30, 1998
Airbus Model A300, A300-600, and A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A300-600, and A310 series airplanes, that requires repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. For certain airplanes, this AD also requires repetitive inspections to detect cracking of the rudder attachments, and repair, if necessary; or modification of the rudder attachments. This proposal is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by the proposed AD are intended to detect and correct desynchronization of the rudder servo actuators, which could result in reduced structural integrity of the rudder attachments and reduced controllability of the airplane.
AD 98-13-35 · published Jun 25, 1998, effective Jul 30, 1998
McDonnell Douglas Model DC-9 and DC-9- 80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or longeron, and various follow-on actions. This amendment also requires installation of a preventative modification, which terminates the repetitive inspections. This amendment is prompted by reports indicating that, due to material fatigue caused by installation preload and cabin pressurization cycles, fatigue cracks were found in the skin and longerons of the fuselage. The actions specified by this AD are intended to prevent such fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane.
AD 98-13-36 · published Jun 25, 1998, effective Jul 30, 1998
Saab Model SAAB SF340A, SAAB 340B, and SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A, SAAB 340B, and SAAB 2000 series airplanes, that requires repetitive operational tests of the pitch trim system of the elevator trim-tab of the flight control unit to ensure that the system operates correctly, and repair if necessary. This amendment is prompted by a report of uncommanded movement of the right-hand elevator trim-tab to a maximum deflection position, which was apparently due to a failure in the aircraft harness and a fault in the pitch trim synchronizer. The actions specified by this AD are intended to prevent such uncommanded movement of the elevator trim-tab, which could lead to structural overload of the horizontal stabilizers at speeds above 180 knots, and consequent reduced controllability of the airplane.
AD 98-13-37 · published Jun 25, 1998, effective Jul 30, 1998
Airbus Model A300 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and all Model A300-600 series airplanes, that requires a one-time inspection for cracking of the gantry lower flanges in the main landing gear (MLG) bay area; and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the gantry lower flanges in the MLG bay area, which could result in decompression of the airplane.
AD 98-13-38 · published Jun 25, 1998, effective Jul 30, 1998
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires installation of a warning placard for the fire extinguisher exhaust port located in the rear baggage bay. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent blockage of the fire extinguisher exhaust port, which could result in reduced fire protection in the rear baggage bay and consequent injury to the passengers and crewmembers.
AD 98-13-41 · published Jun 26, 1998, effective Jul 20, 1998
Cessna Aircraft Company Model 172R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Model 172R airplanes. This action requires: inspecting for incorrectly routed aileron control cables in the center console area; inspecting for incorrectly routed aileron control cables in the right-hand (RH) wing area; inspecting for a loose or improperly installed center lock clamp on the forward aileron control cable drum; and inspecting for loose or missing elevator trim actuator mounting screws, loose rudder circuit pulleys, missing rudder cable guard pins, incorrect elevator trim cable routing, aileron control cable clearance, and flight control cable tension or rigging outside specification. If any of the above conditions are found, this AD requires correcting, repairing, or replacing any damaged or missing part, and reporting any of the above conditions found to the Wichita Aircraft Certification Office. Notification by the manufacturer, service difficulty reports (SDR's), and an FAA surveillance audit at the manufacturing facility identifying potential deficiencies on the affected airplanes prompted the action. The actions specified by this AD are intended to prevent loss of aileron and elevator control, which could result in loss of directional control of the airplane.
AD 98-12-08 · published Jun 4, 1998, effective Jul 9, 1998
Eurocopter France (Formerly Aerospatiale, Society Nationale Industrielle, Sud Aviation) Model SA- 365N, SA-365N1, SA-365N2, and SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Formerly Aerospatiale, Society Nationale Industrielle, Sud Aviation) Model SA-365N, SA-365N1, SA- 365N2, and SA-366G1 helicopters, that requires an inspection of the transmission deck for cracks; repair of any cracked transmission deck; and replacement of the transmission deck support beams (support beams) with redesigned support beams. This amendment is prompted by several reports of cracks in the transmission deck and support beams. The actions specified by this AD are intended to detect cracks that reduce the strength of the main gearbox strut attachment and could result in failure of the main gearbox mounting, and subsequent loss of control of the helicopter.
AD 98-12-15 · published Jun 9, 1998, effective Jul 14, 1998
Eurocopter France Model AS 332C, L, L1, and L2 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters that requires visually inspecting the intermediate gearbox- to-structure attachment stirrup (stirrup) front tabs for cracks, and if a crack is discovered, removing the intermediate gearbox and replacing it with an airworthy intermediate gearbox; and inspecting for the conformity of the attachment parts. This amendment is prompted by five reports of failure of the two stirrup tabs. The actions specified by this AD are intended to prevent failure of the intermediate gearbox stirrup front tabs, loss of anti-torque drive, and subsequent loss of control of the helicopter.
AD 98-12-16 · published Jun 9, 1998, effective Jul 14, 1998
Eurocopter France Model SA 330F, G, and J Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA 330F, G, and J helicopters that requires visually inspecting the intermediate gearbox (IGB) fairing safety stop (safety stop) for cracks, crazing, or edge wear, and if a crack, crazing, or edge wear exceeds the established limits, replacing the safety stop; and, inspecting to ensure that the inclined drive shaft fairing hinge pin is properly locked. A terminating action is provided in the AD by installing an additional safety stop on the IGB fairing. This amendment is prompted by one report of an accident involving the loss of the inclined drive shaft fairing. The actions specified by this AD are intended to prevent loss of the inclined drive shaft fairing, impact with the tail rotor, and subsequent loss of control of the helicopter.
AD 98-12-20 · published Jun 9, 1998, effective Jul 14, 1998
Eurocopter France Model SE3130, SA3180, SE313B, SA318B, and SA318C Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SE3130, SA3180, SE313B, SA318B, and SA318C helicopters, that requires an initial and repetitive visual inspections and modification, if necessary, of the horizontal stabilizer spar tube (spar tube). This amendment is prompted by an in- service report of fatigue cracks that initiated from corrosion pits. The actions specified by this AD are intended to prevent fatigue failure of the spar tube, separation and impact of the horizontal stabilizer with the main or tail rotor, and subsequent loss of control of the helicopter.
AD 98-12-21 · published Jun 10, 1998, effective Jul 15, 1998
Eurocopter France Model SA. 315B Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA. 315B helicopters that requires an initial and repetitive visual inspections and modification, if necessary, of the horizontal stabilizer spar tube (spar tube). This amendment is prompted by an in-service report of fatigue cracks that initiated from corrosion pits. The actions specified by this AD are intended to prevent fatigue failure of the spar tube, separation and impact of the horizontal stabilizer with the main or tail rotor and subsequent loss of control of the helicopter.
AD 98-12-22 · published Jun 10, 1998, effective Jul 15, 1998
Bell Helicopter Textron Canada Model 407 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters that requires shimming the tail rotor drive system bearing supports (bearing supports). This amendment is prompted by reports of cracked bearing hangar support arms in the area of the fillet radius. The actions specified by this AD are intended to prevent failure of the bearing supports, which could result in excessive tail rotor drive system vibration, loss of tail rotor drive, and subsequent loss of control of the helicopter.
AD 98-06-04 · published Jun 26, 1998, effective Jul 13, 1998
Eurocopter France Model AS332C, L, and L1 and Model SA330F, G, and J Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-06-04 which was sent previously to all known U.S. owners and operators of Eurocopter France Model AS332C, L, and L1 and Model SA330F, G, and J helicopters by individual letters. This AD requires performing a procedure to determine the angular play of the tail rotor gearbox, and repeating the procedure at certain intervals. This amendment is prompted by an accident involving a Model SA330 helicopter which resulted from the loss of the tail rotor drive. An investigation determined that the loss of the tail rotor drive was caused by excessive play between the tail rotor gearbox bevel gear and the bevel wheel. This condition, if not corrected, could result in failure of the tail rotor gearbox, loss of tail rotor drive, and subsequent loss of control of the helicopter.
AD 98-09-11 · published Jun 26, 1998, effective Jul 13, 1998
Eurocopter Deutschland GmbH Model EC 135 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-09-11 which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (Eurocopter) Model EC 135 helicopters by individual letters. This AD requires, before further flight, a review of aircraft records to determine if a tail rotor drive shaft vibration survey and installation of a Fenestron Shaft Retrofit Kit have been accomplished; before further flight, and thereafter at intervals not to exceed 15 hours time-in-service, inspecting the tail rotor drive shaft bearing (bearing) attaching lock plates for bent-open tabs, and broken or missing slippage marks; and visually inspecting each bearing support for cracks. This amendment is prompted by three reports of loose bearings and attachment bolts, and one report of a cracked bearing support. Excessive vibrations in the tail rotor drive shaft can loosen attachment bolts or cause cracking in the bearing supports. This condition, if not corrected, could result in loss of drive to the tail rotor and subsequent loss of control of the helicopter.
AD 98-13-28 · published Jun 26, 1998, effective Jul 13, 1998
Agusta S.p.A. Model A109C and A109K2 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A. (Agusta) Model A109C and A109K2 helicopters. This action requires a one-time inspection of each tail rotor blade (blade) for debonding, and if debonding exists which exceeds certain limits, replacement of the blade with an airworthy blade. This amendment is prompted by two incidents in which helicopters lost a blade tip fairing during ground run-up. The actions specified in this AD are intended to prevent loss of the tip fairing on a blade, which could result in increased vibrations, loss of the tail rotor assembly, and subsequent loss of control of the helicopter.
AD 98-13-39 · published Jun 26, 1998
Eurocopter France Model AS 332C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, and L1 helicopters that requires initial and repetitive inspections of the tail rotor shaft flapping hinge retainers (retainers) for cracks. This amendment is prompted by a report of high vibrations occurring on a helicopter while in service due to a cracked retainer. The actions specified by this AD are intended to detect cracks on the retainers that could lead to high tail rotor vibrations, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 98-13-40 · published Jun 26, 1998, effective Jul 31, 1998
Eurocopter France Model SA 330F, G, and J Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA 330F, G, and J helicopters, that requires verifying the torque on the nut that secures the two transformer-rectifiers' common ground; and subsequently installing a modification to separate the grounds of the two transformer-rectifiers. This amendment is prompted by a report from the airworthiness authority of France about an unsafe condition resulting from the loss of the common ground of the two transformer-rectifiers. The actions specified by this AD are intended to prevent loss of the common ground of the two transformer-rectifiers, which could result in a complete electrical failure (essential and secondary), loss of electrically-powered instrumentation, and subsequent loss of control of the helicopter.
AD 98-14-01 · published Jun 29, 1998, effective Aug 3, 1998
Eurocopter France Model AS-350B, BA, B1, B2, and D, and Model AS-355E, F, F1, F2, and N Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Model AS-350B, BA, B1, B2, and D, and Model AS-355E, F, F1, F2, and N helicopters, that requires inspections of the main gearbox suspension bi-directional cross-beam (cross-beam) for cracks, and replacement of the cross-beam if a crack is found. This amendment is prompted by several reports of cracks in the cross-beam. The actions specified by this AD are intended to provide a terminating action to prevent failure of the cross-beam that could cause the main gearbox to pivot, resulting in severe vibrations and a subsequent forced landing.
AD 98-11-32 · published Jun 3, 1998, effective Jun 18, 1998
Allison Engine Company AE 3007A and AE 3007C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines. This action supersedes priority letter AD 98-02-09, that currently requires certain checks of the center sump magnetic chip collector plug for paste. Engines found with paste are required to be removed from service. This action references revisions of the applicable Alert Service Bulletins (ASB) providing clarifications of check procedures. This amendment is prompted by a change in the part number applicability, a change in the check interval, and the publication of these revised ASBs. The actions specified by this AD are intended to prevent No. 4 bearing failure due to excessive bearing wear, which can result in an inflight engine shutdown.
AD 98-12-09 · published Jun 8, 1998, effective Aug 7, 1998
AlliedSignal Inc. Model TPE331 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. Model TPE331 series turboprop engines, that requires removal of suspect fuel manifold assemblies and replacement with serviceable assemblies. This amendment is prompted by an FAA investigation into Hoses Unlimited's repairs of TPE331 fuel manifolds, which were not approved by the FAA. The actions specified by this AD are intended to prevent fuel leakage at the fuel manifold fittings, resulting in fuel spraying on hot turbine components, which could result in an engine fire.
AD 98-12-07 · published Jun 9, 1998, effective Aug 10, 1998
Pratt & Whitney JT8D Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D series engines, that currently requires a determination of the utilization rate and coating type of the 7th, 8th, 9th, 10th, 11th, and 12th stage high pressure compressor (HPC) disks, and removal, inspection for corrosion, and recoating of those HPC disks based on utilization rate. This amendment shortens the inspection interval for certain low utilization disks. This amendment is prompted by reports of an additional uncontained 9th stage HPC disk failure due to corrosion pitting. The actions specified by this AD are intended to prevent fracture of the HPC disks, which can result in uncontained release of engine fragments, inflight engine shutdown, and airframe damage.
AD 98-12-12 · published Jun 9, 1998, effective Jun 24, 1998
Allison Engine Company Model AE 3007A Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company Model AE 3007A turbofan engines. This action requires reprogramming the Full Authority Digital Engine Control (FADEC) to the latest, improved software version. This amendment is prompted by reports of inflight engine shutdowns due to inadequate fault accommodation logic. The actions specified in this AD are intended to prevent inflight engine shutdowns due to inadequate fault accommodation logic.
AD 97-21-07 R1 · published Jun 19, 1998, effective Jul 6, 1998
AlliedSignal Inc. (Formerly Textron Lycoming) Model T5313B, T5317A, and T53 (Military) Turboshaft Engines
This amendment revises an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming) Model T5313B, T5317A, and T53 series military turboshaft engines approved for installation on aircraft certified in accordance with Section 21.25 of the Federal Aviation Regulations (FAR), that currently requires a one- time visual inspection of accessory drive carrier assemblies for affected serial numbers (S/Ns) designating a defective assembly, and if the S/N is applicable, replacement with a serviceable assembly. This amendment adds military helicopter models and removes one civilian helicopter model to the sentence in the Applicability paragraph of the AD that provides guidance as to the helicopter models with the affected engines. This amendment is prompted by the need to revise the Applicability paragraph. The actions specified by this AD are intended to prevent accessory drive carrier assembly failure, which could result in an N2 overspeed and an uncontained engine failure.
AD 98-12-32 · published Jun 19, 1998, effective Jul 20, 1998
CFM International CFM56-2, -2A, -2B, - 3, -3B, and -3C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, and -3C series turbofan engines, that requires a one-time eddy current inspection (ECI) for cracks or gouges in certain high pressure turbine rotor (HPTR) disks. This amendment is prompted by a report of a HPTR disk found to have a crack in a rim bolt hole during a routine shop manual ECI. The actions specified by this AD are intended to prevent the potential for an uncontained failure of the HPTR disk, which could result in an inflight engine shutdown, aborted takeoff, or damage to the aircraft.
AD 98-13-20 · published Jun 25, 1998, effective Jul 10, 1998
Rolls-Royce Limited, Aero Division- Bristol, S.N.E.C.M.A., Olympus 593 Series Turbojet Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A, Olympus 593 series turbojet engines. This action requires a radiological inspection of the combustion chamber No. 2 outer cooling ring scoop circumferential and axial weld for weld quality, and reweld and reinspection, if necessary; and an inspection of the combustion chamber No. 2 inner and outer cooling ring web length, marking acceptable components with the letter ``T'' adjacent to the part number, and replacement of unacceptable components with serviceable parts. This amendment is prompted by reports of circumferential cracks at the No. 2 outer and inner rings of the combustor chamber, resulting in a section of the combustion chamber detaching and causing significant ignitor and low pressure turbine damage. The actions specified in this AD are intended to prevent combustion chamber detachment, which could result in an inflight engine shutdown or an engine fire.
AD 98-13-21 · published Jun 25, 1998, effective Jul 10, 1998
Rolls-Royce Limited, Aero Division- Bristol, S.N.E.C.M.A Olympus 593 Series Turbojet Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A Olympus 593 series turbojet engines. This action requires initial and repetitive visual inspections of the low pressure (LP) shaft signal system for cable wear and refurbishment of the LP shaft signal system at when the cable is found frayed, or at every engine shop visit, whichever occurs first. This amendment is prompted by reports of frayed rear cables in the LP shaft signal system. The actions specified in this AD are intended to prevent LP shaft signal system failure, which could result in an LP turbine overspeed, burst, uncontained engine failure, and damage to the aircraft in the event of a LP shaft failure.
AD 98-12-29 · published Jun 10, 1998
Lucas Air Equipment Electric Hoists
This amendment adopts a new airworthiness directive (AD), applicable to Lucas Air Equipment electric hoists (hoists) installed on, but not limited to, all models of Eurocopter France SA-360 and SA- 365 helicopters that requires visually inspecting the cable for damage before the next hoist operation, blanking (plugging) the electronic control box upper vent, and performing an end-of-travel procedure before each hoist operation. This amendment is prompted by several incidents of cable failures caused by dynamic overload on the winding- up limit due to uncontrolled excessive speed of the cable, which is normally regulated by the automatic speed-reducing mechanism or the operator. The actions specified by this AD are intended to prevent breaking of the cable, which could become entangled with a main rotor or tail rotor blade, and result in damage or separation of a rotor blade, and subsequent loss of control of the helicopter.
AD 98-12-03 · published Jun 4, 1998, effective Jul 14, 1998
Alexander Schleicher Segelflugzeugbau Models ASW-19 and ASK 21 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Models ASW-19 and ASK 21 sailplanes. This AD requires: modifying the rudder surface panels; replacing the airbrake bellcrank; and modifying the rear canopy hinge structure. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent loss of the canopy caused by design deficiency, airbrake failure caused by cracking, and rudder panel flutter caused by high density altitude conditions, all of which could result in reduced sailplane controllability.
AD 98-12-04 · published Jun 4, 1998, effective Jul 21, 1998
Glaser-Dirks Flugzeugbau GmbH Model DG- 500M Gliders
This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG- 500M gliders. This AD requires installing a rudder gap seal and modifying the cooling liquid reservoir mount. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent rudder vibrations caused by flow separation at the rudder gap, which could result in flutter with consequent loss of rudder control.
AD 98-12-06 · published Jun 4, 1998, effective Jul 17, 1998
Stemme GmbH & Co. KG Models S10 and S10-V Sailplanes.
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10 and S10-V sailplanes. This AD requires replacing the fuel filter if it is contaminated, inserting a revision to the Limitations Section of the flight manual, and inspecting the engine valve shafts for brownish- black sticky residue. If a residue is found on the valve shafts, this action will require cleaning the engine. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent engine valve malfunction, which could cause engine failure during flight and loss of control of the sailplane.
AD 98-13-04 · published Jun 16, 1998, effective Aug 2, 1998
Glaser-Dirks Flugzeugbau GmbH Models DG-100 and DG-400 Gliders
This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Models DG- 100 and DG-400 gliders. This AD requires repetitively inspecting the airbrakes to assure they retract at their outboard end first, and repairing the airbrakes if they do not retract at their outboard end first; and repetitively inspecting the airbrake torque tube in the fuselage for cracks or deformations, and reinforcing or replacing, as necessary, if cracks or deformations are found in the airbrake torque tube. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent overloading of the airbrake control system caused by free play between the bellcrank and airbrake plate, which could result in failure of the operating lever of the airbrake torque tube in the fuselage.
AD 98-13-05 · published Jun 16, 1998, effective Aug 1, 1998
Alexander Schleicher Segelflugzeugbau Model AS-K13 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model AS-K13 sailplanes. This AD requires inspecting the main spar fitting for excessive tolerance, traces, movement, etc., and repairing the main spar fitting if any of the above conditions exist. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the main spar caused by excessive movement of the main spar fitting, which could result in loss of control of the sailplane.
AD 98-13-06 · published Jun 19, 1998, effective Aug 2, 1998
Glaser-Dirks Flugzeugbau GmbH Model DG- 400 Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG-400 gliders. This AD requires replacing the bungees that secure the left engine restraining cable and the bowden cable of the rear engine door. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the engine from locking in flight and not extending because of the left restraining cable or bowden cable of the rear door making contact with the engine, which could result in loss of glider power and potential loss of control.
