40 Airworthiness Directives: 28 airplane, 4 rotorcraft, 3 engine, 1 propeller, 4 glider.
AD 98-16-13 · published Aug 3, 1998, effective Aug 18, 1998
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 for missing fasteners of the splice fitting of the forward inner chord of the Body Station (BS) 2598 bulkhead; and corrective actions, if necessary. This amendment is prompted by a report that fasteners were missing from the splice fitting of the forward inner chord. The actions specified in this AD are intended to prevent accelerated fatigue cracking of the inner chords of the BS 2598 bulkhead, which could result in inability of the structure to carry horizontal stabilizer flight loads, and consequent reduced controllability of the airplane.
AD 98-16-12 · published Aug 4, 1998, effective Sep 8, 1998
Airbus Model A320 and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes, that requires replacement of the fuel pump strainers with improved strainers. 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 fuel by the buildup of ice crystals, which could result in low fuel pressure, and consequent shutdown of the engine during critical phases of flight.
AD 97-20-10 R1 · published Aug 7, 1998, effective Sep 11, 1998
de Havilland Model DHC-8-100, -200, and -300 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100, -200, and - 300 series airplanes, that currently requires modification of the attitude and heading reference systems (AHRS). That action was prompted by a report of loss of power to both AHRS's during flight due to a faulty terminal block to which the signal ground for the AHRS's is connected. The actions specified by that AD are intended to prevent simultaneous power loss to both AHRS's, which could result in reduced controllability of the airplane. This amendment reduces the applicability of the existing AD.
AD 98-16-14 · published Aug 7, 1998, effective Sep 21, 1998
Pilatus Britten-Norman Ltd. BN-2, BN- 2A, BN-2B, and BN-2T Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN- 2, BN-2A, BN-2B, and BN-2T series airplanes. This AD requires replacing the attachment bolts, nuts and washers of the lower fitting of the main landing gear (MLG), and adjusting the torque values of the nuts. 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 bolts that attach the lower fitting of the MLG to the nacelle from becoming threadbound, which could result in structural failure of the MLG with consequent loss of control of the airplane during takeoff, taxi, or landing operations.
AD 98-16-15 · published Aug 7, 1998, effective Sep 21, 1998
British Aerospace Model B.121 Series 1, 2, and 3 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Model B.121 Series 1, 2, and 3 airplanes. This AD requires installing an inspection opening in the area of the main spar web, repetitively inspecting the area at the main spar web for cracks, and repairing or replacing any cracked part. This AD also requires installing nuts of improved design at the wing to fuselage main-spar attachment fittings. 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 structural failure of the main spar web area caused by fatigue cracking or separation of the wing caused by loose nuts at the wing to fuselage main-spar attachment fittings, which could result in loss of control of the airplane.
AD 98-16-16 · published Aug 7, 1998, effective Sep 21, 1998
Pilatus Aircraft Ltd. Model PC-7 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. Model PC-7 airplanes. This AD requires replacing the seal unit on both main landing gear (MLG) legs and the nose landing gear (NLG) leg. 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 MLG or NLG failure caused by deterioration of a MLG or NLG leg seal unit, which could result in damage to the airplane or airplane control problems during takeoff, landing, or taxi operations.
AD 98-16-17 · published Aug 7, 1998, effective Aug 24, 1998
Cessna Model 750 Citation X Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Cessna Model 750 Citation X series airplanes. This action requires repetitive in-flight functional tests to verify proper operation of the secondary horizontal stabilizer pitch trim system, and repair, if necessary. This amendment is prompted by reports of simultaneous failures of the primary and secondary horizontal stabilizer pitch trim system during flight, due to internal water contamination and corrosion damage in the system actuator. The actions specified in this AD are intended to detect and correct such contamination and damage, which could result in simultaneous failure of both primary and secondary pitch trim systems, and consequent reduced controllability of the airplane.
AD 98-16-18 · published Aug 7, 1998, effective Aug 24, 1998
Learjet Model 60 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 60 airplanes. This action requires repetitive measurements of the brake wear dimension between the housing subassembly and the pressure plate that is adjacent to the top pistons of the brake assembly; and follow-on corrective actions, if necessary. This amendment is prompted by reports of abnormal (uneven) brake wear. The actions specified in this AD are intended to detect and repair an abnormal brake wear condition, which could result in loss of brake effectiveness and cause the airplane to leave the runway surface.
AD 98-16-19 · published Aug 7, 1998, effective Aug 24, 1998
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747 series airplanes. This action requires, for certain airplanes, revising the Airplane Flight Manual (AFM) to advise the flightcrew of limitations on dry (no fuel) operation of the override/jettison pumps of the center wing fuel tank. This action also requires repetitive inspections for wear or damage of the inlet check valves and inlet adapters of the override/jettison pumps, and replacement of the check valves and pumps with new or serviceable parts, if necessary. Such replacement terminates the AFM revision. This amendment is prompted by a report that inlet adapters of override/jettison pumps were found to be worn excessively, which allowed contact to occur between the inlet check valve and the inducer. The actions specified in this AD are intended to ensure that the flightcrew is advised of the hazards of dry operation of the override/ jettison pumps of the center wing fuel tank, and to detect and correct wear or damage to the inlet check valves and inlet adapters of the override/jettison pumps; such conditions, if not corrected, could result in a fire or explosion in the fuel tank during dry operation.
AD 98-16-20 · published Aug 7, 1998, effective Aug 24, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes. This action requires a one-time visual inspection of the right-and left-hand propeller gearbox to ensure that the attachment nut that secures the borescope plug to the gearbox is installed; and installation of an attachment nut, 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 oil leakage from the propeller gearbox, which could lead to an increase in oil temperature and result in engine shutdown.
AD 98-16-21 · published Aug 7, 1998, effective Sep 11, 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 one-time inspections to verify the correct shape of the stiffeners for the upper engine cowl and to detect wear of the aft upper fittings of the rear engine mounts, 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 prevent wear (scratches or grooving) of the aft upper fittings of the rear engine mount, and consequent reduced structural integrity of the engine mounts.
AD 98-16-22 · published Aug 7, 1998, effective Sep 11, 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 a one-time inspection for cracking of the rear pressure bulkhead; and installation of a reinforcement angle on the rear pressure bulkhead; or 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 cracking of the rear pressure bulkhead, which could result in sudden loss of cabin pressure and the inability to withstand fail-safe loads.
AD 98-16-23 · published Aug 7, 1998, effective Sep 11, 1998
Construcciones Aeronauticas, S.A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires repetitive high frequency eddy current (HFEC) inspections of the flap transmission shafts to detect cracking, and repetitive functional tests (checks) to verify proper operation of the flap braking sub-system; 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 in the flap transmission shafts, and to correct a malfunctioning flap braking sub-system, which could result in the inability to move the flaps, or in an asymmetric flap condition, and consequent reduced controllability of the airplane.
AD 98-16-24 · published Aug 7, 1998, effective Sep 11, 1998
British Aerospace Model BAe 146 and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and certain Model Avro 146-RJ series airplanes, that requires a one-time inspection for ``drill marks'' and corrosion on the underside of the wing top skin, 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 prevent corrosion from developing on the underside of the top skin of the center wing, which could result in reduced structural integrity of the airplane.
AD 98-16-25 · published Aug 7, 1998, effective Sep 11, 1998
Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) airplanes, that currently requires repetitive inspections to detect discrepancies of the shock strut end caps and attachment pins of the main landing gear (MLG), and replacement of discrepant parts with new parts. It also requires a check for and replacement of certain pins that currently may be installed on some airplanes. This amendment adds a requirement for the installation of new, improved MLG shock strut upper and lower attachment pins, which constitutes terminating action for the repetitive inspections. This amendment also reduces the applicability of the existing AD by removing certain airplanes. 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 attachment pins and the attachment pin end caps, which could result in failure of the MLG.
AD 98-17-05 · published Aug 13, 1998, effective Aug 28, 1998
Airbus Model A319, A320, A321, A330, and A340 Series Airplanes Equipped With AlliedSignal RIA-35B Instrument Landing System Receivers
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, A321, A330, and A340 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to require the flightcrew to discontinue use of any Instrument Landing System (ILS) receiver for which a certain caution message is displayed. This action also requires, for certain airplanes, replacing any faulty ILS receiver with a new, serviceable, or modified unit. This AD also provides for an optional terminating action for the AFM revisions. This amendment is prompted by a pilot's report of errors in the glide slope deviation provided by an ILS receiver. The actions specified in this AD are intended to detect and correct faulty ILS receivers and to ensure that the flightcrew is advised of the potential hazard of performing ILS approaches using a localizer deviation from a faulty ILS receiver, and advised of the procedures necessary to address that hazard. An erroneous localizer deviation could result in a landing outside the lateral boundary of the runway.
AD 98-17-09 · published Aug 13, 1998, effective Sep 17, 1998
Airbus Model A310 and A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A310 and A300-600 series airplanes, that currently requires a revision of the Airplane Flight Manual that warns the flightcrew of certain consequences associated with overriding the autopilot when it is in the pitch control axis. That AD also requires modification of certain flight control computers, and a modification to the autopilot. For certain airplanes, that AD also requires repetitive operational testing of the modified autopilot to determine if the disconnect function operates properly, and repair, if necessary. This amendment adds a new requirement to accomplish those repetitive operational tests on other airplanes. 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 an out-of-trim condition between the trimmable horizontal stabilizer and the elevator, which could result in severely reduced controllability of the airplane.
AD 98-17-06 · published Aug 14, 1998, effective Sep 18, 1998
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires repetitive inspections to detect fatigue cracking of certain fuselage skin panels, and repair, if necessary. For certain airplanes, this amendment also provides for an optional preventative modification, which, if accomplished, would terminate the repetitive inspections. This amendment is prompted by reports of fatigue cracking of certain fuselage skin panels. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the airplane, and consequent loss of pressurization.
AD 98-17-07 · published Aug 14, 1998, effective Sep 18, 1998
Fokker Model F28 Mark 0070 and Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires inspection of the wing leading edge sections for the correct amount of bleed air exhaust holes, 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 prevent malfunction of the wing leading edge thermal anti-ice system, which could result in reduced controllability of the airplane and/or reduced structural integrity of the wing due to overheating.
AD 98-17-08 · published Aug 14, 1998, effective Sep 18, 1998
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive inspections to detect any discrepancy in the sealwire of the fireguards of the engine fire shut- off system, 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 inadvertent closure of the fire shut-off valves due to ineffective or absent sealwires, which could result in in-flight engine shutdown.
AD 98-15-05 · published Aug 19, 1998, effective Aug 19, 1998
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-200A series airplanes, that requires a one-time inspection of the gust damper of the elevator control system to determine if the gust damper is properly charged, and of the horizontal stabilizer to detect cracking of elevator hinge rib 1; and corrective action, if necessary. 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 cracking of elevator hinge rib 1 of the horizontal stabilizer, which could occur if the gust damper of the elevator control system discharges and allows the elevator to move freely in ground gust conditions. Such cracking could result in damage to the structural attachment of the elevator to the horizontal stabilizer, and consequent reduced controllability of the airplane.
AD 98-17-12 · published Aug 19, 1998, effective Sep 23, 1998
British Aerospace (Jetstream) Model 4100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4100 series airplanes, that requires an eddy current conductivity test to measure the conductivity of the upper splice plate of the wing, and follow-on 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 correct corrosion of the upper splice plate of the wing, which could result in reduced structural integrity of the airplane.
AD 98-17-13 · published Aug 19, 1998, effective Sep 3, 1998
Boeing Model 747 and 767 Series Airplanes Equipped with Rolls-Royce Model RB211-524G/H Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 and 767 series airplanes. This action requires modification of the engine fire detection system. This amendment is prompted by a report of a combustor burn-through event that damaged the engine fire detection system such that no fire warning message was annunciated in the flight deck. The actions specified in this AD are intended to prevent failure of the engine fire detection system to annunciate a fire warning message to the flight crew following a severe engine failure, which could lead to delayed or improper flight crew response to the engine failure.
AD 98-18-02 · published Aug 27, 1998, effective Oct 1, 1998
Airbus Industrie Model A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Industrie Model A300-600 series airplanes, that currently requires inspections to detect cracks in the center spar sealing angles adjacent to the pylon rear attachment and in the adjacent butt strap and skin panel, and correction of discrepancies. This amendment requires that the initial inspections be accomplished at reduced thresholds. This action also limits the applicability of the existing AD. This amendment is prompted by reports of cracking in the vertical web of the center spar sealing angles of the wing. The actions specified by this AD are intended to prevent crack formation in the sealing angles; such cracks could rupture and lead to subsequent crack formation in the bottom skin of the wing, and resultant reduced structural integrity of the center spar section of the wing.
AD 98-18-03 · published Aug 27, 1998, effective Oct 1, 1998
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires modification of the wiring of the strake ice protection system (SIPS). This amendment is prompted by a report of a fire in the electrical and electronic compartment of a Model MD-90-30 series airplane. The actions specified by this AD are intended to prevent an electrical short circuit of the wiring of the SIPS, which could result in a fire in the electrical and electronic compartment of the airplane.
AD 98-18-04 · published Aug 27, 1998, effective Oct 1, 1998
Aerospatiale Model SN-601 (Corvette) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model SN-601 (Corvette) series airplanes, that requires repetitive inspections to detect corrosion, cracking, or rupture of the support arms of the aileron balance weights; and repair, if necessary. Accomplishment of the repair terminates the repetitive inspection requirement of this 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 corrosion, cracking, or rupture of the support arms of the aileron balance weights, which may cause reduced flutter damping or jamming of the aileron, and consequent reduced controllability of the airplane.
AD 98-18-07 · published Aug 27, 1998, effective Oct 12, 1998
Pilatus Britten-Norman Ltd. BN-2, BN- 2A, BN-2B, and BN-2A MK. 111 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Britten-Norman Ltd. (PBN) BN-2, BN-2A, BN- 2B, and BN-2A MK. 111 series airplanes that are equipped with a PBN Modification NB/M/256, 50A generator system. This AD requires inspecting the airplanes that are equipped with a 50A generator system for a 70A generator. If a 70A generator is installed, this AD requires replacing the 70A generator with a 50A generator, or (for the BN-2, BN-2A, and BN-2B series only) upgrading the airplane generator system to a 70A system to match the 70A generator. 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 detect and correct damage to the components of the electrical system, which could result in electrical system failure during critical phases of flight.
AD 98-18-08 · published Aug 27, 1998, effective Oct 10, 1998
Bombardier Inc. Model Otter DHC-3 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Bombardier Inc. (formerly deHavilland Inc) Model DHC-3 (Otter) airplanes that have been modified in accordance with A.M. Luton Supplemental Type Certificate (STC) No. SA3777NM. This AD requires modifying the airplane's electrical system. The actions specified by this AD are intended to prevent electrical system failure caused by inadequate electrical system design, which could result in the loss of the engine instruments or a possible electrical fire in the airplane's cockpit.
AD 98-12-19 · published Aug 13, 1998, effective Aug 28, 1998
Robinson Helicopter Company (RHC) Model R44 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-12-19 which was sent previously to all known U.S. owners and operators of RHC Model R44 helicopters by individual letters. This AD requires, within 5 hours TIS, a dye penetrant inspection of each main rotor blade skin (blade skin) around both inboard trim tab alignment rivet holes. Thereafter, a repetitive visual inspection of the blade skin around both inboard trim tab alignment rivet holes is required prior to the first flight of each day or at intervals not to exceed 5 hours TIS, whichever occurs first. This amendment is prompted by an incident in which a crack in the main rotor blade resulted in a forced landing. Subsequent investigations revealed that the manufacturing process utilized to drill the trim tab alignment rivet holes in the blade skin can allow a fatigue crack to originate at these holes and propagate in the skin. This condition, if not corrected, could result in failure of the main rotor blade and subsequent loss of control of the helicopter.
AD 98-16-02 · published Aug 20, 1998, effective Sep 4, 1998
Eurocopter France Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-16-02 which was sent previously to all known U.S. owners and operators of Eurocopter France Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by individual letters. This AD requires an initial and recurring visual inspections of the upper and lower surfaces of the tail rotor blade (blade) skin for cracks. If a crack is found, replacing the blade with an airworthy blade is required. This amendment is prompted by a report of a crack on the blade skin near an attachment bolt on the blade cuff stem. This condition, if not corrected, could result in fatigue failure of a blade and subsequent loss of control of the helicopter.
AD 98-18-01 · published Aug 25, 1998
Bell Helicopter Textron, Inc. Model 214B, 214B-1, and 214ST Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B, 214B-1, and 214ST helicopters, that currently establishes a retirement life of 60,000 high-power events for the main rotor trunnion (trunnion). This amendment requires changing the method of calculating the retirement life for the trunnion from high-power events to a maximum accumulated Retirement Index Number (RIN). This amendment is prompted by fatigue analyses and tests that show certain trunnions fail sooner than originally anticipated because of the unanticipated higher number of lifts or takeoffs (torque events) performed with those trunnions. The actions specified by this AD are intended to prevent fatigue failure of the trunnion, which could result in loss of the main rotor and subsequent loss of control of the helicopter.
AD 98-10-09 · published Aug 31, 1998, effective Sep 15, 1998
Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-10-09 which was sent previously to all known U.S. owners and operators of Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by individual letters. This AD requires an initial and recurring inspections of the blade spar for cracks. This amendment is prompted by an accident in which a Model SA.315B helicopter lost a main rotor blade. The cause of the blade failure was fatigue cracking. This condition, if not corrected, could result in separation of a blade and subsequent loss of control of the helicopter.
AD 98-17-01 · published Aug 11, 1998, effective Oct 13, 1998
AlliedSignal Inc. TFE731 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. TFE731 series turbofan engines, that currently requires the installation of a clamp assembly to support the rigid fuel tube. This action would require the installation of a clamp assembly to support the rigid fuel tube. This amendment requires installation of an improved flexible (flex) fuel tube. This amendment is prompted by reports of fuel leaks from a cracked fuel tube in engines that have already installed a clamp assembly in accordance with the current AD. The actions specified by this AD are intended to prevent cracking of the fuel tube and the subsequent leakage of fuel on or around electrical components, which can cause an engine fire.
AD 98-17-11 · published Aug 20, 1998, effective Oct 19, 1998
Textron Lycoming and Teledyne Continental Motors Reciprocating Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Textron Lycoming and Teledyne Continental Motors reciprocating engines that had crankshafts repaired by Nelson Balancing Service, Repair Station Certificate No. NB7R820J, Bedford, Massachusetts, that requires removal from service of affected crankshafts, or a visual inspection, magnetic particle inspection, and dimensional check of the crankshaft journals, and, if necessary, rework or removal from service of affected crankshafts and replacement with serviceable parts. This amendment is prompted by reports of crankshafts exhibiting heat check cracking of the nitrided bearing surfaces which led to crankshaft cracking and subsequent failure. The actions specified by this AD are intended to prevent crankshaft failure due to cracking, which could result in an inflight engine failure and possible forced landing.
AD 98-18-10 · published Aug 31, 1998, effective Sep 30, 1998
General Electric Company CF6-6 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-6 series turbofan engines, that requires removal from service of affected low pressure turbine (LPT) stage 4 disks prior to reaching new, reduced cyclic life limits, and replacement with serviceable parts. This amendment is prompted by reports of LPT stage 4 disk cracking in the blade dovetail slot bottom area. The actions specified by this AD are intended to prevent LPT stage 4 disk cracking, which could result in an uncontained engine failure and damage to the aircraft.
AD 98-17-04 · published Aug 14, 1998, effective Aug 31, 1998
Hartzell Propeller Inc. HC-E4A-3(A,I,J) Series Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. HC-E4A-3(A,I,J) series propellers. This action requires a one-time inspection of the propeller blade counterweight clamps for thread damage in the bolt holes, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of a counterweight clamp bolt hole thread failure that resulted in the separation of the counterweight and the separation of a blade following impact with the counterweight. The actions specified in this AD are intended to prevent propeller blade counterweight clamp bolt hole thread failure, which can result in counterweight and propeller blade separation, and possible damage to the aircraft.
AD 98-17-02 · published Aug 12, 1998, effective Sep 26, 1998
Alexander Schleicher Segelflugzeugbau Model ASW-19 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASW-19 sailplanes. This AD requires inspecting the tow release cable guide fittings for the correct mounting, and, if the fittings are mounted in the front of the bulkhead, moving the fitting to the rear of the bulkhead and adjusting the neutral travel of the cable. 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 premature release of the tow cable during take-off, which could result in loss of the sailplane.
AD 98-17-03 · published Aug 12, 1998, effective Sep 26, 1998
Glaser-Dirks Flugzeugbau GmbH Model DG- 400 Gliders
This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG- 400 gliders. This AD requires replacing the propeller shaft, the bearings, and the front drive belt retaining rings with ones of improved design. 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 propeller shaft caused by an ineffective design, which could result in loss of glider propulsion during critical phases of flight.
AD 98-18-05 · published Aug 27, 1998, effective Oct 12, 1998
Alexander Schleicher Segelflugzeugbau Models K 8 and K 8 B Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Models K 8 and K 8 B sailplanes. This AD requires inspecting the canopy hood lock assembly to assure that the height of the cam is at least 2 millimeters (mm), and modifying or replacing any canopy hood lock assembly where the cam is less than 2 mm in height. 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 canopy from coming open in flight because the height of the locking cam is less than 2 mm, which could result in loss of the canopy with consequent pilot injury.
AD 98-18-06 · published Aug 27, 1998, effective Oct 12, 1998
Schempp-Hirth K.G. Model Cirrus Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schemmp-Hirth) Model Cirrus sailplanes. This AD requires modifying or replacing the connecting rod between the airbrake bellcranks, and replacing the existing 6 millimeter (mm) bolt with an 8 mm bolt. 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 threaded bolt that is welded to the connecting rod between the airbrake bellcranks from breaking, which could result in loss of airbrake control with a possible reduction/loss of sailplane control.
