42 Airworthiness Directives: 31 airplane, 3 rotorcraft, 5 engine, 3 glider.
AD 98-07-04 · published May 4, 1998, effective May 4, 1998
328 Support Services GmbH Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection for discrepancies of certain engine control cables, and replacement of the cables with new or serviceable control cables, if necessary. It also requires modification of the cable fairleads on the nose rib firewall. Additionally, this amendment requires modification of the mounting brackets of the control cable pulleys in the pulley box. 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 of engine control cables, which could cause the cables to break and result in loss of engine control and consequent reduced controllability of the airplane.
AD 98-09-28 · published May 4, 1998, effective Jun 8, 1998
Short Brothers Model SD3-30 and SD3-60 Series Airplanes Equipped With Fire Fighting Enterprises (U.K.) Ltd. Fire Extinguishers
This amendment adopts a new airworthiness directive (AD), applicable to all Shorts Model SD3-30 and SD3-60 series airplanes equipped with certain fire extinguishers, that requires replacement of the covers for fire extinguisher adapter assemblies that are installed on certain bulkheads with new covers that swivel to lock the extinguishers in place; and replacement of nozzles and triggers on these fire extinguishers with better fitting nozzles and stronger triggers. It also requires the installation of new fire extinguisher point placards and a revision of the Airplane Flight Manual to instruct the flight crew in the use of the new covers for these adapter assemblies. This amendment is prompted by reports that these fire extinguishers are not discharging properly because they do not fit correctly with the adapter, and that triggers on these extinguishers are failing. The actions specified by this AD are intended to ensure that, in the event of fire in the baggage bay, extinguishing agent is properly distributed within this area, and portable extinguishers operate properly; and to prevent injury to crew and passengers when a portable extinguisher is discharged.
AD 98-09-30 · published May 5, 1998, effective May 20, 1998
Airbus Model A330-301 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301 series airplanes. This action requires a one-time visual inspection to measure clearances between the engine forward feed pipe and shroud sleeve in the engine pylon; and repetitive operational tests for fuel leakage, and replacement of the shroud sleeve with a new improved part, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fuel from leaking into the pylon primary structure and into the engine nacelle core zone, which could result in a fire in the engine.
AD 98-10-01 · published May 5, 1998, effective May 20, 1998
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires a revision of the Airplane Flight Manual to alert the flightcrew that both flight management computers (FMC's) must be installed and operational. This AD also requires an inspection to determine the serial number of the FMCs, and follow-on corrective actions, if necessary. This amendment is prompted by a report indicating that, due to incorrect multiplexers that were installed in the flight management computer system (FMC'S) during production, certain data busses failed simultaneously during a ground test. The actions specified in this AD are intended to prevent loss of airspeed and altitude indications on both primary flight displays in the cockpit, and/or loss or degradation of the autopilot functionality due to installation of incorrect multiplexers, and consequent failure of the data busses.
AD 98-09-29 · published May 6, 1998, effective Jun 10, 1998
Boeing Model 747-400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires removal and reconfiguration of the battery grounds of the auxiliary power unit (APU). This amendment is prompted by reports of smoke or fire coming from the APU due to battery grounds that were not installed or maintained properly. The actions specified by this AD are intended to prevent overheating and heat damage of the APU battery grounds due to improper installation of the APU battery ground, which could result in heat damage and consequent smoke or fire on the airplane.
AD 98-10-02 · published May 6, 1998, effective Jun 10, 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 replacement of certain wheel tie bolts with new bolts; and placing a life limit on these wheel tie bolts. 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 metal fatigue failure of the wheel tie bolts, which could result in a tire burst or loss of the main wheel/tire assembly, and consequent reduced controllability of the airplane.
AD 98-10-10 · published May 12, 1998, effective May 27, 1998
Boeing Model 747 and 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 and 767 series airplanes. This action requires a one-time inspection to confirm the installation of Teflon sleeves over certain electrical wires inside conduits installed in the fuel tanks; and corrective actions, if necessary. This amendment is prompted by a report of missing Teflon sleeves, which protect the wiring insulation from chafing. The actions specified in this AD are intended to prevent such chafing, which could eventually expose the electrical conductor creating the potential for arcing from the wire to the conduit, and consequent fuel tank fire/explosion.
AD 98-10-06 · published May 13, 1998, effective Jun 28, 1998
Burkhart Grob Luft-und Raumfahrt Models G115C, G115C2, G115D, and G115D2 Airplanes
This amendment supersedes Airworthiness Directive (AD) 96-19- 07, which currently requires the following on Burkhart Grob Luft-und Raumfahrt (Grob) Models G115C, G115C2, G115D, and G115D2 airplanes: installing a placard that restricts the never exceed speed (Vne) of the affected airplane models from 184 knots to 160 knots; installing on the airspeed indicator glass a red line at 296 km/h (160 knots); installing a placard that prohibits aerobatic maneuvers; and placing a copy of the AD in the Limitations Section of the airplane flight manual. This AD will temporarily retain the flight restrictions that are currently required by AD 96-19-07; and will eventually require accomplishing certain inspections and modifications, as terminating action for these flight restrictions. 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 control of the airplane caused by excessive speed or aerobatic maneuvers.
AD 98-10-08 · published May 13, 1998, effective Jun 17, 1998
Construcciones Aeronauticas, S.A. (CASA) Model C-212 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model C-212 series airplanes, that requires a one-time inspection of the lower shaft and support structure of the rudder for corrosion, repair of any discrepancy found, and modification of the structure. 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 in the lower shaft and support structure of the rudder, which could result in the failure of the rudder lower shaft and consequent reduced controllability of the airplane.
AD 98-10-05 · published May 14, 1998, effective Jun 27, 1998
Raytheon Aircraft Company Models B200, B200C, and B200T Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models B200, B200C, and B200T airplanes (formerly referred to as Beech Models B200, B200C, and B200T airplanes). This AD requires replacing the wiring for the engine fire detector system with fire resistant wiring. This AD is the result of the discovery during aircraft production of the potential for the existing engine fire detector system wiring on the affected airplanes to fail because of high heat and/or fire. The actions specified by this AD are intended to prevent failure of the engine fire detector system if high heat and/or fire stopped an electrical signal between the engine fire detectors and the engine fire warning annunciator lights located in the cockpit, which could result in passenger injury in the event of an airplane fire.
AD 98-10-12 · published May 15, 1998, effective Jun 8, 1998
REVO, Incorporated Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all REVO, Incorporated (REVO) Models Colonial C-2, Lake LA- 4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 airplanes. This action requires measuring for a clearance of \5/32\ of an inch between the attachment fitting and the horizontal stabilizer rear beam, and a clearance of \1/16\ of an inch between the attachment fitting and the stabilizer skin. If either area does not meet these minimum measurements, this AD requires removing the affected horizontal tail half from the airplane and inspecting the attachment fitting for any evidence of fretting, cracking, or corrosion. If cracks, fretting, or corrosion are present, the attachment fitting must be replaced with a new fitting, and the stabilizer skin must be trimmed to provide a positive clearance for the fitting. This action is prompted by an incident report of an airplane losing control during flight after the attachment fitting to the horizontal stabilizer fractured. The actions specified by this AD are intended to prevent fatigue cracks to the horizontal and vertical stabilizer attachment fitting, which could result in loss of control of the airplane.
AD 98-10-13 · published May 15, 1998, effective Jun 19, 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 modification of the aft avionic fan. 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 aft avionic fan due to inadequate cooling airflow through the fan housing, which could result in failure of the avionics equipment.
AD 98-10-14 · published May 15, 1998, effective Jun 19, 1998
Lockheed Model L-1011-385 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires various types of inspections to detect fatigue cracking of certain areas of the rear spar caps, web, skin, and certain fastener holes; and repair or modification, if necessary. This amendment reduces the repetitive inspection interval for all of the currently required inspections, except for the X-ray inspections. It also revises the terminating modification provision for some airplanes. This amendment is prompted by reports of cracks found during the currently required inspections, which had progressed to lengths greater than predicted. The actions specified by this AD are intended to ensure that fatigue cracking is detected and corrected in a timely manner before it can lead to rupture of the rear spar, extensive damage to the wing, and spillage of fuel.
AD 97-25-11 R1 · published May 18, 1998, effective Jun 25, 1998
Bombardier Inc. Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B16 series airplanes, that currently requires disabling the remote fuel/defuel panel in the cockpit; and provides for an optional modification of the remote fuel/defuel panel, which would terminate the requirement to disable the panel. This amendment reduces the applicability of the existing AD. This amendment is prompted by reports of in-flight failure of the panel that resulted when a circuit breaker on a battery bus opened due to insufficient current flow capacity. The actions specified in this AD are intended to prevent the circuit breakers from opening during flight, which could result in irreversible loss of engine indicating and fuel quantity systems in the cockpit.
AD 98-11-01 · published May 18, 1998, effective Jun 7, 1998
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment supersedes Airworthiness Directive (AD) 97-23- 04, which currently requires replacing the fuel tank vent valves with modified fuel tank vent valves on certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD retains the fuel tank vent valves replacement required by AD 97-23-04, and requires drilling a 4.8 millimeter (0.1875 inch) hole in each fuel filler cap. This AD 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 is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the fuel tank inward vent valve from freezing, which, if followed by a cold soak at altitude, could result in wing airfoil distortion and structural damage with consequent degradation of the airplane's handling qualities.
AD 98-11-02 · published May 18, 1998, effective Jun 2, 1998
Fokker Model F28 Mark 0070 and Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with instructions not to arm the liftdumper system prior to commanding the landing gear to extend. 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 inadvertent deployment of the liftdumpers during approach for landing, and consequent reduced controllability and performance of the airplane.
AD 98-11-03 · published May 19, 1998, effective Jun 23, 1998
Boeing Model 727 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that currently requires that the FAA-approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item, and repair of cracked structure. That AD was prompted by a structural re-evaluation by the manufacturer that identified additional structural elements where, if damage were to occur, supplemental inspections may be required for timely detection. This amendment requires additional and expanded inspections, and repair of cracked structure. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to ensure the continued structural integrity of the entire Boeing Model 727 fleet.
AD 98-11-04 · published May 19, 1998, effective Jun 23, 1998
Boeing Model 737-100 and -200 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100 and -200 series airplanes, that currently requires that the FAA-approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item, and repair of cracked structure. That AD was prompted by a structural re-evaluation by the manufacturer which identified additional structural elements where, if damage were to occur, supplemental inspections may be required for timely detection. This amendment requires additional and expanded inspections, and repair of cracked structure. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to ensure the continued structural integrity of the entire Boeing Model 737-100 and -200 fleet.
AD 98-11-08 · published May 20, 1998, effective Jun 24, 1998
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires replacement of the non-return valves located in the engine fuel feed lines on the outer fuel tank with new return valves; and, for certain airplanes, replacement of the inner tank booster pump canisters with modified canisters. 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 sticking of non-return valves located in the fuel system, which could result in an internal fuel transfer from the center tank to the inner or outer tank. Such a transfer of fuel could lead to fuel spillage overboard through the vent system, and consequent insufficient fuel for the airplane to reach its flight destination.
AD 98-11-09 · published May 20, 1998, effective Jun 24, 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 a one-time visual inspection of the pilot valve harness tubes for bulges and cracks, cleaning the tubes, applying sealant at the tube end opening, and replacing any discrepant tubes with serviceable tubes. This amendment also requires replacement of the pilot valve harness tubes and vent valve tubes with new tubes having improved anti- corrosion protection. 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 pilot valve harness tubes, which could allow fuel to enter the conduit and leak overboard; this condition could result in increased risk of a fuel tank explosion and fire.
AD 98-11-07 · published May 21, 1998, effective Jun 25, 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 of the double shuttle valve in the upper fuselage fairing for incorrectly labeled part numbers, 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 ensure replacement of the double shuttle valves when they have reached their maximum life limit; incorrectly labeled part numbers of the double shuttle valves that are not replaced could result in the failure of the roll control spoilers, and, consequently, lead to reduced controllability of the airplane.
AD 98-11-10 · published May 22, 1998, effective Jun 26, 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 an inspection to determine if the latching lever pin of the speed brake passes an axial force check, and a visual inspection to determine if the staking of the latching lever pin is acceptable; and follow-on corrective action, if necessary. This amendment is prompted by reports that the speed brake handle jammed in the ground spoiler position. The actions specified by this AD are intended to prevent a jammed speed brake handle pin, which could result in retraction of the spoilers and full advancement of the left throttle during a go-around.
AD 98-11-13 · published May 22, 1998, effective Jun 8, 1998
Raytheon Model Hawker 800XP Series Airplanes, and Hawker 800 (U-125A Military Derivative) Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Raytheon Model Hawker 800XP series airplanes and Hawker 800 (U-125A military derivative) airplanes. This action requires removal of the sealant from the firewall mounting flanges and mounting points of the fire extinguisher assemblies; removal of sealant obstructing the discharge tubes of the fire extinguisher assemblies; cleaning and flushing of the mounting flanges, mounting points, and discharge tubes with solvent; and installation of new gaskets on the firewall mounting flanges and mounting points. This amendment is prompted by reports of excessive sealant applied during manufacture of the firewall mounting flanges and mounting points of the fire extinguisher assemblies, which subsequently entered and obstructed the discharge tubes. The actions specified in this AD are intended to prevent obstructions of the discharge tubes of the fire extinguisher assemblies, which could result in improper distribution of the fire extinguishing agent within the nacelle in the event of a fire.
AD 98-11-06 · published May 26, 1998, effective Jun 30, 1998
Aerospatiale Model ATR42-300 and -320, and Model ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and -320, and Model ATR72 series airplanes, that requires modification of the engine fuel drainage 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 fuel from overflowing into the engine nacelle, which could result in a fire in the nacelle.
AD 98-11-11 · published May 26, 1998, effective Jun 30, 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 modification of the passenger and crew doors and repetitive visual inspections, adjustments, and tests of the passenger and crew door latching and locking systems to ensure correct operation. 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 opening of a door during flight of the airplane, which could result in rapid decompression of the passenger cabin.
AD 98-11-12 · published May 26, 1998, effective Jun 30, 1998
de Havilland Model DHC-8-301, -311, - 314, and -315 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-301, -311, -314, and - 315 series airplanes, that requires installation of additional wiring and new electrical connectors for the lights in the forward end of the passenger overhead compartments. 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 severe overheating of the electrical connectors for the lights in the forward end of the passenger overhead compartments, which could result in smoke and fire in the passenger cabin.
AD 98-11-05 · published May 28, 1998, effective Jul 2, 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 performing a one-time inspection of the dropout boxes of the passenger oxygen system to detect discrepancies and determine whether the system operates properly; correcting any discrepancy found; and reworking or installing new components, if necessary. This amendment is prompted by a report indicating that the oxygen system failed to operate correctly after activation at a low cabin pressure due to the incorrect installation of the oxygen masks or oxygen generators during manufacturing. The actions specified by this AD are intended to ensure that a sufficient supply of oxygen is provided to airplane passengers in the event of rapid decompression of the airplane.
AD 98-11-16 · published May 28, 1998, effective Jul 11, 1998
Dornier Luftfahrt GmbH Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Dornier Luftfahrt GmbH (Dornier) Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes. This AD requires modifying the logic in the failure detection circuits of the landing gear uplock switches. 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 a false warning indication of landing gear failure because of the design of the landing gear warning system, which could result in incorrect actions from the pilot based on the warning indications.
AD 98-11-19 · published May 28, 1998, effective Jul 2, 1998
Airbus Model A310 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a visual inspection to detect cracks in the aft mount beam assembly of the engine; and replacement of any cracked beam with a new beam or beam assembly. This amendment also requires a fluorescent penetrant inspection to detect cracks in the aft mount beam assembly of the engine, and various follow-on actions. This amendment is prompted by reports indicating that, apparently due to manufacturing defects during the forging process, cracking was found in two engine aft mount beams. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural integrity of the aft mount beam assembly of the engine.
AD 98-11-20 · published May 28, 1998, effective Jul 13, 1998
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC- 12/45 airplanes that incorporate an executive cabin layout. This AD requires modifying the lavatory wall and passenger seat configuration. 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 head injuries during an airplane crash because the lavatory wall and passenger seat configuration do not meet current head injury criteria regulations.
AD 98-11-24 · published May 29, 1998
Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA series airplanes. This amendment requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. 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 and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 98-10-04 · published May 7, 1998, effective Jun 11, 1998
Eurocopter France Model SA-365N1, AS- 365N2, and SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Eurocopter) Model SA-365N1, AS-365N2, and SA-366G1 helicopters, that requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for cracks or delaminations. This amendment is prompted by a report of delamination of a Kevlar tie-bar. The actions specified by this AD are intended to detect cracks that could lead to delamination of the Kevlar tie-bar, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 97-18-11 · published May 13, 1998, effective May 28, 1998
Bell Helicopter Textron (Bell) Model 204B, 205A, and 205A-1 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-18-11, issued on August 29, 1997, which was sent previously to all known U.S. owners and operators of Bell Model 204B, 205A, and 205A-1 helicopters by individual letters. This AD requires modification and inspections of the vertical fin spar. If any crack is discovered, replacement of the vertical fin spar with an airworthy vertical fin spar is required before further flight. This amendment is prompted by several failures of the vertical fin spar, including those with steel doublers, caused by fatigue cracks that result from a large number of high-power events. The actions specified by this AD are intended to prevent in-flight failure of the vertical fin spar and subsequent loss of control of the helicopter.
AD 97-20-09 · published May 13, 1998, effective May 28, 1998
Arrow Falcon Exporters, Inc., California Department of Forestry, Rotorcraft Development Corporation, San Joaquin Helicopters, International Helicopters, Inc., Robinson Air Crane, Inc., Smith Helicopters, Southern Helicopter, Inc., Southwest Florida Aviation International, Tamarack Helicopters, Inc., US Helicopter, Inc., Richards Heavylift Helo, Inc., Hagglund Helicopters,
This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Bell-manufactured Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters; and Southwest Florida Aviation SW204, SW204HP, and SW205 helicopters, that currently requires modification and inspections of the vertical fin spar. This amendment requires the same modification and inspections required by the existing priority letter AD, but adds the Southwest Florida Aviation Model SW205A-1 and Utah State University UH-1H helicopters to the applicability of this AD. This amendment is prompted by accidents involving in-flight failure of the tailboom vertical fin spar. The actions specified by this AD are intended to prevent in-flight failure of the vertical fin spar and subsequent loss of control of the helicopter.
AD 98-09-15 · published May 6, 1998, effective Jul 6, 1998
General Electric Company Model GE90-76B Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) Model GE90-76B turbofan engines, that requires reduced life limits for certain rotating components. This amendment is prompted by the results of a refined life analysis performed by the manufacturer which revealed minimum calculated low cycle fatigue lives lower than the published low cycle fatigue retirement lives for certain rotating components. The actions specified by this AD are intended to prevent a low cycle fatigue failure of a rotating component and possibly an uncontained engine failure.
AD 98-09-27 · published May 6, 1998, effective May 21, 1998
Rolls-Royce, plc RB211 Trent 768 and 772 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 768 and 772 series turbofan engines. This action requires initial and repetitive visual inspections of thrust reverser hinge lugs and attachment ribs for cracks, and, if necessary, removal from service and replacement with serviceable parts. This amendment is prompted by aircraft certification testing which revealed that stresses on the thrust reverser hinge were higher than had been anticipated during engine certification. The actions specified in this AD are intended to prevent thrust reverser hinge failure, possibly resulting in liberation of the thrust reverser cowl duct from the engine nacelle, which could result in impact damage to other sections of the aircraft.
AD 98-10-03 · published May 8, 1998, effective May 26, 1998
Allison Engine Company Model 250-C47B Turboshaft Engines
This amendment supersedes an existing airworthiness directive (AD) 97-21-09, applicable to Allison Engine Company Model 250-C47B turboshaft engines, that currently requires replacing the engine main electrical harness assembly with an improved assembly, installing a new hydromechanical unit (HMU) and electronic control unit (ECU), removing the placard notifying the pilot that the overspeed protection system is disabled, and revising the Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC), Model 407 Rotorcraft Flight Manual (RFM). This amendment continues the requirements of the current AD, but adds the requirement to install ECUs with improved resistance to corrosion. This amendment is prompted by reports of ECUs with annunciated hard faults due to corrosion on internal connectors. The actions specified by this AD are intended to prevent uncommanded inflight engine shutdowns, which can result in autorotation, forced landing, and possible loss of the helicopter.
AD 98-10-11 · published May 19, 1998, effective Jun 3, 1998
CFM International CFM56-3, -3B, -3C, - 5, -5B, and -5C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-3, -3B, -3C, -5, -5B, and -5C series turbofan engines. This action supersedes telegraphic AD T97-25- 51 that currently requires removal of one engine from an aircraft, and replacement with a serviceable engine or replacement of parts, if both engines are equipped with a specific accessory gearbox (AGB) starter gearshaft or transfer gearbox (TGB) input bevel gear, and daily checks of the AGB/TGB magnetic chip detector. This amendment is prompted by further investigation that has revealed that certain TGB output bevel gears and AGB intermediate gear assemblies on CFM56-3, -3B, and -3C series engines, and AGB gearshaft cluster spur assemblies on CFM56-5, - 5B, and -5C series engines could also be affected. The actions specified by this AD are intended to prevent inflight engine shutdowns due to an AGB starter gearshaft, TGB input bevel gear, TGB output bevel gear, AGB gearshaft cluster spur assembly or AGB intermediate gear assembly failure.
AD 98-10-15 · published May 19, 1998, effective May 19, 1998
AlliedSignal Inc. Model TFE731-40R-200G Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to AlliedSignal Inc. Model TFE731-40R-200G turbofan engines. This action requires replacing the fuel line between the main fuel pump and the motive flow pump with a serviceable assembly and adding a supporting bracket and clamp. This amendment is prompted by a report of a cracked fuel line between the main fuel pump and the motive flow pump causing the spraying of fuel on and around electrical components. The actions specified in this AD are intended to prevent fuel spraying on and around electrical components due to a cracked fuel line, which could result in an engine fire.
AD 98-10-07 · published May 13, 1998, effective Jun 26, 1998
Alexander Schleicher Segelflugzeugbau Model ASK 21 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASK 21 sailplanes that have certain modifications installed. This AD requires changing the sailplane flight manual's weight and balance information. 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 operator from using inaccurate weight and balance information provided in the sailplane flight manual (SFM), which could lead to hazardous flight conditions.
AD 98-11-17 · published May 28, 1998, effective Jul 10, 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 Bosch electrical system regulator, part number (P/N) 0212920001, with a type 4 E 26 regulator. 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 electrical system regulator, which could result in smoke entering the cockpit with consequent passenger injury.
AD 98-11-18 · published May 28, 1998, effective Jul 10, 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 upper rubber shock mounts with mounts made of stainless steel. This AD will also require inspecting the rear plate of the propeller mount for cracks and proper mounting, and replacing or modifying as necessary. 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 suspension system caused by cracks in the propeller mounts, which could result in loss of the propeller with consequent reduced glider controllability.
