55 Airworthiness Directives: 28 airplane, 13 rotorcraft, 4 engine, 2 appliance, 8 glider.
AD 98-22-01 · published Nov 2, 1998, effective Dec 7, 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 a one-time visual inspection and a one-time eddy current and/or dye penetrant inspection of the nose landing gear (NLG) main fitting to detect cracking; and rework of the NLG main fitting, 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 NLG main fitting, which could lead to collapse of the NLG during takeoff and landing and possible injury to the flightcrew and passengers.
AD 98-23-02 · published Nov 4, 1998, effective Dec 22, 1998
Cessna Aircraft Company 180 and 185 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 80-10- 01, which applies to certain Cessna Aircraft Company (Cessna) 180 and 185 series airplanes that have either Airglas Engineering Company, Inc., (AECI) Model LW3600-180 (single position) or Model LW3600-180A (two position) fixed penetration wheel skis installed in accordance with Supplemental Type Certificate (STC) SA213AL. AD 80-10-01 requires modifying the ski bungee assemblies, safety cables, and check cables, and their attachments to the airplane and the skis; limiting the maximum airspeed to 160 knots with skis installed; and installing an airspeed limitation placard. This AD is the result of field reports of incidents occurring on the affected airplanes that were in compliance with AD 80-10-01, and the fact that Cessna Model 180K airplanes were inadvertently left out of the existing AD. This AD retains the actions required by AD 80-10-01; requires re-marking the airspeed indicator to display the reduced airspeed limits and placing a certain airplane flight manual (AFM) supplement in the cockpit; and adds Cessna Model 180K airplanes to the Applicability section of the AD. The actions specified by this AD are intended to prevent one or both wheel skis from rotating into a nose-down position during flight, which could result in loss of control of the airplane and/or possible airplane damage during flight or landing operations.
AD 98-23-05 · published Nov 5, 1998, effective Dec 10, 1998
Boeing Model 767 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires an inspection to detect damage of the wire bundles in the left side of the flight compartment in the vicinity of the stowage box for the captain's oxygen mask, and repair, if necessary; a continuity check on repaired wires; installation of sleeving over the wire bundles; and rerouting of the wire bundles. This amendment requires modifications of the captain's and first officer's consoles in the flight compartment to ensure adequate clearance between oxygen equipment and adjacent wire bundles. This amendment is prompted by reports indicating that chafed wiring and wire insulation wear occurred in the vicinity of the stowage box for the captain's oxygen mask due to interference between oxygen line fittings and adjacent wire bundles. The actions specified by this AD are intended to prevent such chafing and inadequate clearance, which could result in electrical arcing and consequent oxygen leakage in the vicinity of the stowage box; these conditions, if not corrected, could result in a fire in the flight compartment.
AD 98-23-11 · published Nov 12, 1998, effective Dec 17, 1998
McDonnell Douglas Model DC-9-31 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-31 series airplanes, that requires a one-time visual inspection to determine if all corners of the forward service door doorjamb have been modified previously, various follow-on repetitive inspections, and modification, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners of the forward service door doorjamb. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
AD 98-23-12 · published Nov 12, 1998, effective Dec 17, 1998
de Havilland Model DHC-7 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that currently requires certain structural inspections, and repair, if necessary. This amendment requires an additional structural inspection. 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 in certain significant structural areas, which could reduce the structural integrity of these airplanes.
AD 98-23-13 · published Nov 12, 1998, effective Dec 17, 1998
British Aerospace Model Viscount 744, 745, 745D, and 810 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model Viscount 700, 800, and 810 series airplanes, that currently requires repetitive inspections to detect cracks and corrosion in the inboard and outboard engine nacelle structures on the wings; replacement of any cracked fittings and mating struts; and treatment or replacement of any corroded fittings or struts. This amendment requires repetitive inspections to detect cracking or corrosion of the eye end fittings of the outboard engine lower support or of the bore of the taper pin holes, and repair, if necessary. This amendment also limits the applicability of the existing AD. This amendment is prompted by reports of cracked and separated lower eye end fittings. The actions specified by this AD are intended to detect and correct cracking of the eye end fittings of the outboard engine lower support, which could result in reduced structural integrity of the engine nacelle support structures.
AD 89-18-07 R1 · published Nov 13, 1998, effective Dec 18, 1998
Raytheon Model BAe.125, DH.125, BH.125, and HS.125 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Raytheon Model BAe.125, DH.125, BH.125, and HS.125 series airplanes, that currently requires inspection of the elevator mass balance side plate assembly and spigot for corrosion, and repair, if necessary; application of corrosion protection treatment; and installation of corrosion resistant Monel rivets in the elevator balance weight structure. That AD was prompted by reports of corrosion on the elevator mass balance side plate assembly and the balance weight spigot. The actions specified by that AD are intended to prevent such corrosion damage, which could lead to displacement of the side plate and consequent control surface interference and jamming of flight controls. This amendment limits the applicability of the existing AD.
AD 96-04-11 R1 · published Nov 13, 1998, effective Nov 30, 1998
Boeing Model 757-200 Series Airplanes Equipped With Rolls Royce Model RB211-535E4/E4B Engines
This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that currently requires a revision to the Airplane Flight Manual to ensure that the flightcrew activates the engine cowl thermal anti-ice (CTAI) system for both engines at the top of descent to avoid engine rundown (loss of engine power). This amendment clarifies the relationship between two existing AD's. The actions specified in this AD are intended to ensure that the flightcrew activates the engine cowl thermal anti-ice system for both engines prior to descent; activation of the engine CTAI system in the middle of descent could result in a compressor stall and subsequent engine rundown of multiple engines.
AD 98-23-15 · published Nov 13, 1998, effective Dec 18, 1998
Raytheon Model Hawker 800XP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP series airplanes, that requires replacement of the fuel feed hose assemblies of the auxiliary power unit (APU) with new hose assemblies. This amendment is prompted by a report of the collapse of the inner casing of the fuel feed hose that supplies fuel to the APU. The actions specified by this AD are intended to prevent failure of the fuel feed hose assemblies, which could result in fuel leakage and consequent risk of fire in the aft equipment bay.
AD 98-23-16 · published Nov 13, 1998, effective Dec 18, 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 the installation of certain rivets on support arm 2 of the left and right flaps. 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 of the support arms of the flaps, which could result in reduced structural integrity of the airplane.
AD 98-24-02 · published Nov 13, 1998, effective Nov 30, 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 one-time inspection to identify the part numbers of two dimmer controls for the overhead instrument panel light and circuit breaker lightplate located in the flight compartment. For airplanes on which a dimmer control having an incorrect part number is installed, this action also requires replacing the dimmer control with a new part; modifying and reinstalling the existing dimmer control; or reinstalling a dimmer control following modification of the part by the part manufacturer. This amendment is prompted by reports of smoke emitting from the overhead panels in the cockpit area. The actions specified in this AD are intended to prevent an electrical failure in the overhead dimmer control due to overheating of a printed circuit board capacitor in the dimmer control, which could result in rupture of the capacitor and smoke in the flight compartment.
AD 98-23-14 · published Nov 16, 1998, effective Dec 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 inspecting the elevator and aileron control retaining pins for proper installation and damage, and replacing any improperly installed or damaged pins. 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 retaining pins from interfering with the flight control elements, which could result in loss of the cable retaining function with consequent loss of control of the airplane.
AD 98-23-17 · published Nov 16, 1998, effective Dec 21, 1998
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of the emergency evacuation slide/raft 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 the container release cable of the emergency evacuation slide/raft system from jamming, which could result in the inability to open the emergency exit doors or to correctly deploy the emergency evacuation slide/rafts, and consequent delay or impedance of passengers exiting the airplane during an emergency.
AD 98-24-01 · published Nov 18, 1998, effective Dec 23, 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 repetitive detailed visual inspections to detect cracking or other damage of certain diaphragm support structures of the forward equipment compartment; and repair, 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 failure of the two diaphragms that support the upper structure of the forward equipment compartment, which could accelerate fatigue damage in adjacent structure and result in reduced structural integrity of the airframe.
AD 98-24-05 · published Nov 23, 1998, effective Jan 4, 1999
HOAC-Austria Model DV-20 Katana Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain HOAC-Austria (HOAC) Model DV-20 airplanes equipped with ROTAX 912 A3 engines. This AD requires replacing the engine electronic modules. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Austria. The actions specified by this AD are intended to prevent electromagnetic interference (EMI) on the engine electronic module, which could cause the airplane engine to stop due to the interruption of the airplane's ignition system and result in loss of control of the airplane.
AD 98-24-06 · published Nov 23, 1998, effective Dec 28, 1998
Dornier-Werke G.m.b.H. Model Do 27 Q-6 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Dornier-Werke G.m.b.H. (Dornier) Model Do 27 Q-6 airplanes. This AD requires repetitively inspecting the rivets that attach the forward stabilizer attach fitting to the airplane fuselage for looseness, and replacing any loose rivets. 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 stabilizer from detaching at the forward stabilizer attach flanges because of loose rivets, which could result in reduced or loss of control of the airplane.
AD 98-24-07 · published Nov 23, 1998, effective Dec 28, 1998
EXTRA Flugzeugbau GmbH Models EA-300, EA-300S, and EA-300L Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300, EA- 300S, and EA-300L airplanes. This AD requires repetitively inspecting the rudder pedal for proper alignment, the safety control stop for wear and proper clearance, the rudder cables for elongation, and the rudder pedal footrest for cracks. This AD also requires correcting or replacing any discrepant part, as applicable. 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 rudder pedal footrest caused by overloading the rudder pedal safety control stop, which could result in loss of directional control of the airplane.
AD 98-24-08 · published Nov 23, 1998, effective Dec 28, 1998
Burkhart Grob Luft-und Raumfahrt Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Burkhart Grob Luft-und Raumfahrt (Grob) Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes. This AD requires inspecting the area of the elevator trim tab hinges for cracks and a secure fit, and repairing any elevator trim tab hinges with cracks or where a proper secure fit is not found. 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 structural damage of the trim tab hinges caused by cracks, which could result in trim tab failure with consequent loss of control of the airplane.
AD 98-24-11 · published Nov 23, 1998, effective Dec 28, 1998
Mooney Aircraft Corporation Models M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, and M20R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Mooney Aircraft Corporation (Mooney) Models M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, and M20R airplanes. This AD requires inspecting the aileron control links for the installation of a reinforcing gusset; and, if no gusset is installed, repetitively inspecting the aileron control links (left-hand and right-hand) for cracks. If cracks are found, this AD requires replacing the aileron control links with parts of improved design. This AD is the result of service difficulty reports (SDR's) on the aileron control links and reported failures of the aileron control links. The actions specified by this AD are intended to detect and correct cracked aileron control links, which could result in loss of aileron control with consequent loss of control of the airplane.
AD 98-24-18 · published Nov 23, 1998, effective Dec 8, 1998
Bombardier Model DHC-8-100 and -300 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102 and -103 series airplanes, that currently requires a one-time inspection to detect disbonding of the upper and lower skin panels of the horizontal stabilizer, and repair, if necessary. This amendment establishes repetitive intervals for the inspection to detect disbonding of the upper and lower skin panels of the horizontal stabilizer. This amendment also revises the applicability of the existing AD to include certain additional airplanes, and to exclude certain 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 reduced strength capability and consequent failure of the horizontal stabilizer, which could result in loss of controllability of the airplane.
AD 97-09-15 R1 · published Nov 24, 1998, effective Dec 29, 1998
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and - 500 series airplanes, that currently requires a one-time inspection to determine the part number of the engage solenoid valve of the yaw damper on the rudder power control unit, and replacement of the valve with a valve having a different part number, if necessary. That AD was prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by that AD are intended to prevent sudden uncommanded yawing of the airplane due to potential failures within the yaw damper system, and consequent injury to passengers and crewmembers. This amendment makes certain editorial changes to clarify the requirements of the existing AD.
AD 98-24-04 · published Nov 24, 1998, effective Dec 28, 1998
SOCATAGroupe 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 repetitively inspecting (using visual methods) the web of the left and right flap carriage for cracks, and replacing any cracked flap carriage with one of improved design. The proposed 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 detect and correct cracks in a flap carriage, which could result in loss of the flap function with consequent reduced and/or loss of airplane control.
AD 98-24-17 · published Nov 24, 1998, effective Dec 29, 1998
McDonnell Douglas Model DC-10-10, -30, and -40 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -30, and -40 series airplanes, that requires replacement of certain taper-lok attachments and forward trunnion bolts with new components that attach the left and right main landing gear (MLG) to each wing. This amendment is prompted by a report indicating that, due to overstrength of the forward trunnion bolt, an MLG broke away and ruptured a wing fuel tank while an airplane was being operated off the runway. The actions specified by this AD are intended to ensure that the MLG separates from the wing when it is subjected to unpredictable overloads during abnormal operations, and to prevent consequent primary structural damage to the airplane.
AD 98-24-19 · published Nov 25, 1998, effective Dec 10, 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 certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 series airplanes. This action requires revising the Performance Section of the Airplane Flight Manual (AFM) to provide the flightcrew with procedures to adjust landing distances for landings performed with the anti-icing system active. This action also requires revising the Limitations Sections of the AFM to prohibit certain types of approaches with the anti-icing system active. This amendment is prompted by a report that increased (i.e., higher than normal) flight idle thrust may occur when the anti-icing system is active. The actions specified in this AD are intended to ensure that the flightcrew is advised of appropriate landing field lengths when operating with the anti-icing system active, and that instrument approaches at certain flap settings are prohibited with the anti-icing system active. Increased flight idle thrust when the anti-icing system is active, if not corrected, could result in landing overrun.
AD 98-24-24 · published Nov 25, 1998, effective Dec 30, 1998
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain MD-11 series airplanes, that requires a one-time visual inspection to detect discrepancies of the seat tracks and adjacent structure underneath lavatories, and repair, if necessary. This amendment also requires installation of a non-metallic barrier on the bottom of each lavatory foot fitting, and replacement of existing seat track fittings with new seat track fittings. This amendment is prompted by reports of galvanic corrosion found on the seat tracks at attachment points under certain lavatories. The actions specified by this AD are intended to prevent corrosion of seat tracks and adjacent structure. Corrosion of the seat tracks and adjacent structure could result in shifting of lavatories, which could lead to injury of passengers and crew, as well as damage to aircraft structure and systems.
AD 98-24-25 · published Nov 25, 1998, effective Dec 30, 1998
Lockheed Model L-188A and L-188C Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-188A and L-188C series airplanes, that requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in icing conditions. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines that experienced tailplane stall due to ice accretion on the horizontal stabilizer of the airplane. The actions specified by this AD are intended to prevent undetected accretion of ice on the horizontal stabilizer, which could result in ice contaminated tailplane stall and consequent loss of pitch control.
AD 98-24-26 · published Nov 25, 1998, effective Dec 30, 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 replacing the cam assembly, cam bellcrank assembly, and thrust reverser control switch actuator on all four thrust levers with new components. This amendment is prompted by a report of an uncommanded automatic retraction of the leading edge flaps during takeoff. The actions specified by this AD are intended to prevent such uncommanded automatic retraction, which would seriously degrade liftoff and climb capabilities, and could result in near-stall conditions at a critical phase of the flight.
AD 98-24-29 · published Nov 25, 1998, effective Jan 8, 1999
Aerostar Aircraft Corporation PA-60-600 and PA-60-700 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Aerostar Aircraft Corporation (Aerostar) PA-60-600 and PA-60-700 series airplanes. This AD requires repetitively inspecting the forward face of each wing's 55-percent upper spar cap for cracks above the main landing gear fitting in the top of the wheel well, and replacing or repairing any cracked upper spar cap. Reports of spanwise cracks in the area above the main landing gear attachment on two of the affected airplanes prompted this action. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing upper spar cap, which could result in structural failure of the wing spar to the point of failure with consequent loss of control of the airplane.
AD 98-15-25 · published Nov 3, 1998, effective Nov 18, 1998
Eurocopter Deutschland GmbH Model EC 135 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-15-25, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH Model EC 135 helicopters by individual letters. This AD supersedes AD 98-09-11, applicable to Eurocopter Deutschland GmbH Model EC 135 helicopters, that required, before further flight, a tail rotor drive shaft vibration survey and installation of a Fenestron Shaft Retrofit Kit; 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 AD requires the same actions as the superseded AD, however it changes the required compliance time for the repetitive inspections. This amendment is prompted by reports of loose bearings and attachment bolts. This condition, if not corrected, could result in loose bearing attachment bolts, or cracked bearing supports, which could result in loss of drive to the tail rotor and subsequent loss of control of the helicopter.
AD 98-23-03 · published Nov 5, 1998, effective Dec 10, 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 removing and replacing each tail rotor electrical bonding braid (bonding braid). This amendment is prompted by an in-service report of the failure of a bonding braid. The actions specified by this AD are intended to prevent failure of a bonding braid due to fatigue, resulting impact with the tail rotor blades, and subsequent loss of control of the helicopter.
AD 98-23-04 · published Nov 5, 1998, effective Dec 10, 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 replacing main rotor blades with modified main rotor blades. This amendment is prompted by reports of an investigation that found broken braids on main rotor blade de-icers. The actions specified by this AD are intended to prevent loss of deicing capabilities of the main rotor blades, adverse performance during flight in icing conditions, and subsequent loss of control of the helicopter.
AD 98-22-16 · published Nov 10, 1998, effective Nov 10, 1998
Robinson Helicopter Company (RHC) Model R44 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-22-16 which was sent previously to all known U.S. owners and operators of RHC Model R44 helicopters by individual letters. This amendment supersedes AD 98-12- 19, issued August 5, 1998, applicable to RHC Model R44 helicopters, that currently requires main rotor blade inspections and replacement if a crack is found. This amendment requires the same inspections as AD 98-12-19, but mandates replacement of all the affected main rotor blades prior to further flight after November 15, 1998. This amendment is prompted by an incident in which a crack was discovered in a main rotor blade. The actions specified by this AD are intended to prevent failure of a main rotor blade and subsequent loss of control of the helicopter.
AD 98-23-09 · published Nov 10, 1998, effective Dec 15, 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 an initial and repetitive inspections of each tail rotor shaft flapping hinge retainer (retainer) for cracks and replacement of a retainer if a crack is discovered. This amendment is prompted by a report of high vibrations due to a cracked retainer occurring on a helicopter while it was in service. The actions specified by this AD are intended to detect cracks in the retainers that, if left undetected, could lead to high tail rotor vibrations, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 98-23-18 · published Nov 13, 1998, effective Nov 30, 1998
Bell Helicopter Textron, Inc. Model 214B, 214B-1, and 214ST Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (Bell) Model 214B, 214B- 1, and 214ST helicopters. This action requires a visual inspection of thin-flanged attachment barrel nuts (barrel nuts) manufactured by Kaynar Technologies, Inc. for cracks or lubrication residue, and replacement of the barrel nuts and corresponding attaching bolts, as necessary. These barrel nuts have been installed in main rotor grips, pitch horns, and tailboom assemblies. This amendment is prompted by a report of a cracked barrel nut, which was discovered on a helicopter being prepared for shipment. The actions specified in this AD are intended to detect cracks in a barrel nut, which could lead to failure of a main rotor grip, pitch horn, or tailboom, and subsequent loss of control of the helicopter.
AD 98-24-13 · published Nov 19, 1998, effective Dec 4, 1998
Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model MBB-BK117 A-1, A-3, A-4, B-1, B-2, and C-1 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter Model MBB-BK117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, that currently requires initial and repetitive inspections of both surfaces of the tail boom vertical fin (vertical fin) spar, the skin, and the left-hand and right-hand frame sheets for cracks or loose rivets. That AD also requires repairing certain cracks, if found, and repairing and reporting those loose rivets and certain other cracks, if found. This amendment requires the same inspections, repairs, and reporting as the existing AD, but changes the reference to the service bulletin and prohibits the use of blind rivets for the vertical fin spar repair. This amendment is prompted by an accident that occurred on April 15, 1997, resulting in one fatality. The actions specified by this AD are intended to prevent failure of the vertical fin and subsequent loss of control of the helicopter.
AD 98-24-15 · published Nov 23, 1998, effective Dec 8, 1998
Bell Helicopter Textron Model 204B, 205A, 205A-1, 205B, and 212 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron Model 204B, 205A, 205A-1, and 212 helicopters, that currently establishes a retirement life for the main rotor masts (masts) and main rotor trunnions (trunnions) based on time-in-service (TIS) and types of operations. This amendment adds Model 205B helicopters to the applicability; requires creation of component history cards or equivalent records using a Retirement Index Number (RIN) system; establishes a system for tracking increases to the accumulated RIN; and establishes a maximum accumulated RIN for certain masts and trunnions. This amendment is prompted by an accident involving a Model 205A-1 helicopter, in which a mast failure caused a separation of the main rotor from the helicopter. The actions specified by this AD are intended to prevent fatigue failure of the mast or trunnion and subsequent loss of control of the helicopter.
AD 98-21-09 · published Nov 24, 1998, effective Dec 9, 1998
Robinson Helicopter Company Model R22 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-21-09, which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R22 helicopters by individual letters. This AD requires installing fuel tank vent tube(s), with modified attachment to the mast tube, if not previously accomplished; installing a spring into the flexible tube leading to the main fuel tank; and installing a spring into the flexible tube leading to the auxiliary fuel tank, if an auxiliary fuel tank is installed. This amendment is prompted by an incident in which the flexible vent connecting the rigid vent tube to the main fuel tank kinked, resulting in fuel starvation and a hard landing after uncommanded engine shutdown. The actions specified by this AD are intended to prevent fuel starvation, loss of engine power, and a subsequent forced landing.
AD 98-24-21 · published Nov 24, 1998, effective Dec 9, 1998
Eurocopter France Model AS 332C, AS 332L, AS 332L1, and AS 332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France (ECF) Model AS 332C, AS 332L, AS 332L1, and AS 332L2 helicopters. This action requires inserting instructions into the Model AS 332C, AS 332L, AS 332L1, and AS 332L2 Rotorcraft Flight Manuals (RFMs) regarding actions to take if either the ``OVSP 1'' or ``OVSP 2'' amber warning light illuminates. This action also requires, for the Model AS 332C, AS 332L, and AS 332L1 helicopters, measuring the vibration levels of the engine-to-main gearbox (MGB) shaft, inspecting the torque on the MGB coupling bolts, and conducting an engine-to-MGB coupling 23,000 revolutions per minute (RPM) input check. This amendment is prompted by an accident involving a Model AS 332L1 helicopter in which the helicopter experienced an engine overspeed resulting in failure of both engines. The actions specified in this AD are intended to prevent failure of the rotor drive engine-to-MGB coupling, which, if undetected, could result in an engine overspeed leading to an uncontained engine turbine wheel burst and subsequent loss of control of the helicopter.
AD 98-24-22 · published Nov 24, 1998, effective Dec 9, 1998
Agusta A109C Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta A109C helicopters. This action requires, within the next 5 hours time-in-service (TIS), replacing the tail rotor blade grip assemblies (grip assemblies) with modified airworthy grip assemblies. This amendment is prompted by cracks that were found on the grip assemblies during maintenance inspections. This condition, if not corrected, could result in separation of a tail rotor blade and subsequent loss of control of the helicopter.
AD 98-24-23 · published Nov 25, 1998, effective Dec 10, 1998
Eurocopter France Model SE.3160, SA.316B, SA.316C, and SA.319B Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SE.3160, SA.316B, SA.316C, and SA.319B helicopters. This action requires inspecting certain horizontal stabilizer spar tubes and replacing them if cracks are found or repairing them if crazing, corrosion, fretting marks, or scratches are found and are repairable. This amendment is prompted by several service reports of spar tube corrosion and fatigue cracks discovered during normal maintenance inspections, which could cause loss of the horizontal stabilizer and subsequent loss of control of the helicopter.
AD 98-24-32 · published Nov 27, 1998, effective Dec 14, 1998
Eurocopter France Model AS-365N2, SA- 360C, SA-365C, C1, C2, N, N1, and SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS-365N2, SA-360C, SA-365C, C1, C2, N, N1, and SA-366G1 helicopters. This action requires inspecting for broken or out-of-tolerance attachment springs on the tail rotor hub fairing (fairing), replacing broken attachment springs and attachment springs that are out-of-tolerance, and marking the fairing to indicate compliance with this AD. This amendment is prompted by three in-service reports of failed attachment springs. The actions specified in this AD are intended to prevent failure of an attachment spring, which could cause loss of the fairing, damage to the tail rotor, and subsequent loss of control of the helicopter.
AD 98-23-06 · published Nov 5, 1998, effective Nov 20, 1998
General Electric Aircraft Engines CJ610 Turbojet and CF700 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Aircraft Engines (GEAE) CJ610 series turbojet and CF700 series turbofan engines. This action requires operators to remove and replace with serviceable parts unapproved combustion liner assemblies prior to further flight. This amendment is prompted by findings that unapproved combustion liner assemblies are installed on the affected engines. The actions specified in this AD are intended to prevent combustor liner cracking at multiple locations, progressing to liner fragmenting and combustor casing burnthrough, which could result in an engine fire.
AD 98-20-18 · published Nov 13, 1998, effective Nov 30, 1998
International Aero Engines (IAE) V2500- A1 Series Turbofan Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-20-18 that was sent previously to all known U.S. owners and operators of International Aero Engines (IAE) V2500-A1 series turbofan engines by individual letters. This AD requires, prior to further flight, removal from service of affected high pressure turbine (HPT) disks, identified by part number and serial number in the applicability paragraph of this AD, and replacement with a serviceable part. This amendment is prompted by a report of an uncontained HPT disk failure. The actions specified by this AD are intended to prevent an HPT disk fracture, an uncontained engine failure, and damage to the aircraft.
AD 98-23-07 · published Nov 13, 1998, effective Jan 12, 1999
Pratt & Whitney JT9D Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT9D series turbofan engines, that requires a one-time acid etch inspection of the turbine exhaust case (TEC) wall between and on either side of the ``R'' and ``S'' rails in the engine mount lug area (top quadrant of the case) for the presence of weld material, and if weld material is detected, removal from service and replacement with serviceable parts. This amendment is prompted by reports of weld rework performed in the outer case wall of the TEC, in the mount lug fillet area, during original production to address local under minimum wall thickness conditions which have left the TEC's structural capability compromised. The actions specified by this AD are intended to prevent TEC structural failure under abnormal operating conditions, which could result in reduced main mount load capability, engine separation from the wing and subsequent loss of control of the aircraft.
AD 98-23-08 · published Nov 13, 1998, effective Jan 12, 1999
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) PW4000 series turbofan engines not incorporating modifications described in certain PW service bulletins listed in the applicability section, that requires high pressure compressor (HPC) blade tip grinding of the rotor assembly, installation of aluminum oxide coated HPC blade tips in stages 9 through 12, modification of HPC 8th through 14th stage stators, incorporation of 1st stage high pressure turbine (HPT) vanes with increased airflow area which also requires additional HPT hardware modifications, and incorporation of HPC 13th-15th stage zirconium oxide blade tips. This amendment is prompted by reports of HPC surge caused by excessive HPC rear stage rotor-to-case clearance. The actions specified by this AD are intended to prevent HPC surge, which can result in engine power loss at a critical phase of flight such as takeoff or climb.
AD 98-23-01 · published Nov 17, 1998, effective Nov 20, 1998
Parker Hannifan Airborne Dry Air Pumps, Conversion Kits, and Coupling Kits
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-23-01, which was sent previously to all known U.S. owners and operators of aircraft and engines equipped with certain Parker Hannifin Airborne dry air pumps, conversion kits, and coupling kits, utilizing part number (P/N) B1-19-1 flexible coupling that has a date code resembling a clockface and indicating a manufacture date of either ``12/97'' or ``5-6/98''. This AD requires replacing the affected flexible coupling with P/N B1-7-3 flexible coupling (part of Parker Hannifin flexible coupling kit, Airborne P/N 350). The AD resulted from reports of failure of the affected flexible coupling due to a manufacturing defect of this coupling. The actions specified by this AD are intended to prevent failure of the primary dry air pump caused by defective flexible coupling, which could result in loss of primary attitude and direction references during instrument flight rules (IFR) operations.
AD 98-24-27 · published Nov 30, 1998, effective Jan 29, 1999
First Technology Fire and Safety Ltd. Toilet Compartment Fire Extinguishers
This amendment adopts a new airworthiness directive (AD) that is applicable to First Technology Fire and Safety Ltd. toilet compartment fire extinguishers. This amendment requires inspection of suspect fire extinguishers for leakage, and removal from service and replacement with serviceable parts if the extinguisher is found to be leaking. This amendment is prompted by reports of leakage at the fire extinguisher's eutectic tip. The leakage is the result of a design change. The actions specified by this AD are intended to prevent fire extinguisher failure due to leakage, which in the event of a toilet compartment fire could result in an uncontained fire and damage to the aircraft.
AD 98-22-14 · published Nov 2, 1998, effective Dec 14, 1998
Rolladen Schneider Flugzeugbau GmbH Models LS 3-A, LS 4, and LS 4a Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to Rolladen Schneider Flugzeugbau GmbH (Rolladen Schneider) Models LS 3-A, LS 4, and LS 4a sailplanes. This AD requires repetitively inspecting the forward elevator mounting bracket on the vertical tail fin for looseness, and, if any loose bracket is found, modifying the area and installing a new forward elevator mounting bracket. 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 detect and correct loose forward elevator mounting brackets, which could result in these brackets separating from the sailplane with consequent loss of control of the sailplane.
AD 98-22-15 · published Nov 2, 1998, effective Dec 14, 1998
Slingsby Aviation Limited Models Dart T.51, Dart T.51/17, and Dart T.51/17R Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Slingsby Aviation Limited (Slingsby) Models Dart T.51, Dart T.51/17, and Dart T.51/17R sailplanes that are equipped with aluminum alloy spar booms. This AD requires repetitively inspecting the aluminum alloy spar booms and the wing attach fittings for delamination or corrosion damage, and repairing any delamination or corrosion damage found. 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 spar assembly and adjoining structure caused by delamination or corrosion damage to the aluminum alloy spar booms or the wing attach fittings, which could result in reduced controllability or loss of control of the sailplane.
AD 98-23-10 · published Nov 12, 1998, effective Dec 17, 1998
Burkhart GROB Luft-und Raumfahrt GmbH Model G 109B Gliders
This amendment adopts a new airworthiness directive (AD) that applies to all Burkhart GROB Luft-und Raumfahrt GmbH (Grob) Model G 109B gliders. This AD requires inspecting the engine mounting frame for paint scratches and damage (abrasions, notches, or chafing); and repairing any paint scratches, and repairing or replacing any engine mounting frame that is found damaged. 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 detect and correct damage to the engine mounting frame, which could result in failure of the engine mount structure with consequent loss of the engine.
AD 98-24-09 · published Nov 23, 1998, effective Dec 28, 1998
Burkhart GROB Luft-und Raumfahrt GmbH Model G 109B Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain Burkhart GROB Luft-und Raumfahrt GmbH (Grob) Model G 109B gliders. This AD requires inspecting the elevator and trim tab for water, and assuring that the necessary drain holes are installed and existing drain holes are open. This AD also requires drilling any necessary drain holes and opening any existing drain holes that are closed; and, if a significant amount of water (more than \1/2\ liter) is found in the elevator, assuring that the elevator's weight and residual momentum and the glider's center of gravity (C.G.) are within the limits specified in the flight manual, and adjusting the elevator's weight and residual momentum and the glider's C.G., as needed. 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 water from penetrating the elevator and trim tab because of inadequate drainage, which could result in a delaminated elevator and trim tab structure with consequent elevator imbalance and flutter.
AD 98-24-10 · published Nov 23, 1998, effective Dec 9, 1998
Stemme GmbH & Co. KG Model S10 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Model S10 sailplanes. This AD requires replacing the flap drive rocker, part number (P/N) 10SW-RMW, with a modified flap drive rocker. 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 flap drive rocker caused by the design of the original part, which could result in loss of lateral control and wing flap control with consequent reduced and/or loss of sailplane control.
AD 98-24-12 · published Nov 23, 1998, effective Dec 24, 1998
Ursula Hanle Model H101 ``Salto'' Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Ursula Hanle (Hanle) Model H101 ``Salto'' sailplanes. This AD requires replacing the airbrake lever with one 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 the airbrake from deploying during high g maneuvers, which could result in an overstressing effect on the airframe with consequent reduced sailplane control.
AD 98-24-20 · published Nov 25, 1998, effective Jan 9, 1999
Grob Luft-und Raumfahrt, GmbH Models G 109 and G 109B Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Grob Luft-und Raumfahrt (Grob) Models G 109 and G 109B sailplanes. This AD requires inspecting the radius of the landing gear retaining bars, installing additional supportive parts, and replacing the retaining bars if the retaining bars' chamfer radius is less than 3.0 millimeters (mm). This AD also requires inspecting the landing gear legs for cracks and proper thickness, and either polishing out the cracks or replacing the landing gear legs with parts of improved design depending on the crack length. 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 detect and correct fatigue cracking of the landing gear legs, which could result in landing gear failure with consequent loss of control of the sailplane during landing operations.
AD 98-24-30 · published Nov 25, 1998, effective Dec 18, 1998
Stemme GmbH & Co. KG Models S10, S10-V, and S10-VT Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10, S10-V, and S10-VT sailplanes. This AD requires inspecting certain areas in the flight control system for cracks; immediately replacing any cracked parts; and eventually replacing all longitudinal coupling with modified coupling regardless if found cracked. 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 detect and correct cracks in certain areas of the flight control system, which could result in flight control system failure with consequent reduced or loss of control of the sailplane.
