76 Airworthiness Directives: 55 airplane, 11 rotorcraft, 1 engine, 1 propeller, 1 appliance, 7 glider.
AD 98-07-08 · published Apr 1, 1998, effective Apr 16, 1998
Israel Aircraft Industries (IAI), Ltd., Model 1125 Westwind Astra and Astra SPX Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all IAI, Ltd., Model 1125 Westwind Astra and Astra SPX series airplanes. This action requires disabling of the baggage compartment electrical heating blankets. 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 overheating of the electrical heating blankets, and consequent increased risk of fire in the baggage compartment.
AD 98-07-22 · published Apr 1, 1998, effective Apr 16, 1998
British Aerospace Model HS 748 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model HS 748 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits the positioning of the power levers below the flight idle stop during flight, and to add 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 propeller ground beta range was used improperly during flight. The actions specified in 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 98-07-12 · published Apr 2, 1998, effective May 7, 1998
Dornier Model 328-100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires repetitive tightening of the screws and quick- release fasteners on the wing/body fairing panels. This action will continue to require the repetitive tightening of these parts on certain airplanes. This amendment requires the installation of new fastener systems for those panels on certain airplanes and the application of new torque values. Accomplishment of these actions will terminate the requirement for repetitive tightening of the screws and fasteners of those airplanes. In addition, the AD will limit the applicability of the existing AD by removing certain airplanes. This amendment is prompted by the manufacturer's development of new fastener systems that will not vibrate and loosen. The actions specified by this AD are intended to prevent separation of loosened wing/body fairing panels from the airplane, which, if not corrected, could lead to structural damage to the horizontal or vertical stabilizer, and potential injury to persons on the ground.
AD 98-07-13 · published Apr 2, 1998, effective May 7, 1998
Boeing Model 767-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that requires a one-time inspection for worn or broken wire bundles in the ceiling above the main passenger door and repair, if necessary; and relocation of the wire bundles to prevent chafing. This amendment is prompted by a report indicating that the opening of the main passenger door caused the door liner and a ceiling panel to chafe and ultimately break wires installed in this area. The actions specified by this AD are intended to prevent these wires from becoming worn or breaking, which could lead to the failure of several systems, such as the fuel shutoff valves, and may contribute to the inability of the flight crew to stop the flow of fuel to the engines in the event of an engine fire.
AD 98-07-14 · published Apr 2, 1998, effective May 7, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that 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 98-07-15 · published Apr 2, 1998, effective May 7, 1998
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires an internal visual inspection to detect cracks of the skin and internal doublers above main entry door 1 at body station 460, and various follow-on actions. This amendment is prompted by reports indicating that multiple fatigue cracks were found in both internal skin doublers. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in reduced structural integrity of the fuselage and consequent rapid depressurization of the cabin.
AD 98-07-16 · published Apr 2, 1998, effective May 7, 1998
Boeing Model 737-300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires interchanging the location of the hydraulic fuse and the flow limiter of the standby hydraulic system of the leading edge. This amendment also requires replacing the existing hydraulic fuses in the standby hydraulic system with new fuses. This amendment is prompted by reports of a performance test of the hydraulic fuses, which revealed that the positioning of the flow limiter in the existing configuration, and excessive fusing volumes of some of the fuses in extreme cold environment, can adversely affect the operation of the fuse. The actions specified by this AD are intended to prevent such adversely affected operation of the fuse, which could result in the loss of all standby hydraulic system pressure and consequent severely reduced controllability of the airplane during certain flight phases.
AD 98-07-23 · published Apr 2, 1998, effective Apr 17, 1998
Airbus Model A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with procedures to prevent thrust loss during initial climb. This action also requires installing a new or modified electronic control unit on each engine, which, when accomplished, terminates the requirement for the AFM revision. 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 significant thrust loss during initial climb, which could result in an increased risk of collision with obstacles in the initial climb path of the airplane.
AD 98-07-24 · published Apr 2, 1998, effective Apr 17, 1998
Airbus Model A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires a rototest inspection for fatigue cracking of the vertical support beam at the upper first fastener row of the actuator attachment fitting of the center landing gear (CLG), and follow-on actions. 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 fatigue cracking in the vertical support beam that supports the CLG actuator attachment fitting, which could result in reduced structural integrity of the airplane.
AD 98-07-25 · published Apr 2, 1998, effective Apr 17, 1998
Aerospatiale Model ATR42-500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 series airplanes. This action requires a one-time inspection to measure the gap between the lower fairing of the rudder horn and the vertical stabilizer, and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interference between the rudder horn and the vertical stabilizer, which could cause the rudder to jam, and consequent reduced controllability of the airplane.
AD 98-07-17 · published Apr 6, 1998, effective May 29, 1998
Twin Commander Aircraft Corporation 500, 520, 560, 680, 681, 685, 690, 695, and 720 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 94-04- 17, which currently requires the following on Twin Commander Aircraft Corporation (Twin Commander) 500, 520, 560, 680, 681, 685, 690, 695, and 720 series airplanes: inspecting (one-time) the flap system for cables with broken wires or pulleys with worn cable clips, replacing any damaged parts, and replacing the master pulley and cable with new parts of improved design. This AD requires inspecting all flap system cable grooves for the correct width, inspecting all flap system pulleys for rubbing on the support brackets, inspecting all flap pulley cable assemblies for frayed wires, and reworking or replacing any parts with discrepancies. This AD results from several reports of worn and frayed flap system cables attributed to flap pulley grooves that are too narrow. The actions specified by this AD are intended to prevent failure of a flap system cable caused by fatigue, which could result in loss of control of the airplane.
AD 98-07-18 · published Apr 6, 1998, effective Apr 28, 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. This AD requires replacing certain propeller de-icing controllers with ones that are not susceptible to electromagnetic interference (EMI). 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 improper operation of the propeller de-icing controller caused by EMI, which could result in ice build-up on the propeller with possible airplane controllability problems.
AD 98-07-26 · published Apr 6, 1998, effective Apr 21, 1998
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a detailed visual inspection(s) for damage or chafing of certain electrical wire bundles and for clearance between the wire bundles and adjacent forward galley air chiller; and follow-on corrective actions. This amendment is prompted by a report indicating that damaged wires caused the tripping of electrical circuit breakers and the display of caution messages by the engine indication and crew alerting system. The actions specified in this AD are intended to prevent failure of essential electrical systems and a potential fire hazard for passengers and crewmembers, due to damage or chafing of the wire bundles that resulted in arcing between exposed conductors and burning of the adjacent electrical bundles.
AD 98-08-02 · published Apr 7, 1998, effective May 12, 1998
Airbus Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires repetitive replacement of the universal joints and steady bearings of the flap transmission system with new parts at regular intervals, or overhaul. This amendment is prompted by a report of a malfunction of a universal joint in the flap transmission system on one wing due to fatigue failure. The actions specified by this AD are intended to ensure replacement or overhaul of certain universal joints and bearings of the transmission system when they have reached their maximum life limit. Failure of universal joints and bearings could lead to an asymmetric condition of the flaps, which could adversely affect controllability of the airplane.
AD 98-08-01 · published Apr 9, 1998, effective May 14, 1998
Fokker Model F28 Mark 0070 and Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires a one-time visual inspection to detect heat damage of the fuselage skin and stubwing structure. This proposal also would require either repetitive leak tests of the seals of the bleed air system, or repair of any heat-damaged structure, as necessary; and replacement of corrujoint seals with new improved seals. 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 prevent the leakage of hot air from the corrujoint seals of the low- and high-pressure check valves located in the stubwings, which could result in heat damage to the fuselage skin and stubwing structure, and consequent reduced structural integrity of the airplane.
AD 98-08-04 · published Apr 9, 1998, effective May 26, 1998
AERMACCI S.p.A. Models S.208 and S.208A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all AERMACCI S.p.A. Models S.208 and S.208A airplanes. This AD requires inspecting the landing gear rod springs to assure they are made with a wire diameter of 4.5 millimeters (mm), and replacing any that have a wire diameter of 4.0 mm. 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 failure of the landing gear caused by an insufficient wire diameter of the rod springs, which could result in loss of control of the airplane during landing operations.
AD 98-08-05 · published Apr 9, 1998, effective May 26, 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 main landing gear (MLG) for interference between the MLG drag brace link and the MLG retraction actuator, and modifying this area if interference is found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent MLG failure caused by interference between the MLG retraction actuator and the MLG drag brace link, which could result in loss of control of the airplane during landing operations.
AD 98-08-07 · published Apr 9, 1998, effective Apr 28, 1998
Pilatus Aircraft Ltd. Model PC-7 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires replacing the rudder and elevator pivot arms with parts of improved design. This AD results from reports of cracks in the elevator and rudder trim tab pivot arms on the above- referenced airplanes. The actions specified by this AD are intended to prevent failure of the elevator and rudder caused by fatigue cracking of the pivot arms, which could result in reduced airplane controllability and possible loss of control of the airplane.
AD 98-08-10 · published Apr 9, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Saab Model SAAB 2000 series airplanes, that 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 98-08-06 · published Apr 10, 1998, effective May 26, 1998
AERMACCI S.p.A. S.205 Series and Models S.208 and S.208A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to AERMACCI S.p.A. S.205 series and Models S.208 and S.208A airplanes. This AD requires inspecting all flight control cables (elevator control, aileron control, rudder, flaps, nose gear steering, parking brake, safety belts, and autopilot systems) for cracks in the eye end, and replacing any control cable with any crack in the eye end. 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 loss of critical airplane functions because of cracked flight control cables, which could result in loss of control of the airplane if occurring during flight.
AD 98-08-08 · published Apr 10, 1998, effective Apr 27, 1998
Aerospatiale Model ATR42-500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 series airplanes. This action requires a one-time inspection to verify the installation of certain stringer clips at the junction of frame 34 and stringer 6, and installation of stringer clips, 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 fatigue cracking in the skin of the fuselage, which could result in loss of pressure inside the airplane.
AD 98-07-21 · published Apr 13, 1998, effective May 18, 1998
Lockheed Model 1329-23 and -25 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 1329-23 and -25 series airplanes, that requires replacement of a certain tailpipe V-band coupling with a new tailpipe V-band coupling. This amendment is prompted by reports indicating that the flight crew received a fire/overheat warning as a result of displacement of engine tailpipes, which allowed hot exhaust gases into the engine bypass duct. The actions specified by this AD are intended to prevent such displacement, which could result in escape of the hot exhaust gases from the engine tailpipe, and consequent damage to adjacent structure.
AD 98-08-15 · published Apr 13, 1998, effective Apr 28, 1998
Boeing Model 747-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, -200, and -300 series airplanes. This action requires repetitive detailed visual and/or borescope inspections to detect discrepancies of certain areas of the wing strut. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by reports that fatigue cracking was found in the vertical chords, midspar webs, and canted closure webs. The actions specified in this AD are intended to detect and correct fatigue cracking and stress corrosion of the wing strut, which could result in failure of the strut-to-wing interface, and consequent separation of the engine and strut from the airplane.
AD 98-08-16 · published Apr 14, 1998, effective May 19, 1998
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and 340B series airplanes, that requires a one-time inspection to detect discrepancies of the flight idle stop override mechanism, 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 prevent increased braking distance for landings that require the flight idle stop override, resulting from the combination of failure of the override mechanism and inability of the power levers to be moved below the flight idle position after touchdown.
AD 98-08-18 · published Apr 15, 1998, effective May 26, 1998
The New Piper Aircraft, Inc. Models PA- 31, PA-31-300, PA-31-325, PA-31-350, and PA-31P Airplanes
This amendment supersedes Airworthiness Directive (AD) 79-01- 04, which currently requires repetitively inspecting the elevator bungee spring for cracks or surface deformities on certain Piper Aircraft Corporation (known currently as The New Piper Aircraft, Inc.) Model PA-31-350 airplanes, and replacing any elevator bungee spring with cracks or surface deformities. This AD retains the repetitive inspection and replacement requirements from AD 79-01-04 on The New Piper Aircraft, Inc. (Piper) Model PA-31-350 airplanes until an elevator bungee spring of improved design is installed, and requires these repetitive inspection and replacement requirements on certain other Piper PA-31 and PA-31P series airplanes not affected by AD 79-01- 04. This AD also requires replacing the elevator bungee link with a link of improved design on all affected airplanes except for the Piper Model PA-31P airplanes, and repetitively replacing the elevator bungee spring on all affected airplanes. This AD results from reports of cracked elevator bungee springs on airplanes incorporating the older design elevator bungee spring that are not affected by AD 79-01-04, and by reports of cracked elevator bungee springs on airplanes that have improved design elevator bungee springs installed. The actions specified by this AD are intended to prevent failure of the elevator bungee spring, which could result in a reduction in elevator control and consequent loss of control of the airplane.
AD 98-08-23 · published Apr 16, 1998, effective May 1, 1998
Boeing Model 747 and 767 Series Airplanes Equipped With General Electric (GE) CF6-80C2 Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 and 767 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to prohibit the use of certain fuels; and either replacing the existing placard on the door of the fueling control panel with a new placard, or replacing all dribble flow fuel nozzles (DFFN's) with standard fuel nozzles, which terminates the requirements for a placard and AFM revision. This amendment continues these requirements and adds additional airplanes to the applicability. This amendment is prompted by a report of an engine flameout due to the use of JP-4 or Jet B fuel during certification testing on an engine with DFFN's installed. The actions specified in this AD are intended to prevent such engine flameouts and consequent engine shutdown.
AD 98-08-19 · published Apr 17, 1998, effective May 18, 1998
Twin Commander Aircraft Corporation 500, 600, and 700 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Twin Commander Aircraft Corporation (Twin Commander) 500, 600, and 700 series airplanes. This AD requires installing access holes in both wing leading edges and repetitively inspecting the forward attach brackets and straps for cracks. Reports of cracks in the wing to fuselage attachment brackets and straps, wing station (WS) 24, and fuselage frames prompted this action. The actions specified by this AD are intended to detect cracks at the wing to fuselage attach points, which, if not detected and corrected, could cause structural failure and loss of control of the airplane.
AD 98-08-21 · published Apr 17, 1998, effective Jun 3, 1998
SOCATA-Groupe AEROSPATIALE Models TB10 and TB200 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA-Groupe AEROSPATIALE (Socata) Models TB10 and TB200 airplanes. This AD requires inspecting the wing rear attachment fittings for cracks, replacing any cracked fitting, and incorporating wing rear attachment fitting reinforcement kits. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural failure of the wing rear attachment fittings caused by cracks in this area, which could result in the wing separating from the airplane if the airplane is operated with cracked wing rear attachment fittings over an extended period of time.
AD 98-08-22 · published Apr 17, 1998, effective May 31, 1998
Pilatus Aircraft Ltd. Model PC-7 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires inspecting the elevator and rudder attachment brackets for cracks and/or corrosion, and repairing or replacing any cracked or corrosion-damaged parts, as applicable. 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 failure of the elevator and rudder attachment brackets because of cracks or corrosion damage, which could result in the elevator and/or rudder separating from the airplane with consequent loss of airplane control.
AD 98-08-24 · published Apr 17, 1998, effective May 22, 1998
McDonnell Douglas Model DC-9-10, -20, - 30, -40, and -50 Series Airplanes, and C-9 (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the forward lower cargo doorjamb have been previously modified. This amendment also requires low frequency eddy current inspections to detect cracks of the fuselage skin and doubler at all corners of the forward lower cargo doorjamb, various follow-on repetitive inspections, and modification, if necessary. This amendment is prompted by fatigue cracks found in the fuselage skin and doubler at the corners of the forward lower cargo 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 98-08-25 · published Apr 20, 1998, effective May 18, 1998
Twin Commander Aircraft Corporation 500, 680, 690, and 695 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 96-12- 08 on certain Twin Commander Aircraft Corporation (Twin Commander) 500, 680, 690, and 695 series airplanes, which currently requires replacing the nose landing gear (NLG) drag link bolt with one that has been manufactured with the proper heat-treatment. This action will retain the requirements of AD 96-12-08, add an additional model and additional serial numbers to the applicability section of the AD, and require replacing bolt part number (P/N) ED10055 with bolt P/N 750076-1 on certain Models 690D and 695A airplanes. This action is prompted by a defective manufacture of a certain lot of drag link bolts used in the NLG. The actions specified by this AD are intended to prevent the NLG from collapsing caused by a failed drag link bolt, which could result in loss of control of the airplane during landing operations.
AD 98-08-26 · published Apr 20, 1998, effective May 29, 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. This AD requires installing aluminum bonding bushings over certain screws in certain fuel tank underwing access panels. Several reports from the field revealing fuel tank access panels insufficiently electrically bonded to the airframe prompted this action. The actions specified by this AD are intended to prevent electrical arcing in the fuel tanks and detonation of the fuel-air mixture, which can be created by poor electrical bonding of fuel tank underwing access panels, and could result in a fire on the airplane.
AD 98-08-27 · published Apr 20, 1998, effective May 31, 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 modifying the airplane's left-hand (LH) front side lower panel. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent interference between the side trim of the LH front side lower panel and the roll control compass on the LH wheel assembly, which could result in loss of directional control of the airplane.
AD 98-08-28 · published Apr 20, 1998, effective May 15, 1998
Avions Pierre Robin Model R3000/160 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin (Avions) Model R3000/160 airplanes. This action requires replacing the top bolts in the front wheel fork assembly and the top bolts attaching the front landing gear to the engine mount. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent collapse of the nose landing gear, which could result in loss of control of the airplane during taxi and landing operations.
AD 98-09-01 · published Apr 20, 1998, effective May 5, 1998
Gulfstream Model GV Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model GV series airplanes. This action requires inspections and functional tests of the elevator Hardover Prevention System (HOPS) to detect any miswiring of electrical connectors, correction of any discrepancy found, and eventual modification of the HOPS wiring. This amendment is prompted by reports of incorrect matching of electrical connectors to the hydraulic deactivation valves of the elevator HOPS. The actions specified in this AD are intended to prevent the incorrect operation of the elevator HOPS, which could result in loss of control of the airplane.
AD 98-08-09 · published Apr 23, 1998, effective Apr 28, 1998
Lockheed Model L-1011-385 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-08-09 that was sent previously to all known U.S. owners and operators of certain Lockheed Model L- 1011-385 series airplanes by individual notices. This AD requires revision of the Airplane Flight Manual (AFM) to prohibit operation of the fuel boost pumps when fuel quantities are below certain levels, and to add new maintenance procedures for operating the airplane with an inoperative fuel boost pump assembly or with an inoperative flight station fuel quantity indicating system. This AD also requires the installation of a placard on the engineer's fuel panel to advise the maintenance crew that operation of the fuel boost pumps when less than 1,200 pounds of fuel are in the corresponding wing fuel tank is prohibited. This action is prompted by reports of internal electrical failures in the fuel boost pump of the wing fuel tanks that could result in either electrical arcing or localized overheating. The actions specified by this AD are intended to prevent such electrical arcing or overheating, which could breech the protective housing of the fuel boost pump and expose it to fuel vapors and fumes, and consequent potential fire or explosion in the wing fuel tank.
AD 98-08-11 · published Apr 23, 1998, effective Apr 28, 1998
McDonnell Douglas Model MD-11 and MD- 11F Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-08-11 that was sent previously to all known U.S. owners and operators of certain McDonnell Douglas Model MD-11 and MD-11F series airplanes by individual notices. This AD requires opening the circuit breaker of the pneumatic sense line heater tape, installing an inoperative ring, and coiling and stowing the electrical wire to the circuit breaker of the pneumatic sense line heater tape. This AD also provides for an optional inspection, which, if accomplished, constitutes terminating action for deactivation of the pneumatic sense line heater tape. This action is prompted by a report indicating that, while an airplane was on the ground, fuel was found leaking from the fuel feed pipe of the number 2 engine due to inadequate clearance between the fuel feed pipe and the pneumatic sense line heater tape. The actions specified by this AD are intended to detect and correct such inadequate clearance, which could result in a hole in the fuel feed pipe caused by electrical arcing, and consequent fuel leakage and possible ignition of the fuel vapors.
AD 98-09-16 · published Apr 23, 1998, effective May 8, 1998
Aerospatiale Model ATR-42 and ATR-72 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Aerospatiale Model ATR-42 and ATR-72 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to add specific flightcrew instructions to be followed in the event of failure of one or both of the direct current (DC) generators. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the second of two DC generators after the failure of the first generator, which could lead to the loss of main battery power and result in the loss of all electrical power, except the emergency battery supply, during flight.
AD 98-09-03 · published Apr 24, 1998, effective May 29, 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 one-time, detailed visual inspection for discrepancies of the electrical bundles in the power generation compartment, 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 chafing and consequent damage to the electrical generation wires in the 101VU panel, which could result in a loss of electrical generation channels.
AD 98-09-04 · published Apr 24, 1998, effective May 29, 1998
Aerospatiale Model ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires a one-time high frequency eddy current inspection to detect cracking of the lower fuselage structure, and repair, if necessary. This amendment also requires modification of certain fastener holes in the lower fuselage 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 reduced structural integrity of the airplane due to fatigue cracking in the lower fuselage structure.
AD 98-09-05 · published Apr 24, 1998, effective May 29, 1998
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive inspections to detect corrosion of the brake hydraulic accumulators in the vicinity of the mounting straps; 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 corrosion of the brake hydraulic accumulators, which could lead to loss of hydraulic pressure and consequent loss of braking capability of the airplane.
AD 98-09-06 · published Apr 24, 1998, effective May 29, 1998
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires an inspection to determine the serviceability of the fire extinguisher of the forward lavatory waste bin, and corrective actions, if necessary. This amendment also requires installation of a placard adjacent to the fire extinguisher in the forward lavatory waste bin. 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 prevent leakage of the fire extinguishing agent, which could prevent proper distribution of the agent within the lavatory waste bin in the event of a fire.
AD 98-09-07 · published Apr 24, 1998, effective May 29, 1998
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a modification of the lapjoint below the chine line at certain fuselage stations. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking in the lapjoint below the chine line at certain fuselage stations, which could result in reduced structural integrity of the fuselage.
AD 98-09-08 · published Apr 24, 1998, effective May 22, 1998
Avions Pierre Robin Model R3000/160 Airplanes.
This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin (Avions) Model R3000/160 airplanes. This action requires repetitively inspecting the flap control shaft and the welds of the flap levers for cracks; replacing the cracked part, if cracks are found; and adjusting the flap travel, if no cracks are found. Reports of cracked flap control shafts found during routine maintenance prompted this action. The actions specified by this AD are intended to prevent cracks on the flap control shaft and around the welds of the flap levers, which, if not detected and corrected, could result in loss of airplane control during flight.
AD 98-09-10 · published Apr 24, 1998, effective Jun 7, 1998
EXTRA Flugzeugbau GmbH Models EA-300 and EA-300S Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300 and EA-300S airplanes. This AD requires inspecting the rudder control cables to assure that correctly swaged Nicopress<SUP></SUP> type sleeves are installed at each end of the cables, and replacing any cable assembly where correctly swaged Nicopress<SUP></SUP> type sleeves are not installed. 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 control cable from pulling through an incorrectly swaged sleeve, which could result in loss of rudder control with consequent loss of control of the airplane.
AD 98-09-17 · published Apr 24, 1998, effective May 11, 1998
Boeing Model 747-200F and -200C Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-200F and -200C series airplanes. This action requires repetitive inspections or a one-time inspection to detect cracking of certain areas of the upper deck floor beams; and corrective actions, if necessary. This amendment is prompted by reports indicating that fatigue cracks were found in the upper chord and web of upper deck floor beams. The actions specified in this AD are intended to prevent such fatigue cracking and the resultant failure of such floor beams. Failure of the floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent reduced controllability of the airplane; failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane.
AD 98-09-12 · published Apr 28, 1998, effective Jun 12, 1998
Raytheon Aircraft Company Model 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly known as Beech Aircraft Corporation Model 1900D airplanes). This AD requires inspecting and repairing the radio switching panel relay printed circuit board (PCB) and the nose avionics wire harnesses, and replacing the existing A017 component PCB with a new A017 component PCB that has internal overcurrent protection fuses. Several reported incidents of lost use of the pilot/co-pilot intercom system, VHF communication system, and public address system while in flight prompted this action. The actions specified by this AD are intended to prevent the loss of the pilot and co-pilot intercom, VHF communications, and passenger address system, which could result in loss of all communication during critical phases of flight.
AD 98-09-25 · published Apr 28, 1998, effective Jun 15, 1998
The New Piper Aircraft, Inc. Models PA- 31, PA-31-300, PA-31-325, and PA-31-350 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. This AD requires replacing the lower spar splice plate and reworking the lower spar caps. This AD results from numerous reports of fretting and cracking of the lower spar splice plates on Piper PA-31 series airplanes in Australia, and a report of one incident in the United States. The actions specified by this AD are intended to prevent failure of the lower spar splice plate caused by fretting and cracking, which could result in loss of control of the airplane.
AD 98-09-18 · published Apr 29, 1998, effective Jun 3, 1998
Airbus Industrie Model A320 and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A320 and A321 series airplanes, that requires replacement of two elevator aileron computers (ELAC) with ELAC's that contain new software. This amendment is prompted by a report indicating difficulty maintaining the intended flight path during landing in turbulent conditions. The actions specified by this AD are intended to prevent situations that could lead to reduced controllability of the airplane due to adverse airplane- pilot coupling characteristics.
AD 98-09-19 · published Apr 29, 1998, effective Jun 3, 1998
McDonnell Douglas Model DC-9, DC-9-80, and C-9 (Military) Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires modification of certain non-regulating shutoff valves on the engine starter, or installation of a pressure relief valve in the pneumatic supply line to the starter air shutoff valve on engines 1 and 2. This amendment is prompted by reports of uncontained failures of engine starters during flight and maintenance, which resulted from the application of excessive pressure on the engine starter that was associated with the installation of non-regulating shutoff valves on the starter. The actions specified by this AD are intended to prevent such uncontained failures of the engine starters, which could create a fire hazard in the engine nacelle.
AD 98-09-20 · published Apr 29, 1998, effective Jun 3, 1998
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; 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 fatigue cracks and corrosion around and under chafing plates of the wing root, which could result in reduced structural integrity of the airplane.
AD 98-09-21 · published Apr 29, 1998, effective Jun 3, 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 a one-time inspection for corrosion of electrical connectors in certain areas on the pressure bulkhead and rear baggage bay areas, and repair, if necessary; and installation of improved sealing. 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 accumulation of moisture inside the electrical connectors, which could result in a short circuit and consequent autopilot disconnect, or a latent failure of the stick pusher system.
AD 98-09-22 · published Apr 29, 1998, effective Jun 3, 1998
Aerospatiale Model ATR42-200, -300, and -320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, and -320 series airplanes, that requires an inspection to detect fatigue cracking of the windshield frame structure, and modification of the windshield frame structure. 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 prevent reduced structural integrity of the airplane resulting from fatigue cracking of the windshield frame structure.
AD 98-09-23 · published Apr 29, 1998, effective Jun 3, 1998
Lockheed Model L-1011 Series Airplanes Equipped With Rolls Royce Model RB211-22B Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model L-1011 series airplanes, that currently requires various modifications and corrective actions to prevent a potential fire hazard caused by heat damage to the flex fuel feed line from an undetected gearbox fire. In lieu of the various modifications and corrective actions, that AD also provides for an optional terminating action (i.e., installation of a vent air tube in the gear compartment and thickened gearbox housings) for another existing AD. For airplanes on which that optional terminating action has been accomplished, this amendment requires accomplishment of the various modifications and corrective actions. This amendment is prompted by a report indicating that, due to bearing failure, an in- flight fire occurred on an airplane on which a thickened gearbox housing was installed. The actions specified by this AD are intended to detect and correct bearing failure, which could lead to a fire in the gearbox.
AD 98-09-26 · published Apr 30, 1998, effective May 15, 1998
Dassault Model Falcon 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Falcon 2000 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with procedures for monitoring and properly setting the fuel booster pump pressure; and repetitive visual inspections of the fuel lines to detect fatigue cracking and fuel leakage. This action also requires a one-time inspection of the fuel lines to detect cracking, replacement of any discrepant part with a new part, and installation of new brackets between the pressure switch and the fuel pump of the numbers 1 and 2 engines, which constitutes terminating action for the repetitive inspections and the AFM revision. 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 fatigue cracking of the fuel line at the pressure switch pickoff point, which could result in fuel leakage and potential engine fire.
AD 97-24-17 · published Apr 1, 1998, effective Apr 16, 1998
Bell Helicopter Textron Canada Model 407 Helicopters
This document publishes in the Federal Register an amendment adopting priority letter airworthiness directive (AD) 97-24-17, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires inspections of components in the tail rotor drive system for scratches, cracks, fretting, corrosion, and proper torquing, lubrications of the oil cooler blower shaft hanger bearings and oil cooler hanger bearings (hanger bearings), and removal of corrosion inhibitive adhesive barrier tape (barrier tape) from the tail rotor gearbox and the tail rotor gearbox support assembly faying surfaces. This amendment is prompted by numerous reports of three problems, all of which are related to the tail rotor drive system. The actions specified by this AD are intended to: detect scratches, cracks, fretting, and corrosion in the disc pack couplings; prevent inadequate lubrication of the hanger bearings and oil cooler blower shaft; and prevent loss of mounting torque on the tail rotor gearbox. Failure of any of these components could result in loss of power to the tail rotor and subsequent loss of control of the helicopter.
AD 98-07-09 · published Apr 1, 1998, effective May 6, 1998
Bell Helicopter Textron, Inc. Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G- 3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J- 2A, and 47K helicopters, that requires installing a safety washer kit designed to preclude separation of the stabilizer bar damper link (damper link) if the damper link rod end bushing (bushing) loosens and exits the damper link rod end. This amendment is prompted by two reported incidents in which the bushings loosened and exited the damper link rod ends, allowing the damper link to slide over the retention bolt and separate from the stabilizer bar (in the first incident), and from the hydraulic damper (in the second incident). The actions specified by this AD are intended to prevent failure of the damper link assembly, which can result in degraded control response and subsequent loss of control of the helicopter.
AD 98-07-10 · published Apr 1, 1998, effective Apr 16, 1998
Agusta S.p.A. Model AB 412 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A. (Agusta) Model AB 412 helicopters. This action requires an inspection of the tail rotor blades for debond voids and replacement, if necessary. This amendment is prompted by the loss of a tail rotor blade tip on a tail rotor blade while the helicopter was in service. This condition, if not corrected, could result in increased vibration levels, damage to the tail rotor drive system or tail rotor assembly, and subsequent loss of control of the helicopter.
AD 98-07-11 · published Apr 1, 1998, effective Apr 16, 1998
GKN Westland Helicopters Limited WG-30 Series 100 and 100-60 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to GKN Westland Helicopters Limited (Westland) WG-30 series 100 and 100-60 helicopters. This action requires an initial visual inspection and replacement, if necessary, of all main rotor head tie-bars. Thereafter, this AD requires, at intervals not to exceed 220 hours time-in-service (TIS), replacing each main rotor head tie-bar (tie-bar) with an airworthy tie-bar. This amendment is prompted by an accident on a similar model military helicopter in which a tie-bar failed; it is suspected that the military helicopter involved in the accident exceeded the power-off transient rotor speed limitation. This condition, if not corrected, could result in failure of a tie-bar, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 98-07-19 · published Apr 2, 1998, effective May 7, 1998
McDonnell Douglas Helicopter Systems Model 369F and 369FF Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369F and 369FF helicopters, that requires removing the tail rotor control rod assembly (rod assembly) and replacing it with an airworthy rod assembly. This amendment is prompted by a failure of a rod assembly during a proof-load test conducted by the manufacturer. The actions specified by this AD are intended to prevent buckling of the rod assembly when subjected to ultimate jam loads, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 98-07-20 · published Apr 2, 1998, effective Apr 17, 1998
Eurocopter France Model AS 332C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, and L1 helicopters that have not been modified in accordance with Eurocopter France Modifications 332A07-41.569 and 332A07-66.150. This action requires revisions to the Limitations section of the Rotorcraft Flight Manual (RFM) to prohibit flight into meteorological conditions that may produce lightning for helicopters that are not equipped with lightning- resistant tail rotor blades. A terminating action is provided in the AD by the installation of tail rotor blades having a lightning-resistant system. This amendment is prompted by the forced ditching of a Model AS 332 helicopter after experiencing a lightning strike. The actions specified in this AD are intended to prevent damage to the tail rotor blades that could result in loss of a tail rotor blade and subsequent loss of control of the helicopter.
AD 98-04-12 · published Apr 10, 1998, effective Apr 27, 1998
Robinson Helicopter Company Model R44 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-04-12 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R44 helicopters by individual letters. This AD requires an initial and repetitive measurement of the lateral cyclic trim spring shaft (shaft) diameter and replacement of the shaft spring assembly (spring assembly) if the shaft diameter is excessively worn. Replacement of the spring assembly with a modified spring assembly is considered terminating action for this AD. This amendment is prompted by an incident in which a pilot felt binding in the cyclic control when attempting to move it to the left. A precautionary landing was made using only right-hand turns. Subsequent inspection revealed that a notch was worn in the shaft, which caused the shaft and spring to move from the lower mount and interfere with the lateral control. Inspection of a second RHC Model 44 helicopter revealed similar wear. Excessive wear can create a notch on the shaft, which can cause the spring assembly to move out of its lower mount. This condition, if not corrected, could lead to the shaft interfering with lateral cyclic control, which could result in loss of control of the helicopter.
AD 98-08-13 · published Apr 10, 1998, effective Apr 27, 1998
Eurocopter France Model SA 330F, G, and J, and AS 332C, L, L1, and L2 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA 330F, G, and J, and AS 332C, L, L1, and L2 helicopters. This action requires daily inspections of the root of each tail rotor head pitch change spider arm (spider arm) for cracks, and an inspection of the tail rotor head pitch change spider (spider) for cracks and fretting corrosion. A terminating action for the requirements of this AD is the installation of an airworthy modified spider, an airworthy replacement spider, or an airworthy repaired spider. This amendment is prompted by one in-service report of fatigue cracking on a Model AS 332 helicopter. This condition, if not corrected, could result in failure of the spider arm, loss of control of the tail rotor blade, and subsequent loss of control of the helicopter.
AD 98-08-14 · published Apr 10, 1998
Eurocopter France Model SA 365N, N1 and AS 365N2 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France (Eurocopter) Model SA-365N, N1 and AS- 365N2 helicopters that requires inspections of the main gearbox suspension diagonal cross-member (diagonal cross-member) for cracks, and removal of the diagonal cross-member and replacement with an airworthy diagonal cross-member if any crack is found. This amendment is prompted by several reports of the discovery of cracks in diagonal cross-members. The actions specified by this AD are intended to prevent failure of the diagonal cross-member which could cause the main gearbox to pivot, resulting in severe vibrations and a subsequent forced landing.
AD 98-04-40 · published Apr 17, 1998, effective May 4, 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) 98-04-40 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, for certain blades, inspecting each blade spar for cracks using a dye-penetrant inspection, and visually inspecting each blade cuff for cracks. If a crack is discovered in either a blade spar or cuff, removal and replacement of the blade with an airworthy blade is required prior to further flight. This amendment is prompted by an accident in which a Model SA.315B helicopter lost a main rotor blade (blade) just prior to take-off. The cause of the blade failure was determined to be fatigue cracks that originated from the outboard blade-to-cuff attachment bolt hole and progressed through the blade spar and cuff. This condition, if not corrected, could result in separation of a blade and subsequent loss of control of the helicopter.
AD 98-09-02 · published Apr 21, 1998, effective May 6, 1998
McDonnell Douglas Helicopter Systems Model 369 (YOH-6A), 369A (OH-6A), 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, and 500N Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369 (YOH-6A), 369A (OH-6A), 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS helicopters, that currently requires replacing overrunning clutch outer races (outer races) having certain heat treatment numbers. This amendment requires replacing all outer races with airworthy outer races, regardless of the heat treatment number, and is applicable to a particular model helicopter that was not included in the existing AD (Model 500N helicopters). This amendment is prompted by several reports of failed clutch races having heat treatment numbers other than the ones addressed in the earlier AD. The actions specified by this AD are intended to prevent failure of the overrunning clutch assembly outer race, which could result in loss of engine drive to the rotor system and a subsequent forced landing.
AD 98-07-07 · published Apr 14, 1998, effective Apr 29, 1998
Rolls-Royce, plc RB211 Series Turbofan Engines
This amendment supersedes existing airworthiness directive (AD) 96-13-04, applicable to Rolls-Royce, plc RB211 series turbofan engines, that currently requires removing and replacing a rigid low pressure (LP) fuel system tube assembly with a tube assembly incorporating flexible sections and revised clip points in order to preclude cracking and subsequent fuel leakage. This amendment requires replacing one of the flexible fuel tube assemblies installed in accordance with AD 96-13-04 with an alternate flexible fuel tube assembly that is not prone to rupture. This AD also requires immediate replacement of any rigid fuel tubes not previously removed from service as required by AD 96-13-04. The amendment is prompted by reports of fuel line rupture on one of the flexible fuel tube assemblies installed in accordance with AD 96-13-04. The actions specified by this AD are intended to prevent high volume fuel leaks and reported fuel collection inside the engine nacelle, which could result in an uncontrolled engine fire.
AD 98-08-17 · published Apr 14, 1998, effective May 19, 1998
Turbo-Propeller Powered General Dynamics (Convair) Model 240, 340, and 440 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to various turbo-propeller powered General Dynamics (Convair) Model 240, 340, and 440 series airplanes, that 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 98-08-20 · published Apr 17, 1998, effective Jun 2, 1998
AlliedSignal Aerospace Bendix/King Model KSA 470 Autopilot Servo Actuators, Part Numbers 065-0076-10 Through 065-0076-15
This amendment adopts a new airworthiness directive (AD) that applies to certain AlliedSignal Aerospace Bendix/King Model KSA 470 autopilot servo actuators, part numbers 065-0076-10 through 065-0076- 15, that are installed on aircraft. This AD requires replacing the autopilot servo actuator with a modified actuator. This is the result of two reports of the affected autopilot servo actuators containing loose roll pins within the servo housing. Loose roll pins could fall out, become lodged in the output shaft clutch mechanism, and prevent this mechanism from disengaging. The actions specified by this AD are intended to prevent such an occurrence, which could result in increased effort by the pilot to control the aircraft and possible loss of control of the affected flight control axis.
AD 97-08-02 R1 · published Apr 7, 1998, effective Apr 17, 1998
Schempp-Hirth K.G. Models Nimbus-2B, Mini-Nimbus B, Discus a, and Discus b Sailplanes
This document clarifies information in an existing airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schempp-Hirth) Models Standard-Cirrus, Nimbus-2, Nimbus-2B, Mini- Nimbus HS-7, Mini-Nimbus B, Discus a, and Discus b sailplanes. That AD currently requires accomplishing a load test of the elevator control system, and replacing the elevator vertical actuating tube either immediately or at a certain time period depending on the results of the load test. The actions specified in that AD are intended to prevent corrosion in the elevator caused by water entering the elevator control rod, which could result in elevator failure and consequent loss of control of the sailplane. The Schempp-Hirth Models Nimbus 2, Mini- Nimbus HS-7, and Standard Cirrus sailplanes are not equipped with elevator control systems, and should not be affected by the current AD. This action eliminates all reference to the Shempp-Hirth Models Nimbus 2, Mini-Nimbus HS-7, and Standard Cirrus sailplanes in the current AD.
AD 98-08-03 · published Apr 9, 1998, effective May 26, 1998
Stemme GmbH & Co. KG Models S10 and S10-V Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10 and S10-V sailplanes. This AD requires replacing the horizontal stabilizer rear fittings with parts 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 structural failure of the horizontal stabilizer caused by cracked rear fittings, which could result in loss of sailplane controllability.
AD 98-08-29 · published Apr 20, 1998, effective May 18, 1998
Alexander Schleicher Segelflugzeugbau Model ASK 21 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASK 21 sailplanes. This AD requires removing certain pages from the sailplane flight manual and replacing these pages with new pages having different information regarding spin and stall recovery. This action 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 operators from using inaccurate stall and spin recovery information provided in the sailplane flight manual (SFM), which could result in the inability to recover from a spin or stall during flight.
AD 98-09-09 · published Apr 24, 1998, effective Jun 1, 1998
Alexander Schleicher GmbH Segelflugzeugbau Model ASH-26E Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher GmbH Segelflugzeugbau (Alexander Schleicher) Model ASH-26E sailplanes. This AD requires replacing the internal cooling air fan with a fan that incorporates a certain modification. 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 internal cooling system air fan caused by the impeller slipping, which could result in loss of compression and power and possible engine failure.
AD 98-09-13 · published Apr 28, 1998, effective Jun 14, 1998
Alexander Schleicher Segelflugzeugbau Model ASK 21 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASK 21 sailplanes. This AD requires inspecting the S- shaped rudder pedal tube for displacement, and correcting any displacement of the plastic tube. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent rudder control jamming, which could result in loss of directional control of the sailplane.
AD 98-09-14 · published Apr 28, 1998, effective Jun 14, 1998
Diamond Aircraft Industries Models HK 36 TTS and HK 36 TTC Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Diamond Aircraft Industries (Diamond) Models HK 36 TTS and HK 36 TTC sailplanes. This AD requires inspecting the engine turbocharger oil-pressure line for the correct banjo bolt. The correct banjo bolt will have a valve seat, instead of a built-in orifice. If the banjo bolt does not have a valve seat, then this action will require replacing the banjo bolt with one that has a valve seat, and repairing or replacing the turbocharger. 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 possible loss of engine power, which could result in possible loss of control of the sailplane.
AD 98-09-24 · published Apr 30, 1998, effective Jun 15, 1998
Diamond Aircraft Industries Models H-36 ``Dimona'' and HK 36 R ``Super Dimona'' Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Diamond Aircraft Industries (Diamond) Models H-36 ``Dimona'' and HK 36 R ``Super Dimona'' sailplanes. This AD requires: inspecting the elevator rib area for damage on certain Models H-36 ``Dimona'' and HK 36 R ``Super Dimona'' sailplanes, and either immediately or eventually replacing the elevator ribs depending on the results of the inspection; replacing the M6 screws that attach the wheel axle to steel support with M8 screws on certain Model HK 36 R ``Super Dimona'' sailplanes; and inspecting the shoulder harness fittings for improper bonding on certain Diamond Model H-36 ``Dimona'' sailplanes, and repairing any harness with an improper bond. 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 failure of either the shoulder harness fittings, elevator rib, or the wheel axle to steel support attachment, which could result in passenger injury caused by an inadequate restraint system; reduced sailplane controllability caused by structural damage to the elevator; and/or reduced sailplane controllability during takeoff, landing, and ground operations caused by the installation of incorrect wheel axle screws.
