35 Airworthiness Directives: 27 airplane, 4 rotorcraft, 1 engine, 3 glider.
AD 85-02-05 R1 · published Nov 3, 1997, effective Nov 21, 1997
The New Piper Aircraft, Inc. PA-20, PA- 22, PA-23, PA-24, PA-25, PA-30, PA-31P, PA-36, PA-39, and PA-44 Series Airplanes
This document clarifies information in Airworthiness Directive (AD) 85-02-05, which applies to all The New Piper Aircraft, Inc. (Piper) PA-20, PA-22, PA-23, PA-24, PA-25, PA-30, PA-31P, PA-36, PA-39, and PA-44 series airplanes. AD 85-02-05 currently requires installing on the pilot's instrument panel a Piper part number (P/N) 81090-02 placard, which provides information for operation of the parking brake. Piper has superseded that placard with a P/N 683-107 placard, and operators in need of a new placard can only obtain the P/N 683-107 placard. In this scenario, the owners/operators of the affected airplanes could not comply with AD 85-02-05 as currently written. The P/N 683-107 placard contains the same wording as the P/N 81090-02 placard. The actions specified in that AD are intended to prevent airplane controllability problems while involved in ground operation because of improper brake operations. This document maintains the placard requirement of AD 85-02-05, and adds the installation of the P/ N 683-107 placard as an option of compliance.
AD 97-23-01 · published Nov 3, 1997, effective Dec 1, 1997
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 93-15- 02 R2, which currently requires the following on Fairchild Aircraft, Inc. (Fairchild Aircraft) SA226 and SA227 series airplanes that are equipped with a certain Simmonds-Precision pitch trim actuator: repetitively measuring the freeplay of the pitch trim actuator and repetitively inspecting the actuator for rod slippage; immediately replacing any actuator if certain freeplay limitations are exceeded or rod slippage is evident; and, eventually replacing the actuator regardless of the inspection results. This action retains the repetitive inspections and replacement requirements, adds the repetitive inspections after the installation of certain Barber-Coleman pitch time actuators, and removes the terminating action. This action is the result of failure of the no-backs on a Barber-Colman pitch time actuator installed on a Fairchild Aircraft SA227 series airplane. The actions specified by this AD are intended to prevent failure of the pitch trim actuator, which could cause loss of control of the airplane.
AD 97-23-02 · published Nov 4, 1997, effective Nov 19, 1997
Boeing Model 727-100 Series Airplanes Modified in Accordance With Supplemental Type Certificate (STC) SA8472SW
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 727-100 series airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to prohibit stabilized operation between 60 and 75 percent N1 speed during ground operations in reverse or forward thrust. This amendment is prompted by a report that, during preparation for takeoff, a transport category airplane equipped with Rolls-Royce Tay 650-15 engines sustained an engine fan blade failure, followed by an engine fire. The actions specified in this AD are intended to prevent uncontained failure of engine fan blades due to high cycle fatigue cracking, which could result in loss of thrust from the affected engine and secondary damage to the airplane and/or fire.
AD 97-23-03 · published Nov 4, 1997, effective Nov 19, 1997
British Aerospace (Jetstream) Model HS 748 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model HS 748 series airplanes. This action requires a one-time visual inspection of the retraction jack mounting brackets in the nose landing gear bay to determine the type of attachment bolts installed on the bracket bearing caps, and replacement of any incorrect bolt with a serviceable bolt of the correct type. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the bearing cap attachment bolts, which could result in detachment of the bearing caps and consequent collapse of the nose landing gear on landing.
AD 97-23-04 · published Nov 6, 1997, effective Dec 1, 1997
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires replacing the fuel tank vent valves with modified fuel tank vent valves. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the fuel tank inward vent valve from freezing, which, if followed by a cold soak at altitude, could result in wing airfoil distortion and structural damage with consequent degradation of the airplane's handling qualities.
AD 97-23-05 · published Nov 7, 1997, effective Dec 1, 1997
Avions Pierre Robin Model R3000 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R3000 airplanes. This AD requires replacing the attachment bolt between the pitch control cables and control column lever with a bolt of improved design. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the pitch control cables on the control column from becoming jammed due to failure of the attachment bolt, which could result in a reduction in the directional controllability of the airplane.
AD 97-23-09 · published Nov 10, 1997, effective Dec 22, 1997
de Havilland DHC-6 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 78-26- 02, which currently requires repetitively inspecting the fuselage side frame flanges at Fuselage Station (FS) 218.125 and FS 219.525 for cracks on certain de Havilland DHC-6 series airplanes, and repairing or replacing any cracked part. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This AD requires modifying the fuselage side frames at the referenced FS areas as terminating action for the repetitive inspections that are currently required by AD 78-26-02. The actions specified in this AD are intended to prevent failure of the fuselage because of cracks in the fuselage side frames, which, if not detected and corrected, could result in loss of control of the airplane.
AD 97-23-10 · published Nov 12, 1997, effective Dec 17, 1997
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires modification of the cable tension regulator on both the left and right elevators by installing certain parts on the lever arm of the regulator. This amendment is prompted by a report indicating that design testing and analysis have shown applied loads could cause the regulator's lever arm to break. The actions specified by this AD are intended to prevent failure of the regulator, and consequent reduced controllability of the airplane.
AD 97-23-11 · published Nov 12, 1997, effective Dec 17, 1997
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 modifying the main landing gear (MLG) bay areas by installing additional slush protection covers in those areas. This amendment is prompted by the identification of a problem during flight test analysis, which indicated that slush can accumulate in the MLG bay areas. The actions specified by this AD are intended to prevent the accumulation of slush in the MLG bay areas, which could freeze and interfere with the landing gear or render it inoperative.
AD 97-23-12 · published Nov 12, 1997, effective Dec 17, 1997
Fokker Model F28 Mark 0100 and 0070 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 and 0070 series airplanes, that requires replacement of the fusible pin in the upper torque link of the main landing gear with an improved pin. 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 and potential collapse of the main landing gear.
AD 97-23-13 · published Nov 12, 1997, effective Dec 17, 1997
Airbus Model A320 and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes, that requires a one-time inspection for discrepancies of the release cable of the forward and rear passenger doors, and replacement of any discrepant release cable with a new release cable. 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 failure of the passenger door to open and consequent inability of the slide/slide raft to deploy, which could delay or impede passengers when exiting the airplane during an emergency.
AD 97-21-16 · published Nov 13, 1997, effective Nov 18, 1997
Dassault Model Mystere-Falcon 50 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 97-21-16 that was sent previously to all known U.S. owners and operators of Dassault Model Mystere-Falcon series airplanes by individual notices. This AD requires a revision to the Limitations section of the FAA-approved Airplane Flight Manual (AFM) to include procedures to use certain values to correctly gauge the minimum allowable N1 speed of the operative engines during operation in icing conditions. This action is prompted by a report indicating that erroneous minimum anti-icing N1 thrust setting indications were displayed on the Engine Indication Electronic Display (EIED). The actions specified by this AD are intended to prevent flightcrew use of erroneous N1 thrust setting information displayed on the EIED, which could result in in-flight shutdown of engine(s).
AD 97-23-08 · published Nov 13, 1997, effective Dec 5, 1997
Avions Pierre Robin Model R3000 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R3000 airplanes that are equipped with yaw damper Modification No. 013. This AD requires inspecting the bridle cable ends for correct installation in the grooved screw, inspecting for correct cable winding on the capstan and correct cable tension, and correcting any discrepancies found. This AD also requires installing lockwire to the tension adjustment screw. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the rudder control from becoming jammed because of the yaw damper control cables slipping out of the groove on the tension adjustment screw, which could result in a reduction in the directional controllability of the airplane.
AD 97-23-14 · published Nov 13, 1997, effective Dec 18, 1997
Fairchild Model FH-227 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fairchild Model FH-227 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning of the power levers below the flight idle stop during flight, and to add a statement of the consequences of such positioning of the power levers. 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 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 when the airplane is in flight.
AD 97-23-15 · published Nov 13, 1997, effective Dec 18, 1997
Fairchild Model F-27 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fairchild Model F-27 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning 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 propeller ground 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 97-23-16 · published Nov 17, 1997, effective Dec 22, 1997
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires replacement of certain overhead electronics units (OEU) of the passenger address and entertainment communication systems with modified OEU's. This amendment is prompted by reports of smoke coming from the overhead panels near the passenger reading lights, which was caused by overheating of the transformers located in the OEU's. The actions specified by this AD are intended to prevent overheating of the transformers, which potentially could cause a fire in the transformer assembly and/or electronic components located in the OEU and could cause smoke to enter the passenger cabin.
AD 97-24-01 · published Nov 18, 1997, effective Dec 3, 1997
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires repetitive inspections to detect migration or damage of the bushings of the main landing gear (MLG) trailing arm, and replacement of any damaged or displaced bushing. This amendment is prompted by reports indicating that damagedor displaced bushings have been found on several MLG trailing arms of Dornier Model 328-100 series airplanes. The actions specified in this AD are intended to prevent failure of the bushings of the MLG trailing arm, which could result in collapse of the MLG during landing.
AD 97-24-02 · published Nov 18, 1997, effective Dec 3, 1997
Bombardier Model CL-600-1A11, -2A12, and -2B16 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11, -2A12, and -2B16 series airplanes. This action requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, 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 detect and correct cracking in the pressure bulkhead at frame station (FS) 409.00, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
AD 97-23-17 · published Nov 20, 1997, effective Dec 29, 1997
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) 90, 100, 200, and 300 series airplanes. This action requires inspecting gray, blue, or clear Ethylene Vinyl Acetate (EVA) tubing near the co-pilot's foot warmer for collapse or deformity. If the tubing is collapsed or deformed, this action requires replacing and re-routing the tubing. This EVA tubing is used on the pneumatic de-ice indicator lines and the pressurization control system pneumatic lines that provide vacuum to the outflow safety valves that depressurize the airplane. This action is the result of several reports of collapsed EVA tubing. The actions specified by this AD are intended to prevent a loss of vacuum to depressurize the airplane cabin, which could result in personal injury to the door operator; and to prevent malfunction of the de-ice indicator system, which could cause the pilot to immediately exit icing conditions.
AD 97-24-03 · published Nov 20, 1997, effective Dec 26, 1997
Dassault Model Falcon 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 series airplanes, that requires a revision to the Limitations section of the FAA-approved Airplane Flight Manual (AFM) to limit the allowed loads in the baggage compartment aft of the center baggage net. This AD also requires replacement of the center baggage net in the baggage compartment with a net having reinforced straps, which terminates the requirement for the AFM revision. This amendment is prompted by a report indicating that the center baggage net cannot sustain design loads in the event of an accident. The actions specified by this AD are intended to prevent injury to passengers, as a result of inadequate breaking strength of the baggage net, in the event of an accident.
AD 97-24-05 · published Nov 24, 1997, effective Jan 6, 1998
Aerospace Technologies of Australia Pty Ltd. (Formerly Government Aircraft Factory) Models N22B, N22S, and N24A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Aerospace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N22S, and N24A airplanes. This AD requires repetitively inspecting the aft wing break connectors for arcing damage, deposits between contacts, and looseness of contacts; and removing deposits between contacts, tightening any loose contacts, and replacing any aft wing break connectors with arcing damage. This AD results from several reports of uncommanded flap extensions and displays of incorrect stall warning indications on the affected airplanes. The actions specified by this AD are intended to prevent contamination in the aft wing break connectors, which could result in uncommanded flap extensions and incorrect stall warning indications with consequent loss of airplane control.
AD 97-24-07 · published Nov 24, 1997, effective Dec 31, 1997
Jetstream Aircraft Limited Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes that have kit JK 2496 and modification JM 7537 installed. This action requires installing magnetic latching relays on the ignition system because of the auto-ignition system becoming disabled when switching from ground power to the airplane's internal power. 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 loss of the airplane's internal power connection to the auto-ignition system, which could cause loss of engine power and possible loss of control of the airplane.
AD 97-24-11 · published Nov 28, 1997, effective Jan 2, 1998
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires repetitive inspections of certain flanges and finger strips at rib 5.0 of the vertical stabilizer to detect fatigue cracking, and repairs, if necessary. This amendment also requires modifications that would strengthen the torsion box at rib 5.0 and prevent fatigue cracking; one of these modifications constitutes terminating action for the repetitive inspections. This amendment is prompted by reports indicating that, during full-scale fatigue testing, cracking has been found on the vertical stabilizer of the test article. The actions specified by this AD are intended to detect and prevent fatigue cracking in the subject area, which, if not corrected, could reduce the structural integrity of the vertical stabilizer.
AD 97-24-12 · published Nov 28, 1997, effective Jan 2, 1998
British Aerospace Model BAC 1-11 200 and 400 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires a one-time inspection to determine the tension of the control cables of the thrust reversers, and to detect breakage, damage, wear, or signs of corrosion; and corrective actions, if necessary. This amendment requires that the inspections be repeated at certain intervals. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the control cables, which may lead to the inability of the thrust reverser to deploy and/or an uncommanded deployment of the thrust reverser while the airplane is in flight.
AD 97-24-13 · published Nov 28, 1997, effective Jan 2, 1998
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires a detailed visual inspection of the flap drive torque tubes in the wing root area to detect inadequate clearance between the torque tubes and surrounding structure or scoring damage to the tubes; and follow-on repetitive inspections or corrective action, if necessary. Accomplishment of certain replacements and modifications would constitute terminating action for the repetitive inspections. This amendment is prompted by reports of inadequate clearance between flap drive torque tubes and surrounding structures, and possible scoring damage to the tubes. The actions specified by this AD are intended to prevent failure of the torque tubes, which could result in an asymmetric flap condition and reduced controllability of the airplane.
AD 97-24-14 · published Nov 28, 1997, effective Jan 2, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires inspection of the two-way check valve on the engine fire extinguishing system for discrepancies, and corrective action, if necessary. This amendment is prompted by issuance of mandatory continued airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent discrepancies of the check valve, which could result in improper functioning of the engine fire extinguishing system.
AD 97-24-16 · published Nov 28, 1997, effective Jan 2, 1998
Fokker Model F28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0070 and 0100 series airplanes, that requires a one-time operational test of a certain pitot heating system, repair or replacement of failed elements, and repair or replacement of the pitot heating system with a new improved system. This amendment also requires installation of new power supply wiring with increased gauge thickness, and a circuit breaker with an increased amperage rating. 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 icing of the No. 1 pitot tube, which could result in failure of the No. 1 Air Data Computer, or output of erroneous airspeed data to all on-side subsidiary systems, including the Automatic Flight Control and Augmentation System.
AD 97-23-06 · published Nov 5, 1997, effective Dec 10, 1997
Schweizer Aircraft Corporation Model 269A, A-1, B, and C, and TH-55A Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Schweizer Aircraft Corporation Model 269A, A-1, B, and C, and TH-55A helicopters, with a certain main rotor transmission ring gear (ring gear) installed, that requires inspections of the ring gear teeth for surface deterioration which includes pitting, excessive wearing, cracking or corrosion, and replacement of the ring gear if such ring gear teeth surface deterioration is found; and also requires creating a main rotor transmission component log card (log card), if none is available, and making a notation on the log card if a ring gear is changed. This amendment is prompted by reports of failures of the ring gear due to single tooth distress as a result of improper gear tooth spacing during the manufacturing of the ring gear. The actions specified by this AD are intended to prevent failure of the ring gear, loss of drive to the main rotor gearbox, and a subsequent forced landing.
AD 97-23-07 · published Nov 5, 1997
Eurocopter Deutschland GmbH Model MBB- BK 117 A-1, A-3, A-4, B-1, B-2 and C-1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (Eurocopter) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, that establishes a new retirement life for the clutch and requires an entry into the Accessory Replacement Record indicating the new life limit. This amendment is prompted by a recalculation of life limitations by the part manufacturer, Warner Electric. The clutch manufacturer used the airframe load spectrum to establish the new life limit of 3,600 hours time-in-service (TIS). The actions specified by this AD are intended to prevent failure of the clutch, loss of power to the main rotor and a subsequent forced landing of the helicopter.
AD 97-12-02 · published Nov 17, 1997, effective Dec 2, 1997
McDonnell Douglas Helicopter Systems MD900 Helicopters
This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD900 helicopters, which prohibits flight or ground operations of helicopters with a certain adjustable collective drive link assembly (link assembly) installed. This amendment requires installation of a redesigned airworthy link assembly after which further operations are permitted. This amendment is prompted by recent incidents in which the link assembly failed during flight. The actions specified by this AD are intended to prevent failure of the link assembly, which could result in loss of control of the helicopter.
AD 97-24-04 · published Nov 21, 1997, effective Dec 8, 1997
Eurocopter France (Eurocopter) Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C helicopters. This action requires a visual inspection of the main rotor blade reinforcement strips for debonding between the reinforcement strips of the blade; and a visual inspection of the main rotor blade (blade) skin for cracks or corrosion, and replacement of the blade with an airworthy blade if certain debonding or a crack or corrosion is found. This amendment is prompted by an accident in which a blade separated in flight. The actions specified in this AD are intended to detect debonding, cracks, or corrosion in the affected blades and to prevent failure of a blade and subsequent loss of control of the helicopter.
AD 97-21-09 · published Nov 18, 1997, effective Dec 3, 1997
Allison Engine Company Model 250-C47B Turboshaft Engines
This amendment supersedes existing airworthiness directive (AD) 96-24-09, applicable to Allison Engine Company Model 250-C47B turboshaft engines, that currently requires replacing the engine main electrical harness assembly with an improved assembly, disabling the overspeed solenoid, inspecting the engine control unit (ECU) internal PW10 voltage to determine electrical noise characteristics, and replacing units not considered serviceable. In addition, the existing AD requires adding a placard to the helicopter instrument panel notifying the pilot that the overspeed protection system is disabled and removes a placard which was required by priority letter AD 96-21- 12; revises the Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 407 Rotorcraft Flight Manual (RFM); and requires maintenance actions to clear the ECU of faults prior to each flight. This amendment continues to require replacing the engine main electrical harness assembly with an improved assembly, but adds the requirements to install a new hydromechanical unit (HMU) and ECU, removing the placard notifying the pilot that the overspeed protection system is disabled, and revises the BHTC Model 407 RFM. This amendment is prompted by the development of overspeed protection system modifications to reactivate the overspeed solenoid in conjunction with raising the power turbine overspeed trip point and revising the overspeed system to default to a minimum fuel flow in the event of its activation. The actions specified by this AD are intended to prevent uncommanded inflight engine shutdowns, which can result in autorotation, forced landing, and possible loss of the helicopter.
AD 97-24-08 · published Nov 26, 1997, effective Jan 5, 1998
Burkhart Grob, Luft-und Raumfahrt, GmbH. Model G102 Astir CS Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to Burkhart Grob, Luft-und Raumfahrt, GmbH. (Grob) Model G102 Astir CS sailplanes. This action requires replacing the elevator control lever with an improved elevator control lever. The discovery of cracks in the elevator control lever during a routine inspection of a Grob Model G102 Astir CS sailplane prompted this action. 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 elevator control lever, which could result in loss of control of the sailplane.
AD 97-24-09 · published Nov 26, 1997, effective Jan 5, 1998
Burkhart Grob, Luft-und Raumfahrt, Model G 103 C Twin III SL Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to Burkhart Grob, Luft-und Raumfahrt (Grob), Model G 103 C Twin III SL sailplanes. This action requires repetitively inspecting the propeller bearing and upper pulley wheel for increased play and, if increased play is found, modifying the propeller bearing and pulley wheel with a part 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 loss of the sailplane engine propeller and possible loss of the sailplane.
AD 97-24-10 · published Nov 26, 1997, effective Dec 29, 1997
Burkhardt Grob Luft-und Raumfahrt, GmbH. Model G 103 Twin Astir Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to Burkhardt Grob Luft-und Raumfahrt, GmbH. (Grob) Model G 103 Twin Astir sailplanes. This action requires replacing the airbrake over-center lever and installing new inspection holes. The AD is the result of cracked airbrake over-center levers found during routine inspections. The actions specified by this AD are intended to prevent an asymmetrical airbrake deployment, which could result in an uncontrollable roll and possible loss of control of the sailplane.
