39 Airworthiness Directives: 30 airplane, 4 rotorcraft, 4 engine, 1 propeller.
AD 97-20-14 · published Oct 2, 1997, effective Oct 17, 1997
Mitsubishi Heavy Industries, Ltd., MU- 2B Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. This AD requires incorporating information into the Limitations Section of the Airplane Flight Manual (AFM) that would require pilot training before flight into known or forecast icing conditions after a certain date. This AD results from the Federal Aviation Administration's analysis that the current training level of the pilots-in-command (PIC) of the MU-2B series airplanes makes it difficult for pilots to recognize adverse operating conditions and operate safely while flying in icing conditions. Similar training to that required in this AD for pilots of other high performance airplanes has shown a lower accident rate over time after the training than before. The actions specified by this AD are intended to decrease the chance of icing-related incidents or accidents of the MU-2B series airplanes due to pilot error.
AD 97-18-06 · published Oct 8, 1997, effective Nov 12, 1997
Boeing Model 737 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that requires revising the FAA-approved maintenance program to prohibit the use of pressure washing within the wheel well or on the landing gear and to prohibit the use of pumps and/or nozzles for washing wheel wells or the landing gear; or incorporation of a certain Temporary Revision to the Boeing Airplane Maintenance Manual into the FAA-approved maintenance program. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent corrosion of certain equipment due to the use of inappropriate pressure washing techniques. Corrosion of bearings, cables, electrical connectors, or other equipment in the main wheel well, if not detected and corrected in a timely manner, could result in reduced controllability of the airplane.
AD 97-21-03 · published Oct 15, 1997, effective Nov 19, 1997
Raytheon Model BAe 125-800A Series Airplanes and Hawker 800 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe 125-800A series airplanes and Hawker 800 series airplanes, that requires a detailed visual inspection of the fuel feed hose assemblies of the auxiliary power unit (APU) to detect overheating, degradation, proper routing, and adequate clearance; and the correction of any discrepancies found. This amendment also requires modification of the fuel feed hose of the APU. This amendment is prompted by reports of heat damage to the fuel feed hose assembly of the APU due to contact between the hose assembly and hot surfaces. The actions specified by this AD are intended to prevent heat damage of the fuel feed hose, which could lead to a possible fire/ smoke hazard when failure of the hose assembly occurs and consequent fuel mist or spray is emitted into the rear equipment bay.
AD 97-21-10 · published Oct 17, 1997, effective Nov 3, 1997
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual to increase monitoring of the flight path of the airplane to detect certain software anomalies of the flight management guidance system (FMGS), and take appropriate corrective actions. 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 ensure that the flightcrew detects and corrects an unintended flight path if certain software anomalies of the FMGS occur, which could result in an increased risk of collision with terrain or other airplanes.
AD 97-21-11 · published Oct 17, 1997, effective Nov 3, 1997
Short Brothers Model SD3-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Short Brothers Model SD3-30 series airplanes. This action requires a one-time inspection to measure the depth of the skin flutes of the skin panels of the rudder and elevators, and repair, if necessary. This amendment is prompted by reports indicating that, due to a manufacturing process error, the depth of certain skin flutes of the rudder and elevators is less than the design specification. The actions specified in this AD are intended to prevent structural damage and/or loss of the rudder or elevators if the airplane is operated under ultimate load conditions, which could result in reduced controllability of the airplane.
AD 97-21-04 · published Oct 20, 1997, effective Nov 24, 1997
Airbus Model A310 and A300-600 Series Airplanes Equipped With Pratt & Whitney Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires flow checks of the hydraulic pump drain system to ensure that the system is not clogged, and correction of any discrepancy. Additionally, this amendment requires replacement of the existing seal of the accessory gearbox with a new, improved seal assembly; this replacement terminates the requirement for repetitive flow checks. This amendment is prompted by reports indicating that hydraulic fluid had contaminated the engine oil system as a result of failure of the seal of the hydraulic pump shaft. The actions specified by this AD are intended to prevent clogging of the hydraulic pump drain system, which could cause failure of the seal of the hydraulic pump shaft and subsequent contamination of the engine accessory gearbox oil; this condition could result in an in-flight engine shutdown.
AD 97-21-05 · published Oct 20, 1997, effective Nov 24, 1997
Raytheon Model DH.125-400A; BH.125-400A and -600A; HS.125-600A and -700A; BAe 125-800A Series Airplanes; and Hawker 800 and Hawker 800 XP Series Airplanes Including Military Variants
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model DH.125-400A; BH.125-400A and - 600A; HS.125-600A and -700A; BAe 125-800A series airplanes; and Hawker 800 and Hawker 800 XP series airplanes (including military variants C29A, U125, U125A). This amendment requires a one-time inspection to determine if certain high pressure oxygen hose assemblies are installed, and, if installed, replacement of those hose assemblies with new, improved hose assemblies. This amendment is prompted by a report that certain high pressure oxygen hose assemblies are susceptible to leakage due to those hose assemblies not meeting design specifications during manufacturing. The actions specified by this AD are intended to prevent leaks in high pressure oxygen hose assemblies, which, if not detected and corrected, could result in insufficient oxygen available to the passengers or crew if the cabin pressure altitude should rise to a level requiring emergency oxygen.
AD 97-21-06 · published Oct 20, 1997, effective Nov 24, 1997
Construcciones Aeronauticas, S.A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires repetitive inspections of the torsion tubes and fittings of the elevator and rudder assemblies to detect stress corrosion cracking, and replacement of cracked parts. This action also requires accomplishment of a modification that constitutes terminating action for the repetitive inspections. This amendment is prompted by reports indicating that stress corrosion cracking in these parts has been found on some airplanes. The actions specified by this AD are intended to prevent loss of control of the elevator and/or rudder, due to failure of the elevator and/or rudder assemblies as a result of stress corrosion cracking.
AD 97-21-12 · published Oct 20, 1997, effective Nov 24, 1997
Construcciones Aeronauticas, S. A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires a one-time inspection to detect fatigue cracking in the area of the center wing-to-fuselage attachment fitting, and repair, if necessary. This amendment also would require installation of a reinforcing plate in the attachment area of that fitting. This amendment is prompted by a report from the manufacturer indicating that, during full-scale fatigue testing, fatigue cracks were detected in this area. The actions specified by this AD are intended to prevent fatigue cracking, which consequently could reduce the structural integrity of this area.
AD 97-21-13 · published Oct 20, 1997, effective Nov 24, 1997
Lockheed Model 382 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model 382 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit the positioning of the power levers below the flight idle stop, and to provide a statement of the consequences of positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller beta 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 97-21-14 · published Oct 20, 1997, effective Nov 24, 1997
Construcciones Aeronauticas, S.A. (CASA) Model C-212 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires an initial inspection of the restrictor pistons on the shock absorbers of the left and right main landing gear (MLG) to determine the number and condition of threaded screw pins that are installed; replacement of any discrepant pin; and repetitive inspections of certain pistons. Modification of certain pistons by the installation of two additional pins terminates these inspections. This amendment is prompted by reports indicating that the threaded screw pin that holds the restrictor piston on the slide tube of the shock absorber has been found to have loosened on some airplanes. The actions specified by this AD are intended to prevent the loss of hydraulic damping in the MLG, due to failure of the screw pins that hold the restrictor pistons on the slide tubes of the shock absorbers, and consequent structural damage to the airplane.
AD 97-21-15 · published Oct 20, 1997, effective Nov 24, 1997
British Aerospace Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Avro 146-RJ series airplanes, that requires a modification of the electrical system in the equipment bay area by replacing certain cables, clamps, and fairleads with new components. This amendment is prompted by a report indicating that the incorrect size of electrical cables were used in the generator feeder circuit to certain busbars from the generator contactors. As a result, the electrical cables are not compatible with generator rating requirements and can overheat. The actions specified by this AD are intended to prevent possible overheating of electrical generator feeder cables and consequent damage, which could lead to possible fire or the loss of essential electrical systems.
AD 86-07-02 R1 · published Oct 21, 1997, effective Nov 28, 1997
Pilatus Britten-Norman Ltd. (Formerly Britten-Norman) BN2A MK. 111 Series Airplanes
This amendment revises Airworthiness Directive (AD) 86-07-02, which currently requires repetitively inspecting the junction of the torque link lug and upper case of the main landing gear (MLG) torque link assemblies for cracks on Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN-2A, BN-2B, BN-2T, and BN2A MK. 111 series airplanes, and replacing any part found cracked with a like part. This AD removes from the applicability the BN-2A, BN-2B, and BN-2T series airplanes, and retains the repetitive inspection and replacement (if necessary) requirements of AD 86-07-02 for the BN2A MK. 111 series airplanes. This AD results from the Federal Aviation Administration's determination that additional AD action needs to be taken on the BN-2A, BN-2B, and BN-2T series airplanes. This additional action will be addressed in a separate AD. The actions specified by this AD are intended to prevent failure of the main landing gear caused by cracks in the torque link area, which could lead to loss of control of the airplane during landing operations.
AD 97-19-16 · published Oct 21, 1997, effective Oct 27, 1997
Fokker Model F28 Mark 0100 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 97-19-16, that was sent previously to all known U.S. owners and operators of Fokker Model F28 Mark 0100 series airplanes equipped with Rolls-Royce Tay 650-15 engines, by individual notices. This AD requires a revision to the FAA- approved Airplane Flight Manual (AFM) to include procedures to prohibit use of reverse engine thrust power settings between idle and emergency maximum; and submission of a report to the airplane manufacturer. This action is prompted by a report that, during preparation for takeoff, an engine fan blade failure occurred, followed by an engine fire. The actions specified by this AD are intended to prevent uncontained engine fan blade failure due to high cycle fatigue cracking, which could result in loss of thrust from the affected engine and secondary damage to aircraft and/or fire.
AD 97-22-01 · published Oct 21, 1997, effective Nov 28, 1997
Pilatus Britten-Norman Ltd. (Formerly Britten-Norman) BN-2A, BN-2B, and BN-2T Series Airplanes
This amendment adopts a new airworthiness directive that applies to Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN-2A, BN-2B, and BN-2T series airplanes. This AD requires repetitively inspecting the junction of the torque link lug and upper case of the main landing gear (MLG) torque link assemblies for cracks, and replacing any MLG torque link assembly with a Modification A39 MLG torque link assembly, either immediately when cracks are found or after a certain period of time if cracks are not found. Replacing all MLG torque link assemblies with Modification A39 MLG torque link assemblies eliminates the need for the repetitive inspections. These repetitive inspections are currently required by AD 86-07-02 for the BN-2A, BN-2B, and BN-2T series airplanes, as well as the BN2A MK. 111 series airplanes. There are no improved design parts for the BN2A MK. 111 series airplanes. The Federal Aviation Administration (FAA) is issuing in a separate action a revision to AD 86-07-02 to retain the repetitive inspection and replacement (if necessary) requirements for the BN2A MK. 111 series airplanes. The actions specified in this AD are intended to prevent failure of the main landing gear caused by cracks in the torque link area, which could lead to loss of control of the airplane during landing operations.
AD 84-23-06 R1 · published Oct 23, 1997, effective Nov 24, 1997
Pilatus Britten-Norman Ltd. Models BN- 2, BN-2A, BN-2B, BN-2T, and BN-2A MK. 111 Series Airplanes
This amendment revises airworthiness directive (AD) 84-23-06, which currently requires repetitively inspecting the upper mounting brackets, bolts, and bushings on wing mounted engines for cracks, wear, and insufficient fit on certain Pilatus Britten-Norman Ltd. (Pilatus) Models BN-2, BN-2A, BN-2B, BN-2T, and BN-2A MK. 111 series airplanes, and replacing any cracked, worn, or ill-fitting part. This action retains the same action required in AD 84-23-06, except the action is only applicable to the BN-2A MK. 111 series airplanes. This action is the result of a terminating modification, now available to the Pilatus Models BN-2, BN-2A, BN-2B, BN-2T airplanes, which removes them from the applicability of AD 84-23-06. The actions specified by this AD are intended to prevent failure of the upper mounting brackets on wing mounted engines, which could possibly cause structural failure of the airplane.
AD 97-22-03 · published Oct 23, 1997, effective Nov 24, 1997
Extra Flugzeugbau, GmbH. Model EA-300/ 200 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to Extra Flugzeugbau, GmbH. (Extra) Model EA-300/200 airplanes. This action requires installing a seat belt safety cover. A recent report of an Extra Model EA-300/200 airplane seat belt falling into the rear rudder pedal controls, interfering with the rudder pedals, and causing loss of directional control prompted this action. The action specified by this AD is intended to prevent a loss of directional control caused by seat belt interference with the rear rudder pedal controls, which could cause loss of control of the airplane.
AD 97-22-02 · published Oct 27, 1997, effective Nov 24, 1997
Pilatus Britten-Norman Ltd. Models BN- 2, BN-2A, BN-2B, and BN-2T Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Britten-Norman Ltd. (PBN) BN-2, BN-2A, BN-2B, and BN-2T series airplanes. This action requires modifying the upper engine mounting brackets on the wing front spar as terminating action for the repetitive inspections that were required in AD 84-23-06. AD 84-23-06 is being revised in a separate action, deleting the Pilatus BN-2, BN- 2A, BN-2B, and BN-2T series airplanes from its applicability. This AD is prompted by several reports of cracks in the upper engine mounting brackets and a new terminating action to eliminate the repetitive inspections for Pilatus BN-2, BN-2A, BN-2B, and BN-2T series airplanes. The actions specified by this AD are intended to prevent the failure of the upper engine mounting brackets on the wing mounted engines, which could possibly cause structural failure of the airplane.
AD 97-22-04 · published Oct 28, 1997, effective Nov 12, 1997
Boeing Model 747 and 767 Series Airplanes Equipped With General Electric (GE) CF6-80C2 Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 and 767 series airplanes. This action 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) with standard fuel nozzles, which terminates the requirements for a placard and AFM revision. This amendment is prompted by a report of an engine flameout during certification testing due to the use of JP-4 or Jet B fuel. The actions specified in this AD are intended to prevent such engine flameouts and consequent engine shutdown.
AD 97-22-05 · published Oct 28, 1997, effective Dec 2, 1997
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive applicable to certain McDonnell Douglas Model DC-9 series airplanes and C-9 (military) series airplanes, that requires modification of the emergency internal release system of the tailcone and the accessory compartment. This amendment is prompted by a report that, due to failure of the tailcone release system, the tailcone did not deploy on an airplane during an emergency evacuation. The actions specified by this AD are intended to ensure that the emergency internal release system of the tailcone performs its intended function in the event of an emergency evacuation. The actions also are intended to prevent people on board the airplane from striking their heads on exposed metal frames in the tailcone area, which could cause injury and delay or impede their evacuation during an emergency.
AD 97-22-06 · published Oct 28, 1997, effective Dec 2, 1997
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires performing a ram air turbine (RAT) extension test; removing and disassembling the RAT uplock mechanism; performing an inspection to detect corrosion of the RAT uplock mechanism, and replacement with a new assembly, if necessary; and cleaning all the parts of the RAT control shaft and its bearing component parts. This amendment is prompted by reports indicating that the RAT did not extend during ground testing, due to corrosion in the uplock pin/shaft and the needle bearing of the RAT. The actions specified by this AD are intended to detect and correct such corrosion of the RAT, which could result in failure of the RAT to deploy and subsequent loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
AD 97-22-07 · published Oct 28, 1997, effective Nov 12, 1997
Boeing Model 737 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires repetitive inspections to detect cracking of the lower skin at the lower row of fasteners in the lap joints of the fuselage, and repair of any cracking detected. This amendment requires that the inspections be accomplished at more frequent intervals. This amendment also adds a requirement for modification of the fuselage lap joints at certain locations, which constitutes terminating action for repetitive inspections of modified areas. This amendment is prompted by reports of numerous fatigue cracks in the lower skin of the fuselage lap joints at the lower row of fasteners. The actions specified in this AD are intended to prevent such fatigue cracking, which could result in sudden decompression of the airplane.
AD 97-06-07 R1 · published Oct 29, 1997, effective Nov 13, 1997
Dornier Model 328-100 Series Airplanes Equipped With Burns Aerospace Corporation Passenger Seats
This amendment revises an existing airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that currently requires modification of the restraining systems of certain passenger seats by replacing anchor point fasteners with fasteners that are able to withstand required 16g load conditions. That AD was prompted by a report indicating that the restraining systems on these seats failed to meet 16g test load requirements during dynamic testing. The actions specified by that AD are intended to prevent the fasteners from failing, which could result in release of the seat restraint and consequent injury to passengers. This amendment revises the applicability of the existing AD to specify serial numbers of the affected passenger seats.
AD 97-22-08 · published Oct 29, 1997, effective Dec 5, 1997
Pilatus Aircraft LTD Models PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, and PC-12 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft LTD (Pilatus) Models PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4 airplanes and all Pilatus Model PC-12 airplanes. This AD requires amending the Limitations Section of either the airplane flight manual (AFM) or the pilot's operating handbook (POH) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 97-22-09 · published Oct 29, 1997, effective Dec 5, 1997
Dornier Luftfahrt GMBH Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GMBH (Dornier) Models 228-100, 228- 101, 228-200, 228-201, 228-202, and 228-212 airplanes. This AD requires amending the Limitations Section of the Dornier 228 Pilot's Operating Handbook (POH) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This POH amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 97-22-10 · published Oct 29, 1997, effective Dec 5, 1997
Partenavia Costruzioni Aeronauticas, S.p.A. Models AP68TP 300 ``Spartacus'' and AP68TP 600 ``Viator'' Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Partenavia Costruzioni Aeronauticas, S.p.A. (Partenavia) Models AP68TP 300 ``Spartacus'' and AP68TP 600 ``Viator'' airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 97-22-11 · published Oct 29, 1997, effective Dec 5, 1997
Industrie Aeronautiche e Meccaniche Rinaldo Piaggio S.p.A. Model P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche Rinaldo Piaggio S.p.A. (Piaggio) Model P-180 airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 97-22-12 · published Oct 29, 1997, effective Dec 5, 1997
SIAI Marchetti S.r.1. Models SF600 and SF600A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all SIAI Marchetti S.r.1. Models SF600 and SF600A airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 97-22-13 · published Oct 31, 1997, effective Dec 5, 1997
Airbus Model A320 and A321 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A320 series airplanes, that currently requires revising the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to instruct the flight crew to maintain a flap setting of ``Configuration Full'' (CONF FULL) during landing. That AD was prompted by a report of severe control difficulties which occurred on approach with the flaps locked in CONF FULL and the landing gear down. This amendment adds a requirement for installation of a new, improved flight warning computer (FWC), which, when accomplished, constitutes terminating action for the AFM limitation. This action also revises the applicability of the existing AD to include additional airplanes that are subject to the addressed unsafe condition. The actions specified by this AD are intended to prevent reduced controllability of the airplane during approach when the flaps are locked in CONF FULL.
AD 97-22-16 · published Oct 31, 1997, effective Dec 5, 1997
Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). This AD requires fabricating and installing a placard that restricts the use of the forward and aft vent blower assemblies to only the ``OFF'' or ``HIGH'' position. This AD also requires incorporating a modification that would replace the bearings on the vent blower assemblies with improved design bearings, and provide thermal protection for the vent blowers, as applicable. Incorporating the modification will eliminate the need for the placard. The AD results from reports of vent blower assembly bearings seizing and locking the blower motor on several of the affected airplanes. The actions specified by this AD are intended to prevent the vent blower assembly bearings from seizing, which could result in smoke emanating from the insulating material covering the electrical wiring and entering the airplane cabin.
AD 97-20-12 · published Oct 2, 1997
McDonnell Douglas Helicopter Systems Model MD-900 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters, that requires removing certain serial-numbered main rotor swashplate bearings (bearings) and replacing them with airworthy bearings. This amendment is prompted by reports that inspections of several helicopters revealed that the outer bearing race had been rotating relative to the swashplate assembly, which was evidenced by wear marks in the rotating swashplate. The actions specified by this AD are intended to prevent possible heat accumulation and resulting damage to the bearing caused by the bearing races rotating relative to the bearing seat, which could result in degraded helicopter response to pilot control input and possible loss of control of the helicopter.
AD 97-20-15 · published Oct 8, 1997, effective Nov 12, 1997
Hiller Aircraft Corporation Model UH- 12A, UH-12B, UH-12C, UH-12D, and UH-12E Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Hiller Aircraft Corporation Model UH-12A, UH-12B, UH-12C, UH-12D, and UH-12E helicopters, that currently requires a dye penetrant inspection of the head of the main rotor outboard tension- torsion (T-T) bar pin for cracks; a visual inspection of the outboard T-T bar pin for proper alignment and an adjustment, if necessary; and, installation of shims at the inboard end of the drag strut. This amendment requires the same actions required by the existing AD, but allows a magnetic particle inspection of the T-T bar pin as an alternative to the currently required dye penetrant inspection, and requires reporting the results of the inspections only if cracks are found, rather than reporting all results of inspections as required by the existing AD. This amendment is prompted by an FAA analysis of a comment to the existing AD, and the fact that no cracks have been reported since the issuance of the existing AD. The actions specified by this AD are intended to prevent cracks in the head area of the outboard T-T bar pin, which could result in loss of in-plane stability of the main rotor blade and subsequent loss of control of the helicopter.
AD 97-15-16 · published Oct 9, 1997, effective Oct 24, 1997
Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-15-16, which was sent previously to all known U.S. owners and operators of BHTC Model 430 helicopters by individual letters. This AD requires inspections of all 4 main rotor adapter assemblies for evidence of flapping contact between the adapter liners and the upper stop assembly plugs, and for evidence of lead-lag contact between the adapter pads and the yoke assembly; installing a never-exceed-velocity (VNE) placard; marking the airspeed indicator to reflect the airspeed restriction; installing a slippage mark on the airspeed indicator glass and instrument case; and inserting revisions to the rotorcraft flight manual to reflect the airspeed revision. This amendment is prompted by a report of a main rotor tip path plane separation, which occurred during a ferry flight at an airspeed of more than 140 knots indicated airspeed (KIAS). The actions specified by this AD are intended to prevent tip path plane separation, increased vibrations, possible damage to the main rotor system, and subsequent loss of control of the helicopter.
AD 97-20-16 · published Oct 9, 1997, effective Oct 24, 1997
Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model MBB-BK117 A-1, A-3, A-4, B-1, B-2, and C-1 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter Model MBB-BK117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, that currently requires initial and repetitive inspections of both surfaces of the tail boom vertical fin (vertical fin) spar, the skin, and the left-hand and right-hand frame sheets for cracks or loose rivets. This amendment requires the same initial and repetitive inspections of the vertical fin spar that are required by the existing AD, and also requires repairing certain cracks, if found, and repairing and reporting loose rivets and certain other cracks, if found. This amendment is prompted by an accident which occurred on April 15, 1997, resulting in one fatality. A subsequent investigation revealed that the vertical fin had failed as a result of a fatigue crack that initiated on the left side of the vertical fin spar cap. The actions specified by this AD are intended to prevent failure of the vertical fin and subsequent loss of control of the helicopter.
AD 97-21-02 · published Oct 10, 1997, effective Oct 27, 1997
Teledyne Continental Motors E-165, E- 185, E-225, O-470 and IO-470 Series Reciprocating Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Teledyne Continental Motors E-165, E-185, E-225, O-470 and IO-470 series reciprocating engines. This action supersedes priority letter AD 97-15-01 that currently requires removal from service of affected cylinders, and reassembly with serviceable parts. This action adds the latest revision to applicable Critical Service Bulletin (CSB), corrects references to Parts of that CSB, and lists a new contact telephone number to obtain the CSB from the manufacturer. This amendment is prompted by the availability of the new CSB revision and the need to correct the CSB references. The actions specified by this AD are intended to prevent extreme side loading of the piston, and consequent failure of the piston and engine.
AD 97-21-07 · published Oct 17, 1997, effective Nov 3, 1997
AlliedSignal Inc. (Formerly Textron Lycoming) Model T5313B, T5317A, and T53 (Military) Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to AlliedSignal Inc. (formerly Textron Lycoming) Model T5313B, T5317A, and T53 series military turboshaft engines approved for installation on aircraft certified in accordance with Section 21.25 of the Federal Aviation Regulations (FAR). This action requires a one-time visual inspection of accessory drive carrier assemblies for affected serial numbers (S/Ns) designating a defective assembly, and if the S/N is applicable, replacement with a serviceable assembly. This amendment is prompted by a report of an N2 overspeed condition due to a defective accessory drive carrier assembly. The actions specified in this AD are intended to prevent accessory drive carrier assembly failure, which could result in an N2 overspeed and an uncontained engine failure.
AD 97-21-08 · published Oct 20, 1997, effective Dec 19, 1997
General Electric Company CT58 Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company CT58 series turboshaft engines, that requires removal from service of certain stage 1 and 2 forward cooling plates, and stage 2 aft cooling plates, and replacement with serviceable parts. This amendment is prompted by reports of certain cooling plates forged with contaminated alloy that could reduce the lives of the parts. The actions specified by this AD are intended to prevent cooling plate fracture, which could result in a contained engine failure, and an inflight engine shutdown.
AD 97-22-14 · published Oct 31, 1997, effective Nov 17, 1997
General Electric Company CF6-50 and - 80C2 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-50 and -80C2 series turbofan engines. This action requires removal from service of defective high pressure compressor rotor (HPCR) stage 3-9 spools, and replacement with serviceable parts. This amendment is prompted by a report of an uncontained failure of an HPCR stage 3-9 spool installed on a GE model CF6-80C2 turbofan engine. The actions specified in this AD are intended to prevent failure of the HPCR stage 3-9 spool, which can result in an uncontained engine failure and damage to the aircraft.
AD 97-21-01 · published Oct 7, 1997, effective Oct 22, 1997
MT-Propeller Entwicklung GMBH Model MTV-3-B-C Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to MT-Propeller Entwicklung GMBH Model MTV-3-B-C propellers. This action requires initial and repetitive dye penetrant or eddy current inspections for cracks in the propeller hub, and rework of the propeller hub or replacement with a new model propeller hub. This amendment is prompted by reports of cracks in the propeller flange area of the hub detected during overhaul. The actions specified in this AD are intended to prevent propeller hub cracks, which could result in propeller blade separation and possible loss of control of the aircraft.
