45 Airworthiness Directives: 35 airplane, 6 rotorcraft, 4 engine.
AD 97-25-06 · published Dec 1, 1997, effective Dec 16, 1997
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires disconnection of the electrical connector to the scavenge pump of the center wing tank. This AD also requires a one-time inspection to identify the part number of the electrical connector; and replacement of the pump with a new pump, if necessary. This amendment is prompted by findings from a design review and analysis of scavenge pumps installed on certain Boeing Model 747 series airplanes that was undertaken as part of an accident investigation. The actions specified in this AD are intended to prevent potential failures within the electrical motor assembly of the scavenge pump, which could result in leakage of fuel from the electrical connector into the main landing gear wheel well, or electrical arcing within the scavenge pump motor; these conditions could result in a fuel fire in the wheel well.
AD 96-24-17 R1 · published Dec 3, 1997, effective Jan 27, 1997
The Don Luscombe Aviation History Foundation Models 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F Airplanes
This document clarifies information in airworthiness directive (AD) 96-24-17, which applies to Don Luscombe Aviation History Foundation (Luscombe) Models 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F airplanes. AD 96-24-17 currently requires installing new inspection holes, modifying the wing tip fairings, and inspecting the wing spars for intergranular corrosion. The actions specified in AD 96-24-17 are intended to prevent wing spar failure from intergranular corrosion, which could result in structural failure of the wings and loss of control of the airplane. The AD was published with an Appendix providing an alternative method of compliance. Since issuance of AD 96- 24-17, the FAA has re-examined the Appendix and has determined that clarification of certain inspections procedures is needed. This action clarifies the procedures specified in the Appendix of AD 96-24-17.
AD 97-25-01 · published Dec 3, 1997, effective Jan 11, 1998
Raytheon Aircraft Company 58, 60, 90, 100, 200, and 300 Series and Model 2000 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) 58, 60, 90, 100, 200, and 300 series and Model 2000 airplanes (formerly referred to as Beech 58, 60, 90, 100, 200, and 300 series and Beech Model 2000 airplanes). This AD requires replacing certain AlliedSignal Aerospace outflow/safety valves in the pressurization system with new or serviceable valves. The AD results from a report of cracking and consequent failure of the affected outflow safety valves in the pressurization system. Investigation has revealed problems during the manufacturing process of certain AlliedSignal outflow/safety valves. The actions specified by this AD are intended to prevent outflow/safety valve cracking and consequent failure, which could result in rapid decompression of the airplane.
AD 97-25-02 · published Dec 3, 1997, effective Jan 21, 1998
Mitsubishi Heavy Industries MU-2B Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Mitsubishi Heavy Industry (Mitsubishi) MU-2B series 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 97-25-03 · published Dec 3, 1997, effective Jan 21, 1998
Raytheon Aircraft Company 65, 90, 99, 100, 200, 300, 1900, and 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, 300, 1900, and 2000 series airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit lifting or positioning 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 nose down pitch and a descent rate leading to aircraft damage and injury to personnel caused by the power levers being positioned below the flight idle stop or the power levers being lifted while the airplane is in flight.
AD 97-25-04 · published Dec 3, 1997, effective Jan 21, 1998
Cessna Aircraft Company Models 208, 208A, 208B, 425, and 441 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Models 208, 208A, 208B, 425, and 441 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 97-25-11 · published Dec 8, 1997, effective Dec 23, 1997
Bombardier Model CL-600-2B16 Series Airplanes Modified in Accordance With Supplemental Type Certificate (STC) SA6003NM
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B16 series airplanes. This action requires disabling the remote fuel/defuel panel in the cockpit. This action also provides for an optional modification of the remote fuel/defuel panel, which would terminate the requirement to disable the panel. This amendment is prompted by reports of in-flight failure of the panel that resulted when a circuit breaker on a battery bus opened due to insufficient current flow capacity. The actions specified in this AD are intended to prevent the circuit breakers from opening during flight, which could result in irreversible loss of engine indicating and fuel quantity systems in the cockpit.
AD 97-25-12 · published Dec 9, 1997, effective Jan 13, 1998
Bombardier Model CL-44 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-44 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 97-25-13 · published Dec 10, 1997, effective Jan 14, 1998
British Aerospace BAe Model ATP Airplanes and Model HS 748 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes and all Model HS 748 series airplanes, that requires inspection of the main hydraulic accumulator for corrosion, 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 such corrosion, which could result in loss of certain hydraulic system functions, including nose wheel steering, hydraulic lowering of the landing gear, and main wheel brakes, which are essential for safe operation of the airplane.
AD 97-25-14 · published Dec 10, 1997, effective Jan 14, 1998
de Havilland Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100, -200, and -300 series airplanes, that requires repetitive inspections of certain refuel/defuel tube assemblies in the engine nacelles for fuel leakage, and corrective action, if necessary. This amendment will also require eventual modification of all tube assemblies, which will terminate the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fuel leaks and consequent increased risk of engine fires.
AD 97-25-15 · published Dec 12, 1997, effective Dec 29, 1997
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 727 series airplanes. This action requires repetitive inspections to detect cracking of the rear spar web or fuel leakage of the wing center section, and repair, if necessary. This amendment also provides for an optional modification of the rear spar web that constitutes terminating action for the repetitive inspections. This amendment is prompted by several reports of fuel leakage due to cracking of the rear spar web of the wing center section. The actions specified in this AD are intended to detect and correct such cracking of the rear spar web, which could permit fuel leakage into the airflow multiplier, and could result in an electrical short that could cause a fire.
AD 97-26-07 · published Dec 12, 1997, effective Dec 29, 1997
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires a one-time inspection to detect damage of the sleeving and wire bundles of the boost pumps of the numbers 1 and 4 main fuel tanks, and of the auxiliary tank jettison pumps (if installed); replacement of any damaged sleeving with new sleeving; and repair or replacement of any damaged wires with new wires. For airplanes on which any burned wires are found, that AD also requires an inspection to detect damage of the conduit, and replacement of any damaged conduit with a serviceable conduit. This amendment requires repetitive inspections in lieu of the one-time inspection. This amendment also expands the applicability of the existing AD. This amendment is prompted by reports of chafing of the sleeving. The actions specified in this AD are intended to detect and correct abrasion of the Teflon sleeving and wires in the bundles of the fuel boost pumps for the numbers 1 and 4 main fuel tanks and of the auxiliary tank jettison pumps (if installed), which could result in electrical arcing between the wires and the aluminum conduit and consequent fire or explosion of the fuel tank.
AD 97-25-16 · published Dec 15, 1997, effective Jan 20, 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 of the tailplane (horizontal stabilizer) leading edges and surrounding area for discrepancies, 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 separation of the horizontal stabilizer from the fin, which could lead to reduced controllability of the airplane.
AD 97-25-17 · published Dec 15, 1997, effective Jan 20, 1998
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 revision to the Airplane Flight Manual (AFM) to include procedures for the flightcrew to follow in the event of radio altimeter height malfunction. This amendment also requires replacement of certain radio altimeter antennas with improved antennas, at which time the AFM revision will no longer be required. 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 output of erroneous radio altimeter height information to the flightcrew and autopilot, which could result in reduced ability of the flightcrew to cope with adverse operating conditions.
AD 97-25-18 · published Dec 15, 1997, effective Jan 20, 1998
Aerospatiale Model ATR42 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42 series airplanes, that requires removal of certain landing gear attachment pins, and replacement of the pins with serviceable pins. 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 wear of the attachment pins, which could result in collapse of the main landing gear.
AD 97-26-01 · published Dec 15, 1997, effective Jan 20, 1998
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires repetitive inspections to detect galling on the input shaft and bearing of the standby rudder power control unit (PCU), and replacement of the standby rudder actuator with a serviceable actuator, if necessary. This amendment also requires eventual replacement of the input bearing of the standby PCU with an improved bearing, which constitutes terminating action for the inspections to detect galling. 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 galling on the input shaft and bearing of the standby PCU, which could result in uncommanded movement of the rudder or increased pedal forces. These conditions, if not corrected, could result in reduced controllability of the airplane.
AD 97-26-04 · published Dec 15, 1997, effective Dec 30, 1997
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes. This amendment requires a one-time inspection to determine if certain ailerons are installed on the airplane. This amendment also requires removing any defective aileron, scrapping it, and replacing it with a new or serviceable aileron. This amendment is prompted by reports of failure of the aileron due to an inappropriate repair procedure. The actions specified in this AD are intended to detect and correct defective ailerons, which could result in in-flight separation of an aileron from the airplane and consequent reduced controllability of the airplane.
AD 97-26-05 · published Dec 18, 1997, effective Jan 2, 1998
British Aerospace (Jetstream) Model HS 748 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model HS 748 series airplanes. This action requires inspections of the inspection holes in all engine `W' frame socket fittings to determine if certain fasteners have been installed, or if the inspection holes have been reworked; 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 fatigue cracking at the inspection hole locations, due to the installation of certain fasteners or hole enlargement, which could result in failure of the engine mount structure and consequent separation of the engine from the airplane.
AD 97-26-08 · published Dec 18, 1997, effective Jan 20, 1998
Mooney Aircraft Corporation Models M20F, M20J, and M20L Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Mooney Aircraft Corporation (Mooney) Models M20F, M20J, and M20L airplanes. This action requires removing the fuel cap retaining lanyard from the fuel filler cap assemblies. A report of lost engine power during flight because of fuel starvation prompted the action. The investigation revealed that the airplane fuel float became trapped by the fuel cap retaining lanyard, keeping the float from following the fuel level. This condition caused the pilot to get a false fuel quantity reading. The actions specified by this AD are intended to prevent loss of engine power and fuel depletion during flight caused by a false fuel gauge reading.
AD 97-26-12 · published Dec 18, 1997
The New Piper Aircraft, Inc. Models PA- 31T, PA-31T1, PA-31T2, PA-31T3, PA-42, PA-42-720, and PA-42-1000 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. (Piper) Models PA-31T, PA- 31T1, PA-31T2, PA-31T3, PA-42, PA-42-720, and PA-42-1000 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 97-26-13 · published Dec 18, 1997
Empresa Brasileira de Aeronautica S.A. Models EMB-110P1 and EMB-110P2 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Models EMB-110P1 and EMB-110P2 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 increased propeller drag beyond the certificated limits caused by the power levers being positioned below the flight idle stop while the airplane is in flight, which could result in loss of airplane control or engine overspeed with consequent loss of engine power.
AD 97-26-14 · published Dec 18, 1997
MAULE Models MX-7-420 and MXT-7-420 Airplanes and Models M-7-235 and M-7-235A Airplanes Modified in Accordance With Maule Supplemental Type Certificate (STC) SA2661SO
This amendment adopts a new airworthiness directive (AD) that applies to all MAULE Models MX-7-420 and MXT-7-420 airplanes, and all Models M-7-235 and M-7-235A airplanes that are modified in accordance with Maule STC SA2661SO, which incorporates a certain gas turbine engine, certain amphibious floats, and certain propellers. 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 97-26-06 · published Dec 19, 1997, effective Jan 23, 1998
Empresa Brasileira de Aeronautica, S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the ice protection systems, and to add information regarding operation in icing conditions. This amendment also requires installing an ice detector system and revising the AFM to include procedures for testing system integrity. This amendment is prompted by reports indicating that flightcrews experienced difficulties controlling the airplane during (or following) flight in normal icing conditions, when the ice protection system either was not activated when ice began to accumulate on the airplane, or the ice protection system was never activated. These difficulties may have occurred because the flightcrews did not recognize that a significant enough amount of ice had formed on the airplane to require activation of the deicing equipment. The actions specified by this AD are intended to ensure that the flightcrew is able to recognize the formation of significant ice accretion and take appropriate action; such formation of ice could result in reduced controllability of the airplane in normal icing conditions.
AD 97-26-10 · published Dec 19, 1997, effective Jan 23, 1998
Raytheon Model Hawker 1000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 1000 series airplanes, that requires modifying the aft core cowl nozzles of the engine nacelles. This amendment is prompted by a report indicating that the sealant on the core cowl nozzles may extend higher than the forward flange of the core cowl nozzles, which could result in contact between the cowl sealant surface and the lever of the engine mechanical over-speed control system. The actions specified by this AD are intended to prevent such contact, which could cause the over-speed system to function improperly and consequent engine structural failure.
AD 97-26-11 · published Dec 19, 1997, effective Jan 23, 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 corrosion of the rear spars of the wings, 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 possible corrosion on the rear spars of the wings, which could result in reduced structural integrity of the wings.
AD 97-26-15 · published Dec 19, 1997, effective Jan 25, 1998
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 lubricating the main landing gear actuator rod ends and eventually replacing these rod ends with Teflon-lined rod ends. The AD results from reports of in-flight separations of the rod end that attaches the actuator to the arm of the main landing gear drag brace assembly on two of the affected airplanes caused by excessive friction in the rod end bearing. The actions specified by this AD are intended to prevent actuator rod end failure caused by excessive friction in the rod end bearing, which could result in the inability to lower the main landing gear or result in landing gear collapse during landing.
AD 97-26-16 · published Dec 19, 1997, effective Feb 2, 1998
Cessna Aircraft Company Models 402C and 414A Airplanes
This amendment supersedes Airworthiness Directive (AD) 85-13- 03 R2, which currently requires repetitively inspecting the engine mount beams for cracks on certain Cessna Aircraft Company (Cessna) Models 402C and 414A airplanes, and replacing any cracked beams. This AD requires incorporating engine mount kits that will eliminate the need for the repetitive inspection requirement of AD 85-13-03 R2. This AD results from the Federal Aviation Administration's policy on aging commuter-class aircraft, which is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. The actions specified by this AD are intended to prevent failure of the engine mount beam caused by fatigue cracks, which could result in loss of the engine with consequent loss of the airplane.
AD 97-26-19 · published Dec 23, 1997, effective Jan 7, 1998
Aerospatiale Model ATR42-300 and ATR42- 320 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-300 and ATR42-320 series airplanes, that currently requires repetitive ultrasonic inspections to detect fatigue cracks of the lower lugs of the barrel of the main landing gear (MLG); and replacement of cracked lower lugs with new or serviceable parts, and a follow-on inspection. This amendment expands the applicability of the existing AD. This action also provides for an optional terminating action, which, if accomplished, terminates the repetitive inspection requirement. 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 fatigue cracking of the lower lugs of the barrel of the MLG, which could lead to the collapse of the MLG.
AD 97-26-21 · published Dec 29, 1997, effective Jan 13, 1998
Boeing Model 747-100, 747-200, 747-300, 747SR, and 747SP Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SR, and 747SP series airplanes. This action requires a one-time inspection to detect cracking of the longeron splice fittings at stringer 11, on the left and right sides at body station 2598, and replacement of any cracked fitting with a new fitting. This amendment is prompted by reports that fatigue cracking was found on longeron splice fittings. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in reduced controllability of the horizontal stabilizer.
AD 97-26-22 · published Dec 29, 1997, effective Jan 13, 1998
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-120 series airplanes. This action requires a one-time inspection of the movable backstop of the elevator pitch trim command system to ensure that it is installed correctly, and corrective action, if necessary. This action also requires installation of a guide to maintain the movable backstop in its correct position. 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 a sudden change in pitch attitude caused by autopilot disconnect, which could result in reduced controllability of the airplane.
AD 97-26-20 · published Dec 30, 1997, effective Jan 22, 1998
Aviat Aircraft Inc. Models S-2A, S-2B, and S-2S Airplanes (formerly Pitts Models S-2A, S-2B, and S-2S airplanes)
This amendment supersedes Airworthiness Directive AD 96-09-08 R1, which applies to Aviat Aircraft Inc. (Aviat) Models S-2A, S-2B, and S-2S airplanes (formerly Pitts Models S-2A, S-2B, and S-2S), and currently requires repetitively inspecting the upper longerons just aft of the rear cabane struts for cracks and repairing any cracks. This action retains the same actions as the current AD; lengthens the time interval between repetitive inspections; requires either installing a marked accelerometer in order to continue to perform acrobatic maneuvers and installing a placard that specifies gravity (``g'') force limitations, or installing a placard prohibiting acrobatic maneuvers; and, requires inserting revisions into the Airplane Flight Manual (AFM). This action is the result of reports of cracking in the upper longerons caused by operating the airplane outside of the certificated design limits and the availability of a design modification that, when incorporated, repairs the damaged upper longeron area. The actions specified by this AD are intended to prevent cracking and subsequent failure of the longerons with consequent loss of control of the airplane.
AD 98-01-02 · published Dec 31, 1997, effective Feb 4, 1998
Fokker F28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time visual inspection of the rear cargo door and luggage auxiliary structure for corrosion, repetitive borescope inspections of the rear cargo door, and removal and repair of any corrosion found during the inspections. This amendment also requires the drilling of drain holes and application of a corrosion preventive and sealing compound inside the rear cargo door, and modification of the rear cargo door to aid in future routine borescope inspections. This amendment is prompted by reports of corrosion being found in the affected areas on several of the affected airplanes. The actions specified by this AD are intended to prevent such corrosion, which could result in structural failure of the cargo door and loss of the door during flight, and consequent rapid decompression, aerodynamic instability, and/or damage to other fuselage structures.
AD 98-01-03 · published Dec 31, 1997, effective Jan 15, 1998
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires modification of the air outlet opening of the engine air bypass duct. 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 accumulation of ice in the engine air intake duct and subsequent ingestion of ice into the engine, which could result in engine power fluctuations and reduced controllability of the airplane.
AD 98-01-04 · published Dec 31, 1997, effective Jan 15, 1998
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection of the main landing gear (MLG) locklinks to determine if the lockwire that secures both platform bolts is in one piece and in position; 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 in this AD are intended to prevent collapse of the MLG due to failure of the locklinks to lock in the down position.
AD 98-01-05 · published Dec 31, 1997, effective Jan 15, 1998
British Aerospace Model HS 748 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace HS 748 series airplanes. This action requires installation of an aileron cable support block under the crew compartment floor. 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 jamming or restriction of the aileron cable, which could lead to reduced controllability of the airplane.
AD 97-25-05 · published Dec 8, 1997, effective Jan 12, 1998
Robinson Helicopter Company Model R22 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R22 helicopters with a Lycoming 0-360-J2A engine installation. This AD requires replacing the carburetor and carburetor air temperature (CAT) gage with an improved carburetor that does not require manual leaning of the fuel/air mixture during flight, and a remarked CAT gage; and revising the Rotorcraft Flight Manual to remove the reference to leaning the engine. This amendment is prompted by a report from the Civil Aviation Authority of Great Britain that cautioned that the mixture control could inadvertently be placed in the idle cutoff position during in-flight manual leaning of the fuel/air mixture in the carburetor of the Lycoming 0-360-J2A engine. The actions specified by this AD are intended to prevent inadvertent placement of the mixture control to the idle cutoff position during in-flight leaning of the engine, which could result in an engine shutdown and subsequent loss of control of the helicopter.
AD 97-26-02 · published Dec 16, 1997, effective Dec 31, 1997
Eurocopter Deutschland GmbH (ECD) Model BO-105A, BO-105C, BO-105S, BO-105LS A-1, and BO-105LS A-3 Helicopters and Eurocopter Canada Ltd. Model BO-105LS A-3 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter Deutschland GmbH (ECD) (Eurocopter Deutschland) Model BO-105A, BO-105C, BO-105S, BO-105LS A-1, and BO- 105LS A-3 helicopters; and Eurocopter Canada Ltd. Model BO-105LS A-3 helicopters. This action requires visual inspections for cracks in the ribbed area of the main rotor mast flange (flange). This amendment is prompted by a report of an operator discovering a crack in the flange after experiencing in-flight vibrations. The actions specified in this AD are intended to detect cracks in the flange, which, if not detected, could result in failure of the flange and subsequent loss of control of the helicopter.
AD 97-26-03 · published Dec 16, 1997, effective Dec 31, 1997
Eurocopter Deutschland GmbH (ECD) (Eurocopter Deutschland) 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) that is applicable to Eurocopter Deutschland Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters. This action requires visual inspections for cracks in the ribbed area of the main rotor mast flange (flange). This amendment is prompted by one report of cracks in a flange. The actions specified in this AD are intended to detect cracks in the flange, which, if not detected, could result in failure of the flange and subsequent loss of control of the helicopter.
AD 97-26-09 · published Dec 17, 1997, effective Jan 2, 1998
Agusta S.p.A. Model A109K2 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A (Agusta) Model A109K2 helicopters. This action requires inspecting the Gleason crown on the main transmission for cracks, and replacing the Gleason crown with an airworthy Gleason crown if any crack is found. This amendment is prompted by three reports of fatigue cracks found in the Gleason crown. The actions specified in this AD are intended to prevent failure of the Gleason crown, failure of the main transmission and subsequent loss of control of the helicopter.
AD 97-26-18 · published Dec 19, 1997, effective Jan 5, 1998
Eurocopter France Model SA-360C Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA-360C helicopters. This action requires replacement of the main gear box (MGB) input bevel pinion (bevel pinion). This amendment is prompted by service reports of bevel pinion fatigue cracking. This condition, if not corrected, could result in failure of the MGB and a subsequent forced landing.
AD 97-20-13 · published Dec 29, 1997, effective Dec 29, 1997
Eurocopter Deutschland GmbH Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-20-13 which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland Model EC135 P1 and T1 helicopters by individual letters. This amendment is prompted by the discovery of cracks on the stator blades of the fenestron tail rotor (tail rotor). The actions specified by this AD are intended to prevent failure of the tail rotor and subsequent loss of control of the helicopter.
AD 97-25-08 · published Dec 8, 1997, effective Jan 2, 1998
General Electric Company CJ610 Series Turbojet and CF700 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CJ610 series turbojet and CF700 series turbofan engines. This action requires removal from service of possibly defective turbine torque rings and compressor drive shafts which may have been manufactured from contaminated material; and replacement with serviceable parts. This amendment is prompted by a report of a cooling plate removed from a GE CT58 series engine that was found to have an iron-rich inclusion that came from a contaminated heat lot. Parts on GE CJ610 series and CF700 series engines which were manufactured from the same and similar heat lots may also be contaminated. The actions specified in this AD are intended to prevent turbine torque ring or compressor drive shaft failure due to a manufacturing defect, which could result in an uncontained engine failure.
AD 97-25-09 · published Dec 8, 1997, effective Dec 23, 1997
Allison Engine Company Model 250-C40B Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company Model 250-C40B turboshaft engines. This action requires installation of a placard requiring pilots to record torque level and time in service operating above 86% engine torque until the defective parts have been replaced, no later than December 31, 2000, or when certain maintenance actions are accomplished, or when certain operational restrictions are exceeded, whichever occurs earliest. This amendment is prompted by a report from Allison Engine Company of a manufacturing defect in certain helical power takeoff gearshaft assemblies, identified by serial numbers. The actions specified in this AD are intended to prevent fatigue failure of the helical power takeoff gearshaft assembly, which could result in a loss of engine power and inflight engine shutdown.
AD 97-25-10 · published Dec 8, 1997, effective Jan 12, 1998
Pratt & Whitney JT9D Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT9D series turbofan engines, that currently requires initial and repetitive eddy current inspection (ECI) or fluorescent penetrant inspection (FPI) for cracks in first stage high pressure turbine (HPT) disk cooling air holes. This amendment requires initial and repetitive FPI for cracks in cooling air holes of additional first stage HPT disks, and replacement with serviceable parts. In addition, this amendment requires initial and repetitive FPI for cracks in tie bolt holes of certain other affected second stage HPT disks installed in PW JT9D series turbofan engines. This amendment is prompted by reports of a cracked cooling air hole on one first stage HPT disk, and a cracked tie bolt hole on one second stage HPT disk. The actions specified by this AD are intended to prevent turbine disk failure due to cooling air hole or tie bolt hole cracking, which could result in an uncontained engine failure and damage to the aircraft.
AD 97-26-17 · published Dec 19, 1997, effective Jan 23, 1998
Teledyne Continental Motors IO-360, TSIO-360, LTSIO-360, IO-520, LIO-520, TSIO-520, LTSIO-520 Series, and Rolls-Royce plc IO-360 and TSIO-360 Series Reciprocating Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Teledyne Continental Motors (TCM) IO-520 and TSIO-520 series reciprocating engines, that currently requires ultrasonic inspection for subsurface fatigue cracks in crankshafts installed in TCM IO-520 and TSIO-520 series engines and replacement of the crankshaft if a crack is found. This amendment adds a requirement to remove crankshafts manufactured using the airmelt process and replace them with crankshafts manufactured using the vacuum arc remelt (VAR) process, incorporates new ultrasonic inspection criteria in the AD, adds engine series TCM IO-360, TSIO-360, LTSIO-360, IO-520, LIO- 520, TSIO-520, LTSIO-520 and Rolls-Royce, plc IO-360 and TSIO-360 to the applicability, and revises the economic impact analysis. This amendment is prompted by reports of crankshaft failures due to subsurface fatigue cracking on engines that had been inspected in accordance with the current AD. The actions specified by this AD are intended to prevent crankshaft failure and subsequent engine failure.
