51 Airworthiness Directives: 40 airplane, 1 rotorcraft, 6 engine, 1 appliance, 3 glider.
AD 98-14-04 · published Jul 1, 1998, effective Aug 5, 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 modification of the lever assembly of the roll disconnect system. This amendment is prompted by mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent uncommanded disconnects of the roll control system, which could result in a limited degree of roll control and consequent reduced controllability of the airplane.
AD 98-14-05 · published Jul 1, 1998, effective Aug 5, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires modification of the ground cooling fan. 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 ground cooling fan, which could result in smoke in the flight deck and cabin and consequent inability of the flight crew to perform duties or possible passenger injury due to smoke inhalation.
AD 98-14-06 · published Jul 1, 1998, effective Aug 5, 1998
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes. This amendment requires repetitive inspections for discrepancies of the spring strut assembly of the forward door of the main landing gear (MLG), and replacement of the existing spring strut assembly with a new or serviceable part, if necessary. This amendment also requires eventual replacement of the existing spring strut assembly with an improved part, which, when accomplished, terminates 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 failure of the spring strut assembly of the forward door of the MLG, which, if not corrected, could result in inability to extend the MLG.
AD 98-14-07 · published Jul 1, 1998, effective Aug 16, 1998
Cessna Aircraft Company Model 172R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company Model 172R airplanes. This AD requires modifying the lower forward doorpost bulkhead by installing rivets. This AD is the result of a report from the manufacturer that these rivets were erroneously omitted during manufacture of some of the new production airplanes. The actions specified by this AD are intended to prevent reduced structural rigidity at the forward doorpost bulkhead, which could result in structural cracking and possible loss of control of the airplane.
AD 98-14-09 · published Jul 2, 1998, effective Jul 17, 1998
Boeing Model 737-100, -200, -200C Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, and -200C series airplanes. This action requires repetitive inspections to detect fatigue cracking and certain discrepancies of the forward engine mount support (FEMS) fitting and its attachments, and repair, if necessary. This amendment is prompted by reports of fatigue cracks on the lower flange of the FEMS fitting, broken bolts and bolts with loose or detached nuts on the upper inboard attachment of the FEMS fitting, and cracked or severed lugs at the outboard support link attachment of the FEMS fitting. The actions specified in this AD are intended to detect and correct fatigue cracking and certain discrepancies of the FEMS fitting and its attachments, which could result in an in-flight separation of an engine.
AD 98-14-10 · published Jul 7, 1998, effective Jul 22, 1998
Boeing Model 747-400, 757, 767, and 777 Series Airplanes Equipped with AlliedSignal RIA-35B Instrument Landing System Receivers
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-400, 757, 767, and 777 series airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to prohibit certain types of approaches if only one instrument landing system (ILS) receiver is operational. This action also requires repetitive inspections to detect certain faults of all RIA-35B ILS receivers, and replacement of discrepant ILS receivers with new, serviceable, or modified units; or, alternatively, an additional revision to the AFM and installation of a placard to prohibit certain operations. This AD also provides for optional terminating action for the AFM revisions and repetitive inspections. This amendment is prompted by a report of errors in the glide slope deviation provided by an ILS receiver. The actions specified in this AD are intended to detect and correct faulty ILS receivers, and to ensure that the flightcrew is advised of the potential hazard of performing ILS approaches using a localizer deviation from a faulty ILS receiver and also advised of the procedures necessary to address that hazard. Erroneous localizer deviation could result in a landing outside the lateral boundary of the runway.
AD 98-14-14 · published Jul 7, 1998, effective Aug 11, 1998
Turbopropeller-Powered McDonnell Douglas Model DC-3 and DC-3C Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-3 and DC-3C series airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 98-14-15 · published Jul 7, 1998, effective Aug 11, 1998
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes, and Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, and Model F27 Mark 050 series airplanes, that requires revising the Airplane Flight Manual 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 caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 98-14-11 · published Jul 8, 1998, effective Aug 12, 1998
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections for discrepancies of the lock bolt for the pintle pin on the main landing gear (MLG), and follow-on 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 a rotated, damaged, or missing lock bolt, which could result in disengagement of the pintle pin from the bearing, and consequent collapse of the MLG during landing.
AD 98-14-12 · published Jul 8, 1998, effective Aug 12, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time visual inspection to detect cracking in the axle adapter of the shock absorber of the nose landing gear (NLG), 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 correct cracking in the axle adapter of the shock absorber of the NLG, which could result in failure of the NLG and consequent damage to the airplane structure.
AD 98-14-13 · published Jul 8, 1998, effective Aug 12, 1998
Airbus Model A300, A310, A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes. This amendment requires a one-time operational test and repetitive functional tests of the free fall control mechanism of the landing gear to ensure proper release of the main landing gear (MLG), and corrective action, if necessary. This amendment also requires eventual modification of the free fall control mechanism of the landing gear, which constitutes terminating action for the repetitive functional tests. 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 malfunction of the free fall control mechanism of the landing gear, which could result in the inability to extend the MLG in the event of failure of the hydraulic extension system.
AD 98-14-17 · published Jul 8, 1998, effective Jul 23, 1998
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires disconnection of the electrical connector to the scavenge pump of the center wing tank. That AD also requires a one-time inspection to identify the part number of the electrical connector; and replacement of the pump with a new or serviceable pump, if necessary. This amendment requires a one-time inspection to identify the part number of the scavenge pump motor-impeller unit; and corrective action, if necessary. This amendment is prompted by a report of damage to the internal wiring of a scavenge pump that had been replaced in accordance with the existing AD. 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 98-14-16 · published Jul 9, 1998, effective Jul 24, 1998
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes. This action requires repetitive inspections to detect cracks in the forward canted frames between fuselage frames 47a and 48 from stringer (STGR) 41 to STGR 43; and temporary repair, or replacement of the forward canted frame with a new frame, 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 forward canted frames, which could result in failure of the forward canted frame, and consequent reduced structural integrity of the airplane.
AD 98-15-01 · published Jul 15, 1998, effective Aug 19, 1998
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires a one-time inspection to detect bulging or cracking of the pitot 1 and pitot 2 drain tubes in the forward electronic compartment; and cleaning the tubes or replacing drain tubes with new tubes, if necessary. This amendment also requires modification of the pitot/ static system. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct bulging and cracking of the pitot 1 and pitot 2 drain tubes in the forward electronic compartment caused by cycles of water freezing and expanding inside the tubes, which could result in erroneous airspeed indications to the flight crew and reduced operational safety in all phases of flight.
AD 98-15-04 · published Jul 15, 1998, effective Aug 19, 1998
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections for fatigue cracking of the bottom flanges of the longitudinal floor beams at frame 43; and repair, if necessary. This amendment also requires a one-time inspection for fatigue cracking of the fastener holes in the longitudinal floor beams, and modification of the floor beams, which constitutes terminating action for 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 fatigue cracking on the bottom flanges of the longitudinal floor beams, which could result in reduced structural integrity of the airplane.
AD 98-15-06 · published Jul 16, 1998, effective Aug 20, 1998
Airbus Model A320 and Model A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and Model A321 series airplanes, that requires repetitive inspections to verify proper installation of the plain bushings of the upper and lower connection links on the forward and aft passenger/crew doors, and correction of discrepancies. This amendment also requires installation of shouldered bushings on the frame segment used for attachment of the connection links or modification of the frame segment bushing (as applicable), which terminates the repetitive inspection requirements. This amendment is prompted by a report that, during an emergency evacuation of in- service airplanes, the left aft passenger/crew door jammed against the fuselage structure in a nearly closed position due to bushing migration. The actions specified by this AD are intended to prevent jamming of the passenger/crew door, which could delay or impede the evacuation of passengers during an emergency.
AD 98-15-07 · published Jul 16, 1998, effective Aug 20, 1998
Dassault Model Mystere-Falcon 50 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 series airplanes, that requires installation of a reinforcement fitting at the junction of the baggage floor and frame 35 on both the left- and right- hand sides of the airplane. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking in the subject area, which could result in reduced structural integrity of the airframe.
AD 98-15-08 · published Jul 16, 1998, effective Aug 20, 1998
British Aerospace Model BAe 146 and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes, that requires repetitive detailed visual inspections of the top wing skins for stress corrosion cracks, damage, or missing surface protective finish of the metallic surfaces; and repair, if necessary. This amendment is prompted by reports of stress corrosion cracks found on the top wing skin during routine inspection on three airplanes. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural integrity of the wing.
AD 98-15-09 · published Jul 16, 1998, effective Jul 31, 1998
Airbus Model A320-111 and -211 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 and -211 series airplanes. This action requires repetitive inspections to detect fatigue cracking of the frames of the sliding windows in the cockpit, 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 fatigue cracking of the frames of the sliding windows in the cockpit, which could result in reduced structural integrity of the pressure vessel of the fuselage of the airplane.
AD 98-15-10 · published Jul 16, 1998, effective Aug 20, 1998
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires modification of the detachable center inlet component of the air intake system of the engine. 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 and/or oil that may be present in the nacelle from entering the air intake system of the engine, which could result in a possible engine fire.
AD 98-15-12 · published Jul 16, 1998, effective Aug 20, 1998
Aerospatiale Model ATR42 and ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42 and ATR72 series airplanes, that requires a one-time inspection of the electromagnetic interference (EMI) filter capacitors and electronic cards of the cabin air recirculation fans to detect damage. This amendment also requires replacement of damaged components with new or serviceable parts, and modification of the cabin air assembly fans. 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 overheating and consequent failure of the EMI filter capacitors, which could result in emission of toxic smoke and fumes throughout the airplane, and consequent adverse effects on flight crew and passengers.
AD 98-15-13 · published Jul 16, 1998, effective Aug 28, 1998
Raytheon Aircraft Company 90, 100, 200, and 300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 90, 100, 200, and 300 series airplanes (formerly known as Beech Aircraft Corporation 90, 100, 200, and 300 series airplanes). This AD requires: checking the airplane maintenance records from January 1, 1994, up to and including the effective date of this AD, for any MIL-H-6000B fuel hose replacements on the affected airplanes; inspecting any replaced rubber fuel hose for a spiral or diagonal external wrap with a red stripe the length of the hose with 94519 printed along the stripe; and replacing any MIL-H-6000B rubber fuel hose matching this description with an FAA-approved hose having a criss-cross or braided external wrap. This AD was prompted by a report of a product defect by the manufacturer that could cause fuel system blockage and engine stoppage. The actions specified by this AD are intended to prevent fuel flow interruption, which could lead to uncommanded loss of engine power and loss of control of the airplane.
AD 98-15-11 · published Jul 17, 1998, effective Aug 21, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacing the existing roll spoiler control rods with improved parts. 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 bending stress to the fork end of the roll spoiler, which could result in failure of the roll spoiler and consequent reduced controllability of the airplane.
AD 98-15-14 · published Jul 17, 1998, effective Aug 3, 1998
McDonnell Douglas Model MD-11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a revision of the Airplane Flight Manual (AFM) to alert the flightcrew that both flight management computers (FMC's) must be installed and operational. That AD also requires an inspection to determine the serial number of the FMC's; and follow-on corrective actions, if necessary, which terminate the AFM revision. That amendment was prompted by a report indicating that, due to incorrect multiplexers that were installed in the FMC's during production, certain data busses failed simultaneously during a ground test. This amendment removes the terminating action from the existing AD. The actions specified in this AD are intended to prevent loss of airspeed and altitude indications on both primary flight displays in the cockpit, and/or loss or degradation of the autopilot functionality due to installation of incorrect multiplexers, and consequent failure of the data busses.
AD 98-15-15 · published Jul 21, 1998, effective Aug 25, 1998
McDonnell Douglas Model DC-9, DC-9-80, and C-9 (Military) Series Airplanes, and Model MD-88 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that currently requires an inspection to detect chafing on the FIREX pipe assembly of the number one engine; and either repair of chafed pipe assemblies or replacement of the chafed pipe assemblies with new pipe assemblies; and modification of the FIREX and the pneumatic sense pipe assembly clamp marriage. This amendment revises the applicability of the existing AD to include additional airplanes and remove others. This amendment is prompted by reports of incidents in which the pneumatic sense pipe chafed against the FIREX supply pipe of the number one engine. The actions specified by this AD are intended to prevent chafing of the FIREX supply pipe, which could result in a hole in the pipe and consequently prevent the proper distribution of the fire extinguishing agent within the nacelle in the event of a fire.
AD 98-15-18 · published Jul 21, 1998, effective Sep 9, 1998
Maule Aerospace Technology Corp. M-4, M-5, M-6, M-7, MX-7, and MXT-7 Series Airplanes and Models MT-7-235 and M-8-235 Airplanes
This amendment supersedes Airworthiness Directive (AD) 95-26- 18, which currently requires inspecting (one-time) certain wing lift struts for internal corrosion on certain Maule Aerospace Technology Corp. (Maule) M-4, M-5, M-6, M-7, MX-7, and MXT-7 series airplanes and Models MT-7-235 and M-8-235 airplanes, and replacing any wing lift strut where corrosion is found. That AD was the result of an accident where the wing separated from one of the affected airplanes. This AD retains the initial inspection and possible replacement requirements of AD 95-26-18, requires the inspections to be repetitive, and provides the option of using ultrasonic procedures to accomplish the inspection requirements. The actions specified by this AD are intended to prevent failure of the wing lift struts caused by corrosion damage, which could eventually result in the wing separating from the airplane.
AD 98-15-21 · published Jul 23, 1998, effective Aug 27, 1998
Boeing Model 747-100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100 series airplanes, that currently requires repetitive inspections to detect cracking of the wing front spar web above engine numbers 2 and 3, and to detect cracked or broken fasteners in the web; and repair, if necessary. That AD also provides an optional terminating action for the repetitive inspections. This amendment requires various improved inspections. This amendment is prompted by a report indicating that the existing inspections do not adequately detect vertical cracks. The actions specified by this AD are intended to prevent fuel leakage onto an engine and a resultant fire due to cracked or broken fasteners in the wing front spar.
AD 98-15-22 · published Jul 23, 1998, effective Aug 27, 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 a one-time inspection for delamination, erosion, and condition of fillet sealant and conductive edge sealer of the wing and empennage leading edge area behind the de-ice boots, and follow-on corrective actions. 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 delamination of the wing and empennage leading edge due to improper installation of the wing de-ice boot, which could result in reduced controllability of the airplane.
AD 98-16-03 · published Jul 29, 1998, effective Sep 21, 1998
SOCATAGroupe AEROSPATIALE Models TB9 and TB10 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (Socata) Models TB9 and TB10 airplanes. This AD requires repetitively inspecting the wing front attachments on the wing and fuselage sides for cracks, and repetitively incorporating a certain modification kit (type of kit and time of incorporation depends on whether cracks are found during the inspection). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural failure of the wing front attachments caused by fatigue cracking, which could result in the wing separating from the airplane if the airplane is operated with cracked wing front attachments over an extended period of time.
AD 98-16-04 · published Jul 29, 1998, effective Sep 21, 1998
Cessna Aircraft Company 180, 182, and 185 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) 180, 182, and 185 series airplanes that have wing extension supplemental type certificate (STC) SA00276NY or supplemental type approval (STA) SA93-136 incorporated. This AD requires inspecting between wing station (W.S.) 90 and W.S. 110 for an angle stiffener at the lower wing spar splice. If the angle stiffener is not installed, this AD requires installing a reinforcing strap. This AD is the result of failed test results revealing that the wings of these Cessna airplanes, without the stiffener, do not meet the applicable design requirements after being modified by the above STC. The actions specified by this AD are intended to prevent wing failure during flight caused by the absence of an angle stiffener, which could cause loss of control of the airplane.
AD 98-16-01 · published Jul 30, 1998, effective Aug 14, 1998
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires repetitive inspections to measure for free play (wear on nut assembly) of the horizontal stabilizer actuator assembly, and corrective actions, if necessary. This amendment is prompted by reports of wear of the horizontal stabilizer actuator assembly due to a jackscrew surface finish that was manufactured incorrectly. The actions specified in this AD are intended to prevent excessive free play and wear of the horizontal stabilizer actuator assembly, which could result in a free-floating horizontal stabilizer, and consequent loss of aircraft pitch control.
AD 98-11-01 R2 · published Jul 31, 1998, effective Sep 22, 1998
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment clarifies information contained in Airworthiness Directive (AD) 98-11-01 R1, which currently requires replacing the fuel tank vent valves and drilling a 4.8 millimeter (0.1875 inch) hole in each fuel filler cap on certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 98-11-01 R1 also requires inserting a temporary revision in the Pilot's Operating Handbook (POH) that specifies checking to assure that the fuel filler cap hole is clear of ice and foreign objects. The intent of AD 98-11-01 R1 was to provide the option of incorporating new modified fuel tank vent valves instead of the replacement, drilling, and POH insertion requirements. The new modified vent valves cannot be incorporated without removing the fuel tank vent valves installed as originally required by AD 97-23-04 and carried over in the current AD. This provision of removing those vent valves is currently not provided for. This document clarifies and corrects this procedure. The actions specified in this AD are intended to continue to prevent moisture from entering the fuel tank inward vent valve and then freezing after a cold soak at altitude, which could result in wing airfoil distortion and structural damage with consequent degradation of the airplane's handling qualities.
AD 98-15-51 · published Jul 31, 1998, effective Aug 5, 1998
Airbus Model A319, A320, A321, A300, A310, A300-600, A330, and A340 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-15-51 that was sent previously to all known U.S. owners and operators of all Airbus Model A319, A320, A321, A300, A310, A300-600, A330, and A340 series airplanes by individual telegrams. This AD requires an initial and repetitive in- flight operational checks of the alternate braking system, and replacement of the braking dual distribution valve (BDDV) with a serviceable part, if necessary. This action 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 alternate braking system, which could result in the airplane overrunning the end of the runway during landing.
AD 98-16-05 · published Jul 31, 1998, effective Sep 4, 1998
Airbus Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires inspections of the areas behind the scuff plates below the passenger/ crew doors and bulk cargo door to detect cracks and corrosion, and repair, if necessary. This amendment also requires inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, this amendment provides for optional terminating action for certain inspections. This amendment is prompted by reports indicating that corrosion was found behind the scuff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. The actions specified by this AD are intended to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings.
AD 98-16-06 · published Jul 31, 1998, effective Sep 4, 1998
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires inspections of the lower door surrounding structure to detect cracks and corrosion, and repair, if necessary. This amendment also requires inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, this amendment provides for optional terminating action for certain inspections. This amendment is prompted by reports indicating that corrosion was found between the scuff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. The actions specified by this AD are intended to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings.
AD 98-16-07 · published Jul 31, 1998, effective Sep 4, 1998
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections to detect corrosion or plating cracks of the pin assemblies in the forward trunnion support of the main landing gear (MLG), and replacement of the pin assembly with a new assembly, if necessary. Such replacement, if accomplished, constitutes terminating action for the repetitive inspections. This amendment is prompted by reports indicating that these pin assemblies were found to have corroded as a result of plating cracks. The actions specified by this AD are intended to detect and correct such corrosion and plating cracks, which could cause breakage of these assemblies, and consequent collapse of the MLG.
AD 98-16-08 · published Jul 31, 1998, effective Sep 4, 1998
Airbus Model A300-600 and A310 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to instruct the flightcrew to cross-check certain primary power setting parameters of the Thrust Control Computer (TCC) against tables of these values; and apply corrective action, if necessary. That AD also provides for optional terminating action for the AFM revisions. This amendment requires accomplishment of the previously optional terminating action. 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 incorrect primary power setting parameters of the TCC, which could result in insufficient thrust being applied during takeoff.
AD 98-16-09 · published Jul 31, 1998, effective Sep 4, 1998
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires a one-time operational test of the fire shut- off valves (FSOV's) to determine if the FSOV's are functioning correctly, and replacement of failed parts with new or serviceable parts. 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 FSOV's to close, which could result in failure of the engine fire shut- off system, and consequent inability to extinguish an engine fire.
AD 98-16-10 · published Jul 31, 1998, effective Sep 4, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires revising the Airplane Flight Manual (AFM) to require use of the electrical fuel pump for take-off and landing and performance of an operational check of the electrical fuel pump following landing. This amendment also requires replacement of the jet booster pumps with new or modified jet booster pumps, which terminates the requirement for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the jet booster pumps, which could result in reduced engine thrust during take-off or landing, and consequent increased risk of impact with terrain.
AD 98-16-11 · published Jul 31, 1998, effective Sep 4, 1998
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive detailed visual inspections to detect cracks in the pylon thrust and sideload fitting of the wing, and replacement of any cracked pylon thrust and sideload fitting with a new fitting. 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 cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane.
AD 98-15-26 · published Jul 23, 1998, effective Aug 3, 1998
McDonnell Douglas Helicopter Systems Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, 600N, and OH-6A Helicopters
This amendment supersedes an existing priority letter Airworthiness Directive (AD) 98-03-15, applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, 600N, and OH-6 helicopters that currently requires an inspection for main rotor blade (blade) cracks and for missing or cracked adhesive or paint. This amendment requires the same inspections required by the existing priority letter AD but deletes the Model 369 (Army YOH-6A), specifies recording torque events (TE), and establishes a shorter retirement life for certain blades. This amendment is prompted by an accident in which a blade failed on a Model 369D helicopter due to fatigue cracks. The actions specified by this AD are intended to detect cracks that could lead to failure of the blade and subsequent loss of control of the helicopter.
AD 98-14-02 · published Jul 1, 1998, effective Aug 31, 1998
Pratt & Whitney Canada PW100 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney Canada (PWC) PW100 series turboprop engines, that requires removal of the existing fuel manifold tubes, lock plates, and preformed packing; installation of improved fuel manifold transfer tubes, improved lock plates, and improved preformed packing; and, after installation, the performance of a leak check. This amendment is prompted by reports of engine fuel leaks which resulted in either inflight engine shutdowns or fire warnings. The actions specified by this AD are intended to prevent engine fuel leaks, which can result in inflight engine shutdowns or fire warnings.
AD 97-25-10 R1 · published Jul 14, 1998, effective Jul 29, 1998
Pratt & Whitney JT9D Series Turbofan Engines
This amendment revises an existing airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT9D series turbofan engines, that currently requires initial and repetitive fluorescent penetrant inspections (FPI) for cracks in cooling air holes of first stage high pressure turbine (HPT) disks, and replacement of cracked disks with serviceable parts. In addition, the current AD 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 calls out the second stage HPT hub assembly by part number (P/N) in addition to the hub P/N for clarification of affected parts, and references a service bulletin that does not change any of the requirements in the AD, but better explains the inspection procedures that are referenced in the current AD. This amendment also increases the repetitive inspection interval of first stage HPT disks. This amendment is prompted by the need to clarify the inspection procedures and the parts affected by this AD and by a re- evaluation of the risk analysis, based on new data from service, to establish a new repetitive inspection interval for the first 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 98-15-02 · published Jul 14, 1998, effective Jul 29, 1998
Rolls-Royce Limited, Aero Division- Bristol, S.N.E.C.M.A, Olympus 593 Series Turbojet Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A. Olympus 593 series turbojet engines. This action requires identifying reduced post-rebroaching cyclic life limits for certain rebroached stage 6 high pressure compressor (HPC) disks, inspecting the rebroached disks for cracks, and, if necessary, removing from service cracked disks. This amendment is prompted by reports of the low cyclic lives at which some rebroached stage 6 HPC disks have been found cracked. The actions specified in this AD are intended to prevent rebroached stage 6 HPC disk failure, which could result in an uncontained engine failure and damage to the aircraft.
AD 98-15-03 · published Jul 14, 1998, effective Jul 29, 1998
General Electric Company GE90 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) GE90 series turbofan engines. This action requires initial and repetitive eddy current inspections (ECI) for cracks in the high pressure compressor (HPC) stage 2-6 spool, and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracks in the stage 3-4 and stage 4-5 interstage seal teeth and spacer arms. The actions specified in this AD are intended to identify cracks in the HPC stage 2-6 spool, which could result in an uncontained engine failure and damage to the aircraft.
AD 98-15-16 · published Jul 23, 1998, effective Aug 7, 1998
Bombardier-Rotax GmbH 912 F Series Reciprocating Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Bombardier-Rotax GmbH 912 F series reciprocating engines. This action requires installation of an improved fuel pump and fuel supply tube. This amendment is prompted by reports of fuel leaks at the outlet port of the fuel pump. The actions specified in this AD are intended to prevent fuel leaks from the fuel pump, which could result in undetected loss of fuel in flight or, an engine fire.
AD 98-15-17 · published Jul 23, 1998, effective Aug 7, 1998
General Electric Company CF6-80A3 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-80A3 series turbofan engines. This action requires initial and repetitive on-wing borescope inspections of the left hand aft mount link assembly for cracks, bearing migration, and bearing race rotation, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of a fractured left hand aft mount link discovered during a scheduled engine removal. The actions specified in this AD are intended to prevent left hand aft mount link failure, which can result in adverse redistribution of the aft mount loads and possible aft mount system failure.
AD 98-14-03 · published Jul 1, 1998, effective Aug 16, 1998
AlliedSignal Inc. KT 76A Air Traffic Control (ATC) Transponders
This amendment adopts a new airworthiness directive (AD) that applies to certain AlliedSignal Inc. (AlliedSignal) KT 76A ATC transponders that are installed on aircraft. This AD requires incorporating a modification on the affected transponders that consists of replacing two resistor network modules with glass-coated modules. This AD is the result of reports of these ATC transponders transmitting misleading encoding altimeter information to ground-based ATC radar sites and nearby Traffic Alert and Collision Avoidance System (TCAS)- equipped aircraft. The actions specified by this AD are intended to prevent the transmission of misleading encoding altimeter information between affected aircraft caused by the inability of these ATC transponders to coordinate with ground-based ATC radar sites and nearby TCAS-equipped aircraft.
AD 98-15-19 · published Jul 22, 1998, effective Sep 7, 1998
Aeromot-Industria Mecanico Metalurgica Ltda. Model AMT-200 Powered Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain Aeromot-Industria Mecanico Metalurgica Ltda. (Aeromot) Model AMT-200 powered gliders. This AD requires replacing certain flexible hoses in the engine oil system with flexible hoses with a larger internal diameter. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Brazil. The actions specified by this AD are intended to prevent inefficiency of the engine lubricating system because of ineffective flexible hoses, which could result in an in-flight engine shutdown with consequent loss of powered glider controllability.
AD 98-15-20 · published Jul 22, 1998, effective Sep 9, 1998
Glaser-Dirks Flugzeugbau GmbH Model DG- 500M Gliders
This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG- 500M gliders. This AD requires inspecting the center of gravity (C.G.) tow release cable pulley for correct positioning, and replacing the C.G. tow release cable pulley with one made of aluminum either immediately or eventually depending on the results of the inspection. 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 C.G. tow release cable from coming off the pulley because of incorrect positioning, which could result in the pilot being unable to release from tow operations.
AD 98-15-24 · published Jul 23, 1998, effective Sep 15, 1998
Stemme GmbH & Co. KG Model S10-V Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Model S10-V sailplanes. This AD requires replacing the propeller blade suspension forks with parts of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent propeller suspension fork failure caused by design deficiency, which could result in loss of a propeller blade and loss of sailplane controllability.
