77 Airworthiness Directives: 62 airplane, 1 rotorcraft, 10 engine, 1 appliance, 3 glider.
AD 98-18-14 · published Sep 2, 1998, effective Sep 17, 1998
Boeing Model 757-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200 series airplanes. This action requires a one-time detailed visual inspection to detect damage or chafing of certain electrical wire bundles, and to verify adequate clearance exists between the wire bundles and adjacent disconnect bracket; and repair, if necessary. This amendment is prompted by a report indicating that damaged wires caused an electrical short in the electrical panel, which resulted in a shower of sparks from the overhead panel. The actions specified in this AD are intended to prevent failure of essential electrical systems and a potential fire hazard for passengers and crewmembers, due to damage or chafing of electrical wire bundles.
AD 94-13-02 R1 · published Sep 3, 1998, effective Sep 18, 1998
Boeing Model 757-200, -200PF, and - 200CB Series Airplanes Equipped with Rolls-Royce Model RB211-535E4/E4B Engines
This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires tests of the thrust reverser system, and repair, if necessary; installation of a modification that terminates those tests; and repetitive operational checks of that installation, and repair, if necessary. This amendment limits the applicability of the existing AD by including the specific series of the affected airplanes. This amendment is prompted by the upcoming type certification of the Model 757-300 series airplane, which will address the requirements of this amendment during the type certification process. The actions specified in this AD are intended to prevent deployment of a thrust reverser in flight and subsequent reduced controllability of the airplane.
AD 98-18-13 · published Sep 3, 1998, effective Oct 24, 1998
SOCATAGroupe AEROSPATIALE Models TB20 and TB21 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (Socata) Models TB20 and TB21 airplanes. This AD requires repetitively inspecting the main landing gear (MLG) attachment bearing (using a dye penetrant method) for cracks, and if cracks are found, replacing the bearing. 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 detect and correct cracks in the MLG attachment bearing, which could result in collapse of the main landing gear during taxi and landing operations.
AD 98-18-15 · published Sep 3, 1998, effective Sep 18, 1998
Gulfstream Model G-V Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires a one-time inspection to measure the clearance between a certain wiring harness and the crew oxygen bottle; corrective actions, if necessary; and eventual relocation of the crew oxygen bottle and rework of the lines and tubing associated with the crew and passenger oxygen bottles. This amendment is prompted by a report indicating that interference between the wiring harness and the crew oxygen bottle was found on a production airplane. The actions specified in this AD are intended to prevent chafing of the wiring harness against the crew oxygen bottle, which could result in electrical shorting and possible fire in the underfloor structure of the airplane.
AD 98-18-16 · published Sep 3, 1998, effective Oct 8, 1998
Airbus Model A320 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that currently requires reinforcement of the tail section of the fuselage at frames 68 and 69. This amendment adds a requirement for reinforcement of the tail section of the fuselage at frames 65 to 67. This action also revises the applicability of the existing AD. This amendment is prompted by reports indicating that the tail section has struck the runway during takeoffs and landings. The actions specified by this AD are intended to prevent structural damage to the tail section when it strikes the runway, which could result in depressurization of the fuselage during flight.
AD 98-18-17 · published Sep 3, 1998, effective Oct 8, 1998
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-90-30 and MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-80 series airplanes and Model MD-90-30 and MD-88 airplanes, that requires a one-time inspection of the harness assembly of the tailcone emergency evacuation slide to determine the diameter of the swaged balls; reidentification of the harness assembly; and reinstallation or replacement of the assembly with a new assembly, if necessary. This amendment is prompted by a failed deployment of the tailcone emergency evacuation slide during a system test conducted by the manufacturer. The actions specified by this AD are intended to prevent failure of the tailcone emergency evacuation slide to deploy automatically due to incorrect diameter of the swaged balls on the wire rope of the harness assembly.
AD 98-18-19 · published Sep 3, 1998, effective Sep 18, 1998
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-90-30 series airplanes. This action requires a one-time inspection of the actuator attach bolts of the elevator load feel (ELF) located under the forward cockpit floor, and corrective actions, if necessary. This amendment is prompted by a report indicating that, during manufacture of an airplane, an actuator attach bolt of the ELF was installed improperly. The actions specified in this AD are intended to ensure that the actuator attach bolts are installed properly. Improper installation of such bolts could result in disconnection of the ELF mechanism, and consequent loss of pitch control of the airplane.
AD 98-18-26 · published Sep 8, 1998, effective Oct 13, 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 to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. This amendment also provides for an optional 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 detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in reduced structural integrity of the airframe.
AD 98-19-05 · published Sep 10, 1998, effective Oct 15, 1998
Boeing Model 757-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires the application of a sealant, secondary fuel barrier, and corrosion-inhibiting compound to certain portions of the wing center section. This amendment is prompted by reports indicating that, during manufacture, the secondary fuel barrier was not applied to certain portions of the wing center section. The actions specified by this AD are intended to prevent leakage of fuel through the fasteners, sealant, or structural cracks in the center section structure, which could result in fuel or fuel vapors entering the cargo or passenger compartment of the airplane.
AD 98-19-06 · published Sep 10, 1998, effective Oct 15, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacing the radio tuning units (RTU's) and associated components with new, 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 NAV/COM radios from simultaneously changing tuned frequencies and transponder codes due to a black screen failure or ``blanking'' of an RTU, which could result in loss of communications capability and air traffic control data.
AD 98-19-07 · published Sep 10, 1998, effective Oct 15, 1998
Airbus Model A320-111, -211, and -231 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires modification of certain fastener holes on the outer frames of the fuselage, and installation of new, improved fasteners. 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 of certain fastener holes on the outer frames of the fuselage, which could result in reduced structural integrity of the airplane.
AD 98-18-22 · published Sep 15, 1998, effective Oct 20, 1998
McDonnell Douglas Model DC-9-10, -15, and -30 Series Airplanes, and C-9 (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -15, and -30 series airplanes, and C-9 (military) airplanes, that requires a one- time visual inspection to determine if all corners of the upper cargo doorjamb have been previously modified; various follow-on repetitive inspections; and modification, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners of the upper cargo doorjamb. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
AD 98-18-23 · published Sep 15, 1998, effective Oct 20, 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 repetitive high frequency eddy current (HFEC) inspections to detect cracking on all surfaces of the upper recesses in certain latch support fittings of the cargo doorway, and replacement of cracked fittings with new fittings. The existing AD also provides for optional terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by reports indicating that the repetitive inspections required by the existing AD may not detect cracked fittings in a timely manner. The actions specified by this AD are intended to prevent the cargo door from opening while the airplane is in flight, which could result in rapid decompression of the airplane.
AD 98-18-24 · published Sep 15, 1998, effective Oct 20, 1998
Airbus Industrie Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect cracking in the inner flange of door frame 66, and corrective actions, if necessary. This amendment also provides for an optional 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 correct fatigue cracking in the inner flange of door frame 66, which could result in reduced structural integrity of the airplane.
AD 98-18-25 · published Sep 15, 1998, effective Oct 20, 1998
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires replacement of certain hinges on the forward, center, and aft cargo doors with improved hinges. 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 cargo door hinges caused by stress corrosion or fatigue cracks, which could result in decompression of the airplane, and possible in-flight separation of the cargo door.
AD 98-19-16 · published Sep 15, 1998, effective Oct 20, 1998
Aerospatiale Model ATR72-212A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72-212A series airplanes, that requires installation of bushings on the lower attachment fittings of the flap support beam. 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 rupture of the lower attachment fittings of the flap support beam due to fatigue, and consequent damage to the flaps; these conditions could result in reduced controllability of the airplane.
AD 98-18-20 · published Sep 16, 1998, effective Oct 21, 1998
Boeing Model 727 and Model 737 Series Airplanes Equipped with J.C. Carter Company Fuel Valve Actuators
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and Model 737 series airplanes, that requires replacement of the actuator of the engine fuel shutoff valve and the fuel system crossfeed valve with an improved actuator. This amendment is prompted by a report indicating that, during laboratory tests, the actuator clutch on the engine fuel shutoff and crossfeed valves failed to function properly. The actions specified by this AD are intended to prevent improper functioning of these actuators, which could result in a fuel imbalance due to the inability of the flightcrew to crossfeed fuel; improperly functioning actuators also could prevent the pilot from shutting off the fuel to the engine following an engine failure and/or fire.
AD 98-19-18 · published Sep 16, 1998, effective Oct 21, 1998
Airbus Model A310, A300-600, and A320 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310, A300-600, and A320 series airplanes, that currently requires inspections to verify proper installation of the grill over the air extraction duct of the lavatory and to detect blockages in the air extraction duct of the lavatory, and correction of any discrepancies. This amendment adds a requirement for modification of the grill of the air extraction duct, which, when accomplished, terminates the repetitive inspections. This amendment also expands the applicability of the existing AD to include additional airplanes. 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 obstructions in the air extraction system of the lavatory, which may result in the failure of the smoke detection system to detect smoke in the lavatories.
AD 98-19-19 · published Sep 16, 1998, effective Oct 21, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a one-time inspection to detect discrepancies of the electrical harness of the propeller de-icing system and of the hydraulic pressure pipe from the engine driven pump (EDP); and follow- on corrective actions, if necessary. This action 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 chafing of the hydraulic pressure pipe of the EDP, which could result in charring of the hydraulic tube and consequent engine compartment fire.
AD 98-19-22 · published Sep 17, 1998, effective Oct 22, 1998
Airbus Model A310 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive visual inspections to detect corrosion on the lower rim area of the fuselage rear pressure bulkhead; and follow-on actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion at the lower rim area of the fuselage rear pressure bulkhead, which could result in reduced structural integrity of the bulkhead, and consequent decompression of the cabin.
AD 98-19-23 · published Sep 17, 1998, effective Oct 22, 1998
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires replacement of the existing mounting rack for the Digital Flight Data Recorder (DFDR) with a new rack having improved damping, and installation of a new bracket for re-routing the wiring harness. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the possible loss of data recorded on the DFDR as a result of vibrations and/or accelerations during flight.
AD 98-19-24 · published Sep 17, 1998, effective Oct 22, 1998
Boeing Model 757-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires modification of certain passenger doors. This amendment is prompted by reports that certain passenger doors could not be opened due to the escape slide shelf assembly and escape slide falling onto the girt bar lifting mechanism of the door. The actions specified by this AD are intended to prevent the escape slide shelf assembly and escape slide from falling on the girt bar of a passenger door due to failed rivets of the escape slide shelf assembly, and consequent inability to open the passenger door and to use the escape slide at that door during an emergency evacuation of the airplane.
AD 98-19-25 · published Sep 17, 1998, effective Oct 22, 1998
Boeing Model 777-200 Series Airplanes Equipped With Air Cruisers Evacuation Slide/Rafts
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires modifying the sliding surface of the door 1 left and door 1 right evacuation slide/rafts. This amendment is prompted by a report of injuries to evacuees using the slide/raft to exit the airplane; the evacuees were unable to achieve adequate initial sliding speed and adequate momentum to carry them expeditiously down the slide/raft. The actions specified by this AD are intended to prevent evacuee overload of the slide/rafts, and consequent impeded evacuation and injury to the evacuees.
AD 98-20-01 · published Sep 17, 1998, effective Oct 2, 1998
Bombardier Model CL-600-2B19 (Regional Jet Series 100) Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with revised procedures for checking the flap system. This AD also requires revising the maintenance program to provide procedures for checking the flap system, and performing follow-on actions, 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 an unannunciated failure of the flap system, which could result in a flap asymmetry, and consequent reduced controllability of the airplane.
AD 98-05-14 R1 · published Sep 18, 1998, effective Sep 22, 1998
Cessna Aircraft Company Models T210N, P210N, and P210R Airplanes
This amendment clarifies information contained in Airworthiness Directive (AD) 98-05-14, which currently requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions on certain Cessna Aircraft Company (Cessna) Models T210N, P210N, and P210R airplanes. That publication incorrectly references the possibility of certain ice accumulation on the ``lower'' surface of the wing, instead of the ``upper'' surface of the wing while operating with the flaps extended. This incorrect statement may result in pilot misinterpretation of the icing effects with the flaps extended, and lead to an incorrect action. This document replaces the word ``lower'' with ``upper'' in this sentence. The actions specified in this AD are intended to continue to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
AD 98-20-02 · published Sep 21, 1998, effective Oct 26, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires repetitive inspections to detect chafing of the hydraulic pipe on the emergency uplock release system of the main landing gear (MLG); testing of the hydraulic pipe for leaks, if necessary; and repair of the hydraulic pipe, if necessary. This amendment also requires modification of the attachment bolt and attachment hole on the structural panel, which terminates the repetitive inspection requirements of this AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing between the hydraulic pipe on the emergency uplock release system of the MLG and an attachment bolt on a structural panel, which could result in rupture of the hydraulic pipe, loss of hydraulic pressure, and consequent inability to activate the emergency MLG extension.
AD 98-20-03 · published Sep 21, 1998, effective Oct 26, 1998
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive inspections of the center joint of the main landing gear (MLG) torque link and the MLG assembly for excessive free-play; and correction, if necessary. This AD also requires installation of new MLG torque link dampers, which constitutes terminating action for the repetitive inspections; and revision of the FAA-approved maintenance program to incorporate inspections and overhaul of the new torque link dampers. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the failure of MLG torque links, which could result in reduced controllability of the airplane on the ground during takeoff or landing.
AD 98-20-04 · published Sep 21, 1998, effective Oct 26, 1998
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires replacing certain toilet rinse valves with modified rinse valves. 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 water contamination of the avionics computers, which could result in the display of erroneous or misleading information to the flightcrew, and consequent reduced controllability of the airplane.
AD 98-20-05 · published Sep 21, 1998, effective Oct 26, 1998
Airbus Model A310 and A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that currently requires, among other things, repetitive inspections to ensure correct synchronization of the hydraulic control valves of the trimmable horizontal stabilizer (THS) actuator; replacement of the horizontal stabilizer actuator motors with new or serviceable motors and resynchronization of the valves, or adjustment of the synchronization, if necessary; and a functional test of the THS. This amendment adds a requirement to replace the hydraulic motor of the THS with an improved motor, which constitutes terminating action for the repetitive inspections. This amendment also expands the applicability to include additional airplanes. 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 desynchronization of the hydraulic control valves, which could result in runaway of the horizontal stabilizer to its full up or down position, subsequent reduced maneuvering capability, and potential pitch upset.
AD 98-20-06 · published Sep 21, 1998, effective Oct 26, 1998
Aerospatiale Model ATR42 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42 series airplanes, that requires modification of the electrical power supply for the standby horizon indicator. 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 loss of the standby horizon indicator in the event of failure of emergency direct current (DC) power, which could result in reduced controllability of the airplane during instrument flight rules conditions.
AD 98-20-07 · published Sep 21, 1998, effective Oct 26, 1998
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires an inspection to determine the data on the label of certain hose assemblies, and replacement of all hose assemblies from any discrepant batch with certain new hose assemblies. This amendment requires a one-time inspection for different data on the label of certain hose assemblies, and replacement of all hose assemblies from any discrepant batch with certain new hose assemblies. This action also adds airplanes to the applicability of the existing AD. This amendment is prompted by a report of the failure of a hose assembly in the fire extinguisher system of the engine nacelle due to cracks, caused during manufacture of the hose assemblies, in the swaged ferrule that attaches the hose to the end fitting. The actions specified by this AD are intended to prevent failure of hose assemblies, which could prevent the proper distribution of fire extinguishing agent within the engine nacelle in the event of a fire.
AD 98-19-08 · published Sep 22, 1998, effective Oct 7, 1998
Airbus Model A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A321 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to prohibit automatic landings and Category III operations on runways with a magnetic orientation of 170 degrees through 190 degrees inclusive. This amendment also provides for optional terminating action for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the use of erroneous automatic roll-out guidance generated by the flight management and guidance computer, which could result in the airplane departing the runway upon landing.
AD 98-20-08 · published Sep 22, 1998, effective Oct 27, 1998
McDonnell Douglas Model DC-9-10, -20, - 30, -40, and -50 Series Airplanes and C-9 (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and C-9 (military) series airplanes, that requires visual and eddy current inspections to detect cracking of the frame-to-longeron attachment area, the frame-to- skin shear clips at certain fuselage stations, and the fuselage bulkhead at the front spar of the engine pylon in the aft fuselage; and repair, if necessary. This AD also requires certain modifications which, when accomplished, will terminate the requirement for inspections. This amendment is prompted by reports indicating that fatigue cracking has occurred at those areas. The actions specified by this AD are intended to prevent such fatigue cracking, which could cause damage to adjacent structure and result in reduced structural integrity of the airplane.
AD 98-20-09 · published Sep 22, 1998, effective Oct 27, 1998
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that currently requires repetitive functional testing of the main entrance door, cleaning and lubricating of the ``speed'' lock and ``G'' lock systems, and repair, if necessary. This amendment adds a requirement for replacement of the ``G'' lock rollers with new, improved ``G'' lock rollers. 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 inability of the main entrance door to open, which could delay or impede passengers from exiting the airplane, or rescue personnel from entering the airplane during an emergency.
AD 98-20-10 · published Sep 22, 1998, effective Oct 27, 1998
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires relocation of the engine/master 1 relay from relay box 103VU to shelf 95VU in the avionics bay. 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 a simultaneous cutoff of the fuel supply to both engines, which could result in a loss of engine power and consequent reduced controllability of the airplane.
AD 98-20-12 · published Sep 22, 1998, effective Oct 27, 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 replacement of certain landing gear proximity sensor electrical units (PSEU) with improved units. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the failure of normal extension and retraction of the landing gear, which could result in collapse of the main landing gear upon landing.
AD 98-20-13 · published Sep 22, 1998, effective Oct 27, 1998
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires repetitive inspections to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing; 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 corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel.
AD 98-20-14 · published Sep 22, 1998, effective Oct 27, 1998
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 series airplanes, that requires a one-time inspection to detect chafing of electrical wires in the cable trough below the cabin floor; repair, if necessary; installation of additional tie-mounts and tie-wraps; and application of sealant to rivet heads. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing of electrical wires, which could result in an uncommanded shutdown of an engine during flight.
AD 98-20-15 · published Sep 22, 1998, effective Oct 27, 1998
Saab Model SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B series airplanes, that requires a one-time inspection for moisture or other contamination of a certain wiring harness, electrical relay, and relay socket; a one-time inspection for electrical damage of the same electrical relay and socket; corrective actions, if necessary; and replacement of certain nut plates with new, 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 a short circuit caused by fluid leakage, which could result in inability to retract the landing gear or require the use of emergency extension.
AD 98-20-16 · published Sep 22, 1998, effective Oct 27, 1998
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of the struts for the stowage box located forward of galley 2. 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 struts, which could result in displacement of the stowage box, and possible injury to passengers and flight crew.
AD 98-20-20 · published Sep 22, 1998, effective Oct 7, 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 repetitive inspections for damage or cracking of the aft pressure bulkhead, and repair, if necessary. This amendment continues to require certain repetitive inspections for damage or cracking of the aft pressure bulkhead, and repair, if necessary. This amendment removes certain repetitive inspections for cracking of the bulkhead web to Y-ring lap joint area but retains the initial inspection for cracking in that area. This amendment also adds a one- time inspection from the forward side of the bulkhead to detect fatigue cracking of the upper segment of the bulkhead web, and follow-on corrective actions, if necessary. This amendment is prompted by reports indicating that the inspections required by the existing AD may not detect cracking of the bulkhead web in a timely manner. The actions specified in this AD are intended to detect and correct fatigue cracking of the upper segment of the bulkhead web, which could result in rapid depressurization of the airplane, and consequent reduced controllability of the airplane.
AD 98-20-21 · published Sep 22, 1998, effective Oct 27, 1998
McDonnell Douglas Model DC-9-80 Series Airplanes Equipped With Heath Tecna Aerospace Extended Spacial Concept Interior III Installed in Accordance With Supplemental Type Certificate SA4744NM
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-80 series airplanes, that requires an inspection to detect discrepancies of electrical plugs and receptacles of the sidewall lighting system in the passenger cabin, and to verify that the ends of all pins and sockets are even and that they are seated and locked into place. This amendment also requires replacement of any discrepant part with a new part, and modification of the electrical wiring and connectors of the sidewall lighting system in the passenger cabin. This amendment is prompted by reports of failures of the electrical connectors in the sidewall fluorescent lighting, which resulted in smoke or lighting interruption in the passenger cabin. The actions specified by this AD are intended to prevent failures of the electrical connectors, which could result in poor socket/pin contact, excessive heat, electrical arcing, and consequently, connector burnthrough and smoke in the passenger cabin.
AD 98-20-22 · published Sep 22, 1998, effective Oct 27, 1998
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 repetitive visual inspections to detect cracked or broken door stop fittings on the fuselage frame of the forward passenger doors, and replacement of any cracked or broken 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 cracked or broken door stop fittings of the forward passenger doors, which could result in failure of the door stop fittings, consequent reduced structural integrity of the door support structure, and sudden loss of cabin pressure in the passenger compartment.
AD 98-20-23 · published Sep 22, 1998, effective Oct 27, 1998
Bombardier Model DHC-8-100, -200, and - 300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires a one-time inspection to detect discrepancies in the electrical wiring and wiring harness behind the lavatory, and 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 chafing of electrical wiring, which could result in severe overheating of the wiring, consequent smoke in the flight deck and cabin, and possible injury to flightcrew or passengers.
AD 98-20-24 · published Sep 22, 1998, effective Oct 27, 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 inspection of direct current (DC) power unit 1VE to determine whether electrical connections are correctly installed and stud nuts are correctly torqued, and corrective actions, if necessary. For certain airplanes, this amendment also requires replacement of the existing DC power unit 1VE with a modified DC power unit. 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 of electrical connections, which could result in electrical arcing and consequent fire.
AD 98-20-25 · published Sep 22, 1998, effective Oct 7, 1998
Boeing Model 747-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 series airplanes. This action requires repetitive inspections to detect cracking of the outer chord of the Body Station (BS) 1480 upper and lower bulkhead and longeron splice fitting, and repair, if necessary. Alternatively, this action requires other repetitive inspections to detect cracking of the BS 1480 upper and lower bulkhead, bulkhead outer chord, web, skin, splice components, and lower bulkhead/stringer interface; and modification of the skin splice plate, the outer chord splice fitting, and the stringer interface of the lower bulkhead, if necessary. This amendment is prompted by a report indicating that fatigue cracking was found in the outer chord of the BS 1480 bulkhead at the overwing longeron splice, and that the longeron splice fitting was completely severed. The actions specified in this AD are intended to detect and correct fatigue cracking of the BS 1480 bulkhead outer chord and longeron splice fitting, which could result in reduced structural integrity of the fuselage and the inability to carry limit load.
AD 98-20-26 · published Sep 22, 1998, effective Oct 27, 1998
Airbus Model A320-111, -211, and -231 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires repetitive inspections to detect missing or cracked bolts and fittings of the frame-to-pressure-floor connection; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections of the affected fittings. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking in the bolts and fittings of the frame-to- pressure-floor connection, which could result in reduced structural integrity of the airplane.
AD 98-20-11 · published Sep 23, 1998, effective Oct 28, 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 repetitive detailed visual inspections of the windshield wiper assembly for discrepant conditions, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the windshield wiper assembly, which could result in loss of visibility; or damage to the propeller(s), possible penetration of the fuselage skin, and consequent depressurization of the airplane.
AD 98-20-19 · published Sep 23, 1998, effective Oct 28, 1998
Bombardier Model DHC-8-100 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 and -300 series airplanes, that requires inspections to detect corrosion on areas of the airplane structure where black film thermal insulation is used; repair, if necessary; and replacement of black insulation blankets with certain aluminized (silver) insulation. This amendment is prompted by reports of corrosion forming on areas of the airplane structure where the black film covers the thermal insulation blankets. The actions specified by this AD are intended to prevent degradation of the structural capability of the airplane fuselage and sudden loss of cabin pressure due to corrosion of the airplane fuselage structure.
AD 98-19-15 · published Sep 24, 1998, effective Sep 25, 1998
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-19-15, which was sent previously to all known U.S. owners and operators of Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. The AD applies to those airplanes that are equipped with Barber-Colman pitch trim actuators, part number (P/N) 27-19008-001 or P/N 27-19008-002. This AD requires incorporating information into the Limitations Section of the airplane flight manual (AFM) that imposes a speed restriction and a minimum pilot requirement. The AD resulted from reports of two incidents of abrupt movement of the horizontal stabilizer to or near the full airplane nose-up position. These two incidents involved mechanical failure of these Barber-Colman pitch trim actuators. The actions specified by this AD are intended to lessen the severity of airplane pitch up caused by mechanical failure of the pitch trim actuator, which could result in a pitch upset and structural failure of the airplane.
AD 98-20-27 · published Sep 24, 1998, effective Oct 29, 1998
Airbus Industrie Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires repetitive inspections to detect fatigue cracking of the wing top skin at the front spar joint; and a follow-on eddy current inspection and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing top skin at the front spar joint, which could result in reduced structural integrity of the airplane.
AD 98-20-28 · published Sep 24, 1998, effective Nov 4, 1998
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
AD 98-20-33 · published Sep 24, 1998, effective Nov 17, 1998
Cessna Aircraft Company Model T210R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) Model T210R airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD was prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
AD 98-20-29 · published Sep 25, 1998, effective Oct 30, 1998
Airbus Industrie Model A320 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Industrie Model A320 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to prohibit automatic landings in configuration 3 (CONF 3). This amendment limits the applicability of the existing AD, and adds a new revision to the AFM to indicate that automatic landings in CONF 3 are prohibited and to specify an increased minimum runway visual range for airplanes on which certain modifications have not been accomplished. This amendment also requires eventual replacement of the existing spoiler elevator computers with improved parts, and insertion of new pages into the AFM that correct landing distances required for automatic landings in CONF 3. 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 pitch-up of the airplane due to activation of the spoilers during an automatic landing, which, if not corrected, could result in tail strikes and structural damage to the airplane.
AD 98-20-30 · published Sep 25, 1998, effective Oct 30, 1998
Airbus Model A320 Series Airplanes Equipped With a Bulk Cargo Door
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A320 series airplanes equipped with a bulk cargo door, that requires repetitive inspections to detect fatigue cracking of the upper frame flanges; and repair, if necessary. This amendment also requires modification of the upper frame flanges of the bulk cargo door, 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 of the upper frame flanges, which could result in reduced structural integrity of the airplane.
AD 98-20-31 · published Sep 25, 1998, effective Oct 30, 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 to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, and replacement of any cracked pick-up angle and its associated diaphragms with improved parts. Such replacement terminates the repetitive inspections for that angle. 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 cracking in the pressurized floor pick-up angles at the rear spar of the wing, which could result in reduced structural integrity of the airframe.
AD 98-20-32 · published Sep 25, 1998, effective Oct 30, 1998
Short Brothers Model SD3-60 SHERPA Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires an initial cleaning and visual inspection of the distance piece and adjacent side plates of the fuselage wing strut pick-up of the left- and right-stub wings to detect corrosion; rework or replacement of damaged components; and, for certain conditions, follow- on repetitive cleaning and visual inspections of reworked components. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion of the distance piece and adjacent side plates, which could result in reduced strength of the wing strut attachment to the stub wing on the fuselage, and consequent reduced structural integrity of the main wing.
AD 98-20-34 · published Sep 28, 1998, effective Nov 3, 1998
Twin Commander Aircraft Corporation Models 500, 500-A, 500-B, 500-S, 500-U, 520, 560, 560-A, 560-E, 560-F, 680, 680-E, 680FL(P), 680T, 680V, 680W, 681, 685, 690, 690A, 690B, 690C, 690D, 695, 695A, 695B, and 720 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Twin Commander Aircraft Corporation Models 500, 500-A, 500- B, 500-S, 500-U, 520, 560, 560-A, 560-E, 560-F, 680, 680-E, 680FL(P), 680T, 680V, 680W, 681, 685, 690, 690A, 690B, 690C, 690D, 695, 695A, 695B, and 720 airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
AD 98-20-35 · published Sep 29, 1998, effective Nov 3, 1998
Israel Aircraft Industries (IAI), Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all IAI, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes, that currently requires repetitive inspections of the trim actuator of the horizontal stabilizer to verify jackscrew integrity and to detect excessive wear of the tie rod, and replacement of the actuator or tie rod, if necessary. That AD also provides for optional terminating action for the repetitive inspections. 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 failure of the trim actuator of the horizontal stabilizer due to failure of the jackscrews, which could result in reduced controllability of the airplane.
AD 98-20-38 · published Sep 29, 1998
Raytheon Aircraft Company 200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon 200 series airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD was prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
AD 98-19-09 · published Sep 30, 1998, effective Oct 15, 1998
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and - 500 series airplanes, that currently requires removal of the fuel boost pump wiring in the conduits of the wing and center fuel tanks; an inspection to detect damage of the wiring, and corrective action, if necessary; and eventual installation of Teflon sleeving over the electrical cable. That AD was prompted by reports of severe wear of the fuel boost pump wiring due to chafing between the wiring and the surrounding conduit inside the fuel tank; pin-hole-sized holes in the conduit that appear to be the result of arc-through of the conduit; and exposure of the main tank boost pump wire conductor inside a conduit and signs of arcing to the wall of the conduit. This amendment expands the inspection requirement to include additional airplanes. The actions specified by this AD are intended to detect and correct chafing and electrical arcing between the fuel boost pump wiring and the surrounding conduit, which, if not corrected, could result in arc- through of the conduit, and consequent fire or explosion of the fuel tank.
AD 98-20-40 · published Sep 30, 1998, effective Nov 4, 1998
Boeing Model 747-100, -200, -300, SP, and SR Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-100, -200, -300, SP, and SR series airplanes, that requires the installation of shielding and separation of the electrical wiring of the fuel quantity indication system (FQIS). This amendment is prompted by a failure analysis of the FQIS, and by testing results, which revealed that excessive energy levels in the electrical wiring and probes of the fuel system could be induced by electrical transients. The actions specified by this AD are intended to prevent electrical transients, induced by electromagnetic interference (EMI), or electrical short circuit conditions from causing arcing of the FQIS electrical wiring or probes in the fuel tank(s). Such arcing could result in ignition of the fuel tank(s).
AD 98-18-11 · published Sep 2, 1998, effective Oct 7, 1998
Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, 269D, and TH- 55A Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, 269D, and TH-55A helicopters, that requires a visual inspection of the bond line between the main rotor blade abrasion strip (abrasion strip) and the blade for voids, separation, or lifting of the abrasion strip; a visual inspection of the adhesive bead around the perimeter of the abrasion strip for erosion, cracks, or blisters; a tap (ring) test of the abrasion strip for evidence of debonding or hidden corrosion voids; and removal of any blade with an unairworthy abrasion strip and replacement with an airworthy blade. This amendment is prompted by four reports that indicate that debonding and corrosion have occurred on certain blades where the abrasion strip attaches to the blade skin. The actions specified by this AD are intended to prevent loss of the abrasion strip from the blade and subsequent loss of control of the helicopter.
AD 98-19-02 · published Sep 10, 1998, effective Nov 9, 1998
Superior Air Parts, Inc., Piston Pins Installed on Teledyne Continental Motors Reciprocating Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Superior Air Parts, Inc., piston pins installed on Teledyne Continental Motors reciprocating engines. This amendment requires removal from service of defective piston pins, and replacement with serviceable parts. This amendment is prompted by reports of numerous piston pin fractures. The actions specified by this AD are intended to prevent a piston pin failure from causing secondary engine damage resulting in loss of oil or total power failure, and from causing jamming of the engine crankshaft resulting in a catastrophic engine failure.
AD 98-19-03 · published Sep 10, 1998, effective Nov 9, 1998
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Pratt & Whitney PW4000 series turbofan engines, that requires fluorescent penetrant and eddy current inspections of 2nd stage high pressure turbine (HPT) rotating airseals for cracks, removal from service of cracked parts, incorporation of improved 2nd stage HPT rotating airseals, and modification of 2nd stage ring segments and vane clusters to increase cooling flow and reduce stress as terminating action to the inspection requirements. This amendment is prompted by reports of 2nd stage HPT rotating airseal cracking. The actions specified by this AD are intended to prevent 2nd stage HPT rotating airseal cracking, which could result in an uncontained engine failure and damage to the aircraft.
AD 98-18-12 · published Sep 11, 1998, effective Sep 28, 1998
Textron Lycoming, AVCO Corporation, Lycoming Engines Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming fuel injected reciprocating engines with certain Crane/Lear Romec "AN" rotary fuel pumps installed. This action requires initial and repetitive torque check inspections of pump relief valve attaching screws. In addition, if the torque remains within acceptable values after two inspections, the repetitive torque check inspections may be terminated. This amendment is prompted by reports of inflight engine fires caused by leaking rotary fuel pumps. The actions specified in this AD are intended to prevent rotary fuel pump leaks, which could result in an engine failure, engine fire, and damage to or loss of the aircraft.
AD 98-19-10 · published Sep 11, 1998, effective Sep 28, 1998
CFM International CFM56-3, -3B, and -3C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International (CFMI) CFM56-3, -3B, and -3C series turbofan engines. This action requires, on aircraft with two affected engines installed, removal of one affected engine from an aircraft, and replacement with a serviceable engine, or replacement of a suspect accessory gearbox (AGB) starter gearshaft with a serviceable gearshaft within 350 hours time in service (TIS) after the effective date of this AD, or by September 1, 1998, whichever occurs first. This action also requires, on aircraft with only one affected engine installed, removal of the affected engine from the aircraft, and replacement with a serviceable engine , or replacement of thea suspect starter gearshaft with a serviceable gearshaft within 2,100 hours TIS after the effective date of this AD, or by February 1, 1999, whichever occurs first. This amendment is prompted by reports of two inflight engine shutdowns caused by an AGB starter gearshaft failure. The actions specified in this AD are intended to prevent an AGB starter gearshaft failure, which can result in an inflight engine shutdown, and on aircraft with two affected engines installed, possible dual inflight engine shutdown and forced landing.
AD 98-14-51 · published Sep 16, 1998, effective Oct 1, 1998
CFM International CFM56-7B Series Turbofan Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-14-51 that was sent previously to all known U.S. owners and operators of CFM International CFM56-7B series turbofan engines by individual telegrams. This AD requires checks of the Accessory Gearbox (AGB)/Transfer Gearbox (TGB) Magnetic Chip Detector (MCD) for abnormal magnetic particles that indicate a pending starter gearshaft failure, and, removal from service of suspect starter gearshafts and replacement with serviceable parts. This amendment is prompted by reports of 2 inflight engine shutdowns due to uncontained failures of the AGB starter gearshafts. The actions specified by this AD are intended to prevent a dual inflight engine shutdown event, which could result in a forced landing and loss of the aircraft.
AD 98-19-11 · published Sep 16, 1998, effective Oct 1, 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 initial and repetitive X-ray and ultrasonic inspections of exhaust diffuser vanes for corrosion and cracks, and, if necessary, removal from service of cracked exhaust diffusers and replacement with serviceable parts. This amendment is prompted by reports of 17 turbine exhaust diffuser modules with one or more exhaust diffuser vanes cracked. The actions specified in this AD are intended to prevent exhaust diffuser vane failure, which could result in an adverse effect on the engine oil and reheat systems, possibly causing an inflight engine shutdown or damage to the aircraft.
AD 98-19-12 · published Sep 16, 1998, effective Oct 1, 1998
Rolls-Royce, plc RB211 Trent 700 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 700 series turbofan engines. This action requires repositioning of the oil metering jet up into the oil distributor within the bevel gearshaft, followed by repetitive inspections of the Magnetic Chip Detector (MCD). Evidence of driving bevel gearshaft ball bearing failure requires replacement of the Step Aside Gearbox (SAGB). This amendment is prompted by reports of uncommanded engine rundowns caused by failure of the SAGB driving bevel gearshaft ball bearing due to oil starvation. This causes a loss of drive to the external gearbox and accessories, resulting in an inflight engine shutdown. The actions specified in this AD are intended to prevent inflight engine shutdowns caused by SAGB driving bevel gearshaft ball bearing failure.
AD 98-18-21 · published Sep 22, 1998, effective Oct 7, 1998
Rolls-Royce, plc RB211 Trent 800 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan engines. This action requires initial and repetitive ultrasonic inspections of fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment is prompted by reports of multiple fan blade root cracks in several factory test engines. The actions specified in this AD are intended to prevent fan blade failure, which could result in multiple fan blade release, uncontained engine failure, and possible damage to the aircraft.
AD 98-19-20 · published Sep 22, 1998, effective Oct 7, 1998
CFM International CFM56-7B and -7B/2 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-7B and -7B/2 series turbofan engines. This action requires initial and repetitive inspections of certain hydromechanical unit (HMU) overspeed governor (OSG) spool valves for out-of-specification conditions or the presence of heavy contact or galling on the spool valve, and optional installation of an improved HMU as a terminating action to the inspections. This amendment is prompted by a report of a flameout that occurred on a flight test engine due to a failed HMU OSG spool valve shaft. The actions specified in this AD are intended to prevent failure of the HMU OSG spool valve shaft, and subsequent engine flameout.
AD 98-19-21 · published Sep 22, 1998, effective Oct 7, 1998
Rolls-Royce plc Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan engines. This action requires initial and repetitive ultrasonic inspections of fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment is prompted by reports of multiple fan blade root cracks in several factory test engines. The actions specified in this AD are intended to prevent fan blade failure, which could result in multiple fan blade release, uncontained engine failure, and possible damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 7, 1998. Comments for inclusion in the Rules Docket must be received on or before November 23, 1998.
AD 98-20-17 · published Sep 24, 1998, effective Nov 2, 1998
SAFT America Inc. Part Number (P/N) 021929-000 (McDonnell Douglas P/N 43BO34LB02) and P/N 021904-000 (McDonnell Douglas P/N 43BO34LB03) Nickel Cadmium Batteries
This amendment adopts a new airworthiness directive (AD) that applies to certain SAFT America Inc. P/N 021929-000 (McDonnell Douglas P/N 43BO34LB02) and P/N 021904-000 (McDonnell Douglas P/N 43BO34LB03) nickel cadmium batteries that are installed on aircraft. This AD requires replacing all battery terminal screws, verifying that the battery contains design specification cells, and replacing the cells if the battery contains non-design specification cells. This AD is the result of an incident where the cell screws on one of the affected batteries were exposed to chloride, which caused the heads of some fasteners to shear off and eventually resulted in the battery exploding. The actions specified by this AD are intended to prevent such an occurrence, which could result in loss of emergency power to electrical flight components or other emergency power systems required in the event of loss of the aircraft primary power source.
AD 98-19-01 · published Sep 10, 1998, effective Sep 25, 1998
Stemme GmbH & Co. KG Model S10 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Model S10 sailplanes. This AD requires replacing the O-ring that is installed in the mounting part of the pitot tube (in the propeller dome) with one 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 failure of the pitot tube O-ring caused by an ineffective design, which could result in the pitot tube falling out and the sailplane pilot losing airspeed indications.
AD 98-19-14 · published Sep 15, 1998, effective Nov 9, 1998
S.N. Centrair 101 Series Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all S.N. Centrair (Centrair) 101 series sailplanes. This AD requires replacing the airbrake control system with one of improved design. 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 loss of the airbrake control system caused by cracks in the original design airbrake control system, which could result in an inadvertent forced landing with consequent sailplane damage and/or passenger injury.
AD 98-19-17 · published Sep 17, 1998, effective Oct 30, 1998
Glaser-Dirks Flugzeugbau GmbH Model DG- 400 Gliders'
This amendment adopts a new airworthiness directive (AD) that applies to certain Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG-400 gliders. This AD requires inspecting the powerplant mount and the propeller mount for any loose parts. This AD also requires modifying the starter motor, retrofitting the holder for the starter motor, and checking the engine ignition timing; either immediately or at a certain time 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 damage to the engine caused by vibration, which could result in loss of engine power during critical phases of flight.
