54 Airworthiness Directives: 43 airplane, 3 rotorcraft, 5 engine, 2 propeller, 1 appliance.
AD 98-24-14 · published Dec 2, 1998, effective Dec 21, 1998
Cessna Aircraft Company Models 340A and 414A Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-24-14, which was sent previously to all known U.S. owners and operators of certain Cessna Aircraft Company (Cessna) Models 340A and 414A airplanes that could be equipped with any WYE tube, part number (P/N) 9910299-25 or P/N 9910299-26, in the engine exhaust system. This AD requires removing from service any P/N 9910299-25 or P/N 9910299-26 engine exhaust system WYE tube. The AD resulted from reports of five instances where the engine exhaust components in the WYE tube were manufactured without welds on critical parts that are installed adjacent to the firewall. The actions specified by this AD are intended to detect and correct exhaust leaks caused by nonwelded exhaust system components, which could result in aluminum fuel lines bursting with consequent fuel spillage, an airplane fire, and/or an explosion.
AD 98-24-51 · published Dec 2, 1998, effective Dec 7, 1998
McDonnell Douglas Model MD-11 Series Airplanes Equipped with Certain Collins LRA-900 Radio Altimeters
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) T98-24-51 that was sent previously to all known U.S. owners and operators of certain McDonnell Douglas Model MD-11 series airplanes by individual telegrams. This AD requires a revision to the Airplane Flight Manual to prohibit autopilot coupled autoland operations in certain conditions; or, for certain airplanes, replacement of certain Collins LRA-900 radio altimeters with Collins LRA-700 radio altimeters. This action is prompted by a report that a fault in certain Collins LRA-900 radio altimeters could result in an incorrect and unbounded output of radio altitude to other airplane systems. The actions specified by this AD are intended to prevent an undetected anomalous radio altitude signal that is passed along to the flare control law of the flight control computer, which could cause the airplane to flare too high or too low during landing, and consequently result in a hard landing.
AD 98-24-33 · published Dec 3, 1998, effective Jan 7, 1999
McDonnell Douglas Model DC-9 and DC-9- 80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires a one-time visual inspection to detect fatigue cracking of the lower left nose of certain longerons and the attaching frames; repair, if necessary; and installation of a preventive modification. This amendment is prompted by several reports of fatigue cracking of certain longerons and the attaching frames. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the fuselage, and consequent loss of pressurization of the airplane.
AD 98-25-01 · published Dec 3, 1998, effective Jan 19, 1999
Air Tractor, Inc. AT-300, AT-400, and AT-500 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 96-23- 19, which currently requires installing a new flap actuator overtravel stop and a roll pin through the overtravel stop and jack screw on certain Air Tractor, Inc. (Air Tractor) Models AT-300, AT-400, and AT- 500 series airplanes. This AD requires replacing the existing flap actuator overtravel stop with a new one of improved design. This AD is the result of reports of the jack screw breaking through the roll pin hole on three of the affected airplanes that were already in compliance with AD 96-23-19. The actions specified by this AD are intended to prevent interference between the flap pushrod and the aileron pushrod caused by the flap actuator overtravel nut disengaging, which could result in loss of aileron control.
AD 98-25-03 · published Dec 3, 1998, effective Dec 18, 1998
Cessna Aircraft Company Model 172R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Model 172R airplanes that are not equipped with an autopilot. This AD requires inspecting the right wing for an incorrectly routed, frayed, or damaged aileron control cable, and re-routing any incorrectly routed cable or replacing any frayed or damaged cable. The AD also requires reporting any incorrectly routed, frayed, or damaged cable to the Federal Aviation Administration (FAA). This AD is the result of a report of an incorrectly routed aileron control cable in the right wing of an airplane of the same type design to those affected by this AD. The cable was routed over the aileron auto pilot actuator pulley and the cable was rubbing on the cable guard. The actions specified by this AD are intended to prevent loss of aileron control caused by a damaged or frayed aileron control cable, which could result in loss of directional control of the airplane.
AD 98-25-04 · published Dec 3, 1998, effective Jan 7, 1999
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires repetitive inspections to detect debris in the areas behind the aft lavatory toilet shroud, behind the aft lavatory modules, and below the cabin floor aft of the aft cargo compartment bulkhead; and removal of debris. This amendment also requires modification of the lavatory toilet shroud assemblies and modification of the lavatory entry door louvers, which terminates the repetitive inspections. This amendment is prompted by reports of paper debris collecting below the cabin floor. The actions specified by this AD are intended to prevent paper debris from collecting below the cabin floor, which could result in a potential fire hazard or possible loss of elevator control system redundancy.
AD 98-25-05 · published Dec 3, 1998, effective Dec 18, 1998
Airbus Model A321-111, -112, and -131 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A321-111, -112, and -131 series airplanes. This action requires repetitive inspections to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar; and repair, if necessary. This amendment also provides for 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 in this AD are intended to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane.
AD 98-23-51 · published Dec 9, 1998, effective Dec 14, 1998
Boeing Model 727 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-23-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 727 series airplanes by individual telegrams. This AD requires modification of certain fuselage skin lap joints and, on certain airplanes, modification of the lap joint(s) in the door structure. This AD also requires repetitive internal detailed visual inspections to detect cracking, corrosion, or delamination of the fuselage skin lap joints, and repair, if necessary. This action is prompted by information that a modification required by an existing AD may not have been accomplished completely on as many as 160 airplanes. The actions specified by this AD are intended to prevent corrosion and subsequent fatigue cracking of the fuselage skin lap joints, which could result in rapid decompression of the airplane.
AD 98-25-06 · published Dec 9, 1998, effective Dec 24, 1998
Boeing Model 737-200, -200C, -300, and -400 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200, -200C, -300, and -400 series airplanes. This action requires repetitive inspections to detect cracking of the corners of the door frame and the cross beams of the aft cargo door, and corrective actions, if necessary. This action also provides an optional terminating action for the repetitive inspection requirement of this AD. This amendment is prompted by reports indicating that fatigue cracks have been detected in the corners of the door frame and the cross beams of the aft cargo door on several in- service airplanes, and by another report indicating that rapid depressurization occurred during flight on one of those airplanes. The actions specified in this AD are intended to prevent fatigue cracking of the corners of the door frame and the cross beams of the aft cargo door, which could result in rapid depressurization of the airplane.
AD 98-25-10 · published Dec 9, 1998, effective Dec 24, 1998
Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH Seat Restraint Systems
This amendment adopts a new airworthiness directive (AD) that is applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems, installed on, but not limited to, Beech Aircraft Corp., Bell Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft. This action requires an inspection to ensure the locking mechanism is engaging properly, and replacing the buckle-half of the seat restraint system, if necessary. This amendment is prompted by the manufacturer reporting two failures of the seat restraint system in the field. The actions specified in this AD are intended to prevent failure of the seat restraint system due to the buckle assembly locking mechanism not engaging properly, which could result in the seat restraint system failing to properly secure the occupant during turbulence or landing.
AD 98-13-12 R1 · published Dec 10, 1998, effective Dec 28, 1998
Boeing Model 737, 747, 757, 767, and 777 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 737, 747, 757, 767, and 777 series airplanes, that currently requires a one-time inspection to detect discrepancies of the fasteners that connect the pushrods to the rudder pedal assemblies; and corrective actions, if necessary. That AD was prompted by reports of loose and missing fasteners due to incorrect installation. The actions specified by that AD are intended to prevent loss of rudder control, jamming of the rudder system, uncommanded movement of the rudder system, and consequent reduced controllability of the airplane, due to loose or missing fasteners that connect the pushrods to the rudder pedal assemblies. This amendment clarifies certain procedures for the required inspection and expands the applicability to include additional airplanes, which are not currently on the U.S. Register.
AD 98-25-07 · published Dec 10, 1998, effective Jan 14, 1999
Airbus Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive inspections to detect cracks in the angle fitting at frame 40 of the center wing box, and corrective actions, if necessary; and eventual modification of that angle fitting, which 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 cracks in the center wing box angle fitting, which could result in the failure of the center wing box at frame 40, and consequent reduced structural integrity of the airplane.
AD 98-25-08 · published Dec 10, 1998, effective Jan 14, 1999
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 to detect wear damage on the nosewheel steering control cables located in the nosewheel bay of the nose landing gear (NLG); repetitive testing of the cable pulleys to detect seizing; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the nosewheel steering control cables, which could result in loss of the nosewheel steering or collapse of the NLG, and possible injury to the flightcrew and passengers.
AD 98-25-09 · published Dec 10, 1998, effective Jan 14, 1999
Bombardier Model DHC-7 and DHC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-7 and DHC-8 series airplanes, that requires a one-time visual inspection to determine the serial number of the brake shuttle valves of the main landing gear (MLG); and replacement of the filter fittings with new filter fittings, 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 ensure that proper filter fittings are installed. Installation of improper filter fittings could result in failure of the brake shuttle valves, and consequent loss of brake effectiveness, which could reduce controllability of the airplane during taxi, takeoff, and landing roll.
AD 98-25-11 · published Dec 10, 1998, effective Dec 28, 1998
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors, and repair, if necessary. This amendment is prompted by a report indicating that damaged electrical wires were found above the forward passenger doors due to flapper panels moving inboard and chafing the electrical wire assemblies of this area. The actions specified in this AD are intended to prevent such chafing, which could result in an electrical fire in the passenger compartment.
AD 98-25-12 · published Dec 14, 1998, effective Jan 19, 1999
Boeing Model 757-200 Series Airplanes Powered by Rolls-Royce RB211-535E4/E4B Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires repetitive inspections to detect cracking of the honeycomb core of the acoustic panels in the engine inlet, and repair, if necessary. This amendment also requires eventual replacement of the existing engine inlet with a new or serviceable inlet, which, when accomplished, terminates the repetitive inspections. This amendment is prompted by reports of cracking of the honeycomb core of the acoustic panels in the engine inlet, and incidents of pieces of the panels breaking off and being ingested into the engine. The actions specified by this AD are intended to detect and correct cracking of the honeycomb core of the acoustic panels in the engine inlet, which could result in reduced structural integrity of the engine inlet, and consequent engine shutdown or surge; or, in the event of a fan blade failure, separation of the inlet from the engine.
AD 98-25-15 · published Dec 14, 1998, effective Jan 19, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes. This amendment requires inspections to detect attachment failures of the 12 attachments located on the No. 4 banjo fitting/pylon carry- through cap, and to detect cracking of the forward and aft flanges and bolt holes of the No. 4 banjo fitting; repair, if necessary; and replacement of the 12 attachments with new or serviceable parts. Such replacement terminates the repetitive inspections. This amendment is prompted by a report indicating that attachment bolts on the forward and aft flanges of the No. 4 banjo fitting and the pylon carry-through cap failed due to fatigue cracking. The actions specified by this AD are intended to prevent such cracking, which could result in reduced controllability of the airplane during flight and ground operations.
AD 98-26-01 · published Dec 16, 1998, effective Jan 20, 1999
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires various inspections to detect fatigue cracks at certain locations on the fuselage, horizontal stabilizer, and wings and tail, and repair or modification, if necessary; and installation of doublers. This amendment also adds new inspections and reduces certain inspection intervals. This amendment is prompted by results of full-scale fatigue testing of a Model A310 series airplane, which revealed fatigue cracks at those locations. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage, horizontal stabilizer, and wings.
AD 98-26-03 · published Dec 16, 1998, effective Dec 31, 1998
Airbus Model A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A321 series airplanes. This action requires modification and re-identification of the evacuation slide systems at left-and right-hand emergency exits 2 and 3. 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 loss of the evacuation slides during flight, which could result in damage to the empennage, or inability of airplane occupants to use certain exit doors during an emergency.
AD 98-26-04 · published Dec 16, 1998, effective Dec 31, 1998
Boeing Model 757 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires an inspection of the engine fuel shutoff valves (spar valves) to detect leakage of fuel and to ensure that no leakage occurs when the valves are commanded to close. That amendment also requires an alignment procedure of the engine fuel shutoff valves, if necessary. This amendment expands the applicability of the existing AD. This amendment is prompted by additional reports that certain crossfeed valve assemblies and engine shutoff valve assemblies were improperly installed during manufacturing of the airplane. The actions specified in this AD are intended to prevent uncommanded fuel flow from the fuel tanks to the engine nacelle, which could result in reduced airplane fire protection in the event of a leak in the engine fuel line or a fire in the engine nacelle.
AD 98-26-05 · published Dec 18, 1998, effective Jan 29, 1999
British Aerospace (Operations) Limited Model B.121 Series 1, 2, and 3 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace (Operations) Limited (British Aerospace) Model B.121 Series 1, 2, and 3 airplanes. This AD requires repetitively inspecting (using visual methods) the internal and external surfaces of the brake torque tube assemblies in the cockpit area for cracks. This AD also requires obtaining and incorporating repair procedures for any brake torque tube assembly found cracked. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the brake torque tube assemblies, which could result in reduced brake efficiency with possible reduced and/or loss of airplane control.
AD 98-26-09 · published Dec 18, 1998, effective Jan 22, 1999
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 DC9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if the doorstops and corners of the doorjamb of the forward passenger door have been 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 and doorstops of the doorjamb of the forward passenger door. 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 98-26-10 · published Dec 18, 1998, effective Jan 22, 1999
Dassault Model Mystere-Falcon 20 Series Airplanes, Fan Jet Falcon Series Airplanes, and Fan Jet Falcon Series D, E, and F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 20 series airplanes, Fan Jet Falcon series airplanes, and Fan Jet Falcon Series D, E, and F series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with certain emergency procedures associated with an engine fire, or a rear compartment fire or overheat conditions. 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 fire from spreading throughout the airplane due to an engine fire, or with a rear compartment fire or overheat conditions.
AD 98-26-11 · published Dec 18, 1998, effective Jan 22, 1999
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 replacement of the end-pieces of the expansion chamber attenuator (ECA) for the standby pump of the Number 2 hydraulic system with new, improved end-pieces. 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 leakage of hydraulic fluid from the Number 2 hydraulic system due to failure of the end-pieces of the ECA, which could result in loss of nose wheel steering, flap operation, normal landing gear operation, and reduced redundancy in the brake and flight controls systems.
AD 98-26-12 · published Dec 21, 1998, effective Jan 25, 1999
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 to verify correct installation of the lockplates of the roll spoiler actuators, 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 fatigue cracking of the fork flanges of the roll spoiler actuators due to incorrect installation of the lockplates, which could result in reduced structural integrity of the components of the roll spoiler actuators, and consequent reduced controllability of the airplane.
AD 98-26-13 · published Dec 21, 1998, effective Jan 25, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time inspection to determine the material type of the stop support fittings of the main entry doors. This AD also requires repetitive visual inspections to detect cracks of certain stop support fittings of the main entry doors, and replacement of any cracked stop support fitting with a certain new stop support fitting. This amendment is prompted by reports that stress corrosion cracking was found on certain stop support fittings of the main entry doors. The actions specified by this AD are intended to detect and correct such stress corrosion cracking, which could lead to failure of the stop support fittings. Failure of the stop support fittings could result in loss of a main entry door and consequent rapid decompression of the airplane.
AD 98-26-14 · published Dec 21, 1998, effective Jan 5, 1999
Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes. This action requires a one-time visual inspection to detect chafing or cracking of all electrical wiring conduits located in the center fuel tank, and inadequate clearance between the tube assemblies and adjacent structures; and corrective actions, if necessary. This action also requires a modification to reinforce the right wing crossflow shutoff valve conduit. 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 chafing or cracking of the electrical conduits in the center fuel tank and inadequate clearance between tube assemblies and adjacent structures, which could result in electrical arcing and consequent fire or explosion in the center fuel tank.
AD 98-26-15 · published Dec 21, 1998, effective Jan 25, 1999
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 repetitive detailed visual inspections to detect cracks in the shear cleats of the roller guide structural support of the passenger door, and replacement of any cracked shear cleat with a new shear cleat. That AD also provides for an optional terminating modification that constitutes terminating action for the repetitive inspections. This amendment mandates accomplishment of the previously optional terminating modification. This amendment is prompted by reports indicating that fatigue cracking was detected in the roller guide shear cleats of the passenger door. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in structural failure or loss of the passenger door, and consequent rapid depressurization of the airplane during flight.
AD 98-25-51 · published Dec 22, 1998, effective Dec 28, 1998
Airbus Model A310 and A300-600 Series Airplanes Equipped with Pratt & Whitney JT9D-7R4 or 4000 Series Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-25-51 that was sent previously to all known U.S. owners and operators of certain Airbus Model A310 and A300-600 airplanes by individual telegrams. This AD requires deactivation of both thrust reversers and a revision of the Airplane Flight Manual (AFM) to ensure that safe and appropriate performance is achieved during certain takeoff conditions. 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 inflight deployment of a thrust reverser, which could result in reduced controllability of the airplane.
AD 98-25-53 · published Dec 22, 1998, effective Dec 28, 1998
Airbus Model A300 B4-600R and A300 F4- 600R Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) T98-25-53 that was sent to all known U.S. owners and operators of all Airbus Model A300 B4-600R and A300 F4-600R series airplanes by individual telegrams. This AD requires a one-time visual inspection for damage of the center fuel pumps and fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This action is prompted by reports of damaged center tank fuel pump canisters and damaged center tank fuel pumps. The actions specified by this AD are intended to detect damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank.
AD 98-26-08 · published Dec 22, 1998, effective Jan 26, 1999
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-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the doorjamb of the forward service door have been previously modified. The action also requires various repetitive inspections to detect cracks of the fuselage skin and doubler at all corners of the doorjamb of the forward service door, and to detect cracks on the skin adjacent to the modification; and various follow-on actions. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners of the doorjamb of the forward service door. 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 98-26-16 · published Dec 22, 1998, effective Feb 5, 1999
Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. This AD requires modifying the emergency exit doors and installing interior and exterior placards on each of the emergency exit doors. Difficulty in opening the emergency exit doors prompted this action. The actions specified by this AD are intended to prevent passengers and crew from not being able to open the emergency exit doors during an airplane emergency, which could result in passenger and crew injuries.
AD 98-26-17 · published Dec 22, 1998, effective Feb 5, 1999
British Aerospace Jetstream Model 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Jetstream Model 3201 airplanes. This AD requires accomplishing both a routine visual inspection and either a detailed visual inspection or x-ray inspection of the main landing gear (MLG) bay auxiliary spar booms for cracks or fuel leaks on both the left and right sides of the airplane. This AD also requires obtaining and incorporating repair procedures for the MLG bay auxiliary spar where fuel leaks or cracks are found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent wing failure caused by cracks or fuel leaks in the area of the MLG bay auxiliary spar booms, which could result in loss of control of the airplane.
AD 98-25-52 · published Dec 24, 1998, effective Dec 29, 1998
Boeing Model 747 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-25-52 that was sent previously to all known U. S. owners and operators of all Boeing Model 747 series airplanes by individual telegrams. This AD requires revising the Airplane Flight Manual to include procedures to prevent dry operation of the center wing fuel tank override/jettison pumps and, for certain airplanes, to prohibit operation of the horizontal stabilizer tank transfer pumps in flight. This action is prompted by a report indicating that several override/jettison fuel pumps from the center wing tanks and main tanks had been removed because circuit breakers for the override/jettison fuel pumps were tripped, or low pump output pressure was indicated. The actions specified by this AD are intended to prevent contact between the rotating paddle wheel and the stationary end plates within the center wing tank override/jettison fuel pumps or horizontal stabilizer tank transfer pumps due to excessive wear of the pump shaft carbon thrust bearing, which could cause sparks and/or a hot surface condition and consequent ignition of fuel vapor in the center wing tank or horizontal stabilizer tank during dry pump operation (no fuel flowing).
AD 98-26-22 · published Dec 29, 1998, effective Feb 2, 1999
McDonnell Douglas Model DC-10 Series Airplanes and KC-10A (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires repetitive inspections to detect cracking of the lower cap of the wing rear spar, and repair, if necessary. For certain airplanes, this AD also provides for an optional terminating modification for the repetitive inspections. This amendment is prompted by reports of fatigue cracks found in the lower cap of the wing rear spar. The actions specified by this AD are intended to detect and correct fatigue cracking of the lower cap of the wing rear spar, which could result in reduced structural integrity of the airplane.
AD 98-26-23 · published Dec 29, 1998, effective Feb 2, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive detailed visual inspections to detect corrosion on the rear spar web of the wing center section and adjacent bulkhead fittings at body station 1241; and corrective action, if necessary. This amendment is prompted by reports of corrosion found on the rear spar web and bulkhead fitting. The actions specified by this AD are intended to detect and correct such corrosion, which could cause cracking of the rear spar web, and result in a fuel leak and consequent fire/explosion in the wheel well of the main landing gear.
AD 99-01-03 · published Dec 31, 1998, effective Feb 8, 1999
Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes
This amendment supersedes Airworthiness Directive (AD) 97-14- 16, which applies to Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. AD 97-14-16 currently requires repetitively inspecting the outboard flap support roller bearings and flap attachment brackets for indications of contact (wear), inspecting for elongated holes in the flap attachment brackets, repairing or replacing any part showing wear, and replacing any bracket with elongated holes. AD 97-14-16 was the result of five incidents where the flap roller bearings rubbed on the flap attachment brackets and resulted in aileron interference. This AD retains the repetitive inspection requirement of AD 97-14-16, but reduces the number of ground-air-ground (GAG) cycles allowed between inspections and lowers the total number of accumulated GAG cycles allowed before mandatory accomplishment of the initial inspection. This AD also provides the option of replacing the outboard flap roller bearings with parts of improved design as terminating action for the repetitive inspection requirement. The actions specified by this AD are intended to prevent asymmetric flaps, jammed flaps, and/ or possible interference between the flap and the aileron, which could inhibit aileron travel and result in possible loss of roll control of the airplane.
AD 99-01-04 · published Dec 31, 1998, effective Mar 12, 1999
Avions Pierre Robin Model R2160 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires replacing the left and right rudder bars with improved design rudder bars. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent distortion of the original design rudder bars during operation, which could result in reduced or loss of control of the airplane.
AD 99-01-05 · published Dec 31, 1998, effective Feb 8, 1999
All Airplane Models of The New Piper Aircraft, Inc. (formerly Piper Aircraft Corporation) That Are Equipped with Wing Lift Struts
This amendment supersedes Airworthiness Directive (AD) 93-10- 06, which currently requires repetitively inspecting the wing lift struts and wing lift strut forks for cracks or corrosion on all airplane models of The New Piper Aircraft, Inc. (Piper) that are equipped with wing lift struts, and replacing any strut or fork found cracked or corroded. This AD clarifies certain requirements of AD 93- 10-06, eliminates the lift strut fork repetitive inspection requirement on the Piper PA-25 series airplanes, incorporates models inadvertently omitted from AD 93-10-06, and requires fabricating and installing a placard on the lift strut. This AD results from reports, questions, and information received from the field on AD 93-10-06, which show a need to clarify and add information that will more fully achieve the safety intent of that AD. The actions specified by this AD are intended to prevent in-flight separation of the wing from the airplane caused by corroded wing lift struts or cracked wing lift forks, which could result in loss of control of the airplane.
AD 99-01-06 · published Dec 31, 1998, effective Mar 19, 1999
British Aerospace Jetstream Model 3101 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3101 airplanes. This AD requires installing a standard bonding socket that is fitted flush with the upper surface of each wing at the fueling points (Station 297). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified in this AD are intended to correct a potentially insufficient ground contact between the refueler hose nozzle and the aircraft, which, if not corrected before the fuel cap is removed, could result in sparks with a consequent fire and/or explosion in the fuel tank.
AD 99-01-07 · published Dec 31, 1998, effective Mar 19, 1999
British Aerospace Jetstream Model 3101 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3101 airplanes. This AD requires installing additional stringers at the lower fuselage skin panels between the main and rear spar frames. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified in this AD are intended to correct a strength deficiency in the area of the lower fuselage skin panels between the main rear spar frames, which, if not corrected, could result in reduced or loss of control of the airplane during maximum speed limit operations.
AD 99-01-10 · published Dec 31, 1998, effective Jan 15, 1999
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 to detect discrepancies of the diagonal brace lugs of the engine strut, and rework of the diagonal brace lugs, if necessary. That AD also provides an option to defer the rework for certain cases by accomplishing repetitive inspections and resealing the bushing. That AD also provides for an optional terminating modification for the repetitive inspections. This amendment adds a requirement to repetitively inspect a new area of the diagonal brace of the engine strut. For certain airplanes, this amendment also adds new repetitive inspections of the subject area and requires that certain previously required repetitive inspections be accomplished at reduced intervals. This amendment is prompted by reports of fatigue or stress corrosion cracking in new areas of the diagonal brace. The actions specified in this AD are intended to prevent such fatigue or stress corrosion cracking, which could result in failure of the strut and consequent separation of the engine from the airplane.
AD 98-24-35 · published Dec 2, 1998, effective Dec 17, 1998
Eurocopter France Model AS-350B, B1, B2, BA, C, D, D1, and AS 355E, F, F1, F2, and N Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS-350B, B1, B2, BA, C, D, D1, and AS 355E, F, F1, F2, and N helicopters. This action requires measuring the tail rotor pitch change control rod (control rod) outboard spherical bearing for radial and axial play. If the play exceeds 0.008-inch, replacing the control rod with an airworthy control rod is required. This amendment is prompted by one accident and one incident. Investigations revealed a broken control rod on the helicopter involved in the accident and a severely worn control rod on the helicopter involved in the incident. This condition, if not corrected, could result in separation of the outboard spherical bearing ball from its outer race, rubbing of the body of the control rod against the tail rotor blade pitch horn clevis, failure of the control rod, and loss of control of the helicopter.
AD 98-26-02 · published Dec 16, 1998, effective Jan 20, 1999
Sikorsky Aircraft Corporation Model S- 61A, D, E, L, N, NM, R, and V Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft Corporation Model S-61A, D, E, L, N, NM, R, and V helicopters, that requires a nondestructive inspection (NDI) for cracks in the main rotor shaft (shaft), and requires removal of any shaft with a crack and replacement with an airworthy shaft. This AD also requires appropriate marking of shafts and log book entries by the operator to determine the shaft retirement life, and establishes a new retirement life for the shaft. This amendment is prompted by four reports of cracks occurring in helicopters that were utilized in repetitive external lift (REL) operations. The actions specified by this AD are intended to detect a fatigue crack in the shaft that could result in shaft structural failure, loss of power to the main rotor, and subsequent loss of control of the helicopter.
AD 99-01-02 · published Dec 30, 1998, effective Jan 14, 1999
Westland Helicopters Ltd. 30 Series 100 and 100-60 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Westland Helicopters Ltd. (Westland) 30 Series 100 and 100-60 helicopters. This action requires the removal and replacement of conformal pinion quill shafts installed in certain main rotor gearboxes that fail to pass a magnetic drain plug inspection. This amendment is prompted by a report of a forced landing that occurred when a single conformal pinion quill shaft failed in a main rotor gearbox (MRGB). This condition, if not corrected, could result in the failure of a MRGB, and a subsequent forced landing or loss of control of the helicopter.
AD 98-22-11 · published Dec 3, 1998, effective Dec 18, 1998
AlliedSignal, Inc. Model T5317A-1 Turboshaft Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-22-11 that was sent previously to all known U.S. owners and operators of AlliedSignal, Inc. (formerly Textron Lycoming) model T5317A-1 turboshaft engines by individual letters. This AD requires, prior to further flight, a pressure test to determine if both fuel pumps in the regulator, Part Number (PN) 1-170- 240-93, are producing fuel pressure, and, if necessary, replacement of the fuel regulator with serviceable part. In addition, this AD requires repetitive engine fuel pump pressure tests. This amendment is prompted by a report of an accident involving an AlliedSignal, Inc. (formerly Textron Lycoming) model T5317A-1 turboshaft engine installed on a Kaman Aerospace model K-1200 rotorcraft engaged in logging operations. The actions specified by this AD are intended to prevent loss of fuel flow from the engine fuel regulator due to failure of both primary and secondary fuel pump drive shaft splines. This condition, if not corrected, could result in engine failure and forced autorotation landing.
AD 98-24-28 · published Dec 3, 1998, effective Jan 7, 1999
Allison Engine Company 250-B and 250-C Series Turboshaft and Turboprop Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Allison Engine Company 250-B and 250-C series turboshaft and turboprop engines, that requires replacing existing beryllium copper main fuel control (MFC) bellows assemblies with Inconel 718 stainless steel welded MFC bellows assemblies. This amendment is prompted by reports of leaking MFC bellows assemblies resulting in an uncommanded minimum fuel flow condition, loss of engine fuel flow control and subsequent forced landing. The actions specified by this AD are intended to prevent MFC bellows assembly leakage, which can result in an uncommanded minimum fuel flow condition and subsequent loss of engine fuel flow control.
AD 98-25-14 · published Dec 14, 1998, effective Feb 12, 1999
Rolls-Royce Limited, Bristol Engines Division and Rolls-Royce (1971) Limited, Bristol Engines Division Viper Series Turbojet Engines
This amendment adopts a new airworthiness directive (AD), applicable to Rolls-Royce Limited, Bristol Engines Division and Rolls- Royce (1971) Limited, Bristol Engines Division, Viper series turbojet engines, that requires a one-time visual inspection of the barometric flow control unit (BFCU) augmentor and bypass valve joint washer for joint washer integrity, and replacement, if necessary, with serviceable parts. This amendment is prompted by a report of a high pressure fuel leak at the BFCU augmentor and bypass valve assembly joint, washer interface. The actions specified by this AD are intended to prevent a high pressure fuel leak, which could result in an engine nacelle fire and damage to the aircraft.
AD 98-26-07 · published Dec 18, 1998, effective Feb 16, 1999
Rolls-Royce Limited, Bristol Engines Division, Viper Models Mk.521 and Mk.522 Turbojet Engines
This amendment adopts a new airworthiness directive (AD), applicable to Rolls-Royce Limited, Bristol Engines Division, (R-R) Viper Models Mk.521 and Mk.522 turbojet engines, that requires replacement of certain high pressure (HP) fuel pumps with an improved design which is more tolerant of reduced lubricity fuel caused by water contamination. This amendment is prompted by reports of HP fuel pump drive shaft failures resulting in in-flight engine shutdowns. These failures have been attributed to the reduced lubricity properties of fuel which is contaminated by water. The actions specified by this AD are intended to prevent HP fuel pump failures, which can result in an in-flight engine shutdown.
AD 99-01-08 · published Dec 31, 1998, effective Jan 5, 1999
Pratt & Whitney JT8D and JT3D Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney (PW) JT8D and JT3D series turbofan engines. This action requires operators to remove and replace with serviceable parts, certain stage 7 through stage 15 high-pressure compressor (HPC) disks identified by part number and serial number. This amendment is prompted by a report of an uncontained failure of a stage 8 HPC disk during a takeoff roll that resulted in damage to the airplane. The actions specified in this AD are intended to prevent the failure of a high-pressure compressor disk due to Cadmium embrittlement, resulting in uncontained engine failure and damage to the airplane.
AD 98-24-34 · published Dec 3, 1998, effective Dec 18, 1998
Hamilton Standard 54H60 Series Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hamilton Standard 54H60 series propellers. This action requires affected propeller blades to be removed from service and shipped to designated repair facilities for inspection for insufficient cold rolling of the beveled radius of the blade flange. Affected blades are identified by serial number. This amendment is prompted by reports of propeller blades that cracked due to incomplete cold rolling in the beveled radius area of the blade flange. The actions specified in this AD are intended to prevent propeller blade cracks due to incomplete cold rolling during manufacture, which can result in propeller blade separation and damage to the aircraft.
AD 98-25-13 · published Dec 18, 1998, effective Jan 4, 1999
McCauley Propeller Systems Models 2A36C23/84B-0 and 2A36C82/84B-2 Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to McCauley Propeller Systems (formerly McCauley Accessory Division, The Cessna Aircraft Company) Models 2A36C23/84B-0 and 2A36C82/84B-2 propellers. This action supersedes priority letter AD 89-26-08 that currently requires penetrant inspections for cracks in the propeller blade threaded retention area, and modifying the propeller hub to a red dye filled configuration. This action adds an explanatory note to better define the AD applicability and makes minor adjustments to compliance section language to reflect current AD practice. This amendment is prompted by reports of confusion from operators as to if the AD is applicable to their particular model propeller. The actions specified by this AD are intended to prevent possible cracks in the propeller blade threaded retention area from progressing to blade separation, which can result in loss of aircraft control.
AD 98-25-02 · published Dec 3, 1998, effective Dec 22, 1998
BFGoodrich Avionics Systems, Inc. SKYWATCH SKY497 Installations with a Top-Mounted Antenna
This amendment adopts a new airworthiness directive (AD) that applies to all BFGoodrich Avionics Systems, Inc. (BFGoodrich) SKYWATCH SKY497 installations with a top-mounted antenna that are installed on aircraft. This AD requires incorporating information into the airplane flight manual (AFM) that specifies verifying the correct antenna configuration each time an aircraft equipped with a SKY497 installation with a top-mounted antenna is powered-up. The AD also requires removing from service any of these SKY497 installations with an incorrect antenna configuration. This AD results from numerous reports of internal component failure of the above-referenced installations, which changed the antenna configuration (from TOP to BOTTOM mount). The actions specified by this AD are intended to prevent the display of target indicators on the wrong side of the aircraft caused by an internal component failure in the SKY497 installations with a top- mounted antenna, which could result in the pilot making an incorrect initial maneuver based on the displayed information while trying to visually acquire the aircraft.
