58 Airworthiness Directives: 48 airplane, 2 rotorcraft, 7 engine, 1 appliance.
AD 96-12-03 R2 · published Oct 1, 1998, effective Nov 20, 1998
Aviat Aircraft, Inc. Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes
This amendment revises Airworthiness Directive (AD) 96-12-03 R1, which applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S- 2, S-2A, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating part number (P/N) 76090, P/ N 2-2107-1, or P/N 1-210-102. AD 96-12-03 R1 currently requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks, and modifying any cracked aft lower fuselage wing attach fitting. Modifying both aft lower fuselage wing attach fittings eliminates the repetitive inspection requirement of AD 96-12- 03. Aviat started incorporating modified aft lower fuselage wing attach fittings on newly manufactured airplanes beginning with serial number 5337, instead of 5349 as referenced in the existing AD. This AD retains the repetitive inspection and possible modification requirements of AD 96-12-03 R1, and will change the applicability accordingly. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.
AD 98-20-36 · published Oct 1, 1998, effective Nov 5, 1998
Airbus Model A300 B2 and B4 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that currently requires inspections for cracks of the fuselage, wings, and vertical stabilizer structures; and repairs or modifications, if necessary. That AD was prompted by reports of cracking in several areas of the fuselage, wings, and vertical stabilizer structure due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the fuselage, wing, and vertical stabilizer. This action provides for a new optional terminating action, for certain airplanes, and expands the applicability of the existing AD to include additional airplanes.
AD 98-20-37 · published Oct 1, 1998, effective Nov 5, 1998
Boeing Model 747-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires the replacement of certain switches located in the cabin attendant's panel at doors 1 and 3 right with new, improved switches. This amendment is prompted by reports indicating that fires have occurred on some airplanes due to the internal failure of some of these switches. The actions specified by this AD are intended to prevent the installation and use of such switches that could short circuit when they fail, and consequently cause fire and smoke aboard the airplane.
AD 98-20-39 · published Oct 1, 1998, effective Nov 20, 1998
Mitsubishi Heavy Industries, Ltd. MU-2B Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. This AD requires inspecting each forward attachment fitting bolt of the wing tip tanks for the correct bolt and replacing any incorrect bolt. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Japan. The actions specified by this AD are intended to prevent the wing tip tank from separating from the airplane because of an incorrect bolt corroding, which could result in loss of control of the airplane.
AD 98-21-08 · published Oct 2, 1998, effective Oct 19, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes. This action requires repetitive functional tests (checks) to verify proper operation of the nose wheel steering system (NWSS) limitswitch, and replacement of the existing limitswitch with a new limitswitch, 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 combined failure of the limitswitch and the feedback shaft in the NWSS servo unit, which could result in uncommanded nose wheel steering deflection and reduced controllability of the airplane on the ground during takeoff or landing.
AD 98-21-02 · published Oct 6, 1998, effective Nov 10, 1998
Fokker Model F27 Mark 050, 100, 200, 300, 400, 500, 600, and 700 Rough Field Version (RFV) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Rough Field Version (RFV) series airplanes, that currently requires inspection of the main landing gear (MLG) legs to determine if parts are missing or damaged, and modification, if necessary; and periodic measurements of the extension of each MLG shock absorber sliding member. That AD also provides for the accomplishment of a certain modification as optional terminating action for the periodic measurements. This amendment requires accomplishment of the previously optional terminating action, and revises the applicability of the existing AD to add an airplane model. 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 MLG sliding member, which could result in reduced structural integrity of the MLG.
AD 98-21-03 · published Oct 6, 1998, effective Nov 10, 1998
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires replacement of the existing load limitation labels located in the main baggage compartment with new reduced load limitation labels. This amendment also provides for optional modification of the internal access door of the main baggage compartment, which, if accomplished, terminates the requirement for reduced load limitations. 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 internal access door latches of the main baggage compartment in the event of an emergency landing, which could delay or impede passenger evacuation due to baggage spilling into the aisle and blocking the emergency exit door.
AD 98-21-04 · published Oct 6, 1998, effective Nov 10, 1998
Dornier Model 328-100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires repetitive visual inspections for signs of fuel leakage on the outer wing beginning with Rib 21 and continuing outward; and corrective action, if necessary. This amendment adds a requirement for modification of the lower panels of the outer wing area, which terminates the repetitive inspection requirements. This action also limits the applicability of the existing 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 fuel leakage on the outboard wing, which could result in a fuel explosion and fire.
AD 98-21-05 · published Oct 6, 1998, effective Nov 10, 1998
Short Brothers Model SD3-30, SD3-60, SD3-60 SHERPA, and SD3 SHERPA Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all SD3-30, SD3-60, SD3-60 SHERPA, and SD3 SHERPA series airplanes, that requires repetitive visual inspections of the flap levers and bracket assembly of the inner flap sub-assembly of the left and right wings to detect certain discrepancies; and corrective actions, if necessary. This amendment is prompted by mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct failure of the levers and bracket assembly, which could result in uncommanded retraction of the inner flap assembly and consequent reduced controllability of the airplane.
AD 98-21-06 · published Oct 6, 1998, effective Nov 10, 1998
British Aerospace Model BAe 146-100A, - 200A, and -300A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that requires either a one-time non-destructive test (NDT) or a visual inspection for cracking of the fuselage skin in the vicinity of frame 29 between stringers 12 and 13, 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 fuselage skin in the specified area, which could result in reduced structural integrity of the airplane.
AD 98-21-07 · published Oct 6, 1998, effective Nov 10, 1998
British Aerospace Model Avro 146-RJ85A and RJ100A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model Avro 146-RJ85A and RJ100A series airplanes, that requires a one-time inspection for evidence of machining (undercutting) into the web of the integral stringers of the bottom skin of the wings, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced wing strength and stiffness, and the onset of premature fatigue cracking, which could result in reduced structural integrity of the airplane.
AD 98-21-11 · published Oct 6, 1998, effective Oct 21, 1998
Boeing Model 737-700 and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-700 and -800 series airplanes. This action requires a one-time inspection to determine the serial numbers of the fire detector assemblies and elements for the auxiliary power unit (APU) and engines, and replacement of the assemblies or elements with new or serviceable parts, if necessary. This amendment is prompted by a report indicating that certain fire detector elements were not checked for leaks during manufacturing and, therefore, may not have the correct set points for the fire warning system. The actions specified in this AD are intended to prevent failure of the APU or engine fire detection systems to detect a fire in a timely manner, which could result in egress of an APU or engine compartment fire to other parts of the airplane.
AD 98-21-10 · published Oct 7, 1998, effective Nov 12, 1998
Aerospatiale Model ATR42-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200 and -300 series airplanes, that requires repetitive inspections for cracking of the lower skin panels of the outer wings; and repair, if necessary. This amendment also requires modification of the panels and a follow-on inspection to detect cracking of the modified areas, which constitute terminating action for the repetitive inspections. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking of the lower skin panels of the outer wings, and consequent reduced structural integrity of the airplane.
AD 98-18-18 · published Oct 8, 1998, effective Oct 8, 1998
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires modification of the attach points of the uplock system of the nose landing gear (NLG). This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent wear of the attach points of the uplock system of the NLG; such wear could result in damage to the adjacent emergency hydraulic system, or jamming of the uplock system and consequent inability to extend and retract the NLG.
AD 98-21-16 · published Oct 8, 1998, effective Jan 6, 1999
British Aerospace Model H.P. 137 Jetstream Mk. 1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-12- 23, which currently requires replacing the windshield wiper arm attachment bolts and windshield wiper arm on all British Aerospace (BAe) Model H.P. 137 Jetstream Mk. 1, Jetstream Series 200, and Jetstream Models 3101 and 3201 airplanes. AD 98-12-13 also requires measuring the material thickness of the upper and lower toggle attachment brackets on the nose landing gear of the affected airplanes, and replacing the toggle attachment bracket lugs. This AD is the result of additional mandatory continuing airworthiness information (MCAI) pertaining to this subject received from the airworthiness authority for the United Kingdom. This AD would retain the actions of AD 98-12- 23; would make certain actions repetitive; and would change the reference to certain service information currently utilized. The actions specified in this AD are intended to prevent the windshield wiper arm from corroding, detaching from the airplane during flight, and penetrating the fuselage, which could result in possible injury to the pilot and passengers; and to prevent collapse of the nose landing gear caused by the current design, which could result in loss of control of the airplane during landing operations.
AD 98-08-25 R1 · published Oct 9, 1998, effective Jan 5, 1999
Twin Commander Aircraft Corporation 500, 680, 690, and 695 Series Airplanes
This amendment revises Airworthiness Directive (AD) 98-08-25, which currently requires replacing the nose landing gear (NLG) drag link bolt with an approved heat-treated bolt that has the manufacturer's serial number, manufacture date, and the last three digits of the drawing number (055) on the bolt head on certain Twin Commander Aircraft Corporation (Twin Commander) 500, 680, 690, and 695 series airplanes; and changing the bolt part number (P/N) to be installed on Models 690D and 695A from P/N ED10055 to P/N 750076-1. The FAA inadvertently transposed the serial numbers of the 4 affected Model 695A airplanes. This AD retains the same actions of AD 98-08-25, and corrects the serial numbers of these 4 airplanes. Three of the four airplanes are not on the U.S. Register and the other one is already in compliance with the actions of AD 98-08-25. The actions specified in this AD are intended to continue to prevent the NLG from collapsing due to failure of a drag link bolt, which could result in loss of control of the airplane during landing operations.
AD 98-21-13 · published Oct 13, 1998, effective Nov 20, 1998
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 replacing the elevator trim servo motor with a new motor of improved design; and inspecting the cable tension and electrical operation of the elevator and trim tab for proper operation, and making any necessary adjustments. 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 the elevator trim servo motor drive gear assembly from remaining engaged when the autopilot is disengaged, which could result in the pilot having to manually overpower the elevator trim control and possibly lose directional control of the airplane during critical phases of flight.
AD 98-21-14 · published Oct 13, 1998, effective Nov 2, 1998
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 modifying the airplane's navigational system by shortening and re-clipping the cable looms to the No. 1 and No. 2 vertical gyroscopes, installing a warning label adjacent to the gyroscopes, and performing an operational check on the system. 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 a cross connection in the No. 1 and No. 2 vertical gyroscopes, which could result in navigational errors during flight.
AD 98-21-15 · published Oct 13, 1998, effective Nov 20, 1998
SOCATAGroupe AEROSPATIALE Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires modifying the oxygen generators. 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 failure of the oxygen generators caused by misalignment of the firing pin, which could result in crew incapacitation and loss of the airplane.
AD 98-21-17 · published Oct 13, 1998, effective Nov 17, 1998
Boeing Model 747 Series Airplanes Equipped with Pratt & Whitney Model JT9D-70 Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect fatigue cracking of the spring beams on the outboard struts; replacement of cracked spring beams with new or serviceable spring beams; and follow-on actions. That action also provides an optional terminating action for the repetitive inspections. This amendment removes that optional terminating action, and requires a new terminating action. This amendment is prompted by the development of an improved process for manufacturing titanium spring beams that will eliminate the embedded porosity flaws in the existing spring beams from which fatigue cracking can originate. The actions specified by this AD are intended to prevent fatigue cracking of the spring beam, which could result in loss of an outboard strut.
AD 98-21-18 · published Oct 13, 1998, effective Nov 17, 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 the de-icing system timer with a new, improved timer. This amendment is prompted by reports of possible overheating and debonding of the propeller blade due to a failure of the de-icing system timer and a dormant short circuit in the propeller de-icer system. The actions specified by this AD are intended to prevent such overheating and debonding of the propeller blade, which could result in reduced controllability of the airplane.
AD 98-21-19 · published Oct 13, 1998, effective Nov 17, 1998
Saab Model SAAB 2000 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that currently requires deactivation of certain floormat heaters in the cabin area. In addition, that AD provides for optional terminating action for that deactivation. This amendment removes the optional terminating action of the existing AD and adds airplanes to the applicability of the existing 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 short circuiting between the flight attendant's floormat heater and the floor panel, which could cause overheating of the floormat heater and lead to smoke or fire in the airplane cabin.
AD 98-21-28 · published Oct 14, 1998, effective Jan 15, 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 modifying the propeller de-icing system to assure system performance at low ambient temperatures. 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 prevent propeller-induced vibrations from occurring during icing encounters at low ambient temperatures, which could result in decreased performance of the de-icing system during icing encounters with possible loss of control of the airplane.
AD 98-21-20 · published Oct 15, 1998, effective Nov 20, 1998
Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes
This amendment supersedes Airworthiness Directive (AD) 97-04- 02, which currently requires installing new exterior placards with operating instructions for the airstair door, cargo door, and emergency exits, as applicable, on certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. This AD requires either modifying the existing exterior placards with door operating instructions installed in accordance with AD 97-04-02; or installing new exterior placards with operating instructions for the airstair door, cargo door, and emergency exits, as applicable. This AD results from reports of the placards (required by AD 97-04-02) covering the atmospheric vents for the cabin door differential pressure lock. The actions specified by this AD are intended to continue to assure that clear and complete operating instructions are visible for opening the airstair door, cargo door, or emergency exits, and to prevent improper operation of the cabin door differential pressure lock caused by the placards blocking the atmospheric vents.
AD 98-21-25 · published Oct 15, 1998, effective Nov 26, 1998
British Aerospace Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Models 3101 and 3201 airplanes that are equipped with the ground inhibit function (Modification JM7813A (SB 27-JM7813A) or JM7813B). This AD requires removing the ground inhibit time delay and the ground test relay from the stall warning and protection system and rewiring part of the stall warning and protection system to assure that system reliance is maintained after relay removal. 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 failure of the ground inhibit relay while it is in the energized position caused by the current design, which could result in failure of the stall warning system and possible loss of control of the airplane in certain situations if the crew was not aware that the system had failed.
AD 98-21-26 · published Oct 15, 1998, effective Nov 26, 1998
Mooney Aircraft Corporation Models M20J, M20K, M20M, and M20R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Mooney Aircraft Corporation (Mooney) Models M20J, M20K, M20M, and M20R airplanes. This AD requires grinding the surface of the main landing gear (MLG) leg bracket, inspecting this area for cracks, and replacing any cracked MLG leg bracket. This AD is the result of the manufacturing of several of the MLG leg brackets using laser pattern cutting. The brackets, when manufactured using this process, develop minor cracks at the bends, which could propagate over time. The actions specified by this AD are intended to prevent failure of the MLG side brace bolt caused by cracking of the MLG leg bracket, which could result in MLG collapse with consequent loss of control of the airplane during taxi, takeoff, or landing operations.
AD 98-21-27 · published Oct 16, 1998, effective Nov 26, 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. (Pilatus) Models PC-12 and PC-12/45 airplanes that are equipped with the ``corporate commuter cabin layout.'' This layout is a Pilatus designation only and the affected airplanes are not certificated for commuter operation. This AD requires modifying the passenger seats and seat rail covers. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent passenger injuries because the passenger seat configuration has been found to not fully meet current head injury criteria regulations.
AD 98-21-29 · published Oct 16, 1998, effective Nov 20, 1998
Boeing Model 747-100, -200, -300, -400, 747SP, and 747SR Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, -300, -400, 747SP, and 747SR series airplanes, that requires a one-time visual inspection to determine the part number of the fuel shutoff valve installed in the outboard engines. The AD also requires replacement of certain valves with new valves, or modification of the spar valve body assembly, and various follow-on actions. This amendment is prompted by reports indicating that, due to high fuel pressure, certain fuel system components of the outboard engines have failed on in-service airplanes. The actions specified by this AD are intended to prevent such high fuel pressure, which could result in failure of the fuel system components; this situation could result in fuel leakage and, consequently, lead to an engine fire.
AD 98-21-30 · published Oct 16, 1998, effective Nov 20, 1998
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes and all Model A310 and A300-600 series airplanes, that requires repetitive inspections for wear damage of the aft attachment fittings of the articulated seats and dummy tracks in the passenger compartment; 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 wear damage of the aft attachment fittings of the articulated seats and dummy tracks. Such wear damage could cause the floor panels to sag and result in failure of flight control systems and consequent reduced controllability of the airplane.
AD 98-21-31 · published Oct 16, 1998, effective Nov 2, 1998
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes. This action requires incorporating into the FAA-approved maintenance program certain torque values for installing certain nuts and bolts of the engine attachment fittings; 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 in this AD are intended to prevent cracking of the nuts and bolts of the engine attachment fittings due to overtorquing; such cracking could propagate and result in separation of the engine from the airplane.
AD 98-21-32 · published Oct 16, 1998, effective Nov 20, 1998
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that currently requires performing a ram air turbine (RAT) extension test; removing and disassembling the RAT uplock mechanism; performing an inspection to detect corrosion of the RAT uplock mechanism, and replacement with a new assembly, if necessary; and cleaning all the parts of the RAT control shaft and its bearing component parts. This amendment requires modification of the RAT unlocking control unit, which constitutes terminating action for the repetitive tests and inspections. This amendment also limits the applicability of the existing 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 corrosion of the RAT uplock pin/shaft and needle, which could result in failure of the RAT to deploy and consequent loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
AD 98-21-33 · published Oct 16, 1998, effective Nov 20, 1998
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time inspection of the torque links of the main landing gear (MLG) assemblies to determine if the lockwire is present on the apex bolt; 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 MLG due to loose connections between the upper and lower torque links of the MLG.
AD 98-21-34 · published Oct 16, 1998, effective Nov 20, 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 inspections to detect corrosion and cracks on the bottom area of the wing skin, 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 detect and correct corrosion and cracks on the bottom area of the wing skin, which could result in reduced structural integrity of the airplane.
AD 98-21-35 · published Oct 16, 1998, effective Nov 23, 1998
Raytheon Aircraft Company Models A200CT, B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models A200CT, B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C airplanes. This AD requires replacing the main landing gear left and right actuator clevis assembly. Reports of main landing gear failure on two of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent failure of the actuator clevis assembly in the main landing gear caused by fatigue cracking of the original design part, which could result in loss of control of the airplane during landing operations.
AD 98-21-37 · published Oct 20, 1998, effective Nov 23, 1998
McDonnell Douglas Model DC-10-10, -15, -30, and -40 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and - 40 series airplanes, that requires installation of a new protector cap in all fuel tank boost/transfer pump housings. This amendment is prompted by reports of inoperative fuel boost/transfer pumps due to arcing or burning of the electrical connectors. The actions specified by this AD are intended to prevent damage to the fuel tank boost/ transfer pump housings in case of an electrical connector malfunction, which could result in increased risk of a fuel tank explosion or fire.
AD 83-22-01 R1 · published Oct 22, 1998
The New Piper Aircraft, Inc.; Models PA-23-235, PA-23-250, and PA-E23-250 Airplanes
This amendment clarifies information contained in Airworthiness Directive (AD) 83-22-01, which currently requires inserting certain zero fuel weight limitations into the Limitations Section of the airplane flight manual (AFM) on certain The New Piper Aircraft, Inc. (Piper) Models PA-23-235, PA-23-250, and PA-E23-250 airplanes. The FAA has received reports that reference in the AD to two of the AFM reports contains incorrect information. In particular, reference to Report 1308, Revision B, contains the words ``normally aspirated''; and reference to Report 1360, Revision B, contains the word ``Turbocharged.'' These references should be removed. This document clarifies AD 83-22-01 by removing the words ``normally aspirated'' and ``Turbocharged'' from the reference to these reports. The actions specified in this AD are intended to continue to prevent possible wing structure damage caused by excessive fuel weight, which could result in loss of control of the airplane.
AD 98-22-02 · published Oct 22, 1998, effective Nov 27, 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 replacement of the outboard trunnion pin of the shock strut on the main landing gear (MLG) with a new and improved outboard trunnion pin. 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 outboard trunnion pin due to fatigue cracking, which could result in collapse of the MLG.
AD 98-22-03 · published Oct 22, 1998, effective Nov 27, 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 a one-time visual inspection of the main landing gear (MLG) brake assemblies to determine the brake configuration, and reconfiguration, 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 an incorrect brake combination configuration of the MLG, and consequent reduced controllability of the airplane during take-off and landing.
AD 98-22-04 · published Oct 22, 1998, effective Nov 27, 1998
Construcciones Aeronauticas, S.A. (CASA) Model C-212 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that currently requires replacement of the cover of the power control quadrant pedestal with a cover that incorporates slot protection. This amendment requires repetitive inspections for deterioration or damage of the slot protection installed in the cover of the power control quadrant pedestal. This amendment also requires eventual modification of the cover, 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 deterioration of the slot protection installed in the cover of the power control quadrant pedestal, which could allow foreign objects to jam or interfere with the power or trim control system and result in reduced controllability of the airplane.
AD 98-22-05 · published Oct 22, 1998, effective Nov 27, 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 lower surface panel on the wing center box; and repair, if necessary. This amendment also requires modification of the lower surface panel on the wing center box, 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 lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane.
AD 98-22-07 · published Oct 27, 1998, effective Nov 12, 1998
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires revising the Airplane Flight Manual to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. 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 uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
AD 98-22-10 · published Oct 27, 1998, effective Nov 12, 1998
Boeing Model 737 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires repetitive inspections for cracking of the aft frame and frame support structure of the forward service doorway, and repair, if necessary. This amendment reduces the compliance time for performing the initial inspection, and reduces the repetitive inspection intervals. This amendment also adds repetitive inspections for cracking of the aft frame web of the forward service doorway, and follow-on corrective actions, if necessary. This amendment also provides for an optional terminating action for the repetitive inspection requirements of this AD. This amendment is prompted by reports indicating that the repetitive inspections required by the existing AD may not detect cracking of the aft frame and frame support structure of the forward service doorway in a timely manner. The actions specified in this AD are intended to prevent fatigue cracking of the aft frame and frame support structure of the forward service doorway, which could result in loss of the door, and consequent rapid decompression of the fuselage.
AD 98-22-08 · published Oct 28, 1998, effective Dec 2, 1998
Aerospatiale Model SN 601 (Corvette) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model SN 601 (Corvette) series airplanes, that requires repetitive inspections to detect discrepancies of the upper and lower reinforcement panels and panel fasteners of the wing roots; 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 debonding of the upper and lower reinforcement panels of the wing roots, which could result in reduced structural integrity of the wing.
AD 98-22-09 · published Oct 28, 1998, effective Dec 2, 1998
Dassault Model Falcon 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 series airplanes, that requires modification of the front galley and rear lavatory water heaters. 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 water heater control thermostat and the associated electrical relay, which could lead to overheating of the water and damage to the adjacent wiring, and consequent smoke and fumes in the passenger cabin and possible injury to the flight crew and passengers.
AD 98-22-12 · published Oct 28, 1998, effective Nov 12, 1998
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires repetitive detailed visual inspections to detect cracked, corroded, or stained collar fittings on both inboard trailing edge flaps; and follow-on corrective actions, if necessary. This amendment is prompted by a report indicating that a collar fitting suffered a complete fracture as a result of stress corrosion cracking. The actions specified in this AD are intended to prevent separation of the inboard trailing edge flap from the airplane due to fractured collar fittings.
AD 98-22-13 · published Oct 28, 1998, effective Dec 2, 1998
McDonnell Douglas Model DC-9-10, -20, - 30, and -40 Series Airplanes; and C-9 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, and - 40 series airplanes; and certain C-9 (military) series airplanes. This amendment requires modifying the piping of the potable water system. This amendment is prompted by reports of ice forming on the control cables in the wheel well of the left main landing gear due to the freezing and rupturing of undrained potable water pipes. The actions specified by this AD are intended to prevent such ice formation, which could render the slat, aileron, and spoiler flight controls inoperative, and consequently could result in reduced controllability of the airplane.
AD 97-01-01 R1 · published Oct 29, 1998, effective Dec 8, 1998
The New Piper Aircraft, Inc. PA-24, PA- 28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes
This amendment revises AirworthinessDirective (AD) 97-01-01, which currently requires repetitively inspecting the main gear sidebrace studs for cracks on The New Piper Aircraft, Inc. (Piper)Models PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 series airplanes, and replacing any main gear sidebrace stud found cracked. The Federal Aviation Administration (FAA) has approved certain alternative methods of compliance (AMOC) for AD 97-01-01, and has determined that these AMOC's should be incorporated into the AD. This AD will retain all the actions of AD 97-01-01, and will incorporate certain AMOC's as a way of accomplishing the actions specified in AD 97-01-01. The actions specified by this AD are intended to prevent a main landing gear collapse caused by main gear sidebrace stud cracks, which could result in loss of control of the airplane during landing operations.
AD 96-10-01 R1 · published Oct 30, 1998, effective Dec 14, 1998
The New Piper Aircraft, Inc. Models PA- 28-140, PA-28-150, PA-28-160, and PA-28-180 Airplanes
This amendment revises Airworthiness Directive (AD) 96-10-01, which currently requires a complete landing light support replacement on certain The New Piper Aircraft, Inc. (Piper) Models PA-28-140, PA-28-150, PA-28-160, and PA-28-180 airplanes. Some of the serial numbers for these airplanes were incorrectly referenced in the Applicability section of AD 96-10-01. This AD maintains the requirements of AD 96-10-01, and corrects the serial numbers referenced in the Applicability section. The actions specified by this AD are intended to prevent the landing light retainer support seal from being ingested by the updraft carburetor, which could result in rough engine operation or possible engine failure and loss of control of the airplane.
AD 98-21-12 · published Oct 7, 1998, effective Oct 22, 1998
McDonnell Douglas Helicopter Systems Model 369D, 369E, 369FF, 500N, AH-6, and MH-6 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369D, 369E, 369FF, 500N, AH-6 and MH-6 helicopters. This action requires visual inspections of the overrunning clutch retainer, carrier, housing, and pin for wear from spinning of the bearing outer race. This amendment is prompted by a report of inflight vibrations and subsequent investigations of three other overrunning clutches, which indicated wear of the bearing carrier due to spinning of the bearing outer race. The actions specified in this AD are intended to detect wear of other clutch components, excessive vibration which could lead to failure of the overrunning clutch, wear on the bearing carrier, and subsequent loss of power to the helicopter rotor drive system.
AD 98-21-36 · published Oct 19, 1998, effective Nov 23, 1998
Robinson Helicopter Company Model R44 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters, that requires removing and replacing the cyclic control pilot's grip assembly (grip assembly) with an airworthy grip assembly. This amendment is prompted by a report of a crack in the welded corner of a grip assembly. The actions specified by this AD are intended to prevent use of a grip assembly that may crack, resulting in failure of the grip assembly and subsequent loss of control of the helicopter.
AD 98-17-10 · published Oct 6, 1998, effective Oct 21, 1998
Pratt & Whitney Canada PW530A Series Turbofan Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-17-10 that was sent previously to all known U.S. owners and operators of Pratt & Whitney Canada (PWC) PW530A series turbofan engines by individual letters. This AD requires recording engine surge events in the aircraft maintenance records. If an engine surge event is experienced, this AD requires, prior to the next flight, inspecting that engine for evidence of second stage stator vanes rubbing on the compressor rotor. In addition, this AD requires reworking all affected engines to increase the clearance between the second stage stator vanes and the compressor rotor. This amendment is prompted by reports of 4 inflight engine shutdowns and 2 additional unscheduled engine removals for significant compressor rotor damage. The actions specified by this AD are intended to prevent an inflight engine shutdown due to rubbing of the second stage stator vanes on the compressor rotor.
AD 98-21-01 · published Oct 6, 1998, effective Oct 21, 1998
International Aero Engines AG (IAE) V2500-A1 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to International Aero Engines AG (IAE) V2500-A1 series turbofan engines. This action requires a one-time ultrasonic inspection of fan blade roots for cracks, and, if necessary, replacement of cracked fan blades with serviceable parts. This amendment is prompted by a report of dovetail root cracks visually detected on three fan blades from one engine during a routine inspection. The actions specified in this AD are intended to prevent fan blade root cracks, which could result in fan blade root failures, an uncontained engine failure, and damage to the aircraft.
AD 98-21-22 · published Oct 16, 1998, effective Dec 15, 1998
Pratt & Whitney JT9D Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT9D series turbofan engines, that requires initial and repetitive eddy current inspections (ECI) of 14th and 15th stage high pressure compressor (HPC) disks for cracks, and removal of cracked disks and replacement with serviceable parts. This amendment is prompted by reports of disk bore cracks found during shop inspections on both the 14th and 15th stage HPC disks. The actions specified by this AD are intended to prevent 14th and 15th stage HPC disk rupture, which could result in an uncontained engine failure and damage to the aircraft.
AD 98-21-23 · published Oct 16, 1998, effective Nov 2, 1998
CFM International, S.A. CFM56-7B Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International, S.A. (CFMI) CFM56-7B series turbofan engines. This action supersedes telegraphic AD T98-18-51 that currently requires an inspection of electronic engine control (EEC) fault messages on both engines for the presence of any of the hydromechanical unit (HMU) fuel metering valve (FMV) signal faults identified in the All Operators Wire every 20 flight cycles or 3 calendar days, whichever occurs first, and, if necessary, removing the HMU and replacing it with a serviceable HMU. This action also requires installation of improved EEC software that constitutes terminating action to the repetitive fault message inspections. This amendment is prompted by development of improved EEC software that obviates the need for the repetitive fault message inspections. The actions specified by this AD are intended to prevent an uncommanded engine acceleration event, or inflight engine shutdown.
AD 98-21-24 · published Oct 16, 1998, effective Nov 16, 1998
Pratt & Whitney JT8D Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D series turbofan engines, that requires removal, visual inspection, eddy current inspection, repair or replacement of affected compressor disks. This amendment is prompted by reports of improper fixturing during the electrolytic cleaning process of certain compressor disks at a certified repair station, Avial or Greenwich Air Services, currently GE Engine Services Dallas LP, certificate number RA1R445K of Dallas, Texas, that can result in damage to the disks in the form of arc burns. The actions specified by this AD are intended to prevent compressor disk cracking from arc burns in tie rod holes, shielding holes, or pressure balance holes, which could lead to a fracture of a compressor disk, resulting in uncontained release of engine fragments, inflight engine shutdown, and airframe damage.
AD 96-18-08 R1 · published Oct 26, 1998, effective Nov 10, 1998
Pratt & Whitney PW2000 Series Turbofan Engines
This amendment revises an existing airworthiness directive (AD), applicable to Pratt & Whitney PW2000 series turbofan engines, that currently requires a reduction in the cyclic service life limit for hubs, disks, airseals, blade retaining plates, and airsealing ring supports on certain high pressure turbines (HPT) and low pressure turbines (LPT), and provides for optional inspections for cracks or rework of certain HPT and LPT hardware in order to retain the original, higher cyclic service life limit for these components. This amendment clarifies questions from operators regarding 2nd stage HPT hub detail vs. assembly part numbers (P/Ns). This amendment is prompted by comments from operators describing confusion as to which 2nd stage HPT hubs, identified by P/N, needed to be removed prior to the new life limit. The actions specified by this AD are intended to prevent HPT or LPT failure, which may result in an uncontained engine failure and possible damage to the aircraft.
AD 98-22-06 · published Oct 28, 1998, effective Nov 23, 1998
General Electric Company CF6-6, -45, - 50, -80A, and -80C2 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-6, -45, -50, -80A, and - 80C2 series turbofan engines. This action requires, prior to further flight, an ultrasonic immersion inspection for cracks in stage 1 fan disks, and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracked fan disks found during routine shop inspections on fan disks manufactured between late 1984/ early 1985. The actions specified in this AD are intended to prevent fan disk failure due to cracks, which could result in an uncontained engine failure and damage to the aircraft.
AD 98-21-21 · published Oct 15, 1998, effective Oct 30, 1998
Bob Fields Aerocessories Inflatable Door Seals
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-21-21, which was sent previously to all known U.S. owners and operators of aircraft equipped with Bob Fields Aerocessories inflatable door seals installed in accordance with the applicable supplemental type certificate (STC). These inflatable door seals could also be installed on aircraft through field approval.This AD requires either de-activating the electric door seal inflation system; fabricating and installing a placard specifying that the system is inoperative; and inserting a copy of the AD into the Limitations Section of the airplane flight manual (AFM); or removing all provisions of the Bob Fields Aerocessories inflatable door seals installation, and installing original equipment manufacturer door seals or an FAA-approved equivalent that is of different design than the referenced Bob Fields Aerocessories inflatable door seals. The AD resulted from occurrences of overheated components associated with the electric door seal inflation system on aircraft equipped with the affected inflatable door seals. The actions specified by this AD are intended to prevent smoke and a possible fire in the cockpit caused by overheating of the electric door seal inflation systems, which could result in passenger injury.
