51 Airworthiness Directives: 37 airplane, 4 rotorcraft, 10 engine.
AD 2000-11-03 · published Jun 1, 2000, effective Jun 16, 2000
Dassault Model Falcon 2000, Mystere-Falcon 900, Falcon 900EX, Fan Jet Falcon, Mystere-Falcon 50, Mystere-Falcon 20, and Mystere-Falcon 200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Falcon 2000, Mystere-Falcon 900, Falcon 900EX, Fan Jet Falcon, Mystere-Falcon 50, Mystere-Falcon 20, and Mystere-Falcon 200 series airplanes. This action requires revising the Airplane Flight Manual to include speed limitations in the event of failure indications of the pitch feel system. These limitations are intended to mitigate severe pitch oscillations of the airplane.
AD 2000-11-04 · published Jun 1, 2000, effective Jun 23, 2000
Commander Aircraft Company Model 114TC Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Commander Aircraft Company (Commander) Model 114TC airplanes. This AD requires you to replace the existing Aeroquip V-band exhaust clamp with a new clamp of improved design. This AD is the result of reports of this clamp failing on 4 of the affected airplanes. This clamp attaches the exhaust stack to the turbocharger. The actions specified in this AD are intended to prevent the exhaust stack from detaching from the turbocharger due to failure of the V-band exhaust clamp. This could result in the release of high temperature gases inside the engine compartment with a consequent airplane cabin fire.
AD 2000-11-07 · published Jun 1, 2000, effective Jul 6, 2000
Boeing Model 747-200, -300, and -400 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that currently requires repetitive high frequency eddy current (HFEC) inspections to detect cracking of the front spar web of the center section of the wing, and repair, if necessary. This amendment requires that the existing inspection be accomplished at a reduced threshold, and adds a requirement that the existing HFEC inspection be accomplished on repaired areas. This amendment is prompted by reports of cracking in repaired areas of the front spar web and cracking of the front spar web on an airplane that had accumulated fewer flight cycles than the inspection threshold of the existing AD. The actions specified by this AD are intended to prevent the leakage of fuel into the forward cargo bay, as a result of fatigue cracking in the front spar web, which could result in a potential fire hazard.
AD 2000-11-08 · published Jun 1, 2000, effective Jul 6, 2000
Boeing Model 747 and 767 Series Airplanes Powered by General Electric Model CF6-80C2 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 and 767 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to prohibit the use of certain fuels; and either replacing an existing placard with a new placard, or replacing all dribble flow fuel nozzles (DFFN) with standard fuel nozzles, which terminates the requirements for the new placard and AFM revision. This amendment continues these requirements and adds identical requirements applicable to airplanes on which standard fuel nozzles are not installed. This amendment is prompted by a report of an engine flameout due to use of JP-4 or Jet B fuel during certification testing on an engine with DFFN's installed. The actions specified by this AD are intended to prevent such engine flameouts and consequent engine shutdown.
AD 2000-11-09 · published Jun 1, 2000, effective Jul 6, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections of the sliding tube subassembly on the main landing gear (MLG) to detect cracks, and replacement of a cracked subassembly with a new subassembly. This amendment also eventually requires a more extensive, one-time inspection of the same area and corrective actions, if necessary; 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 cracking of the MLG sliding tube subassembly, which could result in collapse of the MLG.
AD 2000-11-05 · published Jun 2, 2000, effective Jun 23, 2000
Air Tractor Incorporated Models AT-301, AT-401, and AT-501 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor Incorporated (Air Tractor) Models AT- 301, AT-401, and AT-501 airplanes that are equipped with a \3/16\-inch thick aluminum fin front spar fitting and an all metal rudder. This AD requires that you repetitively inspect the vertical fin front spar attachment fittings for fatigue cracks, and rework the vertical fin if any cracks are found. This AD is the result of reports of a vertical fin front spar fitting failure on a Model AT-401 airplane. The actions specified by this AD are intended to detect and correct cracks in the vertical fin front spar attachment fittings, which could result in failure of the vertical fin. This condition could lead to loss of directional control and eventual loss of airplane control.
AD 2000-11-14 · published Jun 2, 2000
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/ 45 airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident (on airplanes other than the affected Pilatus airplanes) that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The Pilatus Models PC-12 and PC-12/45 airplanes have a similar type design (as it relates to airframe pneumatic ice boots) to the incident and accident airplanes. The actions specified by this AD are intended to assure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-11-11 · published Jun 5, 2000, effective Jul 10, 2000
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires one-time inspections to detect cracking of the aft wheel well bulkhead, corrective actions, if necessary, and modification of the aft wheel well bulkhead. For certain airplanes, this AD also requires a one-time visual inspection to detect excess sealant covering the outer flange of the side fitting and lower chord and splice area of the aft wheel well bulkhead, and corrective actions, if necessary. This amendment is prompted by a report indicating that numerous fatigue cracks were found in the aft wheel well bulkhead. The actions specified by this AD are intended to prevent fatigue cracking of the aft wheel well bulkhead, which could result in rapid in-flight decompression of the airplane.
AD 2000-11-13 · published Jun 6, 2000, effective Jul 11, 2000
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time review of the maintenance records to determine if tripping of the fuel boost pump circuit breakers has been recorded, repetitive inspections to detect fuel leakage from the fuel boost pump wiring conduits, and corrective actions, if necessary. This amendment also requires replacement of the three single wires inside the metal conduit of the fuel boost pumps with new wires protected by a polyamide sleeve, 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 the fuel boost pump wiring from chafing, which could result in electrical arcing and a possible fuel tank ignition source.
AD 2000-10-20 · published Jun 7, 2000, effective Jul 12, 2000
Lockheed Model L-1011-385 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires repetitive inspections to detect cracking of the fuselage skin in the areas of the left- and right-hand stringerless sidewall window belts, and repair, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin where the skin thickness steps from 0.40 to 0.23 inch. The actions specified by this AD are intended to detect and correct cracking of the fuselage skin, which could result in reduced structural integrity of the airplane.
AD 2000-11-16 · published Jun 7, 2000, effective Jul 25, 2000
Ayres Corporation S2R Series and Model 600 S2D Airplanes
This amendment supersedes Airworthiness Directive (AD) 97-17- 03, which currently requires you to accomplish the following on Ayres Corporation (Ayres) S2R Series and Model 600 S2D airplanes: inspect the \1/4\-inch and \5/16\-inch bolt hole areas on the lower spar caps for fatigue cracking; replace any lower spar cap where fatigue cracking is found; and report any fatigue cracking. This AD retains the inspection and replacement (if necessary) requirements of the lower spar caps that are currently required in AD 97-17-03. This AD also makes these inspections repetitive, adds additional airplanes to the Applicability of the AD, changes the initial compliance time for all airplanes, and arranges the affected airplanes into groups (six) based on usage and configurations. The existing AD was the result of an accident of an Ayres S2R series airplane where the wing separated from the airplane in flight. The actions specified by this AD are intended to detect and correct fatigue cracking of the lower spar caps, which could result in the wing separating from the airplane with consequent loss of control of the airplane.
AD 2000-10-51 · published Jun 13, 2000, effective Jun 19, 2000
Boeing Model 767 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-10-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 767 series airplanes by individual notices. This AD requires a one-time inspection to determine whether certain bolts are installed in the side load underwing fittings on both struts, and various follow-on actions, if necessary. This action is prompted by a report that two fractured bolts and one cracked bolt were found in the side load underwing fittings. The actions specified by this AD are intended to detect and correct cracking or fracturing of the tension bolts on the side load underwing fittings on the strut, which would eventually result in loss of the strut.
AD 2000-11-19 · published Jun 13, 2000, effective Jul 18, 2000
Boeing Model 767-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that requires repetitive inspections to detect wear or damage of the door latches and disconnect housings in the off-wing escape slide compartments, and replacement of any discrepant component with a new component. This amendment is prompted by reports of worn and damaged door latches and disconnect housings in the off-wing escape slide compartments. The actions specified by this AD are intended to ensure deployment of an escape slide during an emergency evacuation. Non- deployment of an escape slide during an emergency could slow down the evacuation of the airplane and result in injury to passengers or flightcrew. The actions specified by this AD are also intended to detect damaged disconnect housings in the off-wing escape slide compartments, which could result in unexpected deployment of an escape slide during maintenance, and consequent injury to maintenance personnel.
AD 2000-11-20 · published Jun 13, 2000, effective Jul 18, 2000
Bombardier Model DHC-8-100 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 and -300 series airplanes, that requires revising the Aircraft Log Book to correct the airplane Production Modification List; performing an inspection to determine which bonded skin panels on the airplane require bonding integrity inspections (BII); and revising the Airworthiness Limitations List of the Approved Maintenance Plan to include the BII requirements. This amendment also requires, for certain airplanes, repetitive ultrasonic bond inspections to detect disbonding of airplane skin panels, 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 prevent damage to bonded skin panels to go undetected, which could result in failure of the bonded skin panels, and consequent loss of controllability of the airplane.
AD 2000-11-21 · published Jun 13, 2000, effective Jul 18, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires a one-time general visual inspection to determine the part number and serial number of the spoiler servocontrol, 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 spoiler servocontrol piston rod, which could result in reduced controllability of the airplane.
AD 2000-11-23 · published Jun 13, 2000, effective Jul 18, 2000
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 an inspection to detect damage of the electrical bonding leads in specified locations of the fuel tanks, and replacement of any damaged electrical bonding leads with serviceable electrical bonding leads. For certain airplanes, this amendment also requires modifying the fuel pipe couplings in specified locations of the fuel tank. 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 electrical arcing/discharge in the fuel tank due to damaged electrical bonding leads or inadequate electrical bonding of the fuel pipe couplings, which could result in fuel ignition and consequent uncontained rupture of the fuel tank.
AD 2000-11-24 · published Jun 13, 2000, effective Jul 18, 2000
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive inspections to detect discrepancies of the downlock support assembly and attachment of the nose landing gear (NLG), and of the bulkhead and adjacent structure in the NLG bay; 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 damage of the NLG downlock support, which could result in collapse of the NLG and consequent injury to passengers or flightcrew.
AD 2000-11-25 · published Jun 13, 2000, effective Jul 18, 2000
Airbus Model A320-232 and -233 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-232 and -233 series airplanes, that requires replacement of the fuel metering units (FMU) of each engine with modified FMU's. 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 inadvertent increase in thrust, which could result in reduced controllability of the airplane during final approach.
AD 2000-11-26 · published Jun 13, 2000, effective Jul 18, 2000
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires repetitive ultrasonic inspections to detect corrosion of the retraction links of the main landing gear (MLG), and replacement of the retraction link with a new retraction link, 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 of the retraction link of the MLG, which could result in reduced structural integrity and possible collapse of the MLG.
AD 2000-11-27 · published Jun 13, 2000, effective Jun 28, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires a one-time ultrasonic inspection to detect disbonding of the skin attachments at the stringers and spars of the vertical stabilizer, and repair, if necessary. This action is necessary to detect and correct disbonding of the vertical stabilizer structure, which could result in reduced structural integrity of the spar boxes of the vertical stabilizer.
AD 2000-11-28 · published Jun 13, 2000, effective Jul 18, 2000
Boeing Model 747-400 and 767-200 and -300 Series Airplanes Powered by Pratt & Whitney Model PW4000 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and 767-200 and -300 series airplanes, that requires repetitive inspections to detect damage and wear of the auxiliary track assembly of the thrust reverser, and corrective actions, if necessary. This amendment also requires eventual repair of the auxiliary track assembly, or replacement of the slider and liner or the entire assembly, with new, improved parts, which, when accomplished, would terminate the repetitive inspections. This amendment is prompted by reports of damage and wear to the auxiliary track assembly. The actions specified by this AD are intended to prevent a slider disengaging from the auxiliary track assembly, which could lead to separation of a portion of the thrust reverser from the airplane during flight, possible impact of separated portions on airplane structure, and consequent possible rapid decompression of the airplane, reduced controllability of the airplane, or reduced structural integrity of the fuselage.
AD 2000-11-29 · published Jun 14, 2000, effective Jul 19, 2000
Fokker Model F27 Mark 050, 100, 200, 300, 400, 500, 600, and 700 Series Airplanes; and Model F28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050, 100, 200, 300, 400, 500, 600, and 700 series airplanes, and Model F28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time functional test to verify correct installation of the shoulder harnesses of the pilot's and co-pilot's seats and, if necessary, replacement of the shoulder harness assembly with a new or serviceable shoulder harness assembly. 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 shoulder harness, which could result in injury to the flight crew during extremely turbulent flight conditions or during emergency landing or stopping conditions.
AD 2000-12-04 · published Jun 14, 2000, effective Jul 19, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires an initial inspection of fastener holes on certain outer frames of the fuselage to detect fatigue cracking, and modification of the area by cold expanding the holes and installing oversized fasteners. This amendment requires revising the applicability to include additional airplanes; a high frequency eddy current inspection to detect fatigue cracking in the frames and frame feet at fuselage frames FR37 through FR41; and follow-on actions. This amendment also provides for an optional terminating action for the follow-on 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 fuselage frames and frame feet, and consequent reduced structural integrity of the fuselage.
AD 2000-12-06 · published Jun 15, 2000, effective Jul 20, 2000
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive inspections to check the play of the eye-end of the piston rod of the elevator servo-controls, and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct excessive play of the eye-end of the piston rod of the elevator servo-controls, which could result in failure of the elevator servo-control.
AD 2000-12-07 · published Jun 15, 2000, effective Jul 20, 2000
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 inspection to detect corrosion and scratches on the bearing housing surfaces of the support assembly on the main landing gear (MLG), 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 corrosion in the inboard and outboard bearing housings of the MLG support assembly, which could result in fatigue cracks in the support assembly and lead to failure of the MLG.
AD 2000-12-15 · published Jun 15, 2000
Dassault Model Falcon 2000, Mystere-Falcon 900, Falcon 900EX, Fan Jet Falcon, Mystere-Falcon 50, Mystere-Falcon 20, Mystere-Falcon 200, and Falcon 10 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Falcon 2000, Mystere-Falcon 900, Falcon 900EX, Fan Jet Falcon, Mystere-Falcon 50, Mystere-Falcon 20, Mystere-Falcon 200, and Falcon 10 series airplanes, that requires repetitive tests and inspections to detect discrepancies of the overwing emergency exit; 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 overwing emergency exits to open, and consequent injury to passengers or crew members during an emergency evacuation.
AD 2000-12-11 · published Jun 19, 2000, effective Jul 24, 2000
Airbus Model A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that currently requires repetitive ultrasonic inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair, if necessary. This amendment requires revising the compliance thresholds for the inspection and requires that the inspections be repeated at reduced intervals. 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 cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.
AD 2000-12-13 · published Jun 19, 2000, effective Jul 24, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to increase monitoring of the flight path of the airplane to detect certain software anomalies of the flight management guidance system, and take appropriate corrective actions. This amendment adds a requirement to either modify the existing on-board replaceable modules of the flight management guidance computers (FMGC) to incorporate software changes, or replace the FMGC's with new, improved FMGC's; which would terminate the requirements for the AFM revision. 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 erroneous navigational calculations, which could result in an increased risk of collision with terrain or other airplanes.
AD 2000-12-14 · published Jun 19, 2000, effective Jul 24, 2000
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 inspection to detect chafing of the wires and harnesses in the cabin compartment ceiling; repair, if necessary; and installation of protective sleeving. 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 false warnings of a hot engine exhaust tailpipe and intermittent signal failure, which could result in the consequent execution of unnecessary procedures by the flightcrew.
AD 2000-12-16 · published Jun 19, 2000, effective Jul 5, 2000
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 fatigue cracking or loose or missing fasteners of the aft torque bulkheads of the outboard nacelle struts; and repair, if necessary. This amendment expands the applicability of the existing AD to include certain additional airplanes, and removes certain other airplanes from the applicability of the existing AD. For all airplanes subject to this AD, this amendment also requires accomplishment of a new terminating action. This action is necessary to prevent fatigue cracking and loose or missing fasteners in the aft torque bulkheads of the outboard nacelle struts, which could result in failure of an outboard nacelle strut diagonal brace load path and possible separation of the nacelle from the wing. This action is intended to address the identified unsafe condition.
AD 2000-12-17 · published Jun 19, 2000, effective Jul 24, 2000
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections to detect fatigue cracking of the pitch load fittings of the wing front spar, and rework, if necessary. This amendment also provides for optional terminating action for the repetitive inspections required by this AD. This amendment is prompted by a structural fatigue analysis that shows that the operational loads of the nacelle are higher than the loads used during initial design of the Model 767. The actions specified by this AD are intended to detect and correct fatigue cracking in the pitch load fittings of the wing front spar, which could result in reduced structural integrity of the strut.
AD 2000-12-12 · published Jun 23, 2000, effective Jul 28, 2000
Airbus Industrie Model A300, A300-600, and A310 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, and A310 series airplanes, that currently requires inspections to detect cracks in the lower spar axis of the nacelle pylon between ribs 9 and 10, and repair, if necessary. The existing AD also provides for optional modification of the pylon, which terminates the inspections for Model A300 and A310 series airplanes and increases the threshold and repetitive interval of the inspections for Model A300-600 series airplanes. This amendment reduces the inspection threshold and requires repetitive inspections following accomplishment of the optional modification for Model A310 series airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
AD 2000-12-19 · published Jun 23, 2000, effective Jul 28, 2000
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections of the aft pressure bulkhead to detect cracking, and repair, if necessary. This amendment is prompted by a report of fatigue cracking found in the upper half of the aft pressure bulkhead. The actions specified by this AD are intended to detect and correct cracking in the aft pressure bulkhead, which could result in rapid decompression of the fuselage or overpressurization of the tail section.
AD 2000-12-20 · published Jun 23, 2000, effective Jul 28, 2000
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires modification of the position 1 flap screw jack. 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 fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane.
AD 2000-13-02 · published Jun 27, 2000, effective Jul 3, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires revising the Airplane Flight Manual, and eventual disconnection of the precooler differential pressure switches. This action is necessary to prevent incorrect operation of the precooler differential pressure switches, which could result in inappropriate automatic shutoff of the engine bleed valve, and consequent inability to restart a failed engine using cross-bleed from the other engine or possible failure of the anti-ice system. This action is also necessary to ensure that the flight crew is advised of the procedures necessary to restart an engine in flight using the auxiliary power unit.
AD 2000-13-03 · published Jun 27, 2000
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger to a cargo-carrying ("freighter") configuration, that requires a revision to the Airplane Flight Manual Supplement to ensure that the main deck cargo door is closed, latched, and locked; inspection of the door wire bundle to detect discrepancies and repair or replacement of discrepant parts. This amendment also requires, among other actions, modification of the hydraulic and indication systems of the main deck cargo door, and installation of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. This amendment is prompted by the FAA's determination that certain main deck cargo door systems do not provide an adequate level of safety, and that there is no means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage.
AD 2000-13-04 · published Jun 28, 2000, effective Jul 13, 2000
Boeing Model 777-200 and -300 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 777-200 and -300 series airplanes, that currently requires revising the Limitations Section of the Airplane Flight Manual (AFM) to prohibit the dispatch of certain airplanes under certain conditions. That amendment also requires repetitive inspections to ensure correct operation of the backup generators; and, for certain airplanes, a one-time inspection to detect damage of the engine external gearbox; and corrective actions, if necessary. This amendment continues the AFM and inspection requirements and expands certain corrective action requirements. This amendment is prompted by reports of inflight shutdowns due to sheared backup generator shafts. The actions specified in this AD are intended to prohibit the dispatch of an airplane with an engine-mounted backup generator having a sheared shaft; and to detect and correct damage to the engine, which could result in inflight shutdowns.
AD 2000-11-18 · published Jun 6, 2000
Eurocopter France Model SA-365C, C1, C2, N, and N1; AS-365N2 and N3; and SA-366G1 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model SA-365C, C1, C2, N, and N1; AS-365N2, and SA-366G1 helicopters. That AD currently requires inspecting the tightening torque of the main rotor hub blade attach beam spherical thrust bearing bolts (bolts) and either applying a specified torque or, if necessary, inspecting for a crack in the metal components. That AD also requires replacing the spherical thrust bearing (bearing) with an airworthy bearing if a crack is found. This amendment requires the same actions as the existing AD, but adds the Eurocopter France Model AS-365N3 helicopter to the applicability. This amendment is prompted by reports of cracks in the metal components of the bearing attachment joint and the need to add the Eurocopter France Model AS-365N3 helicopter to the applicability. The actions specified by this AD are intended to prevent loosening of bearing bolts in flight, which may cause cracks in the metal components, failure of the bearing, and subsequent loss of control of the helicopter.
AD 2000-11-17 · published Jun 7, 2000, effective Jul 12, 2000
Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 helicopters and that currently requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for cracks or delaminations. This amendment requires the same actions required by the existing AD and corrects an incorrectly stated part number (P/N) in the existing AD. This amendment is prompted by a report of delamination of a Kevlar tie-bar. The actions specified by this AD are intended to detect cracks that could lead to delamination of the Kevlar tie-bar, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 2000-12-03 · published Jun 14, 2000, effective Jul 19, 2000
Eurocopter France Model AS332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model AS332L2 helicopters. This AD requires inspecting for interference between the transmission flexible mounting plate (plate) and the forward and aft shims (shims), replacing shims and repairing the plate if interference is found, and inspecting the plate for a broken plate slat (slat) and repairing the plate if a broken slat is found or replacing the plate if slat damage beyond repair limits is found. This AD is prompted by the discovery that several helicopters were manufactured with shims that did not have cutouts to permit relative motion between the plate slats and the shims without interference. The actions specified by this AD are intended to prevent cracking of the plate slats, increased helicopter vibration, loss of transmission mounting integrity, and subsequent loss of control of the helicopter.
AD 2000-12-09 · published Jun 23, 2000, effective Jul 28, 2000
Sikorsky Aircraft Corporation (Sikorsky) Model S-76A Helicopters
This amendment adopts a new airworthiness directive (AD) for Sikorsky Model S-76A helicopters. This AD requires inspecting the air conditioning system at specified intervals until installing a soft- start assembly retrofit kit to prevent a continuous flow of current through the soft-start resistor. This amendment is prompted by a report of overheating of the soft-start assembly. The actions specified by this AD are intended to prevent overheating of the air conditioning soft-start assembly, damage in the lower tailcone, an electrical fire, and subsequent loss of control of the helicopter.
AD 2000-11-15 · published Jun 5, 2000, effective Jul 10, 2000
Honeywell International Inc. (Formerly AlliedSignal Inc.) ALF502R and LF507 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to Chapter 5, Airworthiness Limitations section, of the Honeywell International Inc. ALF502R and LF507 series Engine Manuals to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This action is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-11-10 · published Jun 6, 2000, effective Aug 7, 2000
Rolls-Royce plc RB211 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD) applicable to certain Rolls-Royce plc (R-R) RB211 series turbofan engines. That AD currently requires the removal from service of intermediate pressure (IP) compressor stage 6-7 rotor shafts that exceed reduced cyclic life limits. This amendment requires further reduction of cyclic life limits and introduction of new reduced cyclic bands for rework. This action is prompted by additional stress analysis conducted following failure of an IP compressor stage 6 disk. The actions specified by this AD are intended to prevent an uncontained engine failure due to rupture of an IP compressor stage 6-7 rotor shaft.
AD 2000-11-51 · published Jun 7, 2000
Teledyne Continental Motors Engines
AD 2000-11-22 · published Jun 8, 2000, effective Aug 7, 2000
Allison Engine Company AE 3007A and AE 3007C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines. This AD requires revisions to the Airworthiness Limitations Section of the Allison Engine Company AE 3007A and AE 3007C Engine Manuals to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. Air carriers with an approved continuous airworthiness maintenance program will be allowed to either maintain the records showing the current status of the inspections using the record keeping system specified in the air carrier's maintenance manual or establish an acceptable alternate method of record keeping. This amendment is prompted by an FAA study of in- service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that, if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-12-05 · published Jun 12, 2000, effective Aug 11, 2000
International Aero Engines AG V2500-A1/-A5/-D5 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to International Aero Engines AG (IAE) V2500-A1/-A5/- D5 series turbofan engines, that requires revisions to the Airworthiness Limitations Section (ALS) and Maintenance Scheduling Section (MSS) of the Instructions for Continued Airworthiness (ICA), located in the Time Limits Manual (Chapter 05-10-00) of the Engine Manuals, to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action would add additional critical life-limited parts for enhanced inspection. This action is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-11-12 · published Jun 13, 2000, effective Aug 14, 2000
General Electric Company CF6-45/50 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-45/50 series turbofan engines. This AD requires initial and repetitive inspections for cracks in the stage 14 high pressure compressor (HPC) disk lock slots, and removal from service of certain disks, at the first piece-part level or HPC rotor disassembly level exposure, after 6,000 cycles since new (CSN). This amendment is prompted by reports of stage 14 HPC disk lock slot cracks discovered during shop fluorescent penetrant inspections. The actions specified by this AD are intended to prevent stage 14 HPC disk failure, which could result in an uncontained engine failure and damage to the aircraft.
AD 2000-12-01 · published Jun 13, 2000, effective Dec 11, 2000
Airworthiness Directives; CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -5C, and -7B Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain CFM International (CFMI) CFM56 series turbofan engines, that requires revisions to the Airworthiness Limitations Section of applicable Engine Shop Manuals (ESMs). These revisions incorporate required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment requires the addition of CFM56 engine models to the applicability section of the AD, and the introduction of additional inspections. This amendment is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-12-02 · published Jun 15, 2000, effective Sep 13, 2000
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney PW4000 Series Turbofan Engines, that currently requires revisions to the Time Limits Section of the manufacturer's Engine Manuals (EM's) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by additional focused inspection procedures for other critical life-limited rotating engine parts that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-12-18 · published Jun 26, 2000, effective Jul 31, 2000
Rolls-Royce Ltd. Dart 511, 511-7E, 514-7, 528, 528-7E, 529-7E, 532-7, 532-7L, 532-7N, 532-7P, 532-7R, 535-7R, 551-7R, and 552-7R Turboprop Engines
This amendment adopts a new airworthiness directive (AD), applicable to Rolls-Royce Ltd. Dart 511, 511-7E, 514-7, 528, 528-7E, 529-7E, 532-7, 532-7L, 532-7N, 532-7P, 532-7R, 535-7R, 551-7R, and 552- 7R turboprop engines. This AD requires the installation of a feathering probe and a steel retaining ring in the reduction gear housing (RGH) and replacement of a transfer bobbin installed in the torquemeter. This amendment is prompted by two reports of the failure of a propeller to feather following the failure of the RGH annulus gear, which resulted in the propeller overspeeding and the release of a propeller blade, causing damage to the airplane. The actions specified by this AD are intended to prevent a propeller from overspeeding and the release of a propeller blade after a failure of the RGH annulus gear, which could result in damage to an adjacent engine or to the airplane.
AD 2000-12-08 · published Jun 27, 2000, effective Aug 28, 2000
General Electric Company Models CF6-80C2A1/A2/A3/A5/A5F/A8/D1F Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) Models CF6-80C2A1/A2/A3/ A5/A5F/A8/D1F turbofan engines. This AD requires initial and repetitive visual inspections of left hand and right hand aft engine mount link assemblies for separations, cracks and spherical bearing race migration. Cracked or separated parts must be replaced prior to further flight. If spherical bearing race migration is discovered, an additional borescope inspection for cracks is also required. If no cracks are discovered by the additional borescope inspection, assemblies have a 75-cycle grace period for remaining in service before replacement. Finally, installation of improved aft engine mount link assemblies constitutes terminating action to the inspections of this AD. This amendment is prompted by a report of a fractured left hand aft engine mount link discovered during a scheduled removal of an engine of similar design. The actions specified by the AD are intended to prevent aft engine mount link failure, which can result in adverse redistribution of the aft engine mount loads and possible aft engine mount system failure.
