48 Airworthiness Directives: 34 airplane, 9 rotorcraft, 4 engine, 1 propeller.
AD 2000-11-06 · published Aug 1, 2000, effective Jul 6, 2000
Boeing Model 767 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to all Boeing Model 767 series airplanes. That AD currently requires repetitive inspections to detect discrepancies of the wiring and surrounding Teflon sleeves of the fuel tank boost pumps and override/jettison pumps; replacement of the sleeves with new sleeves, for certain airplanes; and repair or replacement of the wiring and sleeves with new parts, as necessary. This document corrects the date for the relevant service information referenced in that AD. This correction is necessary to ensure that operators use the correct source of service information to accomplish the actions required by the existing AD, which are intended to ensure adequate protection from chafing for the fuel pump wire insulation.
AD 95-19-08 R1 · published Aug 1, 2000, effective Aug 16, 2000
Boeing Model 727-100 and -200 Series Airplanes Equipped With an Engine Nose Cowl for Engine Numbers 1 and 3, Installed in Accordance With Supplemental Type Certificate (STC) SA4363NM
This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 727-100 and -200 series airplanes, that currently requires replacing the attaching nutplates on certain engine nose cowls with washers and self-locking nuts. This amendment changes the responsible office for approval of an alternative method of compliance. This amendment is prompted by the transfer of the supplemental type certificate. The actions specified in this AD are intended to prevent the attach bolts from becoming loose, which could result in subsequent separation of the nose cowl from the engine.
AD 2000-15-04 · published Aug 2, 2000, effective Sep 6, 2000
Boeing Model 747-200 and -300 Series Airplanes Equipped with General Electric CF6-80C2 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-200 and -300 series airplanes, that currently requires various inspections and functional tests to detect discrepancies of the thrust reverser control and indication system, and correction of any discrepancy found. This amendment requires installation of a terminating modification, and repetitive functional tests of that installation, and repair, if necessary. This amendment is prompted by the results of a safety review of the thrust reverser systems on Model 747 series airplanes. The actions specified by this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
AD 2000-15-08 · published Aug 2, 2000, effective Sep 6, 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 for damage or cracking of the aft pressure bulkhead, and cracking of the bulkhead web-to-Y-ring lap joint area and the upper segment of the bulkhead web. That AD also requires certain follow-on actions, if necessary. This amendment requires that a currently required one-time inspection to detect cracking of the upper segment of the bulkhead web be accomplished repetitively, and adds additional repetitive inspections to detect cracking of the upper and lower segments of the aft bulkhead web. The actions specified by this AD are intended to detect and correct fatigue cracking of the bulkhead web, which could result in rapid depressurization of the airplane, and consequent reduced controllability of the airplane.
AD 2000-15-11 · published Aug 3, 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. This amendment 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 modification of the existing 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 and the existing means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked, do not provide an adequate level of safety. 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 2000-10-23 · published Aug 7, 2000, effective Jun 30, 2000
Boeing Model 747-100, -200, -300, 747SR, and 747SP Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain Boeing Model 747- 100, -200, -300, 747SR, and 747SP series airplanes. That AD currently requires repetitive inspections to detect cracking of the longeron splice fittings at stringer 11, on the left and right sides at body station 2598, and replacement of any cracked fitting with a new fitting. This document clarifies the applicable compliance time for certain airplanes. This correction is necessary to ensure that fatigue cracking on longeron splice fittings, which could result in reduced controllability of the horizontal stabilizer, is detected and corrected in a timely manner.
AD 2000-15-12 · published Aug 8, 2000, effective Aug 23, 2000
Boeing Model 737-100, -200, and -200C Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, and -200C series airplanes. This action requires inspections of a certain component, and corrective action, if necessary. This action is necessary to detect and correct stress corrosion cracking in the front spar of the center section of the horizontal stabilizer, which could result in structural failure of the horizontal stabilizer and loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-15-13 · published Aug 8, 2000, effective Aug 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a one-time inspection to verify correct wire terminations of certain circuit breakers in the cockpit overhead switch panel; and correction of incorrect wire termination. That AD also requires that operators submit a report of the inspection results to the FAA. That AD was prompted by incidents in which the wiring of circuit breakers on the overhead switch panel lighting were found to be terminated improperly during production of the airplane, which bypassed the circuit breaker protection. This amendment expands the applicability of the existing AD to include additional airplanes, and removes the reporting requirement. The actions specified in this AD are intended to prevent smoke and possible fire in the overhead switch panel lighting circuitry due to an overload condition, as a result of lack of circuit breaker protection.
AD 2000-15-14 · published Aug 8, 2000, effective Aug 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires repetitive inspections to verify operation of the remote control circuit breakers (RCCB) of the alternating current (AC) cabin bus switch, and replacement of any discrepant RCCB with a new RCCB. This action is necessary to prevent propagation of smoke and fumes in the cockpit and passenger cabin due to an inoperable RCCB of the AC cabin bus switch during smoke and fume isolation procedures. This action is intended to address the identified unsafe condition.
AD 2000-15-15 · published Aug 8, 2000, effective Aug 23, 2000
McDonnell Douglas Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 airplanes, that currently requires inspecting the general condition of the jackscrew assembly and the area around the jackscrew assembly to detect the presence of metal shavings and flakes. This amendment also requires inspecting for metallic particles in the lubrication for the jackscrew assembly of the horizontal stabilizer and surrounding area to detect any discrepancy; follow-on actions; and corrective actions, if necessary. This amendment is prompted by numerous reports from operators that indicate instances of metallic shavings in the vicinity of the jackscrew assembly and gimbal nut of the horizontal stabilizer. The actions specified in this AD are intended to prevent loss of pitch trim capability due to excessive wear of the jackscrew assembly of the horizontal stabilizer, which could result in reduced controllability of the airplane.
AD 2000-15-16 · published Aug 8, 2000, effective Sep 12, 2000
Boeing Model 737, 757, 767, and 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD); applicable to certain Boeing Model 737, 757, 767, and 777 series airplanes; that requires a one-time general visual inspection to determine the vendor and manufacturing date of all oxygen masks in the passenger cabin; and corrective action, if necessary. This amendment is prompted by a report that passengers were unable to activate supplemental oxygen generators during an in-flight decompression due to stress corrosion cracking of the crimped copper alloy ferrules used to secure loops on the lanyard ends. The actions specified by this AD are intended to prevent failure of the supplemental oxygen system to deliver oxygen to the passengers and flight attendants in the event of decompression, which could result in injury to passengers and flight attendants.
AD 2000-15-17 · published Aug 8, 2000, effective Sep 12, 2000
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87); Model MD-88 Airplanes; and Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87); Model MD-88 airplanes; and Model MD-90-30 series airplanes; that requires installation of a pipe support and clamps on the hydraulic lines in the aft fuselage; replacement of the hydraulic pipe assembly in the aft fuselage with a new pipe assembly; and installation of drain tube assemblies and diverter assemblies in the area of the auxiliary power unit (APU) inlet; as applicable. This amendment is prompted by reports of smoke and odor in the passenger cabin and cockpit due to hydraulic fluid leaking into the APU inlet, and subsequently, into the air conditioning system. The actions specified by this AD are intended to prevent such hydraulic fluid leakage due to fatigue vibration and cracking in the flared radius of a hydraulic pipe in the aft fuselage, which could result in smoke and odors in the passenger cabin or cockpit.
AD 2000-15-18 · published Aug 8, 2000, effective Sep 12, 2000
Boeing Model 737-100 and -200 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that currently requires inspections to detect cracking of the support fittings of the Krueger flap actuator; and, if necessary, replacement of existing fittings with new steel fittings and modification of the aft attachment of the actuator. That AD also provides for an optional terminating modification that constitutes terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. The actions specified by this AD are intended to prevent such cracking, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, and resultant loss of hydraulic fluids. These conditions, if not corrected, could result in possible failure of one or more hydraulic systems, and consequent reduced controllability of the airplane.
AD 2000-15-51 · published Aug 8, 2000, effective Aug 14, 2000
Cessna Model 560XL Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-15-51 that was sent previously to all known U.S. owners and operators of Cessna Model 560XL airplanes by individual notices. This AD requires, for certain airplanes, repetitive inspections to measure the amount the aileron fairlead tube protrudes beyond the clamp at the aft aileron sector, and modification of the aileron fairlead tubes, which terminates the repetitive inspections to measure the tube protrusion; and, for all airplanes, repetitive general visual inspections, and corrective actions, if necessary, to ensure that the fairlead tube remains flush with the clamp. This action is prompted by reports of two occurrences of improper aileron function discovered during preflight checks. The actions specified by this AD are intended to prevent interference between the aileron cable fairlead tube and the aileron cable sector, which could result in loss of control of the airplane.
AD 2000-13-03 R1 · published Aug 15, 2000
McDonnell Douglas Model DC-8 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger to a cargo-carrying ("freighter") configuration. That AD currently 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. That AD 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 document corrects an error that resulted in the omission of a note, which informs operators of an alternative approved means of compliance for certain requirements. This correction is necessary to ensure operators are informed of this approved means of compliance.
AD 2000-16-01 · published Aug 15, 2000, effective Sep 19, 2000
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires replacement of certain ground block screws with new screws; and retermination of the circuit ground wires of the electrical power control unit (EPCU) to separate grounding points. This amendment is prompted by reports of complete loss of the primary electrical power on an airplane during flight. The actions specified by this AD are intended to prevent a loose electrical ground block of the circuit ground wires of the EPCU, which could result in complete loss of the primary electrical power of an airplane during flight.
AD 2000-16-07 · published Aug 16, 2000, effective Sep 20, 2000
Airbus Industrie Model A300 B2 and B4 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300 B2 and B4 series airplanes, that currently requires inspection of the fuselage longitudinal lap joints and circumferential joints, and of the stringers and doublers for bonding delamination and cracks; and repairs, as necessary. This amendment requires expansions of certain inspection areas; revisions of certain inspection thresholds or intervals; changes in references to inspection methods; and the addition of a modification to certain longitudinal lap joints. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent delamination and cracking of the fuselage, which could result in rapid decompression of the airplane.
AD 2000-16-08 · published Aug 16, 2000, effective Sep 20, 2000
Lockheed Model L-1011-385 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that currently requires repetitive inspections to detect cracking of the canted pressure bulkhead at fuselage station (FS) 1212, and repetitive inspections to detect cracking of the web at the fastener rows of the vertical stiffener-to-web; and repair or replacement of the web with a new web, if necessary. This amendment requires that the initial inspections be accomplished at a reduced threshold. This amendment is prompted by a report of fatigue cracking of the canted pressure bulkhead at FS 1212. The actions specified by this AD are intended to detect and correct fatigue cracking of the canted pressure bulkhead at FS 1212, which could result in blowout of a panel between adjacent stiffeners and consequent cabin depressurization.
AD 2000-16-09 · published Aug 16, 2000, effective Sep 20, 2000
Saab Model SAAB 340B and SAAB 2000 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB 340B and SAAB 2000 series airplanes, that currently requires various inspections of fluorescent lamps and lampholders in the cabin area for discrepancies; corrections, if necessary; and reinspection of the lamps to ensure correct installation after replacement or reinstallation of the lamps. This amendment requires replacement of the electronic light ballasts with improved ballasts, which terminates the reinspections, and expands 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 electrical arcing between the fluorescent tube pins and the lampholders, which could burn the surrounding area and lead to smoke and fumes in the passenger compartment or lavatory area.
AD 2000-16-03 · published Aug 17, 2000, effective Sep 21, 2000
Bombardier Model DHC-7-100, and DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-7-100, and DHC-8-100, -200, and -300 series airplanes, that requires a one-time inspection of maintenance records to determine the method used during the most recent weight and balance check of the airplane and, if necessary, accomplishment of a weight and balance check. 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 unusual handling characteristics and consequent reduced controllability during ground operations due to incorrect methods of weighing and balancing the airplane.
AD 2000-16-10 · published Aug 21, 2000, effective Sep 25, 2000
McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A Military), and -40 Series Airplanes; and Model MD-10-10F and MD-10-30F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes, and Model MD-10-10F and MD-10-30F series airplanes that requires performing repetitive ultrasonic inspections of the attaching bolts on the inboard and outboard support on the inboard and outboard flap assembly to detect failed bolts, or verifying the torque of the attaching bolts on the inboard support on the outboard flap; and follow-on actions. This AD also requires replacing all bolts with bolts made from Inconel, which constitutes terminating action for the repetitive inspection requirements. This amendment is prompted by an in-flight loss of the inboard flap assembly on an airplane during approach for landing. The actions specified by this AD are intended to prevent in-flight loss of inboard and outboard flap assemblies due to failure of H-11 attaching bolts, which could result in reduced controllability of the airplane.
AD 2000-16-11 · published Aug 21, 2000, effective Sep 25, 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 for backlash of the spherical bearing of the active aileron servo-controls, and follow-on corrective actions, if necessary. This amendment also provides optional terminating action for the repetitive inspections. This action is necessary to detect and correct excess backlash of the spherical bearing of the active aileron servo-controls, which could result in failure of the active aileron servo-controls and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-16-13 · published Aug 21, 2000, effective Sep 29, 2000
British Aerospace HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires you to inspect the nose wheel steering system to assure that the free play between the steering handle or knob and the nose wheels is within acceptable limits, and requires you to adjust the free play as necessary. 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 inability to steer the airplane because of excessive free play in the steering linkage. This excessive free play could then result in loss of control of the airplane during take-off, landing, or taxi operations.
AD 2000-16-14 · published Aug 21, 2000, effective Sep 25, 2000
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This AD requires either an inspection to detect damage or chafing of the insulation or wires, modification of the cable assembly, and repairs, if necessary; or replacement of the cable assembly of the lower anti-collision light with a new cable assembly. This amendment is prompted by reports of electrical arcing on structure near the lower body anti-collision light due to chafing of the cable. The actions specified by this AD are intended to prevent such chafing as a result of improper installation of the lower body anti-collision light assembly, which could result in electrical arcing or sparking in a flammable leakage zone of the airplane.
AD 2000-16-15 · published Aug 21, 2000, effective Sep 5, 2000
Saab Model SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B series airplanes. This action requires adjustment of the cargo baggage net, replacement of baggage net placards with new placards, and installation of certain new baggage net placards. This action is necessary to prevent failure of the cargo bulkhead floor attachments, which could result in damage to the airplane structure and possible injury to passengers and crewmembers. This action is intended to address the identified unsafe condition.
AD 2000-16-16 · published Aug 21, 2000, effective Sep 25, 2000
Boeing Model 777-200 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that currently requires a one-time inspection to determine the serial numbers of various switch modules on the overhead panel and control stand, and replacement of certain switch modules with new, improved modules. That AD also requires repetitive tests of the cargo fire extinguishing system, and one-time tests of the fuel crossfeed valve, pack, trim air, and alternate flap control switches; and repair or replacement of switch modules with new improved modules, if necessary. This amendment revises the applicability of the existing AD. This action also requires replacement of the existing switch modules with new switch modules; replacement of the existing module assemblies with new module assemblies; or reworked module assemblies; as applicable. This amendment is prompted by the FAA's determination that certain switches are susceptible to contamination. The actions specified by this AD are intended to minimize contamination of the switch contacts and consequent failure of the switches, which, if not corrected, could result in inability of the flight crew to activate the cargo fire extinguishing, fuel, air conditioning, and alternate flap systems.
AD 2000-16-51 · published Aug 21, 2000, effective Aug 21, 2000
Wytwornia Sprzetu Model PZL-104 Wilga 80 Airplanes
This document publishes in the Federal Register an amendment adopting emergency Airworthiness Directive (AD) 2000-16-51. The Federal Aviation Administration (FAA) previously sent emergency AD 2000-16-51 to all known U.S. owners and operators of Wytwornia Sprzetu Komunikacyjnego (PZL "Warszawa-Okecie") Model PZL-104 Wilga 80 airplanes. This AD requires you to repetitively replace the front tailplane to fuselage joint connector and bushing. This AD is the result of an incident report where the pin that fastens the tailplane to the fuselage fractured and separated on an airplane of similar design to that of the affected airplanes. The actions specified by this AD are intended to prevent failure of the front tailplane to fuselage joint connector, which could result in loss of control of the airplane if the tailplane and fuselage become disconnected during flight.
AD 2000-17-01 · published Aug 22, 2000, effective Oct 6, 2000
Fairchild Aircraft, Inc. Models SA226-T, SA226-AT, SA226-T(B), SA226-TC, SA227-AT, SA-227-TT, and SA-227-AC Airplanes
This amendment supersedes Airworthiness Directive (AD) 92-01- 02, which currently requires you to accomplish the following on certain Fairchild Aircraft SA226 and SA227 series airplanes: modify the parking brake system; and inspect (repetitively) certain landing gear brake assemblies. That AD resulted from wheel brake system malfunctions on several of the affected airplanes where regular brake system maintenance had been performed. This AD retains the modification and inspection requirements of AD 92-01-02 and incorporates inspection and replacement requirements for additional landing gear brake assemblies. The actions specified by this AD are intended to prevent wheel brake system malfunctions that could result in a fire in the brake area.
AD 2000-17-04 · published Aug 25, 2000, effective Sep 11, 2000
Boeing Model 737-100, -200, and -200C Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, and -200C series airplanes. This action requires repetitive inspections to detect discrepancies in the upper and lower skins of the fuselage lap joint, and repair, if necessary. This action is necessary to detect and correct such discrepancies, which could result in sudden fracture and failure of a lap joint and rapid decompression of the airplane fuselage.
AD 2000-17-05 · published Aug 25, 2000, effective Sep 11, 2000
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires a functional check of the shear rivets in all six elevator power control actuator (PCA) bellcrank assemblies to determine the condition of the shear rivets, and replacement or rework of the bellcrank assemblies, if necessary. This action is necessary to detect and correct any failed or partially yielded shear rivets of the elevator PCA bellcrank assemblies. Failure of two bellcrank assemblies on one side can result in that single elevator surface moving to a hardover position independent of pilot command resulting in a significant pitch upset recoverable by the crew. Failure of three bellcrank assemblies on one side may result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-17-51 · published Aug 25, 2000, effective Aug 30, 2000
Boeing Model 737-200 and -300 Series Airplanes Equipped with a Main Deck Cargo Door Installed in Accordance with Supplemental Type Certificate (STC) SA2969SO
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-17-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 737-200 and -300 series airplanes by individual notices. This AD supersedes an existing AD to require a one-time inspection to detect cracks of the lower frames and reinforcing angles of the main deck cargo door where the door latch fittings attach between certain fuselage stations and water lines, and replacement of any cracked part with a new part having the same part number. This action is prompted by reports that, during the inspections required by the existing AD, cracks were found in the reinforcing angles of the main deck cargo door frame. The actions specified by this AD are intended to detect and correct cracking of the lower portion of the main deck cargo door frames, which could result in sudden depressurization, loss or opening of the main deck cargo door during flight, and loss of control of the airplane.
AD 2000-17-02 · published Aug 29, 2000, effective Oct 3, 2000
British Aerospace Model BAe 146 and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and certain Model Avro 146-RJ series airplanes, that requires inspections and torque checks of the stringer crown fittings and bolts at Ribs 0 and 2 of the wings for discrepancies, corrective action, if necessary; and eventual modification of the stringer crown fittings, which terminates the inspections and checks. This amendment is necessary to prevent increased loads on the upper wing skin due to looseness of the stringer fittings and bolts at Ribs 0 and 2 of the wings, which could result in reduced structural integrity of the wings. This action is intended to address the identified unsafe condition.
AD 2000-17-03 · published Aug 29, 2000, effective Oct 3, 2000
Fokker Model F.28 Mark 0100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that currently requires a one-time visual inspection and a one-time eddy current and/or dye penetrant inspection of the nose landing gear (NLG) main fitting to detect cracking; and rework of the NLG main fitting, if necessary. This amendment requires new inspections (one-time detailed visual inspection and repetitive eddy current or dye penetrant inspections) to detect cracking of the NLG main fitting subassembly, and corrective actions, if necessary. This amendment also revises the applicability of the existing AD. 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 cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flightcrew and passengers.
AD 2000-17-06 · published Aug 31, 2000, effective Oct 5, 2000
Boeing Model 747 and 767 Series Airplanes Equipped With General Electric CF6-80C2 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 and 767 series airplanes, that requires repetitive functional tests of the directional pilot valve (DPV) of the thrust reversers to detect pneumatic leakage, and corrective action, if necessary. This amendment is prompted by a report of a latent failure mode of the fail-safe features of the thrust reverser system identified as possible leakage of the DPV that is due to a poppet being jammed slightly open or a leaking o-ring. The actions specified by this AD are intended to ensure the integrity of the fail- safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.
AD 2000-15-19 · published Aug 9, 2000, effective Aug 24, 2000
Eurocopter France Model SA-365N, N1, and AS-365N2, N3 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model SA-365N, N1, and AS-365N2, N3 helicopters. This action requires inspecting the sand filter ejection nozzle (nozzle) for cracks and replacing any cracked nozzle. This amendment is prompted by the discovery of a cracked nozzle during a preflight inspection. This condition, if not corrected, could result in loss of the nozzle in flight, impact with the main or tail rotor, and a subsequent forced landing.
AD 2000-15-21 · published Aug 9, 2000, effective Aug 24, 2000
AST, Inc, Rotorcraft Development Corporation, Southwest Florida Aviation International Helicopters
This amendment adopts a new airworthiness directive (AD) that applies to Bell Helicopter Textron Inc. (BHTI)-manufactured Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P; and Southwest Florida Aviation SW204, SW204HP, SW205, and SW205A-1 helicopters. This AD requires removing and replacing certain main rotor mast (mast) assemblies. This AD is prompted by a BHTI-manufactured Model UH-1B accident due to fatigue failure of a thin-wall mast installed on the helicopter. The actions specified by this AD are intended to prevent fatigue failure of the mast and subsequent loss of control of the helicopter.
AD 2000-15-20 · published Aug 15, 2000, effective Sep 19, 2000
Agusta S.p.A. Model A109A and A109A II Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A and A109A II helicopters. This AD requires radiographic inspections of the internal surface of each main rotor blade spar (spar) for corrosion. This AD is prompted by the discovery of corrosion on the internal surfaces of the spar in the area adjacent to the main rotor blade inertia balance weights. The actions specified by this AD are intended to prevent failure of a main rotor blade due to corrosion on the internal surface of the spar and subsequent loss of control of the helicopter.
AD 2000-16-04 · published Aug 15, 2000, effective Sep 19, 2000
Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for BHTC Model 430 helicopters. That AD currently requires inspecting all four main rotor adapter assemblies for evidence of flapping and lead-lag contact. That AD also requires installing a never-exceed-velocity (VNE) placard with markings on the airspeed indicator glass and instrument case and revising the rotorcraft flight manual (RFM) to reflect the airspeed revision. This amendment provides mandatory terminating action for requirements of that AD by replacing the fluidlastic damper blade sets with improved sets that incorporate a pressure indicator to detect loss of damper fluid. This amendment is prompted by the need for a positive means of detecting loss of damper fluid that could result in main rotor tip path plane separation. The actions specified by this AD are intended to prevent increased vibrations, damage to the main rotor system, and subsequent loss of control of the helicopter.
AD 2000-16-05 · published Aug 15, 2000, effective Sep 19, 2000
Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, 269C-1, 269D, and TH-55A Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Schweizer Aircraft Corporation (Schweizer) Model 269A, 269A-1, 269B, 269C, 269C-1, 269D helicopters. That AD requires inspecting the tail rotor swashplate shaft (shaft) nut for looseness and, if loose, inspecting the shaft for proper size; subsequently inspecting the shafts not previously inspected; and replacing any undersized shaft prior to further flight. This amendment reduces the applicability by specifying certain serial number tail rotor pitch control (pitch control) assemblies and shipping dates but adds the Schweizer Model TH-55A helicopter to the applicability. This amendment is prompted by the discovery of an undersized replacement shaft during routine maintenance. The actions specified by this AD are intended to prevent failure of the shaft, loss of the tail rotor, and subsequent loss of control of the helicopter.
AD 2000-11-52 · published Aug 16, 2000, effective Aug 31, 2000
Sikorsky Aircraft Corporation Model S-76 Series Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-11-52, which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Corporation (Sikorsky) Model S-76 series helicopters by individual letters. This AD requires determining the serial number (S/N) of each main rotor blade and removing certain serial numbered main rotor blades. This AD also requires visually inspecting and replacing, if necessary, other certain serial numbered main rotor blades. This AD is prompted by a report of a crack in a main rotor blade and three reports of root end pocket separation from main rotor blades during flight. The crack and the main rotor blade root end pocket separation were due to improper manufacture of certain main rotor blade skins. The actions specified by this AD are intended to prevent main rotor blade root end pocket separation, impact with main rotor or tail rotor blades, and subsequent loss of control of the helicopter.
AD 2000-16-06 · published Aug 16, 2000, effective Sep 20, 2000
Bell Helicopter Textron Canada Model 430 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters. This AD requires replacing arm clamp screws (screws) in the yaw, roll, pitch, and collective syncro resolvers, and installing a guard bracket on the yaw, roll, pitch, and collective syncro resolvers. This AD is prompted by an operator's report that a yaw control channel jammed during freedom-of-control checks following maintenance. The actions specified by this AD are intended to prevent a jammed flight control and subsequent loss of control of the helicopter.
AD 2000-17-07 · published Aug 28, 2000, effective Sep 12, 2000
Eurocopter France Model EC120B Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model EC120B helicopters. This action requires adjusting the clearance of the cabin sliding door if necessary. This amendment is prompted by an in-flight loss of a cabin sliding door, which had been locked in the fully opened position. The actions specified in this AD are intended to prevent in-flight loss of a cabin sliding door, impact with the horizontal stabilizer, main rotor, or fenestron tail rotor, and subsequent loss of control of the helicopter.
AD 2000-17-08 · published Aug 28, 2000
Eurocopter Deutschland GMBH Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB- 4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 helicopters. That AD requires creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap. That AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment establishes a life limit for certain main rotor TT straps. This amendment is prompted by a need to establish a life limit for certain TT straps because of an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part-numbered TT strap is used on the ECD Model BO-105 helicopters. The actions specified by this AD are intended to prevent fatigue failure of the TT strap, loss of a blade, and subsequent loss of control of the helicopter.
AD 2000-15-01 · published Aug 2, 2000, effective Oct 2, 2000
CFM International CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5A, -5B, -5C series turbofan engines, that requires initial and repetitive visual inspections of the fuel pump filter cover helicoil inserts and bolts for damage, and, if necessary, repair or replacement with serviceable parts. This amendment also requires the installation of new or reworked fuel pumps that incorporate an improved filter cover retention design (D-bolts), or an on-wing repair of existing fuel pumps, as terminating action to the inspections. This amendment is prompted by reports that fuel pump filter cover helicoil inserts have loosened or pulled out. The actions specified by this AD are intended to prevent fuel leakage from between the fuel pump filter cover and gear housing, which could result in an engine fire and damage to the airplane.
AD 2000-15-09 · published Aug 8, 2000, effective Oct 10, 2000
Honeywell International Inc. TFE731-2, -3, -4, and -5 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Honeywell International, Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Company) high pressure compressor (HPC) impellers installed on TFE731-2, -3, -4, and -5 series turbofan engines. This AD requires the removal and inspection of the HPC impeller and, if necessary, replacement of the HPC impeller with a serviceable impeller. This amendment is prompted by an incident of an uncontained impeller failure due to cracking in the seal relief area of the HPC impeller. The actions specified by this AD are intended to prevent HPC impeller failure due to fatigue cracking.
AD 2000-16-02 · published Aug 15, 2000, effective Oct 16, 2000
Pratt & Whitney PW4164, PW4168, and PW4168A Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney PW4164, PW4168, and PW4168A series turbofan engines. The current AD requires initial and repetitive torque checks for loose or broken bolts used to secure the engine to the airplane made from INCO 718 material (front pylon mount bolts). The current AD also requires the replacement of the bolts, if necessary, with new bolts, and establishes a new cyclic life limit for the front pylon mount bolt. This amendment adds requirements for initial and repetitive torque checks of front pylon mount bolts made from a new material, MP159, and initial and repetitive visual inspections of the primary mount thrust load path. This amendment is prompted by the use of front pylon mount bolts made from MP159 material and fatigue testing that shows that the forward engine mount bearing housings have insufficient fatigue life expectancy. The actions specified by this AD are intended to prevent front pylon mount bolt and primary mount thrust load path failure, which could result in an engine separating from the airplane.
AD 2000-16-12 · published Aug 21, 2000, effective Sep 5, 2000
General Electric Company CF6-45, -50, -80A, -80C2, and -80E1 Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-45, -50, -80A, - 80C2, and -80E1 turbofan engines with certain high pressure compressor rotor (HPCR) stage 3-9 spools installed. This action requires initial ultrasonic and eddy current inspections of certain HPCR stage 3-9 spools for cracks. This amendment is prompted by an uncontained failure of an HPCR 3-9 spool. The actions specified in this AD are intended to detect cracks which can cause separation of the HPCR stage 3-9 spool and result in an uncontained engine failure.
AD 2000-15-10 · published Aug 8, 2000, effective Aug 23, 2000
McCauley Propeller Model 4HFR34C653/L106FA-0
This amendment adopts a new airworthiness directive (AD) that is applicable to McCauley Propeller Systems 4HFR34C653/L106FA-0 model propellers that are installed on Jetstream Series 3200 airplanes. This action is also applicable to 4HFR34C653/L106FA-0 model propellers that are installed on Ayres S2R-G5 and S2R-G10 airplanes if the propeller was previously installed on Jetstream Series 3200 airplanes or if installation history of the propeller is unknown. This action requires one-time and repetitive eddy current inspections of the camber side of the blade surface. This amendment is prompted by a report of a crack on the camber side of the blade surface. The crack was found during a dye penetrant inspection as part of a normal overhaul process. The actions specified in this AD are intended to detect cracks that could cause failure of the propeller blade, which can result in loss of control of the airplane.
