50 Airworthiness Directives: 37 airplane, 8 rotorcraft, 3 engine, 2 glider.
AD 2000-22-18 · published Dec 4, 2000, effective Dec 29, 2000
Raytheon Aircraft Company Beech Model 58 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Model 58 airplanes. This AD requires you to inspect the rudder bellcrank interconnect tube for damage; replace or refinish the interconnect tube, if necessary; and modify the floorboard. Four reports of damage to the interconnect tube prompted this action. The actions specified by this AD are intended to correct the wrong use of screws and consequent wear in the pilot/copilot pedal interconnect tube, which could result in loss of rudder control.
AD 2000-23-34 · published Dec 4, 2000, effective Jan 8, 2001
Boeing Model 737-300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-300, -400, and -500 series airplanes, that requires replacement of the existing autothrottle computer with a new, improved autothrottle computer. This amendment is prompted by reports of asymmetric thrust conditions during flight caused by irregular autothrottle operation in which the thrust levers slowly move apart causing the airplane to bank excessively and go into a roll. The actions specified by this AD are intended to prevent such conditions, which could result in loss of control of the airplane.
AD 2000-24-01 · published Dec 4, 2000, effective Dec 19, 2000
Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600- 2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This action requires installation of protection shields in the wheel bay of the main landing gear (MLG). This action is necessary to prevent water, ice or slush accumulation on the aileron quadrants and/or control cable pulleys in the wheel bay of the MLG during ground roll. Such water, ice or slush accumulation could subsequently freeze during the climb to cruise altitude and cause stiffness in the aileron controls, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-24-02 · published Dec 4, 2000, effective Jan 8, 2001
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 repetitive inspections to detect wear of the inboard flap trunnions, and to detect wear or debonding of the protective half-shells; and corrective actions, if necessary. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing and resultant wear damage on the inboard flap drive trunnions or on the protective half-shells, which could result in failure of the trunnion primary load path; this would adversely affect the fatigue life of the secondary load path and could lead to loss of the flap.
AD 2000-24-03 · published Dec 4, 2000, effective Jan 8, 2001
Dornier Model 328-100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. This amendment requires revising the existing AFM revision to include a flap system test to be performed prior to the first flight of the day. This amendment also requires, for certain airplanes, modification of the flap actuators of the flight controls. The actions specified by this AD are intended to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
AD 2000-24-04 · published Dec 4, 2000, effective Jan 5, 2001
Raytheon Aircraft Company Beech Models A36, B36TC, and 58 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Beech Models A36, B36TC, and 58 airplanes. This AD requires you to inspect for misrouted rudder control cables; replace any worn or damaged guard pins; replace any pulley brackets that are damaged or worn; and replace any misrouted rudder control cables. Three reports of misrouted cables prompted this action. The actions specified by this AD are intended to correct the misrouted rudder control cable and consequent guard pin wear or fraying of the cables with loss of rudder control.
AD 2000-24-05 · published Dec 4, 2000, effective Jan 5, 2001
Vulcanair S.p.A. Models P 68 “OBSERVER”, P68 “OBSERVER 2”, and P68TC “OBSERVER” Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Vulcanair S.p.A. (Vulcanair) Models P 68 "OBSERVER", P68 "OBSERVER 2", and P68TC "OBSERVER" airplanes. This AD requires you to inspect the nose landing gear (NLG) upper strut for evidence of cracking (cracks or crack beginnings), and replace the NLG upper strut if you find evidence of cracking. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent failure of the NLG upper strut caused by cracking in the area of the seeger retaining ring groove, which could result in loss of control of the airplane.
AD 2000-24-06 · published Dec 4, 2000, effective Jan 8, 2001
Boeing Model 707, 727C, and 727-100C Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 707, 727C, and 727-100C series airplanes, that currently requires repetitive inspections to detect cracking of the main cargo door skin and frames, and repair, if necessary. The existing AD also provides optional terminating modifications. This amendment requires follow-on repetitive inspections of repaired or modified areas for certain airplanes. This amendment is prompted by reports of cracking and/or tearing of the main cargo door outer skin and subsequent failure of the door frame. The actions specified by this AD are intended to detect and correct such cracking and/or tearing, which could result in failure of the door frame and consequent rapid decompression of the airplane.
AD 2000-24-07 · published Dec 4, 2000, effective Jan 8, 2001
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of the frame web, doubler, and inner chord of the forward edge frame of main entry door number 1, and various follow-on actions. This amendment is prompted by reports of cracking in the frame web, doubler, inner chord, and strap of the forward edge frame of main entry door number 1. The actions specified by this AD are intended to prevent cracks in the frame web and doubler of the forward edge frame of main entry door number 1, which could result in inability of the edge frame to react door stop loads, and consequent rapid depressurization of the airplane.
AD 2000-24-08 · published Dec 4, 2000, effective Jan 8, 2001
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, and A321 series airplanes, that requires a revision to the Airplane Flight Manual; inspection to detect damage of the wiring and adjacent structure along the length of the fairing of the fuel boost pump; corrective actions, if necessary; and modification of the fuel pump wire and fairing. The actions specified by this AD are intended to prevent electrical arcing of the fuel boost pump wire, which could result in wing structural damage, fire, and/or fuel vapor explosion. This action is intended to address the identified unsafe condition.
AD 2000-24-09 · published Dec 4, 2000, effective Jan 8, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires modification of the insulation blankets in the area surrounding the main external power ground studs. This action is necessary to prevent smoke and fire in the forward cargo compartment due to burn damage to the insulation blankets in the area surrounding the main external power ground studs. This action is intended to address the identified unsafe condition.
AD 2000-24-10 · published Dec 4, 2000, effective Jan 8, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires relocating the B7-28 bus located in the upper main circuit breaker in the rear cockpit observer's station from the lower to the upper terminals of the circuit breakers in Row P. This action is necessary to prevent insufficient clearance and contact between the B7- 28 bus and an adjacent panel, which could result in arcing damage, smoke, and/or fire in the upper main circuit breaker panel. This action is intended to address the identified unsafe condition.
AD 2000-24-11 · published Dec 4, 2000, effective Jan 8, 2001
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 detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors, and repair, if necessary. For certain airplanes, that AD also requires installation or modification of a flapper door ramp deflector on the forward entry drop ceiling structure. For certain other airplanes, that AD requires inspection of the wire assembly support installation for evidence of chafing, and corrective actions, if necessary. For certain airplanes subject to the existing AD, as well as additional airplanes being added to the applicability of this AD, this action adds a requirement for modification of a support bracket for the ramp deflector assembly. This action is necessary to prevent chafing of electrical wire assemblies above the forward passenger doors, which could result in an electrical fire in the passenger compartment. This action is intended to address the identified unsafe condition.
AD 2000-24-12 · published Dec 4, 2000, effective Jan 8, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection to detect chafing or damage of the electrical wires leading to the terminal strips in the center accessory compartment (CAC) area; and corrective actions, if necessary. This amendment also requires revising the wire connection stack up of certain cable terminals at the electrical power center bays in the CAC, and replacing certain terminal strips with new strips and removing applicable nameplates at electrical power center bays. This action is necessary to prevent arcing and sparking damage to the power feeder cables, terminal strips, and adjacent structure, and consequent smoke and fire in the CAC. This action is intended to address the identified unsafe condition.
AD 2000-24-13 · published Dec 4, 2000, effective Jan 8, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires replacing the ground support bracket(s); and rerouting the ground cables of the galley external power and main external power, or ground cables of the main external power; as applicable. This action is necessary to prevent arcing and heat damage to the attachment points of the main external and galley power receptacle ground wire, insulation blankets outboard and aft of the receptacle area, and adjacent power cables, which could result in smoke and fire in the forward cargo compartment. This action is intended to address the identified unsafe condition.
AD 2000-24-14 · published Dec 4, 2000, effective Jan 8, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection of the electrical wires routed above the door actuation cables for minimum .50-inch clearance with the door in the open and closed position, damage due to chafing or electrical arcing, or damaged door actuation cables; and corrective actions, if necessary. This action is necessary to prevent damaged electrical wires or damaged door actuation cables due to chafing by the cables during operation of the forward passenger door, which could result in electrical arcing and consequent smoke in the area above the forward passenger door. This action is intended to address the identified unsafe condition.
AD 2000-24-15 · published Dec 4, 2000, effective Jan 8, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time detailed visual inspection to detect discrepancies of all electrical wiring installations in various areas of the airplane; and corrective actions, if necessary. This amendment is necessary to prevent electrical arcing and/or heat damaged wires due to improper wire installations during manufacture and/or maintenance of the airplane, and consequent fire and smoke in various areas of the airplane. This amendment is intended to address the identified unsafe condition.
AD 2000-24-16 · published Dec 4, 2000, effective Jan 8, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection of the one phase remote control circuit breaker (RCCB) in the main avionics compartment and center accessory compartment to determine its part number and serial number, and replacement of the RCCB with a certain RCCB, if necessary. This action is necessary to ensure that defective braze joints of certain latch assemblies of the RCCB are not installed on the airplane. Defective braze joints could fail and prevent the RCCB from tripping during an overload condition, which could result in a fire and smoke in certain wire bundles that are routed to and from the main avionics compartment or center accessory compartment. This action is intended to address the identified unsafe condition.
AD 2000-24-17 · published Dec 4, 2000, effective Jan 8, 2001
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 deactivation of the forward and center cargo control units (CCU). This amendment requires, among other actions, a general visual inspection to verify that all six external connectors of suspect CCU's have a certain part number stamped on the connector bodies on all CCU assemblies, and follow-on actions, which would constitute terminating action for the deactiviation requirements. The actions specified by this amendment are intended to prevent overheating of the electrical pins inside the CCU's and subsequent release of hot gases and flames, which could result in smoke and fire in the cargo compartment.
AD 2000-24-18 · published Dec 4, 2000, effective Jan 8, 2001
Airbus Model A300 B2 and B4 Series Airplanes, and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-600) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, and Model A300-600 series airplanes, that requires repetitive inspections to detect chafing and the existence of repairs of the harness of the high-level sensor of the fuel surge tanks, and to detect chafe marks on the support canisters of the magnetic level indicators; and follow-on corrective actions, if necessary. This amendment also requires modification of the harness for the high-level sensor of the outer wing fuel tanks, which terminates certain 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 chafing of the harness of the high-level sensor, which could result in a short circuit and consequent fuel ignition source inside the outer wing fuel tanks.
AD 2000-24-20 · published Dec 4, 2000, effective Jan 8, 2001
Boeing Model 707 and 720 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that requires repetitive inspections of certain stringers and around certain fastener holes of the lower skin of the wings to detect fatigue cracking, and repair, if necessary. This action is necessary to detect and correct such cracking and consequent damage to adjacent structure, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-24-25 · published Dec 11, 2000, effective Jan 16, 2001
Raytheon Model Hawker 800A (U-125A) and Hawker 800XP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800A (U-125A) and Hawker 800XP series airplanes, that requires inspecting the roller clearance in the nose landing gear drag stay and making any necessary adjustments. This amendment is prompted by reports indicating multiple findings of roller clearances that are in excess of specifications. The actions specified by this AD are intended to prevent the inability to extend the nose landing gear, which could result in damage to the airplane upon landing.
AD 2000-25-04 · published Dec 13, 2000, effective Jan 17, 2001
Raytheon (Beech) Model MU-300, MU-300-10, 400, 400A, and 400T Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model MU-300, MU-300-10, 400, 400A, and 400T series airplanes, that requires a one-time inspection to detect hydraulic fluid leakage from the B-nut area, which attaches a hydraulic tube to the anti-skid valve assembly, and corrective actions, if necessary; and installation of an additional support for the hydraulic tube. This amendment is intended to prevent an asymmetric braking condition and a longer stopping distance due to sudden loss of normal braking to the left wheel. Such loss of normal braking could result in the airplane overrunning the runway surface. This action is intended to address the identified unsafe condition.
AD 2000-25-05 · published Dec 13, 2000, effective Dec 28, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently requires a one-time inspection of the coupling hinge and locking fastener of the Gamah couplings of the fuel system tubing located in the wing dry bay to detect discrepancies, and follow-on corrective actions. This amendment retains those requirements and adds a requirement to revise the applicability of the existing AD to add certain airplanes. The actions specified in this AD are intended to prevent failure of the rivets of the Gamah couplings and consequent separation of a Gamah coupling, which could result in fuel leakage and consequent fire in or around the wing. This action is intended to address the unsafe condition.
AD 2000-25-01 · published Dec 18, 2000, effective Jan 19, 2001
The New Piper Aircraft, Inc. (formerly Piper Aircraft Corporation) PA-31 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 80-26- 05, which currently requires you to repetitively inspect the main landing gear (MLG) inboard door hinges and attachment angles for cracks on certain The New Piper Aircraft, Inc. (Piper) PA-31 series airplanes. AD 80-26-05 also requires you to replace any cracked MLG inboard door hinge or attachment angle with parts of improved design. This AD results from the Federal Aviation Administration's policy on aging commuter-class aircraft and the determination that an improved design MLG inboard door hinge and attachment assembly, when incorporated, will eliminate the need for the currently required repetitive short-interval inspections; however, we have received reports of cracks in the improved design MLG inboard door hinge assemblies on the affected airplanes. This AD retains the current repetitive inspections contained in AD 80-26-05, and requires inspections on the improved design parts. The actions specified by this AD are intended to detect and correct cracked MLG inboard door hinge assemblies. These cracked door hinge assemblies could result in the MLG becoming jammed, with consequent loss of control of the airplane during landing operations.
AD 2000-25-02 · published Dec 18, 2000, effective Jan 19, 2001
American Champion Aircraft Corporation 7, 8, and 11 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-05- 04, which currently requires you to repetitively inspect the front and rear wood spars for damage (including installing any as-needed inspection holes) and repair or replace any damaged wood spar on certain American Champion Aircraft Corporation (ACAC) Model 8GCBC airplanes. Damage is defined as cracks, compression cracks, longitudinal cracks through the bolt holes or nail holes, or loose or missing nails. This AD retains the actions of AD 98-05-04 for the ACAC Model 8GCBC airplanes; extends the actions to all ACAC 7, 8, and 11 series airplanes (except the inspections are not repetitive for certain 7 and 11 series airplanes); incorporates alternative methods of accomplishing the actions; and requires reporting any damage found. This AD is the result of a review of the service history of the affected airplanes that incorporate wood wing spars where damage was found in this area and consideration of all public comments received. The actions specified by this AD are intended to detect and repair or replace damaged wood wing spars. Continued operation with such damage could progress to in-flight structural failure of the wing with consequent loss of control of the airplane.
AD 2000-25-07 · published Dec 18, 2000, effective Jan 2, 2001
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 of the aft end of each inboard flap track of the wing outboard flap, and corrective actions, if necessary. This action is necessary to detect and correct damage of the aft end of each flap track, which could result in loss of the outboard trailing edge flap and consequent loss of controllability of the airplane.
AD 2000-03-19 REM · published Dec 19, 2000, effective Jan 2, 2001
Piaggio Aero Industries S.p.A. Airplanes
This amendment removes Airworthiness Directive (AD) 2000-03-19, which currently applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes that are equipped with pneumatic deicing boots. AD 2000-03-19 requires revising the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. Since FAA issued AD 2000-03-19, I.A.M. has shown the language currently included in the AFM and the airplane configuration are satisfactory to address the conditions identified in AD 2000-03-19. Therefore, this action removes AD 2000-03-19.
AD 2000-23-16 · published Dec 21, 2000, effective Dec 6, 2000
Boeing Model 747 Series Airplanes Powered by Pratt & Whitney JT9D-3 and -7 Series Engines
This document corrects a minor error that appeared in airworthiness directive (AD) 2000-23-16, that was published in the Federal Register on November 21, 2000 (65 FR 69862). The error resulted in a reference to a part number that does not exist. That AD is applicable to certain Boeing Model 747 series airplanes, and requires repetitive inspections and torque checks of the hanger fittings and strut forward bulkhead of the forward engine mount and adjacent support structure, and corrective actions, if necessary. That AD also provides for optional terminating action for the repetitive inspections and checks.
AD 2000-25-10 · published Dec 21, 2000, effective Jan 25, 2001
Airbus Model A300 B2 and B4 Series Airplanes, and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-600) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 and B4 series airplanes, and Model A300-600 series airplanes, that requires verifying the correct location of the labels of the hydraulic pipes supplying the strut unlocking actuator of the left-hand main landing gear (MLG), and of the pipes of the left- and right-hand cross brace; reidentifying the pipes; and replacing any incorrectly located label with a new label. The actions specified by this AD are intended to prevent cross connection of the hydraulic hoses or pipes that supply the main strut unlocking actuator, and collapse of the MLG under lateral taxiing loads. This action is intended to address the identified unsafe condition.
AD 2000-25-11 · published Dec 26, 2000, effective Jan 30, 2001
Boeing Model 747-400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires repetitive inspections to detect fatigue cracking of the longeron splice fittings at stringer 11 on the left and right sides at body station 2598, and various follow-on actions. The actions specified by this AD are necessary to detect and correct fatigue cracking of the longeron splice fittings and subsequent damage to adjacent structure. Such damage could result in the inability of the structure to carry horizontal stabilizer flight loads, and consequent reduced controllability of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
AD 2000-25-12 · published Dec 26, 2000, effective Jan 30, 2001
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of the front spar web of the wing, and corrective action, if necessary. The actions specified by this AD are necessary to detect and correct fatigue cracking of the front spar web, which could result in fuel leaking onto an engine and a consequent fire. This action is intended to address the identified unsafe condition.
AD 2000-15-17 R1 · published Dec 27, 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-987 (MD-87); Model MD-88 Airplanes; and Model MD-90-30 Series Airplanes
This document corrects a typographical error that appeared in airworthiness directive (AD) 2000-15-17 that was published in the Federal Register on August 8, 2000 (65 FR 48368). The typographical error resulted in the omission of an airplane model from paragraph (c) of the AD. This AD is 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. This AD 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 inlet; as applicable.
AD 2000-25-53 · published Dec 28, 2000, effective Jan 2, 2001
Airbus Model A330 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-25-53, which was sent previously to all known U.S. owners and operators of Airbus Model A330 series airplanes by individual notices. This AD requires either repetitive detailed visual inspections or repetitive borescopic inspections to detect cracking or other damage of the barrel nuts of the engine aft mount; and replacement of any cracked nut and its associated bolt with a new nut and bolt, or replacement of all 4 nuts and their associated bolts if two or more nuts on the same engine mount are found cracked. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the aft engine mount nut, which could result in reduced structural integrity of the engine-to-pylon aft mount assembly, or, in the case of multiple cracked nuts, possible loss of an engine.
AD 2000-26-03 · published Dec 28, 2000, effective Feb 1, 2001
Airbus Model A300 B2 and B4 Series Airplanes, and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-600) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 and A300-600 series airplanes, that currently requires wiring modifications to the engine and auxiliary power unit (APU) fire detection system. This amendment requires new wiring modifications for the engine and APU fire detection system. 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 fire warning from terminating prematurely, which could result in an unnoticed, uncontained engine/APU fire.
AD 2000-26-04 · published Dec 29, 2000, effective Feb 2, 2001
Boeing Model 747, 757, 767 and 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747, 757, 767 and 777 series airplanes, that requires modification of certain drip shields located on the flight deck, and follow-on actions. This action is necessary to prevent potential ignition of the moisture barrier cover of the drip shield, which could propagate a small fire that results from an otherwise harmless electrical arc, leading to a larger fire. This action is intended to address the identified unsafe condition.
AD 2000-26-05 · published Dec 29, 2000, effective Feb 2, 2001
Boeing Model 737, 747, 757, and 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737, 747, 757, and 767 series airplanes, that requires rework of certain duct assemblies of the environmental control system (ECS) or replacement of the duct assemblies with new or reworked duct assemblies. This action is necessary to prevent potential ignition of fiberglass insulation material installed on the outside of the ECS ducts, which could propagate a small fire and lead to a larger fire. This action is intended to address the identified unsafe condition.
AD 2000-24-21 · published Dec 6, 2000, effective Jan 10, 2001
Siam Hiller Holdings, Inc. Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, UH-12E-L, UH-12L, and UH-12L4 Helicopters
This amendment adopts a new airworthiness directive (AD), for Siam Hiller Holdings, Inc. (Hiller), formerly Rogerson Hiller Corporation, Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, UH- 12E-L, UH-12L, and UH-12L4 helicopters, that requires replacing all undrilled-shank bolts at pivoting joints in the control system linkage with drilled-shank bolts and installing castellated nuts and cotter pins. This amendment is prompted by an accident caused by separation of the control system linkage of a Model UH-12E helicopter. The actions specified by this AD are intended to prevent separation of the control system attachments at pivoting points and subsequent loss of control of the helicopter.
AD 2000-22-51 · published Dec 11, 2000, effective Dec 26, 2000
Arrow Falcon Exporters, Inc., Rotorcraft Development Corporation, San Joaquin Helicopters, International Helicopters, Inc., Robinson Air Crane, Inc., Smith Helicopters, Southern Helicopter, Inc., Southwest Florida Aviation International, Tamarack Helicopters, Inc., US Helicopter, Inc., Richards Heavylift Helo, Inc., Hagglund Helicopters, LLC, Overseas Aircraft Support Inc
This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-22-51, which was sent previously by individual letters to all known U.S. owners and operators of 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 manufactured by Bell Helicopter Textron Inc. (BHTI) for the Armed Forces of the United States. This AD requires establishing a retirement life for certain main rotor masts, creating a component history card or equivalent record, and identifying certain masts as unairworthy. This AD also requires removing the hub spring, if installed, and determining whether a main rotor mast (mast) has ever been installed on a helicopter while operated with a hub spring. Conducting certain inspections based on the retirement index number (RIN) and on whether the helicopter was ever operated with a hub spring is also required.Replacing any mast that has inadequate radius or a burr in the damper clamp splined area is also required. Finally, this AD requires sending information concerning the mast to the FAA. This amendment is prompted by the discovery of a crack in a mast with a lower RIN value than the established life limit. This action is necessary to preclude the occurrence of a fatigue crack in the damper clamp splined area of a mast. This condition, if not corrected, could result in failure of a mast or main rotor trunnion (trunnion), separation of the main rotor system, and subsequent loss of control of the helicopter.
AD 2000-15-52 · published Dec 13, 2000, effective Dec 28, 2000
Bell Helicopter Textron, Inc. Model 204B, 205A, 205A-1, 205B, and 212 Helicopters
This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-15-52, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. Model (BHTI) Model 204B, 205A, 205A-1, 205B, and 212 helicopters by individual letters. This AD reduces the retirement index number (RIN) life limit for the main rotor mast (mast); increases the RIN factor for masts and main rotor trunnions (trunnions); applies standard RIN factors for all external load lifts; and requires a one-time inspection of the snap ring groove area of the mast. This AD also establishes RIN factors for masts and trunnions that have been previously installed on military or restricted category helicopters and removes from service those masts that have been previously installed with a hub spring. This amendment is prompted by an occurrence of a cracked mast at a lower value than the established RIN life limit. The actions specified by this AD are intended to preclude the occurrence of fatigue cracks in the damper clamp splined area of a mast. A crack in the damper clamp splined area could result in failure of a mast or trunnion, separation of the main rotor system, and subsequent loss of control of the helicopter.
AD 2000-25-03 · published Dec 13, 2000, effective Dec 28, 2000
Bell Helicopter Textron Inc. Model 205A-1, 205B, 212, 412, and 412CF Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and 412CF helicopters. This action requires inspecting the locking washer on each main rotor actuator (actuator) for twisting or damage to the tab and replacing any locking washer that has a twisted or damaged tab. Replacing certain locking washers, regardless of condition, is also required within a specified time period. Installing a certain airworthy locking device on each actuator constitutes terminating action for the requirements of this AD. This amendment is prompted by an incident in which a damaged locking washer allowed the rod end to detach from the collective actuator, causing loss of collective control of the main rotor. The current locking washer is subject to mechanical damage and failure, which allows the actuator piston to unthread itself from its rod end. This condition, if not corrected, could cause loss of control of the main rotor and subsequent loss of control of the helicopter.
AD 2000-26-01 · published Dec 22, 2000, effective Jan 26, 2001
Eurocopter Deutschland GMBH Model BO-105CB-5 and BO-105CBS-5 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model BO-105CB-5 and BO-105CBS-5 helicopters. That AD currently requires, before further flight, creating a component log card or equivalent record and determining the calendar age and number of flights on each tension- torsion (TT) strap. This amendment requires before further flight, establishing 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 a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
AD 2000-26-02 · published Dec 22, 2000
Eurocopter Deutschland Model EC135 P1 and T1 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland Model EC135 P1 and T1 helicopters. That AD currently requires visual and dye-penetrant inspections for a cracked stator blade of the fenestron tail rotor (tail rotor). That AD also requires either stop drilling a cracked blade or, as necessary, replacing an unairworthy stator blade with an airworthy stator blade. This amendment requires replacing the existing stator blade assembly with a new stator blade assembly that incorporates a reinforced base and modified riveting and limits the applicability to certain serial numbered tail booms. This amendment is prompted by additional reports of cracked stator blades of the tail rotor. The actions specified by this AD are intended to prevent failure of the tail rotor and subsequent loss of control of the helicopter.
AD 2000-25-09 · published Dec 29, 2000, effective Feb 2, 2001
Agusta S.p.A. Model A109E Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that currently requires inspecting the exhaust ejector locking system, clamp, and dampers for each engine. The existing AD also requires verifying the torque of the metallic clamps and installing safety wire on the metallic clamps; inspecting and modifying the ejector saddles and the locking metallic clamps; and inspecting the metallic clamps, locking mechanisms, and dampers. This amendment requires modifying the engine exhaust ejectors. This amendment is prompted by the development of a kit to modify the engine exhaust ejectors to provide terminating action from the requirements of the current AD. The actions specified by this AD are intended to prevent loss of the metallic clamp or the engine exhaust ejector, damage to the main or tail rotor system and subsequent loss of control of the helicopter.
AD 2000-26-11 · published Dec 29, 2000, effective Jan 16, 2001
Agusta S.p.A. Model A109E Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires replacing certain tail rotor blades with airworthy tail rotor blades. This amendment is prompted by a tail rotor blade (blade) failure that caused a high vibration level in the helicopter. Investigation revealed that the failure was due to a change in the manufacturing process for an identified production lot of blades. This condition, if not corrected, could result in a failure of a blade and subsequent loss of control of the helicopter.
AD 2000-24-24 · published Dec 13, 2000, effective Jan 12, 2001
Rolls-Royce plc RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 series turbofan engines having common nozzle assembly part number (P/N) FK16544 or FK16558. This action requires initial and repetitive visual inspections of the inner and outer skins of the common nozzle assembly and specifies allowable limits for cracks, loose rivets, and missing rivets. This action also requires repair if the common nozzle assembly damage exceeds allowable limits. This amendment is prompted by two reports of in-flight inner skin detachment. The actions specified in this AD are intended to detect cracks, loose rivets, and missing rivets, which could result in inner skin detachment, release of common nozzle assembly debris from the engine, and possible damage to the airplane control surfaces.
AD 2000-24-26 · published Dec 13, 2000, effective Feb 12, 2001
Rolls-Royce plc Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Rolls-Royce plc RB211 Trent 800 series turbofan engines, that currently requires initial and repetitive ultrasonic inspections of fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment requires the reduction of the initial cyclic compliance threshold and repetitive inspection intervals. This amendment also allows inspections to be accomplished within 100 cycles-in-service if the initial or repetitive thresholds are exceeded on the effective date of this AD. This amendment is prompted by an improved understanding of the crack propagation mechanism and the latest service operational data. The actions specified by this AD are intended to detect and prevent fan blade failure, which could result in multiple fan blade releases, uncontained engine failure, and possible damage to the airplane.
AD 2000-25-06 · published Dec 14, 2000, effective Dec 29, 2000
Pratt & Whitney PW4000 Series Turbofan Engines.
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney (PW) PW4000 turbofan engines with the current design low pressure turbine (LPT) 4th stage air seal installed. This action requires, based on engine model, replacement of the current design seal with a new design seal, or with a modified seal. This amendment is prompted by reports of cracks in LPT 4th stage air seals. The actions specified by this AD are intended to reduce stresses that could lead to LPT 4th stage air seal cracking, resulting in seal fracture, uncontained engine failure, and damage to the airplane.
AD 2000-24-23 · published Dec 11, 2000, effective Jan 27, 2001
S.N. CENTRAIR 101 Series Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain S.N. CENTRAIR 101 series gliders. This AD requires you to inspect the airbrake control system for cracks; and if cracks are detected, replace the airbrake control system. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to detect cracks in the airbrake control system and replace cracked parts with parts of improved design. A crack in the airbrake control system could prevent the pilot from using the airbrake system.
AD 2000-24-22 · published Dec 13, 2000, effective Jan 27, 2001
S.N. CENTRAIR Model 201B Gliders
This amendment adopts a new airworthiness directive (AD) that applies to all S.N. CENTRAIR Model 201B gliders. This AD requires you to modify the rear canopy emergency release system. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the rear canopy retaining strap from not releasing properly during the emergency egress procedure because of the current design of the rear canopy emergency release system. This condition, if not corrected, will not allow the rear canopy to completely separate from the glider and could result in potential injury to the pilot during an emergency egress.
