28 Airworthiness Directives: 19 airplane, 7 rotorcraft, 2 engine.
AD 2000-17-10 · published Sep 1, 2000, effective Oct 6, 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 modifications of the engine turbine cooling air panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and monitoring system for the engine turbine air temperature. This amendment is prompted by reports of an undetected fire breaching the high speed gearbox (HSGB) case on certain Rolls Royce engines installed on in-service airplanes due to lack of an internal fire detection system within the HSGB. The actions specified by this AD are intended to prevent undetected fires originating within the HSGB from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire.
AD 2000-17-11 · published Sep 1, 2000, effective Sep 22, 2000
Fairchild Aircraft, Inc., SA226 Series and SA227 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped with certain Ozone Industries, Inc., main landing gear (MLG) assemblies. This AD requires you to repetitively inspect the MLG drag brace assembly (consists of both brace and links) for cracks, and requires you to replace or rework any cracked MLG drag brace assembly. This AD is the result of several reports of cracks in the MLG drag brace assemblies on the affected airplanes. The actions specified by this AD are intended to detect and correct cracks in MLG drag brace assembly. Continued airplane operation with such cracks could lead to MLG failure and result in loss of control of the airplane during takeoff or landing operations.
AD 2000-18-01 · published Sep 1, 2000, effective Sep 18, 2000
Boeing Model 747 Series Airplanes Powered By Pratt & Whitney JT9D-7 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes powered by Pratt & Whitney JT9D-7 series engines. This action requires inspection of the lugs on the bulkhead fitting of the rear engine mount, and corrective action, if necessary. This action is necessary to detect and correct bushing migration, corrosion, or cracking of the lugs on the bulkhead fitting of the rear engine mount, which could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2000-17-09 · published Sep 6, 2000, effective Oct 11, 2000
Aerospatiale Model ATR42-300, -300, and -320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-200, -300, and -320 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2000-18-02 · published Sep 7, 2000, effective Sep 22, 2000
Raytheon Aircraft Company Models A65, A65-8200, 65-B80, 70, 95-A55, 95-B55, 95-C55, D55, E55, 56TC, A56TC, 58, 58P, 58TC, and 95-B55B (T42A) Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models A65, A65-8200, 65-B80, 70, 95-A55, 95-B55, 95-C55, D55, E55, 56TC, A56TC, 58, 58P, 58TC, 95-B55B (T42A) airplanes. This AD requires replacement of certain elevator skin assemblies that Raytheon shipped from January 1, 1999, through December 31, 1999, and prevents the future installation of these elevator skin assemblies. This AD authorizes the pilot to check the logbooks to determine whether one of these elevator skin assemblies is installed. This AD is the result of reports that certain elevator skin assemblies did not receive a 250-degree Fahrenheit bake operation after corrosion treatment, thus making the skin susceptible to separation from the elevator assembly. The actions specified by this AD are intended to detect and correct potential elevator skin separation, which would lead to a reduction in static strength capability with continued operation. This could then result in potential airplane flutter with consequent loss of control of the airplane.
AD 2000-14-07 · published Sep 8, 2000, effective Aug 17, 2000
Boeing Model 727 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain Boeing Model 727 series airplanes. That AD supersedes an earlier airworthiness directive to require repetitive inspections to detect cracking of the rear spar web or fuel leakage of the wing center section; repair, if necessary; and modification of the rear spar web. This document corrects the effective date of the earlier, superseded AD, which was stated incorrectly in the existing AD. This correction is necessary to ensure that operators are advised of the correct effective date of the original AD, specifically as it affects the compliance time for a certain paragraph of this AD.
AD 2000-18-05 · published Sep 8, 2000, effective Oct 13, 2000
Aerospatiale Model ATR42 and ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42 and ATR72 series airplanes, that requires modification of the alerting capability of the anti-icing advisory system to improve crew awareness of icing conditions, replacement of the median wing de-icing boots with extended de-icing boots, and installation of de-icing boots on the metallic wing leading edge. 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 reduce the degradation of lift and drag characteristics in prolonged severe icing exposure, which could result in loss of lift and consequent reduced controllability of the airplane.
AD 2000-18-07 · published Sep 8, 2000, effective Oct 13, 2000
Airbus Model A300, A300-600, and A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, and A310 series airplanes, that requires replacement of the transformer rectifier units (TRU) in the avionics compartment with new, improved TRU'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 failure of the TRU's. Failure of multiple TRU's could result in loss of the thrust reversers, autothrottle, flaps, and various systems (wing/cockpit window anti-ice, trim tank pumps, and windshield wipers) on the airplane; or incorrect information displayed to the flight crew.
AD 2000-18-11 · published Sep 14, 2000, effective Sep 29, 2000
Israel Aircraft Industries, Ltd., Model 1125 Westwind Astra Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model 1125 Westwind Astra series airplanes. This action requires revising the Airplane Flight Manual to provide the flight crew with operational guidance under certain failure conditions and a limitation not to engage the long-range navigation system during takeoff, approach, or landing. This action is necessary to prevent the loss of primary attitude and directional gyros, which relate position information to the flight crew. This action is intended to address the identified unsafe condition.
AD 2000-18-12 · published Sep 15, 2000, effective Sep 27, 2000
Polskie Zaklady Lotnicze Spolka zo.o. Models PZL M18, PZL M18A, and PZL M18B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Polskie Zaklady Lotnicze Spolka zo.o. (PZL-Mielac) Models PZL M18, PZL M18A, and PZL M18B airplanes. This AD requires you to repetitively inspect the centerwing-to-outboard wing attach joints for cracks in the lugs, corrosion in the main holes, and ovalization of the main holes; repair corrosion and apply anti-corrosion protection; replace the wing attach joints, as necessary; and eliminate any ovalization of the wing main joint holes. This AD is the result two instances of in-flight wing separation on Model PZL M18A airplanes where severe corrosion and pitting led to high stress concentrations on the wing attachment joints. The actions specified by this AD are intended to detect and correct cracks in the lugs, corrosion in the main holes, and ovalization of the main holes, in the centerwing-to- outboard wing attach joints. Such damage could result in failure of the joints with consequent in-flight wing separation.
AD 2000-19-02 · published Sep 18, 2000, effective Oct 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 all EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, and follow-on corrective actions. This action is necessary to prevent failure of the electrical connectors of the fuel pumps, which could result in fuel leakage from the connectors or electrical arcing across the connector pins of the pump, and consequent fuel fire or explosion.
AD 2000-19-03 · published Sep 18, 2000, effective Oct 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 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 action is necessary 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 identified unsafe condition.
AD 2000-19-04 · published Sep 18, 2000, effective Oct 31, 2000
Raytheon Aircraft Company Beech Models 1900C, 1900C (C-12J), and 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900C, 1900C (C-12J), and 1900D airplanes. This AD requires you to install a spiral wrap around the wing fuel quantity wiring harness and apply an adhesive sealant to the Wiggins couplings on the internal fuel tank wiring carry-through conduit. This AD is the result of reports of chafed or shorted wing fuel quantity harness wires on the affected airplanes. These occurrences were found during regular maintenance inspections. The actions specified by this AD are intended to prevent chafing between the wing fuel quantity wiring harness and the internal wing harness supports at each wing rib location, which could cause the fuel quantity indication to become unreliable. This could leave the flight crew without an indication of the amount of fuel the airplane has during flight. The actions are also intended to prevent fuel from leaking through the wiring carry-through conduit and into the wing tip or wheel well area, which could lead to a fire or explosion.
AD 2000-19-01 · published Sep 20, 2000, effective Oct 25, 2000
Bombardier Model CL-600-1A11 (CL-600) and CL-600-2A12 (CL-601) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Bombardier Model CL-600-1A11 (CL-600) and CL-600-2A12 (CL-601) series airplanes, that requires modification of the main landing gear (MLG) brake units and inboard MLG wheels; and a revision to the Airplane Flight Manual (AFM) to include the increased cooling times for the modified brakes. This amendment allows, for certain cases, removal of the inboard and/or outboard wheel discs by installation of a placard to limit airplane operation on the ground and a revision to the AFM to include information for operating the airplane with the wheel discs removed. Additionally, this amendment provides for an acceptable method of compliance that involves installation of a new revision to the AFM. 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 water freezing on the brake while the airplane is in flight due to water, slush, or snow from the runway entering into the brake assemblies during takeoff, and consequently, a tire burst during landing of the airplane.
AD 2000-19-06 · published Sep 20, 2000, effective Oct 5, 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. This action requires modifying the bottom skin panel 3 (located aft of the rear spar). This action is necessary to prevent corrosion and consequent reduced structural integrity of the wings due to lack of cold expansion of an existing drain hole, which could lead to cracks initiating from that drain hole; and the incorrect location of the drain hole, which can allow moisture to be trapped. This action is intended to address the identified unsafe condition.
AD 2000-19-08 · published Sep 22, 2000, effective Oct 10, 2000
Boeing Model 777 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 777 series airplanes. The existing AD requires repetitive detailed visual inspections to detect cracking of the coveskin on the outboard leading edge slats; a slat adjustment check; and corrective actions, if necessary. This amendment reduces the repetitive inspection interval, but also provides for an optional modification that would significantly increase the repetitive inspection interval. This amendment also revises the applicability of the existing AD to remove certain airplanes. This amendment is prompted by findings of increased vibration of the coveskins due to air leaking and resonating within the cavity between the fixed leading edge and the coveskin; the vibration can result in fatigue cracking and high fatigue loads. The actions specified in this AD are intended to detect and correct cracking and/or missing pieces of the coveskin on the outboard leading edge slats on the wings, which could result in skin separation or structural damage to the leading edge slats and consequent reduced controllability of the airplane.
AD 2000-19-07 · published Sep 26, 2000, effective Oct 31, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, EMB-120ER, and EMB-120RT Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120, EMB-120ER, and EMB-120RT series airplanes, that requires removal of a certain fastener, if applicable, and sealing of the corresponding fastener hole. This action is necessary to prevent contact between one of the bolts that attaches the direct current (DC) relay box on the left-hand side of the airplane and one of the power terminals of electrical emergency contactor 2, which could result in a short circuit in the DC relay box, and consequent partial loss of the electrical system, and degraded operation of airplane systems. This action is intended to address the identified unsafe condition.
AD 2000-20-03 · published Sep 27, 2000, effective Oct 2, 2000
Bombardier Model CL-600-2B19 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires installation of shields for the aileron quadrants in the wheel bay of the main landing gear (MLG). This action is necessary to prevent the accumulation of water, ice, or slush on the aileron quadrants and control cable pulleys in the wheel bay of the MLG, which could freeze and result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-19-10 · published Sep 28, 2000, effective Oct 13, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that currently requires a one-time inspection of the movable backstop of the elevator pitch trim command system to ensure that it is installed correctly, and corrective action, if necessary. That AD also requires installation of a guide to maintain the movable backstop in its correct position. This amendment adds a requirement for an additional one-time inspection. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent a sudden change in pitch attitude caused by autopilot disconnect, which could result in reduced controllability of the airplane.
AD 2000-18-10 · published Sep 11, 2000, effective Sep 26, 2000
Kaman Model K-1200 Helicopters
This amendment adopts a new airworthiness directive (AD) for Kaman Model K-1200 helicopters. This action requires replacing certain unairworthy sprag clutches with airworthy sprag clutches. This amendment is prompted by two incidents of sprag clutch failure during external load operations. The actions specified in this AD are intended to prevent a malfunctioning transmission clutch, loss of drive to the main rotor system, and subsequent loss of control of the helicopter.
AD 2000-18-09 · published Sep 13, 2000, effective Sep 28, 2000
Bell Helicopter Textron, Inc. Model 412, 412EP, and 412CF Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 412, 412EP, and 412CF helicopters. This AD requires inspecting the upper left-hand cap angle (cap angle) and adjacent structure for a crack and, before further flight, replacing any cracked cap angle and repairing any crack in the adjacent structure. This AD is prompted by a report of a fatigue crack in a tailboom attachment cap angle. The actions specified in this AD are intended to prevent failure of a cap angle, loss of the tailboom, and subsequent loss of control of the helicopter.
AD 2000-16-52 · published Sep 14, 2000, effective Sep 29, 2000
Eurocopter France Model AS350B3 Helicopters
This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2000-16-52 which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model AS350B3 helicopters by individual letters. This AD requires visually inspecting the heat shield attachment areas on the tail rotor drive shaft forward fairing (fairing) for a crack. This AD also requires, at specified time intervals, removing the fairing and inspecting the heat shield attachment areas on the fairing for a crack. If a crack is found, this AD requires replacing the fairing with an airworthy fairing. This amendment is prompted by an in-flight loss of the fairing heat shield due to cracking in the areas where the heat shield is attached to the fairing. The actions specified by this AD are intended to prevent an in-flight loss of the heat shield, impact with tail or main rotor blades, and subsequent loss of control of the helicopter.
AD 2000-18-08 · published Sep 14, 2000, effective Oct 19, 2000
MD Helicopters, Inc. Model MD-900 Helicopters
This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD-900 helicopters that requires modifying the non-rotating swashplate assembly and re- identifying it and the swashplate assembly with new part numbers. This AD also requires creating a component history card or equivalent record to track the life of the newly identified non-rotating swashplate assembly and establishing a life limit of 1800 hours time-in-service (TIS). Additionally, this AD requires inspecting and modifying, if necessary, the longitudinal drive link assembly. This AD is prompted by reports of damage to the longitudinal drive link assembly caused by the sharp inner edge of the bushing in the non-rotating swashplate assembly. The actions specified by this AD are intended to prevent damage to the longitudinal drive link, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
AD 2000-18-13 · published Sep 14, 2000
Eurocopter Canada Ltd. Model BO 105 LS A-3 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Canada Ltd. Model BO 105 LS A-3 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, and 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 an accident in which a main rotor blade (blade) separated from a Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part-numbered TT strap is used on the Model BO 105 LS A-3 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 2000-18-14 · published Sep 14, 2000
Sikorsky Aircraft-Manufactured Model CH-54A Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Sikorsky Aircraft-manufactured Model CH-54A helicopters. That AD currently requires initial and recurring inspections and rework or replacement, if necessary, of the second stage lower planetary plate (plate). This AD requires the same actions as the existing AD but would add two additional type certificate (TC) holders to the applicability of the AD and change one TC holder who has transferred ownership of the affected helicopters since the issuance of the existing AD. This amendment is prompted by the discovery that the applicability section of the existing AD is incomplete. The actions specified by this AD are intended to prevent failure of the plate due to fatigue cracking, which could result in failure of the main gearbox, failure of the drive system, and subsequent loss of control of the helicopter.
AD 2000-17-52 · published Sep 22, 2000, effective Oct 10, 2000
Agusta S.p.A. Model A109E Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-17-52, which was sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model A109E helicopters by individual letters. This AD requires, before further flight, visually inspecting any main rotor rotating scissors assembly for correct installation and replacing any unairworthy part with an airworthy part. If the rotating scissors attachment bolt (attachment bolt) is not replaced with a new part at the initial inspection, this AD also requires removing the rotating scissors assembly to inspect the attachment bolt for a crack and replacing any cracked attachment bolt with a new attachment bolt before further flight. This amendment is prompted by two incidents of flight control malfunctions. The actions specified by this AD are intended to prevent failure of the rotating scissors assembly and subsequent loss of control of the helicopter.
AD 2000-18-03 · published Sep 7, 2000, effective Sep 22, 2000
Rolls-Royce plc RB211-524D4 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc models RB211-524D4-19, -524D4-B-19, - 524D4-B-39, -524D4X-19, and 524D4X-B-19 turbofan engines with a cold stream nozzle assembly Part Number (PN) LJ32826 installed. This action requires inspection for cracks and repair of the cold stream nozzle assembly longitudinal flange. This amendment is prompted by a report of the loss of a large section of cold stream nozzle assembly in flight. The actions specified in this AD are intended to detect cracks that could result in failure of the cold stream nozzle assembly, possible release of cold stream nozzle debris from the engine, and possible damage to airplane control surfaces.
AD 2000-18-06 · published Sep 7, 2000, effective Sep 22, 2000
Allison Engine Company AE 3007A and 3007C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines with certain full authority digital electronic controls (FADEC's), listed by hardware serial number (SN), installed. This action requires inspections of installed FADEC's before further flight to be sure that no more than one engine with suspect FADEC's is installed on the same airplane, and eventual replacement of all of the suspect FADEC's with serviceable FADEC's. This amendment is prompted by reports of uncommanded in-flight shutdowns of engines. The actions specified in this AD are intended to prevent an uncommanded in-flight engine shutdown and the potential for an in-flight dual-engine shutdown caused by a potential hardware failure mode in some AE 3007 series FADEC's.
