35 Airworthiness Directives: 29 airplane, 3 rotorcraft, 2 engine, 1 glider.
AD 2000-13-07 · published Jul 3, 2000, effective Aug 7, 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 AD requires repetitive detailed visual and ultrasonic inspections of the main landing gear (MLG) to detect fatigue cracks, and repair if necessary; replacement of certain nose landing gear (NLG) handwheel controllers and certain placards with new placards; installation of steering angle recording software; and corrective action for exceeding certain steering angles. This AD also requires an AFM revision to limit the nose wheel steering angle for pushback and towing and to limit the nose wheel steering for powered turns. 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 MLG failure due to fatigue cracking, which could result in reduced structural capability of the airplane and collapse of the MLG.
AD 99-05-13 R1 WD · published Jul 5, 2000, effective Jul 5, 2000
Beech Aircraft Corporation, Hawker Beechcraft Corporation Airplanes
This amendment withdraws Airworthiness Directive (AD) 99-05-13, which currently applies to Raytheon Aircraft Company (Raytheon) Beech 17, 18, 19, 23, 24, 33, 35, 36/A36, A36TC/B36TC, 45, 50, 55, 56, 58, 58P, 58TC, 60, 65, 70, 76, 77, 80, 88, and 95 series airplanes. AD 99-05-13 requires installing a placard on the fuel tank selector to warn of the no-flow condition that exists between the fuel tank detents. Since the issuance of AD 99-05-13, the Federal Aviation Administration (FAA) has re-evaluated all information related to this subject, and determined that the subject matter in this AD is an operational issue and does not address an unsafe condition. Accordingly, this action withdraws AD 99-05-13.
AD 2000-09-01 R1 · published Jul 7, 2000, effective Jun 7, 2000
McDonnell Douglas Model DC-8 Series Airplanes
This document corrects and clarifies information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-8 series airplanes. 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; repetitive inspections of the wire bundle and door latch rollers to detect damage; and repair or replacement of damaged components. That AD also requires, among other actions, modification of the indication and hydraulic 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 two errors that resulted in the incorrect references of two paragraphs. This correction is necessary to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of the door, flight control, or severe structural damage.
AD 2000-13-09 · published Jul 7, 2000, effective Aug 11, 2000
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires repetitive detailed visual and dye penetrant inspections of the backup struts in the left and right nacelles to detect discrepancies; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the backup struts in the left and right nacelles due to fatigue cracking, which could result in loss of fail-safe redundancy in the design of the nacelle in terms of load capability.
AD 2000-14-08 · published Jul 10, 2000, effective Aug 21, 2000
The New Piper Aircraft, Inc. PA-42 Series Airplanes
This document adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. (Piper) PA-42 series airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident (on airplanes other than the affected Piper airplanes) that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The Piper PA-42 series airplanes have a similar type design (as it relates to airframe pneumatic deice boots) to the incident and accident airplanes. The actions specified by this AD are intended to assure that flight crews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-14-02 · published Jul 13, 2000, effective Jul 28, 2000
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and -800 series airplanes. This action requires installation of placards on the P3-1 panel. This action is necessary to prevent loss of communication between the flight crew and Air Traffic Control; this situation could result in the flight crew being unaware of an unsafe scenario when the airplane is on the ground. This action is intended to address the identified unsafe condition.
AD 2000-14-03 · published Jul 13, 2000, effective Aug 17, 2000
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires replacing the smoke detectors in the cargo compartment with new, improved smoke detectors. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent false smoke warnings from the cargo compartment smoke detectors, which could result in aborted takeoffs, diversions of flight routes, and emergency evacuation of flight crew and passengers.
AD 2000-14-04 · published Jul 13, 2000, effective Jul 28, 2000
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747 series airplanes. This action requires a one-time inspection of the fuselage skin adjacent to the drag splice fitting to detect cracking, and follow-on actions, if necessary. This action is necessary to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the fuselage, and consequent rapid depressurization of the airplane.
AD 2000-14-05 · published Jul 13, 2000, effective Jul 28, 2000
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777 series airplanes. This action requires a one-time measurement of the electrical bonding resistance between the wing spar connectors of the fuel quantity indicating system (FQIS) and the spar structure, installation of bonding jumpers, a one- time operational check of the FQIS system, and corrective action, if necessary. This action is necessary to ensure adequate electrical bonding between the wing spar connectors of the FQIS and the spar structure. Inadequate electrical bonding, in the event of a lightning strike, could cause electrical arcing and ignition of fuel vapor in the main or center fuel tank, which could result in a fuel tank explosion. This action is intended to address the identified unsafe condition.
AD 2000-14-06 · published Jul 13, 2000, effective Aug 17, 2000
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires a one-time inspection to determine the part number of the fuel shutoff spar valve for the outboard engines. That AD also requires replacement of certain valves with new valves, or modification of the spar valve body assembly, and various follow-on actions. This amendment adds new requirements to accomplish those actions on additional airplanes; and requires a one- time inspection of the maintenance records of certain airplanes to determine if the fuel shutoff spar valve for the outboard engines has ever been replaced, and various follow-on actions. This amendment is prompted by reports indicating that, due to high fuel pressure, certain fuel system components of the outboard engines have failed. The actions specified by this AD are intended to prevent such high fuel pressure, which could result in failure of the fuel systemcomponents; this situation could result in fuel leakage, and, consequently, lead to an engine fire.
AD 2000-12-21 · published Jul 18, 2000, effective Jul 28, 2000
Boeing Model 747-400 Series Airplanes Equipped with Pratt & Whitney PW4000 Series Engines
This document corrects information in an existing airworthiness directive (AD) that applies to certain Boeing Model 747- 400 series airplanes. That AD currently requires installation of a modification of the thrust reverser control and indication system and wiring on each engine; and repetitive functional tests of that installation to detect discrepancies, and repair, if necessary. This document publishes Appendix 1, which was referenced in, but inadvertently omitted from, the existing AD. Appendix 1 describes procedures for a functional test to detect discrepancies of the additional locking system on each engine thrust reverser. This correction is necessary to ensure that operators have the procedures necessary to perform the required functional test.
AD 2000-14-01 · published Jul 19, 2000, effective Aug 23, 2000
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires replacement of any brake system accumulator that has aluminum end caps with an accumulator that has stainless steel end caps. This amendment is prompted by reports of fractures of aluminum end caps on brake system accumulators. The actions specified by this AD are intended to prevent high-velocity separation of a brake system accumulator barrel, piston, or end cap, which could result in injury to personnel in the wheel well area, loss of cabin pressurization, loss of certain hydraulic systems, or damage to the fuel line of the auxiliary power unit.
AD 2000-14-09 · published Jul 19, 2000, effective Aug 23, 2000
Short Brothers Model SD3-60 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3-60 series airplanes, that requires affixing a label containing revised engine limitations on the ditching hatch, and revising the airplane flight manual to reflect the revised engine limitations. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the use of incorrect engine limitations, which could result in an overspeed of the propellers and potential for blade failure.
AD 2000-14-10 · published Jul 19, 2000, effective Aug 23, 2000
McDonnell Douglas Model DC-10-10, -15, -30, and -40 Series Airplanes; Model MD-10-10F and MD-10-30F Series Airplanes; and KC-10A (Military) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that currently requires repetitive inspections to detect failure of the attachment fasteners located in the banjo No. 4 fitting of the vertical stabilizer. That AD also requires a one-time inspection to detect cracking of the flanges and bolt holes of the banjo No. 4 fitting, and repair or replacement of the attachment fasteners with new, improved fasteners. This amendment adds a new one-time inspection to determine whether certain fasteners are installed in the banjo No. 4 fitting of the vertical stabilizer, and follow-on actions, if necessary. This amendment is prompted by reports of failure of certain fasteners installed in the banjo No. 4 fitting of the vertical stabilizer. The actions specified by this AD are intended to prevent cracking of the attachment fasteners of the vertical stabilizer, which could result in loss of fail-safe capability of the vertical stabilizer and reduced controllability of the airplane.
AD 2000-14-11 · published Jul 19, 2000, effective Aug 23, 2000
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes equipped with General Electric Model CF6-45 or -50 series engines, that requires repetitive inspections and tests of the thrust reverser control and indication system, and corrective actions, if necessary. This amendment also requires installation of a thrust reverser actuation system (TRAS) lock, repetitive functional tests of that installation, and repair, if necessary. Installation of the TRAS lock terminates the repetitive inspections and certain tests. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in a significant reduction in airplane controllability. 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 2000-14-12 · published Jul 19, 2000, effective Aug 23, 2000
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 replacement of the upper and lower reading lights in the forward crew rest area with a redesigned light fixture. This amendment is prompted by reports of burning and smoldering blankets in the forward crew rest area due to a reading light fixture that came into contact with the blankets after the light was inadvertently left on. The actions specified by this AD are intended to prevent a possible flammable condition, which could result in smoke and fire in the forward crew rest area.
AD 2000-14-13 · published Jul 19, 2000, effective Aug 23, 2000
Boeing Model 737-200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-200, -300, -400, and -500 series airplanes, that requires replacement of existing door handle mounting hub assemblies with new, improved hub assemblies. This amendment is prompted by reports of cracked or broken mounting hub assemblies for the interior door handles on the cabin doors. The actions specified by thisAD are intended to prevent cracking or breaking of the door handle mounting hub, which could result in the interior door handle breaking off while the door is being opened. In an emergency situation, this could impede evacuation of the airplane.
AD 2000-13-51 · published Jul 20, 2000, effective Jul 25, 2000
Boeing Model 737-200 and -300 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-13-51 that was sent previously to certain U.S. owners and operators of Boeing Model 737-200 and -300 series airplanes by individual notices. This AD requires repetitive special detailed inspections to detect cracking of the main deck cargo door frames, their existing reinforcing angles (where applicable), and the attach holes of the latch fittings between frame station (FS) 361.87 and FS 498.12, and between water line (WL) 202.35 and WL 213.00, in the area where the main deck cargo door latch fittings attach to the frames, and corrective actions, if necessary. This action is prompted by a report indicating that three of the subject airplanes had multiple cracks in the lower portion of the main deck cargo door frames and, in some cases, the reinforcing angles. 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 2000-14-14 · published Jul 21, 2000, effective Aug 7, 2000
BFGoodrich Main Brake Assemblies as Installed on Airbus Model A319 and A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain BFGoodrich main brake assemblies as installed on Airbus Model A319 and A320 series airplanes. This action requires repetitive inspections to determine the length of the wear indicator pins of the main brake assemblies of the main landing gear (MLG); follow-on inspections; and corrective actions, if necessary. This amendment is prompted by reports from several operators that severe oxidation was found on the rotor disk assemblies of the main brake assemblies. This action is necessary to detect and correct thermal oxidation of the main brake assemblies, which could result in deterioration of the MLG brakes, and consequent reduced braking performance.
AD 2000-09-15 R1 · published Jul 24, 2000, effective Jul 24, 2000
Mitsubishi Heavy Industries, Ltd. Airplanes
This amendment clarifies information contained in Airworthiness Directive (AD) 2000-09-15, which currently requires you to incorporate modifications to the airplane operating systems on all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. The Federal Aviation Administration (FAA) inadvertently omitted service information from the AD that is needed to accomplish these modifications on some of the affected airplanes. This document retains the requirements of AD 2000-09-15, and adds the service information to the AD. The actions specified in this AD are intended to continue to assist in preventing departure from controlled flight while operating in icing conditions.
AD 2000-14-15 · published Jul 24, 2000, effective Aug 28, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modifying the fuel pipe couplings and installing bonding leads in specified locations within the fuel tank. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent ignition sources and consequent fire/explosion in the fuel tank.
AD 2000-14-17 · published Jul 24, 2000, effective Aug 28, 2000
Bombardier Model CL-600-2B19 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to require the flight crew to check, and reset, if necessary, certain instrument settings prior to each takeoff and after any event during which generators are switched. This amendment adds a new revision to the AFM and revises the applicability of the existing AD. This amendment also requires modification of the air data reference systems. 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 uncommanded changes in certain instrument settings on the pilot's and co-pilot's instrument displays, which could result in confusion among the flight crew about the correct position and flight configuration of the airplane.
AD 2000-15-02 · published Jul 25, 2000, effective Aug 9, 2000
Boeing Model 747-400 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-400 series airplanes. This action requires a one-time inspection to determine if certain wire bundles are routed incorrectly and to detect damage, and corrective actions, if necessary. This action is necessary to prevent damage of certain wire bundles routed to the fuel tank transfer pumps in the horizontal stabilizer, which could result in electrical arcing and a possible fire adjacent to the fuel tank. This action is intended to address the identified unsafe condition.
AD 2000-14-18 · published Jul 27, 2000, effective Aug 11, 2000
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. This action requires an inspection of the powered drive unit power wires within three feet of each affected powered drive unit termination for mechanical damage; and repair, if necessary. This action also requires revising the wire harnesses; splicing any additional length wire; routing and installing parts; and replacing the floor panels with new and retained floor panels. This action is necessary to ensure that the powered roller pans are positioned properly. Improperly positioned powered roller pans could pierce a powered roller wire harness and cause sparking that could ignite adjacent insulation material, which could result in smoke and fire in the center cargo compartment of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-14-51 · published Jul 31, 2000, effective Aug 4, 2000
Air Tractor, Inc. Models AT-501, AT-502, and AT-502A Airplanes
This document publishes in the Federal Register an amendment adopting emergency Airworthiness Directive (AD) 2000-14-51. The Federal Aviation Administration (FAA) previously sent emergency AD 2000-14-51 to all known U.S. owners and operators of Air Tractor Models AT-501, AT-502, and AT-502A airplanes. This AD requires you to inspect the wing lower spar cap for cracks and modify or replace any cracked lower spar cap. This AD is the result of an accident report of an Air Tractor Model AT-502A airplane where the wing separated in flight. The actions specified by this AD are intended to detect and correct fatigue cracks in the wing lower spar cap, which could result in an in-flight separation of the wing from the airplane.
AD 2000-15-05 · published Jul 31, 2000, effective Sep 4, 2000
McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10 Military), -40, and -40F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10 military), -40, and -40F series airplanes, that requires a one-time inspection of the wiring and wire bundles of the aft main avionics rack (MAR) to determine if the wires are damaged, or riding or chafing on structure, clamps, braces, standoffs, or clips, and to detect damaged or out of alignment rubber cushion inserts of the wiring clamps; and corrective actions, if necessary. This amendment is prompted by an incident in which the automatic and manual cargo door test in the cockpit was inoperative during dispatch of the airplane, due to wiring of the MAR chafing against clamps as a result of the wire bundles being installed improperly during production of the airplane. The actions specified by this AD are intended to ensure that the wires that route from the main wire bundles to the MAR and associated brackets, clamps, braces, standoffs, and clips are installed properly. Improper installation of such wiring and structure could cause chafing of the wires/wire bundles, which could result in electrical arcing, smoke, and possible fire in the MAR.
AD 2000-15-06 · published Jul 31, 2000, effective Sep 4, 2000
McDonnell Douglas Model DC-10 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes, that requires a general visual inspection of electrical power feeder cables, airplane structure, and insulation blankets at a certain fuselage station to detect chafing and arcing damage, and corrective actions, if necessary; and installation of a standoff and clamp. This amendment is prompted by an incident in which the power feeder cables in the cabin electrical system were found to be chafed and arced against a fuselage frame due to insufficient clearance between the cables and airplane structure. The actions specified by this AD are intended to prevent such chafing and arcing, which could cause smoke and fire in the overhead of the main cabin.
AD 2000-15-07 · published Jul 31, 2000, effective Sep 4, 2000
McDonnell Douglas Model DC-10 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes, that requires a one-time detailed visual inspection of the galley power feeder cables and fuselage structure at a certain station to detect chafing or arcing damage to the cables and structure or to detect arcing damage to the insulation blankets; and corrective actions, if necessary. This AD also requires installation of spacers between the galley power feeder cable clamps and fuselage structure. This amendment is prompted by reports indicating that the galley power feeder cables chafed against a certain fuselage frame in the forward lower cargo compartment, which resulted in electrical arcing. The actions specified by this AD are intended to prevent such chafing and arcing due to insufficient clearance between the cables and the airplane structure, which could result in smoke and fire in the forward lower cargo compartment.
AD 90-15-12 R1 · published Jul 31, 2000, effective Aug 15, 2000
Boeing Model 727 Series Airplanes Modified in Accordance with Valsan Supplemental Type Certificate (STC) SA4363NM
This amendment revises an existing airworthiness directive (AD), applicable to Boeing Model 727 series airplanes modified by the installation of Pratt and Whitney JT8D-217C or -219 engines in accordance with Valsan STC SA4363NM, that currently requires repetitive inspections of the through-bolt nut for proper torque and for certain other conditions of the through-bolt and nut, and replacement, if necessary. That AD also requires the installation of anti-rotation plates, which constitutes terminating action for the repetitive inspections. 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 nut coming off the through-bolt allowing the through-bolt to migrate out of the engine mount flange and cone bolt and possible separation of the engine.
AD 2000-13-06 · published Jul 3, 2000, effective Jul 18, 2000
Sikorsky Model S-61 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Model S-61 helicopters. That AD requires inspecting certain pylon upper and lower hinge web fittings (web fittings) for corrosion or a crack and either repairing certain web fittings or replacing any unairworthy web fittings with airworthy web fittings. That AD also requires creating a log card or equivalent record and implementing a recurring inspection of the web fittings. This amendment retains the requirements of that AD but corrects an error in paragraph (a)(3) by removing the words "and 3.E." This amendment is prompted by an operator notifying the FAA of that error which requires an unnecessary major inspection within 25 hours time-in-service (TIS). The actions specified in this AD are intended to remove an undue burden on the public by superseding the AD and removing the requirement for the major inspection within 25 hours TIS.
AD 2000-13-08 · published Jul 5, 2000, effective Aug 9, 2000
Eurocopter Deutschland GmbH Model EC 135 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GmbH (ECD) Model EC 135 helicopters. That AD requires conducting a tail rotor drive shaft vibration survey (survey), installing a Fenestron Shaft Retrofit Kit, inspecting each tail rotor drive shaft bearing (bearing) attaching lock plate for bent-open tabs and broken or missing slippage marks, and visually inspecting each bearing support for cracks. This AD requires conducting the survey and installing the Fenestron Shaft Retrofit Kit. This AD also requires installing double bearing supports and struts, revising the required compliance time for the repetitive inspections of the bearing attach hardware and supports, and removing the requirement to contact the FAA if a lock plate tab is bent open or if slippage marks are broken or missing. This amendment is prompted by continued reports of misaligned or cracked bearing supports and loose bearing attachment bolts. The actions specified by this AD are intended to prevent loss of drive to the tail rotor and subsequent loss of control of the helicopter.
AD 2000-14-16 · published Jul 25, 2000, effective Aug 29, 2000
Bell Helicopter Textron Canada Model 407 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. That AD requires installing a tail rotor pitch-limiting left-pedal stop (pedal stop), installing an airspeed limitation placard, marking a never-exceed velocity (Vne) placard on all airspeed indicators, and revising the Limitations section of the Rotorcraft Flight Manual (RFM). This AD requires installing a redesigned tail rotor system and modifying the vertical fin and horizontal stabilizer to allow restoring the Vne to 140 knots indicated airspeed (IAS). This AD is prompted by design changes to the tail rotor system and modification of the pedal stop for airspeed actuation to eliminate a tail rotor strike to the tailboom. The actions specified by this AD are intended to prevent the tail rotor blades from striking the tailboom, separation of the aft section of the tailboom with the tail rotor gearbox and vertical fin, and subsequent loss of control of the helicopter.
AD 2000-13-01 · published Jul 3, 2000, effective Sep 1, 2000
Allison Engine Company, Inc. AE 3007A and AE 3007C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company, Inc. AE 3007A and AE 3007C series turbofan engines. This AD requires the removal from service of certain turbine wheels before exceeding new, reduced cyclic life limits. This amendment is prompted by a refined life analysis that was performed by the manufacturer. The actions specified by this AD are intended to prevent an uncontained turbine wheel failure, which could result in damage to the airplane.
AD 2000-13-05 · published Jul 3, 2000, effective Aug 2, 2000
Rolls-Royce plc. RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-60, Trent 772- 60, and Trent 772B-60 turbofan engines. This action requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and if necessary, replacement with serviceable parts. This amendment is prompted by reports of fan blade failures due to dovetail root cracks. The actions specified in this AD are intended to prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-15-03 · published Jul 26, 2000, effective Aug 4, 2000
Stemme GmbH & Co. KG Models S10-V and S10-VT Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to Stemme GmbH & Co. KG (Stemme) Models S10-V and S10-VT sailplanes. This AD supersedes AD 98-15-24, which currently requires replacing the propeller blade suspension forks with parts of improved design on Stemme S10-V sailplanes. This AD requires you to remove the propeller blade suspension forks, exchange them with the manufacturer for improved design forks, and install the improved design propeller blade suspension forks. This AD is the result of analysis that shows that the existing propeller blade suspension forks are currently cracking more rapidly than originally projected. The actions specified by this AD are intended to prevent certain propeller blade suspension forks from cracking, which could result in the loss of a propeller blade during flight with possible lateral imbalance and loss of thrust.
