52 Airworthiness Directives: 40 airplane, 10 rotorcraft, 2 engine.
AD 99-21-02 · published Oct 1, 1999, effective Nov 5, 1999
Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA series airplanes, that requires detailed visual and borescopic inspections to detect corrosion of the engine mounting tube assembly, and replacement of corroded parts with new or serviceable parts. 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 engine mounting tube assembly, which could result in loss of the engine in flight.
AD 99-21-03 · published Oct 1, 1999, effective Oct 18, 1999
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-145 series airplanes. This action requires revising the Airplane Flight Manual (AFM) for operation in the rain, and modifying the anemometric static ports. This action also provides for optional terminating action for the requirements of this AD. 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 limit or prohibit the use of the autopilot and flight director during the descent and approach to land in the rain, and to prevent fluctuations and erratic indications in the vertical speed, airspeed, and altitude readings in the cockpit during the descent and approach to land in the rain; such conditions could result in reduced controllability of the airplane during the descent and approach to land in the rain.
AD 99-21-04 · published Oct 1, 1999, effective Nov 5, 1999
Airbus Model A330-301, and Model A340- 211, -212, -311, and -312 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, and Model A340-211, -212, -311, and -312 series airplanes, that requires repetitive detailed visual inspections of the fuselage belly fairing support structure to detect cracks; and corrective action, if necessary. This amendment also provides an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the fuselage belly fairing support structure, which could result in reduced structural integrity of the fuselage belly fairing support structure.
AD 99-20-09 · published Oct 4, 1999, effective Nov 8, 1999
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections of the lower engine mount to determine if the tangential link upper bolt and nut are oriented properly, and if the tangential link upper bolt nut is torqued within certain limits. Additionally, that amendment requires replacement of the bolt and nut with serviceable parts, if necessary, and requires certain follow-on actions for airplanes on which the upper bolt is missing. This amendment requires accomplishment of a previously optional terminating action or a new alternative terminating action for the repetitive inspections. This amendment is prompted by development of a new terminating action by the manufacturer. The actions specified by this AD are intended to prevent separation of the engine from the airplane due to migration of the tangential link upper bolt.
AD 99-20-10 · published Oct 4, 1999, effective Nov 8, 1999
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires modification of the pressure web of the nose landing gear wheel well. This amendment is prompted by reports of fatigue cracks in the pressure web of the nose landing gear wheel well. The actions specified by this AD are intended to prevent cracking of the pressure web of the nose landing gear wheel well, which could result in loss of airplane pressurization.
AD 95-04-07 R2 · published Oct 6, 1999, effective Nov 10, 1999
McDonnell Douglas Model DC-10-10, -15, and -30 Airplanes, and KC-10A (Military) Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, and -30 airplanes, and KC-10A (military) airplanes, that currently requires inspections to determine the condition of the lockwires on the forward engine mount bolts and correction of any discrepancies found. That amendment also provides for termination of the inspections for some airplanes by installing retainers on the bolts. That AD was prompted by reports of stretched or broken lockwires on the forward engine mount bolts. The actions specified by that AD are intended to prevent broken lockwires, which could result in loosening of the engine mount bolts, and subsequent separation of the engine from the airplane. This amendment provides an additional optional terminating modification and clarification of the requirements of the previous optional terminating modification, and removes the reporting requirements for the repetitive inspections.
AD 99-21-09 · published Oct 6, 1999, effective Nov 10, 1999
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, - 201, -202, -301, -311, and -315 series airplanes, that currently requires a one-time inspection to detect chafing of electrical wires in the cable trough below the cabin floor; repair, if necessary; installation of additional tie-mounts and tie-wraps; and application of sealant to rivet heads. This amendment requires the accomplishment of these same actions on additional airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing of electrical wires, which could result in an uncommanded shutdown of an engine during flight.
AD 99-21-05 · published Oct 7, 1999, effective Nov 16, 1999
Fairchild Aircraft, Inc. Models SA226- T, SA226-T(B), SA226-AT, and SA226-TC Airplanes
This amendment supersedes Airworthiness Directive (AD) 77-25- 03, which currently requires repetitively inspecting for cracks on the landing gear actuator rod ends that are equipped with grease fittings, on Fairchild Aircraft, Inc. (Fairchild Aircraft) Models SA226-T, SA226- AT, and SA226-TC airplanes. AD 77-25-03 also requires replacing the landing gear actuator rod ends with an improved part either immediately or at a certain time period depending on the results of the inspections. Replacement of all six rod ends terminates the repetitive inspection requirements of AD 77-25-03. This AD is the result of failures of the landing gear rod ends on airplanes where the rod ends were replaced in accordance with AD 77-25-03. Fairchild has re-designed the landing gear rod ends as a result of these failures. This AD requires replacing all landing gear rod ends with these improved design parts on all SA226 series airplanes, including those manufactured since AD 77-25-03 was issued (i.e., the Model SA226-T(B) airplanes). The actions specified by this AD are intended to prevent failure of the landing gear actuator caused by cracks in the rod ends, which could result in the inability to lower the landing gear during a landing with consequent possible loss of control of the airplane.
AD 99-21-06 · published Oct 7, 1999, effective Nov 12, 1999
McDonnell Douglas Model DC-9-81, -82, - 83, and -87 Series Airplanes (MD-81, -82, -83, and -87), and Model MD- 88 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes (MD-81, -82, -83, and -87), and Model MD-88 airplanes, that currently requires visual or eddy current inspections to detect cracks of the actuator cylinder support brackets of the slat drive mechanism assembly, and replacement of any cracked brackets. This amendment continues to require repetitive eddy current inspection, adds an inspection requirement, and expands the area of inspection. This amendment also provides terminating action for the repetitive inspections. This amendment is prompted by reports indicating that additional cracking was found outside the original inspection area. The actions specified by this AD are intended to prevent inadvertent slat retraction in flight.
AD 99-21-07 · published Oct 7, 1999, effective Nov 12, 1999
McDonnell Douglas Model DC-9, DC-9-80, and C-9 (Military) Series Airplanes, and Model MD-88 Airplanes
This amendment supersedes two existing airworthiness directives (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that currently require installation of hydraulic line restrictors in the main landing gear (MLG), and modification or replacement of the left and right MLG hydraulic damper assemblies. This amendment requires an additional modification of the MLG hydraulic damper assemblies, or replacement of the MLG hydraulic damper assemblies with modified and reidentified hydraulic damper assemblies. This amendment is prompted by reports indicating that MLG hydraulic damper assemblies removed for overhaul had failed or damaged spring retainers, due to insufficient material thickness of the spring retainers. The actions specified by this AD are intended to prevent failure of the hydraulic damper assemblies of the MLG, which could result in vibration damage and collapse of the MLG.
AD 99-21-08 · published Oct 7, 1999, effective Nov 12, 1999
Raytheon (Beech) Model 400A Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A airplanes, that requires replacement of the fuel drain tube assembly in the aft fuselage with a new, modified assembly. This amendment is prompted by a report of chafing of the fuel tube assembly against the elevator control cable due to inadequate clearance between the components. The actions specified by this AD are intended to prevent chafing of the fuel drain tube assembly, which could result in fuel leakage from the fuel drain tube assembly and consequent risk of a fire.
AD 99-21-10 · published Oct 7, 1999, effective Nov 12, 1999
Boeing Model 727-100 and -100C Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100 and -100C series airplanes, that requires replacement of certain skin panels of the lower fuselage with non-bonded skin panels. This amendment is prompted by reports of corrosion of the skin panels of the lower fuselage on airplanes with hot-bonded doublers. The actions specified by this AD are intended to prevent degradation of the structural integrity of certain skin panels of the lower fuselage, which could result in loss of airplane pressurization.
AD 99-21-11 · published Oct 8, 1999, effective Nov 12, 1999
Bombardier Model CL-600-2B19 (Regional Jet Series 100) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires a one-time inspection to detect damage of the input connectors and wiring of the main and auxiliary power unit (APU) battery chargers, and corrective action, if necessary. This amendment also requires installation of secure connectors for the battery charger input connections. In addition, this amendment requires, for certain airplanes, either the installation of a resistor in the battery charger wiring, or the installation of new batteries with internal resistors. 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 increased risk of a short circuit and consequent electrical smoke or fire in the aft fuselage.
AD 99-21-12 · published Oct 8, 1999, effective Nov 12, 1999
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires a one-time visual inspection of the conduit pipe for distortion or repairs, and replacement of the conduit pipe with a new pipe, if necessary. This amendment also requires replacement of the cable assemblies to the fuel standby pumps with new cable assemblies that have improved sheathing protection. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent electrical arcing due to damaged fuel standby pump cable assemblies and conduit pipes, which could create a possible ignition source, and consequent fire hazard.
AD 99-21-15 · published Oct 8, 1999, effective Nov 12, 1999
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and - 500 series airplanes, that currently requires removal of the fuel boost pump wiring in the conduits of the wing and center fuel tanks; an inspection to detect damage of the wiring, and corrective action, if necessary; and eventual installation of Teflon sleeving over the electrical cable. This amendment expands the inspection requirement to include airplanes with fewer than 20,000 flight hours; requires additional repetitive inspections for all airplanes; reidentifies the requirement to install Teflon sleeving as a nonterminating action; and removes the requirement to report inspection results. This amendment is prompted by the FAA's determination that Model 737-100 through -500 series airplanes that are not affected by the current AD must also be protected against excessive wire chafing of the fuel boost pump wiring and that all Model 737-100 through -500 series airplanes must be repetitively inspected. The actions specified by this AD are intended to detect and correct chafing and prevent electrical arcing between the fuel boost pump wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank.
AD 99-21-16 · published Oct 8, 1999, effective Nov 12, 1999
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive replacements of the weight on wheels microswitch harness subassembly with a new microswitch harness subassembly. 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 a nose wheel shimmy, which could result in the collapse of the nose landing gear during takeoff or landing and possible injury to the flightcrew and passengers.
AD 99-21-17 · published Oct 13, 1999, effective Oct 28, 1999
Airbus Model A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A321 series airplanes. This action requires reinforcement of the fuselage structure between frames 62 and 64. 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 the loss of structural integrity of the rear part of the fuselage structure in the event of an undetected tail scrape during landing or takeoff.
AD 99-21-19 · published Oct 13, 1999, effective Nov 17, 1999
Airbus Model A319-131, A320-232 and - 233, and A321-131 and -231 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319-131, A320-232 and -233, and A321-131 and -231 series airplanes, that requires replacement of all titanium thrust links with steel thrust links. 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 titanium thrust links due to the life limit of the thrust links, which in combination with other failures, could result in the separation of an engine from the airplane.
AD 99-21-20 · published Oct 13, 1999, effective Nov 17, 1999
Dassault Model Falcon 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 series airplanes, that requires a detailed inspection for interference between the safety-lock hooks and upper cowls, and corrective action, if necessary. This amendment also requires modification of the attachment supports of the inner locking hooks; and a detailed inspection of the safety-lock hooks on the lower engine cowl for proper operation and for clearance between the outer edges of the upper and lower cowls; 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 unintended disengagement of the engine cowl hooks during ground maintenance, which could result in in-flight loss of an engine cowl from the airplane and possible damage to the airplane and persons or property on the ground.
AD 99-21-21 · published Oct 13, 1999, effective Nov 17, 1999
Airbus Model A310-300 and A300-600R Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310-300 and A300-600R series airplanes, that requires installation of a new cover assembly, associated new drain and vent pipework, and a new electrical harness on the trimmable horizontal stabilizer for the fuel tank water scavenge motive pump. 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 fuel leakage from the seal of the water scavenge pumps, which, if not corrected, could result in leakage of fuel into fuselage areas not designed for fuel, and consequent potential for fuel to be in contact with a fuel ignition source.
AD 99-21-22 · published Oct 13, 1999, effective Nov 17, 1999
Short Brothers Model SD3-30, SD3-60, SD3 SHERPA, and SD3-60 SHERPA Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3 SHERPA, and SD3-60 SHERPA series airplanes, that requires a visual inspection to detect corrosion of the shear decks and ribs of the left and right stub wings; follow-on corrective actions, if necessary; and drilling of new drain holes in the lower shear decks. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent corrosion of the stub wing shear decks and ribs, which could result in cracking or failure of the stub wing structure.
AD 99-21-23 · published Oct 13, 1999, effective Dec 3, 1999
Avions Mudry et Cie Model CAP 10B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Avions Mudry et Cie (Avions Mudry) Model CAP 10B airplanes. This AD requires restricting the entry speed for performing flick maneuvers to 97 knots. Inserting a copy of this AD into the Limitations Section of the CAP 10B flight manual is also required, along with fabricating and installing a placard (in the cockpit of the airplane within the pilot's clear view) that indicates this limitation. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to provide the flight information necessary to the pilot so that excessive speed is not used during aerobatic maneuvers, which could result in the wing separating from the airplane.
AD 99-21-18 · published Oct 18, 1999, effective Nov 22, 1999
Boeing Model 767 Series Airplanes Powered by Pratt & Whitney JT9D-7R4 Series Turbofan Engines or General Electric CF6-80A Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections to detect certain discrepancies of the cables, fittings, and pulleys of the engine thrust control cables; and repair, if necessary. For certain airplanes, this amendment also requires replacement of certain pulleys with new pulleys, and re-rigging of the engine thrust control cable. This amendment is prompted by reports of engine thrust control cable failures. The actions specified by this AD are intended to prevent such failures, which could result in a severe asymmetric thrust condition during landing, and consequent reduced controllability of the airplane.
AD 99-21-26 · published Oct 18, 1999, effective Nov 22, 1999
Raytheon (Beech) Model 400, 400A, 400T, and MU-300-10 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400, 400A, 400T, and MU-300-10 airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to provide pilots with special operating procedures during icing conditions. This amendment adds a requirement to modify the airplane ice protection system. This amendment also removes Model MU-300 airplanes from the applicability of the existing AD. This amendment is prompted by the development of a modification that will positively address the unsafe condition. The actions specified by this AD are intended to prevent uncommanded nose-down pitch at certain flap settings during icing conditions.
AD 99-21-27 · published Oct 18, 1999, effective Nov 22, 1999
Bombardier Model DHC-8-311 and -315 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-311 and -315 series airplanes, that currently requires replacement of the nitrogen cylinder assemblies that inflate the airplane's ditching dams with improved nitrogen cylinder assemblies. This amendment expands the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the ditching dams to inflate fully during an emergency water landing, which could result in water entering the airplane.
AD 99-21-28 · published Oct 18, 1999, effective Nov 22, 1999
Airbus Model A319, A320, A321, A330, and A340 Series Airplanes Equipped With AlliedSignal RIA-35B Instrument Landing System Receivers
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, A321, A330, and A340 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to require the flightcrew to discontinue use of any Instrument Landing System (ILS) receiver for which a certain caution message is displayed. It also requires, for certain airplanes, replacing any faulty ILS receiver with a new, serviceable, or modified unit, and provides for optional terminating action for the AFM revisions. This amendment requires accomplishment of the previous optional terminating action. This amendment is prompted by a pilot's report of errors in the glide slope deviation provided by an ILS receiver. The actions specified by this AD are intended to detect and correct faulty ILS receivers and to ensure that the flightcrew is advised of the potential hazard of performing ILS approaches using a localizer deviation from a faulty ILS receiver, and advised of the procedures necessary to address that hazard. An erroneous localizer deviation could result in a landing outside the lateral boundary of the runway.
AD 99-21-29 · published Oct 18, 1999, effective Nov 22, 1999
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires modification of the autopilot mode engagement/disengagement lever of the rudder artificial feel unit. 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 reduced controllability of the airplane due to the failure of the rudder artificial feel unit to properly disengage from autopilot mode during approach and landing.
AD 99-21-31 · published Oct 20, 1999, effective Nov 24, 1999
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 removing the control quadrant, securing the power lever cam screws with Loctite, and reinstalling the control quadrant. 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 cam screws of the engine power levers from backing out and interfering with the movement of the engine power levers, which could result in limited engine power, and consequent reduced controllability of the airplane.
AD 99-21-32 · published Oct 20, 1999, effective Nov 24, 1999
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires a one-time inspection to measure clearance and detect interference between the elevator cable pulley and the shroud frame of the ventral stairway, and modification of the shroud frame of the ventral stairway. This amendment is prompted by reports of pitch oscillation of several Model MD-90-30 series airplanes. The actions specified by this AD are intended to prevent interference between the elevator cable pulley and the shroud frame of the ventral stairway, which could result in pitch oscillation of the airplane, and consequent damage to the elevator cable pulley and reduced controllability of the airplane.
AD 99-21-33 · published Oct 20, 1999, effective Nov 4, 1999
Fokker Model F.27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.27 Mark 050 series airplanes. This action requires a one-time inspection to detect improper installation of countersunk screws used to attach the access panels to the bottom skin of the center wing; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct such improper installation, which could result in fatigue cracking of the bottom skin of the center wing and consequent reduced structural integrity of the airplane.
AD 99-22-02 · published Oct 20, 1999, effective Nov 24, 1999
Boeing Model 757-200PF Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 757-200PF series airplanes, that requires revising the Airplane Weight & Balance (W&B) Manual to prohibit operation of any airplane without side vertical restraints installed on the main cargo deck when carrying a particular pallet. This amendment also provides for optional terminating action for the Airplane W&B Manual revision. This amendment is prompted by reports indicating that some airplanes have been operated without side vertical restraints installed on the main cargo deck when carrying certain pallets. The actions specified by this AD are intended to prevent inadvertent movement of a cargo pallet during flight, which could result in an adverse center of gravity condition and consequent reduced controllability of the airplane.
AD 99-22-03 · published Oct 22, 1999, effective Nov 26, 1999
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive inspections to detect chafing on the fuel manifold drain hose and the adjacent access panel; and corrective actions, if necessary; and installation of a protective spiral wrap on the fuel manifold drain hose. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by reports of chafing between the fuel manifold drain hose and the access panel due to contact between the two components over time. The actions specified by this AD are intended to prevent chafing within the engine nacelle, which could result in flammable fluid leaking into a zone that contains ignition sources.
AD 99-22-04 · published Oct 22, 1999, effective Nov 26, 1999
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 series airplanes, that requires modification of the wiring of the emergency lighting 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 pilots from having full authority over the cabin emergency lights, which could result in delayed egress of the passengers and crew from the cabin during emergency evacuation.
AD 99-22-05 · published Oct 22, 1999, effective Nov 26, 1999
Short Brothers Model SD3-60 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes, that requires repetitive inspections of the elevator trim control cables for signs of wear damage or broken wires; replacement of damaged or broken cables with certain new cables; and replacement of all 7 x 7 cables with 7 x 19 cables. 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 elevator trim cable due to fatigue cracking, which if not corrected, could result in reduced controllability of the airplane.
AD 99-22-06 · published Oct 22, 1999, effective Nov 26, 1999
Construcciones Aeronauticas, S.A. (CASA), Model CN-235 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that currently requires repetitive eddy current inspections to detect fatigue cracks in the nose landing gear (NLG) turning tube, and replacement of cracked tubes. This amendment adds a requirement for the replacement of the existing NLG turning tube constructed of aluminum alloy with a new NLG turning tube made of steel; such replacement terminates the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking and failure of the NLG turning tube, which could result in reduced structural integrity of the NLG.
AD 99-22-07 · published Oct 22, 1999, effective Nov 26, 1999
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires a one-time inspection of the rail release pins and parachute pins of the escape slide/raft pack assembly for correct installation, 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 improper deployment of the escape slide/raft and blockage of the door in the event of an emergency evacuation.
AD 99-21-30 · published Oct 26, 1999, effective Nov 30, 1999
Raytheon Model Mitsubishi MU-300 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Model Mitsubishi MU-300 airplanes, that requires revising the Airplane Flight Manual (AFM) to provide pilots with certain operating procedures during icing conditions, and to limit the maximum flaps position for flight in icing conditions or landing after an icing encounter. The amendment also requires installing an ice detector, and accomplishing a corresponding AFM revision to address its operation. For certain airplanes, the amendment requires converting the airplane configuration or modifying the warning horn system of the landing gear; and revising the AFM to specify flaps 10 degrees as a normal landing flap configuration. The actions specified by this AD are intended to prevent uncommanded nose-down pitch at certain flap settings during icing conditions.
AD 99-22-08 · published Oct 26, 1999, effective Nov 30, 1999
McDonnell Douglas Model DC-9, DC-9-80 and C-9 (Military) Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80 and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires revising the wiring of the air conditioning pneumatic supply control, if applicable, and revising the wiring of the pneumatic augmentation valve. This amendment is prompted by a report indicating that the pneumatic augmentation valve may go fully open when an engine fails during initial climb prior to deactivation of the second segment climb switch. The actions specified by this AD are intended to prevent opening of the pneumatic augmentation valve, which could result in significant loss of thrust from the remaining engine and consequent inadequate initial climb performance of the airplane.
AD 99-22-09 · published Oct 26, 1999, effective Nov 10, 1999
Boeing Model 747-400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. This action requires an inspection of the crew rest area heat exchangers to detect deflection or interference with the flight control cables; and various follow-on actions. This action also requires replacement of certain nutplate attachment rivets that attach the heat exchangers to the airframe with stronger rivets. This amendment is prompted by a report of interference between insulation blankets adjacent to the heat exchangers and flight control cables. The actions specified in this AD are intended to prevent a reduction in maximum rudder and elevator surface deflection due to the separation of heat exchangers from the body frame, which could result in reduced controllability of the airplane.
AD 99-22-11 · published Oct 28, 1999, effective Dec 2, 1999
British Aerospace Model BAe 146 and Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires installation of modified roller sub- assemblies in both the main landing gear (MLG) door lock and the MLG uplock. 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 roller sub-assemblies, which could result in failure of the MLG to retract and lock after takeoff, or to deploy properly for landing.
AD 99-19-23 · published Oct 4, 1999, effective Oct 19, 1999
Eurocopter France Model EC 120B Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-19-23 which was sent previously to all known U.S. owners and operators of Eurocopter France Model EC 120B helicopters by individual letters. This AD requires, at specified time intervals, inspecting the engine coupling tube for cracks and replacing any cracked engine coupling tube with an airworthy engine coupling tube. This amendment is prompted by the discovery, during routine maintenance inspections, of three cracked engine coupling tubes caused by structural resonance. The actions specified by this AD are intended to detect a crack in the engine coupling tube which could result in coupling failure, loss of engine drive, and a subsequent forced landing.
AD 99-21-01 · published Oct 4, 1999, effective Oct 19, 1999
Eurocopter France Model SA-360C, SA- 365C, C1, and C2 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA-360C, SA-365C, C1, and C2 helicopters. This action requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. This condition if not corrected could result in loss of electrical continuity, which could cause loss of critical rotorcraft electrical systems and subsequent loss of control of the helicopter.
AD 99-21-13 · published Oct 6, 1999, effective Nov 10, 1999
Eurocopter France Model AS332C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS332C, L, and L1 helicopters, that requires inspecting and replacing certain bolts that secure the hoist arm lower fitting. This amendment is prompted by a report of a failure of the bolts that secure the hoist arm lower fitting during a factory load test. The actions specified by this AD are intended to prevent failure of the bolts that secure the hoist arm lower fitting, separation of components from the helicopter, impact with the main or tail rotor, and subsequent loss of control of the helicopter.
AD 99-19-22 · published Oct 8, 1999, effective Oct 25, 1999
Eurocopter Deutschland GMBH Model BO- 105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-19-22 which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GMBH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO- 105LS A-1 helicopters by individual letters. This AD requires, before further flight, creating a component log card or equivalent record and determining the age and number of flights on each tension-torsion (TT) strap. The AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter because of fatigue failure of the TT strap. The ECD Model MBB-BK 117 and the BO-105 helicopters use the same part- numbered TT strap. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
AD 99-21-14 · published Oct 8, 1999, effective Nov 12, 1999
Eurocopter France Model SA-360C, SA- 365C, C1, C2, SA-365N, N1, AS-365N2, and SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-360C, SA-365C, C1, C2, SA- 365N, N1, AS-365N2, and SA-366G1 helicopters, that requires inspecting and, if necessary, replacing certain circuit breakers. This amendment is prompted by the manufacturer discovering the loss of electrical continuity between the terminals of a circuit breaker. The actions specified by this AD are intended to prevent loss of electrical power, loss of instrumentation, and subsequent loss of control of the helicopter.
AD 99-21-24 · published Oct 14, 1999, effective Nov 18, 1999
Eurocopter France Model SA-365C, C1, C2, N, and N1; AS-365N2; and SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-365C, C1, C2, N, and N1; AS- 365N2; and SA-366G1 helicopters, that requires inspecting the tightening torque of the main rotor hub blade attach beam spherical thrust bearing bolts (bolts). This AD also requires either applying the specified torque or, if necessary, conducting a dye penetrant inspection for cracks in the metal components. Replacing the spherical thrust bearing (bearing) with an airworthy bearing is also required if a crack is found. This amendment is prompted by reports of cracks in the metal components of the bearing attachment joint. The actions specified by this AD are intended to prevent loosening of bearing bolts in flight, which may cause cracks in the metal components, failure of the bearing, and subsequent loss of control of the helicopter.
AD 99-21-25 · published Oct 14, 1999, effective Oct 29, 1999
Eurocopter France Model SE.3160, SA.315B, SA.316B, SA.316C, and SA.319B Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SE.3160, SA.315B, SA.316B, SA.316C, and SA.319B helicopters with a main gearbox (MGB), all part numbers, not modified in accordance with MOD 072241. This action requires, prior to further flight and thereafter prior to the first flight of each day, inspecting the MGB magnetic plug for metal particles. This AD also requires inspecting the MGB oil filter for metal particles. This amendment is prompted by the failure of a bevel wheel gear attachment bolt (bolt) during testing of an SA.315B MGB. The actions specified in this AD are intended to detect a condition that could cause bolt failure and damage to the MGB, resulting in loss of drive to the main rotor and subsequent loss of control of the helicopter.
AD 99-20-13 · published Oct 18, 1999, effective Nov 2, 1999
Eurocopter Canada Ltd. Model BO 105 LS A-3 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-20-13, which was sent previously to all known U.S. owners and operators of Eurocopter Canada Ltd. Model BO 105 LS A-3 helicopters by individual letters. This AD requires, before further flight, creating a component log card or equivalent record and determining the age and number of flights on each tension-torsion (TT) strap. The AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from a Eurocopter Deutschland GMBH Model MBB-BK 117 helicopter because of fatigue failure of the TT strap. The Model MBB-BK 117 and the Model BO 105 LS A-3 helicopters use the same part-numbered TT strap. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
AD 99-22-12 · published Oct 26, 1999, effective Nov 30, 1999
Eurocopter France Model AS332C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS332C, L, and L1 helicopters, that requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. The actions specified by this AD are intended to prevent loss of electrical continuity, which could cause loss of critical systems and subsequent loss of control of the helicopter.
AD 99-22-13 · published Oct 28, 1999, effective Dec 2, 1999
Bell Helicopter Textron Canada (BHTC) Model 407 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to BHTC Model 407 helicopters, that requires visually inspecting the vertical fin (fin) for reduced skin thickness; repairing or replacing the fin, if necessary; and identifying fins that have been inspected or repaired. This amendment is prompted by a report of an inboard skin damaged during production. The actions specified by this AD are intended to detect fin assemblies with reduced skin thickness which, if not corrected, reduce the strength of the skin and could lead to failure of the fin and loss of control of the helicopter.
AD 99-22-10 · published Oct 26, 1999, effective Dec 27, 1999
General Electric Aircraft Engines CF34 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain General Electric Aircraft Engines CF34 series turbofan engines, that establishes new life limits for certain high pressure compressor (HPC) spools, stage 9 HPC disks, and rear HPC spools. This amendment is prompted by a cyclic life analysis using increased stress levels resulting from manufacturing discrepancies. The actions specified by this AD are intended to prevent HPC spool and disk cracking, which could result in an uncontained engine failure and damage to the aircraft.
AD 99-22-14 · published Oct 29, 1999, effective Dec 28, 1999
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT8D-200 series turbofan engines, that currently requires installation of high pressure turbine (HPT) containment hardware. This amendment requires removing low pressure turbine (LPT)-to-exhaust case bolts and nuts and replacement with improved LPT-to-exhaust case bolts and nuts, and installation of improved HPT containment hardware. This amendment is prompted by uncontained HPT events resulting from HPT shaft fractures and LPT flange separations resulting from LPT blade failures. The actions specified by this AD are intended to prevent damage to the airplane resulting from uncontained engine debris following an HPT shaft fracture or an LPT blade failure.
