43 Airworthiness Directives: 32 airplane, 5 rotorcraft, 4 engine, 1 propeller, 1 appliance.
AD 99-25-04 · published Dec 3, 1999, effective Jan 7, 2000
Lockheed Model 382 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 382 series airplanes, that requires a one-time visual inspection of the under floor to ring fittings at fuselage station 817E to verify installation of the correct sized fasteners; and follow-on corrective actions, if necessary. This amendment is prompted by notification from the manufacturer indicating that during production incorrect sized fasteners were installed on the under floor to ring fittings at fuselage station 817E. The actions specified by this AD are intended to prevent fatigue cracking of the fastener holes and adjacent fuselage structure due to installation of the incorrect sized fasteners, which could result in reduced structural integrity of the airplane.
AD 99-25-06 · published Dec 8, 1999, effective Jan 12, 2000
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires a one-time inspection of the bottom aft roller of the main baggage-bay door structure for cracking or damage to the sub-frame; repetitive operational tests to determine if the counter- balance motor functions properly; 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 sub-frame damage, which, if left undetected, could cause rapid decompression of the airplane and consequent injury to passengers and crew.
AD 99-25-07 · published Dec 8, 1999, effective Dec 23, 1999
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 a one-time inspection of the wear indicator pins to determine the level of wear of the main brake assemblies of the main landing gear (MLG), and corrective actions, if necessary. This action also requires modification of the main brake assemblies of the MLG, and incorporation of specified wear limits into the maintenance inspection program. This amendment is prompted by in-service reports of brake deterioration caused by thermal oxidation of the carbon disks of certain BFGoodrich main brake assemblies. The actions specified in this AD are intended to prevent thermal oxidation of the main brake assemblies, which could result in deterioration of the MLG brakes, and consequent reduced braking performance.
AD 99-25-09 · published Dec 8, 1999, effective Jan 12, 2000
Dassault Model Mystere-Falcon 50 and 900 Series Airplanes, Falcon 900EX Series Airplanes, and Falcon 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 50 and 900 series airplanes, Falcon 900EX series airplanes, and Falcon 2000 series airplanes, that requires revising the Airplane Flight Manual to provide the flight crew with certain instructions associated with the onset of stall warning. This amendment also requires repetitive inspections to detect discrepancies of the hinge pin assemblies of the rear horizontal stabilizer, and corrective actions, if necessary. For certain airplanes, this amendment also requires replacement of the hinge pin assemblies with new, improved 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 excessive movement and consequent deformation of the hinge pin assemblies of the rear horizontal stabilizer, which could result in flutter and possible failure of the rear horizontal stabilizer.
AD 99-25-10 · published Dec 8, 1999, effective Jan 12, 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 a one-time inspection of the forward engine mount assembly of the left and right engines to verify that the part number on each assembly is correct; re-identification of the forward engine mount assembly; and follow-on 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 structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane.
AD 98-25-10 R1 · published Dec 10, 1999, effective Jan 14, 2000
Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH Seat Restraint Systems
This amendment revises an existing airworthiness directive (AD), applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems installed on, but not limited to, Beech Aircraft Corp., Bell Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft, that currently requires inspecting to ensure the locking mechanism is engaging properly and replacing the buckle-half of the seat restraint system, if necessary. This amendment will allow an owner/operator (pilot) to determine if the locking mechanism is engaging properly and will require replacing the buckle-half of the seat restraint system, if necessary. This amendment is prompted by a determination made by the FAA that pilots may perform the one-time check of the locking mechanism and that only affected seat restraint systems manufactured between March 1997 and November 1998 must be checked. The actions specified by this AD are intended to prevent failure of the seat restraint system due to the buckle assembly locking mechanism not engaging properly, which could result in the seat restraint system failing to properly secure the occupant during turbulence or landing.
AD 99-11-05 · published Dec 13, 1999, effective Jun 28, 1999
Boeing Model 737 Series Airplanes
This document corrects and clarifies information in an existing airworthiness directive (AD) that applies to all Boeing Model 737 series airplanes. That AD currently requires repetitive displacement tests of the secondary slide in the dual concentric servo valve of the power control unit (PCU) for the rudder, and replacement of the valve assembly with a modified valve assembly, if necessary. This document corrects certain PCU part and serial numbers and clarifies that PCU's with certain other serial numbers are not required to comply with the requirements of this AD. This correction is necessary to prevent failure of the secondary slide and consequent rudder hardover and reduced controllability of the airplane.
AD 99-25-14 · published Dec 13, 1999, effective Jan 18, 2000
McDonnell Douglas Model MD-11 and MD- 11F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that requires a one-time inspection to determine if metallic transitions are installed on wire harnesses of the tail tank fuel transfer pumps, and to determine if damaged wires are present; and repair, if necessary. This amendment also would require repetitive inspections of the repaired area; and a permanent modification of the wire harnesses if metallic transitions are not installed, which terminates the repetitive inspections. This amendment is prompted by a report of chafing and damage to a wire harness of a tail tank fuel transfer pump. The actions specified by this AD are intended to prevent wire chafing and damage, which could result in an inoperative fuel transfer pump and/or an increased risk of a fire or explosion from a fuel leak.
AD 99-25-15 · published Dec 13, 1999, effective Jan 18, 2000
Airbus Model A300, A310, A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A310, A300-600 series airplanes, that currently requires a one-time operational test and repetitive functional tests of the free fall control mechanism of the landing gear to ensure proper release of the main landing gear (MLG), and corrective action, if necessary. It also requires eventual modification of the free fall control mechanism of the landing gear, which constitutes terminating action for the repetitive functional tests. This amendment requires, for certain airplanes, that the modification of the free fall control mechanism of the landing gear be accomplished in accordance with a corrected version of the manufacturer's service bulletin. 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 malfunction of the free fall control mechanism of the landing gear, which could result in the inability to extend the MLG in the event of failure of the hydraulic extension system.
AD 99-25-16 · published Dec 13, 1999, effective Dec 28, 1999
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires the removal of tapered nylon shims from under the seat rails from fuselage station 14025 to the aft end of the seat rails, and installation of shorter bolts. This action also requires the installation of shims under galleys and partition walls for certain configurations. 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 failure of the seat rail attachments due to shim material aging, which could result in detachment of the seats and consequent injury to the airplane occupants.
AD 99-26-01 · published Dec 13, 1999, effective Jan 12, 2000
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection to verify the tension values of the aileron control cables of the left-and right-hand wings, and corrective actions, if necessary. This action also requires either replacement of the aileron control cables with new, improved aileron control cables, or replacement of the aileron control cables with new, improved aileron control cables and modification of the pulley bracket on the rear face of the bulkhead at frame station 3100. The FAA is issuing this AD in response to mandatory continuing airworthiness information issued by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interference between the turnbuckles of the aileron control cables and the lightening holes, which could result in binding of the aileron control cables and consequent reduced controllability of the airplane.
AD 99-26-05 · published Dec 14, 1999, effective Jan 13, 2000
The New Piper Aircraft, Inc. Models PA- 25, PA-25-235, PA-25-260, PA-28S-160, PA-28S-180, PA-32S-300, PA-28- 151, and PA-28-161 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to the following airplanes that incorporate certain Facet (manufactured by the Purolator Products Company) induction air filters:
AD 99-26-02 · published Dec 20, 1999, effective Jan 24, 2000
Boeing Model 747-400 and 767 Series Airplanes Powered by Pratt & Whitney PW4000 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and 767 series airplanes, that requires replacement of the existing deactivation pin, pin bushing, and insert flange on each thrust reverser half, with new, improved components. This amendment is prompted by reports of partial deployment of deactivated thrust reversers during landing. The actions specified by this AD are intended to prevent failure of the thrust reverser deactivation pins, which could result in deployment of the thrust reverser in flight and consequent reduced controllability of the airplane.
AD 99-26-07 · published Dec 20, 1999, effective Jan 24, 2000
Boeing Model 737-100, -200, and -200C Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, and -200C series airplanes, that currently requires periodic inspections to detect missing nuts and/or damaged secondary support hardware adjacent to the aft engine mount, and replacement, if necessary. That AD also provides for optional terminating action for certain inspections and a torque check. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by the FAA's determination that the repetitive inspections required by the existing AD may not be providing the degree of safety assurance necessary for the transport airplane fleet. The actions specified by this AD are intended to prevent failure of the secondary support to sustain engine loads in the event of failure of the aft engine mount cone bolt, which could result in the separation of the engine from the wing.
AD 99-26-09 · published Dec 20, 1999, effective Jan 24, 2000
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections to ensure the proper condition of the engine thrust link components, and follow-on corrective action, if necessary; and replacement of the end cap assembly with an improved assembly. Such replacement, when accomplished, terminates the repetitive inspections. This amendment is prompted by a report of fatigue cracking of end cap bolts caused by improper installation. The actions specified by this AD are intended to prevent failure of the end cap assembly, which could lead to separation of the engine from the airplane in the event of a primary thrust linkage failure.
AD 99-26-10 · published Dec 20, 1999, effective Jan 24, 2000
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, and -800 series airplanes, that requires installation of a drain at each of the number 2 window frame assemblies in the airplane. This amendment is prompted by reports that flight deck emergency exits (number 2 windows) were found frozen shut after landing. The actions specified by this AD are intended to prevent water accumulation in the lower corners of the flight deck emergency exits (number 2 windows), which can freeze and prevent the exits from being used during an emergency evacuation.
AD 99-26-11 · published Dec 20, 1999, effective Jan 24, 2000
Bombardier Model DHC-7 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-7 series airplanes, that requires a one-time visual inspection to detect corrosion on the upper half of the lower longerons on the inboard nacelles; and corrective actions, if necessary. This AD also requires modification of the upper and lower longeron halves. 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 corrosion in the upper halves of the left and right hand lower longerons on the inboard nacelles, which could result in a landing gear failure.
AD 99-26-12 · published Dec 20, 1999, effective Jan 24, 2000
Airbus Model A330-301, -321, -322 Series Airplanes, and Model A340-211, -212, -213, -311, -312, and -313 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330-301, -321, and -322 series airplanes, and Model A340-211, -212, -213, -311, -312, and -313 series airplanes, that requires repetitive replacements of the yaw damper actuator installed on active position with a new or overhauled yaw damper actuator. 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 hydraulic leakage from the yaw damper actuator installed on active position due to premature wear of the dynamic seals between the actuator piston and the piston bearing. Hydraulic leakage could lead to complete loss of the green hydraulic circuit, which could result in reduced controllability of the airplane.
AD 99-26-08 · published Dec 21, 1999, effective Jan 25, 2000
Airbus Model A310 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the rudder trim switch in the flight compartment with a new switch having a longer shaft; modification of wiring in panel 408VU; and replacement of the rudder trim control knob with an improved new knob. 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 inadvertent and uncommanded rudder trim activation, which could result in yaw and roll excursions and consequent reduced controllability of the airplane.
AD 99-26-15 · published Dec 21, 1999, effective Jan 25, 2000
Airbus Model A300 B2 and B4 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that requires repetitive inspections to detect cracking of the inner skin panel of the longitudinal lap joint; and repair, or modification and new repetitive inspections, 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 detect and correct stress corrosion cracking of the inner skin panel of the longitudinal lap joint, which could result in rapid depressurization of the airplane.
AD 99-25-13 · published Dec 22, 1999, effective Dec 23, 1999
Boeing Model 777-200 and -300 Series Airplanes
This document corrects two typographical errors that appeared in airworthiness directive (AD) 99-25-13 that applies to all Boeing Model 777-200 and -300 series airplanes. That AD currently requires revising the Limitations Section of the Airplane Flight Manual to prohibit the dispatch of certain airplanes under certain conditions. That AD also requires repetitive inspections to ensure correct operation of the backup generators; and, for certain airplanes, a one- time inspection to detect damage of the engine external gearbox; and corrective actions, if necessary. This document corrects incorrect paragraph references. This correction is necessary to ensure that operators accomplish the appropriate requirements of the AD.
AD 99-25-13 C1 · published Dec 22, 1999, effective Dec 23, 1999
The Boeing Company Airplanes
This document corrects two typographical errors that appeared in airworthiness directive (AD) 99-25-13 that applies to all Boeing Model 777-200 and -300 series airplanes. That AD currently requires revising the Limitations Section of the Airplane Flight Manual to prohibit the dispatch of certain airplanes under certain conditions. That AD also requires repetitive inspections to ensure correct operation of the backup generators; and, for certain airplanes, a one-time inspection to detect damage of the engine external gearbox; and corrective actions, if necessary. This document corrects incorrect paragraph references. This correction is necessary to ensure that operators accomplish the appropriate requirements of the AD.
AD 99-24-04 · published Dec 27, 1999, effective Dec 27, 1999
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. That AD currently requires a one-time visual inspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective actions, if necessary. This document corrects a typographical error in a service bulletin reference. This correction is necessary to ensure that the appropriate service information is used to accomplish the AD.
AD 99-24-04 C1 · published Dec 27, 1999, effective Dec 27, 1999
The Boeing Company Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. That AD currently requires a one-time visual inspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective actions, if necessary. This document corrects a typographical error in a service bulletin reference. This correction is necessary to ensure that the appropriate service information is used to accomplish the AD. \n\n\tThe incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of December 27, 1999. (64 FR 63187, November 19, 1999).
AD 99-25-11 · published Dec 28, 1999, effective Feb 1, 2000
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 series airplanes and certain British Aerospace Model Avro 146-RJ series airplanes, that requires repetitive eddy current inspections to detect fatigue cracking along the face of the retraction attachment boss in the nose landing gear sidewall; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil aviation authority. The actions specified by this AD are intended to detect and correct fatigue cracking along the face of the retraction attachment boss in the nose landing gear sidewall, which could result in premature extension of the nose landing gear or depressurization of the airplane.
AD 99-26-16 · published Dec 28, 1999, effective Feb 1, 2000
Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL- 604) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600- 2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes, that requires, for certain airplanes, removing the hydraulic tube assemblies from the main landing gear (MLG) bay, installing new re-routed hydraulic tube assemblies, and repositioning a fuel line, as applicable. For certain other airplanes, this amendment requires a general visual inspection to determine the routing of certain hydraulic and fuel lines, and repair, 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 damage to hydraulic and fuel lines resulting from failure of an MLG, which could cause a fire in the MLG wheel well.
AD 99-26-17 · published Dec 28, 1999, effective Feb 1, 2000
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 modification of the engine intake ducts to provide new cable routes and improved contamination protection of connectors on the engine intake de-icing 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 chafing and subsequent damage to the engine intake de-icing system wiring, and contamination of electrical connectors and plugs. Damage to system wiring or contamination of the electrical connectors or plugs could result in loss of engine intake de-icing capability, accretion of ice in the intake duct, ice ingestion, and consequent engine flameout.
AD 99-26-18 · published Dec 28, 1999, effective Feb 1, 2000
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 repetitive inspections to detect loose or migrated levers of the elevator cable tension regulators, and replacement of the regulator assembly with a new assembly, 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 detect and correct loose or migrated regulator levers of the elevator cable tension regulators, which could result in reduced controllability of the airplane.
AD 99-26-19 · published Dec 28, 1999, effective Feb 14, 2000
The New Piper Aircraft, Inc. J-2 Series Airplanes That Are Equipped With Wing Lift Struts
This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) J-2 series airplanes equipped with wing lift struts. This AD requires repetitively inspecting the wing lift struts for dents and corrosion and the wing lift strut forks for cracks; replacing any strut found with corrosion or dents, or forks with cracks; and repetitively replacing the wing lift strut forks. This AD also requires incorporating a ``NO STEP'' placard on the lift strut. This AD is the result of the Federal Aviation Administration (FAA) inadvertently omitting the J-2 series airplanes from the applicability of AD 99-01-05. The actions specified by this AD are intended to prevent in-flight separation of the wing from the airplane caused by wing lift struts with dents or corrosion or wing lift forks with cracks, which could result in loss of control of the airplane.
AD 99-26-22 · published Dec 28, 1999, effective Feb 1, 2000
Airbus Model A319 and A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A320 series airplanes, that requires repetitive inspections to detect cracking and delamination of the containers in which the off-wing emergency evacuation slides are stored, and corrective actions, if necessary. The AD also requires eventual modifications of the slides, which terminates the requirement for 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 the loss of the escape slides during flight, which could make the emergency exits located over each wing unusable and result in damage to the fuselage.
AD 99-27-02 · published Dec 29, 1999, effective Jan 21, 2000
Cessna Aircraft Company 170, 172, 175, and 177 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) 170, 172, 175, and 177 series airplanes. This AD requires replacing certain fuel selector valve cams or fuel selector valves that Cessna shipped from December 6, 1998, through May 10, 1999, and prevents the future installation of these fuel selector valve cams or fuel selector valves. This AD allows the pilot to check the logbooks to determine whether one of these fuel selector valve cams or fuel selector valves is installed. This AD results from reports from Cessna that fuel selector valve cams and fuel selector valves were manufactured with control shafts that will not allow both tanks to supply fuel to the engine in certain situations. The actions specified by this AD are intended to prevent an inadequate supply of fuel from reaching the engine because of a fuel selector valve cam or fuel selector valve. This could result in an emergency landing or loss of control of the airplane.
AD 99-27-03 · published Dec 29, 1999, effective Jan 13, 2000
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires repetitive inspections of the connections between certain ribs and stringers of the wing skins to detect loose or missing rivets or gaps, and corrective actions, if necessary. This action also requires eventual modification of the rib-stringer connection, which terminates the repetitive inspections. 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 fatigue cracking in the skin and stringers, which could result in reduced structural integrity of the wings.
AD 99-22-01 · published Dec 2, 1999, effective Dec 17, 1999
Eurocopter Deutschland GmbH Model EC135 P1 and T1 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-22-01, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and T1 helicopters by individual letters. This AD requires, before further flight and at specified time intervals until a modified tail boom connecting frame flange (frame flange) is installed, inspecting and replacing, if necessary, the frame flange. This AD also requires, within 7 days, installing an additional bearing support on the frame flange. Thereafter, this AD requires visually inspecting the frame flange for cracks or misalignment of the slippage marks at specified time intervals. This amendment is prompted by the discovery of a crack in the frame flange at the attachment points of the tail rotor drive shaft bearing support. The actions specified by this AD are intended to prevent a fracture of the bearing frame flange, failure of the tail rotor drive shaft, and subsequent loss of control of the helicopter.
AD 99-25-12 · published Dec 7, 1999, effective Jan 11, 2000
California Department of Forestry, Overseas Aircraft Support Inc, San Joaquin Helicopters, Smith Helicopters, Southwest Florida Aviation International, Arrow Falcon Exporters Inc., AST Inc., Bell Helicopter Textron Inc., Hagglund Helicopters LLC, International Helicopters Inc., Richards Heavylift Helo Inc., Robinson Air Crane Inc., Rotorcraft Development Corporation, Sout
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron (Bell)-manufactured Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters; and Southwest Florida Aviation SW204, SW204HP, SW205, and SW205A-1 helicopters, that currently requires modification and inspections of the tailboom vertical fin spar (vertical fin spar). This amendment requires the same modification and inspections plus two additional inspections and replacement of the vertical fin spar. This amendment is prompted by 6 accidents, 2 of which involved fatalities, involving fatigue cracks in the vertical fin spar that have occurred since the issuance of AD 97-20-09. The actions specified by this AD are intended to prevent in-flight failure of the vertical fin spar and subsequent loss of control of the helicopter.
AD 99-26-13 · published Dec 20, 1999, effective Jan 4, 2000
Agusta S.p.A. Model A109A and A109A II Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109A and A109A II helicopters, that currently requires inspecting each tail rotor blade (blade) for a crack and replacing any cracked blade. This amendment requires, before further flight, inspecting any blade with 400 or more hours time-in- service (TIS) for a crack and replacing any cracked blade. This amendment is prompted by another report of a cracked blade since the issuance of the existing AD. Two of the three occurrences of cracked blades involved the loss of the tail rotor and 90-degree gearbox. The actions specified by this AD are intended to prevent fatigue failure of the blade, loss of the tail rotor, and subsequent loss of control of the helicopter.
AD 99-26-14 · published Dec 20, 1999, effective Jan 4, 2000
Agusta S.p.A. Model AB412 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Agusta S.p.A. Model AB412 helicopters. This action requires removing and replacing certain main rotor yokes with airworthy main rotor yokes before further flight. This amendment is prompted by the fatigue failure of a main rotor yoke (yoke). Fatigue analysis indicates that certain yokes are on the low end of the manufacturer's tolerance for thickness and do not have the desired margin of safety. This condition, if not corrected, could result in fatigue failure of the yoke, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 99-25-03 · published Dec 3, 1999, effective Jan 7, 2000
International Aero Engines AG V2500-A1 Series Turbofan Engines
This amendment supersedes two airworthiness directives (ADs) that apply to International Aero Engines AG (IAE) V2500-A1 series turbofan engines. The first superseded AD, AD 98-20-18, currently requires removal from service of affected high pressure turbine (HPT) disks, identified by part number and serial number in the applicability paragraph of that AD, and replacement with a serviceable part. The second superseded AD, AD 99-05-05, requires initial and repetitive inspections of certain HPT stage 1 and stage 2 disks utilizing an improved ultrasonic method when the disks are exposed during a normal shop visit, and if a subsurface anomaly is found, removal from service and replacement with a serviceable part. This supersedure requires the initial inspection mandated by AD 99-05-05 to be completed at the next shop visit regardless of the planned maintenance or the reason for shop removal. The repetitive inspection interval is redefined to eliminate the cyclic limit and thus be less restrictive. This superseding action is prompted by results from investigations subsequent to the publication of AD 98-20-18 that have revealed that the HPT disks affected by that AD are part of the population addressed by AD 99-05- 05. These HPT disks can be safely reintroduced into service after completing the initial inspection requirements mandated by this proposed AD. This supersedure is also prompted by further analysis that indicates a reduction in risk if the initial inspection required by AD 99-05-05 is completed sooner and the subsequent required inspections can be redefined to eliminate the cyclic limit, thereby creating less burden on operators. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure and damage to the airplane.
AD 99-26-06 · published Dec 21, 1999, effective Feb 22, 2000
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that requires initial and repetitive fluorescent magnetic particle inspections or fluorescent penetrant inspections of the combustion chamber outer case (CCOC) for cracks, and, if necessary, replacement with serviceable parts. Also, this AD requires a one-time boss material verification, and, if necessary, replacement with serviceable parts. Finally, this AD requires replacement of CCOCs with welded-on bosses with improved, one-piece CCOCs. Installation of the one-piece CCOC constitutes terminating action to the inspection requirements of this AD. This amendment is prompted by a report of an uncontained engine failure caused by fatigue cracks originating at the weld joining the drain boss to the CCOC. The actions specified by this AD are intended to prevent CCOC cracks, which could result in an uncontained engine failure and damage to the airplane.
AD 99-27-01 · published Dec 29, 1999, effective Feb 2, 2000
Pratt & Whitney JT8D-209, -217, -217A, -217C, and -219 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and - 219 series turbofan engines, that requires inspection of the 3rd stage and 4th stage low pressure turbine (LPT) blades for shroud notch wear and replacement of the blade if wear limits are exceeded. This amendment is prompted by a report of an uncontained blade failure. The actions specified by this AD are intended to prevent an uncontained blade failure that could result in damage to the airplane.
AD 99-27-04 · published Dec 29, 1999, effective Feb 28, 2000
Rolls-Royce Limited Dart Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Rolls-Royce Limited Dart series turboprop engines. This amendment requires a one-time visual inspection of the interior of the switch to determine the type of low torque switch, and removal from service of unapproved Klixon low torque switches and replacement with serviceable parts. This amendment is prompted by the discovery of unapproved low torque switches in fleet operation. The actions specified by this AD are intended to prevent possible low torque switch failure, which could result in failure of a propeller to auto-feather following an engine power loss, resulting in possible loss of control of the airplane due to high asymmetric drag.
AD 99-25-05 · published Dec 3, 1999, effective Dec 20, 1999
Hartzell Propeller, Inc. Model HD-E6C- 3( ) Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller, Inc., Model HD-E6C-3( ) series propellers, installed on Fairchild Dornier 328-110 series and 328-120 series airplanes. This action supersedes telegraphic AD T99-06-51 that currently requires initial and repetitive inspections of the propeller hub for cracks or grease leaks, and replacement of the hub if any cracks are found. This amendment requires an initial and repetitive inspections of Hartzell propeller hub, part number (P/N) D-5108-1, for cracks or grease leaks, replacement of the hub if any cracks are found, and allows the installation of propeller hub, P/N D-5108-5, as a terminating action for the inspection requirements. This amendment is prompted by the addition of propeller hub P/N D-5108-5 as a terminating action for the inspection requirements and by the removal of the inspection requirements for Hartzell propeller hub, P/N D-5108-5. The actions specified by this AD are intended to prevent severe vibration due to cracks in the propeller hub that could result in propeller blade loss, loss of control, and possible damage to the airplane.
AD 99-23-22 R1 · published Dec 16, 1999, effective Nov 29, 1999
Transport Category Aircraft Appliances
This amendment revises an existing airworthiness directive (AD), applicable to various transport category airplanes equipped with certain Mode "C" transponder(s) with single Gillham code altitude input. That AD currently requires repetitive tests to detect discrepancies of the Mode "C" transponder(s), air data computer, and certain wiring connections; and corrective actions, if necessary. The existing AD is prompted by reports that, during level flight, the Traffic Alert Collision Avoidance System (TCAS II) issued false advisories that directed the flightcrew to change course and either climb or descend. The actions specified by that AD are intended to prevent such false advisories due to inaccurate airplane altitude reporting, which could result in the flightcrew deviating the airplane from its assigned flight path and a possible mid-air collision. This new action revises certain compliance times and limits the applicability of the existing AD.
