44 Airworthiness Directives: 33 airplane, 8 rotorcraft, 2 engine, 1 propeller.
AD 99-16-02 · published Aug 2, 1999, effective Sep 7, 1999
British Aerospace Model BAC 1-11 200 and 400 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently limits the number of operations at increased cabin pressure differential, and requires repetitive structural inspections for cracking of the fuselage, and repair or replacement of parts, if necessary. This amendment requires additional repetitive inspections for cracking of the fuselage. This amendment is prompted by the determination that airplanes operating at increased cabin pressure differential are more likely to develop fatigue cracking earlier in their service lives than those airplanes operating at normal cabin differential pressures. The actions specified by this AD are intended to detect and correct fatigue cracking of the airplane fuselage, which could result in reduced structural integrity of the airplane.
AD 99-16-03 · published Aug 2, 1999, effective Sep 7, 1999
Learjet Model 23, 24, 25, 28, 29, 31, 55, and 60 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 23, 24, 25, 28, 29, 31, 55, and 60 series airplanes, that requires a one-time detailed visual inspection of the electrical wire leads of the horizontal stabilizer anti-ice system to verify that the numbers on the wire leads correctly correspond to the numbers on the connected airframe wiring; installation of a wire ID strap on the left-and right-hand sides of each terminal block; and installation of a warning placard. This amendment is prompted by a report of severe flight control buffeting of a Learjet Model 55 series airplane due to a malfunction of the horizontal stabilizer anti-ice system. The actions specified by this AD are intended to prevent undetected accretion of ice on the leading edge of the horizontal stabilizer, which could result in the loss of pitch control and consequent reduced controllability of the airplane.
AD 99-16-04 · published Aug 2, 1999, effective Sep 7, 1999
Bombardier Inc. Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-215-1A10 and CL-215-6B11 series airplanes, that currently requires repetitive inspections to detect cracking on certain wing to fuselage frame-angles, and repair, if necessary. This amendment would continue to require the same inspections. This amendment is prompted by an adverse comment received in response to the existing amendment. The actions specified by this AD are intended to detect and correct cracking in the wing to fuselage frame-angles, which could result in reduced structural integrity of the airframe.
AD 99-16-05 · published Aug 3, 1999, effective Sep 7, 1999
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Saab Model SAAB 2000 series airplanes, that requires repetitive inspections for excessive wear of the aileron control cables, cable guides, and cable pulleys located at the rear wing spars; and corrective actions, if necessary. This amendment also requires repetitive replacement of the control cables and cable guides with new or serviceable components. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness. The actions specified by this AD are intended to detect and correct excessive wear on the aileron control cables, cable guides, and cable pulleys located at the rear wing spars, which could result in broken aileron control cables and consequent reduced controllability of the airplane.
AD 99-16-06 · published Aug 4, 1999, effective Sep 24, 1999
The New Piper Aircraft, Inc. Model PA- 46-350P Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) Model PA-46- 350P airplanes. This AD requires installing reinforcement plates to the wing forward and aft attach fittings. This AD is the result of a report that sheet steel material that is below design strength standards may have been utilized on the wing attach fittings on the Model PA-46-350P airplanes manufactured since January 1995. The actions specified by this AD are intended to prevent structural failure of the wing attach fittings caused by the utilization of substandard material, which could result in the wing separating from the airplane with consequent loss of control.
AD 99-16-07 · published Aug 9, 1999, effective Sep 13, 1999
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections to detect cracked or broken support brackets of the upper wing-to-fuselage fairings, and replacement of any discrepant support brackets with new brackets. This amendment also requires replacement of the fairing seals with new, improved seals; modification of the fairing panels; and installation of new bulkheads; which constitutes 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 prevent reduced structural integrity of the fairing support brackets, which could result in loss of the wing-to-fuselage fairings during flight, and consequent structural damage to the airplane.
AD 99-16-08 · published Aug 9, 1999, effective Aug 24, 1999
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 repetitive inspections of the doubler on the upper rudder pedal cover to determine whether it is securely bonded to the upper rudder pedal cover, and corrective action, if necessary. For airplanes on which the doubler is securely attached to the upper rudder pedal cover, this AD also provides for installation of two rivets to retain the doubler, as an optional terminating action for the repetitive inspections. This amendment is prompted by reports that a disbonded doubler interfered with rudder pedal movement. The actions specified in this AD are intended to detect and correct disbonding of the doubler on the upper rudder pedal cover, which could result in restricted rudder pedal movement and reduced controllability of the airplane.
AD 99-16-10 · published Aug 9, 1999, effective Aug 24, 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 repetitive inspections of the E-42 satellite communications (SATCOM) rack and fuselage (supporting) structure to detect fatigue cracking of the area surrounding the fastener holes, and to detect broken or missing fasteners; and corrective actions, if necessary. This amendment is prompted by reports indicating that fatigue cracking and broken and/or missing fasteners were found on the E-42 SATCOM equipment rack structure that attaches to the fuselage structure. The actions specified in this AD are intended to detect and repair fatigue cracking of the E-42 SATCOM rack and its supporting structure, which could result in the SATCOM equipment falling from the rack, loss of SATCOM capabilities, injury to passengers, and reduced controllability of the airplane.
AD 99-16-11 · published Aug 9, 1999, effective Aug 24, 1999
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 a test of the squib circuit ground studs of the engine fire extinguisher bottles to measure the resistance, and repair or replacement of the ground stud with a new ground stud, if necessary. This amendment is prompted by reports of improper grounding of the squib circuit. Such a condition would prevent the engine fire extinguisher bottle from discharging when commanded, which could result in the inability to extinguish an engine fire.
AD 99-16-12 · published Aug 9, 1999, effective Sep 27, 1999
Raytheon Aircraft Company Model Beech 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model Beech 1900D airplanes that are equipped with the electric elevator trim option. This AD requires installing electric elevator trim servo covers. This AD is the result of reports of the affected airplanes leaving the factory without electric elevator trim servo covers installed. If the covers are not installed, moisture could freeze on parts of the electric actuator. The actions specified by this AD are intended to prevent failure of the electric elevator trim and difficulty operating the manual elevator trim caused by moisture freezing on parts of the electric actuator installation, which would result in the pilot having to apply constant pressure to the control wheel during flight.
AD 99-16-14 · published Aug 9, 1999, effective Aug 24, 1999
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300, A310, and A300-600 series airplanes. This action requires a one-time inspection of the autopilot systems for proper engagement to determine if the main electro valve electrical connectors of the yaw, roll, and pitch autopilot actuators are correctly installed; 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 in this AD are intended to prevent erratic movements of the ailerons, elevator, and/or rudder that are commanded by discrepant autopilot actuators, which could result in reduced controllability of the airplane.
AD 99-17-01 · published Aug 13, 1999, effective Oct 1, 1999
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC- 12/45 airplanes. This AD requires replacing all flap drive shafts with flap drive shafts of improved design, installing additional gaskets on the power drive unit, and modifying the attachment and supporting hardware. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the flap drive shafts from corroding to the point where the flexible shafts in the flap drive system rupture, which could result in the inability to utilize the flap system with reduced airplane control.
AD 99-17-02 · published Aug 13, 1999, effective Sep 17, 1999
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires repetitive inspections of the safety spring wear plate doublers attached to the auxiliary power unit (APU) firewall, measurement of wear of the doublers, and follow-on actions, if necessary. For certain airplanes, this amendment also requires a one-time inspection to detect improper clearance between the safety spring wear plate doubler and the APU firewall, and corrective action, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports indicating that excessive wear was found on the safety spring wear plate doublers on the APU firewall of Boeing Model 777 series airplanes. The actions specified by this AD are intended to detect and correct wear of the safety spring wear plate doublers on the APU firewall, which could result in a hole in the APU firewall, and consequent decreased fire protection capability.
AD 99-17-05 · published Aug 17, 1999, effective Sep 1, 1999
Israel Aircraft Industries, Ltd., Model Astra SPX Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries Model Astra SPX series airplanes. This action requires repetitive inspections to detect cracking of the main fuel tube assemblies of the left and right engines, 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 fuel line fractures, which could result in in-flight engine shutdowns or an increased risk of engine nacelle fires.
AD 99-17-04 · published Aug 18, 1999, effective Sep 22, 1999
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires replacement of the fairlead support assemblies of the aileron control cable located in the nacelle outboard fittings with new, improved assemblies; and replacement of certain attachment screws with new screws. This amendment also provides an option for performing repetitive inspections until accomplishment of the replacement. This amendment is prompted by reports of aileron cable wear due to chafing found between the aileron control cables and nylon grommets. The actions specified by this AD are intended to prevent such chafing, which could result in failure of the aileron cables, and consequent reduced controllability of the airplane.
AD 99-17-06 · published Aug 18, 1999, effective Sep 22, 1999
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections and tests to detect missing or damaged vespel bushes on the slat system universal joint assemblies of the left- and right-hand wings; and replacement of the universal joints with new joints, if necessary. This amendment also provides for an optional terminating modification for the repetitive inspection and test requirements. This amendment is prompted by a report of loose and migrated vespel bushes and partial cracking within unsupported bush areas found on the slat system universal joint assemblies. The actions specified by this AD are intended to prevent rupture of the universal joints, which could result in inadvertent movement of the slats, and consequent reduced controllability of the airplane.
AD 99-17-08 · published Aug 19, 1999, effective Oct 4, 1999
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC- 12/45 airplanes. This AD requires modifying the generator 2 excitation by removing certain diodes and installing a new 5-amp circuit breaker and suppression filter. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent damage to electrical components if the generator 2 is not switched off prior to engine shutdown and it overheats, which could result in loss of electrical power to certain critical airplane components.
AD 99-17-13 · published Aug 20, 1999, effective Sep 24, 1999
Lockheed Model L-1011-385 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires repetitive inspections to detect discrepancies of the lower actuator pins and/or bushings of the horizontal stabilizer, and replacement of any discrepant component with a new component. Replacement of all four actuator pins and bushings terminates the repetitive inspections. This amendment is prompted by a report indicating that a fractured lower actuator pin of the horizontal stabilizer was detected. The actions specified by this AD are intended to detect and correct discrepancies of the lower actuator pins and bushings of the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer control system, and consequent reduced controllability of the airplane.
AD 99-17-14 · published Aug 20, 1999, effective Sep 24, 1999
Bombardier Model DHC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8 series airplanes, that requires a one-time inspection of the spring assemblies located in the rudder control feel unit to verify that dual rate configuration springs are installed; and revising the Airplane Flight Manual to prohibit airplane operation from runways less than 75 feet wide, if necessary. This amendment also requires eventual replacement of any single rate configuration springs with dual rate configuration springs, which terminates the requirement for the AFM revision. 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 an asymmetric rudder force condition, which could result in reduced controllability of the airplane and consequent potential for center line deviation.
AD 99-17-20 · published Aug 20, 1999, effective Sep 24, 1999
Boeing Model 757-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -300 series airplanes, that requires modification of the off-wing emergency evacuation slide system. This amendment is prompted by reports that a certain type of off-wing escape slide aboard several airplanes separated from the airplane during flight. The actions specified by this AD are intended to prevent separation of the emergency evacuation slide from the airplane, which could result in damage to the fuselage and unavailability of an escape slide during an emergency evacuation.
AD 99-17-11 · published Aug 23, 1999, effective Sep 27, 1999
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 repetitive inspections to detect wear of the inboard flap trunnions, and to detect wear or debonding of the protective half-shells; and corrective actions, if necessary. This amendment 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 chafing and resultant wear damage on the inboard flap drive trunnions or on the protective half-shells, which could result in failure of the trunnion primary load path; this would adversely affect the fatigue life of the secondary load path and could lead to loss of the flap.
AD 99-17-12 · published Aug 23, 1999, effective Sep 27, 1999
British Aerospace Model BAe 146 and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes, that requires a one-time measurement to determine the thickness of the outer links of the side stays of the main landing gear (MLG), and corrective actions, if necessary. This amendment also provides for replacement of a thin outer link with a new or serviceable part in lieu of certain follow-on 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 cracking of the outer links of the side stays of the MLG, which could result in failure of a side stay, and consequent collapse of the landing gear.
AD 99-18-01 · published Aug 25, 1999, effective Sep 9, 1999
Boeing Model 737-700 and -800 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-700 and -800 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to prohibit operation of the airplane under certain conditions; repetitive inspections of the tab mast fitting of the elevator tab assemblies to detect cracking; an elevator tab freeplay check; and corrective actions, if necessary. That AD also provides for optional terminating action for certain repetitive inspections, and requires installing an additional fastener on the elevator tab mast fitting, which terminates the AFM revision and extends certain repetitive inspection intervals. This amendment continues to require certain actions, and revises and adds certain other requirements. This amendment is prompted by a report of a severe vibration incident on a Boeing Model 737-800 series airplane; inspection revealed fracturing of the elevator tab mast fitting and excessive freeplay in the elevator tab. The actions specified in this AD are intended to prevent loss of controllability of the airplane due to excessive freeplay in the elevator tab or a free tab.
AD 99-18-03 · published Aug 31, 1999, effective Sep 15, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes. This action requires repetitive inspections and tests of the thrust reverser control and indication system on each engine, and corrective actions, if necessary; installation of a terminating modification; and repetitive operational checks of that installation, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in significant reduction in airplane controllability. The actions specified in 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 99-18-05 · published Aug 31, 1999, effective Oct 5, 1999
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires repetitive inspections to detect cracks in the forward flange of the vertical beam of the aft pressure bulkhead at certain buttock lines, and installation of a splice repair, if necessary. The amendment also requires installation of a preventative modification on the vertical beam of the door frame in certain cases. This amendment is prompted by reports of fatigue cracks found in the vertical beam web and forward flange of the aft pressure bulkhead. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in the inability of the subject vertical beam to withstand the fail-safe loads, and consequent loss of cabin pressurization.
AD 99-18-06 · published Aug 31, 1999, effective Oct 5, 1999
Aerospatiale Model ATR42-300 and ATR42- 320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and ATR42-320 series airplanes, that requires a one-time inspection for cracking of a fastener hole located on the lower surface of the outer wing, and repair, if necessary; and cold working of the hole and installation of a new fastener in the hole. 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 damage on the outer wing and consequent reduced structural integrity of the wing.
AD 99-18-07 · published Aug 31, 1999, effective Oct 5, 1999
Boeing Model 747-400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires installation of strap assemblies on the ceiling panels and rails that support the video monitors. This amendment is prompted by reports of the video monitor ceiling panels falling into the cabin area due to the failure of certain latch assemblies during turbulence. The actions specified by this AD are intended to prevent ceiling panels from falling into the passenger area in the event of failure of certain latch assemblies on the ceiling panels, which could result in consequent injury to the crew and passengers.
AD 99-18-08 · published Aug 31, 1999, effective Oct 5, 1999
Israel Aircraft Industries, Ltd. (IAI), Model 1124 and 1124A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all IAI Model 1124 and 1124A series airplanes, that requires installation of an independent circuit breaker and associated wiring changes for the hydraulic low pressure warning lights. 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 loss of the hydraulic low pressure warning lights. Low pressure in the hydraulic system can result in reduced controllability of the airplane.
AD 99-18-09 · published Aug 31, 1999, effective Oct 5, 1999
Short Brothers Model SD3-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3-30 series airplanes, that requires modification of electrical wiring associated with heater components. 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 autofeather system, which could result in reduced controllability of the airplane in the event of engine failure during takeoff.
AD 99-18-10 · published Aug 31, 1999, effective Oct 5, 1999
Short Brothers Model SD3-SHERPA, SD3-60 SHERPA, SD3-30, and SD3-60 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-SHERPA, SD3-60 SHERPA, SD3- 30, and SD3-60 series airplanes, that requires a one-time detailed visual inspection of the emergency brake accumulator mounting structure for evidence of cracking; 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 by this AD are intended to prevent failure of the mounting angle that supports the emergency brake system due to cracking, which could result in loss of the emergency brake system.
AD 99-18-12 · published Aug 31, 1999, effective Sep 15, 1999
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection to detect cracking of the fuselage between stations 15375 and 16275, at the skin splice above the cabin windows; 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 cracking, which could result in depressurization of the cabin and reduced structural integrity of the airplane fuselage.
AD 99-18-13 · published Aug 31, 1999
de Havilland Inc. Models DHC-6-1, DHC- 6-100, DHC-6-200, and DHC-6-300 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all de Havilland Inc. Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers aft of the flight idle stop while the airplane is in flight. The AFM amendment includes a statement of consequences if the limitation is not followed. This AD is a result of numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. None of the incidents or accidents involved de Havilland Inc. Models DHC-6-1, DHC-6-100, DHC-6- 200, and DHC-6-300 airplanes. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned aft of the flight idle stop while the airplane is in flight.
AD 99-18-15 · published Aug 31, 1999, effective Sep 27, 1999
Raytheon Aircraft Company Beech Models C90A, B200, B300, and 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models C90A, B200, B300, and 1900D airplanes. This AD requires replacing the landing gear hand pump for airplanes that had a pump within a certain serial number range installed at manufacture; and prohibits the future installation of any of these pumps on all of the affected airplanes. This AD is the result of information from the manufacturer of improper machining of the pump housing on certain landing gear emergency hand pumps on the affected airplanes. This resulted in an insufficient groove depth to retain a snap ring, which retains the check valve in its proper position within the housing. The actions specified in this AD are intended to detect any improperly machined landing gear emergency hand pumps, which, if not removed from service, could result in the inability to properly lower and lock the landing gear in the event of failure of the primary retraction/extension system.
AD 99-13-10 · published Aug 2, 1999, effective Aug 2, 1999
Bell Helicopter Textron Canada Limited Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to BHTC Model 206L-4 helicopters, that requires replacing certain hydraulic relief valves (valves) with airworthy valves. This amendment is prompted by a pilot s report of intermittent hydraulic pressure in the flight controls that was caused by a defective hydraulic relief valve. The actions specified by this AD are intended to prevent intermittent hydraulic pressure to the flight controls and subsequent loss of control of the helicopters
AD 99-16-13 · published Aug 6, 1999, effective Sep 10, 1999
MD Helicopters, Inc. (MDHI) Model MD- 900 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to MDHI Model MD-900 helicopters, that currently requires applying specified serial numbers and establishing life limits for certain parts. This amendment is prompted by additional analysis that supports an increase in the life limit of certain parts. The actions specified by this AD are intended to increase the life limits for various parts.
AD 99-17-07 · published Aug 6, 1999
Eurocopter Deutschland GmbH Helicopters
AD 99-16-09 · published Aug 9, 1999, effective Aug 24, 1999
Bell Helicopter Textron Canada Model 230 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron Canada (BHTC) Model 230 helicopters. This action requires verifying the torque on the vertical fin attachment bolts (bolts); inspecting the vertical fin and tailboom fittings for cracks, elongation of bolt holes, distortion and corrosion; and re-verifying the torque on the bolts after inspecting the fittings. This amendment is prompted by a report of a loose vertical fin, which was discovered during a post-flight inspection. The actions specified in this AD are intended to prevent loss of torque of the bolts, which could lead to fracture of the bolts, separation of the vertical fin from the helicopter, and loss of control of the helicopter.
AD 99-17-03 · published Aug 12, 1999, effective Sep 16, 1999
Bell Helicopter Textron, Inc. Model 204B, 205A, and 205A-1 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 204B, 205A, and 205A-1 helicopters, that currently requires modifying and inspecting the vertical fin spar (fin spar) for cracks. This amendment requires modification and visual and dye-penetrant inspections of the fin spar for cracks, and if a crack is discovered, replacing the fin spar. A tapping test for disbonding and replacing certain fin spars within 12 calendar months is also required. This amendment is prompted by an accident involving a Model 205A-1 helicopter and four other accidents involving helicopters of similar type design. The actions specified by this AD are intended to prevent failure of the fin spar, loss of the tail rotor, and subsequent loss of control of the helicopter.
AD 99-17-10 · published Aug 18, 1999, effective Sep 2, 1999
Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, 269C-1, and 269D Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Schweizer Aircraft Corporation (SAC) Model 269A, 269A-1, 269B, 269C, 269C-1, and 269D helicopters. This action requires inspecting the tail rotor swashplate shaft (shaft) nut for looseness and, if loose, inspecting the shaft for proper size; subsequently inspecting the shafts not previously inspected; and replacing any undersized shaft prior to further flight. This amendment is prompted by the discovery of an undersized replacement shaft during routine maintenance. The actions specified in this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
AD 99-17-18 · published Aug 20, 1999, effective Sep 24, 1999
MD Helicopters, Inc. Model 600N Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to MD Helicopters, Inc. (MDHI) Model 600N helicopters, that requires applying serial numbers to several life-limited components related to pitch control and removing and replacing the components according to new life-limits. This amendment is prompted by fatigue tests that indicate a need for shorter service lives for these components. The actions specified by this AD are intended to prevent failure of the collective pitch control tubes, collective stick housings, and collective pitch tube assemblies, which can cause loss of collective pitch control, and subsequent loss of control of the helicopter.
AD 99-17-19 · published Aug 20, 1999, effective Sep 24, 1999
Bell Helicopter Textron, A Division of Textron Canada, Model 206L, L-1, L-3, and L-4 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada (BHTC), Model 206L, L-1, L-3, and L-4 helicopters, that currently requires the creation of a component history card or equivalent record using the Retirement Index Number (RIN) system for certain mast and trunnions and a system for tracking increases to the accumulated RIN. That AD also establishes retirement lives for the mast and trunnion. This amendment requires the same actions required by the existing AD but increases the RIN multiplier for the mast and corrects a helicopter model number. This amendment is prompted by further tests and analyses that indicate the RIN multiplier for the Model 206L-4 helicopters needs to be increased and the discovery of an error in a model designation in the existing AD. The actions specified by this AD are intended to prevent fatigue failure of the mast or trunnion, which could result in loss of the main rotor system and subsequent loss of control of the helicopter.
AD 99-17-09 · published Aug 20, 1999, effective Sep 7, 1999
Allison Engine Company, Inc AE 2100A and AE 2100C Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company, Inc AE 2100A and AE 2100C series turboprop engines. This action requires initial and repetitive visual inspections of the propeller gearbox (PGB) and power section (P/ S) strut fittings for notches and cracks, and, if necessary, replacement with serviceable parts. In addition, this action requires removing and replacing strut fittings as well as reworking them to the latest configuration identified by a new part number (P/N). This amendment is prompted by reports of P/S strut fitting notches and cracks. The actions specified in this AD are intended to prevent PGB and P/S strut fitting cracks, which could result in PGB misalignment, in-flight engine shutdown, and possible loss of the propeller.
AD 99-17-16 · published Aug 20, 1999, effective Sep 24, 1999
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) PW4000 series turbofan engines, that requires short term criteria for limiting the number of engines with potentially reduced stability on each airplane to no more than one engine, would require initial and repetitive on-wing or test cell cold-engine high pressure compressor (HPC) stability tests, would require removal of engines from service that fail on-wing test acceptance criteria, and would allow a follow-on test cell stability test. The AD also establishes required intervals for stability testing of the remaining engine with potentially reduced stability on the airplane and requirements for reporting test data. This amendment is prompted by a report of a dual-engine HPC surge event and reports of single-engine HPC surge events during the takeoff and climb phases of flight. The actions specified by this AD are intended to prevent an HPC surge event, which could result in engine power loss at a critical phase of flight such as takeoff or climb.
AD 97-21-01 R1 · published Aug 27, 1999, effective Aug 27, 1999
MT-Propeller Entwicklung GmbH Propellers
