47 Airworthiness Directives: 32 airplane, 11 rotorcraft, 2 engine, 1 appliance, 1 glider.
AD 98-26-24 · published Jan 4, 1999, effective Feb 8, 1999
Boeing Model 737-100 and -200 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that currently requires replacement of certain outboard and inboard wheel halves with improved wheel halves; cleaning and inspecting certain outboard and inboard wheel halves for corrosion, missing paint in large areas, and cracks; and repair or replacement of the wheel halves with serviceable wheel halves, if necessary. That AD was prompted by a review of the design of the flight control systems on Model 737 series airplanes. This amendment requires that the actions be accomplished in accordance with revised service information. The actions specified by this AD are intended to prevent failure of the wheel flanges, which could result in damage to the hydraulics systems, jammed flight controls, loss of electrical power, or other combinations of failures; and consequent reduced controllability of the airplane.
AD 97-20-01 R1 · published Jan 7, 1999, effective Feb 11, 1999
Boeing Model 747 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect cracks, corrosion, or damage of the lower spar fitting body and lug, and corrective actions, if necessary. That AD also provides for optional terminating action for the repetitive inspection requirements. That AD was prompted by reports that fatigue cracking was found in the lower spar fitting lug on the number 3 pylon and in the lower spar fitting body. The actions specified by that AD are intended to detect and correct such fatigue cracking, which could result in failure of the strut and separation of the engine from the airplane. This amendment references additional service bulletins for accomplishment of the optional replacement, and clarifies that accomplishment of certain AD's terminates the repetitive inspections.
AD 98-11-03 R1 · published Jan 7, 1999, effective Jun 23, 1998
Boeing Model 727 Series Airplanes
This amendment corrects information in an existing airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that currently requires that the FAA-approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item (SSI), and repair of cracked structure. The actions specified in that AD are intended to ensure the continued structural integrity of the entire Boeing Model 727 fleet. This amendment corrects the requirements of the current AD by allowing operators not to change their programs if they determine that the existing inspections are effective for the new or affected SSI. This amendment is prompted by a review of the requirements of the existing AD.
AD 98-11-04 R1 · published Jan 7, 1999, effective Jun 23, 1998
Boeing Model 737-100 and -200 Series Airplanes
This amendment corrects information in an existing airworthiness directive (AD), applicable to all Boeing Model 737-100 and -200 series airplanes, that currently requires that the FAA- approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item, and repair of cracked structure. The actions specified in that AD are intended to ensure the continued structural integrity of the entire Boeing Model 737-100 and - 200 fleet. This amendment corrects the requirements of the current AD by allowing operators not to change their programs if they determine that the existing inspections are effective for the new or affected SSI. This amendment is prompted by a review of the requirements of the existing AD.
AD 99-01-13 · published Jan 8, 1999, effective Feb 12, 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 modification of the airplane wiring to separate the electrical inputs sent by the engine interface units (EIU) to certain probe heat computers (PHC). This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent simultaneous loss of heating to pitot probes 1 and 3, which could result in incorrect airspeed indications to both the pilot's and first officer's airspeed indication systems. Malfunction of these systems could result in reduced controllability of the airplane.
AD 99-01-14 · published Jan 8, 1999, effective Feb 12, 1999
Honeywell IC-600 Integrated Avionics Computers, as Installed In, But Not Limited To, Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Honeywell IC-600 integrated avionics computers, that requires modification of the integrated avionics computers. This amendment is prompted by a report of integrated avionics computer failures, which caused a ``random reset'' condition of the electronic flight instrument system. The actions specified by this AD are intended to prevent such ``random reset'' conditions, which could affect the pilot's ability to control the airplane.
AD 99-01-15 · published Jan 8, 1999, effective Jan 25, 1999
Airbus Model A340-211, -212, -213, - 311, -312, and -313 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A340-211, -212, -213, -311, -312, and - 313 series airplanes. This action requires repetitive operational tests to ensure proper operation of the actuator of the secondary locks of the thrust reversers; 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 the inadvertent opening of a thrust reverser door in the event of failure of the primary and secondary locks of the thrust reverser. Such inadvertent opening could result in reduced controllability of the airplane.
AD 99-01-16 · published Jan 8, 1999, effective Feb 12, 1999
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires installation of a placard that warns the cabin crew not to put the selector valve for the forward lavatory water supply in the ``DRAIN'' position during flight. This amendment also requires installation of an isolation valve in the drain line downstream of the selector valve, which would terminate the requirement for the placard installation. This amendment is prompted by reports of damage to the horizontal stabilizer, and engine flameout caused by ice formed from water drained inadvertently through a mispositioned selector valve. The actions specified by this AD are intended to prevent damage to the engines, airframe, or horizontal stabilizer, and/ or to prevent a hazard to persons or property on the ground, as a result of ice that could dislodge from the airplane.
AD 99-01-17 · published Jan 8, 1999, effective Feb 12, 1999
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage; and corrective action, if necessary. This amendment also provides for 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, which could result in reduced structural integrity of the airplane.
AD 99-01-18 · published Jan 8, 1999, effective Feb 12, 1999
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage; and corrective action, if necessary. This amendment also provides for 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, which could result in reduced structural integrity of the airplane.
AD 99-01-19 · published Jan 8, 1999, effective Feb 12, 1999
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage; and corrective action, if necessary. This amendment also provides for 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, which could result in reduced structural integrity of the airplane.
AD 98-25-11 R1 · published Jan 11, 1999, effective Dec 28, 1998
McDonnell Douglas Model MD-11 Series Airplanes
This amendment corrects and clarifies information in an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes, that currently requires a one- time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors, and repair, if necessary. The actions specified in that AD are intended to prevent chafing of the electrical wire assemblies, which could result in an electrical fire in the passenger compartment. This amendment corrects and clarifies the requirements of the current AD by specifying the specific area in which the subject inspection must be conducted and by correcting the part number of the ramp deflector assembly. This amendment is prompted by communication received from the manufacturer that the current requirements of the AD are unclear.
AD 98-26-18 · published Jan 12, 1999, effective Feb 16, 1999
Boeing Model 727 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1767SO, SA1768SO, or SA7447SW
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger to a cargo-carrying (``freighter'') configuration, that requires limiting the payload on the main cargo deck by revising the Limitations Sections of all Airplane Flight Manuals (AFM), AFM Supplements, and Airplane Weight and Balance Supplements for these airplanes. This amendment also provides for the submission of data and analyses that substantiate the strength of the main cargo deck, or modification of the main cargo deck, as optional terminating action for these payload restrictions. This amendment is prompted by the FAA's determination that under certain conditions unreinforced floor structure of the main cargo deck is not strong enough to enable the airplane to safely carry the maximum payload that is currently allowed in this area. The actions specified by this AD are intended to prevent failure of the floor structure, which could lead to loss of the airplane.
AD 98-26-19 · published Jan 12, 1999, effective Feb 16, 1999
Boeing Model 727 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1368SO, SA1797SO, or SA1798SO
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger to a cargo-carrying (``freighter'') configuration, that requires limiting the payload on the main cargo deck by revising the Limitations Sections of all Airplane Flight Manuals (AFM), AFM Supplements, and Airplane Weight and Balance Supplements for these airplanes. This amendment also provides for the submission of data and analyses that substantiate the strength of the main cargo deck, or modification of the main cargo deck, as optional terminating action for these payload restrictions. This amendment is prompted by the FAA's determination that under certain conditions unreinforced floor structure of the main cargo deck is not strong enough to enable the airplane to safely carry the maximum payload that is currently allowed in this area. The actions specified by this AD are intended to prevent failure of the floor structure, which could lead to loss of the airplane.
AD 98-26-20 · published Jan 12, 1999, effective Feb 16, 1999
Boeing Model 727 Series Airplanes Modified in Accordance With Supplemental Type Certificate ST00015AT
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger to a cargo-carrying (``freighter'') configuration, that requires limiting the payload on the main cargo deck by revising the Limitations Sections of all Airplane Flight Manuals (AFM), AFM Supplements, and Airplane Weight and Balance Supplements for these airplanes. This amendment also provides for the submission of data and analyses that substantiate the strength of the main cargo deck, or modification of the main cargo deck, as optional terminating action for these payload restrictions. This amendment is prompted by the FAA's determination that under certain conditions unreinforced floor structure of the main cargo deck is not strong enough to enable the airplane to safely carry the maximum payload that is currently allowed in this area. The actions specified by this AD are intended to prevent failure of the floor structure, which could lead to loss of the airplane.
AD 98-26-21 · published Jan 12, 1999, effective Feb 16, 1999
Boeing Model 727 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1444SO, SA1509SO, SA1543SO, SA1896SO, SA1740SO, or SA1667SO
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger to a cargo-carrying (``freighter'') configuration, that requires limiting the payload on the main cargo deck by revising the Limitations Sections of all Airplane Flight Manuals (AFM), AFM Supplements, and Airplane Weight and Balance Supplements for these airplanes. This amendment also provides for the submission of data and analyses that substantiate the strength of the main cargo deck, or modification of the main cargo deck, as optional terminating action for these payload restrictions. This amendment is prompted by the FAA's determination that under certain conditions unreinforced floor structure of the main cargo deck is not strong enough to enable the airplane to safely carry the maximum payload that is currently allowed in this area. The actions specified by this AD are intended to prevent failure of the floor structure, which could lead to loss of the airplane.
AD 99-02-03 · published Jan 15, 1999, effective Feb 19, 1999
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires installation of a rubber strip and replacement of connection sheets and the seal retainer on the avionics compartment access door with new parts; and installation of drip pans and additional drain gutters on the avionics racks. 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 trickling of water into the avionics compartment, which could result in avionics computer and equipment malfunctions.
AD 99-02-04 · published Jan 15, 1999, effective Feb 19, 1999
Airbus Model A320 and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes. This amendment requires modification of the slat and flap control computer (SFCC) in the aft electronics rack. 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 SFCC caused by computer software anomalies or contamination by conductive dust. This condition, if not corrected, could result in uncommanded slat retraction during takeoff and consequent insufficient wing lift available to complete a successful takeoff.
AD 99-02-05 · published Jan 15, 1999, effective Feb 19, 1999
Lockheed Model L-1011-385-1 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385-1 series airplanes, that requires modification of the power drive units and the lower drive sprocket assemblies of the galley lift system. This amendment is prompted by a report indicating that, due to fatigue cracking, the primary and secondary drive shafts of the galley lift failed and caused the galley lift to drop to the lower level, injuring a flight attendant. The actions specified by this AD are intended to prevent such fatigue cracking of the primary and secondary drive shafts, which could result in complete fracturing of the secondary shaft; such fracturing could allow the galley lift to drop to the bottom of the shaft, and could result in possible injury to crewmembers.
AD 99-02-06 · published Jan 15, 1999, effective Feb 19, 1999
Fokker Model F.28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires modification of the aft cabin sidewall area to improve decompression venting and, for certain airplanes, modification of the aft wardrobe/stowage area door and installation of decompression panels to improve decompression venting. 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 the cabin floor in the event of sudden decompression in the cargo compartment, which could result in injury to passengers, reduced structural integrity of the airplane, and the loss of airplane systems.
AD 99-02-07 · published Jan 19, 1999, effective Feb 23, 1999
Fokker Model F.28 Mark 0070 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that requires modification of the power supply system of the horizontal stabilizer control 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 the loss of primary hydraulic stabilizer control during use of certain emergency procedures, which could result in the inability of the flight crew to control the airplane.
AD 99-02-08 · published Jan 19, 1999, effective Feb 3, 1999
Airbus Model A330-301, -321, -322, - 341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 series airplanes. This action requires repetitive high-frequency eddy current (HFEC) inspections to detect cracking of the inner flange of the rear fuselage frame FR73A, between beams 5 and 6; and corrective actions, if necessary. 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 authority. The actions specified in this AD are intended to detect and correct fatigue cracking of the inner flange of the rear fuselage frame FR73A, which could result in reduced structural integrity of the fuselage.
AD 99-02-10 · published Jan 19, 1999, effective Feb 23, 1999
Airbus Model A320 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires modification of the trimmable horizontal stabilizer (THS). This amendment adds a requirement for a one-time inspection of the flexible hoses of the elevator return lines on the THS to detect installation of incorrect clamps, or missing clamps or bonding leads; and for replacement of the clamps or bonding leads with new parts, 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 leakage from hydraulic pipe fittings in the THS, which could result in failure of the THS and consequent reduced controllability of the airplane.
AD 99-02-11 · published Jan 21, 1999, effective Feb 25, 1999
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes. This amendment requires repetitive tests to detect internal leakage of hydraulic fluid within the hydraulic components of the ground spoiler system and to detect a buildup of pressure in the return line of the bypass valve, and corrective action, if necessary; installation of additional hydraulic lines and an additional hydraulic shutoff valve in the ground spoiler system; and replacement of the valve block of the ground spoiler system with a new part. This amendment also requires eventual replacement of the relief restrictor valves of the ground spoiler system with redesigned parts, which constitutes terminating action for the repetitive tests. 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 ground spoilers from unlocking and deploying during takeoff or in flight, and consequent reduced controllability of the airplane.
AD 99-02-12 · published Jan 21, 1999, effective Feb 25, 1999
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time visual inspection to detect discrepancies of the components of the torque link apex joint and shimmy damper attachments of the main landing gear (MLG), and repair or replacement of any discrepant component with a new or serviceable component. 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 heavy vibration and possible damage to the components of the MLG, and consequent reduced controllability of the airplane during takeoff and landing.
AD 99-02-14 · published Jan 26, 1999, effective Mar 5, 1999
Raytheon Aircraft Company Model 2000 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 2000 airplanes (commonly referred to as Beech Model 2000 airplanes). This AD requires inspecting the stainless steel fuel line, part number (P/N) 3035737, for evidence of chafing and a minimum clearance between the fuel line and power lever bracket, P/N 122-940028-1; and replacing the fuel line and modifying the power lever bracket, as necessary. This AD is the result of chafing found on the stainless steel fuel line on several of the affected airplanes. The actions specified by this AD are intended to prevent fuel line chafing caused by interference with the power lever bracket, which could result in fuel leakage and cause a fire in the engine compartment.
AD 99-02-15 · published Jan 26, 1999, effective Mar 29, 1999
Avions Pierre Robin Model R2160 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires repetitively inspecting the engine bearer for cracks, and replacing the engine bearer with a reinforced part either immediately or at a certain time period depending on whether cracks are found during the inspections. Replacing the engine bearer with a reinforced part terminates the repetitive inspection requirement. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to detect and correct cracks in the engine bearer, which could result in the engine separating from the airplane.
AD 99-02-16 · published Jan 26, 1999, effective Mar 12, 1999
Raytheon Aircraft Company Models B300 and B300C Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models B300 and B300C airplanes (commonly referred to as Beech Models B300 and B300C airplanes). This AD requires modifying the elevator trim tab actuators by incorporating a new elevator trim tab actuator assembly kit, replacing the elevator trim tab pushrod assembly, or modifying the elevator spar opening, whichever is applicable. Reports from operators of ice forming on the elevator trim tab actuators and jamming the trim tab control prompted this action. The actions specified by this AD are intended to prevent jamming of the elevator trim tab actuator caused by ice formations, which could result in loss of control of the airplane.
AD 99-02-18 · published Jan 27, 1999, effective Mar 3, 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 removing the thermal insulating blankets from the upper rear nacelle structure; re-positioning the engine exhaust duct; and replacing the engine exhaust bracket with a new engine exhaust bracket, if necessary. For certain airplanes, this amendment also requires installing new stainless steel plates onto the upper rear nacelle structure. 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 fretting of the titanium thermal insulating blankets, which could result in an increased risk of fire in the engine exhaust duct of the tail pipe.
AD 99-03-02 · published Jan 28, 1999, effective Feb 12, 1999
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection to detect discrepancies of certain wiring and insulation in the cockpit and cabin, and repair, if necessary. This amendment is prompted by test results obtained in support of an accident investigation. The actions specified in this AD are intended to prevent electrical arcing of certain wiring, which could cause a fire and/or smoke in the cockpit or cabin.
AD 98-26-51 · published Jan 29, 1999, effective Feb 3, 1999
McDonnell Douglas Model DC-8 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1802SO
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-26-51 that was sent previously to all known U.S. owners and operators of certain McDonnell Douglas Model DC-8 series airplanes by individual telegrams. This AD requires a revision to the Airplane Flight Manual to specify restrictions on operating if any pressurization anomaly is detected. This AD also requires a one-time inspection to detect discrepancies and cracking of the main deck cargo door in the immediate area of the bolts attaching the latch fittings, and repair, if necessary. This action is prompted by a report that a cabin pressurization anomaly was detected on a McDonnell Douglas Model DC-8 series airplane, and by subsequent investigation, which revealed fatigue cracking in the structure of the main deck cargo door. The actions specified by this AD are intended to detect and correct fatigue cracking in the structure of the main deck cargo door, which could result in cabin decompression of the airplane and loss of the main deck cargo door, and consequent reduced controllability of the airplane.
AD 99-01-12 · published Jan 29, 1999, effective Feb 2, 1999
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 99-01-12 that was sent previously to all known U.S. owners and operators of certain EMBRAER Model EMB-145 series airplanes by individual notices. This AD requires revisions to the Airplane Flight Manual to provide the flight crew with updated procedures for prohibiting use of the autopilot below 1,500 feet above ground level, emergency procedures for pitch trim runaway, and abnormal procedures for autopilot trim failure and stabilizer out of trim. This AD also requires installation of certain warning placards. This action is prompted by a report indicating that, during a flight test of a similar airplane model, the pitch trim monitoring subsystem malfunctioned internally. The actions specified by this AD are intended to prevent failure of the pitch trim system, which could cause undetected autopilot trim runaway, and consequent reduced controllability of the airplane, uncommanded autopilot disconnect, and excessive altitude loss.
AD 98-19-13 · published Jan 12, 1999, effective Jan 27, 1999
Bell Helicopter Textron Canada (BHTC) Model 407 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-19-13, which was sent previously to all known U.S. owners and operators of BHTC Model 407 helicopters by individual letters. This AD requires, on or before the accumulation of 50 hours total time-in-service (TIS) on the engine-to- transmission driveshaft (driveshaft), replacing the driveshaft with an airworthy driveshaft. This amendment is prompted by analysis and test data which revealed that the life limit of the driveshaft is less than that which is stated in the applicable maintenance manual. The actions specified by this AD are intended to prevent failure of the driveshaft, loss of engine drive to the rotor system, damage to critical structural components, and subsequent loss of control of the helicopter.
AD 98-17-15 · published Jan 15, 1999, effective Feb 1, 1999
Sikorsky Aircraft Corporation Model S- 76A, B, and C Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-17-15 which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Corporation Model S-76A, B, and C helicopters by individual letters. This AD requires, before further flight, a one-time visual inspection of the swashplate assembly uniball bearing retainer (retainer) for missing bolts, an inspection with a magnet to detect aluminum bolts, and replacing missing or aluminum bolts with airworthy steel bolts. This amendment is prompted by reports of the installation of aluminum bolts on swashplate assemblies. This condition, if not corrected, could result in failure of the swashplate assembly, loss of the main rotor, and subsequent loss of control of the helicopter.
AD 99-02-02 · published Jan 15, 1999, effective Feb 1, 1999
Robinson Helicopter Company (RHC) Model R22 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to RHC Model R22 helicopters, that currently requires initial and repetitive inspections of the forward flexplate (flexplate) at specified time intervals. This amendment also supersedes an existing priority letter AD that requires, within 25 hours time-in-service (TIS) or 15 calendar days, whichever occurs first, replacing the flexplate with an airworthy flexplate. This amendment requires the same replacement as the priority letter AD. This amendment is prompted by an accident in which the flexplate failed, causing loss of main rotor drive and rupture of the fuel tank. The actions specified by this AD are intended to prevent failure of the flexplate, which could result in failure of the main rotor drive system and subsequent loss of control of the helicopter.
AD 99-02-09 · published Jan 15, 1999
Agusta S.p.A. Model A109C and A109K2 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Agusta S.p.A. Model A109C and A109K2 helicopters. This amendment requires removing the main rotor pitch link assemblies, measuring the radial play of the upper and lower spherical bearings (bearings), and replacing any unairworthy bearings. This amendment is prompted by four reports of increased vibration of the helicopters caused by wear in the bearings of the main rotor pitch change link assembly. The actions specified by this AD are intended to detect unairworthy bearings on the pitch change link assembly and to prevent increased vibration and subsequent reduced controllability of the helicopter.
AD 98-12-30 · published Jan 19, 1999, effective Feb 3, 1999
McDonnell Douglas Helicopter Systems Model MD-900 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-12-30 which was sent previously to all known U.S. owners and operators of McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters by individual letters. This AD requires inspecting the main rotor upper hub assembly (hub assembly) for cracks, and if a crack is found, replacing the hub assembly. The AD also requires verifying attachment nut torque values and a repetitive inspection at intervals not to exceed 150 hours time- in-service. This amendment is prompted by the discovery of cracks in 6 main rotor upper hub assemblies. This condition, if not corrected, could result in failure of the hub assembly, loss of drive to the main rotor, and subsequent loss of control of the helicopter.
AD 98-24-31 · published Jan 19, 1999, effective Feb 3, 1999
Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-24-31, which was sent previously to all known U.S. owners and operators of BHTC Model 430 helicopters by individual letters. This AD requires, within 10 hours time-in-service (TIS), inspecting the lateral control tube (control tube) assembly and the forward fairing assembly for chafing. If chafing is found, replace the control tube assembly and rework the forward fairing assembly before further flight. If no chafing is found during the initial inspection, perform the corrective actions within the next 150 hours TIS. This amendment is prompted by two incidents of binding of the control tube assembly that occurred during flight. The actions specified by this AD are intended to prevent binding of the control tube assembly with the inside surface of the forward fairing assembly under certain load conditions and subsequent loss of control of the helicopter.
AD 98-26-06 · published Jan 19, 1999, effective Feb 3, 1999
Schweizer Aircraft Corporation Model 269D Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-26-06 which was sent previously to all known U.S. owners and operators of Schweizer Aircraft Corporation (Schweizer) Model 269D helicopters by individual letters. This AD requires removing the main rotor drive shaft (shaft) and inspecting it for cracks. If a crack is found, replacing the shaft with an airworthy shaft is required. This AD also requires periodically verifying the torque of the main rotor hub (hub) bolts. This amendment is prompted by four reports of cracking in the shaft of helicopters with a large diameter hub. Wear patterns indicate cracking was caused by loss of clamping torque on the hub and shaft assembly due to the use of grease between the hub and shaft. This condition, if not corrected, could result in failure of the shaft and subsequent loss of control of the helicopter.
AD 98-11-14 · published Jan 26, 1999, effective Feb 10, 1999
Bell Helicopter Textron, Inc. Model 205A-1 and 205B Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-11-14 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI) Model 205A-1 and 205B helicopters by individual letters. This AD requires inspecting the trunnion assembly or tail rotor flapping stop (flapping stop), whichever is applicable, installing a trunnion assembly or flapping stop, if necessary; and replacing the tail rotor yoke (yoke). This amendment is prompted by an accident involving a BHTI Model 205A-1 helicopter in which the yoke failed during flight. This condition, if not corrected, could lead to failure of the yoke, loss of the tail rotor, and subsequent loss of control of the helicopter.
AD 98-11-15 · published Jan 26, 1999, effective Feb 10, 1999
Bell Helicopter Textron, Inc. Model 212 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-11-15, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI) Model 212 helicopters by individual letters. This AD requires inspecting the trunnion assembly or tail rotor flapping stop (flapping stop), whichever is applicable, installing a trunnion assembly or flapping stop, if necessary; and replacing the tail rotor yoke (yoke). This amendment is prompted by an accident involving a BHTI Model 205A-1 helicopter in which the yoke failed during flight. This condition, if not corrected, could lead to failure of the yoke, loss of the tail rotor, and subsequent loss of control of the helicopter.
AD 99-02-17 · published Jan 26, 1999, effective Feb 10, 1999
Bell Helicopter Textron, Inc. Model 214B and 214B-1 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B and 214B-1 helicopters. This action requires a reduction of the never- exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required. This amendment is prompted by reports of inflight failures of yokes installed on civilian and military helicopters of similar type design. The actions specified in this AD are intended to prevent fatigue failure of the yoke that could result in loss of the tail rotor and subsequent loss of control of the helicopter.
AD 99-02-13 · published Jan 28, 1999, effective Mar 4, 1999
Airworthiness Directives, Eurocopter France Model AS332C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters, that requires the replacement of certain main rotor hub spindles (spindles) and flapping hinge pins (pins). This amendment is prompted by testing of aged frequency adapters, which shows that premature failure of the spindles and pins can occur due to increased loading from increased stiffness of the aged frequency adapters. The actions specified by this AD are intended to prevent the loss of a main rotor blade and subsequent loss of control of the helicopter.
AD 99-01-01 · published Jan 6, 1999, effective Jan 21, 1999
General Electric Company CF6-80C2 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-80C2 series turbofan engines. This action requires a one-time visual inspection to ensure the correct accessory gearbox (AGB) idler adapter inserts are installed, and, if necessary, removal of AGB idler adapters with the improper inserts. This amendment is prompted by a report of a failure of a fuel tube flange connection due to improper AGB idler adapter inserts that resulted in a high pressure fuel leak and engine fire. The actions specified in this AD are intended to identify and remove AGB idler adapters with improper inserts, which can result in an engine fire and damage to the aircraft.
AD 99-03-03 · published Jan 29, 1999, effective Feb 16, 1999
Allison Engine Company Model AE 3007A and AE 3007A1/1 Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Allison Engine Company Model AE 3007A turbofan engines, that currently requires reprogramming the Full Authority Digital Engine Control (FADEC) to software version VI.2. This amendment requires reprogramming the FADEC to a serviceable software version and reidentifying the FADEC assembly. This amendment is prompted by reports of at least seven uncommanded engine shutdowns, four of which occurred in flight, as a result of deficiencies in software version VI.2 on the AE 3007A engines and version VI.4 on the AE 3007A1/1 engines. The actions specified by this AD are intended to prevent an unintentional or uncommanded in-flight engine shutdown.
AD 99-01-11 · published Jan 6, 1999, effective Jan 29, 1999
The Uninsured Relative Workshop Inc. Vector Parachute Systems
This amendment adopts a new airworthiness directive (AD) that applies to all The Uninsured Relative Workshop Inc. (doing business as and referred to herein as Relative Workshop) vector parachute systems that were manufactured between January 1, 1996, and September 10, 1998. This AD requires inspecting the amp fittings on the end of the breakaway housing for proper swaging, and re-swaging any incorrectly swaged fittings using the Nicopress<SUP></SUP> or Swage-It swaging tool. This AD is the result of a quality control problem on Relative Workshop vector parachute systems. In particular, a loose amp fitting was found on the breakaway housing during packing of one of these vector parachute systems. Further analysis reveals that the amp fittings on the end of the stainless steel breakaway housing were improperly swaged, and that this condition could exist on any of the 2,127 parachute systems that were manufactured during the above- referenced time period. The actions specified by this AD are intended to prevent the amp fittings from coming off the stainless steel breakaway housing, which could result in an unintentional partial breakaway of the main chute and interference with the deployment of the reserve parachute.
AD 99-03-01 · published Jan 28, 1999, effective Mar 12, 1999
Schempp-Hirth K.G. Models Standard- Cirrus, Nimbus-2, JANUS, and Mini-Nimbus HS-7 Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schempp-Hirth) Models Standard- Cirrus, Nimbus-2, JANUS, and Mini-Nimbus HS-7 sailplanes. This AD requires installing a safety device for the tailplane locking hook. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the locking hook on the tailplane attachment bracket from disengaging, which could result in the horizontal tailplane coming loose from the fin with possible loss of longitudinal control of the sailplane.
