29 Airworthiness Directives: 21 airplane, 2 rotorcraft, 4 engine, 2 appliance.
AD 99-09-18 · published May 4, 1999, effective Jun 8, 1999
Fokker Model F.28 Mark 0070 and Mark 0100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires a one-time inspection for heat damage of the fuselage skin and stubwing structure; either repetitive tests of certain seals or repair of heat damage, as necessary; and eventual replacement of corrujoint seals with new, improved seals. This amendment adds a requirement for repetitive inspections for heat damage of the subject area, and provides for a new optional terminating action for the repetitive inspections. This action 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 of hot air from the corrujoint seals of certain valves in the stubwings, and subsequent heat damage of the fuselage skin and stubwing structure, which could result in reduced structural integrity of the airplane.
AD 99-09-19 · published May 4, 1999, effective May 19, 1999
Aerospatiale Model ATR42 and ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Aerospatiale Model ATR42 and ATR72 series airplanes. This action requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in severe icing conditions. 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 airplane from stalling due to prolonged exposure to severe icing conditions, which could result in reduced performance and controllability of the airplane.
AD 99-10-01 · published May 5, 1999, effective Jun 18, 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 replacing the wing attachment bolts and associated hardware. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent a wing from separating from the airplane caused by damaged wing attachment bolts, which could result in loss of control of the airplane.
AD 99-10-02 · published May 5, 1999, effective Jun 18, 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 inspecting to assure that the fuel filler cap has a 2.5 millimeter (mm) diameter hole drilled through it or that a vinyl piping is connected to the filler neck inside the cabin. If neither of these items exists, this AD requires replacing the fuel filler cap with a fuel filler cap that has a 2.5 mm diameter hole drilled through it. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct the installation of improperly designed fuel venting system parts, which could result in an inadequate fuel supply to the engine with loss of engine power.
AD 99-10-03 · published May 5, 1999, effective Jun 9, 1999
British Aerospace Model BAC 1-11 200 and 400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires an inspection to detect cracking of the flap control lever and to identify the material from which the lever is made; replacement of the flap control lever with an improved part, if necessary; and repetitive inspections for airplanes having a lever made from certain material. 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 flap control lever, which could result in restricted flap movement and consequent reduced controllability of the airplane.
AD 99-10-04 · published May 5, 1999, effective Jun 9, 1999
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires modification of the pulley assemblies of the elevator and rudder control cables on the rear pressure bulkhead. 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 pulley assemblies of the elevator and rudder control cables in the event of an elevator or rudder control cable jam, which could result in reduced controllability of the airplane.
AD 99-10-05 · published May 5, 1999, effective May 20, 1999
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-145 series airplanes. This action requires replacement of certain flexible joints and O-rings of the rear fuselage with improved flexible joints and new O-rings. This action also requires installation of new support assemblies to attach to the engine bleed line tubing in the area of the rear fuselage to improve the engine bleed line tubing alignment. 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 certain flexible joints that attach to the engine bleed lines in the area of the rear fuselage. Failure of these flexible joints could cause damage to the fuel lines leading to the auxiliary power unit, which could result in an increased risk of fire to occur in the rear baggage compartment during flight.
AD 99-10-06 · published May 7, 1999, effective Jun 3, 1999
Raytheon Aircraft Corporation Model Beech 2000 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Model Beech 2000 airplanes. This AD requires immediately incorporating temporary revisions to the Limitations Section of the Airplane Flight Manual (AFM) that include requirements of not allowing flap operation during takeoff, accomplishing the preflight visual checks (referred to as visual inspections in the AFM temporary revisions) of the aft cove panel of the wing for delamination prior to each flight, and incorporating a repair scheme if delamination is found. This AD also requires repetitively inspecting the trailing edge of the wing by looking for delamination (debonding) (also referred to as cracks in the service information) through the thickness of the trailing edge of the wing cove skin panels, and modifying the center flap track rib attachment when delamination (debonding) is found. This AD is the result of a report of the wing cove skin panel separating from the wing while in flight on one of the affected airplanes. The actions specified by this AD are intended to detect and correct delamination of the wing cove skin in the area of the support rib, which could result in the delamination propagating to the trailing edge of the wing with the wing cove skin panel possibly separating from the wing.
AD 99-10-08 · published May 7, 1999, effective Jun 11, 1999
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a detailed visual inspection to detect corrosion inside the forward trunnion joint of the main landing gear (MLG); follow-on actions; and repair, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports of corrosion at the forward trunnion thrust face, tabs, and the internal threads of the forward trunnion of the MLG due to moisture in the forward trunnion joint. The actions specified by this AD are intended to prevent corrosion of the forward trunnion joint, which could lead to a stress corrosion fracture of the forward trunnion and possible consequent collapse of the MLG.
AD 99-10-09 · published May 11, 1999, effective Jun 15, 1999
Boeing Model 747-100, 747-200, and 747- SP Series Airplanes and Military Type E-4B Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and 747-SP series airplanes and military type E-4B airplanes, that requires repetitive inspections to detect cracking of the wing front spar web, and repair of cracked structure. This amendment also provides for optional terminating action for the repetitive inspection requirements. This amendment is prompted by reports indicating that fatigue cracks were found on the aft surface of the wing front spar web. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in a fuel leak, and consequent increased risk of a fire.
AD 99-10-10 · published May 11, 1999, effective Jun 15, 1999
Boeing Model 747-200, -300, and -400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that requires replacement of fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins. This amendment is prompted by reports of cracked fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut due to fatigue and corrosion. The actions specified by this AD are intended to prevent cracking or corrosion of the fuse pins of the nacelle strut, which could result in failure of the fuse pin and strut-to-wing attachment, and consequent loss of the strut and separation of the engine from the airplane.
AD 99-10-12 · published May 12, 1999, effective May 27, 1999
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that currently requires repetitive inspections to detect cracking, plating degradation, and corrosion of the main landing gear (MLG) actuator beam arms and actuator beam attach bolts; and rework or replacement, if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. This amendment removes the requirement to inspect the actuator beam attach bolts, expands the applicability of the existing AD to include additional airplanes, and removes the optional terminating action. This amendment is prompted by reports of cracked MLG actuator beam arms. The actions specified in this AD are intended to detect and correct corrosion and cracking of the MLG actuator beam arm, which could result in damage to the control cables for the aileron and spoiler and consequent reduced controllability of the airplane.
AD 99-10-13 · published May 12, 1999, effective May 27, 1999
Boeing Model 737-300, -400, -500, -600, -700, and -800 Series Airplanes Equipped with Vickers Combined Stabilizer Trim Motors
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737 series airplanes. This action requires repetitive inspections and functional tests of a trailing edge flap limit switch to verify proper operation, and replacement of the existing limit switch with a new limit switch, if necessary. This AD also requires modification of the stabilizer control system, which constitutes terminating action for the repetitive inspections and tests. This amendment is prompted by reports of uncommanded stabilizer trim motion due to failure of the trailing edge flap limit switch. The actions specified in this AD are intended to prevent such failure, which could result in uncommanded (nose down) stabilizer trim motion and consequent reduced controllability of the airplane.
AD 99-10-14 · published May 13, 1999, effective Jun 17, 1999
Boeing Model 747-400, 757, 767, and 777 Series Airplanes Equipped With AlliedSignal RIA-35B Instrument Landing System (ILS) Receivers
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400, 757, 767, and 777 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to prohibit certain types of approaches. That action also requires repetitive inspections to detect certain faults of all RIA-35B ILS receivers, and replacement of discrepant ILS receivers with new, serviceable, or modified units; or, alternatively, an additional revision to the AFM and installation of a placard to prohibit certain operations. That AD was prompted by a report of errors in the glide slope deviation provided by an ILS receiver. This amendment requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent erroneous localizer deviation provided by faulty ILS receivers, which could result in a landing outside the lateral boundary of the runway.
AD 99-09-52 · published May 17, 1999, effective May 24, 1999
Bombardier Model CL-600-2B19 (Regional Jet Series 100) and CL-600-2B16 (CL-601-3R and CL-604) Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 99-09-52 that was sent previously to all known U.S. owners and operators of Bombardier Model CL-600-2B19 (Regional Jet Series 100) and CL-600-2B16 (CL-601-3R and CL-604) series airplanes by individual notices. This AD requires a one-time inspection of the cable harness of the integrated drive generator (IDG) in the right engine nacelle and the adjacent structure to verify clearances and detect chafing; a one-time inspection of both the left and right engine nacelles to detect chafing and verify clearances of the adjacent 10th stage bleed air check valve and fuel manifold pigtails; and repair or replacement of discrepant parts, if necessary. This action is prompted by reports of chafing of the insulation covering on the IDG cable harness and the main engine right fuel manifold. The actions specified by this AD are intended to detect and correct concurrent chafing of both the fuel manifold and the IDG wire and subsequent leakage of fuel, which could come in contact with live wiring and result in fire or explosion.
AD 99-10-07 · published May 18, 1999, effective Jun 8, 1999
Raytheon Aircraft Corporation Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, H90, and F90 Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-10-07, which was sent previously to all known U.S. owners and operators of Raytheon Aircraft Corporation (Raytheon) Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, H90, and F90 airplanes. This AD requires inspecting for interference or damage between the elevator control cable and equipment under the cockpit floor panels (wire harnesses, stainless steel clamps, etc.) and running a cloth wrap around the control cable to detect broken strands of the control cable. This AD also requires replacing or repairing any damaged items, securing any component that is interfering with the elevator control cable, and installing additional supports and clamps as necessary to prevent sagging or further interference. This AD resulted from reports of reduced or loss of elevator control on five of the affected airplanes. The actions specified by this AD are intended to detect and correct interference between the elevator control cable and equipment under the cockpit floor panels before the elevator control cable breaks, which could result in loss of elevator control with potential loss of control of the airplane.
AD 99-10-16 · published May 18, 1999, effective Jun 22, 1999
Mitsubishi Model YS-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Mitsubishi Model YS-11 series airplanes, that requires repetitive inspections to detect fatigue cracking in the manhole doublers of the lower wing panels; and repair, if necessary. This amendment also requires eventual modification of screw holes in the manhole doublers of the lower wing panels, which constitutes terminating action for the repetitive inspections required by this AD. 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 fatigue cracking in the manhole doublers of the lower wing panels, which could result in failure of the wing structure.
AD 99-11-01 · published May 18, 1999, effective Jun 2, 1999
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-145 series airplanes. This action requires repetitive replacement of the bleed-air check valve and associated gaskets on the bleed low-pressure line of the engine, with new parts. 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 bleed-air check valve on the bleed low-pressure line of the engine. Such failure could result in engine compressor stall and consequent flameout of the affected engine.
AD 99-11-06 · published May 21, 1999, effective Jul 5, 1999
Industrie Aeronautiche e Meccaniche Model Piaggio P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires inspecting both (left and right wing configurations) environmental control system bleed tubes for damage, leakage, and a correct gap between the tube and wing lower panel crossing area, inspecting the wiring and surrounding structures for damage, and correcting any discrepancies found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent thermal expansion from causing leakage of an environmental control system bleed tube because of improper installation, which could result in deterioration of the electrical wiring and the surrounding structure.
AD 99-11-07 · published May 24, 1999, effective Jun 15, 1999
Mooney Aircraft Corporation Model M20R Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Mooney Aircraft Corporation (Mooney) Model M20R airplanes. This AD requires either fabricating and installing a placard that specifies using the air conditioning system during cruise operations only or deactivating the air conditioning system so it cannot be used. This AD is the result of reports of the existence of dangerous levels of carbon monoxide during taxi, climb, and descent operations of the above-referenced airplanes. The actions specified by this AD are intended to prevent dangerous levels of carbon monoxide from entering the airplane cabin during takeoff, climb, and descent operations caused by the present flight cabin sealing design of the affected airplanes, which could result in passenger injury.
AD 99-11-12 · published May 28, 1999, effective Jul 2, 1999
Boeing Model 747-400 Series Airplanes Powered by Pratt & Whitney PW4000 Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires repetitive inspections to ensure proper installation of the engine thrust link components, and follow-on corrective action, if necessary; and replacement of the forward engine mount end cap assembly with an improved end cap assembly. Such replacement, when accomplished, will terminate the repetitive inspections. This amendment is prompted by a report of fatigue cracking of end cap bolts, caused by improper installation. Subsequent investigation revealed that properly installed end caps also are subject to early fatigue cracking. 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 99-11-10 · published May 26, 1999, effective Jun 10, 1999
Eurocopter France Model AS 332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332L2 helicopters with a certain power-loss printed circuit board (PCB) installed. This action requires replacing that power-loss PCB with an airworthy power-loss PCB. This amendment is prompted by malfunctions discovered during environmental testing of the power-loss PCB conducted by the manufacturer. The actions specified in this AD are intended to prevent incorrect engine status indications, random activation of the maximum rotor revolutions-per-minute (RPM) alarm, and failure to reset the One- Engine Inoperative (OEI) logic after an actual loss of power from one engine.
AD 99-11-11 · published May 26, 1999, effective Jun 10, 1999
Eurocopter France Model SA-365N, N1, N2, N3, and SA-366G1 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model SA-365N, N1 and SA-366G1 helicopters, that currently requires repetitive inspections of the main gearbox (MGB) magnetic chip plug and oil filter if certain part number/ modification level MGB's are installed. This new action expands the helicopter model and MGB applicability to include the SA-365N2 and N3 helicopters and all variants of the MGB. It also requires installing a MGB planetary gear shaft (gear shaft) vibration level monitoring unit (VLMU); inserting procedures into the Rotorcraft Flight Manual (RFM) for a preflight vibration check using the VLMU and inserting a related emergency procedure and limitation for an inoperative VLMU into the RFM. This action is prompted by two occurrences of gear shaft cracks. The actions specified by this AD are intended to detect cracks in the MGB planetary gear shaft, which could lead to failure of the MGB and subsequent loss of control of the helicopter.
AD 99-10-11 · published May 13, 1999, effective Jun 14, 1999
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that currently requires periodic inspection of fan blades for locked rotors and foreign object damage (FOD), unlocking of shrouds if necessary, lubrication of fan blade shrouds, and dimensional restoration of the fan blade leading edge. In addition, that AD requires installation of improved design fan blades as terminating action for the inspections. This AD will reduce the lubrication interval, and require removal of rotors that experience repeat lockups within 225 cycles in service. This supersedure is prompted by reports of twenty-five fan blade failures to date. The actions specified by the AD are intended to prevent fan blade failure, which can result in damage to the aircraft.
AD 99-11-02 · published May 18, 1999, effective Jul 19, 1999
Pratt & Whitney R-1340 Series Reciprocating Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney R-1340 series reciprocating engines, that requires initial and repetitive visual and fluorescent penetrant inspections of cylinders for head cracking. This amendment is prompted by reports of cylinder head cracking. The actions specified by this AD are intended to prevent cylinder head cracking, which can result in engine power loss, forced landing, and damage to the aircraft.
AD 99-11-09 · published May 26, 1999, effective Jul 26, 1999
Pratt & Whitney JT9D Series Turbofan Engines
This document supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT9D series turbofan engines, that currently requires initial and repetitive in-shop or on-wing inspections of the diffuser case rear rail for cracking, and removal, if necessary, of the diffuser case. This AD will reduce the allowable crack length, reduce the inspection intervals, and introduce an improved inspection method. This AD is prompted by continued reports of diffuser case ruptures, and improved understanding of crack propagation rates. The actions specified by this AD are intended to prevent diffuser case rupture, uncontained engine failure, and damage to the aircraft.
AD 99-11-08 · published May 28, 1999
General Electric Aircraft Engines CF34 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CF34 series turbofan engines, that requires installation of a main fuel control (MFC) that incorporates a flange vent groove and installation of an MFC with improved overspeed protection. This amendment is prompted by reports of rapid uncommanded engine acceleration events. The actions specified by this AD are intended to prevent uncommanded engine accelerations, which could result in an engine overspeed, uncontained engine failure, and damage to the airplane.
AD 99-10-15 · published May 11, 1999, effective May 26, 1999
Eurocopter France Model AS332L2
This amendment adopts a new airworthiness directive (AD) that is applicable to AS332L2 helicopters. This action requires inspecting each main rotor head drag damper (damper) for a tear, crack, or bonding separation in the elastomer and, if necessary, replacing the damper with an airworthy damper. This amendment is prompted by a report of increased helicopter vibration in flight that was traced to the delamination of the elastomer on a damper. This condition, if not corrected, could result in failure of a damper and subsequent loss of control of the helicopter.
AD 99-11-03 · published May 18, 1999, effective Jun 2, 1999
Eurocopter France Model SA341G and SA342J
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA341G and SA342J helicopters. This action requires, before further flight, visually inspecting the external body of each main rotor head pitch-change rod (rod) for corrosion. If external corrosion is found, this action also requires a visual inspection of the inside of the body of that rod for corrosion. A rod with external corrosion that exceeds the repair criteria or a rod with any internal corrosion must be replaced with an airworthy rod. This amendment is prompted by the report of a deep internal corrosion fault in a rod found by a military helicopter operator performing a daily inspection. This condition, if not corrected, could result in failure of a rod and subsequent loss of control of the helicopter.
