48 Airworthiness Directives: 33 airplane, 10 rotorcraft, 4 engine, 1 appliance.
AD 99-05-02 · published Mar 1, 1999, effective Apr 5, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time detailed visual inspection of the outboard sequence carriage attachment fitting for the presence and condition of a shim and any loose fastener, and follow-on corrective actions, if necessary. This amendment is prompted by a report that a piece of the left wing inboard foreflap came off during a landing approach and struck and penetrated the airplane fuselage. The actions specified by this AD are intended to prevent the failure of the outboard sequence carriage fitting, which could allow the wing inboard foreflap to separate and penetrate the fuselage, possibly injuring passengers and crewmembers.
AD 99-05-03 · published Mar 1, 1999, effective Apr 5, 1999
Boeing Model 757-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires replacement of the stringer clip(s) with a new stringer clip(s), and modification of the life raft support structure and/or life raft doors, as applicable. This amendment is prompted by by a report that certain life raft stowage compartments and certain life raft doors are understrength. The actions specified by this AD are intended to prevent a life raft falling from its stowage compartment, and consequently injuring nearby occupants or delaying or impeding the evacuation of passengers during an emergency landing.
AD 99-05-06 · published Mar 3, 1999, effective Mar 18, 1999
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires a one-time inspection to detect cracking and corrosion of various areas at all four nacelle struts; and repair, if necessary. This amendment requires new repetitive inspections to detect fatigue cracking or loose or missing fasteners of the aft torque bulkheads of the outboard nacelle struts; and repair, if necessary. In addition, this action expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by a report indicating that cracking was found in the aft torque bulkheads of the outboard nacelle struts, and by the availability of new service instructions for detecting fatigue cracking that would not have been detected by the required actions of the existing AD. The actions specified in this AD are intended to detect and correct such fatigue cracking and loose or missing fasteners, which could result in failure of an outboard nacelle strut diagonal brace load path and possible separation of the nacelle from the wing.
AD 99-05-09 · published Mar 3, 1999, effective Mar 19, 1999
The New Piper Aircraft, Inc. PA-23, PA- 24, PA-28, PA-32, and PA-34 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) PA-23, PA-24, PA-28, PA-32, and PA-34 series airplanes that incorporate certain Facet (manufactured by the Purolator Products Company) induction air filters. This AD requires replacing these induction air filters. This AD results from reports of cracking, splitting, crumbling, and deterioration (referred to as damage hereon) of Facet/Purolator induction air filters manufactured between a certain time period. The actions specified by this AD are intended to prevent pieces of a damaged induction air filter from being ingested into the engine, which could result in reduced or loss of engine power.
AD 99-05-12 · published Mar 3, 1999, effective Mar 18, 1999
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, -300, -400, and - 500 series airplanes. This action requires removal of the float switch and wiring and inspection of the float switch wiring in the center fuel tank to detect discrepancies, and either reinstallation of existing float switch and wiring, or replacement of the float switch and wiring with a new float switch and wiring. This action also requires installation of Teflon sleeving over the wiring of the float switch. In lieu of the above mentioned requirements, this AD requires deactivation of the float switch, accomplishment of specific fueling procedures, and installation of Caution signs. This amendment is prompted by a report indicating that chafing of the direct current (DC) powered float switch wiring insulation in the center fuel tank has occurred on several airplanes. The actions specified in this AD are intended to detect and correct such chafing and the resultant arcing from the wiring to the in-tank conduit, which could present an ignition source inside the fuel tank and consequent fire/explosion.
AD 99-05-10 · published Mar 5, 1999, effective Apr 9, 1999
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires revising the maintenance program to require verification that a certain shipping container and shipping sleeve assembly were used in shipping the ram air turbine (RAT) deployment actuator. This amendment also requires inspection of the identification plate on the RAT deployment actuator to determine the actuator serial numbers or a records check to determine such information; and repair or replacement of certain RAT deployment actuators, if necessary. This amendment is prompted by reports of certain RAT actuators that failed to deploy upon command due to interference in the actuator locking mechanism caused by damage incurred during shipping of the actuators. Failure of the RAT to deploy, specifically during a dual engine failure, would result in loss of hydraulic power and would adversely affect the continued safe flight and landing of the airplane.
AD 99-05-11 · published Mar 5, 1999, effective Apr 9, 1999
British Aerospace Model BAC 1-11 200 and 400 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires repetitive visual inspections to detect cracks in the flight deck canopy area, and repair, if necessary; and repetitive detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5, and replacement of cracked parts with new parts, or repair of the top sill members. This amendment continues to require detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5. This amendment also adds a requirement for a one-time inspection to determine the type of fasteners installed in certain holes of the joint strap installation, and replacement of rivets with bolts, if necessary. 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 detect and correct cracking in the flight deck canopy area, which could result in reduced structural integrity of the flight deck frame and adjacent fuselage structure.
AD 99-05-13 · published Mar 5, 1999, effective Apr 19, 1999
Raytheon Aircraft Company 17, 18, 19, 23, 24, 33, 35, 36/A36, A36TC/B36TC, 45, 50, 55, 56, 58, 58P, 58TC, 60, 65, 70, 76, 77, 80, 88, and 95 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 17, 18, 19, 23, 24, 33, 35, 36/A36, A36TC/B36TC, 45, 50, 55, 56, 58, 58P, 58TC, 60, 65, 70, 76, 77, 80, 88, and 95 series airplanes. This AD requires installing a placard on the fuel tank selector to warn of the no-flow condition that exists between the fuel tank detents. This AD is the result of reports of engine stoppage on the affected airplanes where the cause was considered to be incorrect positioning of the fuel selector. The actions specified by this AD are intended to help prevent a lack of fuel flow to the engine caused by incorrect positioning of the fuel selector, which could result in loss of engine power.
AD 99-05-15 · published Mar 8, 1999, effective Mar 23, 1999
Boeing Model 737-100, -200, -200C, - 300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action requires a one-time inspection of the attachment nuts at each end attachment of the elevator tab push rods to measure run-on torque values, and corrective actions, if necessary. This amendment is prompted by reports of excessive high- frequency airframe vibration during flight, with consequent structural damage to the elevator tab, elevator, and stabilizer. The actions specified in this AD are intended to prevent detachment of an elevator tab push rod due to a detached nut at either end attachment of a push rod, which could result in excessive high-frequency airframe vibration during flight; consequent structural damage to the elevator tab, elevator, and horizontal stabilizer; and reduced controllability of the airplane.
AD 99-06-01 · published Mar 10, 1999, effective Apr 20, 1999
The New Piper Aircraft, Inc. Models PA- 31, PA-31-300, PA-31-325, PA-31-350, and PA-31P-350 Airplanes
This amendment supersedes Airworthiness Directive (AD) 81-15- 04 R1, which currently requires repetitively inspecting for cracks at the elevator outboard hinge attachment on the horizontal stabilizer rear spar on certain The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-31-300, PA-31-325, PA-31-350, and PA-31P-350 airplanes, and if cracks are found, incorporating a spar and hinge bracket assembly kit. This AD requires repetitively inspecting the horizontal rear spar in the area of the outboard hinge attachment and the outboard hinge attach bracket for cracks. When cracks are found or at a certain accumulation of time-in-service (TIS), this AD also requires modifying the horizontal stabilizer spar by incorporating an improved stabilizer spar and hinge bracket assembly kit that will terminate the repetitive inspections. This AD is prompted by several field reports of cracks found during routine inspections on airplanes already in compliance with AD 81-15-04 R1. The actions specified by this AD are intended to prevent failure of the horizontal stabilizer rear spar caused by cracks at the elevator outboard hinge attachment, which could result in loss of control of the airplane.
AD 99-06-02 · published Mar 10, 1999, effective Apr 16, 1999
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. This AD requires repetitively inspecting the wing spar center web cutout on both wings for cracks between Wing Station (WS) 8 and WS 17.5, and immediately repairing any area found cracked. This repair will eliminate the need for the repetitive inspections on that particular wing spar. This AD is the result of reports of cracks in the wing spar center web cutout caused by fatigue due to airplane maneuvering and wind gusts. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing spar center web cutout area, which could result in structural failure of the wing spar to the point of failure with consequent loss of control of the airplane.
AD 99-06-05 · published Mar 12, 1999, effective Apr 16, 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 removing the ``Alternate Flap System'' from the airplane flight controls and inserting a temporary revision that specifies this change in SECTION 2--LIMITATIONS of the PC-12 Pilot's Operating Handbook. 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 preclude improper use of the ``Alternate Flap System'', which could result in flap asymmetry with consequent reduced or loss of control of the airplane.
AD 99-06-06 · published Mar 12, 1999, effective Apr 16, 1999
Airbus Model A310 and A300-600 Series Airplanes Equipped With General Electric CF6-80C2 Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive flow checks of the hydraulic pump drain system to ensure that the system is not clogged, and correction of any discrepancy. This amendment also requires replacement of the existing magnetic seals of the accessory gearbox assembly with new, improved seals. Replacement of certain seals terminates the requirement for repetitive flow checks. This amendment also requires replacement of the engine drain modules with drain manifolds. 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 contamination of the engine accessory gearbox oil with hydraulic fluid, which could result in an in-flight engine shutdown.
AD 99-06-07 · published Mar 12, 1999, effective Apr 16, 1999
Short Brothers Model SD3-60 and SD3-60 SHERPA Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 and SD3-60 SHERPA series airplanes, that requires repetitive inspections to detect corrosion and/or wear of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the main landing gear (MLG), and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion and/or wear of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the MLG, which could result in failure of the MLG to extend or retract.
AD 99-06-08 · published Mar 12, 1999, effective Apr 16, 1999
McDonnell Douglas Model DC-10 and MD-11 Series Airplanes, and KC-10 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 and MD-11 series airplanes, and KC-10 (military) series airplanes, that requires a one- time inspection for blockage of the lubrication holes on the forward trunnion spacer assembly, and a one-time inspection of the forward trunnion bolt on the left and right main landing gear (MLG) to detect discrepancies; and repair, if necessary. This amendment is prompted by reports of blockage by opposing bushings of the lubrication holes on the forward trunnion spacer assembly, and reports of flaking, galling, and corrosion of the forward trunnion bolt. The actions specified by this AD are intended to detect and correct such flaking, galling, and corrosion of the forward trunnion bolt, which could result in premature failure of the forward trunnion bolt and could lead to separation of the MLG from the wing during takeoff and landing.
AD 99-06-09 · published Mar 12, 1999, effective Apr 16, 1999
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires an electrical continuity test of the discharge circuit for the cargo compartment fire extinguisher bottle to detect any cross-connection of the electrical wires in the cargo compartment discharge circuit, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent incorrect distribution of fire extinguishing chemicals in the event of a fire in the cargo compartment, which, if unconfined, could spread beyond the cargo compartment.
AD 99-06-10 · published Mar 12, 1999, effective Apr 16, 1999
Airbus Model A300 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that requires replacement of the rivets that attach the pressurized floor panel to gantries 4 and 5 with new titanium alloy bolts. This amendment also requires, for certain airplanes, repetitive inspections to detect discrepancies of the rivets; and corrective actions, if necessary. 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 failure of the rivets that attach the pressurized floor panel to gantries 4 and 5, which could result in the loss of the floor panel and consequent rapid decompression of the airplane.
AD 99-06-11 · published Mar 18, 1999, effective Apr 26, 1999
British Aerospace HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires inspecting the elevator bias spring assembly for correct installation and to assure that the correctly manufactured bias spring is installed. This AD also requires replacing any incorrectly manufactured bias spring, reworking any incorrectly installed bias spring assembly, inspecting the link assembly for distortion or damage, and replacing any distorted and/or damaged parts. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the bearings in the elevator down bias spring assembly caused by the installation of an incorrectly manufactured bias spring or damage or distortion to the assembly, which could result in reduced or loss of control of the airplane.
AD 99-06-12 · published Mar 18, 1999, effective Apr 26, 1999
British Aerospace HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires replacing the nose wheel steering jack seals with seals of an improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the nose landing gear steering from locking up due to deterioration of the original design nose landing gear steering jack seals, which could result in reduced or loss of control of the airplane during takeoff, landing, and taxi operations.
AD 99-06-13 · published Mar 18, 1999, effective Apr 22, 1999
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires inspection(s) to detect fatigue cracking of the shock strut cylinder of the main landing gear (MLG), and replacement of any cracked shock strut cylinder with a serviceable part. That AD also provides for installation of brake line hydraulic restrictors on the MLG brake systems, which, if accomplished, terminates the repetitive inspections. This amendment requires that the subject inspection be accomplished repetitively following installation of brake line hydraulic restrictors. This amendment is prompted by an additional report of fatigue cracking and subsequent fracturing of the shock strut cylinder of the MLG. The actions specified by this AD are intended to prevent collapse of the MLG due to fracturing of the shock strut cylinder.
AD 99-06-14 · published Mar 18, 1999, effective Apr 22, 1999
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires one-time visual inspections of the elevator trim system for paint contamination on the actuator pistons and to determine the moisture level of the moisture indicator; verification of the installation and condition of the gasket of the flex drive; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the elevator trim system due to paint/moisture contamination, and consequent reduced controllability of the airplane.
AD 99-06-18 · published Mar 22, 1999, effective Apr 26, 1999
Boeing Model 747-400, -400D, and -400F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, that requires modification of the P212 and P213 panels of the cabin pressure control system. For certain airplanes, this amendment also requires modification of the P5, P6, and P7 panels, and the W4701, W4703, and W4908 wire bundles, as applicable. This amendment is prompted by a report of in-flight loss of cabin pressurization control due to a single failure of the auxiliary power unit (APU) battery. The actions specified by this AD are intended to prevent loss of control of the cabin pressurization system, which could result in rapid depressurization of the airplane. Such rapid depressurization could result in deleterious physiological effects on the passengers and crew; and airplane diversions, which represent an increased risk to the airplane, passengers, and crew.
AD 98-13-35 R1 · published Mar 23, 1999, effective Jul 30, 1998
McDonnell Douglas Model DC-9 and DC-9- 80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes
This amendment corrects information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or longeron, and various follow-on actions. That AD also requires installation of a preventative modification, which terminates the repetitive inspections. The actions specified in that AD are intended to prevent fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane. This amendment corrects the requirements of the current AD by indicating the specific area in which the subject inspection must be conducted. This amendment is prompted by communication received from the manufacturer that the current requirements of the AD are different than the service information referenced as the appropriate service information in the current AD.
AD 99-05-04 · published Mar 23, 1999, effective Mar 29, 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) 99-05-04 that was sent previously to all known U.S. owners and operators of all EMBRAER Model EMB-145 series airplanes by individual notices. This AD requires repetitive inspections to detect cracking or failure of the rod ends of the aileron power control actuator (PCA), and corrective actions, if necessary. 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 detect and correct cracking or failure of the rod ends of the aileron PCA, which could result in reduced controllability of the airplane.
AD 99-06-17 · published Mar 23, 1999, effective Jun 16, 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 installing a support bracket and a cut-out relay for the second generator control unit. This AD also requires making all the wiring additions and adjustments necessary for the above-referenced installations. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to prevent damage to electrical components because incorrectly connected cables or broken or damaged wires cause excessive voltages to the second generator, which could result in loss of electrical power during any phase of flight.
AD 99-07-03 · published Mar 23, 1999, effective Apr 27, 1999
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect cracks in the edge frame web and doubler of the number 1 main entry door cutout; and repair, if necessary. This AD also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports indicating that fatigue cracks were found in the edge frame web and doubler at the door stop number 1 of the number 1 main entry door cutout. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the airplane.
AD 99-07-05 · published Mar 26, 1999, effective Apr 30, 1999
Lockheed Model L-1011-385 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires repetitive external visual inspections and internal borescope inspections to detect discrepancies of the elevator assembly; and either repair or repair/modification of certain identified discrepancies. This amendment is prompted by a report of fretting at the diagonal truss to web joint of the elevator and cracking in the cap fillet radius adjacent to the joint, apparently due to loose fasteners as a result of local vibration. The actions specified by this AD are intended to detect and correct such fretting and cracking, which could result in reduced structural integrity of the elevator and consequent flutter instability if coupled with other structural failures.
AD 99-07-06 · published Mar 26, 1999, effective Apr 12, 1999
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut, and follow-on actions, if necessary. This action also provides optional terminating action for the repetitive inspections. This amendment is prompted by a report that a fractured diagonal brace lug was found during a routine maintenance inspection. The actions specified in this AD are intended to detect and correct cracking of the diagonal brace of the nacelle strut, which could result in failure of the diagonal brace, and consequent fatigue failure of a strut secondary load path and separation of the engine and strut.
AD 99-07-09 · published Mar 26, 1999, effective May 10, 1999
British Aerospace Jetstream Model 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3201 airplanes. This AD requires replacing the nose landing gear downlock actuator, the flap actuator, the steering selector valve, the hydraulic reservoir, and the emergency selector valve. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent internal corrosion of the hydraulic components on airplanes where these components were exposed to water contamination, which could result in reduced or loss of control of the airplane.
AD 99-07-10 · published Mar 29, 1999, effective May 10, 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 the upper and lower engine nacelle inner panels for any loose or partially detached inner film, and removing any loose or partially detached inner film. 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 the accumulation of loose particles on the engine inlet screen caused by film delamination, which could result in reduced engine power and possible loss of airplane control.
AD 99-07-11 · published Mar 29, 1999, effective Apr 16, 1999
SOCATAGroupe Aerospatiale Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Model TBM 700 airplanes. This AD requires inspecting the left-hand and right-hand outboard hinge fittings of the horizontal stabilizer for cracks, and replacing any cracked fitting. 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 structural damage to the stabilizer caused by outboard hinge fitting cracks, which could result in uncontrolled flight if the hinges break.
AD 99-02-18 R1 · published Mar 30, 1999, effective Mar 3, 1999
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment corrects information in an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB- 120 series airplanes, that currently 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, that amendment also currently requires installing new stainless steel plates onto the upper rear nacelle structure. The actions specified in that 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. This amendment corrects the requirements of the existing AD by correcting affected spare part numbers of thermal insulating blankets. This amendment is prompted by review of the requirements of the existing AD.
AD 99-07-12 · published Mar 31, 1999, effective May 5, 1999
Boeing Model 747-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires repetitive inspections to detect cracking of certain lower lobe fuselage frames, and repair, if necessary. This amendment is prompted by reports indicating that fatigue cracks were found in lower lobe frames on the left side of the fuselage. The actions specified by this AD are intended to detect and correct fatigue cracking of certain lower lobe fuselage frames, which could lead to fatigue cracks in the fuselage skin, and consequent rapid decompression of the airplane.
AD 99-05-07 · published Mar 3, 1999, effective May 3, 1999
Bell Helicopter Textron, Inc. Model 214B and 214B-1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B and 214B- 1 helicopters, that requires creation of a component history card or an equivalent record using the Retirement Index Number (RIN) system, establishing a system for tracking increases to the accumulated RIN, and establishing a maximum accumulated RIN for the pillow block bearing bolts (bearing bolts) of 17,000 before they must be removed from service. This amendment is prompted by fatigue analyses and tests that show certain bearing bolts fail sooner than originally anticipated because of the unanticipated high number of lifts and takeoffs (torque events) performed with those bearing bolts in addition to the time-in- service (TIS) accrued under other operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the bearing bolts, which could result in failure of the main rotor system and subsequent loss of control of the helicopter.
AD 99-05-08 · published Mar 3, 1999, effective Mar 18, 1999
McDonnell Douglas Helicopter Systems Model MD-900 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD- 900 helicopters. This action requires establishing or reducing certain life limits, applying serial numbers (S/N's), determining hours time- in-service (TIS), and creating component history cards or equivalent records for various parts. This amendment is prompted by analysis that indicates a need for establishing or reducing life limits to avoid fatigue failure of certain parts. The actions specified by this AD are intended to apply appropriate life limits to various parts.
AD 99-05-14 · published Mar 3, 1999, effective Apr 7, 1999
Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters, that requires inspecting the main rotor blade cuff attachment fitting in the area of the main rotor blade (blade) attachment bolts for cracks, and removing and replacing the blade if a crack is found. This amendment is prompted by a report of a crack in a blade cuff attachment fitting/spar assembly that was discovered during fatigue testing by the manufacturer. The actions specified by this AD are intended to prevent failure of a blade cuff attachment fitting at a bolt hole location, loss of a blade, and subsequent loss of control of the helicopter.
AD 99-06-03 · published Mar 9, 1999, effective Apr 13, 1999
Eurocopter France Model AS-365N, N1, and N2 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS-365N, N1, and N2 helicopters, that requires inspecting the helicopter to determine if a certain main rotor head frequency adapter (frequency adapter) is installed and, if so, replacing it with an airworthy frequency adapter. This amendment is prompted by a report of disbonding of the metal center section of a frequency adapter from the elastomer on a main rotor head caused by a lack of adherence during the production process. The actions specified by this AD are intended to prevent increased vibrations caused by disbonding of the center section of a frequency adapter from the elastomer and subsequent reduced controllability of the helicopter.
AD 99-06-04 · published Mar 10, 1999, effective Apr 14, 1999
Eurocopter France Model AS 332C, L, and L1, and L2 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters that requires replacing certain circuit breakers. This amendment is prompted by the manufacturer discovering, upon testing a circuit breaker installed in a helicopter, the loss of electrical continuity between the terminals of the installed circuit breaker. The actions specified by this AD are intended to prevent loss of electrical power caused by improper installation of certain circuit breakers, loss of electical power to instrumentation, and subsequent loss of control of the helicopter.
AD 99-03-10 · published Mar 19, 1999, effective Apr 5, 1999
Agusta S.p.A. (Agusta) Model A109E Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-03-10 which was sent previously to all known U.S. owners and operators of Agusta Model A109E helicopters by individual letters. This AD requires, before further flight, inspections of the exhaust ejector locking system, clamp, and dampers for each engine. This AD also requires, at specified time intervals, verifying the torque of the metallic clamps and installing safety wire on the metallic clamps; inspecting and modifying the ejector saddles and the locking metallic clamps; and inspecting the metallic clamps, locking mechanisms, and dampers. This amendment is prompted by an inflight incident in which a metallic clamp which secured the left-hand engine exhaust ejector to the ejector saddle became detached and subsequently separated from the helicopter. The actions specified by this AD are intended to prevent loss of the metallic clamp or the engine exhaust ejector, which could result in damage to the main or tail rotor system and subsequent loss of control of the helicopter.
AD 99-07-01 · published Mar 23, 1999, effective Apr 7, 1999
Sikorsky Aircraft Corporation (Sikorsky) Model S-76C Helicopters
This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Sikorsky Model S-76C helicopters, that currently requires, before further flight, inserting new operating limitations and performance data into the Rotorcraft Flight Manual (RFM) which require lower allowable gross weights for certain operational conditions. This amendment requires the same actions as the priority letter AD, but updates the previously referenced RFM's. This amendment is prompted by the discovery that the RFM's referenced in the priority letter AD have been revised. The actions specified by this AD are intended to provide the correct RFM references and to prevent an inability to achieve the published One- Engine-Inoperative (OEI) performance and subsequent loss of control of the helicopter.
AD 99-07-02 · published Mar 23, 1999, effective Apr 7, 1999
Eurocopter France Model AS 332C, L, L1, and L2 Helicopters and Model SA 330F, G, and J Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters and Model SA 330F, G, and J helicopters. This action requires inspecting the position and bonding of the main rotor blade (blade) leading edge stainless steel protective strips (strips) that were replaced by C.T.I. Dallas. This amendment is prompted by the discovery of a strip that was both mislocated and improperly bonded. The strip had been replaced by C.T.I. Dallas. This condition, if not corrected, could result in failure of the blade and subsequent loss of control of the helicopter.
AD 99-07-07 · published Mar 26, 1999, effective Apr 12, 1999
Eurocopter France Model SA 330J Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France (Eurocopter) Model SA 330J helicopters. This action requires the visual inspection and, if any crack is found, replacement of the affected main rotor head sleeve. This amendment is prompted by the discovery of a crack through the thickness of a lower lug of a blade sleeve. The actions specified by the proposed AD are intended to prevent failure of a main rotor head sleeve that could result in the loss of a main rotor blade and subsequent loss of control of the helicopter.
AD 99-07-08 · published Mar 29, 1999, effective Apr 13, 1999
Eurocopter France Model SA. 315B Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA. 315B helicopters. This action requires inspecting the spar skin and main rotor blade (blade) root reinforcement strip area for bonding separation, corrosion, or a crack, and replacing the blade, if necessary. This amendment is prompted by the in-flight failure of a blade. The actions specified in this AD are intended to detect bonding separation, corrosion, or a crack in the area of the blade root reinforcement strip, which could result in failure of the blade and subsequent loss of control of the helicopter.
AD 99-05-05 · published Mar 1, 1999, effective Apr 30, 1999
International Aero Engines AG (IAE) V2500-A1 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to International Aero Engines AG (IAE) V2500-A1 series turbofan engines, that requires initial and repetitive inspections of certain High Pressure Turbine (HPT) stage 1 and stage 2 disks utilizing an improved ultrasonic method when the disks are exposed during a normal shop visit, and if a subsurface anomaly is found, removal from service and replacement with a serviceable part. This amendment is prompted by the results of a stage 1 HPT disk fracture investigation which has identified a population of HPT stage 1 and 2 disks that may have subsurface anomalies formed as a result of the processes used to manufacture the material. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure, and damage to the airplane.
AD 99-06-16 · published Mar 22, 1999, effective Apr 21, 1999
CFM International CFM56-5 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-5 series turbofan engines, that reduces the low cycle fatigue (LCF) retirement lives for certain high pressure turbine rotor (HPTR) front air seals, and provides a drawdown schedule for those affected parts with reduced LCF retirement lives. This amendment is prompted by results of a refined life analysis performed by the manufacturer that revealed minimum calculated LCF lives significantly lower than the published LCF retirement lives. The actions specified by this AD are intended to prevent a LCF failure of the HPTR front air seal, which could result in an uncontained engine failure and damage to the aircraft.
AD 99-07-04 · published Mar 24, 1999, effective May 24, 1999
Williams International, L.L.C. FJ44-1A Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Williams International, L.L.C. FJ44-1A turbofan engines, that requires removing the high pressure turbine (HPT) disk from service prior to accumulating a reduced cyclic life limit of 1,900 cycles since new (CSN) and replacing with a serviceable disk. As an option, the HPT nozzle can be modified, thereby increasing the HPT disk cyclic life limit from the new reduced cyclic life limit. This amendment is prompted by a revised life analysis conducted by the manufacturer after the failure of a similarly designed HPT disk. The actions specified by this AD are intended to prevent HPT disk rim failure, which could result in an uncontained engine failure and damage to the aircraft.
AD 99-04-15 · published Mar 26, 1999, effective Apr 12, 1999
Dr.Ing.h.c.F. Porsche Aktiengesellschaft (Porsche) 3200N01, N02, and N03 Reciprocating Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-04-15 that was sent previously to all known U.S. owners and operators of Porsche PFM3200N01, N02, and N03 reciprocating engines by individual letters. This AD requires replacement of valve springs prior to further flight on PFM3200N01, N02, and NO3 engines. This amendment is prompted by reports of six cases of undetected fatigue failures of valve springs, with one valve spring failure causing an in-flight engine failure that ended in an emergency landing. The actions specified by this AD are intended to prevent an in-flight engine shutdown due to undetected fatigue failures of valve springs.
AD 97-05-03 R1 · published Mar 10, 1999, effective Apr 20, 1999
AlliedSignal Avionics, Inc. Models GNS- Xls and GNS-Xl Flight Management Systems
This amendment revises Airworthiness Directive (AD) 97-05-03, which currently requires inserting a limitation into the Operations Limitation Section of the Airplane Flight Manual (AFM) or Flight Manual Supplement for all owners/operators of aircraft equipped with an AlliedSignal Avionics, Inc. (AlliedSignal) Models GNS-Xls or GNS-Xl global positioning systems (GPS) flight management system. The limitation specifies prohibiting the use of these AlliedSignal GPS units on previously published non-precision approaches. This AD is the result of AlliedSignal issuing service information that specifies procedures for accomplishing hardware and software modifications to the affected flight management systems. The Federal Aviation Administration (FAA) determined that accomplishment of the actions of the service bulletins should be considered as an alternative method of compliance to the actions of AD 97-05-03. This AD retains the actions of AD 97-05- 03, and incorporates the service bulletins into the AD, as an alternative method of compliance to the existing AD. The actions specified by this AD are intended to continue to prevent deviation from an intended flight path during a non-precision approach to an airport caused by inaccurate information from the GPS flight management system.
