34 Airworthiness Directives: 28 airplane, 4 rotorcraft, 1 engine, 1 glider.
AD 96-07-07 · published May 1, 1996, effective May 1, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires an inspection to verify the proper position of "door open" placards on the inside of the main entrance door, and replacement with new placards appropriately positioned, if necessary. This amendment is prompted by a report that the "door open" placards on the inside of the main entrance door, as currently installed, may not be visible to passengers or flightcrew when the door handle is in the open position. The actions specified by this AD are intended to ensure that certain placards on the inside of the main entrance door are clearly visible and perform their intended function in the event of an emergency evacuation.
AD 96-09-08 · published May 2, 1996, effective May 20, 1996
Aviat Aircraft Inc. Models S-2A, S-2B, and S-2S Airplanes (Formerly Pitts Models S-2A, S-2B, and S-2S Airplanes)
This amendment adopts a new airworthiness directive (AD) that is applicable to Aviat Aircraft Inc., Models S-2A, S-2B, and S-2S airplanes (formerly Pitts Models S-2A, S-2B, and S-2S airplanes). This action requires inspecting the longerons aft of the rear cabane struts for cracks, and if cracked, prior to further flight, repairing the cracks. Reports of longeron failure caused by fatigue aft of the rear cabane struts prompted this action. The actions specified by this AD are intended to prevent cracking and subsequent failure of the longerons resulting in possible loss of control of the airplane.
AD 96-09-04 · published May 3, 1996, effective May 17, 1996
de Havilland Model DHC-3 Airplanes
This amendment supersedes Airworthiness Directive (AD) 90-12- 08, which currently requires the following on de Havilland Model DHC-3 airplanes: repetitively inspecting (using dye penetrant methods) the tailplane main rib forward flanges and the main rib forward lower flanges at the tailplane front attachment fitting for cracks and repairing any cracked flange. This AD action will retain the repetitive inspections currently required by AD 90-12-08, and will allow a certain modification as terminating action for these repetitive inspections. This action is prompted by the Federal Aviation Administration's determination that installing new angles and plates on the tailplane root ribs on de Havilland Model DHC-3 airplanes provides an equivalent level of safety to the repetitive inspections required by AD 90-12-08. The actions specified by this AD are intended to prevent failure of the tailplane structure caused by cracked tailplane main rib forward flanges or main rib forward lower flanges at the tailplane front attachment fitting, which, if not detected and corrected, could result in loss of control of the airplane.
AD 96-09-09 · published May 3, 1996, effective Jun 7, 1996
Piaggio Aero Industries S.p.A. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to I.A.M. Rinaldo Piaggio S.p.A. Model P 180 series airplanes. This action requires installing a shield on the front section of the engine cradle. A report of power control jamming as a result of freezing conditions during a high altitude flight prompted this AD action. The actions specified by this AD are intended to prevent loss of engine power or the propeller controls from jamming as a result of freezing rain entering the engine nacelle, which, if not detected and corrected, could result in loss of control of the airplane.
AD 96-10-03 · published May 3, 1996, effective Jun 14, 1996
Piper Aircraft Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) PA28, PA32, PA34, and PA44 series airplanes. This action will require inspecting and modifying the flap lever assembly. Reports of worn flap handle attach bolts and elongated holes in the flap lever to cable mounting attach point prompted this AD action. The actions specified by this AD are intended to prevent failure of the flap handle attach bolt and sudden retraction of the flaps, which, if not detected and corrected, could result in loss of control of the airplane.
AD 96-21-04 · published May 3, 1996, effective Dec 10, 1996
Piper Aircraft Inc. Airplanes
This amendment supersedes Airworthiness Directive (AD) 86-17-07, which currently requires replacing all hydraulic hoses with hydraulic hoses of an improved design on certain The New Piper Aircraft, Inc. (Piper) PA23, PA31, PA31P, PA31T, and PA42 series airplanes. This AD action will require inspecting for improperly manufactured hydraulic hoses replaced during a specific time frame and replacing all affected hydraulic hoses. An incorrect designation of a Piper Model PA31-310 and a Piper Model PA23-150 airplane prompted the proposed AD action. The actions specified by this AD are intended to prevent hydraulic hose failure which could cause loss of hydraulic capabilities resulting in a gear-up landing and possible loss of the airplane.
AD 96-10-05 · published May 6, 1996, effective Jun 21, 1996
Maule Aerospace Technology, Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Maule Aerospace Technologies, Inc. (Maule) Models M-4-210 and M-4-210C airplanes that have Dual Exhaust System 5230F installed. This action requires relocating the gascolator and electric fuel pump away from the dual exhaust system. The Federal Aviation Administration (FAA) recently became aware that, with these dual exhaust systems installed on the affected airplanes, the left-hand exhaust stack is routed almost directly below the fuel gascolator. The close proximity of the flammable fuel to the exhaust system presents an unsafe condition and violates current regulations. The actions specified by this AD are intended to prevent an airplane engine fire caused by the close proximity of the fuel gascolator and electric fuel pump to the exhaust system.
AD 96-09-11 · published May 7, 1996, effective Jun 11, 1996
de Havilland, Inc. DHC-6 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to de Havilland DHC-6 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
AD 96-09-15 · published May 7, 1996, effective Jun 11, 1996
Cessna Aircraft Company Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
AD 96-10-06 · published May 9, 1996, effective May 24, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737 series airplanes. This action requires repetitive inspections to detect cracks of the lower gate hinge of the forward galley service door, and replacement of any cracked hinge. This action also provides an optional terminating replacement for the repetitive inspections. This amendment is prompted by reports of fatigue cracks found in the lower gate hinge on the forward galley service door. The actions specified in this AD are intended to prevent such fatigue cracking, which could lead to the failure of the lower gate hinge on the forward galley service door and subsequent loss of cabin pressure. If the hinge fails, the hinge and its associated mechanisms and the emergency escape slide could separate from the airplane and be ingested into the engine, or could strike and damage the flight control surfaces.
AD 96-10-07 · published May 9, 1996, effective May 24, 1996
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires inspections to detect damage of the support brackets and clamps of the transfer pipe of the tail tank, and of the transfer pipe assembly; and replacement of damaged parts, or installation of a doubler, if necessary. This amendment is prompted by reports of cracking of the support brackets in the refuel and fuel transfer lines of the tail fuel tank and damage to the nylon clamps and transfer pipe assembly; such damage is due to flexing of the brackets and subsequent contact of the transfer pipe assembly with adjacent structure. The actions specified in this AD are intended to prevent such cracking and damage, which could result in further damage to the transfer pipe assembly and possible fuel leakage.
AD 96-01-04 R1 · published May 10, 1996, effective May 10, 1996
Saab AB, Saab Aerosystems Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to require verification that the auto-ignition system is operational; to define icing conditions at higher ambient temperatures; and to provide the flight crew with limitations and procedures to aid in the avoidance of engine power interruptions. The actions specified by that AD are intended to prevent failure of the auto-ignition system to re-light the engine in the event of power interruptions due to the ingestion of ice and/or slush into the engine, which could result in engine flameout and subsequent shutdown, and to provide the flight crew with guidance to aid in avoidance of such occurrences. This amendment clarifies certain requirements of the AFM revision. This amendment is prompted by communications received from affected operators that certain of the currentrequirements of the AD are unclear.
AD 96-10-08 · published May 14, 1996, effective Jun 13, 1996
Boeing Model 737-300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires inspection to detect damage of a wire bundle and clamp that are located in the electronic/electrical (E/E) equipment bay, and repair of the damaged wire bundle. That action also requires replacement of the existing steel clamp with a nylon clamp, and rearrangement of the clamp installation. This amendment is prompted by a report of fire in the E/E equipment bay due to electrical arcing caused by chafing of a wire bundle. The actions specified by this AD are intended to prevent chafing of a wire bundle that could cause short circuiting of the wire bundle, and could result in smoke and fire in the E/E equipment bay.
AD 96-10-11 · published May 16, 1996, effective Jun 20, 1996
McDonnell Douglas Model DC-9 and DC-9- 80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires certain inspections and structural modifications. This amendment requires additional inspections and structural modifications. This amendment is prompted by an evaluation conducted by the Airworthiness Assurance Working Group, which identified additional inspections and structural modifications for mandatory action. The actions specified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes.
AD 96-10-12 · published May 16, 1996, effective Jun 7, 1996
Aviat Aircraft Inc Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B airplanes that are equipped with a flight control stick with a wall thickness of .035 inch. This action requires repetitively inspecting the flight control stick for cracks, and replacing any cracked flight control stick with one with a wall thickness of .058 inch. An incident on an Aviat Model S-2A airplane where the flight control stick fractured in flight prompted this action. The actions specified by this AD are intended to prevent the inability to maneuver the airplane because of a cracked flight control stick, which, if not detected and corrected, could result in loss of control of the airplane. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 7, 1996. Comments for inclusion in the Rules Docket must be received on or before July 19, 1996.
AD 96-10-13 · published May 16, 1996, effective Jun 27, 1996
Piper Aircraft Inc. Airplanes
This amendment supersedes Airworthiness Directive (AD) 84-08-06, which currently requires the following on certain The New Piper Aircraft, Inc. (Piper) Models PA31T, PA31T1, PA31T2, and PA31T3 airplanes: repetitively inspecting the fuselage station (FS) 332 bulkhead for cracks, and reinforcing or replacing the FS 332 bulkhead if cracks are found. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action retains the current repetitive inspections contained in AD 84-08-06, and requires incorporating a stabilizer forward spar attachment bulkhead reinforcement kit or installing a reinforced bulkhead assembly as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent structural failure of the horizontal stabilizer and the aftfuselage attachment caused by cracks in the FS 332 bulkhead, which, if not detected and corrected, could result in loss of control of the airplane.
AD 96-10-16 · published May 16, 1996, effective Jun 20, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires inspections to detect damage of the sidewall vent box diaphragms, and repair, if necessary. This amendment also requires the eventual installation of stops on the vent box diaphragm, which terminates the inspection requirements of the AD. This amendment is prompted by reports of damage to sidewall vent box diaphragms, which can result in non-functional diaphragms during a rapid decompression. The actions specified by this AD are intended to prevent buckling of the floor beams due to insufficient air flow of the cabin sidewall vent box diaphragms during rapid decompression, and consequent reduction in the controllability of the airplane.
AD 96-10-17 · published May 16, 1996, effective Jun 20, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, and -30 series airplanes and KC-10A (military) airplanes, that requires inspections to detect cracks of the upper aft mating bolt hole of the wing pylon truss fittings, and various follow-on actions. This amendment is prompted by reports of cracks found in the upper aft mating bolt hole of the wing pylon truss fitting located near the engine forward mount on Model DC-10-30 series airplanes, which were caused by fatigue-related stress. The actions specified by this AD are intended to prevent fatigue-related cracking, which could lead to failure of the fitting, separation of a portion of the engine forward mount truss from the pylon, and consequent separation of the engine from the airplane.
AD 96-09-05 · published May 17, 1996, effective May 17, 1996
Diamond Aircraft Industries Inc Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to Diamond Aircraft Industries (Diamond) Model DA 20-A1 airplanes. This action requires inspecting the aft wing cavities for manufacturing debris, removing any debris found, and modifying the aileron pushrod fairings to allow them to flex. Several reports of the aileron controls becoming blocked because of manufacturing debris getting jammed between the short aileron pushrod and the pushrod exit fairing on both left and right wings prompted this action. The actions specified by this AD are intended to prevent the aileron controls from becoming blocked causing jamming between the short aileron pushrod and the pushrod fairing exit, which, if not detected and corrected, could cause loss of control of the airplane.
AD 96-10-14 · published May 17, 1996, effective Jun 27, 1996
The New Piper Aircraft, Inc. (Formerly Piper Aircraft Corporation) PA31, PA31P, and PA31T Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 88-05- 05, which currently requires the following on certain The New Piper Aircraft, Inc. (Piper) PA31, PA31P, and PA31T series airplanes: repetitively inspecting both the left and right main landing gear (MLG) forward sidebrace, and replacing any cracked MLG forward sidebrace. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action retains the current repetitive inspection and necessary replacement requirements contained in AD 88- 05-05, and requires incorporating both a left and right MLG forward sidebrace of improved design as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent the MLG from retracting because of a cracked MLG forward side brace, which, if not detected and corrected, could result in gear collapse and loss of control of the airplane during landing operations.
AD 96-10-15 · published May 17, 1996, effective Jun 27, 1996
Piper Aircraft Inc. Airplanes
This amendment supersedes Airworthiness Directive (AD) 80-14-06, which currently requires the following on The New Piper Aircraft, Inc. (Piper) Models PA31, PA31-300, PA31-325, and PA31-350 airplanes: repetitively inspecting the outboard flap tracks, wing rib flanges, and the rear spar web at Wing Station (WS) 147.5 on each wing, and modifying the area at WS 147.5 on both wings if any cracks are found as terminating action for the repetitive inspection requirement. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action retains the repetitive inspection requirement of AD 80-14-06, and requires modifying the area at WS 147.5 on both wings as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent structural failure under certain load conditions caused by cracked areas at WS 147.5, which, if not detected and corrected, could result in loss of control of the airplane.
AD 96-11-03 · published May 22, 1996, effective Jun 26, 1996
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that currently requires inspection of each fuel feed line of the outboard engine in the engine strut to determine if interference with an adjacent pneumatic duct clamp has caused damage, and repair or replacement of the fuel feed tube, if necessary. That AD also currently requires inspection and replacement of the adjacent pneumatic duct clamp with a non-rotating type clamp, if necessary. This amendment requires modification of the upper gap area of the strut of the number 1 and 4 engines. This amendment is prompted by a report of fuel leakage in the strut of the number 4 engine due to a high profile clamp that chafed the fuel line. The actions specified by this AD are intended to prevent chafing of the fuel line in the strut of the number 1 and 4 engines, which could result in rupture of the fuel line and subsequent in-flightengine fire.
AD 96-11-04 · published May 22, 1996, effective Jun 26, 1996
McDonnell Douglas Model DC-9 and Model DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires modification of the slant panel insulation blankets on the slant pressure panel of the main landing gear. The amendment also requires a visual inspection to detect discrepancies of the left and right seal assemblies of the overwing emergency exit door, and replacement of any discrepant door seal. This amendment is prompted by a report that the flaps and landing gear did not extend or retract properly due to water accumulation in the slant pressure panel area. The actions specified by this AD are intended to prevent such water accumulation, which could result in the failure of the flaps or landing gear to properly extend or retract.
AD 96-11-06 · published May 24, 1996, effective Jun 28, 1996
de Havilland Model DHC-7 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-7 series airplanes, that requires modification of the emergency lights circuitry. This amendment is prompted by reports of the emergency lights turning on inadvertently due to voltage spikes from other equipment; and reports that the existing emergency light switch arrangement allows the flight compartment and flight attendant's panel switches to override each other. The actions specified by this AD are intended to prevent such failures of the emergency light systems, which could prevent the use of the emergency lights in the event of an emergency.
AD 96-11-11 · published May 29, 1996, effective Jul 3, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9 series airplanes, that requires inspection(s) to detect cracking in the nose skin of the fuselage, and various follow-on actions. This amendment also provides for an optional modification, which would defer certain repetitive inspections, if no cracking is detected. This amendment is prompted by reports of cracking in the upper nose skin of the fuselage due to fatigue. The actions specified by this AD are intended to prevent fatigue-related cracking, which could compromise the structural integrity of the airplane.
AD 96-11-13 · published May 31, 1996, effective Jun 17, 1996
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. This action requires a visual inspection to determine the type of fluorescent light ballasts installed in the cabin sidewall; and installation of a protective cover, replacement, or removal/disconnection, if necessary. This action also requires removal of the dust barriers from the outboard ceiling panels, and installation of modified outboard ceiling panels. This amendment is prompted by reports of smoke, fumes, and/or electrical fire emitting from the baggage bin of the aft passenger compartment and from the dust barriers of the outboard ceiling due to the failure of the fluorescent light ballasts. The actions specified in this AD are intended to prevent a fire in the passenger compartment, which could result from failure of the fluorescent light ballast of the upper and lower cabin sidewall, and subsequent failure of the dust barriers of the outboard ceiling panel.
AD 96-11-14 · published May 31, 1996, effective Jun 17, 1996
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes. This action requires inspections to detect cracking of the lower rib of the rudder, and repair, if necessary. This action also provides for an optional terminating action, which, if accomplished, terminates the repetitive inspection requirement. This amendment is prompted by reports of fatigue cracking of the lower rib of the rudder. The actions specified in this AD are intended to prevent such fatigue cracking and subsequent failure of the primary structure of the rudder, which could result in reduced controllability of the airplane.
AD 96-09-29 · published May 3, 1996, effective Jun 7, 1996
Robinson Helicopter Company Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R22 helicopters, that requires replacement of the upper V-belt sheave (sheave). This amendment is prompted by three reports of cracks in the flange of the sheave. The actions specified by this AD are intended to prevent failure of the sheave, which could result in damage to other drive system components, and subsequent loss of control of the helicopter.
AD 96-10-09 · published May 14, 1996, effective May 29, 1996
MD Helicopters, Inc. Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, and 500N helicopters. This action requires initial and repetitive inspections of each main rotor blade (blade) root for either cracks or paint and sealant cracking or separation between the lower surface root end fitting and the doubler. This amendment is prompted by one accident in which a blade separated from the helicopter, as well as eight other reports of cracked blades. The actions specified in this AD are intended to prevent failure of a blade resulting in separation of the blade and subsequent loss of control of the helicopter.
AD 96-11-08 · published May 28, 1996, effective Jul 2, 1996
Robinson Helicopter Company Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R22 helicopters, that currently requires installing a low-rotor RPM caution light and resetting the low-RPM warning unit to activate the warning horn and caution light at 94% to 96% revolutions-per-minute (RPM). This amendment requires installation of an improved throttle governor; an adjustment to the low RPM warning unit threshold to increase the RPM at which the warning horn and caution light activate; and, revisions to the R22 Rotorcraft Flight Manual that prohibit flight with the improved throttle governor selected off, except in certain situations. This amendment is prompted by an FAA Technical Panel review of Model R22 accident history data which revealed that main rotor (M/R) blade stall at abnormally low M/R RPM resulted in accidents. The actions specified by this AD are intended to minimize the possibility of pilot mismanagement of the M/R RPM, which could result in unrecoverable M/R blade stall and subsequent loss of control of the helicopter.
AD 96-06-12 · published May 29, 1996, effective May 29, 1996
Scotts-Bell 47 Inc Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-06-12 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (Bell) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47-K helicopters by individual letters. This AD requires a visual inspection of each tail rotor blade (blade) tip, abrasion strip, blade skin, and blade butt for corrosion or delamination. This amendment is prompted by reports that a number of Model 47 helicopter blades were manufactured using a clad aluminum alloy material instead of a bare aluminum alloy material. The actions specified by this AD are intended to prevent premature delamination or separation of the blade tip block or the abrasion strip, which could lead to failure of the blade and subsequent loss of control of the helicopter.
AD 96-10-04 · published May 9, 1996, effective Jun 13, 1996
Honeywell International Inc. Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal, Inc. LTS101-600 series turboshaft engines, that requires installation of an improved design fuel control. This amendment is prompted by reports of fuel control bearings failing prior to the recommended overhaul period. The actions specified by this AD are intended to prevent a fuel control failure, which could result in an uncommanded increase or decrease in engine power.
AD 96-10-02 · published May 3, 1996, effective Jun 12, 1996
HB Aircraft Industries AG Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain HB Flugtechnik GmbH (Flugtechnik) Model HB-23/2400 sailplanes. This action requires inspecting (one time) the elevator control push rod tube for dents or bending and replacing the push rod tube, if damaged, inspecting the elevator control system for incorrect rigging, and repetitively inspecting the threaded adjustable extension joints in the push rod to control lever connection for cracks. If cracks are found, replacing the threaded adjustable joints at both ends of the push rod. Cracking of the threaded adjustable extension joints and incorrect rigging of the elevator control system prompted this AD action. The actions specified by this AD are intended to prevent failure of the elevator control system, which, if not detected and corrected, could result in possible loss of elevator control and loss of the sailplane.
