39 Airworthiness Directives: 31 airplane, 3 rotorcraft, 5 engine.
AD 96-15-09 · published Sep 3, 1996, effective Sep 3, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires repetitive high frequency eddy current inspections to detect cracks around the fasteners of the lower forward corners of the sliding window frames, and repair, if necessary. This amendment also requires the installation of a modification for each affected fastener hole, which terminates the repetitive inspections. This amendment is prompted by the results of full-scale fatigue tests which indicated that fatigue cracking occurred on the lower forward corner of the sliding window frames at frame 4. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in rapid depressurization of the airplane.
AD 96-15-10 · published Sep 3, 1996, effective Sep 3, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 and 0070 series airplanes, that requires modification of the wheel brake assembly on the main landing gear. This amendment is prompted by reports of aluminum brake pistons that have ballooned and failed. The actions specified by this AD are intended to prevent such failure of the pistons, which could result in leakage of the hydraulic fluid, resultant loss of braking capability, and a possible brake fire.
AD 96-16-03 · published Sep 3, 1996, effective Sep 3, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-200 series airplanes, that requires modification of the shock absorber sub-assembly of the main landing gear (MLG). This amendment is prompted by reports of internal damage to the shock absorber sub-assembly due to loose screws in the upper bearing dowels. The actions specified by this AD are intended to prevent such damage, which could result in the overextension of the shock absorber and failure of the torque link. This situation may lead to the inability of the MLG to retract and subsequent collapse of the MLG.
AD 96-18-07 · published Sep 4, 1996, effective Oct 25, 1996
Bellanca, Incorporated Models 17-30, 17-30A, 17-31, 17-31A, 17-31TC, and 17-31ATC Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Bellanca, Incorporated (Bellanca) Models 17-30, 17-30A, 17- 31, 17-31A, 17-31TC, and 17-31ATC airplanes. This action requires repetitively inspecting, testing, and possibly replacing the nose landing gear (NLG) strut and brackets. A collapse of a Bellanca airplane's NLG during a landing prompted this action. The actions specified by this AD are intended to prevent possible failure of the nose landing gear, which, if not detected and corrected, could result in loss of control of the airplane during landing operations.
AD 96-18-09 · published Sep 4, 1996, effective Oct 9, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125-800A and -1000A, and Model Hawker 800 and 1000 series airplanes, that requires modification of the TKS metering pump in the airframe ice protection system. This amendment is prompted by a report that the pump was found fitted with silver plated wiring. The actions specified by this AD are intended to ensure that silver plated wiring is removed from these pumps; silver plated wiring carrying a direct current can ignite the ice protection fluid (glycol) when exposed to it, which could result in a possible fire hazard.
AD 96-18-06 · published Sep 5, 1996, effective Oct 10, 1996
Airbus Model A320-111, -211, and -231 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires visual inspections to detect cracks of the fittings of the pressurized floor at frame 36, and renewal of the zone protective finish or replacement of fittings with new fittings, if necessary. This amendment is prompted by a report of fatigue cracking found on the pressurized floor fitting at frame 36 under the lower surface panel. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in failure of a floor fitting and subsequent depressurization of the fuselage.
AD 96-18-11 · published Sep 5, 1996, effective Oct 10, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10 and -15 series airplanes, that requires repetitive inspections to detect cracks in the bulkhead tee caps, and repair and follow-on actions, if necessary. It also provides for an optional terminating modification for the repetitive inspections. This amendment is prompted by reports of cracking in the bulkhead tee caps at a fuselage station in the area of certain longerons due to fatigue. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in loss of pressurization and damage to adjacent structure.
AD 96-18-21 · published Sep 6, 1996, effective Oct 25, 1996
B-N Group Ltd. Airplanes
This amendment supersedes Airworthiness Directive (AD) 75-26-15, which currently requires repetitively inspecting the aileron mass balance clamp unit attachment for looseness on Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN-2A and BN2A MK. 111 series airplanes, and modifying the aileron and mass balance clamp unit if any looseness is 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 repetitive inspections required by AD 75-26-15, and requires modifying the aileron and mass balance unit (at a certain time) as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent failure of the aileron mass balance attachment, which could result in loss of control of the airplane.
AD 96-18-19 · published Sep 9, 1996, effective Oct 15, 1996
Viking Air Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-7 series airplanes, that requires repetitive non-destructive inspections to detect disbonding of fuselage skin panels, and repair, if necessary. This amendment is prompted by a report of disbonding on fuselage skin panels, which was attributed to a manufacturing process error. The actions specified by this AD are intended to prevent disbonding of the skin panels of the fuselage, which could result in degradation of the structural capability of the airplane fuselage.
AD 96-18-20 · published Sep 9, 1996, effective Oct 15, 1996
Piaggio Model P-180 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Piaggio Model P-180 airplanes, that requires replacement of outflow/safety valves with serviceable valves. This amendment is prompted by a report of cracking and subsequent failure of outflow safety valves in the pressurization system. The actions specified by this AD are intended to prevent such cracking and subsequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
AD 96-19-03 · published Sep 11, 1996, effective Oct 16, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 and MD-11 series airplanes and KC-10A (military) airplanes, that requires repetitive inspections to detect corrosion or failure of the steel Hi-Lok fasteners at the inboard flap inboard track, and replacement of corroded/failed steel Hi-Lok fasteners with inconel Hi-Lok fasteners. This amendment also provides for termination of the repetitive inspections by replacing all of the steel Hi-Lok fasteners with inconel Hi-Lok fasteners. This amendment is prompted by reports of failed and/or corroded steel fasteners found in the inboard flap inboard track due to stress corrosion. The actions specified by this AD are intended to prevent such stress corrosion, which could result in binding of the flap and inability of the flap to extend or retract; this situation may lead to asymmetric flap deployment and subsequent reduced controllability of the airplane during flight.
AD 96-19-05 · published Sep 12, 1996, effective Oct 1, 1996
Fairchild Aircraft SA226 and SA227 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 95-19- 07, which currently requires the following on Fairchild Aircraft SA226 and SA227 series airplanes equipped with certain main landing gear (MLG) and nose landing gear (NLG): repetitively inspecting, using ultrasonic methods, the left-hand and right-hand MLG yokes and the NLG yokes for stress corrosion cracking, and, if any cracked yokes are found that exceed certain limits, replacing either the cracked yoke, the yoke/cylinder combination, or the affected MLG or NLG assembly. This action also supersedes priority letter AD 95-19-07 R1, which was issued to incorporate revised service information. Reports of landing gear failures on the affected airplanes prompted the original AD action. This action requires the same inspections, but requires replacing any MLG and NLG assembly with any cracks instead of allowing flight until certain crack limits are exceeded. The inability to determine or predict crack growth on areas where stress corrosion occurs on primary structure with a single-load path (MLG and NLG assemblies are considered such structure) prompted this action. The actions specified by this AD are intended to prevent MLG or NLG failure caused by stress corrosion cracking in the yokes, which could result in loss of control of the airplane during landing operations.
AD 96-19-02 · published Sep 16, 1996, effective Oct 28, 1996
Piaggio Aero Industries S.p.A. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Industrie Aeronautiche E Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This action requires modifying the passenger seat cushion next to the emergency exit door handle. Reports of interference between the passenger seat cushion and the emergency exit door handle, preventing the door from opening from the outside, prompted this AD action. The actions specified by the AD are intended to prevent the possibility of not being able to open the emergency exit door during an emergency evacuation of the airplane, which could result in injury to the passengers.
AD 96-19-08 · published Sep 16, 1996, effective Oct 1, 1996
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes. This action requires repetitive visual inspections to detect whether the de-icing system boots on the horizontal stabilizer are inflating fully. It also requires modification of the stabilizer de-icing system tube as terminating action for the repetitive inspections. This amendment is prompted by reports indicating that condensational water may collect in the de-icing system tube, freeze in low temperatures, and keep the boots from inflating fully. The actions specified in this AD are intended to prevent such failure which, if not corrected, could keep the stabilizer de-icing system from operating properly, and consequently result in reduced controllability of the airplane.
AD 96-19-09 · published Sep 16, 1996, effective Oct 21, 1996
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires a one-time inspection to detect cracking of the main landing gear (MLG) pistons, and repair or replacement of the pistons with new or serviceable parts, if necessary. This amendment is prompted by reports of failure of the MLG pistons that occurred during towing of the airplanes. The actions specified by this AD are intended to prevent fatigue cracking of the MLG pistons, which could result in failure of the pistons and subsequent damage to the airplane structure or injury to airplane occupants.
AD 96-19-10 · published Sep 17, 1996, effective Oct 2, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a one-time inspection to detect discrepancies of the main battery shunt, and replacement with a serviceable part, if necessary. This action also requires inspection of certain wires, washers, and brass jam nuts to detect any discrepancy, and replacement with a serviceable part, if necessary. Additionally, this action requires inspection, and adjustment if necessary, of the torque and resistance of the installation of the main battery ground stud. This amendment is prompted by reports of interruptions of electrical power during flight due to improper installation of the main battery shunt and ground stud connection of the main battery. The actions specified in this AD are intended to prevent such electrical power interruptions, which could result in loss of battery power to the source of standby power for the airplane.
AD 96-19-13 · published Sep 17, 1996, effective Oct 22, 1996
Learjet Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Gates Learjet Model 35 and 36 series airplanes that have been modified in accordance with Raisbeck Supplemental Type Certificate (STC) SA766NW, that requires a reduction of the maximum operating limit speed on the affected airplanes to prevent encountering certain potentially hazardous conditions. This amendment is prompted by reports of incidents of aileron buffet or buzz experienced during high speed cruise. The actions specified by this AD are intended to prevent aileron buffet or buzz conditions, which can result in the deterioration of the aircraft lateral control system characteristics to an unacceptable level.
AD 96-16-06 · published Sep 18, 1996, effective Oct 6, 1996
Weatherly Aircraft Company Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-16-06, which was sent previously to all known U.S. owners and operators of certain Weatherly Aviation Company, Inc., (Weatherly) Models 620A and 620B airplanes. This AD requires inspecting all wing hinge pins, part number (P/N) 40852-001, at the main wing-to-center section attachment (four per airplane) for depth of the threaded ends, length of the pin, and position of the pin; and replacing or repositioning any pin, as necessary. A report received by the Federal Aviation Administration of manufacturing deficiencies at the area of the main wing center section attachment prompted the AD. The actions specified by this AD are intended to prevent failure of the wing hinge pin, which could result in the wing separating from the fuselage.
AD 96-19-14 · published Sep 18, 1996, effective Oct 23, 1996
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of certain flexible oxygen hoses, located in the flight compartment gangway and in the consoles, with insulated hose assemblies. This amendment is prompted by reports of either insufficient or no clearance between these hoses and adjacent structure or electrical wiring. The actions specified by this AD are intended to prevent chafing of the flexible oxygen hoses, which could result in an uncontrollable loss of oxygen from the flightcrew oxygen system, and could allow the presence of oxygen in areas where ignition is possible.
AD 96-19-07 · published Sep 19, 1996, effective Sep 27, 1996
Burkhart Grob Luft-Und Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-19-07, which was sent previously to all known U.S. owners and operators of Burkhart Grob Luft-und Raumfahrt (Grob) Models G115C, G115C2, G115D, and G115D2 airplanes. This AD requires installing a placard that restricts the never exceed speed (Vne) of the affected airplane models from 184 knots to 160 knots; installing on the airspeed indicator glass a red line at 296 km/h (160 knots); installing a placard that prohibits aerobatic maneuvers; and placing a copy of this AD in the Limitations Section of the airplane flight manual. An in-flight breakup of a Grob Model G115D airplane prompted priority letter AD 96-19-07. The actions specified by this AD are intended to prevent loss of control of the airplane caused by excessive speed or aerobatic maneuvers.
AD 96-19-16 · published Sep 19, 1996, effective Oct 24, 1996
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires inspections to detect cracking of the Hi-lok bolt holes in the main hinge fittings of the horizontal stabilizer, and repair, if necessary. The amendment also requires modification of the main hinge fitting, modification or replacement of rib connecting angles, and modification of ribs. This amendment is prompted by a report indicating that cracking was found in the main hinge fittings of the horizontal stabilizer during fatigue testing. The cracking was a result of higher- than-anticipated loads induced during operation of the thrust reverser. The actions specified by this AD are intended to prevent deterioration of the fatigue life of the main hinge fittings of the horizontal stabilizer and reduced structural integrity of the horizontal stabilizer due to higher induced loads.
AD 96-19-18 · published Sep 19, 1996, effective Nov 8, 1996
SOCATA Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA Groupe AEROSPATIALE (Socata) TBM 700 airplanes. This action requires installing four rivets on the right side of the rudder and drilling drainage holes at the areas of the elevators and rudder. Reports of water accumulating in the areas of the elevators and rudder and a report of a bonding defect between the skin and rudder rear spar on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent the wing skin and the rear spar from becoming unbonded or water accumulating in either the elevators or rudder, which could result in loss of control of the airplane.
AD 96-19-17 · published Sep 20, 1996, effective Oct 7, 1996
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires a one-time inspection to detect discrepancies of the main battery shunt, and replacement with a serviceable part, if necessary. This action also requires inspection of certain wires, washers, and brass jam nuts to detect any discrepancy, and replacement with a serviceable part, if necessary. Additionally, this action requires inspection, and adjustment if necessary, of the torque and resistance of the installation of the main battery ground stud. This amendment is prompted by a report of interruption of electrical power during flight due to improper installation of the main battery shunt and ground stud connection of the main battery. The actions specified in this AD are intended to prevent such electrical power interruptions, which could result in loss of battery power to the source of standby power for the airplane.
AD 96-17-06 · published Sep 23, 1996, effective Sep 23, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections to detect discrepancies of the slat universal joint and steady bearing assemblies, and replacement of any discrepant assembly with a new, like assembly. This amendment also requires replacement of all slat universal joint and steady bearing assemblies with improved assemblies, which would terminate the repetitive inspections. This amendment is prompted by reports of broken or missing inner races on the slat universal joint and steady bearing assemblies of the slat transmission system. The actions specified by this AD are intended to prevent cracking of the inner race, which could cause it to break off and, consequently, allow the slat universal joint and steady bearing assemblies to become worn; this situation could result in failure of the shaft of the slat transmission system, and subsequent uncommanded movement of the associated slat.
AD 96-17-10 · published Sep 24, 1996, effective Sep 24, 1996
Raytheon Aircraft Company, Hawker Beechcraft Corporation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400, 400A, MU-300-10, and 2000 airplanes, and Model 200, B200, 300, and B300 series airplanes, that requires replacement of outflow/safety valves with serviceable valves. This amendment is prompted by a report of cracking and subsequent failure of outflow safety valves in the pressurization system. The actions specified by this AD are intended to prevent such cracking and subsequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
AD 96-19-04 · published Sep 26, 1996, effective Sep 26, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes. This action requires a one-time inspection to detect cracks of the dimpled lap joints in the fuselage skin, and repair of cracked lap joints. This amendment is prompted by a report indicating that cracks were found at various locations in the outer skin of the dimpled longitudinal lap joints of the fuselage skin. The actions specified in this AD are intended to prevent such cracking, which could result in reduced structural integrity of the fuselage and/or rapid decompression of the airplane.
AD 96-17-14 · published Sep 30, 1996, effective Sep 30, 1996
Airbus Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that currently requires repetitive visual inspections to detect cracks in the forward intermediate section skin at frame 30A where it joins stringer 30, and repair, if necessary. This amendment adds a requirement for eddy current inspection(s) to detect cracks of the outer skin of the fuselage; accomplishment of this inspection terminates the repetitive visual inspections. This amendment also requires repair of any cracked area and modification of the structure at certain frames. This amendment is prompted by in-service experience which has identified fatigue cracks in this area. The actions specified by this AD are intended to prevent fatigue cracking, which could result in rapid decompression of the airplane.
AD 96-20-03 · published Sep 30, 1996, effective Nov 4, 1996
Bombardier Inc. Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all de Havilland DHC-8-100 and -300 series airplanes, that currently requires repetitive inspections to detect loose bolts at the retract actuator support fitting of the main landing gear, and various follow-on actions, if necessary. That AD was prompted by a report of loose actuator supporting bolts and cracks in the relief radius of the boss at the forward surface of the fittings. This amendment adds a requirement to install a new modification, which, when accomplished, terminates the repetitive inspections. The actions specified by this AD are intended to prevent loss of hydraulic systems and reduced controllability of the airplane due to loose actuator support bolts or cracks in the relief radius of the boss at the forward surface of the fittings.
AD 96-20-05 · published Sep 30, 1996, effective Nov 4, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive operational tests to verify proper deployment of the ram air turbine (RAT), and replacement of the rotary actuator motor with a new or serviceable rotary actuator motor, if necessary. This amendment is prompted by reports of corroded rotary actuator motors of the RAT found on in-service airplanes. The actions specified by this AD are intended to ensure that the RAT actuator motor is not corroded to the point where it may result in the failure of the RAT to deploy and subsequently result in loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
AD 96-20-06 · published Sep 30, 1996, effective Nov 4, 1996
BAE Systems (Operations) Limited Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires inspection to determine the number of hours time-in-service on the landing gear control unit, and modification of the cable (electrical wiring circuit) of the landing gear control unit. That AD was prompted by a report of failure of a micro-switch in the landing gear control unit. This amendment requires installation of a new landing gear control unit. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent uncommanded retraction of a landing gear, which could adversely affect airplane controllability.
AD 96-20-08 · published Sep 30, 1996, effective Nov 14, 1996
M7 Aerospace LLC Airplanes
This amendment supersedes AD 93-19-06, which currently requires repetitively inspecting acrylic cabin and cockpit side windows for cracks on certain Fairchild Aircraft SA26, SA226, and SA227 series airplanes, and, if cracks are found that exceed certain limitations, replacing that window. This action maintains the requirement of repetitively inspecting the cabin and cockpit side windows, and adds a life limit for the single-pane cockpit side windows. Acrylic window failures on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent acrylic cabin or cockpit side window failures, which could result in airframe damage and decompression injuries. The incorporation by reference of certain publications listed in the regulations was previously approved by the Director of the Federal Register as of November 19, 1993 (58 FR 51771, October 5, 1993).
AD 96-12-26 · published Sep 6, 1996, effective Sep 23, 1996
Arrow Falcon Exporters, Inc., AST, Inc, Bell Helicopter Textron, Inc., California Department of Forestry, Global Helicopter Technology, Inc., Hagglund Helicopters, LLC, International Helicopters, Inc., Overseas Aircraft Support Inc, Richards Heavylift Helo, Inc., Robinson Air Crane, Inc., Rotorcraft Development Corporation, San Joaquin Helicopters, Smith Helicopters, Sout
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) AD 96-12-26 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI)-manufactured Model AH-1, HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters by individual letters. This AD requires a visual inspection of each tail rotor (T/R) blade (blade) for peeling, flaking, or bubbling paint that may indicate corrosion; an inspection for corrosion, if necessary; and replacement of the T/R blade with an airworthy blade if corrosion is discovered. This amendment is prompted by an FAA determination, based on the manufacturer's data, that certain serial-numbered T/R blades were manufactured with internal leading edge doublers fabricated from clad aluminum instead of bare aluminum material. The actions specified by this AD are intended to prevent debonding of the main spar internal leading edge doubler, which could lead to failure of a T/R blade and subsequent loss of control of the helicopter.
AD 96-18-15 · published Sep 6, 1996, effective Sep 23, 1996
Bell Helicopter Textron, A Division of Textron Canada Ltd. Model 222, 222B, 222U, and 230 Helicopters
This amendment supersedes an existing airworthiness directive (AD) 96-01-08, which superseded Priority Letter AD 95-23-02, both of which were applicable to certain serial-numbered Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHT) Model 222, 222B, 222U, and 230 helicopters, that currently requires an initial check of both surfaces of each tail rotor blade (blade) for cracks; an inspection of the blade skin if a crack of a specified size or location is found in the paint; and replacement of the blade if a crack is found in the blade skin. This AD requires the same actions as required by the existing AD, but expands the applicability to include additional blade part numbers (P/N). This amendment is prompted by three incidents in which a crack developed in the stainless steel blade skins due to sanding marks on the blades that occurred during the manufacturing process on BHT Model 230 helicopters, which are similar in design to the Model 222, 222B and 222U helicopters. The actions specified by this AD are intended to prevent failure of a blade due to a fatigue crack, loss of the tail rotor and tail rotor gear box, and subsequent loss of control of the helicopter.
AD 96-12-25 · published Sep 23, 1996, effective Sep 23, 1996
Bell Helicopter Textron, Inc. Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) AD 96-12-25 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI) Model 204B helicopters by individual letters. This AD requires a visual inspection of each tail rotor (T/R) blade (blade) for peeling, flaking, or bubbling paint that may indicate corrosion; an inspection for corrosion, if necessary; and replacement of the T/R blade with an airworthy blade if corrosion is discovered. This amendment is prompted by an FAA determination, based on the manufacturer's data, that certain serial-numbered T/R blades were manufactured with internal leading edge doublers fabricated from clad aluminum instead of bare aluminum material. The actions specified by this AD are intended to prevent debonding of the main spar internal leading edge doubler, which could lead to failure of a T/R blade and subsequent loss of control of the helicopter.
AD 96-15-06 · published Sep 3, 1996, effective Sep 3, 1996
Pratt & Whitney Division Engines
AD 96-18-13 · published Sep 11, 1996, effective Nov 12, 1996
Honeywell International Inc. Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division) TFE731 series turbofan engines, that requires removing certain fan rotor disks from service in accordance with a drawdown schedule, and would establish new fan rotor disk life limits. This amendment is prompted after additional analyses revealed that stress levels in the fan rotor disk dovetail slots for the applicable engine models are higher than initially calculated. The actions specified by this AD are intended to prevent uncontained failure of the fan rotor disk due to fatigue cracking in the dovetail slots, which can result in inflight engine shutdowns, severe secondary damage, and fan rotor assembly separation from the engine.
AD 96-19-01 · published Sep 11, 1996, effective Sep 26, 1996
Allison 250 Series Turbine Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Allison 250 series turbine engines. This action requires initial and repetitive visual inspections of all engine filters for metal particles resulting from premature wear of two bearings produced under Parts Manufacture Approval (PMA) by Superior Air Parts, Inc. In addition, this AD requires replacement of those bearings with bearings that incorporate improved retainers, which constitutes terminating action to the inspection requirements of this AD. This amendment is prompted by a report of a failure during a ground test of an engine with bearings manufactured by Superior Air Parts, Inc. The actions specified in this AD are intended to prevent bearing failure due to bearing separator instability, which can result in subsequent turbine and engine failure.
AD 96-17-11 · published Sep 17, 1996, effective Nov 18, 1996
Pratt & Whitney JT9D-7R4 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT9D-7R4 series turbofan engines, that requires replacement of 3rd, 4th, and 5th stage low pressure turbine (LPT) vane retention bolts and nuts, the removal of the 5th stage vane configuration which includes an electro-discharge machined (EDM) slot and replacement with a cast slot configuration, and prohibits the use of uncured anti-gallant compound on vane retention hardware. This amendment is prompted by reports of LPT failures that resulted in uncontained engine failures. The actions specified by this AD are intended to prevent LPT vane failures, which can result in uncontained engine failure, fire, and possible damage to the aircraft.
AD 96-18-08 · published Sep 30, 1996, effective Nov 29, 1996
Pratt & Whitney PW2000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney PW2000 series turbofan engines, that requires a reduction in the cyclic service life limit for hubs, disks, airseals, blade retaining plates, and airsealing ring supports on certain high pressure turbines (HPT) and low pressure turbines (LPT), and provides for optional inspections for cracks or rework of certain HPT and LPT hardware in order to retain the original, higher cyclic service life limit for these components. This amendment is prompted in part by new temperature data from engine testing, which were used in recalculating stress levels, and resulted in a change to the calculated cyclic service life limit. The actions specified by this AD are intended to prevent HPT or LPT failure, which may result in an uncontained engine failure and possible damage to the aircraft.
