30 Airworthiness Directives: 26 airplane, 1 rotorcraft, 2 engine, 1 propeller.
AD 96-11-01 · published Jul 2, 1996, effective Jul 2, 1996
British Aerospace Regional Aircraft Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action requires modifying the automatic airframe de-ice system to allow the wing and tail de-ice boots to automatically operate through one cycle. The present system repeats the wing de-ice boot inflation cycle before starting to inflate the tail de-ice boots. Reports of ice accumulating on the tail faster than the automatic tail de-ice boots inflate on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent excessive ice accretion on the tail or wings of the affected airplanes, which could result in loss of control of the airplane.
AD 96-11-02 · published Jul 2, 1996, effective Jul 2, 1996
British Aerospace Regional Aircraft Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes. This action requires repetitively inspecting the spigot housing plate for cracks at the wing/fuselage forward attachment sliding joint, replacing any cracked housing plate, repetitively inspecting the spigots and spigot posts for corrosion and installing improved spigots if corrosion is found that exceeds certain limits, and eventually installing improved spigots if corrosion that does not exceed certain limits is found. For certain affected airplanes, this action requires repetitively inspecting the spigot bushes for migration gaps, replacing the bushes with modified bushes if gaps are found that exceed 0.5 inch, and eventually replacing the bushes with modified bushes if migration gaps are not found. Reports of bush migration gaps found on three of the affected airplanes and another report of corrosion and several cracks found on the spigot housing plate on a Jetstream Model 3101 airplane prompted this action. The actions specified by this AD are intended to prevent structural failure of the wing/fuselage area caused by a cracked or corroded spigot housing assembly.
AD 96-14-03 · published Jul 2, 1996, effective Aug 6, 1996
de Havilland Model DHC-8-301, -311, and -315 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-301,--311, and-- 315 series airplanes, that currently requires modification of the airspeed limitations placard and revision of the Airplane Flight Manual to specify operating at lower airspeeds when the airplane is operating at full flaps. That action also provides for the optional termination of the requirements of the AD for certain airplanes. That action was prompted by a report that incorrect rivets were installed on the outboard flaps assemblies of these airplanes. The actions specified by that AD are intended to prevent structural failure of the outboard flaps of the wings due to the installation of incorrect rivets in the flap assemblies, which could result in reduced controllability of the airplane. This new amendment requires the installation of the previously optional terminating modification on certain airplanes. DATES: Effective August 6, 1996.
AD 96-13-11 · published Jul 5, 1996, effective Aug 9, 1996
Airbus Model A300 B2 and B4 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B2, B4-100, and B4-200 series airplanes, that currently requires supplemental structural inspections to detect fatigue cracking, and repair of cracked structure. This amendment requires revising the supplemental structural inspection (SSID) program by changing some of the inspection techniques, changing some of the thresholds and intervals for inspections, expanding the area to be inspected for some of the inspections, and revising the Fleet Leader Program. This amendment is prompted by a review of recent service history and reports received from the current SSID program required by the existing AD. The actions specified by this AD are intended to prevent reduced structural integrity of these airplanes due to fatigue cracking.
AD 96-14-01 · published Jul 5, 1996, effective Jul 22, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200 "combi" and 747-300 "combi" airplanes. This action requires the installation of a new hose and fitting for the oxygen supply system. This amendment is prompted by a report indicating that a gasket seal in the oxygen hose assembly was omitted during installation. The actions specified in this AD are intended to prevent leakage of oxygen from the passenger oxygen supply lines, which could prevent an adequate flow of oxygen from reaching passengers in the event of a deployment of the passenger oxygen masks.
AD 96-14-02 · published Jul 5, 1996, effective Aug 9, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a visual inspection to verify proper clearance between the number 18 fuel nozzle secondary transfer fuel tube and the pylon drain tube of the engine, and various follow-on actions. This amendment also requires the installation of clamps and associated fasteners between the environmental control system (ECS) controller tube and the pylon drain tube. This amendment is prompted by reports of chafing of the number 18 fuel nozzle secondary transfer fuel tube of the engine due to an improperly installed or loose pylon drain tube. The actions specified by this AD are intended to prevent such chafing, which could lead to subsequent fuel leakage and a possible engine fire.
AD 96-09-08 R1 · published Jul 9, 1996, effective Jul 26, 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 revises Airworthiness Directive (AD) 96-09-08, which currently requires inspecting the longerons aft of the rear cabane struts for cracks, and if cracked, prior to further flight, repairing the cracks. The current AD is applicable to Aviat Aircraft Inc. (Aviat), Models S-2A, S-2B, and S-2S airplanes (formerly Pitts Models S-2A, S-2B, and S-2S airplanes). This action requires the same action as AD 96-09-08; however, after AD 96-09-08 was issued, the FAA was notified by the manufacturer that the compliance time in the service bulletin was changed, and as a result, the issue date for the service bulletin was changed. This revision will ensure that the owner and operators are using the most up-to-date service bulletin applicable to the required actions in this AD. 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 96-11-16 · published Jul 9, 1996, effective Jul 9, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires a one-time measurement during refueling to determine the pressure in each collector tank; for certain airplanes, non-destructive test (NDT) inspections to detect cracking or deformations of the collector tank ribs on each wing, and repair, if necessary; and modification of top-hat stringers in each outer wing tank. This amendment is prompted by a report of damage to the ribs of the wing collector tank caused by over-pressure in the collector tank during refueling. The actions specified by this AD are intended to prevent cracking and deformation of the wing collector tanks due to over-pressure, which could result in reduced structural integrity of the wing.
AD 96-14-04 · published Jul 9, 1996, effective Aug 13, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 and MD-11 series airplanes, and KC-10A (military) airplanes, that requires identifying and replacing certain lock link bolts in the nose landing gear (NLG). This amendment is prompted by a report indicating that certain bolts were improperly heat-treated during manufacturing, which makes them prone to failure. The actions specified by this AD are intended to prevent failure of the lock link bolts in the NLG, which could result in the collapse of the NLG.
AD 96-14-05 · published Jul 9, 1996, effective Aug 13, 1996
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires an inspection of the control rods of the outboard leading edge slat, and follow-on actions (including repetitive ultrasonic inspections), if necessary. For certain airplanes, that AD also requires replacement of the control rod ends and attach bolts. It also provides for an optional terminating action for follow-on repetitive inspections. That AD was prompted by reports of cracks and worn attach bolts of the control rods of the leading edge outboards slats of the wings due to the high breakout torque in the joint of the control rod end. This amendment requires the installation of the previously optional terminating action. The actions specified by this AD are intended to prevent reduced controllability of the airplane and damage in the slat structure or fixed leading edge of the wing, as a result of cracks and worn attach bolts.
AD 96-14-06 · published Jul 9, 1996, effective Jul 24, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive inspections for broken lockwires on the bearing retainer nut of the pivot fittings of the horizontal stabilizer. This AD also requires eventual modification of the bearing nut retention means, which, when accomplished, terminates the repetitive inspections. This amendment is prompted by reports of broken lockwires on the bearing retainer nut of the pivot fittings of the horizontal stabilizer due to inadequate torquing of the nut. The actions specified in this AD are intended to prevent failure of the lockwires, which could result in loosening of the retainer nut for the pivot bearing of the horizontal stabilizer, and subsequent migration of the pivot bearing. This condition, if not corrected, could result in reduced controllability of the airplane.
AD 96-12-01 · published Jul 10, 1996, effective Jul 10, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires replacement of the flexible cables of the power and condition controls of the engines with new flexible cables. This amendment also requires installation of protective tape on the outside case of these flexible cables, and reidentification of the cables. This amendment is prompted by reports of stiff operation of the power and condition controls of the engines due to heat damage to and moisture contamination of the flexible cable. The actions specified by this AD are intended to prevent heat damage and moisture contamination to the flexible cable, which could result in stiff operation of the power and condition controls and subsequent reduced engine control.
AD 93-15-02 R2 · published Jul 15, 1996, effective Jul 25, 1996
Fairchild Aircraft SA226 and SA227 Series Airplanes
This amendment revises Airworthiness Directive (AD) 93-15-02 R1, which requires the following on Fairchild Aircraft SA226 and SA227 series airplanes that are equipped with a certain Simmonds-Precision pitch trim actuator: repetitively measuring the freeplay of the pitch trim actuator and repetitively inspecting the actuator for rod slippage; immediately replacing any actuator if certain freeplay limitations are exceeded or rod slippage is evident; and eventually replacing the actuator regardless of the inspection results. The compliance times for the first inspection of an actuator that is installed in accordance with AD 93-15-02 R1 was inadvertently referenced incorrectly. This action retains the repetitive inspection and replacement requirements of the current AD, corrects the above- referenced compliance times, and adds an additional replacement actuator option that will then require repetitive inspections and replacements of that actuator. The actions specified by this AD are intended to prevent the horizontal stabilizer from going nose-down or jamming because of pitch trim actuator failure, which could result in loss of control of the airplane.
AD 96-12-19 · published Jul 15, 1996, effective Jul 15, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires installation of reinforcement plates under each hook latch fitting on the frame of each large cargo door. For some airplanes, this amendment requires inspections to detect cracking in the area around each hook latch fitting, and repair, if necessary. This amendment is prompted by the results of stress analyses and destructive tests which revealed that fatigue-related cracking may develop in the vicinity of the hook latch fittings on the frame of the large cargo doors. The actions specified by this AD are intended to prevent reduced structural integrity of the frames of the cargo door due to fatigue cracking, which may lead to the cargo door(s) opening while the airplane is in flight.
AD 96-12-12 · published Jul 16, 1996, effective Jul 16, 1996
Piper Aircraft, Inc. Airplanes
This amendment supersedes Airworthiness Directive (AD) 80-22-04, 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 upper section of Fuselage Station (FS) 317.75 bulkhead for cracks, and incorporating a certain reinforcement kit if any crack is found. This action requires inspecting (one-time) the upper section of the FS 317.75 bulkhead for cracks, and incorporating one of two reinforcement kits depending on whether cracks are found in the FS 317.75 bulkhead area. Cracks found on airplanes in compliance with the inspection requirements of AD 80-22-04 and the Federal Aviation Administration's policy on aging commuter-class aircraft prompted this action. The actions specified in this AD are intended to prevent structural failure of the vertical fin forward spar caused by cracks in the FS 317.75 bulkhead, which, if not detected and corrected, could result in lossof control of the airplane.
AD 96-12-14 · published Jul 16, 1996, effective Jul 16, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires reinforcing the lower right-hand wing skin at the fueling adapter. This amendment is prompted by results of tests, which revealed that fatigue cracks can develop in the lower right-hand wing skin at the attachment bolt holes of the fueling adapter. The actions specified by this AD are intended to prevent reduced structural capability of the wing and fuel leakage.
AD 96-14-51 · published Jul 17, 1996, effective Jul 22, 1996
The Boeing Company Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T96-14-51 that was sent previously to all known U.S. owners and operators of Boeing Model 767 series airplanes by individual telegrams. This AD requires an inspection of the aileron control cables and the generator feeder cables to detect chafing damage of the cables and to ensure that a minimum clearance exists between them. It also requires the correction of any discrepancies detected and submission of a report of inspection results to the FAA. This amendment is prompted by reports of failure of the aileron control cables due to inadequate clearance between the aileron control cable and the generator power feeder cable, which occurred during manufacture of the airplane. The actions specified by this AD are intended to prevent reduced controllability of the airplane due to failure of the aileron control cable.
AD 96-14-09 · published Jul 22, 1996, effective Jul 22, 1996
BAE Systems (Operations) Limited Airplanes
AD 96-11-12 · published Jul 24, 1996, effective Jul 24, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Beech Aircraft Corporation (Beech) Model C90A airplanes equipped with an optional Beech electric trim system or a Collins autopilot system. This action requires modifying the elevator electric trim tab actuator assembly. Failure of the elevator electric trim tab system on a Beech Model C90A prompted the proposed AD action. The actions specified by the proposed AD are intended to prevent possible failure of the elevator electric trim tab system, which, if not detected and corrected, could cause loss of airplane maneuverability and possible loss of control of the airplane.
AD 96-14-08 · published Jul 24, 1996, effective Jul 24, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes. This action requires modification of the radio altimeter wiring circuitry associated with the Automatic Flight Control Augmentation System (AFCAS). This amendment is prompted by a report indicating that the AFCAS does not properly monitor the radio altimeter status during automatic landing operations. The actions specified in this AD are intended to prevent erroneous indications and failure of the AFCAS to properly align, flare, and retard the airplane during automatic landing operations if a single radio altimeter were to fail.
AD 96-13-06 · published Jul 26, 1996, effective Jul 26, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 series airplanes, that requires replacement of junction fittings of the horizontal stabilizer with improved fittings. For certain airplanes, this amendment also requires replacement of the drive-fitting bushings and bolts of the horizontal stabilizer with improved bushings and bolts. This amendment is prompted by reports of stress corrosion cracking in a junction fitting lug of the horizontal stabilizer. The actions specified by this AD are intended to prevent such cracking, which could result in failure of a lug and uncommanded movement of the horizontal stabilizer. This condition, if not corrected, could result in reduced controllability of the airplane.
AD 96-15-08 · published Jul 29, 1996, effective Sep 3, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires modification of door 5 evacuation slide/rafts. This amendment is prompted by reports that the door 5 evacuation slide/raft failed to deploy properly due to adverse loads caused by the geometry of this evacuation slide/raft. The actions specified by this AD are intended to prevent failure of the door 5 evacuation slide/raft to deploy properly, which could contribute to injury of passengers on the slide and could delay or impede the evacuation of passengers during an emergency.
AD 96-16-01 · published Jul 29, 1996, effective Sep 3, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10 and DC-10-15 series airplanes, that requires an inspection for evidence of missing chrome and for corrosion on the chrome surfaces, or verification that the forward trunnion bolts have been chrome plated in a specific manner; and rework or replacement of the bolts, if necessary. This amendment is prompted by a report of chrome flaking on the bearing surface of the trunnion bolts due to improper cleaning of the base material prior to chrome plating. The actions specified by this AD are intended to prevent premature failure of the trunnion bolts and subsequent collapse of the main landing gear (MLG) as a result of chrome flaking and severe corrosion on the bearing surface and in the mechanical fuse.
AD 96-16-02 · published Jul 29, 1996, effective Sep 3, 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 either replacement or modification of the inboard and outboard flap actuators. This amendment is prompted by a report of failure of the piston rod of the inboard flap actuator due to a manufacturing process error. The actions specified by this AD are intended to prevent failure of the piston rod, which could result in uncommanded flap extension and could lead to an asymmetric flap configuration, which could reduce controllability of the airplane.
AD 96-12-23 · published Jul 31, 1996, effective Jul 31, 1996
Cessna Aircraft Company Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) 150 and A150 series and Models 152 and A152 airplanes that have a Bush Conversions, Inc., Short Takeoff and Landing (STOL) kit incorporated in accordance with Supplemental Type Certificate (STC) SA1371SW. This action requires measuring the wing stall fence for maximum height, and installing a smaller fence if the fence exceeds the maximum height of 1.28 inches. An accident of a Cessna Model 152 airplane where the STOL kit adversely affected the airplane's stall characteristics prompted this action. The actions specified by this AD are intended to prevent the airplane from entering a stall condition because of improper wing stall fence height, which could result in loss of control of the airplane.
AD 96-16-04 · published Jul 31, 1996, effective Sep 4, 1996
The Boeing Company Airplanes
This amendment supersedes 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) airplanes, that currently requires repetitive inspections to detect fatigue cracking in the area of the attach tees of the ventral aft pressure bulkhead. This amendment requires revised inspection and repair procedures, and provides for terminating action. It also deletes Model MD-88 airplanes from the applicability of the rule. This amendment is prompted by reports of fatigue cracking found in the subject area. The actions specified by this AD are intended to prevent the propagation of fatigue cracking, which could lead to structural failure of the ventral aft pressure bulkhead and subsequent rapid depressurization of the airplane.
AD 96-15-03 · published Jul 19, 1996, effective Aug 19, 1996
Sikorsky Aircraft Model S-76B Helicopters
This amendment supersedes an existing Airworthiness Directive (AD), applicable to Sikorsky Aircraft Model S-76B helicopters, that requires an inspection of the drive shaft for cracks or loose balance weights. This amendment also supersedes a Priority Letter AD that currently requires repetitive inspections for cracks in the driveshaft in helicopters with certain engine drive shaft assemblies (drive shafts) installed. This amendment is prompted by a report of a fatigue crack found in a drive shaft that was caused by fretting of a balance weight rivet washer. The actions specified by this AD are intended to prevent failure of the drive shaft, loss of power to the rotor system, and a subsequent forced landing of the helicopter.
AD 96-13-08 · published Jul 12, 1996, effective Aug 1, 1996
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney (PW) PW4000 series turbofan engines. This action requires initial and repetitive inspections of the aft cascade support frame assembly of thrust reverser for cracks, and replacement, if necessary, with serviceable parts; or lockout of the thrust reversers. This amendment is prompted by reports of aft cascade support frame assembly failures. The actions specified in this AD are intended to prevent aft cascade support frame assembly failure due to cracks, which can result in thrust reverser hardware liberation and ejection from the aircraft during thrust reverser operation, which can contaminate the runway with debris, causing an operational hazard to other aircraft during takeoff and landing.
AD 96-15-02 · published Jul 22, 1996, effective Aug 12, 1996
Pratt & Whitney Division Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Wasp series and R-1340 series (military) reciprocating engines. This action requires initial and repetitive visual and dye penetrant inspections of the crankshaft counterweights for cracks, and replacement of cracked crankshaft counterweights with improved crankshaft counterweights. This amendment is prompted by reports of crankshaft counterweight cracking. The actions specified in this AD are intended to prevent engine failure due to crankshaft counterweight failure, which could result in damage to or loss of the aircraft.
AD 96-15-04 · published Jul 29, 1996, effective Jul 29, 1996
Hartzell Propeller, Inc. Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to certain propeller blades, identified by serial number, installed on Hartzell Propeller Inc. HC-B3TN, HC- B5MP, HC-E4A, and HC-D4N series propellers. This action requires, within specified hours time in service after the effective date of this AD, a one-time fluorescent dye penetrant inspection of a twelve-inch long area on both the face and camber sides of propeller blade shanks for forging flaws or cracks, and replacement of defective propeller blades with serviceable parts. In addition, this action requires this inspection prior to further flight for propellers that experience sudden or unusual vibration. This amendment is prompted by a report of an inflight propeller blade separation. The actions specified in this AD are intended to prevent propeller blade separation caused by propeller blade shank cracks emanating from forging flaws, which could result in loss of control of the aircraft.
