30 Airworthiness Directives: 20 airplane, 5 rotorcraft, 3 propeller, 2 appliance.
AD 96-07-08 · published Apr 1, 1996, effective Apr 16, 1996
Airbus Model A320-111 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 series airplanes. This action requires modification of the splicing cap at nose forward Frame 8 by cold expansion of the fastener holes and installation of new oversize fasteners. This amendment is prompted by results of a full- scale fatigue test which revealed that fatigue cracking can initiate from these fastener holes. The actions specified in this AD are intended to prevent such fatigue cracking which, if not detected and corrected in a timely manner, could compromise the structural integrity of the fuselage and lead to rapid depressurization of the airplane.
AD 96-05-02 · published Apr 3, 1996, effective Apr 3, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of a certain galley; repetitive inspections to detect damage and to determine the clearance of generator wires in the auxiliary power unit (APU); and repair or replacement of the damaged wires. This amendment is prompted by reports indicating that, during an unscheduled removal of a galley from the production line, the insulation of one of the generator wires of the APU was found damaged due to inadequate clearance with the adjacent structure. The actions specified by this AD are intended to prevent such damage, which could result in a short in the electrical wiring of the APU and, thus, pose a potential fire hazard.
AD 96-07-09 · published Apr 3, 1996, effective May 3, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Boeing Model 747-400, 757, and 767 series airplanes, that requires a revision to the Airplane Flight Manual that advises flight crews to monitor the engine indication and crew alerting system (EICAS) for "status" level messages pertaining to impending engine fuel filter bypass. This amendment also requires the installation of upgraded EICAS computers that provide "advisory" level messages to indicate such bypass conditions. This amendment is prompted by a finding that EICAS computers currently installed on these airplanes do not provide an appropriate indication to the flight crew of an impending engine fuel filter bypass condition. The actions specified by this AD are intended to ensure that the flight crew is appropriately aware of conditions involving a severely contaminated airplane fuel system and the associated increased potential for engine power loss.
AD 96-07-10 · published Apr 4, 1996, effective May 6, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires an inspection to determine if hinge bolts and nuts are installed in the overhead stowage bins, and the installation of hinge bolts and nuts, if necessary. This amendment is prompted by reports that overhead stowage bins in the passenger compartment have fallen out of position due to missing hinge bolts. The actions specified by this AD are intended to ensure that hinge bolts are installed in the overhead stowage bins. Missing hinge bolts could result in the overhead stowage bins falling out of position and injuring airplane occupants.
AD 96-07-11 · published Apr 4, 1996, effective May 6, 1996
Beech Model BAe 125-1000A and Hawker 1000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Beech Model BAe 125-1000A and Hawker 1000 series airplanes, that requires a detailed visual inspection to detect chafing damage to the hydraulic pipes adjacent to the hydraulic module, and various follow-on actions. This amendment is prompted by reports of chafing damage between hydraulic pipes at three locations in the rear equipment bay adjacent to the hydraulic module. The actions specified by this AD are intended to prevent such chafing damage to the hydraulic pipe and subsequent hydraulic fluid leakage, which could lead to failure of essential airplane systems.
AD 94-24-09 R1 · published Apr 10, 1996, effective Apr 10, 1996
BAE Systems (Operations) Limited Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires repetitive inspections to detect damage to the overwing fairings, and replacement or repair of structurally damaged fairings. That AD was prompted by a report indicating that an overwing fairing detached from an airplane. The actions specified by that AD are intended to prevent reduced controllability of the airplane due to loss of an overwing fairing. This amendment adds an optional terminating action for the currently required inspections, and limits the applicability of the rule.
AD 96-07-51 · published Apr 10, 1996, effective Apr 15, 1996
McDonnell Douglas Model DC-9 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T96-07-51 that was sent previously to all known U.S. owners and operators of McDonnell Douglas Model DC-9 series airplanes by individual telegrams. This AD requires repetitive inspections to detect corrosion and cracking of the fuselage upper skin and frames in the area of the loop antenna assemblies of the automatic direction finder (ADF), and repair, if necessary. This amendment is prompted by reports of severe corrosion and cracking found in that area. The actions specified by this AD are intended to prevent rapid decompression of the fuselage, significant structural damage, and subsequent reduced structural integrity of the airplane, due to problems associated with corrosion and fatigue cracking in the subject area.
AD 96-07-13 · published Apr 15, 1996, effective May 15, 1996
Lockheed Martin Corporation Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires inspections to detect cracking of certain areas of the rear spar caps, web, skin, and certain fastener holes; and repair or modification, if necessary. That AD was prompted by reports of fatigue cracks in the caps, web, and skin of the wing rear spar inboard of inner wing station 346. The actions specified by that AD are intended to prevent rupture of the rear spar, which could result in extensive damage to the wing and fuel spillage. This amendment adds various improved inspections and follow-on actions, and requires that the initial inspections be accomplished at reduced thresholds.
AD 96-07-15 · published Apr 15, 1996, effective May 15, 1996
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect chafing of or damage to the wire bundle in the overhead switch panel of the cockpit, application of spiral wrap to the wire bundle, and corrective actions, if necessary. That AD was prompted by reports of chafed and shorted wires that resulted in smoke emanating from the overhead switch panel of the cockpit. This amendment expands the applicability of the rule to include certain Model DC-9 and MD-90-30 series airplanes, and C-9 (military) series airplanes. This amendment also adds a requirement to reroute the wire bundle to preclude chafing and damage. The actions specified by this AD are intended to prevent the potential for fire and uncontrolled smoke throughout the cockpit as a result of chafing and shorting in the electrical wire bundles.
AD 96-08-07 · published Apr 18, 1996, effective May 23, 1996
Airbus Model A310 and A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A310 and A300-600 series airplanes, that currently requires a revision to the FAA-approved Airplane Flight Manual (AFM) that warns the flight crew about certain consequences associated with overriding the autopilot while it is in the COMMAND mode or in the pitch axis. That AD also requires modification of certain flight control computers (FCC). This amendment requires replacement of the currently required revision to the AFM with a newly worded revision that explains the effect the modification of the FCC's has on the operation and performance of the autopilot and that clarifies the limitation for unmodified airplanes. This amendment is prompted by the results of an FAA review of the requirements of the existing AD. The actions specified by this AD are intended to prevent an out-of-trim condition between the trimmable horizontal stabilizer and the elevator, which could severely reduce controllability of the airplane.
AD 95-26-16 R1 · published Apr 22, 1996, effective May 16, 1996
Mooney Aircraft Corporation Model M20J Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-26-16 R1, which was sent previously to all known U.S. owners and operators of certain Mooney Aircraft Corporation (Mooney) Model M20J airplanes. This AD requires repetitively inspecting the alternate air door assembly to ensure a cotter pin exists and is secure, and replacing the cotter pin if it does not exist or is not secure. It also provides the option of incorporating an alternate air door plate assembly of improved design as terminating action for the repetitive inspections. Priority letter AD 95-26-16 R1 was prompted by a fatal accident involving one of the affected airplanes where the alternate air door became lodged in the air intake of the fuel injector causing engine failure. The actions specified by this AD are intended to prevent the alternate air door from separating from the airplane and restricting air flow to the engine.
AD 96-06-05 · published Apr 22, 1996, effective Apr 22, 1996
The Boeing Company Airplanes
This amendment supersedes two existing airworthiness directives (AD), applicable to certain Boeing Model 727 series airplanes, that currently require repetitive visual inspections to detect cracks of the elevator rear spar, and repair, if necessary. This amendment adds new inspections to detect cracks and loose brackets of the elevator rear spar; adds a new terminating modification for the inspections, and expands the applicability of the rules to include additional airplanes. This amendment is prompted by reports of cracking in the spar radii at the tab hinge location of the elevator rear spar on certain airplanes. The actions specified by this AD are intended to prevent cracking in elements of the elevator rear spar assembly, which could result in excessive free play of the elevator control tab and possible tab flutter.
AD 96-08-05 · published Apr 23, 1996, effective May 23, 1996
Boeing Model 747-400 Series Airplanes Powered by General Electric CF6-80C2 or Pratt & Whitney PW4000 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires modification of the engine fuel feed system. This amendment is prompted by reports indicating that the coupling nut on the fuel tube on the outboard strut (engine position 1) fractured. The actions specified by this AD are intended to prevent such fracturing of the coupling nut, which could result in release of fuel onto the engine cowling and a subsequent fire.
AD 96-08-06 · published Apr 23, 1996, effective May 23, 1996
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires visual and dye penetrant inspection(s) to detect cracks of the nose rib of the rudder, and stop drilling and blending of minor cracks. This amendment also requires replacement of the nose rib with a new nose rib and reinforcement of the nose rib, if extensive cracking is detected or if an operator elects to terminate the repetitive inspections. This amendment is prompted by the result of an inspection that revealed a cracked nose rib on the front spar of the rudder due to vibration-related stress. The actions specified by this AD are intended to prevent such stress and cracking, which could result in the deformation of the nose rib; this condition may lead to friction and jamming between the fin and the rudder and subsequent reduced controllability of the airplane.
AD 96-07-02 · published Apr 25, 1996, effective Apr 25, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires inspections to verify the correct operation of the main landing gear (MLG) downlock actuators, and replacement of any discrepant unit with a serviceable unit. This amendment also will require eventual replacement of the MLG downlock actuators with improved units. This amendment is prompted by reports of improper operation of the MLG downlock actuator due to jamming. The actions specified by this AD are intended to prevent such jamming of the downlock actuator, which could result in failure of the MLG downlock system, and a potential gear-up landing.
AD 96-09-07 · published Apr 25, 1996, effective May 10, 1996
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD) that is applicable to Boeing Model 757 series airplanes equipped with certain Abex spoiler actuator electro-hydraulic servo valves (EHSV) installed in certain spoiler actuators. The existing AD currently requires a one- time inspection of the spoiler actuator to determine if a suspect EHSV is incorrectly installed, and replacement of the EHSV, if necessary. That amendment was prompted by reports that a bias spring in the EHSV of certain spoiler actuators was found to be incorrectly installed. The actions specified by that AD are intended to prevent a significant control upset of the airplane as a result of problems associated with an incorrectly installed EHSV in the spoiler actuator assembly. This amendment adds additional suspect EHSV's that require inspection; it also corrects the actuator manufacturer's name and corrects the serial number of one EHSV.
AD 96-07-05 · published Apr 29, 1996, effective Apr 29, 1996
328 Support Services GmbH Airplanes
AD 96-07-06 · published Apr 29, 1996, effective Apr 29, 1996
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires inspection(s) to verify that the position indicator of the fuel balance transfer valve (FBTV) is in the closed position, and closing the FBTV, if necessary; and deactivation of the fuel balance transfer system (FBTS). This amendment is prompted by a report that, under certain failure conditions, the actuator of the FBTV could remain in the open position without a flight deck indication. The actions specified by this AD are intended to ensure that the FBTV is not in the open position during flight, which could lead to the reduction of fuel supply to the engines during cross-feed operation and consequent engine fuel starvation.
AD 96-08-08 · published Apr 29, 1996, effective May 29, 1996
Airbus Model A300 Series Airplanes (Excluding Model A300 B4-600 and Model A300 F4-600 Series Airplanes)
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 series airplanes (excluding Model A300 B4-600 series airplanes), that currently requires certain structural inspections and modifications. This amendment requires additional structural inspections and modifications that have been identified as necessary to ensure the structural integrity of these airplanes as they approach their economic design goal. This amendment also excludes additional airplanes from the applicability of the AD. The actions specified by this AD are intended to prevent degradation of the structural capability of the affected airplanes.
AD 96-09-02 · published Apr 29, 1996, effective Jan 29, 1994
Airbus Airplanes
This amendment supersedes two existing airworthiness directives (AD), that are applicable to Airbus Model A310 and A300-600 series airplanes. One AD currently requires repetitive operational tests of feel and limitation computers (FLC) 1 and 2; the other AD requires replacement of certain FLC's on Model A300-600 series airplanes. Those AD's were prompted by reports indicating that the elevator control operated with stiffness. The actions specified by those AD's are intended to prevent stiff operation of the elevator control and undetected loss of rudder travel limitation function, which could adversely affect the controllability of the airplane. This new amendment requires installation of new FLC's, which terminates the currently required repetitive operational tests. This amendment also revises the applicability of the rule to delete airplanes on which these new FLC's have been installed previously.
AD 96-07-12 · published Apr 5, 1996, effective May 10, 1996
Bell Helicopter Textron, Inc., Model 214ST Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214ST helicopters with certain tailboom assemblies and a certain emergency float kit installed, that requires initial and repetitive inspections of the tailboom for cracks until modifications of the tailboom are accomplished. This amendment is prompted by several reports of cracks in the lower aft skin of the tailboom assembly. The actions specified by this AD are intended to prevent cracks in the tailboom assembly, which could result in structural failure of the tailboom and subsequent loss of control of the helicopter.
AD 96-08-04 · published Apr 17, 1996, effective May 22, 1996
Eurocopter Deutschland GmbH (ECD) Model BO-105, BO-105A, BO-105C, BO-105S, and BO-105LS A-1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model BO- 105, BO-105A, BO-105C, BO-105S, and BO-105LS A-1 helicopters, that requires a ground test and inspection of the tandem hydraulic switch- over system (switch-over system) for component wear and parts replacement, if necessary. This amendment is prompted by incidents involving Model BO-105 series helicopters in which, during the switch- over from Hydraulic System 1 to Hydraulic System 2, a 3-inch drop in the collective occurred, caused by component wear in the switch-over system. The actions specified by this AD are intended to detect switch- over system component wear, which could result in a sudden drop in the collective and a sudden loss of altitude.
AD 96-06-02 · published Apr 25, 1996, effective Apr 25, 1996
Enstrom Helicopter Corporation, The Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to The Enstrom Helicopter Corporation Model (Enstrom) F-28A, F-28C, 280, and 280C helicopters, that currently requires an initial and repetitive visual inspections of the upper swashplate bearings for corrosion, and replacement of defective upper swashplate bearings with airworthy bearings. This amendment requires that the visual inspections apply to both the upper and lower swashplate bearings (bearings); expands the applicability to include the Model F-28C-2 helicopter; limits the applicability to those affected helicopters manufactured prior to January 1, 1981; establishes a retirement life of 1,200 hours time-in-service for certain bearings; and provides a corrected upper swashplate bearing part number. This amendment is prompted by the necessity to require visual inspections of the lower swashplate bearings; to expand the applicability to include the Model F-28C-2 helicopter; to establish a retirement life for certain bearings; and to correct the upper swashplate bearing part number from the existing AD. The actions specified by this AD are intended to prevent failure of the bearings and subsequent loss of control of the helicopter.
AD 96-06-04 · published Apr 25, 1996, effective Apr 25, 1996
Bell Helicopter Textron Canada Limited Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada, Ltd., (BHTC) Model 206A and 206B helicopters, that currently requires an inspection of the main transmission input driveshaft assembly (driveshaft) at intervals of 300 hours time-in-service (TIS); the application of a zinc chromate primer inspection visual aid; and, daily visual checks of the driveshaft. This amendment requires inspections of the driveshaft at intervals of 300 hours TIS; the application of a self-adhesive temperature indicator visual inspection aid ; and, preflight visual owner/operator (pilot) checks of the driveshaft. This amendment is prompted by recent studies that indicate self-adhesive temperature indicators are a more reliable means of detecting overheat conditions on grease-lubricated couplings than the zinc chromate primers currently in use. The actions specified by this AD are intended to prevent failure of the driveshaft due to coupling wear or overheating, which could result in loss of power to the main rotor and a subsequent forced emergency landing.
AD 96-09-03 · published Apr 25, 1996, effective May 30, 1996
Societe Nationale Industrielle Aerospatiale and Eurocopter France Model SA-365N, N1, and N2 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Societe Nationale Industrielle Aerospatiale and Eurocopter France Model SA-365N, N1, and N2 helicopters, that requires an inspection of the door jettison systems to determine if the handle shafts are locked to the jettison systems. If the inspection indicates the handle shafts are locked to the jettison systems, this AD requires installation of a snapwire on the jettison systems and a visual inspection of the door jettison handles to determine whether two spring pins are installed, and installation of a second spring pin, if necessary. If the initial inspection indicates that the handle shafts are not locked to the jettison systems, this AD requires replacement of the sheared spring pin with two spring pins. This amendment is prompted by a factory inspection performed by the manufacturer that revealed that the forward passenger door jettison handles may have been fitted with one spring pin instead of two spring pins at the door jettison handle attachment points. The actions specified by this AD are intended to prevent a loss of the doors in flight and subsequent damage to the horizontal stabilizer, main fin, or lateral fins.
AD 95-24-05 R1 · published Apr 12, 1996, effective Apr 12, 1996
McCauley Accessory Division, The Cessna Aircraft Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 Series Propellers
This amendment revises an existing airworthiness directive (AD), applicable to McCauley Accessory Division, The Cessna Aircraft Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 series propellers, that currently requires initial and repetitive visual and dye penetrant inspections of the propeller hub for cracks. This existing AD also requires a one-time eddy current inspection for cracks in the threaded areas of the propeller hub followed by modification of the hub to contain oil with red dye as a terminating action to the repetitive inspections. This amendment clarifies that a dye penetrant inspection is only necessary if crack indications are found or suspected during the visual inspection. This amendment is prompted by requests from operators for clarification of inspection procedures. The actions specified by this AD are intended to prevent propeller blade separation due to a cracked propeller hub, which could result in separation of the engine from the aircraft and subsequent loss of aircraft control.
AD 96-08-01 · published Apr 16, 1996, effective May 1, 1996
Hamilton Standard Model 14RF-9 Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hamilton Standard Model 14RF-9 propellers. This action supersedes priority letter AD 95-24-09 that currently requires a one- time ultrasonic shear wave inspection of the propeller blade shank for cracks or surface indications. This action continues to require an ultrasonic shear wave inspection, but adds a one-time visual and fluorescent penetrant inspection and repair of the propeller blade shank for mechanical damage. This amendment is prompted by propeller blade shank visual inspection results on blades that were removed from service as a result of the one-time ultrasonic shear wave inspections. The inspection results showed that minor damage could exist that is not detected by the ultrasonic shear wave inspection. This amendment is also prompted by the development of a method to remove the fiberglass on the blade shank permitting shank inspection and repair procedures. The actions specified by this AD are intended to prevent propeller blade separation due to propeller blade shank cracking, which could result in loss of control of the aircraft.
AD 96-08-02 · published Apr 24, 1996, effective May 9, 1996
Hamilton Standard Division, Hamilton Sundstrand Propellers
This amendment supersedes an existing airworthiness directive (AD), applicable to Hamilton Standard Models 14RF-9, 14RF-19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propellers, that currently requires that all blades of applicable Hamilton Standard propellers be calibrated for ultrasonic transmissibility before conducting the ultrasonic shear wave inspection. In addition, that AD decreases the repetitive inspection interval for the Hamilton Standard Models 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 propellers from 1,250 flight cycles to 500 flight cycles. That AD also establishes a new ultrasonic shear wave inspection interval of 1,000 flight cycles for the Hamilton Standard Model 14RF-19, and 2,500 flight cycles for the Hamilton Standard Models 14RF-21 and Hamilton Standard/British Aerospace Model 6/5500/F. Also, that AD removes Hamilton Standard Model 14SFL11 propellers from service. This amendment requires a blade repair that constitutes terminating action to the repetitive ultrasonic taper bore inspections. Repetitive ultrasonic taper bore inspections are required until the blade is repaired in accordance with this AD. This amendment is prompted by the development of a taper bore repair process that removes the damaged material and returns the blade to a condition that does not require repetitive ultrasonic taper bore inspections. The actions specified by this AD are intended to prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of aircraft control.
AD 96-08-03 · published Apr 15, 1996, effective May 20, 1996
Flight Trails Helicopter, MD Helicopters, Inc. Appliances
This amendment adopts a new airworthiness directive (AD), applicable to Flight Trails Helicopters, Inc. hardpoint assemblies, installed in accordance with Supplemental Type Certificate (STC) No. SH6080NM, or in accordance with Federal Aviation Administration (FAA) Form 337, "Major Repair and Alteration," approved on McDonnell Douglas Helicopter Systems (MDHS) Model 369D, 369E, 369F, 369FF, and 500N helicopters, that requires removing any Flight Trails Helicopters, Inc. hardpoint assembly not identified by part number (P/N) and serial number (S/N). This amendment is prompted by two incidents in which the hardpoint assembly used to support a search light or night vision system reportedly failed. The actions specified by this AD are intended to prevent failure of the hardpoint assembly, separation of the hardpoint assembly from the helicopter, and subsequent contact between the hardpoint assembly and the fuselage or rotor system of the helicopter.
AD 96-09-06 · published Apr 29, 1996, effective Jun 7, 1996
Maule Aerospace Technology Inc., Piper Aircraft Inc., Swift Museum Foundation Inc., Taylorcraft 2000 LLC, Brackett Aero Filters Inc. Appliances
This document supersedes airworthiness directive (AD) 95-03-02, which currently requires repetitively inspecting (visually) the air filter frame for a loose or deteriorating gasket on airplanes incorporating certain Brackett air filter assemblies and replacing any gasket found loose or deteriorated. This action requires retaining the repetitive inspection as contained in AD 95-03-02, and will incorporate additional Brackett air filter assemblies to the "Applicability" section of that AD. Additionally, this AD will provide a terminating action for the repetitive inspection. The Federal Aviation Administration's determination that certain additional Bracket air filter assemblies should be inspected and replaced prompted this AD action. The actions specified by this AD are intended to prevent gasket particles from entering the carburetor because of air filter gasket failure, which could result in partial or complete loss of engine power and loss of control of the airplane.
