22 Airworthiness Directives: 20 airplane, 2 rotorcraft.
AD 94-11-07 · published Jul 5, 1994, effective Jul 5, 1994
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11-200 and -400 series airplanes, that requires inspection of the landing gear brakes for wear, and replacement of the brakes if the wear limits prescribed in this amendment are not met. This amendment also requires that the specified maximum brake wear limits be incorporated into the FAA-approved maintenance inspection program. This amendment is prompted by an accident in which a transport category airplane executed a rejected takeoff (RTO) and was unable to stop on the runway due to worn brakes; and the subsequent review of allowable brake wear limits for all transport category airplanes. The actions specified by this AD are intended to prevent the loss of brake effectiveness during a high energy RTO.
AD 94-14-04 · published Jul 6, 1994, effective Jul 21, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires inspection to detect cracking of the lower spar chord of the engine strut, removal of the stiffener straps from the mid-chord, inspection of the fastener holes, and modification or repair. This amendment is prompted by a report of cracking in the lower spar chord of an engine strut. The actions specified in this AD are intended to prevent cracking in the lower spar chord of the engine strut, which could result in the inability of the strut to carry required engine support loads.
AD 94-11-08 · published Jul 7, 1994, effective Jul 7, 1994
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires modification of the aileron drive quadrant support structure. This amendment is prompted by results of a stress analysis check, which revealed that the factor of safety of the aileron drive quadrant support structure on Model 4101 airplanes does not meet the tail-to-wind gust load design case strength requirements specified in the Federal Aviation Regulations. The actions specified by this AD are intended to prevent cracking of the support structure, which could result in reduced controllability of the airplane.
AD 94-11-10 · published Jul 7, 1994, effective Jul 7, 1994
Airbus Airplanes
This document adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of certain evacuation door slides. This amendment is prompted by a report that, during flight crew training, the toe end of the slide lane tore. The actions specified by this AD are intended to prevent damage to the slide, which could render the slide unusable, contribute to injury of passengers on the slide, and delay or impede the evacuation of passengers during an emergency.
AD 94-13-08 · published Jul 8, 1994, effective Jul 8, 1994
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 and A300-600 series airplanes. This action requires inspections and replacement or reinstallation of certain aft engine mount link assemblies. This amendment is prompted by reports of cracking in the aft engine mount link assemblies. The actions specified in this AD are intended to prevent loss of the capability of the aft engine mount to support engine loads, and possible separation of the engine from the airplane.
AD 94-14-22 · published Jul 8, 1994, effective Aug 31, 1994
Viking Air Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to de Havilland DHC-6 series airplanes. This action requires repetitively inspecting the horizontal stabilizer center hinge bracket for cracks, and replacing any cracked center hinge bracket. Several reports of cracks in the horizontal stabilizer center hinge bracket flange on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent separation of the elevator control support from the airplane as a result of a cracked horizontal stabilizer center hinge bracket, which could result in reduced controllability of the airplane.
AD 94-14-18 · published Jul 11, 1994, effective Jul 26, 1994
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-8-100 series airplanes. This action requires repetitive inspections of the hydraulic selector valve to determine the rate of leakage of hydraulic fluid, and replacement of certain valves with serviceable valves, if necessary. This AD also provides an optional terminating action for the repetitive inspections. This amendment is prompted by a report of pilot valve leakage of hydraulic fluid in a landing gear selector valve on a Model DHC-7 series airplane. The actions specified in this AD are intended to prevent inadvertent retraction of the landing gear in the event of a low voltage condition at the selector valve down solenoid.
AD 94-14-19 · published Jul 11, 1994, effective Jul 26, 1994
Viking Air Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-7 series airplanes. This action requires repetitive inspections of the hydraulic selector valve to determine the rate of leakage of hydraulic fluid, and replacement of certain valves with serviceable valves, if necessary. This AD also provides an optional terminating action for the repetitive inspections. This amendment is prompted by a report of pilot valve leakage of hydraulic fluid in a landing gear selector valve on a Model DHC-7 series airplane. The actions specified in this AD are intended to prevent inadvertent retraction of the landing gear in the event of a low voltage condition at the selector valve down solenoid.
AD 94-13-05 · published Jul 12, 1994, effective Jul 12, 1994
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 electrical connections in a certain relay panel. This amendment is prompted by a report that, as a result of a previous modification, certain electrical wires with a positive voltage were connected to an electrical connector that is also wired to the liftdumper system, which could negatively affect the liftdumper system. The actions specified in this AD are intended to ensure protection against uncommanded deployment of the liftdumper.
AD 94-13-09 · published Jul 12, 1994, effective Jul 12, 1994
Dassault Aviation Airplanes
AD 94-15-03 · published Jul 15, 1994, effective Aug 1, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767 series airplanes. This action requires revising the Non-Normal Procedures Section of the FAA-approved Airplane Flight Manual (AFM) to include procedures that will enable the flight crew to identify fuel system leaks and to take appropriate action to prevent further fuel loss. This amendment is prompted by reports that flight crew procedures related to fuel system leaks are not defined adequately in the FAA-approved AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard related to fuel exhaustion due to undetected leakage, and the procedures necessary to address it.
AD 94-12-01 · published Jul 20, 1994, effective Jul 20, 1994
Fokker Services Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that requires replacement of certain bolts that are currently installed in various flight critical components of the airplane. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in transport category airplanes that are approaching or have exceeded their economic design goal; these incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent reduced structural integrity of various flight critical components of the airplane.
AD 94-13-01 · published Jul 20, 1994, effective Jul 20, 1994
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires installation of new fairlead assemblies and P-clips; inspection to detect damage of the wiring harness at the wing rear spars; repair or replacement of any damaged wiring harness with a new wiring harness assembly; and verification of the position of the currently installed P-clips, and repositioning, if necessary. This amendment is prompted by a report of abrasion of an electrical power cable in the wiring harness at the wing rear spar. The actions specified by this AD are intended to prevent abrasion of electrical power cables in the wiring harnesses at the wing rear spars, which could lead to a dormant failure of emergency fuel and hydraulic shutoff services.
AD 94-15-02 · published Jul 20, 1994, effective Aug 19, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires inspections to verify the installation of shear pins, shear pin retainers, and shear pin retainer attaching parts in the aft end of the center pylon thrust link, and repair, if necessary. That AD was prompted by a report that both shear pins that attach the aft end of the center engine pylon thrust link to the tail pylon were missing. This amendment adds inspections to verify that the shear pin retainer attaching parts are tightened within specified limits; and adds a terminating modification for those inspections. This amendment also expands the applicability of the rule to include additional airplanes. The actions specified by this AD are intended to prevent structural damage to the engine mount structure, which could lead to loss of airplane components.
AD 94-12-08 · published Jul 22, 1994, effective Jul 22, 1994
Cessna Aircraft Company Airplanes
This amendment supersedes Airworthiness Directive (AD) 92-26-04, which applies to certain Cessna Aircraft Company (Cessna) 210, P210, and T210 series airplanes. That AD requires operational checks of the fuel gauges, fuel cap and adapter modifications, and preflight fuel system quantity checks. The Federal Aviation Administration (FAA) received a petition for reconsideration of AD 92-26-04, and subsequently suspended the effectiveness of this AD while the concerns specified in the petition were evaluated. This action retains certain requirements of AD 92-26-04, and incorporates certain items raised by the petition for reconsideration. The actions specified by this AD are intended to prevent loss of engine power caused by inadvertent fuel loss or inadequate fuel servicing. The incorporation by reference of certain publications listed in the regulations was previously approved by the Director of the Federal Register as of January 22, 1993.
AD 94-15-05 · published Jul 25, 1994, effective Aug 24, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-400 series airplanes, that requires various inspections and functional tests of the thrust reverser control and indication system, and correction of any discrepancy found. This amendment is prompted by an investigation to determine the controllability of Model 747 series airplanes following an in-flight thrust reverser deployment, which has revealed that, in the event of thrust reverser deployment during high-speed climb or during cruise, these airplanes could experience control problems. The actions specified by this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
AD 94-15-06 · published Jul 25, 1994, effective Aug 24, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspecting to detect cracking in certain lower lobe lap joints, and repair, if necessary; reporting any findings of discrepancies; replacing certain countersunk fasteners with protruding head fasteners; and verifying that the airplanes do not have certain countersunk fasteners. This amendment requires inspection of an expanded area, deletion of the reporting requirement, and expansion of the applicability to include additional airplanes. This amendment is prompted by reports of cracking of the fuselage skin in certain areas and findings of additional countersunk fasteners. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage.
AD 94-15-12 · published Jul 26, 1994, effective Aug 10, 1994
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100SR series airplanes, that currently requires that the FAA-approved maintenance inspection program include inspections which will give no less than the required damage tolerance rating (DTR) for each Structural Significant Item (SSI). That AD was prompted by a structural re-evaluation of this airplane model by the FAA. The actions specified in that AD are intended to ensure the continued structural integrity of the total Boeing Model 747-100SR fleet. This amendment revises the applicability of the rule by removing airplanes and adding others.
AD 94-15-13 · published Jul 26, 1994, effective Sep 12, 1994
Aerostar Aircraft Corporation Airplanes
This amendment supersedes Airworthiness Directive (AD) 92-13-01, which currently requires inspecting the nose landing gear (NLG) drag brace assembly for corrosion on certain Aerostar Aircraft Corporation (Aerostar) PA-60-600 (Aerostar 600) and PA-60-700 (Aerostar 700) series airplanes, and replacing any corroded components. It also requires replacing the existing spring and piston with new corrosion-resistant parts. This action requires replacing the NLG drag link assembly with a new assembly of improved design. The Federal Aviation Administration (FAA) has received several reports of frozen moisture in the cylinder of the over-center release system, which has led to nose gear collapse on airplanes already in compliance with AD 92-13-01. The actions specified by this AD are intended to prevent failure of the NLG caused by frozen moisture in the cylinder, which could lead to nose gear collapse and damage to the airplane.
AD 94-15-15 · published Jul 29, 1994, effective Aug 15, 1994
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Raytheon Corporate Jets Model BAe 125-1000A and Hawker 1000 series airplanes. This action requires an inspection to detect damage and to determine the clearance between the hydraulic pipes, adjacent pipes/components, and electrical looms/cables; and repair or replacement, if necessary. This amendment is prompted by reports of chafing of an electrical loom/cable on a hydraulic pipe and of chafing between a hydraulic pipe and an adjacent pipe. The actions specified in this AD are intended to prevent loss of hydraulic pressure, electrical malfunction, or an in-flight fire due to abrasion of electrical loom/cable insulation, eventual electrical shorting of the cable, and subsequent burning of a pinhole in a pipe. Comments for inclusion in the Rules Docket must be received on or before September 27, 1994.
AD 94-13-04 · published Jul 28, 1994, effective Sep 1, 1994
Schweizer Aircraft Corporation Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A series helicopters, that requires mandatory replacement of all the clevis pins associated with the belt drive clutch control installation. This amendment is prompted by an accident involving the separation of the belt drive clutch control spring assembly (spring assembly) from the idler pulley assembly. The actions specified by this AD are intended to prevent separation of the spring assembly from the idler pulley assembly, loss of power to the main rotor system, and a subsequent forced landing.
AD 93-17-12 · published Jul 29, 1994, effective Jul 29, 1994
Bell Helicopter Textron, Inc. Helicopters
