25 Airworthiness Directives: 18 airplane, 1 rotorcraft, 3 engine, 1 propeller, 2 appliance.
AD 96-01-03 · published Jan 3, 1996, effective Jan 30, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 and -200 series airplanes. This action requires a revision of the Airplane Flight Manual (AFM) and of the Airplane Weight and Balance Supplement to restrict the running load and maximum total payload to a suitable level. This amendment is prompted by a determination that these airplanes are incapable of carrying the currently certified payload limits due to the missing external structural doublers located forward of the surround structure of the main deck side cargo door, and deficiencies in the main deck floors. The actions specified in this AD are intended to prevent collapse of the aft fuselage due to inadequate strength in the airplane structure, and subsequent separation of the aft fuselage from the airplane.
AD 95-26-06 · published Jan 4, 1996, effective Jan 4, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This AD requires either that the control circuit breaker of the left fuel pump valve be opened and collared, or that the Airplane Flight Manual (AFM) be revised to prohibit autoland operation below 100 feet above ground level (AGL). Additionally, this action requires an inspection of the fuel system control panel (FSCP) to detect any mis-wiring, and modification or replacement of the FSCP. This AD also provides for an optional terminating modification for the requirements of the AD. This amendment is prompted by a report of improper wiring of the FSCP during production of these airplanes. The actions specified in this AD are intended to prevent degradation of the automatic landing system during flight due to improper wiring of the FSCP.
AD 96-01-04 · published Jan 8, 1996, effective Jan 23, 1996
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This action requires revising the Airplane Flight Manual (AFM) to require verification that the auto-ignition system is operational; to define icing conditions at higher ambient temperatures; and to provide the flight crew with limitations and procedures to aid in the avoidance of engine power interruptions. This amendment is prompted by a report of complete power loss of the left engine and power fluctuations on the right engine as a result of build up of ice and/or slush in the engine inlet and subsequent ingestion into the engines; the auto-ignition system of the left engine had failed, which prevented automatic restart of the engine following power interruption. The actions specified in this AD are intended to prevent failure of the auto-ignition system to re-light the engine in the event of power interruptions due to the ingestion of ice and/or slush into the engine, which could result in engine flameout and subsequent shutdown, and to provide the flight crew with guidance to aid in avoidance of such occurrences.
AD 95-26-10 · published Jan 9, 1996, effective Feb 8, 1996
BAE Systems (Operations) Limited Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires repetitive purging of the hydraulic system and installation of a spoiler actuator that has been previously certified. That AD was prompted by a report of damage to the locking mechanisms on some pistons of the spoiler actuators. The actions specified by the AD are intended to prevent uncommanded extension of the lift spoiler in the event of loss of hydraulic pressure in the spoiler actuator. This amendment establishes an increased life limit for certain spoiler actuators, and provides an optional terminating action for the requirements of that AD. This amendment also limits the applicability of the rule to fewer airplanes.
AD 95-26-18 · published Jan 9, 1996, effective Jan 26, 1996
Maule Aerospace Technology, Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Maule Aerospace Technology (Maule) M-4, M-5, M-6, M-7, MX-7, MXT-7 series and Models MT-7-235, and M-8-235 airplanes. This action requires a one-time inspection of certain wing lift struts for internal corrosion and replacement of the struts if corrosion is detected. An accident involving a wing separating from a Maule airplane in flight prompted this action. The actions specified by this AD are intended to prevent corrosion of the wing lift strut, which, if not detected and corrected, could cause the wing to separate from the airplane.
AD 95-25-04 · published Jan 10, 1996, effective Jan 25, 1996
McDonnell Douglas Model MD-11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires an inspection and other specified actions to ensure that the ground stud assemblies at three locations of the airplane are installed properly and torqued to certain specifications, to verify the integrity of the components of the ground stud assemblies, and to detect heat damage in adjacent areas; and correction of any discrepancy. That AD was prompted by reports indicating that arcing occurred across the pins in the galley external power receptacle due to loose attach hardware on the ground stud. The actions specified in that AD are intended to ensure that the ground stud assemblies are attached correctly so that arcing will not occur. Such arcing, if not corrected, could result in heat damage to adjacent structure and a fire in the forward cargo compartment, the center accessory compartment, or the aft fuselage compartment. This action would expand the applicability of the existing AD to include additional airplanes.
AD 95-25-09 · published Jan 10, 1996, effective Jan 10, 1996
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires that certain flight control computers be modified so that the autopilot will disengage when the airplane is in the "go-around" mode under certain conditions. This amendment is prompted by an accident in which the flight crew may have initiated an inadvertent go-around which, following several subsequent actions by the crew and automated system, placed the airplane in a severe out-of-trim condition. The actions specified by this AD are intended to prevent an out-of-trim condition between the trimmable horizontal stabilizer and the elevator, which may severely reduce controllability of the airplane.
AD 95-25-06 · published Jan 16, 1996, effective Jan 16, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400, 400A, and 400T (military T-1A) airplanes, that requires modification of the standby instrument lighting system. This amendment is prompted by a report that, due to the design of the standby instrument lighting system, the lighting for the standby instruments dimmed to an unacceptable level when the main electrical power was turned off. The actions specified by this AD are intended to ensure that the standby instrument lighting system adequately illuminates the standby instrument, if normal electrical power is lost or is turned off as a result of fire or smoke in the cockpit.
AD 95-24-12 · published Jan 17, 1996, effective Jan 17, 1996
British Aerospace Regional Aircraft Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Model 3201 airplanes. This action requires repetitively inspecting the main landing gear (MLG) bay forward lower edge wing skin structure for cracks, replacing any cracked doubler with a joggled doubler of improved design to reinforce the area and prevent future cracking, and eventually incorporating these doublers on all affected airplanes. Cracking found at the MLG bay forward lower edge wing skin structure during fatigue testing of the JAL Model 3201 prompted this action. The actions specified by this AD are intended to prevent the MLG bay forward lower edge wing skin structure from cracking, which, if not detected and corrected, could cause failure of the wing structure and loss of control of the airplane.
AD 95-24-13 · published Jan 17, 1996, effective Jan 17, 1996
British Aerospace Regional Aircraft Airplanes
This action makes a correction to Airworthiness Directive (AD) 95-24-13 concerning Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 airplanes, which published in the Federal Register on December 22, 1995 (60 FR 246). That publication incorrectly references the number of aileron mounting spigot nut assemblies to be replaced on the wings of the airplanes. The AD currently requires "replacing the securing nut assemblies and split pins with new special nut assemblies (Part No. SL5022 (Qty. 2))". The intent of the AD is to require replacement of 2 special aileron mounting spigot nut assemblies on each wing, for a total of 4 nut assemblies. The Final Rule AD did not specify "each wing", and mentioned that only 2 nut assemblies are required, instead of 4 nut assemblies. This action corrects the AD to reflect this change.
AD 95-25-07 · published Jan 17, 1996, effective Jan 17, 1996
M7 Aerospace LLC Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 series airplanes that are equipped with a part number 27-55001-229 actuator assembly. This action requires replacing the main landing gear door actuator tang and associated hardware with parts of improved design. Reports of the main landing gear doors hanging up and locking the landing gear links on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent the inability to extend the main landing gear because of the main landing gear door actuation roller contacting the lower edge of the tang and causing the linkage to lock over-center.
AD 95-26-14 · published Jan 19, 1996, effective Jan 31, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) Model 1900D airplanes. This action will require inspecting the cabin partition to ensure that a right-hand forward partition bracket exists on certain airplanes, installing this bracket if it does not exist, and improving the right-hand forward partition installation on all affected airplanes. The actions specified by this AD are intended to prevent cabin partition failure because of a structural deficiency in the bracket or if the bracket is not installed, which, if not detected and corrected, could cause passenger injury if the partition could not withstand the load incurred with the baggage compartment loaded to its 250-pound limit.
AD 96-01-02 · published Jan 19, 1996, effective Feb 20, 1996
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 a visual inspection to detect cracks or discrepancies in the aft mount beam assembly of the engines; and replacement of the cracked or discrepant aft mount beam assembly with a new assembly, or a previously inspected and re-identified assembly. That amendment was prompted by reports of cracking in a certain aft mount beam assembly. This new amendment requires additional inspections to detect cracks or discrepancies in the subject area, and various follow-on actions. The actions specified by this amendment are intended to prevent cracks in the aft mount beam assembly of the engines, which could result in loss of the capability of the aft mount beam assembly to support engine loads, and possible separation of the engine from the airplane.
AD 96-01-07 · published Jan 19, 1996, effective Feb 5, 1996
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection to verify that the attachment screws at a pressure switch located on the trim tank fuel transfer line are properly torqued, and that lockwires are installed. This amendment is prompted by reports of loose screws and missing lockwires at this attachment. The actions specified in this AD are intended to prevent loose or missing screws, which could allow fuel to leak from the pressure switch connection; if a leak were to occur during flight with a full trim tank, there would be no warning indication to the flight crew, and the airplane may not have enough fuel to complete the flight safely.
AD 96-01-51 · published Jan 23, 1996, effective Jan 29, 1996
Boeing Model 747-100 and -200 Series Airplanes Modified in Accordance With Supplemental Type Certificate (STC) SA2322SO or SA4227NM-D.
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T96-01-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 747-100 and -200 airplanes by individual telegrams. This AD requires repetitive inspections of the latch safety pins of the main deck side cargo door to ensure that the door is securely latched and locked; it also requires deactivation of certain panel lights and installation of a placard to indicate such deactivation. This amendment is prompted by a report of a malfunction of the safety interlock system of the main deck side cargo door on one airplane. The actions specified by this AD are intended to prevent such malfunctions, which could result in the opening of the main deck side cargo door while the airplane is in flight, and subsequent rapid decompression of the airplane.
AD 96-01-05 · published Jan 26, 1996, effective Feb 26, 1996
McDonnell Douglas Model DC-9-10, -20, - 30, -40, and -50 Series Airplanes and C-9 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9 and C-9 (military) series airplanes, that requires replacement, inspection, and modification of the attach fittings of the main landing gear (MLG). This amendment is prompted by reports of severe structural damage and rupture of the integral fuel tank due to overload of the MLG caused by adverse landing conditions. The actions specified by this AD are intended to minimize the possibility of primary structural damage and rupture of the integral fuel tank due to overload of the MLG; these conditions could lead to fuel spillage and a resultant fire.
AD 96-01-52 · published Jan 29, 1996, effective Feb 5, 1996
Airbus Model A310 and A300-600 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T96-01-52 that was sent previously to all known U.S. owners and operators of Airbus Model A310 and A300-600 series airplanes by individual telegrams. Among other things, this AD requires repetitive inspections to ensure correct synchronization of the hydraulic control valves of the trimmable horizontal stabilizer (THS) actuator; replacement of the horizontal stabilizer actuator motors with new or serviceable motors and resynchronization of the valves, or adjustment of the synchronization, if necessary; and a functional test of the THS. This amendment is prompted by a report of desynchronization of the hydraulic control valves that direct fluid to the horizontal stabilizer actuator motors, which resulted in uncommanded movement of the THS. The actions specified by this AD are intended to prevent such desynchronization, which could lead to runaway of the horizontal stabilizer to its full up or down position, subsequent reduced maneuvering capability, and potential pitch upset.
AD 95-13-11 R1 · published Jan 30, 1996, effective Aug 7, 1995
McDonnell Douglas Model DC-10-10 Airplanes
This amendment clarifies information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10 airplanes, that currently requires repetitive inspections to detect cracking of the upper caps in the front spar of the left and right wing, and repair, if necessary. The actions specified in that AD are intended to prevent progression of fatigue cracking, which could cause reduced structural integrity of the wing front spar and damage to adjacent structures. This amendment clarifies the requirements of the current AD by revising the area of inspection. This amendment is prompted by communications received from affected operators that the current requirements of the AD are unclear.
AD 96-01-08 · published Jan 9, 1996, effective Jan 24, 1996
Bell Helicopter Textron, A Division of Textron Canada Ltd. Model 222, 222B, 222U, and 230 Helicopters
This amendment supersedes an existing priority letter airworthiness directive (AD) 95-23-02, 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 priority letter AD, but corrects some affected serial numbers (S/N) that were incorrectly stated in that AD. This amendment is prompted by two incidents in which a crack developed in the stainless steel blade skins on BHT Model 230 helicopters, which are similar in design to the Models 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 95-03-10 · published Jan 9, 1996, effective Jan 24, 1996
Lycoming Engines Engines
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 95-03-10 that was sent previously to all known U.S. owners and operators of Textron Lycoming O-235 series reciprocating engines by individual letters. This AD requires a one-time inspection within the next 5 hours time in service to determine the part number (P/N) and revision letter of the push rod installed on the engine. All push rods with P/N 73806 and revision letters "V" or "W" must be replaced with serviceable parts. This amendment is prompted by reports of several failures of push rods. The actions specified by this AD are intended to prevent engine roughness and power loss, which could result in loss of the aircraft.
AD 95-26-02 · published Jan 9, 1996, effective Jan 24, 1996
Lycoming Engines, Textron Lycoming, AVCO Corporation Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming reciprocating engines installed on certain aircraft identified by registration numbers. This action supersedes priority letter AD 94-14-13 that currently requires engines certified to operate on 91 octane or higher aviation gasoline (avgas) to undergo a teardown and analytical inspection for detonation damage, and engines certified to operate on 80 octane avgas to undergo inspection for evidence of possible internal engine damage. This action revises incorrect engine model numbers and aircraft registration numbers listed in the priority letter AD. This amendment is prompted by the Federal Aviation Administration (FAA) receiving more accurate information concerning which aircraft were fueled with the contaminated mixture at the affected airports. The actions specified by this AD are intended to prevent detonation due to low octane, which can result in severe engine damage and subsequent failure.
AD 96-02-04 · published Jan 29, 1996, effective Feb 13, 1996
Wytwornia Sprzetu Komunikacyjnego Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Franklin Model 6A4-150-B3 and 6A4-165-B3 reciprocating engines, installed on the following U.S. registered aircraft: N6209M, N74231, and N752C. This action supersedes priority letter AD 94-14-11 that currently requires engines certified to operate on 91 octane or higher avgas to undergo a teardown and analytical inspection for detonation damage, and engines certified to operate on 80 octane avgas to undergo inspection for evidence of possible internal engine damage. This action revises incorrect engine model numbers listed in the priority letter AD. This amendment is prompted by updated information that has identified the correct engine model numbers. The actions specified by this AD are intended to prevent detonation due to low octane, which can result in severe engine damage and subsequent failure.
AD 96-01-01 · published Jan 19, 1996, effective Jan 19, 1996
Hamilton Standard Division, Hamilton Sundstrand Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hamilton Standard Propeller 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. This action supersedes priority letter AD 95-18-06 R1, that was issued on August 30, 1995, that currently requires ultrasonic shear wave inspection on all Hamilton Standard 14RF-9 propeller blades, and ultrasonic shear wave inspection on certain Hamilton Standard Propeller Models 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 propeller blades. This action requires that all blades of applicable Hamilton Standard propellers be calibrated for ultrasonic transmissibility before conducting the ultrasonic shear wave inspection. This action improves the crack detection capability of the ultrasonic shear wave inspection.This action also decreases the repetitive inspection interval for the 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 from 1,250 flight cycles to 500 flight cycles. This action also establishes a new ultrasonic shear wave inspection interval of 1,000 flight cycles for the 14RF-19 and 2,500 flight cycles for the 14RF-21 and the 6/5500/F. This AD also removes 14SFL11 propellers from service. This AD is prompted by reports that the existing ultrasonic shear wave inspection may not detect cracks as originally determined with some blades due to geometric differences. 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 the aircraft.
AD 95-24-10 · published Jan 29, 1996, effective Feb 21, 1996
Cessna Aircraft Company, Michelin Aircraft Tire Corporation Appliances
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-24-10, which was sent previously to all known U.S. owners and operators of airplanes with a Michelin Aircraft Tire Corporation part number (P/N) 028-520-1 (22x5.75-12/10PR) tire installed on the main landing gear. This AD requires replacing any of the affected tires with an FAA-approved tire. Two reports of failure (rupture) of the main landing gear tire during landing operations on Cessna Citation VII airplanes prompted priority letter AD 95-24-10. The actions specified by this AD are intended to prevent loss of control of the airplane during landing operations because of failure of a P/N 028-520-1 (22x5.75-12/10PR) tire.
AD 95-26-15 · published Jan 29, 1996, effective Feb 5, 1996
Alliedsignal Avionics, Inc. Appliances
This document publishes in the Federal Register an amendment adopting an airworthiness directive that was sent previously by individual letters to all known U.S. owners and operators of various transport category airplanes equipped with Allied Signal Commercial Avionics Systems CAS-81 TCAS. This amendment is prompted by reports of failure of the audio output of the CAS-81 TCAS. This AD requires a revision to the Airplane Flight Manual to provide the flightcrew with procedures to cycle power to the TCAS processor via the circuit breaker or power bus, and to perform a TCAS functional test to verify proper operation of the TCAS. The actions specified by this AD are intended to ensure that the flightcrew is advised of the potential hazard associated with failure of the audio output of the CAS-81 TCAS, and of the procedures necessary to address it.
