36 Airworthiness Directives: 25 airplane, 6 rotorcraft, 2 engine, 1 appliance, 2 glider.
AD 95-11-11 · published Jun 1, 1995, effective Jul 3, 1995
McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10 (Military) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-10 and KC-10 series airplanes, that requires repetitive eddy current inspections to detect fatigue cracking of the pylon aft bulkhead flange, upper pylon box web, fitting radius, and adjacent tangent areas; and repair, if necessary. This amendment is prompted by fatigue cracking found in the wing pylon aft bulkheads on two airplanes. The actions specified by this AD are intended to prevent failure of the wing pylon aft bulkhead due to fatigue cracking, which could lead to separation of the engine and pylon from the airplane.
AD 95-11-12 · published Jun 1, 1995, effective Jul 3, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires repetitive replacement of the emergency power switch in the overhead switch panel with a new switch. This amendment is prompted by a report of heavy smoke in the cockpit coming from the overhead switch panel on a Model DC-9-81 series airplane. The actions specified by this AD are intended to ensure replacement of the emergency power switch when it has reached its maximum life limit; an emergency power switch that is not replaced could fail and lead to a short in the electrical circuit, which could result in a fire in the overhead switch panel and smoke in the cockpit.
AD 95-12-01 · published Jun 2, 1995, effective Jul 7, 1995
Piper Aircraft Corporation PA-25 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 93-21- 12, which currently requires inspecting (one-time visual and dye penetrant) the wing forward spar fuselage attachment assembly for cracks or corrosion on certain Piper Aircraft Corporation (Piper) PA-25 series airplanes, and replacing or repairing any cracked or corroded part. This action requires repetitively inspecting (using ultrasonic and dye penetrant procedures) the wing forward spar fuselage attachment assembly for cracks or corrosion, replacing or repairing any cracked or corroded part, and reporting to the Federal Aviation Administration (FAA) the results of the inspections. This action is prompted by the FAA's lack of confidence in detecting internal corrosion in the wing forward spar fuselage attachment fittings while accomplishing the inspection methods required by AD 93-21-12. A report of a crack in the wing forward spar fuselage attachment assembly on an airplane where the inspection requirements of AD 93-21-12 were accomplished also prompted this action. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked or corroded wing forward spar fuselage attachment assembly.
AD 95-10-06 · published Jun 12, 1995, effective Jun 12, 1995
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11, -2A12, -2B16, and -2B19 series airplanes, that requires an inspection to verify the proper operation of the uplock latch of the air driven generator (ADG), and replacement of the uplock latch with a serviceable part, if necessary. This amendment also requires replacing the uplock assembly with a modified uplock assembly, and performing a rigging inspection. This amendment is prompted by a report indicating that, upon operation of the manual release system, the ADG did not deploy due to failure of the shaft pin. The actions specified by this AD are intended to prevent failure of the shaft pin, which could lead to the inability of the pilot to manually deploy the ADG when necessary (i.e., when an airplane's primary electrical power sources are lost and the ADG fails to deploy automatically).
AD 95-12-12 · published Jun 13, 1995, effective Jun 28, 1995
de Havilland Model DHC-8-102, -103, and -106 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-8-102, -103, and -106 series airplanes. This action requires repetitive operational testing of the stall warning computers to ensure activation of the associated stick shakers, and replacement of non-operational stall warning computers with new or serviceable units. This action also provides an optional terminating action for the repetitive operational tests. This amendment is prompted by a report that, during a routine test, the stick shakers of the stall warning system did not activate, due to contamination of the weight-on-wheels contacts in the stall warning computer. The actions specified in this AD are intended to ensure that such contamination is detected. Contamination of the stall warning computers could lead to incorrect logic detection of the weight-on- wheels signal, and subsequent loss of the stick shaker function.
AD 95-12-16 · published Jun 14, 1995, effective Jun 22, 1995
Mooney Aviation Company Inc Airplanes
This amendment supersedes priority letter Airworthiness Directive (AD) 95-07-04, which currently requires the following on certain Mooney Aircraft Corporation (Mooney) Model M20R airplanes: repetitively inspecting the exhaust system for cracks, replacing the exhaust system if any cracks are found, and reporting to the Federal Aviation Administration (FAA) any cracks found. This action retains the repetitive inspection requirement of AD 95-07-04 until the exhaust system is modified, and requires eventual modification of the exhaust system on the affected airplanes. Several reports of exhaust system cracks on Mooney Model M20R airplanes prompted this action. The actions specified by this AD are intended to prevent an airplane engine fire that could result from exhaust system cracks.
AD 95-12-20 · published Jun 14, 1995, effective Jun 29, 1995
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 determine the torque value of all wing slat track stop pins, and correction of discrepancies. This amendment is prompted by a report of a fuel leak that was caused by an incorrectly torqued slat track stop pin that punctured the slat canister. The actions specified in this AD are intended to prevent such fuel leakage conditions, which could result in inadequate fuel for completing a flight and could pose a fire hazard.
AD 95-11-13 · published Jun 16, 1995, effective Jun 16, 1995
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action 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. This amendment is prompted by reports of cracking in a certain aft mount beam assembly on Airbus Model A310 series airplanes. The actions specified in this AD 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 95-12-24 · published Jun 16, 1995, effective Jul 3, 1995
Lockheed Model L-1011-385 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Lockheed Model L-1011-385 series airplanes. This action requires an inspection to detect cracking of the bulkhead at fuselage station (FS) 1363 at butt line (BL) 42.5, and repair or additional inspections, if necessary. This amendment is prompted by reports indicating that fatigue cracking was found in the rear bulkhead at FS 1363. The actions specified in this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking of the pressure bulkhead.
AD 95-10-12 · published Jun 21, 1995, effective Jun 21, 1995
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -212 series airplanes, that requires modification of the junction box and connector backshells of a certain electrical harness assembly. This amendment is prompted by a report indicating that traces of fungus and corrosion have been found on the electrical harness junction box of the thrust reverser. The actions specified by this AD are intended to prevent such corrosion, which could result in multiple faults in the thrust reverser position indication, and subsequent uncontrolled reduction of engine power.
AD 95-13-01 · published Jun 23, 1995, effective Jul 24, 1995
Air Bus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires inspections to determine the gap of the seat track joints at frame 64, and correction of discrepancies. This amendment also requires eventual modification of the seat tracks on all affected airplanes, which terminates the requirement of repetitively removing or repositioning the seats. This amendment is prompted by in-service inspection reports, which have revealed that a gap between the forward and aft seat track at frame 64 could exceed the tolerance limit due to a method used on the assembly line to control the position of the seat track. The actions specified by this AD are intended to ensure that the gap of the seat track joints do not exceed the tolerance limit and subsequently lead to separation of the passenger seats from the seat track under emergency landing conditions.
AD 95-13-03 · published Jun 23, 1995, effective Jul 28, 1995
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Beech Aircraft Corporation (Beech) Model F90, and 99, 100, and 200 series airplanes. This action requires installing a circuit breaker that will open before the landing gear power system motor is damaged to the point of restricting operation of the manual landing gear extension system. An incident where excessive current flow caused the electrical landing gear motor and wiring to catch fire on a Beech Model 200 airplane prompted this action. The actions specified by this AD are intended to prevent excessive current flow through the electrical landing gear motor, which could cause an airplane fire.
AD 95-12-13 · published Jun 26, 1995, effective Jul 26, 1995
Jetstream Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model ATP airplanes, that requires installation of modified engine de-ice timers, modification of the electrical wiring for the duct heat of the engine air intake, and installation of a time delay for the de-ice system in the air intake duct of the right engine. This amendment also requires associated revisions to the Airplane Flight Manual. This amendment is prompted by reports of ice that accreted in the engine air intake ducts and was ingested into the engine; this resulted in engine power rollback (loss of engine power). The actions specified by this AD are intended to prevent loss of multiple engine power during flight in icing conditions.
AD 95-12-07 · published Jun 28, 1995, effective Jun 28, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340-211 and -311 airplanes. This action requires replacement of the inboard and outboard aileron servo controls associated with hydraulic systems with new units that contain an improved seal installation. This amendment is prompted by reports of external leakage of hydraulic fluid on the inboard and/or outboard aileron servo controls on in-service airplanes. The actions specified in this AD are intended to prevent loss of hydraulic fluid, which may lead to the loss of the corresponding hydraulic system and its associated functions, and reduced controllability of the airplane.
AD 95-12-08 · published Jun 28, 1995, effective Jun 28, 1995
ATR - GIE Avions de Transport R gional Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes. This action requires repetitive inspections to detect displacement of the rear hinge bush, and to detect cracking or rupture of the rear hinge pin on the main landing gear (MLG) leg; and the correction of any discrepancies. This amendment is prompted by a report of the failure of this hinge pin on an in-service airplane. The actions specified in this AD are intended to prevent failure of the hinge pin, which can lead to failure of the MLG leg or MLG attachment assembly.
AD 95-12-09 · published Jun 28, 1995, effective Jun 28, 1995
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes. This action requires repetitive inspections to detect cracking in the hinge fittings of the nose landing gear (NLG) aft doors, and replacement of cracked fittings. This amendment is prompted by several reports of loss of an NLG aft door during landing, due to failure of the door's hinge fittings. The actions specified in this AD are intended to prevent the loss of an NLG aft door due to the failure of the hinge fittings; such loss of a door can result in damage to the surrounding aircraft structure or injury to persons on the ground.
AD 95-12-10 · published Jun 28, 1995, effective Jun 28, 1995
Airbus 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 ensure the proper installation of the electrical cable wiring of the evacuation slide system on the passenger and crew doors. This amendment is prompted by a report of incorrect installation of this wiring on two airplanes. The actions specified in this AD are intended to ensure that the electrical cable wiring is installed correctly so that it will not restrain the slide pack and prevent proper deployment of the slide. This condition, if not corrected, could impede the successful egress of passengers from the airplane during an emergency evacuation.
AD 95-12-11 · published Jun 28, 1995, effective Jun 28, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires a one-time inspection of the fuel flow from the main fuel supply hose/tube assembly, and repair, if necessary. This amendment is prompted by a report of a low pressure fuel valve found with the internal thermal relief valve assembled in the wrong position on one airplane. The actions specified in this AD are intended to prevent overpressurization of the fuel supply line due to the incorrect positioning of the internal thermal relief valve. Such overpressurization could cause the fuel pipe coupling to separate and allow fuel to leak into the engine pylon, thus posing a fire hazard.
AD 95-13-05 · published Jun 28, 1995, effective Jul 28, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the nacelle strut and wing structure, inspections and checks to detect discrepancies, and correction of discrepancies. This amendment is prompted by the development of a modification of the strut and wing structure that improves the damage tolerance capability and durability of the strut-to-wing attachments, and reduces reliance on inspections of those attachments. The actions specified by this AD are intended to prevent failure of the strut and subsequent loss of the engine.
AD 95-13-06 · published Jun 28, 1995, effective Jul 28, 1995
Boeing Model 747 Series Airplanes Equipped With General Electric Model CF6-80C2 Series Engines or Pratt & Whitney Model PW4000 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the nacelle strut and wing structure, inspections and checks to detect discrepancies, and correction of discrepancies. This amendment is prompted by the development of a modification of the strut and wing structure that improves the damage tolerance capability and durability of the strut-to-wing attachments, and reduces reliance on non-routine inspections of those attachments. The actions specified by this AD are intended to prevent failure of the strut and subsequent loss of the engine.
AD 95-13-07 · published Jun 28, 1995, effective Jul 28, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the nacelle strut and wing structure, inspections and checks to detect discrepancies, and correction of discrepancies. This amendment is prompted by the development of a modification of the strut and wing structure that improves the damage tolerance capability and durability of the strut-to-wing attachments, and reduces reliance on non-routine inspections of those attachments. The actions specified by this AD are intended to prevent failure of the strut and subsequent loss of the engine.
AD 95-12-21 · published Jun 29, 1995, effective Jun 29, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340-211 and 311 series airplanes. This action requires the installation of doublers on certain stringers located in the center fuselage. This amendment is prompted by the results of the manufacturer's full-scale fatigue test which indicate that fatigue cracking can occur at these stringer locations. The actions specified in this AD are intended to prevent reduced structural integrity of the fuselage due to the problems associated with fatigue cracks in the subject stringers.
AD 95-12-22 · published Jun 29, 1995, effective Jun 29, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires installation of a reinforcement modification on the structure of the left- and right-hand cowls of the thrust reversers. This amendment is prompted by the results of a full-scale fatigue test, conducted by the manufacturer, which indicated that fatigue cracks can occur between the 3 and 9 o'clock thrust reverser beams and the forward frame/"J"-ring. The actions specified in this AD are intended to prevent loss of the use of the thrust reversers as a result of the problems associated with fatigue cracking in their cowling structure.
AD 95-12-27 · published Jun 29, 1995, effective Jul 31, 1995
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires a revision to the input wiring for the flap control unit (FCU). This amendment requires a new systems test for the wiring of the trailing edge flap, and also expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by a report indicating that a wiring error was not detected by the system test required by the existing AD. The actions specified by this AD are intended to prevent the possibility of an all-flaps-up landing due to the loss of control of all flap operations.
AD 95-12-26 · published Jun 30, 1995, effective Jul 31, 1995
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747SP series airplanes, that currently requires repetitive inspections for cracks in the web of the wing front spar over engine numbers 2 and 3, and repair, if necessary. This amendment requires additional inspections in an area beyond that specified in the existing AD. This action also would provide for a new, optional modification, which, if accomplished, would constitute terminating action for the repetitive inspections. This amendment is prompted by a report of cracking in the web in an area outside the inspection zone specified in the existing AD. A crack in the web that is not detected before it extends outside the chord footprints can allow fuel leakage. The actions specified by this AD are intended to prevent fuel leakage onto an engine and a resultant fire due to cracking in the web of the wing front spar.
AD 95-12-02 · published Jun 8, 1995, effective Jun 23, 1995
Hiller Aircraft Corporation Model UH- 12A, UH-12B, UH-12C, UH-12D, and UH-12E Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Hiller Aircraft Corporation (Hiller) Model UH-12A, UH- 12B, UH- [[Page 30185]] 12C, UH-12D, and UH-12E helicopters. This action requires a dye-penetrant inspection of the head of the main rotor outboard tension-torsion (T-T) bar pin for cracks; a visual inspection of the outboard T-T bar pin for proper alignment, and an adjustment, if necessary; and, installation of shims at the inboard end of the drag strut. This amendment is prompted by two accidents involving failure of the outboard T-T bar pin on Hiller UH-12E helicopters. The actions specified by this AD are intended to prevent cracks in the head area of the outboard T-T bar pin, which could result in loss of in-plane stability of the main rotor blade and subsequent loss of control of the helicopter.
AD 95-10-09 · published Jun 16, 1995, effective Jun 16, 1995
Sikorsky Aircraft Corporation Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft Model S-58 and S-58T series helicopters, that requires the removal and replacement of the transmission main gear box ring gear (ring gear) within certain time intervals, and establishes a retirement life for the ring gear. This amendment is prompted by reports of failures of the ring gear due to slow-growth fatigue cracks. The actions specified by this AD are intended to prevent failure of the ring gear, failure of the main transmission, and subsequent loss of control of the helicopter.
AD 95-06-03 · published Jun 29, 1995, effective Jun 29, 1995
Robinson Helicopter Company Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-06-03 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (Robinson) Model R22 helicopters by individual letters. This AD requires an inspection and modification of the main rotor (M/R) gearbox. This amendment is prompted by a report of an incident involving a Model R22 helicopter in which the two M/R mast spanner nuts (nuts) became loose, resulting in failure of the M/R mast support structure. The actions specified by this AD are intended to prevent M/R separation and subsequent loss of control of the helicopter.
AD 95-11-09 · published Jun 29, 1995, effective Jul 14, 1995
Robinson Helicopter Company Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-11-09 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (Robinson) Model R22 helicopters by individual letters. This AD requires installation of a placard in the helicopter, and insertion of a prohibition against low-gravity (G) cyclic pushover maneuvers into the LIMITATIONS section of the Rotorcraft Flight Manual. This amendment is prompted by a recent Federal Aviation Administration (FAA) analysis of the manufacturer's data that indicates a low-G cyclic pushover maneuver may result in mast-bumping on the Robinson Model R22 helicopters. The actions specified by this AD are intended to prevent in-flight main rotor separation or contact between the main rotor blades and the airframe of the helicopter, and subsequent loss of control of the helicopter.
AD 95-11-10 · published Jun 29, 1995, effective Jul 14, 1995
Robinson Helicopter Company Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-11-10 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (Robinson) Model R44 helicopters by individual letters. This AD requires installation of a placard in the helicopter, and insertion of a prohibition against low-gravity (G) cyclic pushover maneuvers into the LIMITATIONS section of the Rotorcraft Flight Manual. This amendment is prompted by a recent Federal Aviation Administration (FAA) analysis of the manufacturer's data that indicates a low-G cyclic pushover maneuver may result in mast- bumping on the Robinson Model R44 helicopters. The actions specified by this AD are intended to prevent in-flight main rotor separation or contact between the main rotor blades and the airframe of the helicopter, and subsequent loss of control of the helicopter.
AD 95-11-14 · published Jun 30, 1995, effective Jun 30, 1995
Bell Helicopter Textron Canada Limited Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. Model 206A, 206B, 206L, 206L-1, 206L-3, and 206L-4 helicopters, that requires removal and replacement of certain crosstube assemblies (crosstubes). This amendment is prompted by two accidents attributed to crosstube failures and 27 field reports that indicated corrosion or metal fatigue may cause a failure of the affected crosstubes. The actions specified by this AD are intended to prevent failure of the crosstubes and subsequent loss of control of the helicopter.
AD 95-08-10 · published Jun 23, 1995, effective Jul 10, 1995
Continental Motors Engines
This document publishes in the Federal Register Airworthiness Directive (AD) 95-08- 10 that was sent previously to all known U.S. owners and operators of Teledyne Continental Motors (TCM) Model TSIO-360 E, EB, F, FB, G, GB, KB, LB, MB, and Model LTSIO-360 E, EB, and KB reciprocating engines by individual letters. This AD requires replacement of the suspect turbocharger check valves prior to further flight, and prohibits special flight permits. This amendment is prompted by three reported engine failures caused by incorrectly assembled turbocharger oil outlet check valves, resulting in an improperly expanded rivet that held the check valve flapper assembly together as one unit. The actions specified by this AD are intended to prevent complete engine failure due to an incorrectly assembled turbocharger oil outlet check valve.
AD 95-13-08 · published Jun 27, 1995, effective Jul 12, 1995
Pratt & Whitney Canada Model PT6A-67D Turboprop Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney Canada (PWC) PT6A-67D turboprop engines, that currently requires inspections of the compressor turbine (CT) disk and blades for cracking and other irregularities using visual inspections and fluorescent penetrant inspections (FPI). That AD also requires amending the Beech Model 1900D Airplane Flight Manual (AFM) and installing a placard that alerts the pilot of a requirement to restrict continuous engine operation above 94.0% and below 97.1% N1 (Gas Generator RPM). In addition, that AD requires the installation of parts having an improved design including a CT stator assembly, a CT shroud housing, CT turbine blades, feather seals, and a small exit duct assembly . This amendment continues the requirements of the current AD and adds the requirements to remove the placard from the cockpit and to remove the amendment to the AFM after installation of the improved engine components. This amendment is prompted by reports from operators and the manufacturer stating that the engine RPM operating restriction is not required after installation of the improved engine components, and that this engine operating restriction can impact aircraft handling. The actions specified by this AD are intended to prevent aircraft handling problems due to imposition of the engine RPM restriction.
AD 94-01-03 R2 · published Jun 13, 1995, effective Jun 28, 1995
Teledyne Continental Motors Appliances
This amendment revises an existing airworthiness directive (AD), applicable to Teledyne Continental Motors (TCM) (formerly Bendix) S-20, S-200, S-600, and S-1200 series magnetos, that currently requires replacing Bendix ignition coils and rotating magnets, regardless of total time in service (TIS), with improved TCM ignition coils, rotating magnets and marking magnetos to indicate compliance, except for the S-1200 series magnetos on which the AD requires replacing only the ignition coils as that series magneto already incorporates rotating magnets with the improved TCM design. This amendment removes several notes after the applicability paragraph and inserts these as paragraphs into the applicability itself and into the compliance section to clarify that these actions are mandatory. In addition, this amendment allows installation of replacement serviceable Parts Manufacturer Approval (PMA) parts in addition to TCM parts. Also, this amendment clarifies that Bendix magnetosreplaced with Slick magnetos satisfy the requirements of the AD, and that operators must perform the requirements of the AD on magnetos with Bendix magneto data plates that have been replaced with an overhaul facility's data plate. This amendment is prompted by comments that request clarification of the compliance notes and by the request to install replacement serviceable PMA parts. The actions specified by this AD are intended to prevent magneto failure and subsequent engine failure.
AD 95-08-13 · published Jun 2, 1995, effective Jun 2, 1995
Burkhart Grob Luft-Und Gliders
This amendment adopts a new airworthiness directive (AD) that applies to B. Grob Flugzeugbau (Grob) Model G109B gliders. This action requires replacing the elevator inner hinges with hinges of improved design. Two occurrences where the elevator inner hinges separated from the elevator prompted the required action. The actions specified by this AD are intended to prevent failure of these hinges because of delamination or corrosion, which, if not detected and corrected, could lead to loss of control of the glider.
AD 95-11-15 · published Jun 7, 1995, effective Jul 14, 1995
Alexander Schleicher GmbH & Co. Model ASK 21 Gliders
This amendment adopts a new airworthiness directive (AD) that applies to Alexander Schleicher GmbH & Co. (Alexander Schleicher) Model ASK 21 gliders. The required action requires replacing the parallel rocker with a part of improved design, and incorporating flight manual revisions. Two incidents of the parallel rocker breaking at the elevator connection on the affected gliders prompted this action. The actions specified by this AD are intended to prevent possible loss of elevator control that could result from a broken parallel rocker.
