34 Airworthiness Directives: 25 airplane, 3 rotorcraft, 4 engine, 2 propeller.
AD 94-26-16 · published Mar 1, 1995, effective Mar 1, 1995
Vickers-Armstrongs (Aircraft Limited) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 series airplanes, that requires various inspections to detect damage, corrosion, or cracking of certain taper plugs and split bushings of the engine mount, and replacement of taper plugs or split bushings with serviceable parts, if necessary. This amendment is prompted by a report of damage of the taper plug and split bushing of the engine mount due to the effects of corrosion. The actions specified by this AD are intended to prevent such damage, which could lead to failure of the engine mount attachment assembly and consequent separation of the engine from the airplane.
AD 95-03-06 · published Mar 1, 1995, effective Mar 31, 1995
Canadair Model CL-600-1A11, -2A12, and -2B16 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-600-1A11, -2A12, and -2B16 series airplanes, that requires a functional check and a test of the idle stop function of the engine throttle quadrant; repair or replacement, if necessary; and eventual replacement of the engine throttle quadrant with a new model. This amendment is prompted by reports of unintentional engine shutdown on certain of these airplanes due to problems associated with operation of the engine throttle quadrant. The actions specified by this AD are intended to ensure the proper operation of the throttle quadrant so as to prevent inadvertent shutdown of an engine while the airplane is taxiing or in flight.
AD 95-04-04 · published Mar 7, 1995, effective Apr 6, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model Avro 146-RJ70A and -RJ85A series airplanes, that requires an inspection to identify and remove certain cable terminals on the auxiliary power unit (APU) starter circuit and installation of certain new cable terminals. This amendment is prompted by a report that, during an inspection of the cable terminals on the APU starter circuit, incorrect cable terminals were found installed on these airplanes. The actions specified by this AD are intended to ensure the installation of correct starter cable terminals in the APU; incorrect cables could lead to the inability of the pilot to start the APU when needed in a situation of loss of other electrical power sources.
AD 95-04-08 · published Mar 7, 1995, effective Apr 6, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Boeing Model 747-300 and -400 series airplanes equipped with certain stretched upper deck evacuation slides manufactured by BFGoodrich series airplanes. This amendment requires modification of the slide's main restraint strap, regulator assembly, and turbo fan flapper retaining roll pins. This amendment is prompted by reports of loss of air pressure and non-inflation of the inflatable tubes of the slide due to problems associated with the restraint strap, regulator assembly, and turbo fan flapper retaining roll pins. The actions specified by this AD are intended to prevent loss of air pressure or non-inflation of the inflatable tubes of the slide, which could impede the successful evacuation of passengers from the airplane during an emergency.
AD 95-04-09 · published Mar 7, 1995, effective Apr 14, 1995
B-N Group Ltd. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Britten-Norman BN2A, BN2B, and BN2T Islander and BN2A Mk III Trislander series airplanes that are equipped with a nose wheel steering disconnect system with either a Modification NB/M/503 or Modification NB/M/733 nose undercarriage unit. This action requires repetitively inspecting the nose wheel steering drive ring for cracks, and replacing any cracked drive ring. A report of the rudder pedals jamming in the central position during takeoff on one of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent failure of the nose wheel steering system because of a cracked drive ring, which, if not detected and corrected, could result in the inability to move the rudder pedals.
AD 95-04-10 · published Mar 7, 1995, effective Apr 7, 1995
Beech Aircraft Corporation Models 34C, T-34C, and T-34C-1 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Beech Aircraft Corporation (Beech) Models 34C, T- 34C, and T-34C-1 airplanes. This action requires replacing the eight wing attachment steel bolts and hardware with Inconel bolts and hardware. A report of the right lower aft wing attachment nut assembly separating in two pieces on a Model T-34C-1 airplane prompted this action. The actions specified by this AD are intended to prevent the wing from separating from the fuselage because of failure of this assembly.
AD 95-04-01 · published Mar 8, 1995, effective Mar 8, 1995
The Boeing Company, Lockheed Martin Corporation, McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain transport category airplanes equipped with Honeywell Standard Windshear Detection and Recovery Guidance System (WSS). This action requires a revision to the FAA-approved Airplane Flight Manual (AFM) to alert the flight crew of the potential for significant delays in the WSS detecting windshear when the flaps of the airplane are in transition. This amendment is prompted by a report of an accident during which an airplane encountered severe windshear during a missed approached. The actions specified in this AD are intended to ensure that the flight crew is aware that there may be significant delays in the WSS detecting windshear when the flaps of the airplane are in transition.
AD 95-04-05 · published Mar 8, 1995, effective Apr 7, 1995
Bombardier (Formerly Canadair) Model CL-600-2B19 (Regional Jet Series 100) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires various modifications of the passenger doors. This amendment is prompted by reports that some passenger doors froze shut during flight and could not be opened after landing the airplane. The actions specified by this AD are intended to prevent the passenger doors from freezing shut, and consequently, prohibiting the passengers from exiting the airplane in the event of an emergency.
AD 95-02-06 · published Mar 10, 1995, effective Mar 10, 1995
British Aerospace Regional Aircraft Airplanes
This amendment supersedes Airworthiness Directive (AD) 91-08-01, which currently requires the following on Jetstream Aircraft Limited (JAL) Jetstream Model 3101 airplanes: revising the maximum speed for flaps at 50 degrees from 153/149 knots indicated airspeed (KIAS) to 130 KIAS; and limiting the maximum flap extension to 20 degrees anytime ice is present on the airplane. This action requires incorporating a flap system modification as terminating action for the requirements of AD 91-08-01. The actions specified by this AD are intended to prevent sudden pitch down of the airplane during icing conditions, which could lead to loss of control of the airplane.
AD 94-18-04 R1 · published Mar 14, 1995, effective Mar 24, 1995
Univair Aircraft Corporation Airplanes
This amendment revises Airworthiness Directive (AD) 94-18-04, which currently requires the following on Univair Aircraft Corporation (Univair) Models Ercoupe 415-C, 415-CD, 415-D, 415-E, and 415-G, Forney F-1 and F-1A, Alon A-2 and A-2A, and Mooney M10 airplanes: installing inspection openings in the outer wing panels, inspecting (one-time) the wing outer panel structural components for corrosion, and repairing any corroded wing outer panel structural component. Several reports of corrosion in the outer wing panels of the affected airplanes prompted that AD. This action incorporates a revision to the service information to include procedures that the Federal Aviation Administration (FAA) has determined are necessary for installing future outer wing panel inspection openings. The actions specified by this AD are intended to prevent wing damage caused by a corroded wing outer panel structural component, which, if not detected and corrected, could progress to the point of structural failure.
AD 95-06-02 · published Mar 14, 1995, effective Apr 13, 1995
Boeing Model 747 Series Airplanes, Excluding Airplanes Equipped With Pratt & Whitney PW4000 and General Electric CF6-80C2 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires replacement of certain fuse pins on the upper link of the inboard and outboard struts. This AD would also require inspections to detect corrosion or cracks of certain fuse pins, and replacement, if necessary. This amendment is prompted by reports of cracked or corroded fuse pins on the upper link of the inboard and outboard struts, which could result in fracturing of the pins. The actions specified by this AD are intended to prevent failure of the strut and separation of an engine from the airplane due to fracturing of the fuse pins.
AD 95-02-09 · published Mar 16, 1995, effective Mar 16, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model ATP airplanes, that requires inspections to detect damage, overheating, and proper operation of the DC connections and cooling fans in certain transformer rectifier units (TRU), and repair or replacement, if necessary. This amendment is prompted by a report of the loss of all DC electrical power, except for the battery emergency bus, due to failure of the TRU's, which occurred during flight. The actions specified by this AD are intended to prevent such failures that could lead to loss of essential electrical power required to continue safe flight of the airplane.
AD 95-02-05 · published Mar 17, 1995, effective Mar 17, 1995
British Aerospace Regional Aircraft Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This action requires repetitively inspecting the passenger/crew cabin door handle mounting platform structure for cracks, and, if found cracked, replacing with a structure of improved design as terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent the inability to open the passenger/crew door because of a cracked internal handle mounting platform structure, which, if not detected and corrected, could result in passenger injury if emergency evacuation was needed.
AD 95-02-12 · published Mar 17, 1995, effective Mar 17, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of the fixed engine cowling at the forward and aft crane beam attachment; and an inspection of the forward and aft crane beam to detect surface damage, and repair, if necessary. This amendment is prompted by several reports of rear cabin noise (engine rumble) during flight and while taxiing, which may have been caused by the interference between the forward and aft crane beams and the fasteners in the fixed engine cowling. The actions specified by this AD are intended to prevent chafing due to normal engine vibration, which could result in structural damage to the engine mount and possible separation of the engine from the airplane.
AD 95-04-07 · published Mar 17, 1995, effective Mar 17, 1995
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes. This action requires inspections to determine the condition of the lockwires on the forward engine mount bolts and correction of any discrepancies found. This action also provides for termination of the inspections for some airplanes by installing retainers on the bolts. This amendment is prompted by reports of stretched or broken lockwires on the forward engine mount bolts. The actions specified in this AD are intended to prevent broken lockwires, which could result in loosening of the engine mount bolts, and subsequent separation of the engine from the airplane.\n\n\tComments for inclusion in the Rules Docket must be received on or before May 1, 1995.
AD 95-04-15 · published Mar 17, 1995, effective Mar 17, 1995
McDonnell Douglas Corporation Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires inspection to detect cracking of the outboard and inboard surfaces of the upper spar angles of certain wing pylons, and repair of any cracked upper spar angles. This amendment requires repetitive inspections to detect cracking of the upper spar angles, and revision of the applicability to exclude an airplane and to include certain other airplanes. This amendment is prompted by an additional report of cracking of the upper inboard spar cap. The actions specified in this AD are intended to prevent reduced structural integrity of the airplane due to cracking in the subject areas.\n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-54A049, Revision 1, dated February 7, 1995, as listed in the regulations, is approved by the Director of the Federal Register as of March 17, 1995.\n\n\tThe incorporation by reference of McDonnell Douglas MD-11 Alert Service Bulletin A54-49, dated December 2, 1994, as listed in the regulations, was approved previously by the Director of the Federal Register as of January 12, 1995 (59 FR 66669, December 28, 1994).\n\n\tComments for inclusion in the Rules Docket must be received on or before May 1, 1995.
AD 95-03-04 · published Mar 20, 1995, effective Mar 20, 1995
Vickers-Armstrongs (Aircraft Limited) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 series airplanes, that requires repetitive inspections to detect fatigue cracking in the pivot pins that attach both nose wheel steering actuators to the steering head assembly, and replacement of cracked pins. This amendment is prompted by a reported failure of a pivot pin due to fatigue cracking. The actions specified by this AD are intended to prevent failure of the pivot pin, which could result in the loss of nose wheel steering capability.
AD 95-06-05 · published Mar 21, 1995, effective Apr 5, 1995
Boeing Model 737-200 and -300 Series Airplanes Equipped With Cargo Doors Installed in Accordance With Supplemental Type Certification (STC) SA2969SO
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200 and -300 series airplanes. This action requires inspections to detect cracking of the fuselage frames at certain locations below the lower jamb of the upper deck main cargo door, and repair, if necessary. This amendment is prompted by reports of fatigue cracking in the fuselage frames at these locations. The actions specified in this AD are intended to prevent rapid decompression of the airplane due to fatigue cracking in the fuselage frames of the main deck cargo door.
AD 95-06-04 · published Mar 22, 1995, effective Apr 21, 1995
McDonnell Douglas Model DC-9-80 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9-80 series airplanes, that requires inspection and replacement of certain suspect horizontal stabilizer primary trim motors. This amendment is prompted by an analysis which revealed that certain incorrectly manufactured motor shafts could fail prematurely and, in turn, cause the primary trim motor to fail. The actions specified by this AD are intended to prevent such failures of the primary trim motor, which could ultimately result in reduced controllability of the airplane.
AD 95-06-06 · published Mar 22, 1995, effective Apr 21, 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 a visual inspection to verify proper installation of the wire termination lugs on the ignition selector switch, and removal and correct installation of any improperly installed wire termination lugs. This amendment also requires application of sealant to the wire termination lugs and the attachment screws. This amendment is prompted by a report that, during the manufacturer's production flight testing, an abnormal engine start valve open annunciation for engine No. 2 occurred and resulted in an uncontained failure of the engine starter. The actions specified by this AD are intended to prevent damage to the engine cowling, damage to adjacent engine components, and possible fire in the cowling, due to an uncontained failure of the engine starter.
AD 93-15-02 R1 · published Mar 27, 1995, effective Apr 17, 1995
Fairchild Aircraft SA226 and SA227 Series Airplanes
This amendment revises Airworthiness Directive (AD) 93-15-02, which requires the following on Fairchild Aircraft SA226 and SA227 series airplanes that are equipped with a certain Simmonds-Precision pitch trim actuator: repetitively measuring the freeplay of the pitch trim actuator and repetitively inspecting the actuator for rod slippage; immediately replacing any actuator if certain freeplay limitations are not met or rod slippage is evident; and eventually replacing the actuator regardless of the inspection results. This action maintains these requirements, but reduces the hours time-in- service (TIS) before the initial inspection is required, and shortens both the time period between repetitive inspections and the actuator replacement compliance time (unless the replacement actuator is new or if the nut tube assemblies have been replaced during overhaul). An in- flight incident where the referenced actuator on one of the affected airplanes failed after accomplishment of the 5,000-hour initial inspection (with satisfactory results) prompted this action. The actions specified by this AD are intended to prevent the horizontal stabilizer from going nose-down or jamming because of pitch trim actuator failure, which could result in loss of control of the airplane.
AD 95-02-17 · published Mar 30, 1995, effective Apr 17, 1995
Beech Aircraft Corporation Model 1900D Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-02-17, which was sent previously to known U.S. owners and operators of certain Beech Aircraft Corporation Model 1900D airplanes. This AD requires inspecting (one- time) the elevator trim tab control cables at the top of the vertical stabilizer to ensure that cables (at the left, right, and crossover pulleys) are correctly routed around the pulleys, within the cable guide pins, and are not contacting any structure; and replacing any cable that is incorrectly routed or chafed. The actions specified by this AD are intended to prevent in-flight separation of the elevator trim tab control cable caused by misrouting, which could result in loss of control of the airplane.
AD 95-03-07 · published Mar 30, 1995, effective Mar 30, 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, that requires an inspection to determine the model and orientation of certain flight control rods, and replacement of the rods with modified rods, if necessary. This amendment is prompted by reports of corrosion found on the pitch and rudder trim and rudder travel limiter fail-safe rods. The actions specified by this AD are intended to prevent problems associated with corrosion of the flight control rods, which could compromise the required strength of these items.
AD 95-03-08 · published Mar 30, 1995, effective Mar 30, 1995
ATR - GIE Avions de Transport R gional Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and -320 series airplanes, that requires an inspection to determine the model and orientation of certain flight control rods, and replacement with modified rods, if necessary. This amendment is prompted by reports of corrosion found on the pitch trim and rudder trim rods. The actions specified by this AD are intended to prevent problems associated with corrosion of the flight control rods, which could compromise the required strength of these items.
AD 95-04-13 · published Mar 2, 1995, effective Mar 17, 1995
Robinson Helicopter Company Model R44 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company Model R44 helicopters, that currently requires revisions to the Limitations section, the Normal Procedures section, and the Emergency Procedures section of the R44 Rotorcraft Flight Manual, revised September 6, 1994. These revisions limit operations in high winds and turbulence; provide information about main rotor (M/R) stalls and mast bumping; and provide recommendations for avoiding these situations. Additionally, emergency procedures are provided for use should certain conditions be encountered. This amendment requires the same revisions required by the existing Priority Letter AD, but revises certain words and phrases to further clarify the revised Limitations and Normal Procedures sections, deletes the paragraph that referenced recording compliance with the AD, and adds another paragraph that states that no special flight permits will be issued prior to compliance with this AD. This amendment is prompted by two Model R44 accidents since April 1994 involving M/R blades contacting the helicopters' fuselage; and, 26 accidents involving M/R blades contacting the fuselage on the Model R22 helicopter since 1981. The Model R22 helicopter M/R system design is similar to the Model R44 helicopter M/R system design. The actions specified by this AD are intended to prevent M/R stall or mast bumping, which could result in the M/R blades contacting the fuselage causing failure of the M/R system and subsequent loss of control of the helicopter.
AD 95-04-14 · published Mar 2, 1995, effective Mar 17, 1995
Robinson Helicopter Company Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company Model R22 helicopters, that currently requires revisions to the Limitations section, the Normal Procedures section, and the Emergency Procedures section of the R22 Rotorcraft Flight Manual, revised February 4, 1993. These revisions limit operations in high winds and turbulence; provide information about main rotor (M/R) stalls and mast bumping; and, provide recommendations for avoiding these situations. Additionally, emergency procedures are provided for use should certain conditions be encountered. This amendment requires the same revisions required by the existing Priority Letter AD, but revises certain words and phrases to further clarify the revised Limitations and Normal Procedures sections, deletes the paragraph that referenced recording compliance with the AD, and adds another paragraph that states that no special flight permits will be issued prior to compliance with this AD. This amendment is prompted by 26 accidents since 1981 that resulted in fatalities and involved the M/R blades contacting the helicopters' fuselage. The actions specified by this AD are intended to prevent M/R stall or mast bumping, which could result in the M/R blades contacting the fuselage causing failure of the M/R system and subsequent loss of control of the helicopter.
AD 95-06-07 · published Mar 20, 1995, effective Apr 4, 1995
Robinson Helicopter Company Model R22 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) Model R22 helicopters, that currently requires an initial dye penetrant inspection of the main rotor drive forward flexplate (flexplate), and repetitive visual inspections of certain installed flexplates. This amendment is prompted by three accidents reported by the airworthiness authority of Australia involving failure of the flexplate, located between the main rotor gearbox and clutch assembly. The actions specified by this AD are intended to prevent failure of the flexplate, failure of the main rotor drive system, and subsequent loss of control of the helicopter.
AD 95-04-11 · published Mar 2, 1995, effective Apr 3, 1995
Honeywell International Inc. Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Textron Lycoming ALF502R series turbofan engines, that currently requires the establishment of a reduced stress rupture retirement life limit for certain third stage turbine disks. This amendment establishes a new increased stress rupture retirement life limit for certain third stage turbine disks used in conjunction with third stage turbine nozzles that have improved cooling effectiveness, expands the applicability by adding the ALF502L series engines, and establishes other new reduced stress rupture retirement life limits. This amendment is prompted by the introduction of an improved design third stage turbine nozzle, and a new reduced stress rupture retirement life limit for certain third stage turbine disks on the ALF502L series engines. The actions specified by this AD are intended to prevent a total loss of engine power, inflight engine shutdown, and possible damage to the aircraft.
AD 95-03-15 · published Mar 7, 1995, effective May 8, 1995
Honeywell International Inc. Engines
This amendment adopts a new airworthiness directive (AD), applicable to Textron Lycoming ALF502R series turbofan engines, that reduces the service life for the No. 2 stage turbine disk, reduces the service lives for No. 1 and No. 3 through No. 7 stage compressor rotor disks, and requires a scheduled removal of these disks from service. This amendment is prompted by reports of cracks in disks returned from the field and in disks tested by the manufacturer. The actions specified by this AD are intended to prevent disk failure resulting in a possible uncontained engine failure.
AD 95-04-02 · published Mar 7, 1995, effective May 8, 1995
Rolls-Royce plc Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Rolls- Royce, plc RB211-524 series turbofan engines, that requires a one-time modification of the nozzle guide vane (NGV) assembly to incorporate vane core reinforcement inserts which would prevent release of the stage 2 NGV seal ring, rotor contact, and severance of the rotor drive arm. This amendment is prompted by a report of an uncontained stage 1 low pressure turbine failure. The actions specified by this AD are intended to prevent release of the stage 2 NGV seal ring, which could result in an uncontained engine failure. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 8, 1995.
AD 95-07-01 · published Mar 28, 1995, effective Apr 12, 1995
Lycoming Engines, Textron Lycoming, AVCO Corporation Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-07-01 that was sent previously to all known U.S. owners and operators of Textron Lycoming O-360, LO-360, HO-360, HIO-360, TIO-360, LIO-360, AEIO-360, O-540, IO-540, TIO-540, LTIO-540, IVO-540, AEIO-540, TIO-541, and IO-720 series reciprocating engines by individual letters. This AD requires removal prior to further flight of suspect unapproved connecting rod bolts and replacement with serviceable connecting rod bolts. This amendment is prompted by reports of connecting rod bolt failures. The actions specified by this AD are intended to prevent engine failure due to connecting rod bolt failure, which could result in damage to or loss of the aircraft.
AD 95-03-03 · published Mar 2, 1995, effective Mar 17, 1995
Hartzell Propeller, Inc. Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. Model HC-B4TN-3/T10173F(N)(B,K)-12.5 and HC-B4TN-3A/T10173F(N)(B,K)- 12.5 propellers installed on Beech A100 and A100A aircraft. This action requires an initial and repetitive inspections, and specified rework or retirement, as necessary, of the propeller hub assemblies and propeller blades. This amendment is prompted by a determination that the current hub design and blade repair limits do not adequately protect against initiation of fatigue cracks in the propeller hub arm bore and do not prevent the resonant speed of the propeller from shifting into the permitted ground idle operating range. The actions specified in this AD are intended to prevent initiation of fatigue cracks in the propeller hub arm bore and subsequent progression to failure, with departure of the hub arm and blade, that may result in loss of aircraft control.
AD 95-05-03 · published Mar 8, 1995, effective Mar 23, 1995
Hamilton Standard 14RF Series, 14SF Series, and Hamilton Standard/British Aerospace Model 6/5500/F Propellers
This amendment supersedes an existing airworthiness directive (AD), applicable to Hamilton Standard 14RF series, 14SF series, and Hamilton Standard/British Aerospace 6/5500/F series propellers, that currently requires a one-time ultrasonic shear wave inspection for cracks in the propeller blade taper bore. This amendment requires initial and repetitive ultrasonic shear wave inspections, and a one- time visual and borescope inspection of the taper bore for corrosion as a terminating action to the ultrasonic shear wave inspections. This amendment is prompted by reports of two incidents where a portion of the propeller blade was lost in flight. The actions specified by this AD are intended to prevent loss of a propeller blade due to cracks initiating in the blade taper bore, that can result in possible aircraft damage, and possible loss of aircraft control.
