20 Airworthiness Directives: 14 airplane, 3 rotorcraft, 3 engine.
AD 95-02-19 · published Feb 2, 1995, effective Mar 10, 1995
Jetstream Aircraft Limited (formerly British Aerospace, Regional Airlines Limited) HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 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 left and right pilot windscreens for poly vinyl butyrate (PVB) interlayer cracks, and replacing any windscreen that has a crack exceeding certain limits. Several reports of PVB interlayer cracking of pilot windscreens on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent such windscreen cracking, which, if not detected and corrected, could result in decompression injuries.
AD 94-26-08 · published Feb 3, 1995, effective Feb 3, 1995
Fokker Services Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that requires accomplishment of certain structural modifications. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion 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 degradation in the structural capabilities of the affected airplanes. This action also reflects the FAA's decision that long term continued operational safety should be assured by actual modification of the airframe rather than repetitive inspections.
AD 94-26-14 · published Feb 3, 1995, effective Feb 3, 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 inspections to detect cracks in the chassis side bracing structure and in the chassis top strut support intercostals inside the wings, and replacement of discrepant parts with new parts. This proposal would also require inspection of the intercostals to determine the specification of the material, if necessary; and replacement of discrepant parts with new parts. This amendment is prompted by a report of cracking in the chassis top strut support intercostal in the side bracing structure inside the wing due to the effects of metal fatigue. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could lead to the failure of the chassis side bracing structure inside the wings and consequent reduced structural integrity of the chassis support structure.
AD 95-02-18 · published Feb 3, 1995, effective Mar 25, 1995
Beech Aircraft Corporation Models 1900, 1900C, and 1900D Airplanes
This amendment supersedes Airworthiness Directive (AD) 92-06- 09, which currently requires repetitively inspecting the engine trusses for cracks on Beech Aircraft Corporation (Beech) Model 1900 and certain Model 1900C airplanes, repairing or replacing any cracked engine truss, and installing reinforcement doublers. That AD also provides the option of installing an engine truss of improved design as terminating action for the repetitive inspections. Since issuing that AD, the Federal Aviation Administration (FAA) has received several reports of these improved design trusses cracking in Area A (as specified in the service information) of the engine truss. This action retains the currently required repetitive inspections, but shortens the repetitive inspection interval in Area A and eliminates the inspection-terminating replacement option; and also incorporates the Beech Models 1900C and 1900D airplanes that have engine trusses of this same type design installed at manufacture. The actions specified by this AD are intended to prevent failure of the engine truss assembly caused by a cracked engine truss.
AD 94-26-51 · published Feb 6, 1995, effective Feb 6, 1995
The Boeing Company Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T94-26-51 that was sent previously to all known U.S. owners and operators of all McDonnell Douglas Model MD-11 series airplanes by individual telegrams. This AD requires a revision to the FAA-approved Airplane Flight Manual (AFM) to prohibit autoland operation below 100 feet above ground level (AGL), and the installation of certain flight control computer software. This AD provides for an optional terminating action for the AFM revision. This amendment is prompted by reports of a loose nut on a coaxial connector on a radio altimeter receiver/transmitter rack, and the transmittal of erroneous altitude data to the flight control computers below 100 feet AGL, which resulted in abnormal flare (pitch) control during autoland operation. The actions specified by this AD are intended to prevent abnormal flare (pitch) control, which could result in degradation of the landing capability of the airplane.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 6, 1995.\n\tComments for inclusion in the Rules Docket must be received on or before March 21, 1995.
AD 95-02-07 · published Feb 14, 1995, effective Mar 16, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires installation of a seal on the wing front spar at each engine strut. This amendment is prompted by a report of a fire that occurred due to fuel leakage from the fuel line coupling in the engine strut area along the wing front spar while the airplane was on the ground after engine shutdown. The actions specified by this AD are intended to ensure that fuel is contained within the strut drainage area and channeled away from ignition sources.
AD 95-02-08 · published Feb 14, 1995, effective Mar 16, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires modification of certain fuselage support structure for the number 2 galley. This amendment is prompted by results of engineering tests and analyses which revealed that certain fuselage support structure for the number 2 galley is unable to support certain loads that may occur during emergency landing conditions. If the fuselage support structure breaks, the galley may shift and cause blockage of the forward service door (galley door). The actions specified by this AD are intended to prevent inability of passengers and crew to exit the airplane through this door after an emergency landing.
AD 95-02-11 · published Feb 15, 1995, effective Mar 2, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-87 (MD-87) series airplanes. This action requires an inspection to detect chafing or arcing damage to the wiring of the aft right coatroom, the intercostal, and the recirculation duct assembly near longeron 5; and modification of the wiring installation for the aft right coatroom. This amendment is prompted by a report of an electrical fire that started due to a short in the coatroom wiring, which was caused by arcing and chafing damage to the wiring. The actions specified in this AD are intended to prevent severe damage to the airframe in the event of a fire caused by arcing and chafing damage to the coatroom wiring.
AD 95-02-13 · published Feb 15, 1995, effective Mar 17, 1995
Boeing Model 747 Series Airplanes Equipped With General Electric CF6-80C2 Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the fire extinguishing system in the number two engine strut. This amendment is prompted by reports of chafing of the fire extinguishing tubes [[Page 8539]] in a certain inboard strut to wing area. The actions specified by this AD are intended to prevent chafing of the fire extinguishing tube; such chafing could cause cracking of the tube and consequently produce a hole in the fire extinguishing tube, which could prevent the proper distribution of the fire extinguisher agent within the nacelle in the event of a fire.
AD 95-02-14 · published Feb 15, 1995, effective Mar 17, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, and Model C-9 (military) airplanes, that requires replacement of the engine nose cowl attaching bolts and the installation of bearing plates on the nose cowl attach ring. This amendment is prompted by incidents in which the nose cowl separated from the airplane due to the elongation and/or breakout of the nose cowl's attachment ring holes, and failure of the attaching bolts. The actions specified by this AD are intended to prevent separation of the engine nose cowl from the airplane, which could result in damage to the airplane structure or could present a hazard to persons or property on the ground.
AD 95-03-05 · published Feb 16, 1995, effective Mar 20, 1995
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires an inspection to detect cracks in the cleats at certain rib stations of the wing, and replacement of the cracked cleats with new cleats. This amendment is prompted by a report that, during manufacture of the wings of these airplanes, cracks were discovered in the cleats at the left- and right-hand rib station 8200 of the wing due to improper installation of certain bolts. The actions specified by this AD are intended to prevent cracking of the cleats, which could result in reduced structural integrity of the wing.
AD 95-02-15 · published Feb 21, 1995, effective Mar 23, 1995
Boeing Model 747-100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100 series airplanes, that currently requires repetitive inspections to detect cracking of the wing front spar web above engine numbers 2 and 3, and repair, if necessary. This amendment requires repetitive inspections to detect cracks in the web and cracked or broken fasteners in an area beyond that specified in the existing AD. This amendment also provides an optional terminating action for the repetitive inspections. This amendment is prompted by reports of broken fasteners and cracking of the web common to the upper and lower chords in an area outside the inspection zone specified in the existing AD. The actions specified by this AD are intended to prevent fuel leakage onto an engine and a resultant fire due to cracking or broken fasteners in the wing front spar.
AD 96-09-28 · published Feb 21, 1995, effective Feb 21, 1995
ATR - GIE Avions de Transport R gional Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Aerospatiale Model ATR-42 and ATR-72 series airplanes. Unless modifications are accomplished or alternative procedures and training are adopted, that AD currently prohibits operation of the airplane in certain icing conditions, and requires restrictions on the use of the autopilot in certain conditions. That AD was prompted by an FAA determination that, during flight, in certain icing conditions, and with the airplane in a specific flight configuration, a ridge of ice can form on the wing and cause an interruption in the airflow over the ailerons, aileron deflection, and resultant lateral control forces. The actions specified by that AD are intended to prevent a roll upset from which the flight crew may be unable to recover. This action adds requirements for modification of the deicing boots on the leading edge of the wing and various follow-on actions. This action also removes certainlimitations and procedures.
AD 95-03-09 · published Feb 28, 1995, effective Mar 30, 1995
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker F28 Mark 0100 series airplanes, that requires inspecting the teleflex cable of the landing gear to detect corrosion, moisture, or improper greasing, and replacing discrepant teleflex cables with serviceable parts. This amendment is prompted by reports of difficulties with the operation of the selector handle of the landing gear when ``gear down'' is selected, due to improper greasing of the teleflex cable of the landing gear during production. The actions specified by this AD are intended to prevent moisture from accumulating on the teleflex cable, which could result in corrosion of the teleflex cable that could inhibit operation of the selector handle of the landing gear.
AD 95-03-11 · published Feb 14, 1995, effective Mar 1, 1995
MD Helicopters, Inc. Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems and Hughes Helicopters, Inc. Model 369, OH-6A, and YOH-6A series helicopters. This action requires initial and repetitive inspections of the tail rotor blade abrasion strip (abrasion strip), installation of stainless steel abrasion tape over the inboard end of the abrasion strip, and as a terminating action, installation of a tail rotor blade with a new-design abrasion strip. This amendment is prompted by several incidents of riveted abrasion strips debonding and separating during flight, resulting in severe out-of-balance conditions and subsequent separation of the tail rotor gearbox from the helicopter. The actions specified in this AD are intended to prevent loss of the abrasion strip, separation of a tail rotor blade, separation of the tail rotor gearbox, and subsequent loss of control of the helicopter.
AD 95-03-12 · published Feb 14, 1995, effective Mar 1, 1995
Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A Series Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A series helicopters, that currently requires an initial and repetitive visual inspection of the clutch control spring assembly for component wear and replacement of affected unairworthy parts. This amendment requires the same initial and repetitive visual inspection and replacements required by the existing Priority Letter AD, but references a revised service bulletin and provides replacement procedures for the aluminum spring retainer thermofit tube (plastic sleeve). This amendment is prompted by a recent accident involving a Model 269C helicopter that reportedly lost engine drive power at 100 feet above ground level (AGL) with a resulting unsuccessful autorotative landing, and the manufacturer's issuance of revised service information that provides more detailed instructions for replacement of two components of the belt drive clutch control assembly. The actions specified by this AD are intended to prevent failure of the aluminum spring retainer, loss of power to the rotor drive system, and a subsequent forced landing.
AD 95-03-13 · published Feb 14, 1995, effective Mar 21, 1995
MD Helicopters, Inc. Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Company and Hughes Helicopters, Inc. Model 369 and OH-6A series helicopters with certain main rotor (M/R) blade assemblies or certain M/R hub lead-lag assemblies installed, that currently requires repetitive inspections and checks for cracks. This amendment requires the same inspections as the superseded AD, but would eliminate pilot checks, expand the areas of inspection, and require the application of slippage marks on each M/R blade root fitting lug and related bushings. This amendment is prompted by additional reports of cracks in the M/R blade root fittings, lugs, and adjacent blade skin, and movement of the root fitting bushings. The actions specified by this AD are intended to prevent failure of a M/R blade assembly or a M/R hub lead-lag link assembly, loss of a M/R blade, and subsequent loss of control of the helicopter.
AD 95-02-16 · published Feb 3, 1995, effective Feb 21, 1995
Pratt & Whitney Division Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT8D series turbofan engines, that currently requires initial and repetitive inspections of the Number 7 fuel nozzle and support assembly, replacement of the Number 7 fuel nozzle and support assembly with a more leak-resistant configuration, and replacement of aluminum oil pressure and scavenge tube fittings with steel fittings. This amendment adds a requirement incorporated in a new revision of a PW Alert Service Bulletin (ASB) that was omitted from the existing AD to replace an additional aluminum oil scavenge line bolt with a steel bolt. This amendment also makes a correction to a note in the compliance section to apply only to PW JT8D-200 series engines. This amendment is prompted by the need to make these corrections. The actions specified by this AD are intended to prevent fuel leakage from the Number 7 fuel nozzle and support assembly, ignition of that leaking fuel, and liberation of oil from melted oil line fittings, which can result in an uncontained engine fire and damage to the aircraft.
AD 95-03-14 · published Feb 24, 1995, effective Mar 13, 1995
Continental Motors Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Teledyne Continental Motors (TCM) IO-346, IO-520, and IO-550 series reciprocating engines, that currently requires initial and repetitive inspections of the engine mount brackets for cracks, and if found cracked, replacement with improved design engine mount brackets. All engine mount brackets require replacement with improved design engine mount brackets at the next engine removal after the effective date of that airworthiness directive (AD). This amendment clarifies the identification procedures to determine which engine mount brackets must be inspected. This amendment is prompted by reports that the engine mount bracket part numbers, which are ink stamped, can be easily obliterated. The actions specified by this AD are intended to prevent engine separation from the aircraft due to cracks in the engine mount brackets.
AD 94-25-07 · published Feb 28, 1995, effective Mar 30, 1995
Pratt & Whitney Division Engines
This amendment supersedes an existing telegraphic airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT8D series turbofan engines, that currently requires repetitive ultrasonic inspections of a combustion chamber outer case (CCOC) weld, but also allows visual inspection or fluorescent magnetic penetrant inspection (FMPI) of certain CCOC's under specified conditions. This amendment allows ultrasonic inspections only. This amendment is prompted by the greater availability of ultrasonic inspection equipment, which provides a more definitive means of discovering cracks than either visual inspections or FMPI. The actions specified by this AD are intended to prevent rupture of the CCOC, which could result in fire, engine cowl release, or aircraft damage.
