23 Airworthiness Directives: 17 airplane, 4 rotorcraft, 1 engine, 1 propeller.
AD 94-24-01 · published Dec 1, 1995, effective Dec 1, 1995
British Aerospace Regional Aircraft Airplanes
This amendment supersedes Airworthiness Directive (AD) 87-04-04 and AD 89-16-02, which currently require the following on Jetstream Aircraft Limited (JAL) HP 137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes: repetitively inspecting the universal joints and universal rivets, replacing any damaged part, and limiting the in-service life of the torque tube shaft assembly. JAL has introduced an improved flap torque tube shaft assembly that includes universal joints that are not life limited. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action requires installing this improved flap torque shaft assembly in place of the repetitive inspection and life limit requirements of the two existing AD's. The actions specified by this AD are intended to prevent failure of the flap torque assembly, which could result in asymmetric flap deployment and loss of control of the airplane.
AD 95-23-08 · published Dec 1, 1995, effective Dec 1, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Avro Model BAe 146 series airplanes. This action requires inspections to detect cracking and damage of the fastener holes in the butt strap at rib 2 at the lower surface of the right-hand wing; repair of discrepancies; and replacement of the fastener bolts. This amendment is prompted by a report that certain wings were manufactured with a reduction in the amount of edge margin between the fastener hole centers and the edge of the butt strap; this condition can result in a decrease in the long-term damage tolerance residual strength of the wing. The actions specified in this AD are intended to prevent cracking and other problems associated with a such decrease in the long-term damage tolerance residual strength of the wing.
AD 95-23-09 · published Dec 1, 1995, effective Jan 2, 1996
McDonnell Douglas Corporation Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that currently requires the implementation of a program of structural inspections to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This amendment requires clarification of some Principle Structural Elements (PSE) and some non-destructive inspection (NDI) procedures. This amendment is prompted by new data submitted by the manufacturer indicating that certain revisions to the program are necessary in order to clarify some PSE's and some NDI procedures. The actions specified by this AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes.
AD 95-24-14 · published Dec 1, 1995, effective Dec 18, 1995
Bombardier Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-8 series airplanes. This action requires eddy current inspections to detect cracking of the pivot tubes in the drag strut of the nose landing gear (NLG), and repair or replacement of any cracked tube with a serviceable or new tube. This amendment is prompted by reports that the pivot tubes cracked or failed completely due to fatigue. The actions specified in this AD are intended to prevent such fatigue cracking and subsequent failure of the pivot tube, which could result in a nose gear-up landing.
AD 95-01-06 R1 · published Dec 5, 1995, effective Dec 20, 1995
Boeing Model 737-200 and -300 Series Airplanes Equipped With Cargo Doors Installed in Accordance With Supplemental Type Certificate (STC) SA2969SO
This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200 and -300 series airplanes, that currently requires inspections to detect cracking in the radii on the support angles on the lower jamb (latch lug fittings) of the main deck cargo door, and replacement of cracked parts. That amendment was prompted by reports of premature fatigue cracking on the support angles on the lower jamb of the main deck cargo door. The actions specified in that AD are intended to prevent in-flight separation of the main deck cargo door from the airplane due to fatigue cracking on the support angles on the lower door jamb. This amendment requires a change in the cognizant aircraft certification office for requesting approvals of alternative methods of compliance with the provisions of this AD.
AD 95-25-11 · published Dec 12, 1995, effective Dec 27, 1995
Empresa Brasileira de Aeronautica, S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-120 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to limit the revolutions per minute (RPM) of the propeller during ground operation, and removing and installing a new placard. This AD also requires revising the FAA-approved maintenance program to limit the maximum RPM of the propeller during ground operations. This amendment is prompted by reports of failures of in-service propellers and subsequent testing, which revealed that operating the propeller at or near certain nominal propeller RPM produces high vibration stress. The actions specified in this AD are intended to limit exposure to high vibration stresses during ground operations under certain weather conditions; this situation could accelerate fatigue cracking if corrosion is present in the propeller, which could lead to the failure of the propeller and subsequent reduced controllability of the airplane.
AD 95-25-01 · published Dec 15, 1995, effective Jan 16, 1996
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires various modifications and terminating actions for the passenger door, and repair, if necessary. This amendment requires additional inspections, and replacement of certain parts, if necessary. This amendment also provides for optional terminating action for certain inspections. This amendment is prompted by reports of excessive gaps between lockout cams and crank stops, which resulted in broken power assist triggers. The actions specified by this AD are intended to prevent broken power assist triggers, which could result in an inoperative door opening system during an emergency evacuation.
AD 95-25-05 · published Dec 15, 1995, effective Jan 16, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400A airplanes, that requires an inspection to verify if the securing rivet is installed on the rod end of the control push rods of the spoiler flight control system, an inspection to verify if the jam nut is secure on the opposite end of the rod end, and repair of any discrepancy. This amendment is prompted by a report of loss of roll control on the co-pilot's control wheel shortly after takeoff due to a rivet missing from the control push rod. The actions specified by this AD are intended to ensure that the push rod rivets are installed. Missing control push rod rivets could result in the disengagement of the push rod end from the push rod tube; this could lead to loss of roll control and subsequent reduced controllability of the airplane after takeoff.
AD 95-25-10 · published Dec 22, 1995, effective Jan 22, 1996
Cessna Model 441, 500, 550, and 560 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 441, 500, 550, and 560 series airplanes, that requires replacement of outflow/safety valves with serviceable valves. This amendment is prompted by a report of cracking and subsequent failure of outflow safety valves in the pressurization system. The actions specified by this AD are intended to prevent such cracking and subsequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
AD 95-23-07 · published Dec 27, 1995, effective Dec 27, 1995
The Boeing Company Airplanes
AD 95-24-04 · published Dec 27, 1995, effective Dec 27, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 and A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracks at the aft spar web of the wings, and repair, if necessary. This amendment is prompted by reports indicating that cracks have been found in the rear spar web of the wings between ribs 1 and 2 of an in-service airplane and during testing on the fatigue test wing; the cracking occurred due to fatigue-related high shear stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the wing.
AD 95-24-07 · published Dec 27, 1995, effective Dec 27, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires modification of the aileron support frame of the wings. This amendment is prompted by reports indicating that tensile cracks have been found at a certain mounting hinge of the aileron support frame during full scale fatigue testing of the test article due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in loss of the aileron control surface and the inability of the pilot to control rolling moments of the airplane.
AD 95-24-08 · published Dec 27, 1995, effective Dec 27, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires replacement of the check valves of the thrust reverser with modified valves on certain airplanes and the replacement of the manual control valves of the thrust reverser with modified valves on certain other airplanes. This amendment is prompted by recent engineering analysis, which revealed that, if the non-return valve installed on the hydraulic return line of the thrust reverser were to jam in the closed position, it could cause pressurization of the Hydraulic Control Unit (HCU). The actions specified by this AD are intended to prevent such pressurization of the HCU due to jamming of the non-return valve in the hydraulic return line, and consequent deployment of a thrust reverser during flight; this condition, if not corrected, could adversely affect the controllability of the airplane.
AD 95-25-02 · published Dec 27, 1995, effective Dec 27, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes. This action requires inspection(s) to detect cracks of the fuselage-mounted half of hinge assemblies of the small cargo door, and replacement of any cracked hinge assembly with a new hinge assembly. This amendment is prompted by a report that the hinges of the small cargo door on these airplanes are made of a material that is sensitive to stress corrosion cracking. The actions specified in this AD are intended to prevent failure of the hinges of the small cargo door due to stress corrosion cracking, which could result in opening and/or separation of the door while the airplane is in flight, and resultant rapid decompression and/or structural damage to the airplane.
AD 95-25-03 · published Dec 27, 1995, effective Dec 27, 1995
Learjet Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 23, 24, 25, 35, and 36 airplanes. This action requires repetitive inspections to detect deterioration of both flapper valves of the tip tank in each wing of the airplane, and various follow-on actions. This AD action also requires replacing the flapper valves with new flapper valves, and repetitively performing certain other follow-on actions. This amendment is prompted by reports of imbalance of the fuel loads in the wings of the airplane due to failed or cracked flapper valves. The actions specified in this AD are intended to prevent significant reduction in the lateral control of the airplane due to imbalance of the fuel loads in the wings of the airplane.
AD 95-26-11 · published Dec 27, 1995, effective Jan 11, 1996
Lockheed Model L-1011-385 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires visual inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers. That AD also currently requires replacement of cracked fittings, and repair of adjacent structure if found to be cracked. This amendment requires new repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, and corrective actions, if necessary. This amendment is prompted by the results of the visual inspections performed in accordance with the existing AD, which indicate that the visual inspection is inadequate to detect fatigue cracking. The actions specified in this AD are intended to prevent fatigue cracking of the aft pressure bulkhead, which could lead to failure of the end fittings and splice tabs, and subsequent rapid decompression of the airplane during flight.
AD 95-26-13 · published Dec 29, 1995, effective Feb 5, 1996
The New Piper Aircraft, Inc. (Formerly Piper Aircraft Corporation) PA28 and PA32 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 76-25- 06, which currently requires replacing oil cooler hoses on The New Piper Aircraft, Inc. (Piper) Model PA28-140 airplanes, and inspecting for a minimum clearance between the oil cooler hose assemblies and the front exhaust stacks and adjusting if proper clearance is not obtained. This action maintains the clearance inspection and oil cooler hose replacements, requires this inspection and these replacements to be repetitive, and extends the applicability to include PA32 series and other PA28 series airplanes. It also provides the option of installing approved TSO-C53a, Type D oil cooler hose assemblies as terminating action for the repetitive inspection requirement. Numerous incidents/ accidents caused by oil cooler hose rupture or failure on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent these oil cooler hoses from failing or rupturing, which could result in engine stoppage and subsequent loss of control of the airplane.
AD 95-26-08 · published Dec 20, 1995, effective Jan 4, 1996
Sikorsky Aircraft Corporation Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Sikorsky Aircraft Model S-58A, S-58B, S-58C, S-58D, S-58E, S-58F, S-58G, S-58H, S-58J, S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, and S-58JT helicopters. This action requires initial and repetitive magnetic particle inspections of the main rotor shaft (shaft) for cracks, and defines power limitations for certain helicopter operations. This amendment is prompted by a recent accident in which a shaft failed, resulting in loss of power. Subsequent inspections on other aircraft of the same type revealed cracks in four additional shafts. The actions specified in this AD are intended to prevent failure of the shaft, loss of power to the rotor system, and subsequent loss of control of the helicopter.
AD 95-26-09 · published Dec 20, 1995, effective Jan 4, 1996
Sikorsky Aircraft-manufactured Model CH-34A, CH-34C, H-34A, HH-34J, HSS-1, HSS-1N, HUS-1, SH-34J, UH-34D, UH-34E, and UH-34J Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Sikorsky Aircraft-manufactured Model CH-34A, CH-34C, H- 34A, HH-34J, HSS-1, HSS-1N, HUS-1, SH-34J, UH-34D, UH-34E, and UH-34J helicopters. This action requires initial and repetitive magnetic particle inspections of the main rotor shaft (shaft) for cracks, and defines power limitations for certain helicopter operations. This amendment is prompted by a recent accident in which a shaft failed, resulting in loss of power. Subsequent inspections on other aircraft of the same type revealed cracks in four additional shafts. The actions specified in this AD are intended to prevent failure of the shaft, loss of power to the rotor system, and subsequent loss of control of the helicopter.
AD 95-26-04 · published Dec 22, 1995, effective Jan 26, 1996
Robinson Helicopter Company Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) 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) stall and mast bumping; and provide recommendations for avoiding these situations. Additionally, emergency procedures are provided for use should certain conditions be encountered. This action would require similar revisions to the Limitations, Normal Procedures and Emergency Procedures sections required by the existing AD, but the revision to the Limitations section would prohibit only pilots without a certain level of experience and training from operating in the flight conditions specified. This action is prompted by data that indicates pilots who possess a certain level of experience and training are more able to recognize and react to the adverse meteorological conditions specified in the AD. 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 95-26-05 · published Dec 22, 1995, effective Jan 26, 1996
Robinson Helicopter Company Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) 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) stall and mast bumping; and provide recommendations for avoiding these situations. Additionally, emergency procedures are provided for use should certain conditions be encountered. This action would require similar revisions to the Limitations, Normal Procedures and Emergency Procedures sections required by the existing AD, but the revision to the Limitations section would prohibit only pilots without a certain level of experience and training from operating in the flight conditions specified. This action is prompted by data that indicates pilots who possess a certain level of experience and training are more able to recognize and react to the adverse meteorological conditions specified in the AD. 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 95-26-03 · published Dec 27, 1995, effective Jan 11, 1996
Pratt & Whitney Division Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT8D series turbofan engines, that currently requires inspection, and replacement, if necessary, of suspect 7th through 12th stage high pressure compressor (HPC) disks. This amendment adds 46 more applicable engines, revises the inspection requirements, incorporates a new PW Alert Service Bulletin (ASB), and requires reporting the results of the inspection to the manufacturer. This amendment is prompted by the identification of additional suspect engines, by the development of revised inspection intervals, and by the issuance of the new PW ASB. The actions specified by this AD are intended to prevent an uncontained HPC disk failure, which can result in damage to the aircraft.
AD 95-24-05 · published Dec 1, 1995, effective Dec 18, 1995
McCauley Accessory Division, The Cessna Aircraft Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 Series Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to McCauley Accessory Division, The Cessna Aircraft Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 series propellers. This action requires initial and repetitive visual and dye penetrant inspections of the propeller hub for cracks. This action also requires a one-time eddy current inspection for cracks in the threaded areas of the propeller hub followed by modification of the hub to contain oil with red dye as a terminating action to the repetitive inspections. This amendment is prompted by reports of cracked propeller hubs. The actions specified in this AD are intended to prevent propeller blade separation due to a cracked propeller hub, which could result in separation of the engine from the aircraft and subsequent loss of aircraft control.
