48 Airworthiness Directives: 39 airplane, 5 rotorcraft, 3 engine, 1 appliance.
AD 97-09-08 · published May 1, 1997, effective Jun 23, 1997
AeroSpace Technologies of Australia Limited (Formerly Government Aircraft Factories), Nomad Models N22S, N22B, and N24A Airplanes
This amendment supersedes Airworthiness Directive AD 82-25-09 which currently requires repetitively inspecting the pilot and co-pilot control wheel sub-assemblies for cracks, and if cracked, modifying the cracked part on the AeroSpace Technologies of Australia, Limited (ASTA), formerly Government Aircraft Factories (GAF) Nomad Models N22S, N22B, and N24A airplanes. This action would retain the repetitive inspection of the pilot and co-pilot control wheel sub-assemblies for cracks, but would include a modification that would terminate the repetitive inspections by replacing or re-working the control wheel sub-assembly with a part of improved design. This superseding action is prompted by cracking in the control wheel sub-assemblies and the manufacture of an improved part that would terminate the repetitive inspection. The actions specified by this Ad are intended to prevent failure of the pilot's and co-pilot's control wheels, which, if not detected and corrected, could result in loss of control of the airplane.
AD 97-08-51 · published May 2, 1997, effective May 7, 1997
Boeing Model 767 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T97-08-51 that was sent previously to all known U.S. owners and operators of Boeing Model 767 series airplanes by individual telegrams. This AD requires an inspection to ensure that all bolts of the hinge fitting assembly support beam on both the left-and right-hand outboard trailing edge flaps are the correct length and type, and correction of any discrepancy found. This action is prompted by a report indicating that a 20-foot section of the right-hand outboard trailing edge flap separated from the airplane due to failure of four bolts of the most inboard hinge fitting. The actions specified by this AD are intended to detect and correct such failed bolts, which could result in loss of an outboard trailing edge flap, and consequent reduced controllability of the airplane.
AD 97-09-07 · published May 2, 1997, effective Jun 6, 1997
McDonnell Douglas Model MD-11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires inspections to detect damage of the support brackets and clamps of the transfer pipe of the tail tank, and of the transfer pipe assembly; and replacement of damaged parts, or installation of a doubler, if necessary. This amendment adds a requirement to install a fuel transfer pipe of the tail tank, and to install support brackets and clamps of the fuel feed pipe of engine No. 2, which constitutes terminating action for the repetitive inspections. This amendment also requires, for certain airplanes, removal of a temporary protective doubler installed on the fuel pipe assembly. This amendment is prompted by reports of cracking of the support brackets in the refuel and fuel transfer lines of the tail fuel tank and damage to the nylon clamps and transfer pipe assembly. The actions specified by this AD are intended to prevent such cracking and damage, which could result in further damage to the transfer pipe assembly and possible fuel leakage.
AD 97-09-10 · published May 2, 1997, effective Jun 6, 1997
Jetstream Model BAe ATP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP series airplanes, that requires modification of certain parts in the elevator flight control system and the propeller switch warning system. This amendment is prompted by a report indicating that these parts could interfere with the proper operation of these systems. The actions specified by this AD are intended to prevent the flight crew from having to engage the standby elevator control system in order to regulate the pitch of the airplane; and to prevent malfunctioning of the pitch warning system for the propellers; either of which could lead to reduced controllability of the airplane.
AD 97-09-11 · published May 2, 1997, effective Jun 6, 1997
Aerospatiale Model ATR42 and ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42 and ATR72 series airplanes, that requires modification of the handle of the passenger/ crew door to change the ``down-to-open'' configuration of the handle to an ``up-to-open'' configuration. This amendment is prompted by a report indicating that, immediately after takeoff, the passenger/crew door opened and separated from the airplane, due to the inadvertent operation of the door handle. The actions specified by this AD are intended to prevent inadvertent opening of the passenger/crew door during unpressurized flight, or delays in opening the door during an emergency evacuation.
AD 97-09-12 · published May 2, 1997, effective Jun 6, 1997
Raytheon Model DH 125-1A, -3A, and - 400A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Model DH 125-1A, -3A, and -400A series airplanes, that requires a one-time inspection to detect scoring of the upper fuselage skin around the periphery of the cockpit canopy blister interface, and repair, if necessary. This amendment is prompted by reports indicating that scoring of the upper fuselage skin had been detected in that area. The actions specified by this AD are intended to detect and correct scoring of the upper fuselage skin around the periphery of the cockpit canopy blister interface, which could result in reduced structural integrity of the fuselage, and consequent cabin depressurization.
AD 97-09-13 · published May 2, 1997, effective Jun 6, 1997
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time inspection to detect corrosion and cracking of the upper deck floor beam at station 980, and repair, if necessary. This amendment is prompted by reports of extensive corrosion found at station 980. Analysis of the corrosion indicated that fatigue cracking of the floor beam at this area could occur and cause the beam to break. The actions specified by this AD are intended to detect and correct such corrosion and/or cracking, which could cause the floor beam to break and result in extensive damage to adjacent structure and possible rapid decompression of the airplane.
AD 97-09-14 · published May 2, 1997, effective Jun 6, 1997
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires an inspection of reworked aileron/ elevator power control units (PCU's) and rudder PCU's to determine if reworked PCU manifold cylinder bores containing chrome plating are installed, and replacement of the cylinder bores with bores that have been reworked using the oversize method or the steel sleeve method, if necessary. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent a reduced rate of movement of the elevator, aileron, or rudder due to contamination of hydraulic fluid from chrome plating chips; such reduced rate of movement, if not corrected, could result in reduced controllability of the airplane.
AD 97-09-15 · published May 5, 1997, effective Jun 9, 1997
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires a one-time inspection to determine the part number of the engage solenoid valve of the yaw damper, and replacement of the valve with a valve having a different part number, if necessary. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent sudden uncommanded yawing of the airplane due to potential failures within the yaw damper system, and consequent injury to passengers and crewmembers.
AD 97-10-01 · published May 6, 1997, effective Jun 10, 1997
Airbus Industrie Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections to detect discrepancies or damage of the steady bearing assemblies of the flap transmission system, and replacement of any discrepant or damaged assembly with a new, like assembly. This amendment also requires eventual replacement of all the steady bearing assemblies with new, improved assemblies, which terminates the repetitive inspection requirements. This amendment is prompted by reports of cracking of the hardened steel inner race, and broken or missing inner races of the steady bearing assemblies. The actions specified by this AD are intended to prevent such discrepancies and damage of the shafts of the steady bearing assemblies, which could cause the shafts to fail; failure of the steady bearing shafts during a subsequent assymetric stop could result in an uncommanded assymetric retraction of the flap, and subsequent reduced controllability of the airplane.
AD 97-10-02 · published May 6, 1997, effective May 21, 1997
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 777 series airplanes. This action requires repetitive corrosion/resistance inspections to measure the resistance of each wire bundle of the flight control system; and repair of the receptacle bond, repair of the bundle connector backshells, or replacement of the wire bundles with new components, if necessary. This amendment is prompted by reports of corroded connectors and numerous other discrepancies of the wire bundles, such as loose backshells and loose shield retention bands, due to the presence of moisture inside the wire bundles. The actions specified in this AD are intended to detect and correct such corrosion, which could reduce system protection against lightning strikes or high intensity radiated field (HIRF) events, and consequently could adversely affect wire bundles used for the flight control system. This situation could result in loss of function of certain flight control surface actuators in the event of a lightning strike.
AD 97-10-03 · published May 6, 1997, effective Jun 10, 1997
British Aerospace Model BAC 1-11 200 and 400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires repetitive ultrasonic inspections to detect cracking of the lugs of the engine mounting beams, and replacement of the beam with a serviceable part, if necessary. This amendment is prompted by reports of fatigue cracking of the lugs of the engine mounting beams. The actions specified by this AD are intended to detect and correct such cracking of the engine mounting lugs, which could result in reduced structural capability of the engine mount.
AD 97-07-10 R1 · published May 7, 1997, effective May 23, 1997
de Havilland DHC-6 Series Airplanes
This document clarifies information in an existing airworthiness directive (AD) that applies to de Havilland DHC-6 series airplanes that do not have a certain wing strut modification (Modification 6/1581) incorporated. That AD currently requires inspecting the wing struts for cracks or damage (chafing, etc.), replacing wing struts that are found damaged beyond certain limits or are found cracked, and incorporating Modification No. 6/1581 to prevent future chafing damage. The actions specified in that AD are intended to prevent failure of the wing struts, which could result in loss of control of the airplane. This document clarifies the requirements of the current AD by eliminating all reference to repetitive inspections. The AD results from several reports of wing strut damage caused by the upper fairing rubbing against the wing strut.
AD 97-09-09 · published May 7, 1997, effective Jun 30, 1997
Raytheon Aircraft Company (Formerly Beech Aircraft Corporation) Models 58P and 58PA Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (formerly Beech Aircraft Corporation) Models 58P and 58PA airplanes. This action requires inspecting for cracks in the right-hand (RH) upper and lower longeron near the second RH cabin window, inspecting for missing rivets in the cabin structure (longeron) adjacent to and aft of the second RH cabin window, repairing any cracked structure or reinforcing the longeron if it is not cracked, and installing rivets, if missing. Reports of cracks in the upper and lower longeron and missing rivets that are supposed to secure the frame, splice, and longeron together prompted this action. The actions specified by this AD are intended to prevent structural cracking to the cabin caused by missing rivets, which if not corrected, could cause decompression injuries to passengers, structural failure of the fuselage, and loss of the airplane.
AD 97-07-08 · published May 9, 1997, effective May 9, 1997
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires the replacement of weight limitation placards in the aft main baggage bay and in the aft right stowage compartment with new placards indicating lower maximum weight limits. It also requires a revision of the Airplane Flight Manual to delete references to the current higher weight limits for these areas. This amendment is prompted by a report indicating that existing weight limitations could result in failure of the front bulkhead of the aft main baggage bay and doors of the aft right stowage compartment during emergency dynamic landing conditions. The actions specified by this AD are intended to prevent such failure, which consequently could result in injury to passengers and flight crew, and hinder evacuation of the airplane through the exit adjacent to this bulkhead.
AD 97-07-09 · published May 9, 1997, effective May 9, 1997
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires repetitive checks and testing of certain equipment that regulates the flow of fuel from wing tank 2A to the number 2 engine. This amendment also requires replacement of this equipment with equipment that has been designed to prevent incorrect installation; this replacement is considered to be terminating action for the repetitive equipment checks and tests. This amendment is prompted by reports indicating that the incorrect installation of this equipment has caused the flight crew to shut off, rather than open, certain valves that regulate the flow of fuel from between this tank and engine. The actions specified by this AD are intended to detect and rectify incorrect installations, which could result in the flight crew inadvertently shutting off the flow of fuel to the engine, and consequent engine failure during flight.
AD 97-10-06 · published May 12, 1997, effective Jun 16, 1997
Israel Aircraft Industries (IAI), Ltd. Model 1125 Westwind Astra Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain IAI Model 1125 Westwind Astra series airplanes, that requires repetitive inspections to detect loose or damaged rivets that fasten a certain support beam to the frame of the fuselage; and modification of the attachment between the support beam and fuselage by installation of additional fasteners, if necessary. This amendment also will require the eventual accomplishment of this modification on all airplanes, which will terminate the repetitive inspections. This amendment is prompted by reports indicating that the attachment between this beam and the fuselage has become loose on several airplanes. Movement of this beam could restrict the movement of the elevator and rudder controls that run through the bellcranks attached to it. The actions specified by this AD are intended to prevent movement of this beam, which could restrict movement of the elevator and rudder controls, and consequently lead to reduced controllability of the airplane.
AD 97-10-07 · published May 12, 1997, effective Jun 16, 1997
Construcciones Aeronauticas, S.A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires disabling the brake control valve of the propeller. This amendment also requires that, prior to restoring propeller brake operation, the propeller brake control unit be replaced with a certain new propeller brake control unit. This amendment is prompted by reports of uncommanded activation of the propeller brake system on in-service airplanes during flight, due to the existing design of the brake control valve. The actions specified by this AD are intended to prevent in-flight uncommanded activation of the propeller brake system, which could result in in-flight shutdown of the engine.
AD 97-10-08 · published May 12, 1997, effective Jun 16, 1997
Construcciones Aeronauticas, S.A. (CASA) Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires replacement of the guide hooks of the cargo doors with new, improved guide hooks. This amendment is prompted by fatigue cracking found in the guide hooks of the cargo door. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the cargo door and, consequently, lead to rapid decompression of the airplane.
AD 97-10-09 · published May 12, 1997, effective Jun 16, 1997
Jetstream Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires repetitive detailed visual inspections to detect cracks on frame 179 at the attachment bracket for the door restraint cable, and various follow-on actions. This amendment also requires installation of new doublers and stress pads on frame 179, which would terminate the repetitive inspections. This amendment is prompted by reports of cracks in frame 179 of the fuselage at the attachment bracket for the door restraint cable on in-service airplanes due to improper rigging of the door restraint system. The actions specified by this AD are intended to prevent such cracking, which could result in structural failure of the fuselage and consequent rapid decompression of the pressurized section of the fuselage.
AD 97-10-11 · published May 12, 1997, effective May 27, 1997
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 777 series airplanes. This action requires repetitive testing of the engine fire shutoff switch (EFSS) to determine that the override mechanism and the switch handle are operational, and replacement of the EFSS, if necessary. This action also requires, for certain airplanes, installation of a collar on a specific circuit breaker of the standby power management panel, and installation of placards to advise the flightcrew that the override mechanism must be pushed in order to pull the fire switch. This amendment is prompted by a report indicating that a solenoid and an override mechanism of the EFSS were not operational due to overheating of the solenoid. The actions specified in this AD are intended to prevent damage to the EFSS solenoid and to the override mechanism, and consequent failure of the EFSS due to overheating of the solenoid; such failure of the EFSS could result in the inability of the flightcrew to discharge the fire extinguishing agent in the event of an engine fire.
AD 97-10-12 · published May 12, 1997, effective Jun 16, 1997
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time inspection to detect riding, chafing, or damage of the wire bundles adjacent to the disconnect panel bracket of the observer's station. This amendment also requires repair or replacement of damaged wires with new or serviceable wires; installation of anti-chafing sleeving on the wire bundles, if necessary; and installation of grommet along the entire upper aft edge of the disconnect panel bracket. This amendment is prompted by a report indicating that the circuit breakers tripped on a Model MD-11 series airplane due to inflight arcing behind the avionics circuit breaker panel as a result of chafing of the wire bundles adjacent to the disconnect panel bracket assembly. The actions specified by this AD are intended to detect and correct such chafing, which could result in a fire in the wire bundles and smoke in the cockpit.
AD 97-10-10 · published May 13, 1997, effective Jul 3, 1997
Aerospace Technologies of Australia, Nomad N22 and N24 Series Airplanes
This amendment supersedes AirworthinessDirective AD 85-21-06 which applies to all AerospaceTechnologies of Australia (ASTA) Nomad N22 and N24 series airplanes and currently requires replacing the attachment fittings of the upper fin rear spar and the fin/horizontal stabilizer. This action requires removing the upper fin to stub fin forward attachment bolts, inspecting the attachment fittings for cracks, and, if no cracks are found, replacing the attachment bolts with bolts of improved design until the life limit of the attachment fittings is reached, at which time the attachment fittings would be replaced with improved attachment fittings. If cracks are found, this AD requires replacing the attachment bolts and attachment fittings. Cracks found in the underhead radius and at the base of the thread of the bolt prompted this action. The actions specified by thisAD are intended to prevent cracking in the upper fin and horizontal stabilizer attachment fittings, which if not corrected, could result in loss of control of the airplane.
AD 97-10-13 · published May 13, 1997, effective Jul 8, 1997
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 96-21- 05, which currently requires the following on certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes that do not have a certain elevator torque tube installed: drilling inspection access holes in the elevator torque tube arm, inspecting the elevator torque tube for corrosion, replacing any corroded elevator torque tube, and applying a corrosion preventive compound. AD 96-21-05 resulted from several reports of corrosion found in the elevator torque tube area on the affected airplanes. This AD retains the actions required by AD 96- 21-05, and adds certain Fairchild Model SA227-BC airplanes to the Applicability section of that AD. The actions specified by this AD are intended to prevent failure of the flight control system caused by a corroded elevator torque tube, which could result in loss of control of the airplane.
AD 96-26-52 R1 · published May 14, 1997, effective Jun 18, 1997
Boeing Model 747 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections of the access doors to the midspar/spring beam fuse pins on all engine pylons to detect cracks on the external surface; repetitive inspections of each midspar/spring beam fuse pin to detect if it protrudes beyond its mating nut by a specified distance; and repair of any discrepancy found. The actions specified by that AD are intended to prevent migration of this fuse pin, which, if not detected and corrected in a timely manner, could result in failure of the engine pylon and consequent separation of the engine from the wing. This amendment increases the intervals between inspections of the access doors and each midspar/spring beam fuse pin, and consequently decreases the frequency of inspections. This amendment is prompted by new data provided by the manufacturer indicating that the reported migration of the fuse pin was apparently the result of an incorrectly installed nut.
AD 97-10-14 · published May 15, 1997, effective Jul 7, 1997
Raytheon Aircraft Company Model 1900D Airplanes (formerly Beech Aircraft Corporation)
This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly referred to as Beech Aircraft Corporation Model 1900D). This action requires inspecting the stabilon attachment angles for the correct thickness, repetitively inspecting for cracks, and replacing the attachment angles that are the incorrect thickness with ones of the correct thickness. Recent reports of the affected airplanes having the incorrect size stabilon attachment angles prompted this action. The actions specified by this AD are intended to prevent separation of the stabilon from the airplane, which could cause loss of airplane stability during flight.
AD 97-06-11 · published May 16, 1997, effective May 16, 1997
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 35 series airplanes (formerly referred to as Beech 35 series airplanes). This action requires inspecting the ruddervator differential tail control rod assembly for corrosion or cracks, repairing or replacing any cracked or corroded part, and applying anti-corrosion sealant to the ruddervator control pushrods. This action results from a report of a split in the ruddervator control push rod on an affected airplane that was found during a routine inspection. The split occurred when water froze in the internal area of the control push rod and then expanded. The actions specified by this AD are intended to prevent failure of the differential tail control rod assembly, which could result in loss of control of the airplane.
AD 97-11-07 · published May 22, 1997
McDonnell Douglas Model MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-90-30 airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness [MD-90-30 Airworthiness Limitations Instructions (ALI)]. The revision will incorporate certain compliance times for inspections to detect fatigue cracking of principal structural elements (PSE) and to add PSE's to the ALI. This amendment is prompted by analysis of data that identified reduced initial inspection thresholds, reduced repetitive inspection intervals for PSE's, and other PSE's to be added to the ALI. The actions specified by this AD are intended to ensure that fatigue cracking of various PSE's are detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 97-11-08 · published May 22, 1997, effective Jun 6, 1997
Bombardier Model CL-415 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-415 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified in this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 97-07-11 · published May 23, 1997, effective May 23, 1997
British Aerospace Regional Aircraft Airplanes
This amendment supersedes Airworthiness Directive (AD) 81-20-01, which currently requires repetitively inspecting the nose landing gear (NLG) actuator support structure and the front pressure bulkhead for cracks on Jetstream Aircraft Limited (JAL) HP137 Mk1 and Jetstream series 200 airplanes, and replacing any cracked part. This AD retains the repetitive inspections required by AD 81-20-01; requires repetitively inspecting the NLG retraction jack upper mounting fitting and attachment hardware for security bolt failure and for bolts with improper torque levels on the HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes, and requires replacing any failed security bolts and adjusting any bolt with an improper torque level; and requires modifying the NLG retraction jack on all affected airplanes, as terminating action for the repetitive inspections. This AD results from reports of NLG jack mounting fitting failures on several of the affected airplanes, and the Federal Aviation Administration's policy on aging commuter-class aircraft. The actions specified by this AD are intended to prevent failure of the NLG caused by a cracked NLG actuator support structure or cracked front pressure bulkhead, which, if not detected and corrected, could lead to nose gear collapse and damage to the airplane.
AD 97-10-05 · published May 23, 1997, effective Jul 11, 1997
Jetstream Aircraft Limited HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires repetitively inspecting the main landing gear (MLG) pintle to cylinder interface area for cracks, and replacing any MLG cylinder where a crack of any length is found in the MLG pintle to cylinder interface area. This AD results from reports of MLG cracks in the area of the pintle to cylinder interface on three of the affected airplanes. The actions specified by this AD are intended to prevent failure of the MLG caused by cracks in the pintle to cylinder interface area, which could result in loss of control of the airplane during landing operations.
AD 97-11-01 · published May 23, 1997, effective Jun 27, 1997
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires an initial inspection of fastener holes on certain outer frames of the fuselage to detect fatigue cracking, and modification of this area by cold expanding these holes and installing oversized fasteners. This amendment is prompted by a report from the manufacturer indicating that, during full-scale fatigue testing of the test article, fatigue cracking was detected in the area where the center fuselage joins the wing. The actions specified by this AD are intended to prevent fatigue cracking and consequent reduced structural integrity of this area, which could lead to rapid depressurization of the fuselage.
AD 97-11-03 · published May 23, 1997, effective Jun 27, 1997
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 series airplanes, that requires inspections of the lower door surrounding structure to detect cracks and corrosion, and repair, if necessary. This amendment also requires inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, this amendment will also require modification of the passenger/crew door frames, which, when accomplished, terminates certain inspections. This amendment is prompted by reports indicating that corrosion was found behind the scuff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. The actions specified by this AD are intended to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings.
AD 97-11-02 · published May 28, 1997, effective Jul 2, 1997
Jetstream Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires an inspection to determine the thickness of the intercostal that attaches the third crew member seat to the floor structure in the flight compartment, and replacement, if necessary. This amendment is prompted by a report from the manufacturer indicating that intercostals have been installed that are not of sufficient thickness (and consequent strength) to support the third crew member seat during emergency landing dynamic conditions. The actions specified by this AD are intended to prevent the failure of this intercostal during an emergency landing, which could consequently result in injury to the flight crew.
AD 97-11-09 · published May 28, 1997, effective Jun 12, 1997
Bombardier Model CL-215T Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-215T series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits the positioning of the power levers below the flight idle stop during flight, and to add a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified in this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
AD 97-09-04 · published May 29, 1997, effective May 29, 1997
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A320, A321, A330, and A340 series airplanes, that requires repetitive testing of certain fire shutoff valves (FSOV) on the left and right engines, repetitive checks of certain parts on the FSOV motors, and replacement of discrepant valves with modified valves. This amendment also requires modification of FSOV seals and motors as terminating action for the repetitive testing and check requirements. This amendment is prompted by reports indicating that FSOV s are not closing completely during maintenance testing. The actions specified by this AD are intended to prevent the flow of hydraulic fluid to the engine in the event of fire which, if not corrected, would fuel the fire, and lead to the loss of fluid in associated hydraulic systems, causing those systems to fail.
AD 97-11-11 · published May 29, 1997, effective Jul 11, 1997
Aerospace Technologies of Australia Pty Ltd. (Formerly Government Aircraft Factory) Models N22B, N22S, and N24A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N22S, and N24A airplanes. This action requires repetitively inspecting the horizontal stabilizer upper and lower skin, intercostal angles, and the horizontal stabilizer trailing edge channel for cracks; and repairing any crack or replacing any cracked parts, as applicable. This AD results from numerous reports of cracking in these horizontal stabilizer areas on the affected airplanes. The actions specified by this AD are intended to prevent structural failure of the horizontal stabilizer caused by fatigue cracks, which could result in loss of control of the airplane.
AD 97-11-12 · published May 29, 1997, effective Jul 11, 1997
Aerospace Technologies of Australia Pty Ltd. (Formerly Government Aircraft Factory) Models N22B, N22S, and N24A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N22S, and N24A airplanes. This action requires repetitively inspecting the stub wing upper front spar cap flanges for cracks, and repairing any cracked part. This AD results from fatigue tests that show that the stub wing upper front spar cap flanges could fail over time because of fatigue. The actions specified by this AD are intended to prevent structural failure of the front spar caused by cracks in the stub wing upper front spar cap flanges, which could result in loss of control of the airplane.
AD 97-11-13 · published May 29, 1997, effective Jul 11, 1997
Fairchild Aircraft SA226 and SA227 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 and SA227 series airplanes. This AD requires modifying the electrical power generation system. The AD results from reports of both generators going off-line during flight on three of the affected airplanes. The actions specified by this AD are intended to prevent failure of both generators during critical phases of flight (such as night operation or while in icing conditions), which could result in loss of control of the airplane.
AD 97-10-04 · published 1997
Sikorsky Aircraft Corporation Helicopters
AD 97-07-06 · published May 9, 1997, effective May 9, 1997
Bell Helicopter Textron, Inc. Helicopters
This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. Model 412 helicopters, that currently requires a daily inspection of certain swashplate support assemblies. It also requires a reduction in VNE, and installation of appropriate airspeed indicator markings and a placard. This amendment requires the same actions required by the existing priority letter AD, but restricts the applicability to the Model 412 helicopters with a certain steel main rotor control swashplate support assembly (steel swashplate support assembly) installed. This amendment also allows the installation of an improved main rotor control swashplate assembly that terminates the requirements of this AD. This amendment is prompted by reported cracking and in-service failures of certain steel swashplate support assemblies. The actions specified by this AD are intended to prevent failure of the steel swashplate support assembly that could result in loss of main rotor control and subsequent loss of control of the helicopter.
AD 97-11-04 · published May 20, 1997
Bell Helicopter Textron, Inc. Model 412 and 412EP Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 412 and 412EP helicopters, that requires creation of a component history card or equivalent record using a Retirement Index Number (RIN) system; establishes a system for tracking increases to the accumulated RIN; and establishes a maximum accumulated RIN for certain main rotor masts (masts) and main rotor spline plates (spline plates). This amendment is prompted by fatigue analyses and tests that show certain masts and spline plates fail earlier than originally anticipated because of an unanticipated high number of takeoffs and external load lifts utilizing high power settings, in addition to the time-in-service (TIS) accrued under normal operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the mast or spline plate, which could result in failure of the main rotor system and subsequent loss of control of the helicopter.
AD 97-10-15 · published May 23, 1997, effective Jun 27, 1997
Sikorsky Aircraft-Manufactured Model S- 64F Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft-manufactured Model S-64F helicopters, that requires inspections, and replacement, if necessary, of the main gearbox second stage lower planetary plate (plate). This amendment is prompted by two incidents in which the plate was found cracked. The actions specified by this AD are intended to prevent failure of the plate due to fatigue cracking, which could lead to failure of the main gearbox and subsequent loss of control of the helicopter.
AD 97-10-16 · published May 23, 1997, effective Jun 27, 1997
Hiller Aircraft Corporation Model UH- 12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, CH-112, H-23A, H-23B, H- 23C, H-23D, H-23F, HTE-1, HTE-2, and OH-23G Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Hiller Aircraft Corporation Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, CH-112, H-23A, H-23B, H-23C, H-23D, H- 23F, HTE-1, HTE-2, and OH-23G helicopters, and UH-12D and UH-12E helicopters converted to turbine engine power in accordance with Supplemental Type Certificate (STC) Nos. SH177WE and SH178WE, having a certain control rotor blade spar tube (blade spar tube) or cuff installed, that currently requires inspections of the blade spar tube and cuff for cracks, and repair or replacement as necessary. This amendment requires inspections of the blade spar tube and cuff for corrosion or cracks, or elongation, corrosion, burrs, pitting or fretting of the bolt holes, and repair as necessary, and defines specific intervals in which the inspections must be performed. This amendment is prompted by analyses that show that the amount of calendar time that elapses between the current repetitive inspections may allow corrosion to develop. The actions specified by this AD are intended to prevent separation of the control rotor blade assembly and subsequent loss of control of the helicopter.
AD 97-09-02 · published May 1, 1997, effective Jun 30, 1997
CFM International CFM56-5C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-5C series turbofan engines, that requires a reduction of the low cycle fatigue (LCF) retirement lives for certain high pressure turbine rotor (HPTR) front shafts, HPTR front air seals, HPTR disks, booster spools, and low pressure turbine rotor (LPTR) stage 3 disks. This amendment is prompted by results of a refined life analysis performed by the manufacturer which revealed minimum calculated LCF lives lower than published LCF retirement lives. The actions specified by this AD are intended to prevent an LCF failure of the HPTR front shaft, HPTR front air seal, HPTR disk, booster spool, and LPTR stage 3 disk, which could result in an uncontained engine failure and damage to the aircraft.
AD 97-11-06 · published May 27, 1997, effective Jun 11, 1997
Pratt & Whitney PW4164 and PW4168 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney PW4164 and PW4168 series turbofan engines. This action requires initial and repetitive visual inspections of the fan blades for surface damage and cracks, initial and repetitive lubrication of the fan blade part span shrouds, a one time ultrasonic inspection (UI) of the fan blade root attachment area for cracks, and a one time fan blade root attachment front corner radii inspection for proper dimension. Also, this AD requires visual inspection of the fan blades and removal of fan blades damaged by a bird strike as well as removal of blades immediately adjacent to damaged blades. In addition, this AD requires installation of an improved fan blade assembly as terminating action to the inspection requirements of this AD. This amendment is prompted by a report of a high N1 rotor imbalance and liberation of the fan containment system causing loss of structural support of the engine inlet cowl, following loss of a fan blade during a test. The actions specified in this AD are intended to prevent fan blade failure and separation at the root section, which could result in high N1 rotor imbalance, and liberation of the fan containment system, which can hazard the aircraft.
AD 97-11-05 · published May 29, 1997, effective Jul 28, 1997
AlliedSignal Inc. ALF502 and LF507 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming) ALF502 and LF507 series turbofan engines, that requires initial and repetitive on- wing eddy current or in-shop fluorescent penetrant inspections of fuel manifold assemblies for cracks, and replacement, if necessary, with serviceable parts. In addition, this AD presents an optional terminating action to the repetitive inspections by replacing the fuel manifold assembly with an assembly of a new, improved design. This amendment is prompted by reports of cracking of the fuel manifold assembly at the No. 5 scallop location. The actions specified by this AD are intended to prevent cracking of the fuel manifold assembly, which could result in an engine fire.
AD 97-11-10 · published May 29, 1997, effective Jun 23, 1997
Puritan Bennett Aero Systems Company Series 174290 Constant Flow Airline Portable Oxygen Masks, Part Numbers 174290-14, 174290-24, 174290-34, 174290-44, and 174290-54
This amendment adopts a new airworthiness directive (AD) that applies to Puritan Bennett Aero Systems Company (Puritan Bennett) Series 174290 Constant Flow Airline Portable Oxygen Masks, Part Numbers 174290-14, 174290-24, 174290-34, 174290-44, and 174290-54, that are utilized on aircraft. This action requires replacing any Series 174290 Constant Flow Airline Portable Oxygen Masks, Part Numbers 174290-14, 174290-24, 174290-34, 174290-44, and 174290-54, that have a manufacturing date between September 1992 to August 1996 with an FAA- approved mask that incorporates a part number not covered by this AD. These masks have a connector with an orifice that could restrict more than half of the oxygen flow to the passenger. This oxygen mask is mainly used for emergency medical action or emergency decompression procedures during flight. The actions specified by this AD are intended to prevent restricted oxygen flow, which, if not corrected, could cause serious injury to a passenger in need of emergency or first aid oxygen during flight.
