20 Airworthiness Directives: 11 airplane, 5 engine, 1 propeller, 2 appliance, 1 glider.
AD 97-07-13 · published Apr 7, 1997, effective May 12, 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 center wing attachment rods with new rods. This amendment is prompted by a report from the manufacturer indicating that these rods failed during a full-scale fatigue test. The actions specified by this AD are intended to prevent fatigue failure of these rods, which consequently could reduce the structural integrity of the wing-to-fuselage attachment.
AD 97-07-14 · published Apr 7, 1997, effective May 12, 1997
Airbus Model A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings. This amendment is prompted by a report from the manufacturer indicating that full-scale fatigue testing on the test model revealed fatigue cracking in this area. The actions specified by this AD are intended to prevent fatigue cracking in this area, which can reduce the structural integrity of fuselage frame 36 and the wing center section.
AD 97-07-12 · published Apr 8, 1997, effective May 13, 1997
McDonnell Douglas Model MD-11 and DC-10 Series Airplanes, and KC-10A (Military) Airplanes
This amendment supersedes an existing airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 and DC-10 series airplanes, and KC-10A (military) airplanes. That AD currently requires functional testing to verify proper installation of the electrical connectors to the engine generator and fire bell shutoff switches, and correction of the installation, if necessary. This amendment requires installation of a modification that terminates the requirement to perform repetitive functional tests. This amendment is prompted by the development of a modification that minimizes the possibility of improperly connecting (crossing) the electrical connectors to the fire extinguishing handles. The actions specified by this amendment are intended to prevent the wrong engine-driven generator from being shut down unnecessarily in the event of an engine fire warning.
AD 97-08-03 · published Apr 10, 1997, effective May 15, 1997
Airbus Model A310 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a functional flow test and leak test to verify if the pressure reducing valve in the cargo fire extinguishing system is in a serviceable condition, and replacement of any faulty valve with a new valve prior to extended range twin-engine operations of the airplane. This amendment is prompted by a report that, during a scheduled maintenance check, an inoperative pressure reducing valve was found in the cargo fire extinguishing system. The actions specified by this AD are intended to ensure that a faulty pressure reducing valve is not installed, which could result in reduced fire protection of the cargo compartment of the airplane.
AD 97-08-04 · published Apr 10, 1997, effective May 15, 1997
Airbus Model A320-111, -211, -212, and -231 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that requires reinforcement of the tail section of the fuselage at frames 68 and 69. This amendment is prompted by reports indicating that the tail section has struck the runway during takeoffs and landings. The actions specified by this AD are intended to prevent structural damage to the tail section when it strikes the runway; that condition, if not detected, could result in depressurization of the fuselage during flight.
AD 97-08-05 · published Apr 10, 1997, effective May 15, 1997
Boeing Model 747-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires replacement of certain switches in the cabin attendant's panel at door 4 right and door 2 right with new improved switches. This amendment is prompted by reports indicating that fires have occurred on some airplanes due to the internal failure of some of these switches. The actions specified by this AD are intended to prevent the installation and use of switches that could short circuit when they fail, and consequently cause fire and smoke aboard the airplane.
AD 97-08-07 · published Apr 22, 1997, effective May 7, 1997
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to determine the type of fluorescent light ballasts installed in the cabin sidewall; and installation of a protective cover on the ballast, replacement, or removal/disconnection of the ballast, if necessary. That action also requires, for some airplanes, removal of the dust barriers from the outboard ceiling panels, and installation of modified outboard ceiling panels. This amendment would add a requirement to replace certain ballasts on which a protective cover is installed with other ballasts, or removal/disconnection of the ballast. This amendment is prompted by additional reports of heavy smoke and fumes emitting from the ceiling panels in the forward passenger cabin due to the failure of the fluorescent light ballasts. The actions specified in this AD are intended to prevent a fire in the passenger compartment, which could result from failure of the fluorescent light ballast of the upper and lower cabin sidewall, and consequent failure of the dust barriers of the outboard ceiling panel.
AD 97-08-08 · published Apr 22, 1997, effective May 7, 1997
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive visual inspections of the forward mounts of certain engines to detect damaged, missing, or failed parts, and eventual modification of those engines. Accomplishment of this modification terminates the requirement for repetitive inspections. This amendment is prompted by a report indicating that bolts that attach the yoke of the forward mount to the fan case of the engine have failed due to fatigue cracking. The actions specified in this AD are intended to prevent fatigue cracking in these bolts, which could lead to failure of these bolts and consequent separation of the engine from the wing.
AD 97-09-03 · published Apr 24, 1997, effective May 29, 1997
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires modification of the wiring for certain hydraulic fire shutoff valves to the right engine to prevent chafing. This amendment is prompted by reports indicating that a circuit breaker to wiring in the right engine had tripped on two airplanes, the cause of which has been attributed to chafing of the associated wire bundle. The actions specified by this AD are intended to prevent this wiring from chafing which, if not corrected, could lead to short circuiting of this wiring and the consequent inability to close the hydraulic fire shutoff valves to the right engine in the event of fire.
AD 97-09-05 · published Apr 25, 1997, effective May 30, 1997
Raytheon Model BAe 125-1000A and Model Hawker 1000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Model BAe 125-1000A and Model Hawker 1000 series airplanes, that requires various modifications to increase the size of certain existing pressure venting areas and to add additional venting areas. This amendment is prompted by results of a design review of the requirements for certification of the cabin pressurization system. The actions specified by this AD are intended to prevent inadequate venting of cabin pressure in the event of rapid decompression, which could cause failure or deformation of certain structural members, and consequent reduced controllability of the airplane.
AD 97-09-06 · published Apr 25, 1997, effective May 15, 1997
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 757 series airplanes. This action requires repetitive inspections to detect damage of the tubes of the fire extinguishing and smoke detection systems, and duct support brackets of the auxiliary power unit (APU); and corrective actions, if necessary. This amendment is prompted by reports of incidents in which the tubes of the fire extinguishing and smoke detection systems chafed against the stiffener rings and support brackets of the pneumatic duct of the APU. The actions specified in this AD are intended to detect and correct such chafing, which could result in a hole in the tube of the fire extinguishing system and consequently, could prevent the proper distribution of the fire extinguishing agent within the aft cargo compartment in the event of a fire. Such chafing also could result in a hole in the smoke detection system, which could result in the delay of detection of a fire in the aft cargo compartment.
AD 97-07-04 · published Apr 7, 1997, effective Jun 6, 1997
Rolls-Royce plc RB.211-524 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Rolls-Royce plc RB.211-524 series turbofan engines, that requires initial and repetitive borescope inspections of the head section and meterpanel assembly of the combustion liner, and replacement, if necessary, with serviceable parts. In addition, this AD allows an optional installation of a front combustion liner with a strengthened head section as a terminating action to the inspection requirements. This amendment is prompted by reports of engine fires due to premature engine combustor distress. The actions specified by this AD are intended to prevent engine combustor liner deterioration due to thermal fatigue, which can result in combustor liner and case burn- through and engine fire.
AD 97-08-01 · published Apr 22, 1997, effective Jun 23, 1997
CFM International CFM56-3, -3B, and -3C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-3, -3B, -3C series turbofan engines, that requires a reduction of the low cycle fatigue (LCF) retirement lives for certain fan disks. This amendment is prompted by the results of a refined life analysis performed by the manufacturer which revealed minimum calculated LCF lives significantly lower than published LCF retirement lives. The actions specified by this AD are intended to prevent a LCF failure of the fan disk, which could result in an uncontained engine failure and damage to the aircraft.
AD 97-07-05 · published Apr 25, 1997, effective Jun 24, 1997
AlliedSignal Inc. T5311, T5313, T5317, and T53 (Military) Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming) T5311, T5313, T5317, and T53 series military engines approved for installation on aircraft certified in accordance with Section 21.25 of the Federal Aviation Regulations (FAR), that requires removal and replacement of the N2 spur gear nut retainer (lock cup). This amendment is prompted by reports of N2 spur gear nut retainer (lock cup) separation. The actions specified by this AD are intended to prevent N2 accessory drive assembly disengagement due to N2 spur gear nut retainer (lock cup) separation, which could result in an uncommanded engine acceleration.
AD 97-09-01 · published Apr 25, 1997, effective May 12, 1997
Pratt & Whitney PW2000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney PW2000 series turbofan engines. This action requires initial and repetitive inspections for cracks in the forward face of the first stage high pressure turbine (HPT) disks at the base of the fir tree lug at the outer diameter (OD) snap fillet radius where the side plates mate with the disk, and rework to the first stage HPT disk. Additionally, this AD establishes a new, reduced cyclic life limit for certain disks. This amendment is prompted by reports of two uncontained disk failures resulting from a fir tree lug fracturing, subsequently releasing two blades and a fir tree lug, which penetrated the engine HPT turbine case. The actions specified in this AD are intended to prevent fracture of the first stage HPT disk, resulting in a possible uncontained engine failure and damage to the aircraft.
AD 97-06-13 · published Apr 30, 1997, effective May 15, 1997
Rolls-Royce plc RB.211 Trent 800 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB.211 Trent 800 series turbofan engines. This action requires initial and repetitive visual and fluorescent penetrant inspections (FPI) of the angled drive upper shroud tube for frettage and cracking, initial and repetitive visual inspections and FPI for cracking, a one-tine FPI for porosity of the intermediate gearbox housing (IGH), and initial and repetitive visual inspections for cracking of the external gearbox lower bevel box (LBB) housing. In addition, this action requires initial and repetitive master magnetic chip detector inspections. Finally, prior to initiation of Extended Range Twin-Engine Operations (ETOPS), or prior to September 30, 1997, whichever occurs first, this action requires installation of a redesigned angled drive upper shroud tube and a lower splitter fairing with revised sealing. This amendment is prompted by reports of loss of oil from the angle drive upper shroud tube, the IGH, the LBB, and by reports of bearing failures. The actions specified by this AD are intended to prevent loss of oil, which could cause an engine fire. This AD is also intended to prevent inflight engine shutdowns and airplane diversions caused by oil loss and from bearing failures.
AD 97-06-16 · published Apr 4, 1997, effective Apr 24, 1997
McCauley Propeller Systems 1A103/TCM Series Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to McCauley Propeller Systems 1A103/TCM series propellers. This action supersedes priority letter AD 95-21-01 that currently requires visual inspections for cracks in the propeller hub of certain propellers using a 10X power magnifying-glass. This action requires an initial inspection for cracks in the propeller hub in accordance with a dye penetrant inspection procedure, replacement of propellers with cracks that do not meet acceptable limits, rework of propellers with cracks that meet acceptable limits, and repetitive inspections of all affected propellers. This amendment is prompted by development of a dye penetrant inspection and rework procedures. The actions specified by this AD are intended to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the aircraft.
AD 97-01-04 · published Apr 7, 1997, effective Apr 22, 1997
Textron Lycoming and Superior Air Parts, Inc.
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-01-04 that was sent previously to all known U.S. owners and operators of certain Textron Lycoming TIO- 540, LTIO-540, and IO-540 series reciprocating engines with certain Superior Air Parts, Inc. Parts Manufacture Approval (PMA) replacement cylinder assemblies installed by individual letters. This AD requires removal from service of affected cylinder assemblies for higher time cylinder assemblies and replacement with serviceable parts, and initial and repetitive dye penetrant inspections for mid-time cylinder assemblies, or replacement with serviceable parts. This amendment is prompted by a report of an inflight engine failure of a Textron Lycoming TIO-540 reciprocating engine with affected Superior Air Parts, Inc. PMA cylinder assemblies installed. The actions specified by this AD are intended to prevent cylinder head separation, inflight loss of power, possible engine failure, and fire.
AD 97-08-06 · published Apr 10, 1997, effective Jun 2, 1997
Louis L'Hotellier, S.A., Ball and Swivel Joint Quick Connectors
This amendment adopts a new airworthiness directive (AD) that applies to Louis L'Hotellier S.A. (L'Hotellier) ball and swivel joint quick connectors installed on gliders and sailplanes that are not equipped with a ``Uerling'' sleeve or an LS-safety sleeve. These connectors allow the operator of the gliders and sailplanes to quickly connect and disconnect the control systems during assembly and disassembly for storage purposes. This action requires enlarging the safety pin guide hole diameter, and fabricating and installing a placard that specifies a check of the security of the connectors prior to each flight. Several in-flight accidents involving inadvertent disconnection of these connectors that are installed on certain gliders and sailplanes prompted this action. The actions specified by this AD are intended to prevent the connectors from becoming inadvertently disconnected, which could result in loss of control of the sailplane or glider.
AD 97-08-02 · published Apr 8, 1997, effective May 30, 1997
Schempp-Hirth K.G. Models Standard- Cirrus, Nimbus-2, Nimbus-2B, Mini-Nimbus HS-7, Mini-Nimbus B, Discus a, and Discus b Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schempp-Hirth) Models Standard- Cirrus, Nimbus-2, Nimbus-2B, Mini-Nimbus HS-7, Mini-Nimbus B, Discus a, and Discus b sailplanes. This AD requires accomplishing a load test of the elevator control system, and replacing the elevator vertical actuating tube either immediately or at a certain time period depending on the results of the load test. This AD results from reported incidents of corrosion found in the elevator because of water entering the elevator control rod. The actions specified by this AD are intended to prevent corrosion in the elevator caused by water entering the elevator control rod, which could result in elevator failure and subsequent loss of control of the sailplane.
