32 Airworthiness Directives: 22 airplane, 7 rotorcraft, 3 engine.
AD 2001-02-10 · published Feb 2, 2001, effective Mar 19, 2001
Raytheon Aircraft Company Beech Models 60, A60, and B60 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 60, A60, and B60 airplanes. This AD requires you to inspect for the existence of any lower forward wing bolts with the Mercury Aerospace trademark, and replace any such bolt with an FAA-approved bolt without this trademark. This AD is the result of a report that wing bolts supplied by Mercury Aerospace may not meet the required Rockwell hardness specifications. The actions specified by this AD are intended to detect and correct wing bolts that do not meet strength requirements. Continued airplane operation with such bolts could result in fatigue failure of the bolts with consequent separation of the wing from the airplane.
AD 2001-02-51 · published Feb 2, 2001, effective Feb 7, 2001
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 and EMB-135 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-02-51 that was sent previously to all known U.S. owners and operators of EMBRAER Model EMB- 145 and EMB-135 series airplanes by individual notices. This AD requires revising the FAA-approved airplane flight manual and installing placards to alert the flight crew to the maximum speed for airplane retrimming after takeoff and during the climb phase. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to prevent high pitch control forces, which could result in possible loss of control of the airplane.
AD 2001-03-01 · published Feb 2, 2001, effective Feb 20, 2001
Israel Aircraft Industries, Ltd., Model Galaxy Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Israel Aircraft Industries, Ltd., Model Galaxy airplanes. This action requires revising the Airplane Flight Manual to advise of the proper operation of the main entry door. This action is necessary to prevent the main entry door from jamming, which could impede the safe evacuation of passengers and crew during an emergency. This action is intended to address the identified unsafe condition.
AD 2001-02-13 · published Feb 6, 2001, effective Feb 28, 2001
The Cessna Aircraft Company Model 525 (CitationJet 1) Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain The Cessna Aircraft Company (Cessna) Model 525 (CitationJet 1) airplanes. This AD requires you to replace certain direct current (DC) power battery switches. This AD is the result of reports of the potential for a certain 8-pole battery switch to fail during flight. The actions specified by this AD are intended to prevent this battery switch from failing while the airplane is in-flight, which is a latent failure. This could result in the pilot's inability to select "EMER" power or the inability to disconnect an overheated main ship's battery. On a battery overheat indication, the Airplane Flight Manual (AFM) instructs the pilot to disconnect the battery and, if the problem cannot be fixed, the pilot should immediately land the airplane. The main ship's battery that remains powered in an overheated condition may become hot enough to damage adjacent components and structure and may interfere with continued flight and a safe landing.
AD 2001-03-04 · published Feb 14, 2001, effective Mar 1, 2001
Bombardier Model CL-600-2B19 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires repetitive ultrasonic inspection to detect damage of the actuator lugs of the flight spoiler center hinge; corrective action, if necessary; and eventual replacement of the flight spoilers with new, improved spoilers. This action is necessary to prevent uncommanded deployment of a flight spoiler, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-03-05 · published Feb 15, 2001, effective Feb 20, 2001
Learjet Model 45 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action requires revising the airplane flight manual (AFM) to prohibit flight into known icing conditions; inspecting the anti-ice manifold assembly for missing material, and performing corrective actions if necessary; replacing the anti-ice manifold assembly with a new assembly, which terminates the AFM revision requirement; and revising the Learjet 45 maintenance program to incorporate additional inspections and maintenance practices for the anti-ice manifold assembly. This action is necessary to prevent metal fragments from breaking off the anti-ice manifold assembly due to fatigue, which could block a duct in the anti- ice system and result in an unannunciated loss of ice protection. This action is intended to address the identified unsafe condition.
AD 2001-03-06 · published Feb 15, 2001, effective Mar 22, 2001
Raytheon (Beech) Model MU-300, MU-300-10, 400, and 400A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Raytheon (Beech) Model MU-300, MU-300-10, 400, and 400A series airplanes, that requires repetitive inspections of the bleed air supply tube assemblies for discrepancies; and replacement of the bleed air tube assembly with a new bleed air tube assembly, if necessary. In lieu of accomplishing the repetitive inspections, this AD also provides for a revision of the Airworthiness Limitations to incorporate, among other things, certain inspections and compliance times to detect discrepancies of the subject area; and corrective action, if necessary. This amendment is prompted by reports of broken wire braiding in the bellows assembly of the bleed air supply tube assembly due to premature failure from loading. The actions specified by this AD are intended to prevent the bleed air supply tube assembly from disconnecting and contacting other pneumatic or electrical systems of the airplane or expelling high temperature air on surrounding systems and structure. Such a condition could reduce the functional capabilities of the airplane or the ability of the flight crew to cope with adverse operating conditions.
AD 2001-03-13 · published Feb 15, 2001, effective Mar 22, 2001
Boeing Model 707 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707 series airplanes, that requires modification of certain areas of the upper skin of the wing. This amendment is necessary to prevent cracking of the upper skin of the wing, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
AD 2001-03-07 · published Feb 16, 2001, effective Mar 23, 2001
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires identifying the part and serial numbers of the pressure reducing valve on each air pressurization unit, testing pressure reducing valves and air pressurization units having affected serial numbers, and replacing faulty valves or units with new parts. The actions specified by this AD are intended to prevent the simultaneous failure of two air pressurization units, which could result in loss of three hydraulic circuits and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-03-09 · published Feb 16, 2001, effective Mar 23, 2001
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires replacement of nuts on the clevis assemblies that support the auxiliary tracks of the inboard leading edge slats. This amendment is necessary to prevent loose or missing nuts on the clevis assemblies, which could cause the inboard leading edge slats to be loose or in an incorrect position and result in partial or total failure or loss of the slats. This action is intended to address the identified unsafe condition.
AD 2001-03-10 · published Feb 21, 2001, effective Mar 28, 2001
Boeing Model 747-100, -200, -300, -400, and 747SR Series Airplanes
This amendment adopts a new airworthiness directive (AD); applicable to all Boeing Model 747-100, -200, -300, -400, and 747SR series airplanes; that requires a one-time inspection to determine whether H-11 steel bolts are installed as attach and support bolts at the trailing edge flap transmissions, and replacement of any H-11 steel bolt with an Inconel bolt. The actions specified by this AD are intended to prevent loss of a flap transmission, which could reduce lateral controllability of the airplane.
AD 2001-03-11 · published Feb 21, 2001, effective Apr 6, 2001
British Aerospace HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes that are equipped with certain main landing gear (MLG) radius rods. This AD requires inspection of the MLG radius rods for cracks and replacement of any cracked rod. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the MLG radius rods. Such cracks could result in MLG failure during takeoff, landing, or taxi operations, with consequent loss of airplane control.
AD 2001-03-12 · published Feb 21, 2001, effective Mar 28, 2001
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that currently requires repetitive inspections to detect loose or migrated levers of the elevator cable tension regulators, and replacement of the regulator assembly with a new assembly, if necessary. This amendment requires modification of the elevator cable tension regulator lever assembly, terminating the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the elevator cable tension regulator from becoming detached from the splined shaft of the assembly, which could result result in difficulty adjusting the elevators, leading to reduced controllability of the airplane.
AD 2001-03-14 · published Feb 21, 2001, effective Mar 28, 2001
Airbus Model A300 B4 Series Airplanes, and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (Collectively Called A300-600) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes and all Airbus Model A300-600 series airplanes, that requires a one-time high frequency eddy current inspection to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 25; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the splice fitting at fuselage FR 47, which could result in reduced structural integrity of the airplane.
AD 2001-04-01 · published Feb 21, 2001, effective Mar 28, 2001
BAe Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAe Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ series airplanes, that requires repetitive non- destructive testing inspections to detect cracking at the fuselage end of the inner sidestays of the main landing gear (MLG) by the anti- rotation pin, and replacement of the sidestay with a new sidestay, if necessary. This amendment is necessary to detect and correct fatigue cracking of the inner sidestays of the MLG, which could result in failure of the MLG. This action is intended to address the identified unsafe condition.
AD 2001-04-02 · published Feb 21, 2001, effective Mar 28, 2001
Bombardier Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires inspection to determine the orientation of the Wiggins fuel couplers of the fuel tank vent line and scavenge line in the right wing at station 249, and follow-on corrective actions. This amendment is necessary to prevent contact between the nuts of the Wiggins fuel couplers and the stiffener on the access panel of the upper surface of the right wing, which could compromise the lightning protection of the fuel tank of the right wing in the event of a lightning strike, and could result in possible fuel tank explosion. This action is intended to address the identified unsafe condition.
AD 2001-04-04 · published Feb 21, 2001, effective Apr 6, 2001
Dornier Luftfahrt GMBH Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GMBH (Dornier) Models 228-100, 228- 101, 228-200, 228-201, 228-202, and 228-212 airplanes that have windshield spray nozzle option SCN 3109 installed. This AD requires you to deactivate the windshield spray nozzle heating elements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the windshield spray nozzle heating system from overheating, which could result in smoke in the cockpit and prompt the crew to initiate emergency actions.
AD 2001-03-08 · published Feb 22, 2001, effective Mar 29, 2001
Bombardier Model CL-600-2B19 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires, among other actions, certain revisions to the Airplane Flight Manual; and removal of all elevator flutter dampers. That AD also requires installation of new elevator flutter dampers, and replacement of shear pins and shear links with new improved shear pins and shear links. This amendment adds airplanes to the applicability of the existing AD; and requires replacing certain shear pins with new, improved shear pins; and, for certain airplanes, inspection of the maintenance records to determine replacement status of the shear pins; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent premature failure of the shear pins of the elevator damper, which may increase the likelihood of jamming or restricting movement of the elevator and the resultant adverse effect on controllability of the airplane.
AD 2001-04-03 · published Feb 22, 2001, effective Mar 29, 2001
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires inspection of the bolts on the hinge fittings that attach the spring tab and the servo tab to the rear spar of the elevators for evidence of loosening; inspection of the region of the hinge fittings on the spring tab for interference of the bonding jumpers attached to the hinge fittings with the leading edge of the spring tab; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to prevent the spring tab or the servo tab from becoming disconnected, resulting in structural failure. The action is also intended to prevent damage to the leading edge of the spring tab, which could result in loss of control of the elevator.
AD 2001-03-52 · published Feb 28, 2001, effective Mar 5, 2001
Bombardier Model CL-600-2B16 (CL-604) Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-03-52 that was sent previously to all known U.S. owners and operators of Bombardier Model CL-600-2B16 (CL-604) series airplanes by individual notices. This AD requires revising the airplane flight manual to provide the flight crew with revised aft center of gravity (CG) limits. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to prevent fuel migration under conditions of acceleration and/or climb, which could result in the airplane exceeding the aft center of gravity limit, and consequent loss of control of the airplane.
AD 2001-04-05 · published Feb 28, 2001, effective Apr 9, 2001
Raytheon Aircraft Company Beech Model 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Model 1900D airplanes that are equipped with a KLN-90B Global Positioning System (GPS) incorporated in accordance with AlliedSignal Supplemental Type Certificate (STC) SA00245WI-D. This AD requires rewiring the KLN- 90B GPS to eliminate the possibility of inconsistent NAV "FLAG" displays. This AD is the result of an instance where the copilot's NAV "FLAG" display was based on the pilot's NAV source validity. The actions specified by this AD are intended to assure that the copilot's NAV "FLAG" displays are based on the copilot's selected NAV source. Inconsistent NAV "FLAG" displays could cause the copilot to make decisions based on an invalid GPS source without knowing it was invalid.
AD 2001-04-07 · published Feb 28, 2001, effective Apr 13, 2001
SOCATA-Groupe Aerospatiale Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Socata-Groupe Aerospatiale (Socata) Model TBM 700 airplanes. This AD requires you to install a thermal protection sleeve on the propeller governor flexible cable. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent loss of propeller control because of hardening or blocking of the control cable, which could result in the inability to control propeller pitch and inability to feather the propeller. Such failure could lead to loss of airplane control.
AD 2000-23-52 · published Feb 1, 2001, effective Feb 16, 2001
Sikorsky Aircraft Corporation Model S-76A, S-76B, and S-76C Helicopters
This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-23-52, which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters by individual letters. This AD requires, before further flight, performing a fluorescent penetrant inspection of the main rotor shaft assembly (shaft). Also required are recurring fluorescent penetrant inspections and visual inspections for any crack. If any crack is found, the shaft must be replaced with an airworthy shaft before further flight. This amendment is prompted by the discovery of two in-service cracked shafts, one with 477 hours time-in-service (TIS) and one with 313 hours TIS. A third shaft, that had been rejected from the manufacturing process for other reasons, was also discovered to have a crack. The actions specified by this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
AD 2001-02-03 · published Feb 2, 2001, effective Mar 9, 2001
Bell Helicopter Textron Canada Limited Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206A, B, L, L1, and L3 helicopters. This AD requires inspecting the collective lever assembly (assembly) for a raised forging boss, inspecting the assembly for adequate clearance between the collective lever and the swashplate outer ring (outer ring), and modifying any assembly with a raised forging boss and inadequate clearance before further flight. Modifying any assembly that has a raised forging boss and adequate clearance would be required before further flight after January 31, 2001. This AD is prompted by the discovery that a raised forging boss could result in control system interference. The actions specified by this AD are intended to prevent interference between the collective lever and the outer ring, damage to flight controls, and subsequent loss of control of the helicopter.
AD 2001-01-52 · published Feb 6, 2001, effective Feb 21, 2001
Bell Helicopter Textron Canada Model 407 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-01-52, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires, before further flight, reducing the maximum approved never exceed velocity (Vne); inserting a copy of this AD into the Rotorcraft Flight Manual (RFM); installing a temporary placard on the flight instrument panel to indicate the reduced Vne limit; and installing a new redline Vne limit on all airspeed indicators. This amendment is prompted by an accident resulting from a suspected tail rotor strike to the tailboom. The actions specified by this AD are intended to prevent tail rotor blades from striking the tailboom, separation of the aft section of the tailboom with the tail rotor gearbox and vertical fin, and subsequent loss of control of the helicopter.
AD 2001-03-03 · published Feb 13, 2001, effective Feb 28, 2001
Bell Helicopter Textron, Inc. Model 214B and 214B-1 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 214B and 214B-1 helicopters. This action requires, within 10 hours time-in-service (TIS), determining the hours TIS for certain main rotor outboard strap fitting assemblies and creating appropriate records. This action also requires, if any main rotor outboard strap fitting assembly (strap fitting) is determined to have 2,500 or more hours TIS or the hours TIS cannot be determined, replacing the strap fitting with an airworthy strap fitting before further flight. This action also establishes a 2,500-hour retirement life for the strap fitting and revises the Airworthiness Limitations section accordingly. This amendment is prompted by fatigue testing that indicates a fatigue crack may occur in the strap fitting with resulting failure. The actions specified in this AD are intended to prevent failure of a strap fitting, separation of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2000-25-54 · published Feb 14, 2001, effective Mar 1, 2001
Agusta S.p.A. Model A109E Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-25-54, which was sent previously to all known U.S. owners and operators of Agusta (Agusta) S.p.A. Model A109E helicopters by individual letters. This AD requires, before each start of the engines, visually checking both sides of each tail rotor blade (blade) for a crack and, at specified intervals, inspecting each blade for a crack using a 5-power or higher magnifying glass. Dye-penetrant inspecting each blade for a crack is also required at specified time intervals. If a crack is found, replacing the blade with an airworthy blade is required before further flight. This amendment is prompted by five reports of cracked tail rotor blades. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.
AD 2001-01-51 · published Feb 15, 2001, effective Mar 2, 2001
Bell Helicopter Textron Canada Model 222, 222B, 222U, 230, and 430 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-01-51, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, 230, and 430 helicopters by individual letters. This AD requires visually inspecting the main rotor hydraulic actuator support (support) to verify the presence of all dowel pins and sealant between the support and transmission and verifying the proper torque of each attaching nut (nut). This amendment is prompted by the failure of a support resulting in an accident of a BHTC Model 222U helicopter. All retaining studs and shear pins were found sheared or pulled out at the junction between the support and the transmission case. The actions specified by this AD are intended to prevent failure of the support and subsequent loss of control of the helicopter.
AD 2001-02-11 · published Feb 15, 2001
Bell Helicopter Textron, Inc. Model 204B Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 204B helicopters that requires replacing any main rotor mast assembly (mast), part number (P/ N) 204-011-450-001, within 25 hours time-in-service (TIS). This amendment is prompted by the crash of a restricted category Model UH-1B helicopter due to failure of a mast, P/N 204-011-450-001. The same mast P/N is used on the Model 204B helicopters. The actions specified by this AD are intended to prevent failure of the mast and subsequent loss of control of the helicopter.
AD 2000-25-51 · published Feb 2, 2001, effective Feb 20, 2001
Rolls-Royce Deutschland GmbH (Formerly BMW Rolls-Royce GmbH) Model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-25-51 that was sent previously to all known U.S. owners and operators of Rolls-Royce Deutschland GmbH (formerly BMW Rolls-Royce GmbH) model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This action requires that certain high pressure turbine (HPT) stage 1 disks, part numbers (P/N's) BRH20009, BRH20010, BRH12167, BRH12168, BRH12466, and BRH12467; and stage 2 disks, P/N's BRH19349 and BRH19350, be removed before exceeding the new reduced cyclic limit, and replaced with a serviceable disk. This amendment is prompted by a reduction of the life limit for several high pressure turbine (HPT) stage 1 and stage 2 disks. The actions specified in this AD are intended to prevent an uncontained failure of the HPT stage 1 or stage 2 disk due to exceeded life-cycle limits.
AD 2001-03-02 · published Feb 6, 2001, effective Feb 21, 2001
Pratt & Whitney Canada Models PW306A and PW306B Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada (PWC) models PW306A and PW306B turbofan engines. This amendment requires removing compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers from service before exceeding new, lower cyclic life limits. This amendment is prompted by the results of test analyses that indicate certain compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers do not have full published life. The actions specified in this AD are intended to prevent premature cracking of compressor rotor 2nd, 3rd, and 4th stage drum assemblies and impellers which could result in an uncontained engine failure and damage to the airplane.
AD 2001-04-06 · published Feb 28, 2001, effective Apr 4, 2001
CFM International, S.A. CFM56-3, -3B, and -3C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International, S.A. CFM56-3, -3B, and -3C series turbofan engines. This amendment requires that use of certain lubricants no longer on the manufacturer's approved list be discontinued. In addition, this amendment requires a one-time fan disk dovetail wear measurement, and if wear exceeds certain limits, requires an ultrasonic inspection for cracks in the fan disk, and, if necessary, removal from service of fan disks and replacement with serviceable parts. This amendment is prompted by reports of fan disk heavy wear and cracks. The actions specified by this amendment are intended to prevent fan disk failure, which could result in an uncontained engine failure and damage to the aircraft.
