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86-07-04: 86-07-04 SHORT BROTHERS, LTD.: Amendment 39-5272. Applies to Models SD3- 30 and SD3-60 airplanes as listed in Short Brothers, Ltd. Service Bulletins SD3-27-29, dated April 1985 (for SD3-30 airplanes), and SD360-27-06, dated April 1985 (for SD3-60 airplanes), certificated in any category. To prevent the loss of elevator control, accomplish the following within the next 90 days after the effective date of this AD, unless already accomplished: 1. Modify the elevator torque tube assembly in accordance with Short Brothers, Ltd. Service Bulletin SD3-27-29, dated April 1985 (for SD3-30 airplanes), or SD360-27-06, dated April 1985 (for SD3-60 airplanes). 2. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment ofinspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Shorts Aircraft, 1725 Jefferson Davis Highway, Suite 510, Arlington, Virginia 22202. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective May 8, 1986.
2012-07-04: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 680 airplanes. This AD was prompted by a false cross-feed command to the right-hand fuel control card, due to the cross-feed inputs on the left- and right-hand fuel control cards being connected together and causing an imbalance of fuel between the left and right wing tanks. This AD requires adding diodes to the fuel cross-feed wiring, and revising the airplane flight manual to include procedures to use when the left or right generator is selected OFF. We are issuing this AD to prevent lateral imbalance of the airplane, resulting from uncontrolled fuel cross-feed, which can be corrected by deflecting the aileron trim; deflecting the aileron trim increases the pilot's workload and could exceed the airplane's limitation in a short period of time, resulting in reduced controllability of the airplane.
97-23-17: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) 90, 100, 200, and 300 series airplanes. This action requires inspecting gray, blue, or clear Ethylene Vinyl Acetate (EVA) tubing near the co-pilot's foot warmer for collapse or deformity. If the tubing is collapsed or deformed, this action requires replacing and re-routing the tubing. This EVA tubing is used on the pneumatic de-ice indicator lines and the pressurization control system pneumatic lines that provide vacuum to the outflow safety valves that depressurize the airplane. This action is the result of several reports of collapsed EVA tubing. The actions specified by this AD are intended to prevent a loss of vacuum to depressurize the airplane cabin, which could result in personal injury to the door operator; and to prevent malfunction of the de-ice indicator system, which could cause the pilot to immediately exit icing conditions.
82-13-01: 82-13-01 BENDIX: Amendment 39-4405. Applies to Bendix Engine Products Division's S-1200 series magnetos which have green distributor blocks and do not have the letter "R" metal stamped on the identification plate as described under "Identification" in Bendix Service Bulletin No. 613. Compliance required as indicated unless already accomplished. To reduce the possibility of magneto and engine malfunction resulting from loose distributor block bushings, accomplish the following: (a) Comply with the inspection, replacement, and identification procedures outlined under "Detailed Instructions" shown in Bendix Service Bulletin No. 613, dated April 1981, or later approved revisions in accordance with the following schedule: MAGNETO TIME IN SERVICE SINCE NEW OR OVERHAUL ACCOMPLISH Less than 1000 hours Inspect within the next 25 hours in service and every 25 hours in service thereafter, unless replaced with new "Gripper Bushing" distributor block. 1000 hoursor more but less service than 1900 hours Inspect within the next 100 hours in service unless replaced with new "Gripper Bushing" distributor block. 1900 hours or more Replace the distributor block with new "Gripper Bushing" distributor block within the next 100 hours in service. Any distributor block discovered having a loose bushing must be replaced before further flight. (b) If compliance with Paragraph (a) reveals the distributor block to be contaminated with brass filings or bronze colored dust, inspect the engine as follows: (1) Observe engine pistons through spark plug holes for evidence of burning. (2) Check valve dry tappet clearance per engine manufacturer's instructions. If piston damage or lower than specified dry tappet clearance is present, the engine must be inspected and maintained in accordance with the engine manufacturer's instructions for continued airworthiness. Make an engine log entry of each compliance with Paragraph (a) including the magneto serial number. Equivalent means of compliance may be approved by the Chief of the New York Aircraft Certification Office, ANE-170, Federal Aviation Administration (FAA), New England Aircraft Certification Division, Federal Building, JFK International Airport, Jamaica, New York 11430. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this AD can be accomplished. This amendment becomes effective June 28, 1982.
2022-04-04: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies, Inc. C-125, C145, IO-360, IO-470, IO-550, O-300, O-470, TSIO-360, TSIO-520 series model reciprocating engines and certain Continental Motors IO-520 series model reciprocating engines with a certain oil filter adapter installed. This AD was prompted by reports of two accidents that were the result of power loss due to oil starvation. This AD requires replacing the oil filter adapter fiber gasket (fiber gasket) with an oil filter adapter copper gasket (copper gasket). The FAA is issuing this AD to address the unsafe condition on these products.
2022-04-02: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000 model turbofan engines. This AD was prompted by reports of high levels of wear on the seal fins on a small number of certain high-pressure turbine triple seals. This AD requires manual deactivation of the modulated air system (MAS) control valves. The FAA is issuing this AD to address the unsafe condition on these products.
2012-04-14: We are adopting a new airworthiness directive (AD) for RB211- Trent 800 series turbofan engines. This AD requires inspecting the front combustion liner head section for cracking, and if found cracked, removing the front combustion liner head section from service at the next shop visit. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. Specifically, routine inspections revealed cracking on the head sections of two RB211-Trent 800 front combustion liners. We are issuing this AD to prevent uncontained engine failure and damage to the airplane.
97-21-09: This amendment supersedes existing airworthiness directive (AD) 96-24-09, applicable to Allison Engine Company Model 250-C47B turboshaft engines, that currently requires replacing the engine main electrical harness assembly with an improved assembly, disabling the overspeed solenoid, inspecting the engine control unit (ECU) internal PW10 voltage to determine electrical noise characteristics, and replacing units not considered serviceable. In addition, the existing AD requires adding a placard to the helicopter instrument panel notifying the pilot that the overspeed protection system is disabled and removes a placard which was required by priority letter AD 96-21-12; revises the Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 407 Rotorcraft Flight Manual (RFM); and requires maintenance actions to clear the ECU of faults prior to each flight. This amendment continues to require replacing the engine main electrical harness assembly with an improved assembly, but adds the requirements to install a new hydromechanical unit (HMU) and ECU, removing the placard notifying the pilot that the overspeed protection system is disabled, and revises the BHTC Model 407 RFM. This amendment is prompted by the development of overspeed protection system modifications to reactivate the overspeed solenoid in conjunction with raising the power turbine overspeed trip point and revising the overspeed system to default to a minimum fuel flow in the event of its activation. The actions specified by this AD are intended to prevent uncommanded inflight engine shutdowns, which can result in autorotation, forced landing, and possible loss of the helicopter.
87-16-03: 87-16-03 AIRBUS INDUSTRIE: Amendment 39-5623. Applies to Model A300 B2 and B4 series airplanes, certificated in any category. To prevent the development of cracks which can lead to wing skin failure, accomplish the following within 90 days after the effective date of this AD, or upon reaching the threshold indicated below, whichever occurs later, unless already accomplished: A. Inspect for cracks in the top skin of each wing at the level of rib 9 between front and rear spars, prior to the accumulation of 17,000 landings for B2 series airplanes, and prior to the accumulation of 14,200 landings for B4 series airplanes, in accordance with the accomplishment instructions of Airbus Industrie (AI) Service Bulletin A300-57-118, Revision 1, dated March 29, 1984. Thereafter, repeat the inspections at intervals not to exceed 7,600 landings. B. If cracks are found during the inspections required by paragraph A., above, follow procedures described in Paragraph 1.C.(5) of AI Service Bulletin A300-57-118, Revision 1, dated March 29, 1984. C. Incorporation of AI Modification 2099, as described in Airbus Service Bulletin A300-57-077, Revision 1, dated December 15, 1979, which replaces clearance fit HI-LOK bolts with taperlock bolts, constitutes terminating action for the inspection requirements of this AD. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Centrecda, Avenue Didier Daurat, 31700 Blagnac,France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 4, 1987.
97-24-01: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires repetitive inspections to detect migration or damage of the bushings of the main landing gear (MLG) trailing arm, and replacement of any damaged or displaced bushing. This amendment is prompted by reports indicating that damagedor displaced bushings have been found on several MLG trailing arms of Dornier Model 328-100 series airplanes. The actions specified in this AD are intended to prevent failure of the bushings of the MLG trailing arm, which could result in collapse of the MLG during landing.
75-12-04: 75-12-04 ROCKWELL INTERNATIONAL: Amendment 39-2231. Applies to Sabreliner Model NA 265-40 airplanes, serial numbers 282-112, -113, -115 through -137, and model NA 265-60 airplanes, serial numbers 306-64 through -102, certificated in all categories. To prevent possible failure of engine supports due to cracks in the engine support beams outer skins, accomplish the following: (a) Within the next 10 hours' time in service after receipt of this airmail letter, unless already accomplished, perform a close visual inspection of the R.H. and L.H. engine support beam outer skin (Ref: 40/60, IPC NA 62-1208, Chapter 17, Page 14, Item 6) for cracks. If cracks are found, either: (1) Install a doubler type repair per NA 265-40/-60 Structural Repair Manual for issuance of special flight permit per FAR's 21.197 and 21.199 to a base where (2) can be performed; or (2) Replace the entire outer skin prior to further flight. Replacement of the outer skin constitutes terminating action under this AD. (b) Within the next 50 hours' time in service after receipt of this airmail letter, unless already accomplished, inspect the R.H. and L.H. engine support beam outer skin by eddy current method for hardness in accordance with Sabreliner Service Bulletin 75-16 dated May 12, 1975, or later FAA-approved revisions. If the material is as required no further action is necessary. If the material is found defective (too hard), compliance is required as follows: For those airplanes having a crack in the engine support beam outer skin, repair and ferry flight only to a base for skin replacement. For those airplanes with no cracks in the engine support beam outer skin, inspect for cracks at intervals not to exceed 100 hours' time in service from the time of the first eddy current inspection using the dye penetrant method in accordance with Sabreliner Service Bulletin 75-16 dated May 12, 1975, or later FAA-approved revisions until the defective skin is replaced. Replacementof defective skin must be accomplished no later than 650 hours' time in service after receipt of this airmail letter and is considered terminating action. (c) Equivalent inspections and repairs may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. This amendment becomes effective June 9, 1975 for all persons except those to whom it was made effective by individual airmail letters, dated May 13, 1975 which contained this amendment.
97-23-08: This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R3000 airplanes that are equipped with yaw damper Modification No. 013. This AD requires inspecting the bridle cable ends for correct installation in the grooved screw, inspecting for correct cable winding on the capstan and correct cable tension, and correcting any discrepancies found. This AD also requires installing lockwire to the tension adjustment screw. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the rudder control from becoming jammed because of the yaw damper control cables slipping out of the groove on the tension adjustment screw, which could result in a reduction in the directional controllability of the airplane.
92-16-07: 92-16-07 CESSNA: Amendment 39-8316. Docket No. 92-CE-16-AD. Applicability: Model 441 airplanes (serial numbers 441-0001 through 441-0362), certificated in any category. Compliance: Required initially upon the accumulation of 3,000 hours time-in-service (TIS) or within the next 200 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,000 hours TIS, unless already accomplished. To prevent loss of horizontal stabilizer front spar structural support caused by cracks in the fuselage bulkhead, accomplish the following: (a) Gain access to and dye penetrant inspect the horizontal stabilizer forward attach bulkhead at Fuselage Station (FS) 387.22 in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Attachment to Service Bulletin CQB91-1R1, dated June 21, 1991. (b) If cracks are found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, replace thehorizontal stabilizer forward attach bulkhead at FS 387.22 and install Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991. (c) The installation of Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991, is considered terminating action for the repetitive inspection requirements of this AD. Although not required, this installation may be accomplished at any time after the initial inspection. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita,Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (f) The inspections and possible installation required by this AD shall be done in accordance with Cessna Attachment to Service Bulletin CQB91-1R1, and Cessna Service Kit SK441-103A, both dated June 21, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (g) This amendment becomes effective on August 30, 1992.
2012-07-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A340-500 and -600 series airplanes. This AD requires repetitive inspections of the forward and aft attachment fittings and of the swan neck for cracks, and replacing the attachment fittings and the swan neck with serviceable ones if necessary. This AD was prompted by reports of cracks on the forward attachment fittings of the left and right sides of the forward hinge of the nose landing gear (NLG) aft door. We are issuing this AD to detect and correct cracks of the forward attachment fittings and the swan neck, which could lead to the in-flight detachment of the NLG aft door and result in injury to persons on the ground or damage to the airplane.
97-23-05: This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R3000 airplanes. This AD requires replacing the attachment bolt between the pitch control cables and control column lever with a bolt of improved design. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the pitch control cables on the control column from becoming jammed due to failure of the attachment bolt, which could result in a reduction in the directional controllability of the airplane.
97-23-04: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires replacing the fuel tank vent valves with modified fuel tank vent valves. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the fuel tank inward vent valve from freezing, which, if followed by a cold soak at altitude, could result in wing airfoil distortion and structural damage with consequent degradation of the airplane's handling qualities.
92-07-14: 92-07-14 AIR TRACTOR INC: Amendment 39-8210. Docket No. 91-CE-55-AD. Applicability: Models AT-300, AT-301, and AT-302 airplanes (serial numbers (S/N) 300-0001 through 301-0688); Model AT-400 airplanes (S/N 400-0244 through 400-0415; and Model AT-400A airplanes (all S/N), certificated in any category. Compliance: Required within the next 90 calendar days after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 12 calendar months. To prevent failure of the wing structure that could result in loss of control of the airplane, accomplish the following: (a) Remove the inspection plates on the lower side of the wing leading edge skin, and visually inspect the upper and lower aluminum spar caps from the centerline to outboard end for corrosion using a flashlight and mirror. (1) If corrosion is found that is equal to or less than the criteria in Air Tractor Inc. Service Letter No. 90, dated May 6, 1991, prior tofurther flight, repair in accordance with the instructions in Air Tractor Inc. Service Letter No. 90, dated May 6, 1991. (2) If corrosion is found that is more than the criteria in Air Tractor Inc. Service Letter No. 90, dated May 6, 1991, prior to further flight, replace the wing spar cap in accordance with the applicable maintenance manual. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas 76193. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. (d) The inspections and possible repair required by this AD shall be done in accordance with Air Tractor Inc. Service Letter No. 90, dated May 6, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Air Tractor Inc., P.O. Box 485, Olney, Texas 76374-0150. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. (e) This amendment becomes effective on May 8, 1992.
2012-06-21: We are adopting a new airworthiness directive (AD) for all DASSAULT AVIATION Model MYSTERE-FALCON 900 airplanes. This AD was prompted by multiple reports of fuel leakage from a defective fuel high-level sensor located in the wing front spar. This AD requires inspecting to determine fuel quantity sensors part numbers and replacing of certain fuel quantity sensors with new fuel quantity sensors. We are issuing this AD to prevent internal fuel leakage with significant fuel vapors, which could result in a fire hazard.
97-23-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 727-100 series airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to prohibit stabilized operation between 60 and 75 percent N1 speed during ground operations in reverse or forward thrust. This amendment is prompted by a report that, during preparation for takeoff, a transport category airplane equipped with Rolls-Royce Tay 650-15 engines sustained an engine fan blade failure, followed by an engine fire. The actions specified in this AD are intended to prevent uncontained failure of engine fan blades due to high cycle fatigue cracking, which could result in loss of thrust from the affected engine and secondary damage to the airplane and/or fire.
97-22-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). This AD requires fabricating and installing a placard that restricts the use of the forward and aft vent blower assemblies to only the "OFF" or "HIGH" position. This AD also requires incorporating a modification that would replace the bearings on the vent blower assemblies with improved design bearings, and provide thermal protection for the vent blowers, as applicable. Incorporating the modification will eliminate the need for the placard. The AD results from reports of vent blower assembly bearings seizing and locking the blower motor on several of the affected airplanes. The actions specified by this AD are intended to prevent the vent blower assembly bearings from seizing, which could result in smoke emanating from the insulating material covering the electrical wiring and entering the airplane cabin.
2012-06-17: We are adopting a new airworthiness directive (AD) for certain [[Page 16918]] Rolls-Royce Deutschland (RRD) Models Tay 611-8 and Tay 611-8C turbofan engines. This AD requires replacement of the high-pressure (HP) turbine spanner retaining nut. This AD was prompted by the discovery that certain HP turbine spanner retaining nuts were improperly heat treated after application of silver plating. We are issuing this AD to prevent failure of the HP turbine stage 2 disc, uncontained engine failure, and damage to the airplane.
2012-06-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by a report of the inability to open the airstair door while on the ground, because the airstair door seal did not deflate, which prevented the airstair door from opening. This AD requires changing the wiring that controls the pneumatic shut-off valve. We are issuing this AD to prevent the airstair door seal from not deflating, which could result in the airstair door not opening and could impede evacuation in the event of an emergency.
92-18-11: 92-18-11 BEECH: Amendment 39-8356. Docket No. 92-CE-28-AD. Applicability: Model A36 airplanes (serial numbers E-1946, E-2104, and E-2111 through E-2682), and Model B36TC airplanes (serial numbers EA-320, and EA-389 through EA-524), certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent failure of the landing gear circuit, which could result in the inability to extend the landing gear, accomplish the following: (a) Seal the upper door upper hinge cavity in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin No. 2437, dated April 1992. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalentlevel of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (d) The modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2437, dated April 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (e) This amendment becomes effective on October 18, 1992.
97-22-14: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-50 and -80C2 series turbofan engines. This action requires removal from service of defective high pressure compressor rotor (HPCR) stage 3-9 spools, and replacement with serviceable parts. This amendment is prompted by a report of an uncontained failure of an HPCR stage 3-9 spool installed on a GE model CF6-80C2 turbofan engine. The actions specified in this AD are intended to prevent failure of the HPCR stage 3-9 spool, which can result in an uncontained engine failure and damage to the aircraft.
97-22-09: 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. This AD requires amending the Limitations Section of the Dornier 228 Pilot's Operating Handbook (POH) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This POH amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight. EFFECTIVE DATE: December 5, 1997.