Results
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.
87-03-09: 87-03-09 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, PZL-MIELEC: Amendment 39-5522. Applies to Model M18 Dromader (Serial Number 1Z001-01 through 1Z014-30, and 1Z015-01 through 1Z016-03) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent loosening of the engine mount shock absorber nuts, accomplish the following: (a) Within the next 100 hours time-in-service (TIS), replace all 0.8mm safety wire on the M6400- 105 nuts with 1.0 to 1.2mm (0.039 inch to 0.047 inch) wire as described in paragraph III.1, PZL-Mielec M18 Mandatory Service Bulletin (MSB) No. E/02.082/85 dated September 6, 1985. (b) Within the next 100 hours TIS and at each 100 hours TIS thereafter, visually inspect the Part Number M6400-105 nuts for security. If loose, prior to further flight, tighten and secure as described in paragraph III.2 of the subject MSB. (c) Within the next 600 hours TIS or the nexttime the engine frame is removed, whichever occurs first, perform the engine frame modification described in paragraph III.3 of the subject MSB. (d) The actions in paragraph (b) of this AD may be discontinued after accomplishment of the modification described in paragraph (c) of this AD. (e) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (f) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance on the airplane. (g) An equivalent means of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B- 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to hereinupon request to Wytwornia Sprzetu Komunikacyjnego; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on March 1, 1987.
2012-06-07: We are superseding an existing airworthiness directive (AD) for certain Model A330-200 and -300 series airplanes, and Model A340- 200, -300, -500, and -600 series airplanes. This AD was prompted by reports of loose pneumatic quick-disconnect unions on Goodrich pitot probes that might be the result of mis-torque of the affected unions at equipment manufacturing level. This AD adds airplanes to the AD applicability. We are issuing this AD to detect and correct loose unions on the pitot probes, which could lead to an air leak, resulting in incorrect total pressure measurement and consequent erroneous calibrated airspeed (CAS)/MACH parameters delivered to the flightcrew by the air data computer.
97-22-08: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft LTD (Pilatus) Models PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4 airplanes and all Pilatus Model PC-12 airplanes. This AD requires amending the Limitations Section of either the airplane flight manual (AFM) or the 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 AFM 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.
72-16-03: 72-16-03 GENERAL ELECTRIC: Amendment 39-1495. Applies to Models CF6-6D and CF6-6D1 turbofan engines. Compliance required as indicated. To prevent cracking and possible failure of stage 2 high pressure turbine discs, unless already accomplished, remove from service stage 2 high pressure turbine discs Part No. 9687M40P03, P04, P05, or P06 prior to reaching a life limit of 2100 cycles. For the purposes of this AD, the definition of cycles is that appearing in the CF6 Shop Manual GEK 9266 Section 72-00-00 Inspection page 301. (General Electric Alert Service Bulletin CF6 72-320 pertains to this subject.) This amendment is effective August 8, 1972.
93-05-18: 93-05-18 FOKKER: Amendment 39-8522. Docket 92-NM-180-AD. Applicability: Model F28 Mark 0100 airplanes, serial numbers 11244 through 11356, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent jamming of the servo and to ensure that the stabilizer can be repositioned after an uncommanded trim movement, accomplish the following: (a) Within 400 hours time-in-service after the effective date of this AD, unless accomplished previously within the last 1,600 hours time-in-service, inspect the end-cap of the horizontal stabilizer dual actuator servo valve manifold to detect moisture in accordance with Fokker Service Bulletin SBF100-27- 029, dated January 29, 1991. Prior to further flight, remove any moisture found in accordance with the service bulletin. (b) Within 2,000 hours time-in-service or one year after the effective date of this AD, whichever occurs first, modify the end-cap of the servo valve of the horizontal stabilizer hydraulic actuator in accordance with Fokker Service Bulletin SBF100-27-032, dated September 20, 1991, as revised by Fokker Service Bulletin Change Notification SBF100-27-032/01, dated October 19, 1992. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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) The inspection shall be done in accordance with Fokker Service Bulletin SBF100-27-029, dated January 29, 1991. The modification shall be done in accordance with Fokker Service Bulletin SBF100-27-032, dated September 20, 1991; and Fokker Service Bulletin Change Notification SBF100-27- 032/01, dated October 19, 1991 (for Fokker Service Bulletin SBF100-27-032, dated September 20, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on May 14, 1993.
2012-05-08: We are adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 airplanes. This AD requires repetitive inspections for fuel leakage and cracks on the wing spar II, close to the rib 10 area, and repair if necessary. This AD was prompted by reports of fuel seepage at the left- hand wing, close to the rib 10 area in two airplanes. We are issuing this AD to detect and correct cracking on the wing spar II, which could result in a fuel leak, consequent reduced structural integrity of the airplane, and possible fire.
47-20-05: 47-20-05 ERCO: (Was Mandatory Note 13 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft Serial Numbers 800 Through 2037. Compliance required prior to October 1, 1947. Cracks have occurred in the belly skin at the rearmost rivet attaching the center section belly skin outer stiffeners (Erco P/N 415-13056 L/R) to the belly skin. To prevent similar failures where cracks have not yet developed, install 0.064-inch 24ST alclad angles 1/2-inch wide with legs of 1 3/32 inches and 1/2 inch (Erco P/N 415-13068). Attach the 1 3/32-inch leg to the outboard side of the aft end of each belly skin outer stiffener with two AN 470AD3-4 rivets (3/32-inch diameter, universal head, A17ST, 1/4-inch long) and to the center section rear beam with one AN 470AD3-5 rivet. (AN 430 type round head rivets may be used.) If cracks are found in the belly skin, drill relief holes at the ends of the cracks and install triangular shaped patch plates as follows in addition to the angle stiffeners described above. Prepare the patch plates of 0.032-inch 24ST alclad material of such a shape that it will pick up the last two rivets which attach the aft end of the belly skin outer stiffener to the belly skin and the three rivets attaching the rear beam to the belly skin which are in line with and to either side of the stiffener. Remove the above-mentioned existing rivets and attach the patch plates through these holes using AN 470AD3-3 and -4 rivets. Attach the patch plate to the belly skin with six additional AN 470AD3-3 rivets, three through each side of each plate. (Erco's Ercoupe Service Department Bulletin No. 18 dated January 9, 1947, covers this same subject.)
97-22-11: This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche Rinaldo Piaggio S.p.A. (Piaggio) Model P-180 airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM 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.
59-01-01: 59-01-01 CONVAIR: Applies to All 240 and 340 Aircraft and to 440, Serial Nos. 312 Through 502. Compliance required as follows: 440 aircraft not later than December 31, 1958; 340 and 240 aircraft not later than April 30, 1960. Inflight fire experience and fire tests on the Convair engine nacelle have shown the need for further improvement in detecting fires originating in zones one and two. Additional continuous type detector coverage was provided in production 440 aircraft for the zone one bellmouth and zone two chimney areas. Because of false warnings the original system was rendered inoperative by Convair Service Air Gram No. 173, and an improvement program was initiated. This program has now been completed and a revised system developed with functional reliability proven by test under laboratory and service conditions. To improve and reactivate the continuous type fire detector system installation on 440 aircraft and to provide equivalent coverage for 240 and 340aircraft, the following must be accomplished: (1) On 440 aircraft, the existing continuous type fire detector system must be modified to incorporate improved detector elements and assemblies, including connectors, control box cannon plugs and mounting provisions. Upon accomplishment, the continuous type system must be made operative. On aircraft of Serial Nos. 503 and subsequent which incorporate these changes, the system must be maintained operative. (Convair Service Bulletin No. 440-41 covers an acceptable method of accomplishing these changes.) (2) On 240 and 340 aircraft, either modification (a) or modifications (b) and (c) must be accomplished: (a) Install additional fire detector coverage consisting of a continuous type system installed in each augmenter bellmouth and each vent chimney, similar to that now installed on 440 aircraft. The airplane flight manual must be revised to include a description of the system operation and the required emergency procedures. (Convair Service Bulletin No. 340-222 covers an acceptable method of accomplishment of this installation on 340 aircraft. Service bulletins applicable to 240 aircraft will be published at a later date, if there is a request for such information from operators desiring to accomplish this in preference to the modifications described in items (b) and (c) following.) (b) Install at least three unit-type detectors at each augmenter tube bellmouth or on brackets mounted on the shroud or engine cowling and located in close proximity to the bellmouths, such as to be in the path of flames which would enter the bellmouth in the event of fire. Existing detectors at the upper cowl flaps and those mounted on the upper side shroud panels may be counted among the three units specified, provided they are installed in accordance with Convair Bulletins No. 240-419 and No. 240-419A or conform to original Model 340 production configuration. The third bellmouth detector location must conformwith figure 6 of Technical Development Center Report No. 250. Revised detector installations must be ground and flight tested in accordance with Thomas A. Edison Installation Manual, Publication No. 1058, dated July 15, 1950, to assure correct circuit adjustment. (c) To minimize flame stratification and improve effectiveness of present fire detection, a reduction in airflow rate in zone two must be effected by modifications in accordance with Convair Service Bulletin 340-176 or equivalent for the 340 aircraft, and in accordance with Convair Service Bulletin 240-473 or equivalent for the 240 aircraft. This supersedes AD 58-10-01.
2006-13-06: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation 250-B and 250-C series turboprop and turboshaft engines with certain part numbers (P/Ns) of gas producer rotor assembly tie bolts manufactured by EXTEX Ltd., Pacific Sky Supply Inc., Rolls- Royce Corporation (RRC), and Superior Air Parts Inc. This AD requires operators to remove from service affected gas producer rotor assembly tie bolts, and install serviceable tie bolts. This AD results from eleven reports of RRC tie bolt failure due to high cycle fatigue. We are issuing this AD to prevent tie bolt failure that could cause loss of engine power, resulting in a first stage turbine wheel overspeed and an uncontained engine failure.