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2016-23-10: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation Model S-76D helicopters. This AD requires revising the rotorcraft flight manual (RFM) to prohibit Barometric Altitude Hold (ALT) mode beyond a certain rate of climb or descent. This AD is prompted by a report of the autopilot being unable to maintain level flight during certain flight conditions. The actions specified by this AD are intended to prevent a significant pilot workload increase, pilot disorientation, and subsequent loss of control of the helicopter.
2001-15-17: This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins, Inc. (Rockwell Collins) CTL-92 transponder control panels that are installed on aircraft. This AD requires you to modify the altitude encoder inputs of the CTL-92 transponder control panels. This AD is the result of reports of noise generation within the CTL-92 transponder control panels that the transponder can interpret and transmit as a random altitude. Air traffic control (ATC) and traffic alert and collision avoidance system (TCAS)-equipped aircraft can then interpret these erroneous random altitudes as valid altitudes. The actions specified by this AD are intended to prevent such erroneous altitude interpretations, which could result in reduced vertical separation or unsafe TCAS resolution advisories.
77-06-01: 77-06-01 MOONEY AIRCRAFT CORPORATION: Amendment 39-2851. Applies to Model M20J airplanes S/N 24-0001 through 24-0085, 24-0087, 24-0088, 24-0090 through 24- 0095, 24-0097 through 24-0102. Compliance required before further flight in instrument meteorological conditions, or night flight, or within the next 5 hours' day visual flight rules time in service after the effective date of this AD, unless already accomplished. To prevent false altitude, airspeed and vertical speed indications from being presented to the pilot, accomplish the following: Disassemble, clean, lubricate, and reassemble the alternate static source valve, Gerdes P/N A-1390, and leak test the static system in accordance with Mooney Service Bulletin No. M20-197 dated February 28, 1977, or later approved revision. The manufacturer's Service Bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directivewho have not already received this Service Bulletin from the manufacturer may obtain a copy upon request to Manager, Engineering Administration and Technical Services, Mooney Aircraft Corporation, Kerrville, Texas 78028; Telephone No. 512-257-4043. This service bulletin may also be examined at the office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Region Office in Fort Worth, Texas. This Amendment becomes effective on March 18, 1977.
93-24-04: 93-24-04 FOKKER: Amendment 39-8753. Docket 93-NM-100-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 to 11286 inclusive, 11289, 11291, 11292, 11293, 11295, 11297, 11300, 11303, 11306, and 11308; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent cracking and reduced structural capability of the forward partial pressure bulkhead and subsequent decompression of the airplane, accomplish the following: (a) Prior to the accumulation of 15,000 total flight cycles, or within 3 months after the effective date of this AD, whichever occurs later, install a doubler assembly on the forward partial pressure bulkhead in accordance with Fokker 100 Service Bulletin SBF100-53-052, Revision 1, dated June 7, 1993. NOTE: Operators who have accomplished the appropriate installation in accordance with the originally issued Fokker Service Bulletin SBF100-53-052, dated January 17, 1992, are considered to be in compliance with this paragraph. (b) 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. 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. (c) 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. (d) The installation shall be done in accordance with Fokker Service Bulletin SBF100-53-052, Revision 1, dated June 7, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-2, 8, 11-13 1 June 7, 1993 3-7, 9-10 Original January 17, 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 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. (e) This amendment becomes effective on January 20, 1994.
93-16-05: 93-16-05 SHORT BROTHERS, PLC: Amendment 39-8662. Docket 93-NM-12-AD. Applicability: All Model SD3-60 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the attachment of the horizontal stabilizer to the airplane, accomplish the following: (a) Prior to the accumulation of 20,000 total landings on the horizontal stabilizer or within 3 months after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 4,000 landings, perform an ultrasonic inspection to detect cracking in the attachment lugs of the horizontal stabilizer in accordance with Shorts Service Bulletin SD360-55-19, dated January 18, 1993. If any cracked lug is found, prior to further flight, replace the lug with a serviceable part in accordance with the service bulletin and continue to inspect at intervals not to exceed 4,000 landings in accordance with this paragraph. (b) 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. (c) 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. (d) The inspections and replacement shall be done in accordance with Shorts Service Bulletin SD360-55-19, dated January 18, 1993. 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 Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. 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. (e) This amendment becomes effective on October 4, 1993.
2022-25-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2001-15-12: This amendment supersedes two airworthiness directives (AD's), 2000-22-01 and 2001-09-07, that both apply to Pratt and Whitney (PW) model PW4000 series turbofan engines. AD 2000-22-01 requires that operators limit the number of PW4000 engines equipped with the high pressure compressors (HPC) in the cutback stator (CBS) configuration to no more than one engine on each airplane, and prohibits the installation of engines with HPC modules in the CBS configuration after the effective date of that AD. AD 2001-09-07 requires that operators limit the number of engines with potentially reduced stability to no more than one engine on each airplane, and remove those engines before exceeding certain cyclic limits. Reports of HPC surges in PW4000 engines that have the HPC in the CBS configuration prompted those AD's. This Amendment will limit the number of PW4000 engines with potentially reduced stability on each airplane by applying rules based on airplane and engine configuration, and require that engines that exceed HPC compressor cyclic limits based on cycles-since-overhaul (CSO) are removed from service. This AD will also limit the number of engines with HPC CBS configuration to one on each airplane, and will establish a minimum rebuild standard for engines that are returned to service. This Amendment is prompted by further analyses of compressor surges in PW4000 engines. The actions specified by this AD are intended to prevent multiple-engine power losses due to high pressure compressor (HPC) surge and to reduce the rate of single-engine surge events.
2001-14-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100 and -200 series airplanes, that requires repetitive inspections for cracking of the station 800 frame assembly, and repair, if necessary. The actions specified by this AD are intended to find and fix fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
75-22-12: 75-22-12 SIKORSKY: Amendment 39-2400. Applies to Sikorsky model S-55 series helicopters incorporating AiResearch model TSE331-3U-303N engines per Supplemental Type Certificate (STC) SH125WE or SH127WE, certificated in all categories. Compliance required as indicated. To prevent possible inflight power loss accomplish the following: A. Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, and thereafter as required by subparagraph (8): (1) Inspect and functionally test the fuel deceleration valve (AiResearch P/N 692545-400 or 868558-1) by disconnecting the fuel bypass line and capping off the line to prevent fuel leakage from the fuel pump. With the engine operating and the "AIR-GROUND" switch in the "GROUND" position, the deceleration bleed valve is to be cycled electrically open and closed using the decel button on the pilot's cyclic control stick to assure that no fuel leakage occurs when the valve is inthe normally closed position. Replace the valve if it does not function properly or leaks any fuel when closed. Remove cap and reconnect bypass line. (2) Remove the tee fitting (AiRearch P/N 3101322-1) from the engine and visually inspect the orifice for blockage. Replace tee fitting if the orifice is restricted. Reinstall tee fitting to engine if found free of obstructions. (3) With the engine operating at 100 percent engine speed and the "AIR- GROUND" switch in the "AIR" position, functionally test the manual fuel flow control valve (AiResearch P/N 868558-2) for proper operation by cycling this valve using the cyclic control switch. If the engine does not react normally by losing RPM and then recovering to 100 percent engine speed as the manual fuel flow control valve is closed and opened, remove and replace this valve and repeat this functional check. (4) Visually inspect the wiring and electrical connections associated with the deceleration control switch toassure that there has been no chafing or other damage which could cause improper operation of the deceleration bleed valve or manual fuel flow control valve. (5) Calibrate engine tachometer and engine tachometer generator as a pair against an accurate standard to within plus or minus 0.5% true reading. (6) Inspect and adjust, as necessary, the underspeed governor adjustment in accordance with the FAA approved rotorcraft maintenance manual. (7) Inspect and adjust, as necessary, the throttle linkage to insure that the throttle high RPM stop is set correctly with respect to the engine fuel control stop in accordance with the FAA approved rotorcraft maintenance manual. (8) Repeat the calibrations and inspections of paragraphs (5), (6) and (7), above, at intervals not to exceed 500 hours time in service, or twelve months, whichever occurs earlier. The calibrations required in (5) must be repeated whenever a tachometer indicator or tachometer generator is replaced.B. Within the next 10 hours time in service after the effective date of this AD, unless already accomplished: (1) Install the fuel enrichment valve system per AiResearch Service Bulletin TSE331-73-0045, dated August 25, 1975, or later FAA approved revisions, and Helitec Corporation Service Bulletin No. AS55-01-3, dated August 29, 1975; and (2) Incorporate and comply with Aviation Specialties Company Sikorsky S- 55, S-55B, and S-55C FAA approved Rotorcraft Flight Manual (RFM) revision No. 6, dated August 29, 1975, or later FAA approved revisions. NOTE 1: B(1) and (2) shall be performed simultaneously. NOTE 2: Refer to AiResearch Service Bulletin TSE331-735004 dated July 16, 1973, and Aviation Specialties Service Bulletin AS55-01-1 dated July 6, 1973, for identification and location of related hardware. C. Until the actions required by paragraph B. above are performed, the following operating limitations and flight limitations (Section I, RFM) shall apply. (1) Before each takeoff with the collective full down and the rotor engaged, determine that the engine idles above 100.5% RPM with the high RPM stop. (2) At takeoff power the engine speed must not be below 99% RPM. (3) Avoid rapid collective increases under high power conditions. D. After the effective date of this AD refer to the rotorcraft flight manual for the nominal specific gravity of approved fuel types (see Section II, Specific Gravity). Operating personnel shall assure that the engine fuel control specific gravity adjustment is set properly at all times for the type of fuel being used. E. Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. F. Aircraft may be flown in accordance with FAR 21.197 to a base for performance of the inspections, maintenance, and modifications required by this AD, provided the operating limitations set forth in paragraph (c) are applied. This amendment becomes effective October 31, 1975 for all persons except those to whom it was made effective by individual airmail letters, dated September 8, 1975 which contained this amendment.
93-17-05: 93-17-05 AIRBUS INDUSTRIE: Amendment 39-8676. Docket 93-NM-35-AD. Applicability: Model A320 series airplanes; manufacturer's serial number (MSN) 005 through 012 inclusive, and MSN's 013 through 024 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the fuselage, accomplish the following: (a) Modify the web installation between frames 1 and 2 in accordance with Airbus Industrie Service Bulletin No. A320-53-1002, Revision 1, dated November 30, 1992, at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. (1) For airplanes having MSN's 005 through 012, inclusive: Within 12,000 landings after the effective date of this AD. (2) For airplanes having MSN's 013 through 024, inclusive: Within 15,000 landings after the effective date of this AD. (b) 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. (c) 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. (d) The modification shall be done in accordance with Airbus Industrie Service Bulletin No. A320-53-1002, Revision 1, dated November 30, 1992, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 5-6, 10-12, 14, 20, 25-26 1 November 30, 1992 2-4, 7-9, 13, 15-19, 21-24 Original January 17, 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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. (e) This amendment becomes effective on October 7, 1993.