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86-05-05 R1: 86-05-05 R1 GATES LEARJET CORPORATION: Amendment 39-5248 as amended by Amendment 39-5792. Applies to the following Gates Learjet models and serial numbers, equipped with a "flow through" battery vent system with the inlet located on the bottom (belly) of the airplane: MODEL SERIAL NUMBERS 23 series 003 thru 099 24, 24A, 24B, 24B-A, 100 thru 357 24C, 24D, 24D-A, 24E, 24F, 24F-A 25, 25A, 25B, 25C, 25D, 25F 003 thru 061; 066 thru 373 28 001 thru 005 29 001 thru 004 35,35A 001 thru 570; 589 thru 600 36, 36A 001 thru 053; 055 Compliance required as indicated, unless previously accomplished. To eliminate the potential for a fire and explosion within the battery, caused by leaking fuel entering the battery vent, accomplish the following within the next 200 flight hours: A. Relocate the battery inlet vent in accordance with instructions contained in Gates Learjet Corporation Service Bulletin (SB) 23/24/25-334B, dated February 19, 1987, for Models 23, 24, and 25 series airplanes; SB 28/29-24-5A, dated October 7, 1985, for Models 28 and 29 series airplanes; or SB 35/36-24-10, dated July 18, 1987, for Models 35 and 36 series airplanes; or later FAA-approved revisions. B. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. C. 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, Wichita Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Gates Learjet Corporation, P.O. Box 7707, Wichita, Kansas 67277. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region,Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas Amendment 39-5248 became effective April 11, 1986. This amendment, 39-5792, becomes effective January 19, 1988.
2016-25-08: We are superseding Airworthiness Directive (AD) 2014-13-12 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014- 13-12 required identifying the part number and serial number of each passenger oxygen container, replacing the oxygen generator manifold of any affected oxygen container with a serviceable manifold, performing an operational check of the manual mask release, and doing corrective actions if necessary. This new AD retains the requirements of AD 2014- 13-12, and requires replacing the oxygen generator manifold of any affected DAe oxygen container with a serviceable manifold. This AD was prompted by reports of silicon particles inside the oxygen generator manifolds, which had chafed from the mask hoses during installation onto the generator outlets. We are issuing this AD to address the unsafe condition on these products.
2016-24-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted [[Page 89368]] by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. This AD requires various repetitive and detailed visual inspections of the affected areas and corrective actions if necessary. This AD also provides terminating action for certain repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
2001-15-28: This amendment adopts a new airworthiness directive (AD), applicable to certain BAe Systems (Operations) Limited Model Avro 146-RJ series airplanes, that requires modification of the passenger service units. The actions specified by this AD are intended to prevent failure of the passenger service units to deliver oxygen to the passengers in the event of decompression of the airplane, which could result in injury to the passengers. This action is intended to address the identified unsafe condition.
89-03-12: 89-03-12 AIRBUS INDUSTRIE: Amendment 39-6124. Applicability: Model A310 series airplanes, as listed in Airbus Industrie Service Bulletin A310-53-2043, Revision 1, dated July 8, 1988. Compliance: Required as indicated, unless previously accomplished. To prevent separation of the rear passenge/crew door from the airplane and subsequent rapid decompression, accomplish the following: A. Prior to the accumulation of 8,000 landings or within the next 1,000 landings after the effective date of this AD, whichever occurs later, inspect frame 73A RH and LH between beams 5 and 7 in accordance with Airbus Industrie Service Bulletin A310-53-2043, Revision 1, dated July 8, 1988. 1. If cracks are detected that are less than 0.4 inch, modify the frame within the next 2,500 landings, in accordance with Airbus Industrie Service Bulletin A310-53-2038, Revision 4, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 1,250 landings until the modification is accomplished. 2. If cracks are detected that are equal to or more than 0.4 inch but less than 0.8 inch, modify the frame within the next 1,500 landings, in accordance with Airbus Industrie Service Bulletin A310-53-2038, Revision 4, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 750 landings until the modification is accomplished. 3. If cracks are detected that are equal to or more than 0.8 inch, prior to further flight, modify the frame in accordance with Airbus Industrie Service Bulletin A310-53- 2038, Revision 4, dated October 13, 1988. 4. If no cracks are detected, repeat the inspection at intervals not to exceed 4,000 landings. B. The repetitive inspections required by paragraph A., above, may be terminated following completion of the modification of the door frame structure in accordance with Airbus Service Bulletin A310-53-2038, Revision 4, dated October 13, 1988. C. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. 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 inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft CertificationOffice, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6124, AD 89-03-12) becomes effective March 7, 1989.
81-03-02: 81-03-02 DETROIT DIESEL ALLISON: Amendment 39-4026. Applies to Model 501-D13, 501-D13A, 501- D13D, 501-D13E, 501-D13H engines equipped with 1st stage turbine wheel, Part Number 6851511; 2nd stage turbine wheel, Part Numbers 6847142 and 6876892; 3rd stage turbine wheel, Part Numbers 6845883 and 6849743; and 4th stage turbine wheel, Part Number 6876468. Compliance is required as indicated. The following limits were established by manufacturer conducted tests, and analyses and are being imposed to preclude the possibility of catastrophic wheel failures which could occur subsequent to the intervals noted. The schedule for wheel removal is as follows and is a function of the wheel spline interference fit: TURBINE WHEEL CYCLIC LIMITS (Spline Fit 0.0000-0.0009T) CYCLIC LIMITS (Spline Fit 0.001-0.0025T) Stage 1 24,000 cycles 30,000 cycles Stage 2 18,000 cycles 26,000 cycles Stage 3 16,000 cycles 22,000 cycles Stage 4 18,000 cycles 26,000 cyclesIt is the operator's responsibility to obtain wheel-to-shaft spline fit data from their overhauler to determine which fit applies to their respective turbine or turbines. Only wheels that have conformed to a .001T minimum fit throughout their entire utilization history qualify for the higher cyclic limits above. NOTE: If any turbine wheel has more than the number of cycles appropriate for its retirement as shown in this table above on the effective date of this AD, it must be replaced prior to accruing 100 additional cycles. The above cyclic limits are in addition to the following existing hourly life limits which are specified in Detroit Diesel Allison Commercial Service Letter CSL-120. TURBINE WHEEL LIFE LIMIT, HOURS Stage 1 9700 Stage 2 11000 Stage 3 9900 Stage 4 11000 Upon request of the operator, an FAA maintenance inspector, subject to approval of the Chief, Engineering and Manufacturing Branch, Great Lakes Region, may permit alternate actions which provide equivalent levels of safety if the request contains substantiating data to justify them. This amendment becomes effective January 28, 1981.
64-15-06: 64-15-06 SCHEIBE-FLUGZEUGBAU: Amdt. 755 Part 507 Federal Register June 26, 1964. Applies to All Model L-Spatz 55 Gliders Up to Serial Number 755. Compliance required as indicated. Because wood deterioration and corrosion have been found in the area of the outer aileron hinge bracket which has been attributed to trapped moisture in this location, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, inspect outer aileron hinge brackets and the surrounding area for corrosion, for rigid attachment to the wing spar and for deterioration of wood and glue. (Deteriorated wood is generally softer and discolored.) (b) If any corrosion or deterioration is found or if hinge brackets are not rigidly attached to the wing spar, repair or replace as provided for in the manufacturer's Technical Information No. 1 dated January 21, 1964, or FAA approved equivalent, before further flight. (c) Within 25 hours' time in service after the effective date of this AD, drill a 1/4 inch-diameter drain hole in each side of the aileron bracket attachment rib. (Scheibe-Flugzeugbau GMBH Technical Information No. 1 dated January 21, 1964, covers this same subject.) This directive effective July 27, 1964.
2001-15-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-311 and -315 series airplanes. This action requires replacement of the door stops on the baggage bulkhead with new, improved door stops. This action is necessary to prevent the internal door on the baggage bulkhead from jamming in the closed position, precluding access to the baggage compartment, which is critical for fire fighting during flight. This action is intended to address the identified unsafe condition.
2001-15-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modifications of route segregation between the low voltage wire bundles of the fuel quantity indicating system and the high voltage wire bundles of the ground power control unit. This amendment is prompted by mandatory continuing airworthiness information from a civil airworthiness authority. The actions specified by this AD are intended to prevent injection of 115 volt alternating current (VAC) into 28 volt direct current (VDC) wire bundles, which could result in high voltage conditions within the fuel tank and the potential for damage to equipment, electrical arcing, and fuel vapor ignition on the ground. This action is intended to address the identified unsafe condition.
2001-16-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, -300F, and -400ER series airplanes equipped with General Electric Model CF6-80C2 series engines. This action requires various repetitive inspections and tests of certain fail-safe features of the thrust reverser control system; and corrective actions, if necessary. This action is necessary to ensure that the fail-safe features of the thrust reverser are fully functional and to protect against an in-flight thrust reverser deployment, which could result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2001-15-19: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS-365N3 helicopters that requires modifying the Full Authority Digital Engine Control (FADEC) software within 90 days after the effective date of this AD. This amendment is prompted by a design problem in the FADEC "power loss printed circuit board" software found during laboratory testing. The actions specified by this AD are intended to prevent loss of the FADEC one-engine-inoperative power and subsequent loss of control of the helicopter.
46-41-02: 46-41-02 BELLANCA: (Was Mandatory Note 1 of AD-773-5.) Applies to Models 14-13, 14-13-2 Serial Numbers 1061, 1063 to 1075 Inclusive. Compliance required prior to November 15, 1946. Remove the steel bushing at the aileron control column sprocket and replace with a bronze bushing. Also remove the cadmium plating for the pin (AN 395) in the area of the bushing. The sprocket should turn freely when reassembled. (Bellanca Service Bulletin No. 1 dated July 16, 1946, covers this same subject.)
2001-15-10: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B2, A300 B4, A310, A319, A320, A321, A330, and A340 series airplanes; and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (collectively called A300-600) series airplanes. That AD currently requires certain repetitive checks, and replacement of the braking dual distribution valve (BDDV) if necessary. This action requires, for certain airplanes, inspecting and/or replacing the BDDV cover. For all other airplanes, this action provides for optional termination of the repetitive checks. 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 failure of the alternate braking system, which could result in the airplane overrunning the end of the runway during landing.
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.
2016-22-16: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, and 702), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that wear and possible leakage of the high-pressure seal in the cylinder of the No. 3 hydraulic system reservoir could occur and cause high hydraulic fluid temperature and/or prevent the system from reaching normal operating pressure. This AD requires repetitive operational checks for wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-20-13: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 airplanes, excluding Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes; all Model 757-200, -200PF, -200CB, and -300 series airplanes; and all Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of latently failed motor-operated valve (MOV) actuators of the fuel shutoff valves. This AD requires replacing certain MOV actuators of the fuel shutoff valves for the left and right engines (on certain airplanes) and of the auxiliary power unit (APU) fuel shutoff valve (on Model 757 and Model 767 airplanes); and revising the maintenance or inspection program to incorporate certain airworthiness limitations (AWLs). We are issuing this AD to address the unsafe condition on these products.