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88-17-09 R1: 88-17-09 R1 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC) (HUGHES HELICOPTERS, INC.): Amendment 39-5964 as revised by Amendment 39-6400. Docket No. 88-ASW-24. Applicability: Model 369D, E, F, and FF helicopters, certificated in any category, which have tail rotor transmission/tail boom extension mounting studs, Part Number (P/N) MS51992A803-13 or -14, installed. Compliance: Required as indicated, unless already accomplished. (a) To prevent failure of the tail rotor transmission mounting studs (P/N MS51992A803-13 or -14) on MDHC Model 369 D/E helicopters, accomplish the following: (1) Prior to further flight after the effective date of this AD, conduct an initial inspection of the tail rotor transmission attachment to the tail boom casting for any indications of relative motion between the parts in accordance with MDHC Service Information Notice (SIN) DN-151/EN-39/FN-28, Part I, paragraphs a, b, c, d, and e, dated October 10, 1987. (2) Within the next 25hours' time in service after the effective date of this amended AD, and at intervals not to exceed 25 hours' time in service from the last check, conduct a check for security in accordance with MDHC SIN DN-151/EN-39/FN-28, Part II, paragraph a, dated October 10, 1987. The checks required by this paragraph may be performed by the pilot and must be recorded in accordance with FAR Section 43.9. (3) If there are indications of relative motion between the tail rotor transmission and the tail boom casting found by the inspection and check of paragraphs (a)(1) and (a)(2), prior to further flight, remove the tail rotor transmission and replace all four mounting studs in accordance with MDHC SIN DN-151/EN-39/FN-28, Part III, paragraphs a thru j, dated October 10, 1987. (4) At intervals not to exceed 100 hours' time in service from the last inspection after the effective date of this AD, conduct repetitive inspections of the torque of each mounting nut and reapply torque stripe paint in accordance with MDHC SIN DN-151/EN-39/FN- 28, Part IV, paragraphs a and b, dated October 10, 1987. (b) To prevent failure of the tail boom extension mounting studs (P/N MS51992A803-13 or -14) on MDHC Model 369 F/FF helicopters, accomplish the following: (1) Prior to further flight after the effective date of this AD, conduct an initial inspection of the tail boom extension attachment to the tail boom casting for any indications of relative motion between the parts in accordance with MDHC SIN DN-151/EN- 39/FN-28, Part I, paragraphs a, b, c, d, and e, dated October 10, 1987. (2) Within the next 25 hours' time in service after the effective date of this amended AD, and at intervals not to exceed 25 hours' time in service from the last check, conduct a check of the tail boom extension installation for security in accordance with MDHC SIN DN- 151/EN-39/FN-28, Part II, paragraph a, dated October 10, 1987. The checks required by this paragraph may be performed by the pilot and must be recorded in accordance with FAR Section 43.9. (3) If there are indications of relative motion of fretting products between the tail boom casting and the tail boom extension found by the above inspections or checks, prior to further flight, remove tail boom extension and replace all four studs in accordance with MDHC SIN DN-151/EN-39/FN-28, Part III, paragraphs b thru j, dated October 10, 1987. (4) At intervals not to exceed 100 hours' time in service from the last inspection after the effective date of this AD, conduct repetitive inspections of the torque of each mounting nut and reapply torque stripe paint in accordance with MDHC SIN DN-151/EN-39/FN- 28, Part IV, paragraphs a and b, dated October 10, 1987. (c) An alternate means of compliance which provides an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, P.O. Box 92007, Worldway Postal Center, Los Angeles, CA 90009-2007. (d) In accordance with Sections 21.197 and 21.199, the helicopters may be flown to a base where compliance may be accomplished. These inspections and check procedures shall be done in accordance with MDHC Mandatory SIN DN-151/EN-39/FN-28, dated October 10, 1987. 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 MDHC Technical Publications, Building 543/D214, McDonnell Douglas Helicopter Company, 5000 E. McDowell Road, Mesa, Arizona 85205-9797, telephone (602) 891-6484. A copy may also be inspected at the Office of the Assistant Chief Counsel, Federal Aviation Administration, 4400 Blue Mound Road, Room 158, Building 3B, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street NW, Room 8401, Washington, D.C. This AD revises Amendment 39-5964 (53 FR 30023; August 10, 1988), AD 88-17-09, which became effective on August 24, 1988. This amendment (39-6400, AD 88-17-09 R1) becomes effective on December 26, 1989.
2023-10-08: The FAA is superseding Airworthiness Directive (AD) 2022-25- 16, which applied to all ATR--GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes. AD 2022-25-16 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2022-25-16 and 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 (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2022-27-04: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, and PW1525G-3 model turbofan engines. This AD was prompted by an uncommanded dual engine shutdown upon landing, resulting in compromised braking capability due to the loss of engine power and hydraulic systems. This AD requires removal from service of certain electronic engine control (EEC) full authority digital engine control (FADEC) software versions and replacement with updated software. The FAA is issuing this AD to address the unsafe condition on these products.
2016-25-23: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-115 and -132 airplanes, and Model A320-214, -232, and -233 airplanes. This AD requires revising the airplane flight manual (AFM) to include information that introduces a fuel limitation for certain types of fuel and a fuel gravity feed ceiling procedure for airplanes equipped with jet pumps. This AD was prompted by a report indicating that certain modified airplanes do not have electrical ground wires on the fuel level sensing control unit (FLSCU), which adversely affects gravity feeding operation. We are issuing this AD to address the unsafe condition on these products.
2001-15-26: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model Astra SPX series airplanes. This action requires a one-time inspection to detect insufficient clearance on the electrical wire bundles routed next to the pilot and copilot air data reference and reversionary switching panels; and corrective action, if necessary. This action is necessary to prevent chafing of the electrical wire bundles, which could result in loss of flight-critical displays or system functions, and potential fire. This action is intended to address the identified unsafe condition.
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.