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2017-07-03: This document corrects an error and correctly adds the AD as an amendment to 14 CFR 39.13. Although no other part of the preamble or regulatory information has been corrected, we are publishing the entire rule in the Federal Register.
2010-25-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: As a result of the fatigue-testing programme on the Jetstream fatigue test specimen, it has been identified that failure of the undercarriage jack mounting shaft assembly can occur. This condition, if not corrected, could lead to a Main Landing Gear (MLG) collapse on the ground or during landing and consequently damage to the aeroplane or injury to the occupants. We are issuing this AD to require actions to correct the unsafe condition on these products.
87-25-04: 87-25-04 ROLLS-ROYCE: Amendment 39-5766. Applies to Rolls-Royce plc (R-R) RB211-535C and -535E4 series turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent low pressure (LP) fuel filter to high pressure (HP) pump tube frettage and cracking that can lead to fuel leaks and substantial fuel quantity loss, accomplish the following: (a) For the RB211-535E4 engines installed on Boeing 757 aircraft and operated in any of the following configurations: (1) the fuel Quantity Indication System (FQIS) inoperative with under the provisions specified in the Master Minimum Equipment List (MMEL), Item 28-41-1; (2) with one of the Fuel Quantity Processor (FQP) Channels inoperative under the provisions specified in the MMEL Item 28-41-2; (3) with both Flight Management Computer (FMC) Systems inoperative under the provisions specified in the MMEL, Item 34-61-1; or (4) with the FQIS functional, both FQP Channels functional, and at least one FMCSystem functional, but operating without the provisions of Boeing Operations Manual Bulletin (OMB) Number 87-7, dated August 20, 1987, accomplish the following: (1) Replace fuel tube Part Number (P/N) UL14975, prior to further flight, with the new fuel tube configuration, P/N UL16692, in accordance with the Accomplishment Instructions contained in R-R Service Bulletin (SB) RB.211-73-8195, dated May 2, 1986. (2) Visually inspect fuel tube P/N UL16692 for frettage each day of operation, in accordance with paragraph D(2) "RB211-535E4 engines - L.P. fuel tubes" of the Accomplishment Instructions contained in R-R SB RB.211-73-8438, Revision 1, dated July 31, 1987, until installation of clips, R-R P/N 1010792, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8457, Revision 1, dated August 7, 1987. (3) Remove from service and replace with serviceable parts, prior to further flight, fuel tube assemblies found to be cracked or fretted. (b)For the RB211-535C engines installed on Boeing 757 aircraft and operated in any of the following configurations: (1) with the Fuel Quantity Indication System (FQIS) inoperative under the provisions specified in the MMEL, Item 28-41-1; (2) with one of the Fuel Quantity Processor (FQP) Channels inoperative under the provisions specified in the MMEL, Item 28-41-2; (3) with both Flight Management Computer (FMC) Systems inoperative under the provisions specified in the MMEL, Item 34-61-1; or (4) with the FQIS functional, both FQP Channels functional, and at least one FMC System functional, but operating without the provisions of Boeing Operations Manual Bulletin (OMB) Number 87-7, dated August 20, 1987, accomplish the following: (1) Replace fuel tube P/N LK78017, prior to further flight, with the new fuel tube configuration, P/N UL22067, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8502, dated August 28, 1987. (2) Visually inspect fuel tubeP/N UL22067 for frettage each day of operation, in accordance with paragraph D(2) "RB211-535C engines - L.P. fuel tubes" of the Accomplishment Instructions contained in R-R SB RB.211-73-8438, Revision 1, dated July 31, 1987, until installation of clip, R-R P/N 1011161, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8534, dated September 18, 1987. (3) Remove from service and replace with serviceable parts, prior to further flight, fuel tube assemblies found to be cracked or fretted. (c) For the RB211-535E4 engines installed on Boeing 757 aircraft operated with the FQIS functional, both FQP Channels functional, at least one FMC System functional, and in accordance with the provisions of Boeing OMB Number 87-7, dated August 20, 1987, accomplish the following: (1) Dye penetrant inspect (red or fluorescent dye) fuel tube P/N UL14975 for cracks not later than the next "A" check after the effective date of this AD, in accordance with paragraph D(1) of the Accomplishment Instructions contained in R-R SB RB.211-73-8438, Revision 1, dated July 31, 1987. (2) Reinspect for cracks in accordance with the requirements of paragraph (c)(1) above, thereafter, at intervals not to exceed 1,000 hours in service, until replacement of fuel tube, P/N UL14975, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8195. (3) Visually inspect fuel tubes P/N UL14975 and UL16692 for frettage, not later than the next "A" check after the effective date of this AD, in accordance with paragraph D(2) "RB211-535E4 engines - L.P. fuel tubes" of the Accomplishment Instructions contained in R-R SB RB.211-73-8438, Revision 1, dated July 31, 1987. Replace clips, R-R P/N 3504226 or R-R P/N 3504225, removed during the inspection, with new clips, R-R P/N 3504226 or R-R P/N 3504225, or with clips, R-R P/N 1010792, prior to reinstallation. (4) Reinspect for frettage in accordance with the requirements of paragraph (c)(3) above, thereafter, at intervals not to exceed "A" check, fuel tubes not incorporating clips, R-R P/N 1010792, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8457, Revision 1, dated August 7, 1987, until incorporation of clips, R-R P/N 1010792. (5) Remove from service and replace with serviceable parts, prior to further flight, fuel tube assemblies found to be cracked or fretted. (d) For the RB211-535C engines installed on Boeing 757 aircraft operated with the FQIS functional, both FQP Channels functional, at least one FMC System functional, and in accordance with the provisions of Boeing OMB Number 87-7, dated August 20, 1987, accomplish the following: (1) Dye penetrant inspect (red or fluorescent dye) fuel tube P/N LK78017 for cracks not later than the next "A" check after the effective date of this AD, in accordance with paragraph D(1) of the Accomplishment Instructions contained in R-R SB RB.211-73-8438, Revision 1, dated July31, 1987. (2) Reinspect for cracks in accordance with the requirements of paragraph (d)(1) above, thereafter, at intervals not to exceed "A" check, until replacement of fuel tube, P/N UL78017, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8502, dated August 28, 1987. (3) Visually inspect fuel tubes P/N UL78017 and P/N UL22067 for frettage not later than the next "A" check after the effective date of this AD, in accordance with paragraph D(2) "RB211-535C engines - L.P. fuel tubes" of the Accomplishment Instructions contained in R-R SB RB.211-73-8438, Revision 1, dated July 31, 1987. Replace clip, R-R P/N 3504234 or R-R P/N 3504233, removed during the inspection, with new clip, R-R P/N 3504234 or R-R P/N 3504233, or with clip R-R P/N 1011161, prior to reinstallation. (4) Reinspect for frettage in accordance with the requirements of paragraph (d) (3) above, thereafter, at intervals not to exceed "A" check, fuel tubes not incorporatingclip, R-R P/N 1011161, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8534, dated September 18, 1987, until incorporation of clip, R-R P/N 1011161. (5) Remove from service and replace with serviceable parts, prior to further flight, fuel tube assemblies found to be cracked or fretted. (e) For RB211-535E4 engines, accomplish the following on or before March 31, 1988: (1) Replace fuel tube P/N UL14975 with the new fuel tube configuration, P/N UL16692, in accordance with the Accomplishment Instructions, contained in R-R SB RB.211-73-8195, dated May 2, 1986. (2) Replace R-R P/N 3504226 or R-R P/N 3504225 clips with R-R P/N 1010792 clips on fuel tube P/N UL16692, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8457, Revision 1, dated August 7, 1987. (f) For RB211-535C engines, accomplish the following on or before March 31, 1988: (1) Replace fuel tube P/N LK78017 with the new fuel tube configuration, P/N UL22067, in accordance with Accomplishment Instructions contained in R-R SB RB.211-73-8502, dated August 28, 1987. (2) Replace R-R P/N 3504234 or R-R P/N 3504233 clip with R-R P/N 1011161 clip on fuel tube P/N UL22067, in accordance with the Accomplishment Instructions contained in R-R SB RB.211-73-8534, dated September 18, 1987. NOTE: Accomplishment of the requirements of R-R SB RB211-72-7437 (interim clip configuration) is not considered an alternative to the requirements of R-R SB RB.211-73-8457 or SB RB.211-73-8534. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submissionof substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance times specified in this AD. The Rolls-Royce SB's identified and described in this document are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the engine manufacturer's SB's may obtain copies upon request to Rolls-Royce plc, Technical Publication Department, P.O. Box 31, Derby DE2 8BJ, England. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 87-ANE-34, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on December 8, 1987.
2001-22-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series airplanes, that requires modifying the oxygen flow control valve. This action is necessary to ensure that proper oxygen flow will be available to passengers when needed. This action is intended to address the identified unsafe condition.
2017-07-10: We are adopting a new airworthiness directive (AD) for certain American Champion Aircraft Corp. Model 8KCAB airplanes. This AD requires fabrication and installation of a placard to prohibit aerobatic flight, inspection of the aileron hinge rib and support, and a reporting requirement of the inspection results to the FAA. This AD was prompted by a report of a cracked hinge support and cracked hinge ribs, which resulted in partial loss of control with the aileron binding against the cove. We are issuing this AD to correct the unsafe condition on these products.
2001-22-10: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 50, Mystere-Falcon 900, and Falcon 900EX series airplanes, that requires revising the Emergency Procedures and Abnormal Procedures sections of the airplane flight manual to advise the flightcrew to immediately don oxygen masks in the event of significant pressurization or oxygen level changes. The actions specified by this AD are intended to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in their inability to continue to control the airplane. This action is intended to address the identified unsafe condition.
66-05-05: 66-05-05 PRATT & WHITNEY: Amdt. 39-195 Part 39 Federal Register February 18, 1966. Applies to Models JT3D-1, JT3D-1-MC6, and JT3D-1-MC7 Turbofan Engines. Compliance required as indicated. To prevent failure of the second stage compressor rotor disc, accomplish the following: (a) Inspect second stage compressor rotor disc, P/N 421602, with less than 5,000 cycles on the effective date of this AD in accordance with (d) before the accumulation of 5,050 cycles and thereafter at intervals not to exceed 100 hours' time in service from the last inspection until the installation of rotor disc, P/N 405702, 457802, or 571202. (b) Inspect second stage compressor rotor disc, P/N 421602, with 5,000 or more cycles on the effective date of this AD that have been inspected using the fluorescent penetrant inspection procedures outlined in Pratt & Whitney Aircraft JT3D Overhaul Manual and the visual inspection procedures contained in Pratt & Whitney Aircraft letter dated June 15,1965, within the last 700 hours' time in service before the effective date of this AD in accordance with (d) before the accumulation of 750 hours' time in service since the fluorescent penetrant and visual inspection, and at intervals not to exceed 100 hours' time in service from the last inspection until the installation of rotor disc, P/N 405702, 457802, or 571202. (c) Inspect second stage compressor rotor disc, P/N 421602, with 5,000 or more cycles on the effective date of this AD that have not been inspected using the fluorescent penetrant inspection procedures outlined in Pratt & Whitney Aircraft JT3D Overhaul Manual and the visual inspection procedures contained in Pratt & Whitney Aircraft letter dated June 15, 1965, within the last 700 hours' time in service before the effective date of this AD in accordance with (d) within the next 50 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 100 hours' time in service from the last inspection until the installation of rotor disc, P/N 405702, 457802, or 571202. (d) Inspect for cracks front and rear sides of the inner portion of second stage compressor rotor disc web visible through the number one hub bore, using a strong light and a glass of at least three power or an FAA- approved equivalent inspection procedure. If any indication of a crack is found, remove the engine before further flight and disassemble for confirmation of the crack. If no cracks are found, the engine may be returned to service. Replace any cracked disc before further flight. (e) Remove from service second stage compressor rotor disc, P/N 421602, before the accumulation of 16,000 hours' time in service. (f) Remove from service second stage compressor rotor disc, P/N 571202 (which is a disc, P/N 421602, that has been modified by Pratt & Whitney Aircraft), before the accumulation of 16,000 hours' time in service as P/N 421602 and P/N 571202 combined. (g) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA maintenance inspector, may be calculated by dividing each second stage compressor rotor disc's hours' time in service by the operator's fleet average time per flight (involving an engine operating sequence, consisting of engine starting, takeoff operation, landing, and engine shutdown) for air planes equipped with Pratt & Whitney Model JT3D-1 Series turbofan engines. (h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiatingdata to justify the increase for that operator. (Pratt & Whitney Aircraft telegram to operators of JT3D-1, JT3D-1-MC6 and JT3D-1-MC7 turbofan engines dated December 10, 1965, pertains to this subject.) This directive effective February 18, 1966.
78-20-05 R4: 78-20-05 R4 SIKORSKY AIRCRAFT: Amendment 39-3305 as amended by Amendment 39-3425 and Amendment 39-3444 and 39-3838 is further amended by Amendment 39-4648. Applies to S-61 series helicopters certificated in all categories, including military counterparts, equipped with main rotor P/N S6112-23025-1 spindles (S6112-23027-006 spindle assemblies) and S6110-23325 series spindles (S6110-23327 series spindle assemblies). Compliance required as indicated. To preclude the possibility of failure of main rotor spindles, accomplish the following. 1. Within the next 20 hours' time in service, unless already accomplished within the last 50 hours' time in service, after the effective date of this amendment, and thereafter at intervals not to exceed 70 hours time in service, conduct ultrasonic inspections of all main rotor P/N S6112-23025-1 spindles (S6112-23027-006 spindle assemblies) and S6110-23325 series spindles (S6110-23327 series spindle assemblies), (plated and unplated), with 70 or more hours time in service, in accordance with the inspection method of Sikorsky Service Bulletin No. 61B10-33F, or an equivalent method approved by the Manager, Boston Aircraft Certification Branch, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. 2. If a crack is found during the above inspections, replace the cracked spindle with a new spindle or a serviceable spindle prior to further flight. 3. Report in writing any cracks found during the above inspections to the Manager, Boston Aircraft Certification Branch, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Each report must include the length and location of the cracks and total time in service of the spindle (reporting approved by the Office of Management and Budget under OMB No. 04-R0174). The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to United Technologies Corporation, Sikorsky Aircraft, North Main Street, Stratford, Connecticut 06601, Attn: S-61 Commercial Product Support Department. These documents also may be examined in the Office of the Regional Counsel, Federal Aviation Administration, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas 76106. Amendment 39-3305 became effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated July 31, 1978. Amendment 39-3425 became effective upon publication in the FEDERAL REGISTER. Amendment 39-3444 became effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated March 9, 1979. Amendment 39-3838 became effective June30, 1980. This Amendment 39-4648 becomes effective May 25, 1983.
93-07-06: 93-07-06 DE HAVILLAND, INC.: Amendment 39-8538. Docket 92-NM-120-AD. Applicability: Model DHC-8-100 and DHC-8-300 series airplanes; serial numbers 3 through 216, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 50 hours time-in-service after the effective date of this AD, inspect the inboard flaps for free play and roller rattle, in accordance with the Accomplishment Instructions, Paragraph A., of de Havilland Service Bulletin S.B. 8-27-53, dated May 11, 1990. NOTE: Evidence of free play and roller rattle, as defined in the service bulletin, is a desirable condition. (b) If free play and roller rattle are found as a result of the inspection required by paragraph (a) of this AD: Within 3,000 hours time-in-service or one year after the effective date of this AD, whichever occurs first, re-rig the flap system, in accordance with the Accomplishment Instructions, Paragraph B., of de Havilland Service Bulletin S.B. 8-27-53, dated May 11, 1990. After accomplishment of this procedure, no further action is required by this AD. (c) If free play and roller rattle are not found as a result of the inspection required by paragraph (a) of this AD: Within 250 hours time-in-service after the effective date of this AD, re-rig the flap system, in accordance with the Accomplishment Instructions, Paragraph B., of de Havilland Service Bulletin S.B. 8-27-53, dated May 11, 1990. (1) If the airplane has accumulated more than 5,000 landings when the flap system is re-rigged in accordance with this paragraph: Within 250 hours time-in-service after the effective date of this AD, begin repetitive inspections of the structurally significant items (SSI) in the vicinity of the re-rigged inner flap (identified in the following table) and repeat at the intervals specified in the applicable FAA-approvedmaintenance program. AIRPLANE MAINTENANCE PROGRAM DHC SSI TASK IDENTIFICATION NO. DHC-8 Series 100, All Models DHC-8 Series 100 Maintenance Program PSM 1-8-7, Part 2, Airworthiness Limitations Listings WF01, WF02, WF03, WF05, WF06, WF07, WF08, WF09, WF10, WF28, WF29, WF30, and WF31 DHC-8 Series 300, Model 301 DHC-8 Series 300 Maintenance Program PSM 1-83-27, Part 2, Airworthiness Limitations Listings WF01, WF02, WF03, WF05, WF06, WF07, WF08, WF09, WF10, WF28, WF29, WF30, and WF31 (2) If the airplane has accumulated 5,000 or fewer landings when the flap system is re-rigged in accordance with this paragraph, no further action is required by this AD. (d) 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, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (e) 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. (f) The inspection and re-rig shall be done in accordance with de Havilland Service Bulletin S.B. 8-27-53, dated May 11, 1990. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 14, 1993.
88-20-06: 88-20-06 MITSUBISHI HEAVY INDUSTRIES, LTD. (formerly Nihon Aeroplane Manufacturing Company (NAMC): Amendment 39-6023. Applies to all Model YS-11/-11A series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the vertical stabilizer front spar-to-fuselage fittings, accomplish the following: A. Within 600 hours time-in-service after the effective date of this AD or within 4 months after the effective date of this AD, whichever occurs first, visually inspect the vertical stabilizer front spar fuselage side fittings, Part Number (P/N) 01-38101-11/-12, for cracked lugs, in accordance with Paragraph 2., "Instructions," of NAMC YS-11 Alert Service Bulletin (SB) A53-71, dated May 23, 1986. Repeat this inspection at intervals not to exceed 1,000 hours time-in-service. B. If any crack is found in fitting P/N 01-38101-11/-12 during the inspections required by paragraph A., above: Prior to further flight, remove that fitting from the airplane and accomplish the inspections, corrosion treatment, and replacement of parts, as necessary, in accordance with Paragraph 2., "Instructions," of NAMC YS-11 Service Bulletin 53-70, dated May 23, 1986. Once this has been accomplished, the required repetitive inspections may be discontinued. C. If no cracking is found in fitting P/N 01-38101-11/-12 during the inspections required by paragraph A., above: Within 6,000 hours time-in-service after the effective date of this AD, or by January 1, 1990, whichever occurs first, accomplish the inspections, corrosion treatment, and replacement of parts, as necessary, in accordance with paragraph 2., "Instructions," of NAMC YS-11 Service Bulletin 53-70, dated May 23, 1986. Once this has been accomplished, the required repetitive inspections may be discontinued. D. The repetitive inspections required by paragraph A., above, may be terminated if the vertical stabilizer front spar fuselageside fitting P/N 01-38101-11/-12 had been given corrosion prevent treatment after September 1, 1985, or once it has been replaced by fitting P/N 01-38101-21/-22. E. 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, Los Angeles Aircraft Certification Office, 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, Los Angeles Aircraft Certification Office. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of 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 the Mitsubishi Heavy Industries, Ltd., Nagoya AircraftWorks, YS-11 Technical Publications, Service Department, 10, Oye-Cho, Minato-ku, Nagoya, Japan. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 E. Spring Street, Long Beach, California. This amendment, 39-6023, supersedes AD 86-03-05, Amendment 39-5233. This amendment, 39-6023, becomes effective November 1, 1988.