Results
2010-25-05: 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: Due to manufacturing problems of BR700-710 HP stage 1 and 2 turbine discs it was necessary to re-calculate the Declared Safe Cyclic Life (DSCL) for all BR700-710 HP turbine discs. The analysis concluded that it is required to reduce the approved life limits for the HP turbine disc part numbers that are listed in Table 1 and Table 2 of this AD (MCAI). Exceeding the revised approved life limits could potentially result in non-contained disc failure. We are issuing this AD to prevent-failure of the high-pressure turbine (HPT) stage 1 and stage 2 discs, uncontained engine failure, and damage to the airplane.
2001-22-11: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-600, -700, and -800 series airplanes, that currently requires an inspection of the power distribution panels (PDP) to verify proper installation of the power feeder terminals and associated hardware, and corrective actions, if necessary. The existing AD also requires repetitive torque checks of the terminal attachment screws. This amendment adds a requirement for repetitive replacement of the PDP rigid bus assembly with a new assembly and provides an optional terminating action for the repetitive torque checks and the repetitive replacement of the PDP rigid bus assembly. This amendment is prompted by reports of loss of electrical power from the engine-driven generators or the auxiliary power unit due to overheating, melting, and subsequent failure of the power feeder terminals at the PDPs. The actions specified by this AD are intended to prevent such conditions, which could result in increased risk of fire and the loss of electrical power from the associated alternating current power source.
2001-22-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes; and certain Boeing Model 747, 757, 767, and 777 series airplanes; that requires replacing the rudder pedal pushrod fasteners for both the captain's and first officer's pedal assemblies with new, improved fasteners. This action is necessary to prevent loss of rudder control due to improperly torqued fasteners that connect the pushrod to the rudder pedal assembly, which could result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
47-14-01: 47-14-01 BELLANCA: (Was Mandatory Note 5 of AD-773-5.) Applies to Models 14- 13, 14-13-2 Serial Numbers 1060 to 1409, Inclusive. Compliance required prior to June 1, 1947. Replace the aluminum alloy inboard flap hinge brackets with X4130 steel brackets, Bellanca P/N 7998-1. Bellanca Service Bulletin No. 7 dated January 14, 1947, covers this same subject.)
2023-01-08: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies GmbH TAE 125-02-99 and TAE 125-02-114 model reciprocating engines. This AD was prompted by manufacturer reports of fractured main bearing studs. This AD requires the removal and replacement of certain main bearing studs. The FAA is issuing this AD to address the unsafe condition on these products.
2017-09-06: We are superseding Airworthiness Directive (AD) 2015-15-03 for all General Electric Company (GE) GEnx turbofan engine models. AD 2015- 15-03 precluded the use of certain electronic engine control (EEC) full authority digital engine control (FADEC) software on GEnx turbofan engines. This AD requires removing a specific part and replacing it with a part eligible for installation and specifying the EEC FADEC software version for the affected GEnx turbofan engines. This AD was prompted by GE implementing final design changes that remove the unsafe condition. We are issuing this AD to correct the unsafe condition on these products.
2001-22-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that requires repetitive eddy current inspections for cracking of the main landing gear (MLG) main fittings, and replacement with a new or serviceable MLG, if necessary. This action also requires servicing the MLG shock struts; inspecting the MLG shock struts for nitrogen pressure, visible chrome dimension, and oil leakage; and performing corrective actions, if necessary. The actions specified by this AD are intended to prevent failure of the MLG main fitting, which could result in collapse of the MLG upon landing. This action is intended to address the identified unsafe condition.
2017-08-12: We are adopting a new airworthiness directive (AD) for GROB Aircraft AG Models GROB G 109 and GROB G 109B gliders. 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 broken pivots of the tail wheel mounting bracket resulting from corrosion and damage due to wear. We are issuing this AD to require actions to address the unsafe condition on these products.
2001-22-08: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 series airplanes, that requires replacing the main landing gear (MLG) torque link dampers with modified and reidentified dampers. This action is necessary to prevent degradation of the dampers, which could result in MLG high amplitude oscillation in a lateral torsional mode, and consequent MLG damage or separation of the MLG from the airplane. This action is intended to address the identified unsafe condition.
2001-21-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires, for certain airplanes, revising the Airplane Flight Manual, and, for all airplanes, performing repetitive inspections for wear or damage of the inlet check valves and inlet adapters of the override/jettison pumps, and corrective actions, if necessary. This amendment applies to fewer airplanes than the existing AD and requires rework of certain components, which ends the repetitive inspection requirement. These actions are necessary to ensure that the flight crew is advised of the hazards of dry operation of the override/jettison pumps of the center wing fuel tank, and to prevent wear or damage to the inlet check valves and inlet adapters of the override/jettison pumps, which could result in a fire or explosion in the fuel tank during dry (no fuel) operation. This action is intended to address the identified unsafe condition. \n\n\tTheincorporation by reference of Boeing Alert Service Bulletin 747-28A2212, Revision 2, dated May 14, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of August 24, 1998 (63 FR 42210, August 7, 1998).
2017-08-09: We are adopting a new airworthiness directive (AD) for DG Flugzeugbau GmbH Model DG-500MB gliders that are equipped with a Solo 2625 02 engine modified with a fuel injection system following the instructions of Solo Kleinmotoren GmbH Technische Mitteilung (TM)/ Service Bulletin (SB) 4600-3 ``Fuel Injection System'' and identified as Solo 2625 02i. 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 possible in-flight engine shut-down and engine fire due to failure of the connecting stud for the two fuel injector mounts of the engine redundancy system. We are issuing this AD to require actions to address the unsafe condition on these products.
64-13-04: 64-13-04 WALTER KIDDE: Amdt. 749 Part 507 Federal Register June 18, 1964. Applies to Aircraft Incorporating Inflatable Escape Slides or Life Rafts Utilizing Walter Kidde Series 1 Actuating Valve P/N's 891771, 891178, 891178-01, 890881-01, 890683, and 890881 Which Have Had Their Seat Assemblies, Walter Kidde P/N 801906 Replaced or Modified With Parts Purchased Since April 1, 1963, and All Series 2 Actuating Valve P/N's 891771-01, 891178-02, 890881-02. Compliance required as indicated. During recent demonstrations of inflatable escape slides and life rafts, certain Walter Kidde inflation valves did not provide adequate inflation and required excessive pull forces to actuate the valve. Effective July 1, 1964, all Walter Kidde valves specified herein which are used in escape slides or life rafts installed in civil aircraft shall be modified as follows or in accordance with an FAA Western Region, Aircraft Engineering Division, approved equivalent: (a) Remove seat assembly Walter Kidde P/N 801906 and install a new nylon seat assembly Walter Kidde P/N 843045. (b) Functionally test the valve by installing it, along with anti-recoil fitting Walter Kidde P/N 6531, on an appropriately charged bottle and discharging the bottle. During this functional check, the pull load required to actuate the valve is to be determined and is not to exceed 30 pounds. Do not install valves which require a pull in excess of 30 pounds. (NOTE: If Walter Kidde P/N 6531 anti-recoil fitting is not available, the bottle should be adequately constrained.) (c) Reidentify the reworked valves in accordance with Walter Kidde Service Bulletin No. 168 dated May 8, 1964. NOTE: Walter Kidde valve P/N's 891771, 891178, 891178-01, 890881-01, 890683 and 890881 which have not had seat assemblies replaced or modified with parts purchased since April 1, 1963, are not affected by the provisions of this AD. (Walter Kidde Company Service Bulletin No. 168 dated May 8, 1964, withAddendum No. 1 dated May 15, 1964, and Addendum No. 2 dated June 2, 1964, and Boeing Alert Service Bulletins Nos. 2000 dated May 11, 1964, and 2000A dated May 15, 1964, cover this same subject. Note that where the applicability specified in these Bulletins is not the same as that in the AD, the applicability specified in the AD applies.) This directive effective June 18, 1964.
2001-22-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3 series airplanes, that requires an inspection to find discrepancies of the hydraulic pipelines to the 7P panel and adjacent electrical wiring harnesses, and corrective action, if necessary. This action is necessary to find and fix such discrepancies, which could result in electrical arcing between the hydraulic lines and adjacent wiring, and a potential fire. This action is intended to address the identified unsafe condition.
92-03-11 R1: 92-03-11 R1 SAAB-SCANIA: Amendment 39-8248. Docket No. 92-NM-73-AD. Revises AD 92-03- 11, Amendment 39-8166. Applicability: Model SF-340A series airplanes, serial numbers 004 through 021, 023 through 028, 030 through 035, 037 through 049, and 051 through 159; and Model SAAB 340B, serial numbers 160 through 169, and 171 through 219; equipped with a forward or aft lavatory; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a possible wire overload and resultant smoke and/or fire in the cabin, accomplish the following: (a) Within 3 months after the effective date of this AD, replace the lavatory circuit breaker, 1MG (1OA size), with circuit breaker, 1MG (7.5A size), and perform an operational test, in accordance with SAAB-SCANIA Service Bulletin 340-25-181, dated March 7, 1991. (b) An alternative method 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, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, 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 replacement shall be done in accordance with SAAB-SCANIA Service Bulletin 25- 181, dated March 7, 1991. This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of March 16, 1992 (57 FR 4847, February 10, 1992). Copies may be obtained from SAAB-SCANIA AB, Product Support, S-581.88, Link ping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on May 6, 1992.
2025-12-03: The FAA is superseding Airworthiness Directive (AD) 2023-09- 06, which applied to all CFM International, S.A. Model (CFM) LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP- 1A35A (LEAP-1A) engines. AD 2023-09-06 required replacement of certain high-pressure turbine (HPT) rotor stage 1 disks (HPT stage 1 disks), forward outer seals, and compressor rotor stages 6-10 spools. AD 2023- 09-06 also prohibited installation of an HPT stage 1 disk, forward outer seal, or compressor rotor stages 6-10 spool that has a part number and serial number identified in the service information onto any engine. Since the FAA issued AD 2023-09-06, the manufacturer identified additional affected parts that were manufactured from material suspected to have reduced material properties due to iron inclusion, which prompted this AD. This AD retains the requirements to replace certain HPT stage 1 disks, forward outer seals, and compressor rotor stages 6-10 spools and expands the applicability to include additional affected parts manufactured from the same material suspected to have reduced material properties due to iron inclusion. The FAA is issuing this AD to address the unsafe condition on these products.
96-09-16: This amendment adopts a new airworthiness directive (AD) that applies to all Fairchild Aircraft SA226 and SA227 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
2023-02-04: The FAA is adopting a new airworthiness directive (AD) for certain Mooney International Corporation Model M20C, M20D, M20E, M20F, and M20G airplanes. This AD was prompted by reports of the hybrid material elevator balance weight cracking. This AD requires inspecting to determine whether a certain elevator balance weight is installed. If installed, this AD requires inspecting each affected elevator balance weight for corrosion and cracking, and depending on the findings, either replacing each affected elevator balance weight with a non- hybrid (lead) elevator balance weight or repetitively inspecting each affected elevator balance weight. This AD also prohibits the installation of an affected elevator balance weight on any airplane. The FAA is issuing this AD to address the unsafe condition on these products.
2001-22-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 B2 and B4 series airplanes. This action requires determining the part and amendment numbers of the variable lever arm (VLA) of the rudder control system to verify the parts were installed using the correct standard, and corrective actions, if necessary. This action is necessary to prevent failure of both spring boxes of the VLA due to corrosion damage, which could result in loss of rudder control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2001-22-01: This amendment supersedes an existing airworthiness directive (AD) for Enstrom Helicopter Corporation (EHC) Model F-28, F-28A, and 280 helicopters. That AD currently requires inspecting the main rotor shaft (shaft) for a crack or other evidence of damage until appropriately modifying or replacing the shaft with an airworthy shaft at specified time intervals. This amendment adds EHC Model F-28C, F-28F, 280C, 280F, and 280FX helicopters and establishes life limits after which all unmodified shafts must be retired. This amendment requires determining the radius of the shaft fillet, certain visual and dye-penetrant inspections before further flight, and replacing certain main rotor transmissions. This amendment is prompted by the failure of a shaft on an EHC Model F-28A helicopter due to a fatigue crack. The actions specified by this AD are intended to prevent shaft failure and subsequent loss of control of the helicopter.
2017-07-07: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. This AD requires repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
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.