Results
98-11-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with instructions not to arm the liftdumper system prior to commanding the landing gear to extend. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent inadvertent deployment of the liftdumpers during approach for landing, and consequent reduced controllability and performance of the airplane.
86-20-09: 86-20-09 ROLLS-ROYCE plc (formerly Rolls-Royce Limited): Amendment 39-5425. Applies to Rolls- Royce (R-R) RB211-22B turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent disk failures that can cause uncontained engine failures, accomplish the following: (a) Remove from service, prior to further flight, all intermediate pressure compressor (IPC) stage 6 to 7 rotor assemblies listed individually by serial numbers in Appendices 1 and 2 of R-R Mandatory Service Bulletin (SB) RB.211-72-6427. Revision 2, dated June 30, 1984, or FAA approved equivalent, that have accumulated total cycles in service since new, on the effective date of this AD, in excess of the service life specified in those appendices. (b) Remove from service all IPC stage 6 to 7 rotor assemblies listed individually by serial number in Appendices 1 and 2 of R-R Mandatory SB RB.211-72-6427, Revision 2, dated June 30, 1984, or FAA approved equivalent, on or before attaining the service life specified in their respective appendix. 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 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. R-R Mandatory SB RB.211-72-6427 dated June 30, 1984, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Rolls- Royce plc, P.O. Box 31, Derby DE2 8BJ, England. This document 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, Rules Docket Number 85-ANE-35, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on November 4, 1986.
83-22-06: 83-22-06 CESSNA: Amendment 39-4763. Applies to the following airplanes certificated in any category: \n\n\nModel\nSerial Number \n152\n15282032 thru 15284659, 15284661 thru 15284684, 15284686 thru 15284851, 15284853 thru 15285417, 15285419 thru 15285621, 15285623 thru 15285625, 15285627 thru 15285651, 15285653 thru 15285681, 15285683, 15285685 thru 15285693, 15285695 thru 15285700, 15285702 thru 15285713, 15285716 thru 15285719, 15285722 thru 15285724, 15285726 thru 15285728, 15285730 thru 15285731, 15285733 thru 15285744, 15285748, 15285750, 15285751, 15285753, 15285756, 15285757, 15285759, 15285760, 15285764, 15285765, 15285767, 15285769, 15285772, 15285773, 15285778, 15285779, 15285781, 15285783, \nA152\nA1520809 thru A1520990, A1520992 thru A1520997, A1520999 thru A1521020, A1521022, \n172N\n17271035 thru 17274009, \n172P\n17274010 thru 17275806, 17275809, 17275817 thru 17275854, 17275857, 17275861 thru 17275881, 17275883 thru 17275910, 17275912 thru 17275947, 17275949 thru 17275953, 17275955 thru 17275958, 17275960 thru 17275971, 17275973, 17275974, 17275976, 17275978, 17275980 thru 17275982, 17275984, 17275986 thru 17275992, 17275994, 17275995, 17275997, 17275999 thru 17276002, 17276005, 17276010, 17276012, 17276014, \n172Q\n17275869 thru 17275881, 17275883 thru 17275910, 17275912 thru 17275947, 17275949 thru 17275953, 17275955 thru 17275958, 17275960 thru 17275971, 17275973, 17275974, 17275976, 17275978, 17275980 thru 17275982, 17275984, 17275986 thru 17275992, 17275994, 17275995, 17275997, 17275999 thru 17276002, 17276005, 17276010, 17276012, 17276014, \n172RG\n172RG0001 thru 172RG1134, 172RG1137, \nR172K\nR1722930 thru R1723454, \n180K\n18053001 thru 18053203,\n182Q\n18266591 thru 18267715, \n182R and \n18267716 thru 18268103, 18268105 thru 18268107, \nT182\n18268109 thru 18268129, 18268131 thru 18268141, 18268143, 18268144, 18268146 thru 18268293, 18268295, 18268310, 18268312 thru 18268322, 18268324 thru 18268327, 18268330 thru 18268332, 18268335, 18268336, 18268339, 18268343, 18268345, 18268348, 18268350, \nR182 and\nR18200584 thru R18201912, R18201914 thru R18201933, \nTR182\nR18201935 thru R18201938, R18201940, R18201942, R18201943, R18201945, R18201946, R18201949, R18201950, R18201953, R18201954, \nA185F\n18503684 thru 18504334, 18504336, 18504337, 18504339 thru 18504395, 18504397, 18504398, 18504400, \nF152\nF15201529 thru F15201883, F15201885 thru F15201896, F15201898 thru F15201931, F15201933, F15201935, F15201936, \nFA152\nFA1520348 thru FA1520382, \nF172N\nF17201750 thru F17202039, \nF172P\nF17202040 thru F17202146, F17202148 thru F17202175, F17202177 thru F17202181, F17202183 thru F17202186, F17202189 thru F17202194, F17202197, F17202200, F17202202,\nFR172K\nFR17200631 thru FR17200675, \nFl82Q\nF18200095 thru F18200169, \nFR182\nFR18200021 thru FR18200070,\n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent possible loss of an aileron hinge pin, accomplish the following: \n\n\ta)\tWithin the next 100 hours time in service, after the effective date of this AD, visually inspect each aileron hinge (6 total) for correct location of the cotter pin in accordance with Figure 1. of this AD or Cessna Service Information Letter SE83-18 dated July 29, 1983. \n\n\t \t1.\tIf the cotter pin holes are correctly located the airplane may be returned to service without further action. \n\n\t \t2.\tIf the cotter pin holes are incorrectly located, prior to further flight modify or replace aileron hinges in accordance with instructions in Figure 1. of this AD or Cessna Service Information Letter SE83-l8 dated July 29, 1983. \n\n\tb)\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished. \n\n\tc)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Wichita, Kansas 67209, telephone (316) 269-7000. \n\n\tThis amendmentbecomes effective on November 8, 1983. \n\n\n\n\n\n\n\n\n\nFigure 1. Aileron Hinge Inspection, Modification or Replacement.
2019-15-10: The FAA is adopting a new airworthiness directive (AD) for certain Safran Aerosystems (formerly Zodiac Aerospace Services) life jackets. This AD was prompted by reports of defective welding on certain life jackets around the inflation system. This AD requires removal and replacement of the affected life jackets. The FAA is issuing this AD to address the unsafe condition on these products.
85-12-03: 85-12-03 DeHAVILLAND: Amendment 39-5074. Applies to DeHavilland Model DHC-7 series airplanes, serial numbers (S/N) 3 thru 86, 89, 91, 94, and 95, certificated in all categories. To preclude the occurrence of a ground fire caused by engine fuel impinging on landing gear brakes under certain wind conditions, accomplish the following, unless already accomplished: A. Within the next nine months after the effective date of this AD, accomplish a modification of the engine fuel drain system in accordance with Modification No. 7/2175 and DeHavilland Service Bulletin 7-71-18, Revision A, dated January 20, 1984. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. C. 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 modifications required by this AD. This amendment becomes effective July 5, 1985.
99-23-26: This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CF34 series turbofan engines, that currently requires installation of a main fuel control (MFC) that incorporates a flange vent groove and installation of an MFC with improved overspeed protection. This amendment requires replacement of Buna-N O-rings with Viton O-rings or a new location of the vent groove on the MFC mounting flange, or installation of an MFC with improved overspeed protection. This amendment is prompted by the determination that the location of the reworked vent groove was ineffective, and that replacement of Buna-N preformed packings with Viton preformed packings will alleviate the unsafe condition. The actions specified by this AD are intended to prevent uncommanded engine accelerations, which could result in an engine overspeed, uncontained engine failure, and damage to the airplane. The incorporation by reference of GE Alert ServiceBulletins (ASB s) No. A73-33, dated November 21, 1997; A73-33, Revision 1, dated May 29.1998; and A73-19, Revision 1, dated February 20, 1998, was approved by the Director of the Federal Register as of July 27, 1999. The incorporation by reference of GE ASB No. CF34AL 73-A0025, dated July 7, 1999; CF34BJ 73-A0040, dated July 7, 1999; CF34AL S/B 73-0026, dated August 12, 1999; and CF34BJ S/B 73-0041, dated August 12,1999, is approved by the Director of the Federal Register as of December 6, 1999. Comments for inclusion in the Rules Docket must be received on or before January 18, 2000.
82-25-10: 82-25-10 AVCO LYCOMING: Amendment 39-4511. Applies to Avco Lycoming ALF502L, L-2, R-3, and R-4 Turbofan Engines. Compliance is required as indicated unless already accomplished. To prevent engine power loss, uncontained engine failure, and in-flight engine shutdown, caused by separation of first stage compressor stator vane airfoils and/or separation of fourth stage turbine blade airfoils, one of which was not contained, accomplish the following: (a) Prior to December 16, 1982, and thereafter at intervals not to exceed 50 operating cycles since the last inspection, perform boroscope inspections of first stator vane segments in accordance with Avco Lycoming Service Bulletin ALF502-72-0012, Revision 2, dated June 17, 1982, until paragraph (b) is accomplished. (b) Prior to July 1, 1983, replace first stage compressor stator vane assembly with the improved first stage compressor stator vane assembly in accordance with Avco Lycoming Service Bulletin ALF502-72-0025,Revision 1, dated June 17, 1982. (c) Prior to December 16, 1982, conduct eddy current inspections of fourth stage turbine blades in accordance with Avco Lycoming Service Bulletin ALF502-72-0027 dated May 26, 1982. (d) Prior to July 1, 1983, replace fourth stage turbine nozzle with the improved fourth stage turbine nozzle in accordance with Avco Lycoming Service Bulletin ALF502-72-0021, dated April 16, 1982. (e) Later FAA approved revisions of the service bulletins, referred to in this AD, and/or equivalent means approved by the Manager, Engine Certification Branch, FAA, New England Region, may be used in lieu of the above listed service bulletins. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Manager, Engine Certification Branch, FAA, New England Region, may adjust the compliance date 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. This amendment becomes effective December 16, 1982.
2019-15-01: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a report that main landing gear (MLG) side stay actuators have been assembled using nonconforming split ball bearings. This AD requires verification of the serial numbers of the installed MLG side stay actuator assemblies, and replacement of the affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2019-15-06: The FAA is superseding Airworthiness Directive (AD) 2018-22-07 for all Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. AD 2018-22-07 required inspection of the stage 6 seal ring for correct installation and inspection of the high-pressure compressor (HPC) stages 2-5 spool for cracks and, depending on the results of the inspections, replacement of the HPC stages 2-5 spool with a part eligible for installation. This AD requires the same inspections but reduces the inspection interval and adds a repetitive inspection and a mandatory terminating action. This AD was prompted by a shop finding of axial cracks in the interstage 5-6 seal teeth of the HPC stages 2-5 spool spacer arm due to an incorrectly installed stage 6 seal ring. The FAA is issuing this AD to address the unsafe condition on these products.
99-02-18: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires removing the thermal insulating blankets from the upper rear nacelle structure; re-positioning the engine exhaust duct; and replacing the engine exhaust bracket with a new engine exhaust bracket, if necessary. For certain airplanes, this amendment also requires installing new stainless steel plates onto the upper rear nacelle structure. 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 fretting of the titanium thermal insulating blankets, which could result in an increased risk of fire in the engine exhaust duct of the tail pipe.