Results
2021-14-02: The FAA is adopting a new airworthiness directive (AD) for all Aircraft Industries a.s. Models L-420, L 410 UVP-E20, and L 410 UVP-E20 CARGO airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as cracking of the retaining bolt on the nose landing gear (NLG) control. The FAA is issuing this AD to address the unsafe condition on these products.
92-16-12 R1: 92-16-12 R1 BRITISH AEROSPACE: Amendment 39-8702. Docket 93-NM-157-AD. Revises AD 92-16-12, Amendment 39-8321. Applicability: Model DH/BH/HS/BAe 125 series airplanes, as listed in British Aerospace Service Bulletin SB.53-74-3193C&D, Revision 1, dated March 12, 1992; certificated in any category. NOTE 1: Model BAe 125-1000A airplanes are not affected by this AD. Compliance: Required within 4 months after the effective date of this AD, unless accomplished previously. To prevent fire in the tail cone, accomplish the following: (a) Install fluid vent masts on the undercarriage fairing, and plug certain existing vent holes, in accordance with British Aerospace Service Bulletin SB.53-74-3193C&D, dated January 7, 1992; or Revision 1, dated March 12, 1992. (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 2: 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 British Aerospace Service Bulletin SB.53-74-3193C&D, dated January 7, 1992; or British Aerospace Service Bulletin SB.53-74-3193C&D, Revision 1, dated March 12, 1992. (The issuance date of Revision 1 of this service bulletin appears only on page 1 of the document.) The incorporation by reference of the former service bulletin was approved previously by the Directorof the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51, as of September 28, 1992 (57 FR 38266, August 24,1992). The incorporation by reference of the latter service bulletin 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment is effective on September 28, 1992.
2021-13-03: The FAA is adopting a new airworthiness directive (AD) for certain Safran Helicopter Engines, S.A. (Safran Helicopter Engines) Arriel 2B, 2B1, 2C, 2C1, 2C2, 2S1 and 2S2 model turboshaft engines. This AD was prompted by reports of non-conforming fuel filter pre- blockage pressure switches. This AD requires repetitive visual inspections of the fuel filter by-pass indicator pop-up, a one-time operational test of the fuel filter pre-blockage pressure switch and, depending on the findings, replacement of the fuel filter pre-blockage pressure switch with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
98-01-06: This amendment supersedes an existing airworthiness directive (AD), applicable to Precision Airmotive Corporation carburetors, that currently requires the inspection of those carburetors equipped with a two-piece venturi at each annual inspection to determine if the primary venturi is loose or missing, and requires the replacement of a two-piece venturi with a one-piece venturi within 48 months after the effective date of the existing AD. This amendment eliminates the requirement to install a one-piece venturi, and allows the installation of a one-piece venturi on affected carburetors as an optional terminating action; or, requires repetitive inspections of a two-piece venturi on affected carburetors. This AD also adds an additional carburetor model, and requires the installation of a new fuel nozzle on certain carburetors when a one-piece venturi is installed. This amendment is prompted by service difficulty reports describing engines that fail to attain rated power, runrough, or experience power loss after installation of a one-piece venturi in accordance with the existing AD, and by incidents of forced landings of aircraft powered by engines modified to comply with the existing AD. The actions specified by this AD are intended to prevent disruption of fuel flow to the engine resulting in failure to attain rated power, power loss in flight, and forced landings.
98-01-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires modification of the air outlet opening of the engine air bypass duct. 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 accumulation of ice in the engine air intake duct and subsequent ingestion of ice into the engine, which could result in engine power fluctuations and reduced controllability of the airplane.
2021-12-07: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11 model turbofan engines. This AD was prompted by an investigation by RRD, which revealed a quality escape during the high-pressure turbine (HPT) stage 1 disk rim cooling air hole manufacturing process. This AD requires removing affected HPT disks from service prior to reaching specified compliance times or at the next engine shop visit, whichever occurs first. The FAA is issuing this AD to address the unsafe condition on these products.
2021-13-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD was prompted by a report of a yaw control failure that was the result of the disconnection of the tail rotor hub (TRH) pitch control rod from the tail rotor servo-control, which resulted from a seized TRH bearing. The TRH bearing had grease dissolving after contamination by leaked hydraulic fluid from the tail rotor servo- control that came through the TRH assembly boot. This AD requires repetitive inspections for hydraulic leaks, corrective actions if necessary, and an optional modification which constitutes terminating action, 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.
97-26-22: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-120 series airplanes. This action requires a one-time inspection of the movable backstop of the elevator pitch trim command system to ensure that it is installed correctly, and corrective action, if necessary. This action also requires installation of a guide to maintain the movable backstop in its correct position. 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 a sudden change in pitch attitude caused by autopilot disconnect, which could result in reduced controllability of the airplane.
2004-06-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, -321, -322, -341, and -342 series airplanes; and certain Model A340 series airplanes, that requires inspecting for and repairing cracking of the wire harness slots in the inner rear spars of the wings between ribs 4 and 5, and cold-expanding crack-free wire harness slots and bolt holes. This action is necessary to prevent cracking of the wire harness slot, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
65-19-03: 65-19-03\tBOEING: Amdt 39-118 Part 39 Federal Register August 24, 1965. Applies to Models 707 and 720 Series Airplanes Listed in Boeing Service Bulletin No. 2014 (R-2). \n\tCompliance required as indicated. \n\n\t(a)\tFor Model 720 Series airplanes with 4,500 or more hours' time in service on the effective date of this AD, comply with (c) within the next 600 hours' time in service, unless accomplished within the last 600 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(b)\tFor Model 720 Series airplanes with less than 4,500 hours' time in service on the effective date of this AD, comply with (c) before the accumulation of 5,100 hours' time in service, unless accomplished after the accumulation of 3,900 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(c)\tInspect visually for cracks in the left-hand and right-hand frames at Body Stations 760 and 780 on Model 720 Series airplanes except 720-025 Series and at Body Station 800 on all Model 720 Series airplanes in the vicinity of waterline 208.1 (top of floor beam). If cracks are found, rework the frames before further flight in accordance with paragraph 3 of Boeing Service Bulletin No. 2014(R-2) or later FAA-approved revision; Boeing Structural Repair Manual D6- 1891, paragraph 53-3-5, page 1; or a method approved by the Aircraft Engineering Division, FAA Western Region. The repetitive inspections required by (a) and (b) of this AD may be discontinued when cracked frames have been reworked in accordance with this paragraph, or when uncracked frames have been reworked in accordance with Boeing Drawing 65-42173, or a method approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(d)\tFor Model 707 Series airplanes with 10,000 or more hours' time in service on the effective date of this AD, comply with (f) within the next 600 hours' time in service, unless accomplished within the last 600 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(e)\tFor Model 707 Series Airplanes with less than 10,000 hours' time in service on the effective date of this AD, comply with (f) before the accumulation of 10,600 hours' time in service, unless accomplished after the accumulation of 9,400 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(f)\tInspect visually for cracks in the left-hand and right-hand frames at Body Station 800 in the vicinity of waterline 208.1 (top of floor beam). If cracks are found, rework the frames before further flight in accordance with paragraph 3 of Boeing Service Bulletin No. 2014(R-2) or later FAA-approved revision; Boeing Structural Repair Manual D6-1649, paragraph 53-3-5, page 1, for 707-100/200 Series airplanes, and Boeing Structural Repair Manual D6-2962 for 707- 300/400 Series airplanes; or a method approved by the Aircraft Engineering Division, FAA Western Region. The repetitive inspections required by (d) and (e) of this AD may be discontinued when cracked frames have been reworked in accordance with this paragraph, or when uncracked frames have been reworked in accordance with Boeing Drawing 65-42173, or a method approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(g)\tUpon request of an operator, an FAA maintenance inspector, with prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals required by this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for the operator. \n\n\tThis directive effective September 23, 1965.