Results
2013-03-10: We are adopting a new airworthiness directive (AD) for certain Lindstrand Hot Air Balloons Ltd female ACME threaded hose connectors, part numbers HS6139 and HS6144, installed on balloons. 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 insufficient tightness of the threaded hose connector in the assembly area that could result in fuel leakage. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-524C2-19 and RB211-524C2-B-19 series turbofan engines. This AD requires replacing the existing low pressure (LP) compressor location bearing assembly, intermediate pressure (IP) compressor location bearing, IP compressor bearing support housing, IP compressor rear stub shaft, LP compressor location bearing support, oil transfer connector assembly, hydraulic oil seal housing, and hydraulic oil seal with improved design parts. This AD is prompted by statistical analysis by the manufacturer of in-service premature bearing failures. The actions specified in this AD are intended to prevent LP compressor failure and uncontained disc failures, resulting in damage to the airplane.
84-19-08: 84-19-08 HILLER HELICOPTERS, a subsidiary of Rogerson Aircraft Corp (formerly Hiller Aviation): Amendment 39-4914. Applies to Model UH-12D and UH-12E series helicopters equipped with engine mount Part No. 63181-5 certificated in any category which have been converted to turbine power by STC SH177WE or SH178WE. Compliance is required as indicated (unless already accomplished). (a) Within the next 20 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 600 hours time in service from the last inspection, remove the paint from the outer gimbal forward attach fitting of the Hiller engine mount Part No. 63181-5 and dye penetrant or magnetic particle inspect the gusset weld beads for cracks on both the front and back sides of the gusset. (b) If cracks are found, replace the engine mount Part No. 63181-5 before further flight. (c) Prior to or immediately following installation or reinstallation of engine mount Part No.63181-5 in any of the Model UH-12 series helicopters listed above, perform the inspection required by paragraph (a) of this AD. (d) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. This supersedes Amendment 39-3538 (44 FR 50035; August 27, 1979), AD 79-18-01. This amendment becomes effective September 20, 1984.
2018-04-10: We are adopting a new airworthiness directive (AD) for Pilatus Aircraft Limited Model PC-7 airplanes. 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 the brakes remaining activated after release of the brake pedal. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-01: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric (GE) CF6-6 series turbofan engines. This amendment requires a reduction of the cyclic life limit for certain high pressure turbine rotor (HPTR) rear shafts, and requires removing certain HPTR rear shafts from service before exceeding the new, lower cyclic life limit. In addition, this amendment requires removing from service certain HPTR rear shafts that currently exceed, or will exceed, the new, lower cyclic life limit according to the compliance schedule described in this AD. This amendment is prompted by an updated low-cycle-fatigue (LCF) analysis performed by the manufacturer that resulted in a lower cyclic life limit for certain HPTR rear shaft part numbers (PNs) installed in CF6-6 engines. The actions specified by this AD are intended to prevent cracks in HPTR rear shafts that could result in uncontained engine failure and damage to the airplane.
75-15-08: 75-15-08 BEECH AND CESSNA: Amendment 39-2266 as amended by Amendment 39- 2361. Applies to Beech Models 35, A35, B35, C35, D35, E35, F35, 35R, 35-33, 35-A33, 35- B33, 35-C33, H35, J35, K35, M35, N35, P35 series airplanes; Cessna Models 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, A150K, 150L, A150L series airplanes certificated in all categories which have been modified in accordance with STC SA2219WE. Compliance required as indicated unless already accomplished. To prevent loss of engine oil, improper engine lubrication or engine oil contamination, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 25 hours' time in service, unless (b) has been accomplished, remove the Beryl Aviation air oil separator Filtrator Assembly and inspect in accordance with the following procedure. (1) Add one quart of clear gasoline to the assembly can and plug or cap the ends of all tubes. (2) Hold the assembly can upright and shake vigorously for about two minutes. (3) Completely drain the gasoline from the 1/8 inch oil return tube through a paint strainer or similar fine mesh strainer and check for the presence of polyester urethane particles that have broken off of the internal screen material. (4) If screen particles are present, accomplish (b). (5) If screen particles are not present, install a 1/8 inch rivet in the top center of the assembly can to fasten the inside center cone to the outside can. Seal the rivet with an oil and fuel resistant type sealant if required. After assuring that cleaning agent has evaporated, reinstall the filtrator assembly. (b) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished, accomplish (1), (2), or (3). (1) (i) For Beech Models 35, A35, B35, C35, D35, E35, F35, and 35R Series Airplanes, remove the Beryl Aviation filtrator assembly P/N 1000-1 and install P/N B- 1119-M, P/N B-1119-RM, or P/N 1000-1-RM. (ii) For Beech Models H35, J35, K35, M35, N35, P35, 35-33, 35- A33, and 35-B33 and 35-C33 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N 1000-1 and install P/N B-1114-M, P/N B-1114-RM, or P/N 1000-1-RM. (iii) For Cessna Models 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, A150K, 150L, and A150L Series Airplanes, remove the Beryl Aviation filtrator assembly P/N 1000-1 and install P/N B-1119-M, P/N B-1119-RM, or P/N 1000-1-RM. (2) Remove the modification incorporated by STC SA2219WE and return the airplane to the standard unmodified configuration. (3) Provide compliance with an equivalent method approved by Chief, Engineering and Manufacturing Branch, Southern Region. Beryl Aviation Specialties, Route 1, Box 127D, Leesburg, Florida 32748, Service Bulletin B-1-1-75-1 also pertains to this subject. Amendment 39-2266 became effectiveFriday, July 25, 1975. This amendment 39-2361 becomes effective September 10, 1975.
2000-03-11: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires replacement of 10 amp circuit breakers with 5 amp circuit breakers in the left and right windshield anti-ice power controllers; and replacement of the anti-ice control panel with a new or modified panel, or modification and reidentification of the anti-ice control panel. This amendment is prompted by reports of smoke and sparks emanating from the anti-ice control panel in the cockpit. The actions specified by this AD are intended to prevent burnt internal circuit boards caused by a short in either the engine or airfoil anti-ice valve, or the windshield anti-ice controller, which could result in smoke in the cockpit.
73-08-03: 73-08-03 BELL: Amdt. 39-1622. Applies to Bell Models 206A, 206B, 206A-1 and 206B-1 helicopters equipped with pylon support links, P/N 206-031-508-5 or -7, certificated in all categories. Compliance required as indicated. To prevent possible failure of a pylon support link, P/N 206-031-508-5 or -7 accomplish the following: (a) Within the next ten hours time in service after the effective date of this A.D., unless already accomplished, inspect the pylon support link assemblies in accordance with Part II of Bell Helicopter Company Service Bulletin No. 206-01-73-2, Revision A, dated March 27, 1973, or later FAA approved revision or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. If the bearing inner race measures more than 1.255 inches in diameter or there is any crack in the link, the link assembly must be replaced prior to next flight. (b) Within twenty-five hours time in service after compliance with paragraph (a) and thereafter at intervals not to exceed twenty-five hours from the last inspection, inspect the pylon support link assemblies in accordance with Part III of Bell Service Bulletin No. 206-01-73-2, Revision A, dated March 27, 1973, or later FAA approved revision or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. If any crack is found, the link assembly must be removed and replaced prior to next flight. (c) This airworthiness directive is no longer applicable when pylon support links, P/N 206-031-589, are installed. This supersedes Amendment 39-1602 (38 F.R. 6377), A.D. 73-05-04. This amendment becomes effective April 18, 1973.
2021-20-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that during flight tests, the opening of the ram air outlet flaps was found to cause a disturbance of the air flow around the ram air turbine (RAT) when the landing gear (L/G) is extended. This AD requires revising the existing airplane flight manual (AFM) and applicable corresponding operational procedures to provide procedures for all engines failure and L/G gravity extension related to certain software, and installing Airbus temporary quick change (ATQC) V3 for the flight warning system (FWS) software (SW) standard (STD) 6/ 2.0, 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.
2013-05-22: We are adopting a new airworthiness directive (AD) for all Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A109S, and A119 helicopters. This AD was prompted by a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that a Model A109E helicopter experienced a failure of the tail rotor pitch control link assembly caused by a production defect. The actions of this AD are intended to prevent failure of a tail rotor pitch control link and subsequent loss of control of the helicopter.