Results
2021-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted by a report that damage (scorch marks) was found on an internal life raft installation that contained a half rescue kit. This AD requires identifying the part number and serial number of each half rescue kit located in the internal life raft installation and, depending on the findings, inspecting the life raft for damage, inspecting the condition of the flashlight battery, testing the flashlight battery, and replacing the life raft or flashlight battery (including the leak test) as applicable, as specified in a European Aviation Safety Agency (now 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.
2021-14-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that certain airplanes have navigation units with outdated magnetic variation (MagVar) tables. This AD requires revising the existing airplane flight manual (AFM) and applicable corresponding operational procedures to update the flight management system (FMS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2006-25-07: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135ER and -135KE airplanes and Model EMB-145, -145ER, -145MR, -145MP, and -145EP airplanes. This AD requires inspecting the fuel quantity indication system (FQIS) wire harness and the direct current (DC) fuel pump wire harness to determine if the harnesses are properly attached at their respective attachment points and properly separated from one another, and performing corrective actions if necessary. This AD results from a report that the FQIS wire harness may not be properly attached at its attachment points or properly separated from the DC fuel pump wire harness. We are issuing this AD to prevent chafing between those harnesses or chafing of the harnesses against adjacent airplane structure or components, which could present a potential ignition source that could result in a fire or explosion.
2021-10-09: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) CFM56-5B and CFM56-7B model turbofan engines with a certain high-pressure turbine (HPT) inner stationary seal installed. This AD was prompted by cracks found in the rotating air HPT front seal. This AD requires removal, inspection, and replacement of the affected HPT inner stationary seal and, depending on the findings, replacement of the rotating air HPT front seal, HPT rotor blades, and No. 3 ball bearing. The FAA is issuing this AD to address the unsafe condition on these products.
2000-13-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GmbH (ECD) Model EC 135 helicopters. That AD requires conducting a tail rotor drive shaft vibration survey (survey), installing a Fenestron Shaft Retrofit Kit, inspecting each tail rotor drive shaft bearing (bearing) attaching lock plate for bent-open tabs and broken or missing slippage marks, and visually inspecting each bearing support for cracks. This AD requires conducting the survey and installing the Fenestron Shaft Retrofit Kit. This AD also requires installing double bearing supports and struts, revising the required compliance time for the repetitive inspections of the bearing attach hardware and supports, and removing the requirement to contact the FAA if a lock plate tab is bent open or if slippage marks are broken or missing. This amendment is prompted by continued reports of misaligned or cracked bearing supports and loose bearing attachment bolts. The actions specified by this AD are intended to prevent loss of drive to the tail rotor and subsequent loss of control of the helicopter.
87-26-05: 87-26-05 FOKKER B.V.: Amendment 39-5805. Applies to Model F-28 series airplanes, as listed in Fokker B.V. Service Bulletin F28/52-a/100, Revision 1, dated June 19, 1987, certificated in any category. Compliance required within 120 flight hours after the effective date of this AD, unless previously accomplished. To prevent sudden decompression of the airplane as a result of failure of a cargo hinge lugs, accomplish the following: A. Visually or dye penetrant inspect the cargo door hinge lugs for cracks, in accordance with Fokker Service Bulletin F28/52-a/100, Revision 1, dated June 19, 1987. Any lugs found to be cracked must be replaced with a serviceable part prior to further flight, in accordance with the limitations set forth in the service bulletin. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approvedby the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Fokker Aircraft, 1199 North Fairfax Street, Alexandria, Virginia 22314. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East marginal Way South, Seattle, Washington. This amendment becomes effective February 1, 1988.
2006-25-04: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 airplanes. That AD currently requires repetitive inspections for cracking and corrosion in the lower rim area of the rear pressure bulkhead and adjacent areas, repetitive inspections for cracking or corrosion in the service apertures and the upper rim area of the rear pressure bulkhead, and corrective actions if necessary. This new AD removes certain repetitive inspections and reduces the repetitive interval of one inspection. This new AD also requires an inspection for missing or damaged sealant in the area between the outer attachment angle and circumferential joint doubler, and corrective action if necessary. This new AD also requires additional inspections for corrosion of certain areas and repetitive inspections for airplanes on which repairs have been done. This AD results from reports of corrosion and cracking in the various components associated with the rear pressure bulkhead. We are issuing this AD to prevent reduced structural capability of the fuselage and consequent decompression of the airplane.
2018-16-51: We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD was sent previously to all known U.S. owners and operators of these helicopters as Emergency AD 2018-16-51, dated July 26, 2018, which superseded Emergency AD 2018-15-51, dated July 20, 2018. This AD requires inspecting the tail rotor (T/R) gearbox installation, inspecting the T/R gearbox retaining hardware and support attachment point areas, and replacing each nut. This AD is prompted by two reports of T/R gearbox assemblies loosely attached to the gearbox support. The actions of this AD are intended to address an unsafe condition on these products.
2000-13-06: This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Model S-61 helicopters. That AD requires inspecting certain pylon upper and lower hinge web fittings (web fittings) for corrosion or a crack and either repairing certain web fittings or replacing any unairworthy web fittings with airworthy web fittings. That AD also requires creating a log card or equivalent record and implementing a recurring inspection of the web fittings. This amendment retains the requirements of that AD but corrects an error in paragraph (a)(3) by removing the words "and 3.E." This amendment is prompted by an operator notifying the FAA of that error which requires an unnecessary major inspection within 25 hours time-in-service (TIS). The actions specified in this AD are intended to remove an undue burden on the public by superseding the AD and removing the requirement for the major inspection within 25 hours TIS.
82-27-03: 82-27-03 ROTO-MASTER, INC. (RAJAY INDUSTRIES, INC.): Amendment 39-4515. Applies to Rajay Model 325E10 and 3AT6EE10J2 turbochargers, installed on but not limited to: Continental Engine Models TSIO-360, 0-470, IO-470, IO-520, TIO-520; Lycoming Engine Models O-320, IO-320, LIO-320, 0-360, IO-360, TO-360, 0-540, IO-540, TIO-540. These engines are installed on, but not limited to the following aircraft: Piper PA-28R-201T, PA-28-RT-201T, PA-28-201T series; PA-34-200, PA-34-200T, series; PA-30 and -39 series; Mooney M-20 A thru K series; Lake LA-4, LA-4A, and LA-200 Series. \n\n\tCompliance is required as indicated, unless already accomplished. \n\n\tTo prevent the possibility of a fire in the powerplant nacelle and/or heat damage to the powerplant installation caused by the engine exhaust gases escaping through a cracked turbocharger turbine housing, accomplish the following: \n\n\t(a)\tWithin 50 hours of time in service after the effective date of this AD inspect the engine turbochargerexhaust systems and determine whether or not the turbine housing Rajay P/N TC-60-11 or Rajay P/N 600510, 600510-01, 600510-02 or TCM P/N 643930 or turbocharger model 325E10 or 3AT6EE10J2 is installed. If any of these part numbers are installed, or if the turbine housing part number cannot be determined, before further flight, and thereafter at intervals not to exceed 200 hours time in service from the last inspection, comply with paragraph (b) through (g) of this AD. \n\n\t(b)\tRemove the turbocharger turbine housing exhaust coupling V-Band and tailpipes (see Figure 1). \n\n\n\n\n\n\n\n\n\n\t(c)\tVisually inspect the turbocharger turbine housing for cracks using a dye penetrant inspection method. (NOTE: The suspect area can be viewed through the exhaust port to ascertain possible presence of cracks penetrating through the outer wall as shown in Fig. 2.) \n\n\t(d)\tInspect coupling V-Band clamp for cracks by spreading the band segments and checking for failed spot welds and for indicationof exhaust flanges bottoming in coupling V-Band (see Figure 1) and clamp bolt for bending, overstress, thread damage, and cracks (see Figure 1). \n\n\t(e)\tInspect turbochargers and tailpipe flanges for cracks and distortion (see Figure 1). Remove all carbon deposits from mating flanges before reassembly. \n\n\t(f)\tInspect mating area of turbocharger exhaust flange to exhaust tailpipe connection for proper mating of surfaces. \n\n\t(g)\tInspect engine mount for indication of overheat, warpage, and corrosion, or rust. Repair as required.\n\n\t(h)\tIf during inspection required by paragraph (c), an internal crack is found that either exceeds the limit shown in Figure 2, View 1 or 2, or a crack penetrates the outer wall of a turbine housing as shown in Figure 2, View 3, the existing turbine housing must be removed from service and replaced with a serviceable turbine housing prior to the next flight. \n\n\t(i)\tIf during the inspections required by paragraphs (d) through (g), cracked, distorted,or otherwise damaged parts, components, or assemblies are found, before further flight repair or replace with serviceable parts, components, and assemblies of the same part number. \n\n\t(j)\tThe inspections required by this AD may be discontinued when the turbine housing is replaced with a Roto-Master part number 600510-04 (TCM P/N 643931). \n\n\t(k)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections required by this AD. \n\n\t(l)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, Hawthorne, California. \n\n\tNOTE: Roto-Master, Inc. Service Letter Number 27, Rev. A dated September 24, 1982, refers to the above procedures. \n\n\tThis amendment becomes effective December 30, 1982.