Results
2022-02-15: The FAA is superseding Airworthiness Directive (AD) 2020-12-06 for all Gulfstream Aerospace Corporation (Gulfstream) Model G-IV airplanes. AD 2020-12-06 required replacing the nose wheel steering servo valve manifold, incorporating revised operating procedures into the airplane flight manual (AFM), doing a records inspection for any incidents of un-commanded nose wheel steering turns, and reporting the results to the FAA. Since the FAA issued AD 2020-12-16, the FAA determined that a typographical error was made in citing one of the AFM documents. This AD retains the actions of AD 2020-12-06 and corrects the citation to the AFM. The FAA is issuing this AD to address the unsafe condition on these products.
88-03-06: 88-03-06 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5888. Applies to IO-360, TSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, GTSIO-520, and IO-550 series engines equipped with oil filters. Compliance is required at the next oil change or within 10 flight hours, whichever occurs first, unless already accomplished. To prevent possible loss of engine oil and subsequent engine failure, accomplish the following: (a) Determine if oil filter TCM P/N 649309 or 649310 is installed. (1) If neither filter is installed, proceed to paragraph (b). (2) If P/N 649309 is installed, replace with P/N 649923 or equivalent Parts Manufacturer Approval (PMA) product. (3) If P/N 649310 is installed, replace with P/N 649922 or equivalent PMA product. (b) Make appropriate log book entry showing compliance with this AD. (c) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where this AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. (e) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Manager, Atlanta Aircraft Certification Office, may adjust the compliance time specified in this AD. NOTES: (1) TCM Service Bulletin No. M88-4, dated January 15, 1988, refers to this subject. (2) TCM oil filter P/N's 649309 and 649310, in inventory, should be returned to TCM in accordance with the TCM service bulletin referenced in Note 1. This amendment, 39-5888, becomes effective April 15, 1988, as to all persons except those persons to whom it was made immediately effective by individual priority letter AD 88-03-06, issued February 5, 1988, which contained this amendment.
99-01-03: This amendment supersedes Airworthiness Directive (AD) 97-14- 16, which applies to Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. AD 97-14-16 currently requires repetitively inspecting the outboard flap support roller bearings and flap attachment brackets for indications of contact (wear), inspecting for elongated holes in the flap attachment brackets, repairing or replacing any part showing wear, and replacing any bracket with elongated holes. AD 97-14-16 was the result of five incidents where the flap roller bearings rubbed on the flap attachment brackets and resulted in aileron interference. This AD retains the repetitive inspection requirement of AD 97-14-16, but reduces the number of ground-air-ground (GAG) cycles allowed between inspections and lowers the total number of accumulated GAG cycles allowed before mandatory accomplishment of the initial inspection. This AD also provides the option of replacing the outboard flap roller bearings with parts of improved design as terminating action for the repetitive inspection requirement. The actions specified by this AD are intended to prevent asymmetric flaps, jammed flaps, and/ or possible interference between the flap and the aileron, which could inhibit aileron travel and result in possible loss of roll control of the airplane.
65-15-03: 65-15-03 CONSOLIDATED AERONAUTICS: Amdt. 39-103 Part 39 Federal Register July 1, 1965. Applies to Model Lake LA-4 Aircraft. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent failure of the nose landing gear to latch in the down and locked position, accomplish the following: (a) Inspect the bolt at the top of the nose gear drag strut at Fuselage Station 12 5/8 that connects the upper drag strut assembly, Lake P/N 2-4411-1, to the support assembly plates, Lake P/N 2-4412-27, to ensure that an AN5-16A bolt or an FAA-approved equivalent is installed and that the bolt head is on the right-hand side of the aircraft. (b) If an AN5-15A bolt is installed, remove the bolt and visually inspect the bolt hole of the upper drag strut assembly and both support assembly plates for elongation. (c) Rework any part having an elongated bolt hole in accordance with Consolidated Aeronautics, Inc., Lake Aircraft Division, Service Letter No. 11B, dated February 22, 1965, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or replace the part with a new part of the same part number or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Replace any AN5-15A bolt with an AN5-16A bolt or an AN5-17A bolt as necessary when bushings are installed or an FAA-approved equivalent, installing the bolt with the head on the right-hand side of the aircraft. (e) Reverse any AN5-16A bolt that is installed with the head on the left-hand side of the aircraft. This directive effective July 1, 1965.
2021-26-25: The FAA is adopting a new airworthiness directive (AD) for certain Schempp-Hirth Flugzeugbau GmbH Model Duo Discus and Duo Discus T gliders. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated 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 jerky extension of the air brakes at very high air speeds, including cases where the air brake blades interlock. This AD requires replacing certain air brake end stop bushings, inspecting certain other air brake end stops, and repairing if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2022-02-16: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that, during landings, as a result of this interference, certain airplane systems may not properly transition from AIR to GROUND mode when landing on certain runways, resulting in degraded deceleration performance and longer landing distance than normal due to the effect on thrust reverser deployment, speedbrake deployment, and increased idle thrust. This AD requires revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate limitations prohibiting certain landings and the use of certain minimum equipment list (MEL) items, and to incorporate operating procedures for calculating landing distances, when in the presence of 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
89-14-07: 89-14-07 AEROSPATIALE: Amendment 39-6257. Applicability: Model ATR42-300 series airplanes, Serial Numbers 003 through 052, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the emergency exit frame, accomplish the following: A. Prior to the accumulation of 12,000 landings or within 60 days after the effective date of this AD, whichever occurs later, accomplish modification of the fuselage emergency exit frame in accordance with Aerospatiale Service Bulletin ATR42-53-0024, Revision 2, dated May 16, 1988. B. An alternate means 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either 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 airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6257, AD 89-14-07) becomes effective on August 7, 1989.
47-36-02: 47-36-02 DOUGLAS: (Was Mandatory Note 2 of AD-3L-1.) Applies to A-26B and A-26C Aircraft. Compliance required prior to operation in cold weather and not later than next engine overhaul. To preclude collapse of the oil screen during cold weather starting, replace oil screen assembly No. 51887 with oil screen assembly Nos. 51887M or 107547. P/N 51887 may be reworked to P/N 51887M by incorporating reinforcing spring No. 107542 and adding the letter "M" to the part number.
2004-13-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that currently requires a one-time inspection to detect loose bolts attaching the gustlock counter-bracket to the pulley on the elevator tension regulator (control) assembly, and corrective action if necessary. This AD instead requires a modification of the elevator tension control mechanism. This AD also revises the applicability to include additional airplanes. The actions specified by this AD are intended to prevent restricted elevator movement and consequent reduced controllability of the airplane. This AD is intended to address the identified unsafe condition.
53-10-02: 53-10-02 de HAVILLAND: Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 401 Inclusive. Compliance required as indicated. After the aircraft has acquired 500 hours of flying time and pending the incorporation of the recommended repair, the wings should be inspected for cracks in lower wing skin at ends of the short stringers at the root end station of the wing leading edges at 50-hour intervals. If no cracks are evident reinforcements should be installed on the bottom surface of the wing as a preventive measure. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet Series B, No. 59 - Issue 2 dated January 15, 1953, available from de Havilland Aircraft of Canada, Ltd., Toronto, Ontario, Canada, covers this same subject and describes method of reinforcement.)
2021-26-26: The FAA is superseding Airworthiness Directive (AD) 2005-12-08 for certain Safran Helicopter Engines, S.A. (Safran Helicopter Engines) Arrius 2B1, 2B1A, 2B1A-1, and 2B2 model turboshaft engines. AD 2005-12- 08 required replacing the software in the engine electronic control unit (EECU). This AD was prompted by a report of simultaneous loss of automatic control on both engines installed on an Airbus Helicopters Deutschland (formerly Eurocopter Deutschland) EC135 helicopter during flight. This AD requires replacement of the EECU or upgrade of the EECU software for engines with a certain EECU part number (P/N) installed. This AD also prohibits installation of an affected EECU onto any engine. The FAA is issuing this AD to address the unsafe condition on these products.
2012-12-21: We are superseding an existing airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 C-2 helicopters. That AD currently requires revising the ``Emergency and Malfunction Procedures'' and ``Performance Data'' sections of the Rotorcraft Flight Manual (RFM) by inserting three temporary pages into the RFM to alert pilots to monitor the power display when a generator is deactivated and provides procedures to prevent failure of the remaining generator. Before we issued that AD, the manufacturer developed a procedure to modify the two ``After Junction Boxes'' by removing a diode from each box, which provides terminating action for our AD requirements. These actions are intended to require implementing this terminating action to prevent an electrical power system failure and subsequent loss of control of the helicopter and revising the RFM accordingly, by removing the temporary pages inserted to comply with the superseded AD.
95-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires an inspection to determine the model and orientation of certain flight control rods, and replacement of the rods with modified rods, if necessary. This amendment is prompted by reports of corrosion found on the pitch and rudder trim and rudder travel limiter fail-safe rods. The actions specified by this AD are intended to prevent problems associated with corrosion of the flight control rods, which could compromise the required strength of these items.
48-19-03: 48-19-03\tDOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43024; 43035 Through 43052; 43055 Through 43058; 43061 Through 43064; and 43105 through 43110. \n\n\tCompliance required by September 15, 1958. \n\n\tDue to two failures in flight and to reported excessive looseness in the elevator trim tab operating mechanism, the following must be accomplished: \n\n\t1.\tRework drum, P/N 4344461 into drum, P/N 4357010-4, by boring hole in end of drum 0.8755-0.8745 diameter, 0.188-0.189 deep and concentric within 0.002 full indicator reading, and press in bushing 4357010-2 into hole. Remove nut, P/N 2335472, press in nut, P/N 2357008, in place so that two holes in nut match two holes in drum, P/N 4357010-4, and insert two pins, P/N 1335480, and stake in place. This rework changes jackshaft mechanism assembly, P/N 434460, into P/N 4357010. \n\n\t2.\tRework push-pull tubes, P/N 2344790, into P/N 2357984-2 by cutting off swaged end of tube 1/8 inch so that new tube lengthis 10 inches. Insert large end of plug, P/N 2357980, into tube 1 3/4 inches, drill two 0.161 diameter holes (No. 20 drill) and attach plug to tube with two rivets, P/N AN 430 AD5-16. Machine hex end on socket, P/N 2331924, and install in end of the tube opposite to plug, P/N 2357980. Rework end assemblies, P/N 2331925 into end assemblies, P/N 2357983, and install with locknuts, P/N AN 316-5R and washer 1357982. \n\n\tReassemble trim tab mechanism and install on aircraft. \n\n\t(Douglas Service Bulletin DC-6 No. 123 covers this same subject.)
2012-13-51: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (Type Certificate previously held by Israel Aircraft Industries, Ltd.) Model Gulfstream G150 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires a one-time detailed or borescope inspection of the left- and right-hand inboard vent holes for debris or obstructions, and repair if necessary. This AD was prompted by a report indicating that an inboard vent tube hole was completely covered with sealant, which blocked airflow through the vent. Under these conditions, the rise of internal pressure during pressure fueling or due to thermal expansion is sufficient to damage the wing. We are issuing this AD to detect and correct compromised integrity of the wing structure.
2021-26-03: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame splice between certain stringers is subject to widespread fatigue damage (WFD). This AD requires an inspection of certain fuselage frame splices for existing repairs, repetitive inspections of certain fuselage frame splices for cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2012-16-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports that some nuts installed on the wing, including on primary structural elements, were found cracked. This AD requires inspecting to determine if certain nuts are installed or cracked, and replacing the affected nuts if necessary. We are issuing this AD to detect and correct missing and cracked nuts, which could result in the structural integrity of the airplane wings being impaired.
50-18-02: 50-18-02 DOUGLAS: Applies to All Model DC-6 Aircraft Equipped With Hamilton Standard 43D60/6841A-O, 6851A-O, and 6873A-O Propeller Blades and R-2800-83AM4, R-2800-83A or CA Type Engines. \n\n\tTo have been accomplished by April 28, 1950. \n\n\tA recent propeller blade tip failure of a Hamilton Standard 43D60/6851A-O propeller on a DC-6 powered with R-2800-CA-15 engines probably resulted from a worn 4 1/2 order engine crankshaft torsional damper P/N 101169. Until further notice or until the engines are known definitely to comply with P&W Service Bulletin No. 1033 dated November 30, 1949, all DC-6 aircraft using Hamilton Standard 6841A-O, 6851A-O and 6873A-O blades and R-2800-83AM4 or CA type engines shall be placarded to avoid all operation between 1,800 and 1,975, between 2,025 and 2,175 and between 2,225 and 2,450 r.p.m. Only acceleration and deceleration through placarded ranges shall be permitted. For gross weights above 80,000 pounds, 2,450 r.p.m. is permissible for normal climb. For gross weights below 80,000 pounds, climbing r.p.m. between 2,450 and 2,600 permissible. For gross weights above 80,000 pounds avoid operation above 2,450 r.p.m. except for takeoff and emergencies. For R-2800-83A engine installations, operating restriction presently covered in Aircraft Specification A781, Note 5C (1) applicable and until further notice operation between 1,800 and 1,975 and between 2,025 and 2,175 shall be prohibited.
2004-13-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-301, -311, and -315 airplanes. This AD requires determining the modification number of the angle of attack (AOA) sensor vanes; testing the movement of the affected vanes to evaluate sticking against both the upper and the lower vane travel end stops; and corrective action, if necessary. This action is necessary to prevent an incorrect AOA indication to the stall warning system in flight, which could result in an inadvertent stall and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
98-26-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time inspection to determine the material type of the stop support fittings of the main entry doors. This AD also requires repetitive visual inspections to detect cracks of certain stop support fittings of the main entry doors, and replacement of any cracked stop support fitting with a certain new stop support fitting. This amendment is prompted by reports that stress corrosion cracking was found on certain stop support fittings of the main entry doors. The actions specified by this AD are intended to detect and correct such stress corrosion cracking, which could lead to failure of the stop support fittings. Failure of the stop support fittings could result in loss of a main entry door and consequent rapid decompression of the airplane.
2021-25-05: The FAA is superseding Airworthiness Directive (AD) 2017-23- 02, which applied to certain The Boeing Company Model 737-200, -200C, - 300, -400, and -500 series airplanes. AD 2017-23-02 required repetitive inspections, replacement, and applicable on-condition actions for certain fuselage crown skin panels. This AD was prompted by an evaluation by the design approval holder indicating that the fuselage crown skin panels are subject to widespread fatigue damage. This AD retains the actions in AD 2017-23-02, revises certain airplane configurations and inspection locations, and adds airplanes to the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
48-15-03: 48-15-03 DOUGLAS: Applies to C-54 and DC-4 Aircraft. \n\n\tCompliance required by November 1, 1948. \n\n\tBecause of service failures of hydraulic pressure regulator valves, the following must be accomplished: \n\n\t1.\t(a)\tModify Douglas hydraulic pressure regulator valve P/N 5104005, P/N 5231848, or P/N 5327293 to the equivalent of Douglas regulator P/N 5332857, or \n\n\t\t(b)\tConvert Douglas hydraulic pressure regulator valve P/N 5104005, P/N 5231848, or P/N 5327293 to Douglas regulator P/N 5332857, or \n\n\t\t(c)\tInstall Douglas hydraulic pressure regulator P/N 5332857, or \n\n\t\t(d)\tInstall Bendix hydraulic pressure regulator P/N 407484, or \n\n\t\t(e)\tInstall Air Associates hydraulic pressure regulator valve P/N HC-3600, or \n\n\t\t(f)\tInstall Vickers hydraulic pressure regulator valve P/N AA-34551, P/N AA-34552, or P/N AA-34585 which must have the letter "C" or subsequent terminating the regulator serial number, i.e., "Serial No. 0000C," "Serial No. 0000D," etc. \n\n\t2.\tInstall a hydraulic fluid filter with Purolator core in regulators listed in 1, (a) through (d). \n\n\t(Douglas Service Bulletin DC-4 No. 22, "Rework of Hydraulic Pressure Regulator Valve" with addendum, "Optional Installation of Hydraulic Pressure Regulators" covers part 1. Douglas Service Bulletin C-54-239, "Installation of Filter in Hydraulic Regulator Operating Line," covers part 2.)
96-12-09: This amendment adopts a new airworthiness directive (AD), applicable to PTC Seating Products Division, B/E Aerospace (PTC), formally known as PTC Aerospace, Model 950 series passenger seats with footrest assembly. This amendment will require the removal of the footrest assembly arms and the installation of a conversion kit on each PTC Model 950 series passenger seat equipped with footrest assembly. This amendment is prompted by two incidents of finger injuries that occurred during attempts to either extend or retract the footrest system on PTC Model 950 series passenger seats equipped with footrest assembly. The actions specified by this AD are intended to prevent injury to hands during the operation of a PTC Model 950 series passenger seat equipped with footrest assembly.
2004-13-13: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires a one-time inspection of the access door ramp of the fueling control panel for damage or deformation, and applicable corrective actions. This action is necessary to prevent inadvertent fuel transfer in flight due to fuel service personnel not repositioning the defuel valve switch control to the closed position after utilization on the ground, which could cause in-flight fuel starvation. This action is intended to address the identified unsafe condition.
2021-26-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam, and a report from the airplane manufacturer that airplanes were assembled with seals throughout various areas of the airplane (including flight deck and cargo compartments) made of BMS 8-39 urethane foam, a material with fire- retardant properties that deteriorate with age. This AD requires replacing the system tube/wire seals made of BMS 8-39 urethane foam in certain areas of the airplane. The FAA is issuing this AD to address the unsafe condition on these products.