Results
2012-10-13: We are superseding an existing airworthiness directive (AD) for certain Continental Motors, Inc. (CMI) models TSIO-520, TSIO-550-K, TSIOF-550K, and IO-550-N series reciprocating engines with new or rebuilt CMI starter adapters installed between January 1, 2011 and November 20, 2011. That AD currently requires replacing affected CMI starter adapters with starter adapters eligible for installation. This AD requires the same actions, but to an expanded population of reciprocating engines. This AD was prompted by two additional reports received of fractures in starter adapter gear shafts in certain additional part number (P/N) CMI starter adapters since we issued the existing AD. We are issuing this AD to prevent starter adapter gear shaft failure which could cause oil scavenge pump failure and engine in-flight shutdown.
2021-24-08: The FAA is superseding Airworthiness Directive (AD) 2021-04- 21, which applies to certain Airbus Helicopters Model EC120B helicopters. AD 2021-04-21 required an inspection of the attachment bolts of the main rotor (MR) hub scissors assembly for discrepancies and repair if necessary; part marking of the attachment bolts of the MR hub scissors assembly; and repetitive inspections of the part marking of the attachment bolts, and repair if necessary. This AD continues to require the actions in AD 2021-04-21; and also requires part marking of the washer, scissor branch, and mast ring of the corresponding nut side, and repetitive inspections of the additional part markings and repair if necessary; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of broken and bent attachment bolts of the MR hub scissors assembly and a determination that additional part markings of the washer, scissor branch, and mast ring of the corresponding nut side, and repetitive inspections of those part markings, are necessary to detect any rotation. The FAA is issuing this AD to address the unsafe condition on these products.
58-17-02: 58-17-02 CURTISS-WRIGHT: Applies to all C-46 Series aircraft including the Models C-46R and C-46/CW20-T aircraft. Compliance required as noted. Due to recurrent fatigue cracking on the horizontal tail surfaces, the following inspections must be accomplished: 1. Conduct a daily visual external inspection of the horizontal tail surfaces for cracks with especial reference to cracks developing in the skin and ribs in the area of the elevator balance weights and the elevator hinge cutouts. 2. A detailed visual inspection of the horizontal tail surfaces must be conducted at intervals not to exceed 100 hours' time in service. Particular attention should be paid to cracks developing in the area of the balance weights on the elevator, elevator nose ribs, elevator main spar, and elevator and stabilizer hinge ribs. 3. Any cracks found must be repaired in accordance with the structural repair manual or other approved repair method prior to the next flight. Stop-drilling of cracks is not considered a repair but may form part of a repair. To facilitate inspection, the horizontal stabilizer may be modified in accordance with L.B. Smith Aircraft Corporation Drawing No. 5.040.02, or approved equivalent. To provide access to the elevator interiors for visual inspection, access holes may be added in the elevator skin as shown on Riddle Airlines Incorporated Service Bulletin No. RSB-C- 46-8. Revised July 11, 1961.
2004-11-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that requires inspection of cables installed on certain contactors in the electrical power center (EPC) for proper installation of wires, and reinstallation of wires if necessary. These actions are necessary to prevent a short circuit in the EPC, possibly leading to a fire in the main cabin and damage to the airplane, or injury to passengers and flightcrew. These actions are intended to address the identified unsafe condition.
2021-23-13: The FAA is adopting a new airworthiness directive (AD) for all helicopters equipped with a radio (also known as radar) altimeter. 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). This AD requires revising the limitations section of the existing rotorcraft flight manual (RFM) for your helicopter to incorporate limitations prohibiting certain operations requiring radio altimeter data when in the presence of 5G C-Band interference in areas as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
2021-22-08: The FAA is adopting a new airworthiness directive (AD) for H[eacute]licopt[egrave]res Guimbal (HG) Model Cabri G2 helicopters. This AD was prompted by the determination that certain parts need life limits and certification maintenance requirement (CMR) tasks. This AD requires establishing life limits and CMR tasks for various parts and removing any parts from service that have reached or exceeded their life limits. Depending on the results of the CMR tasks, this AD requires corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
66-06-02: 66-06-02\tBOEING: Amdt. 39-200 Part 39 Federal Register February 24, 1966. Applies to Models 707 and 720 Series Airplanes Equipped with Turbofan Engines and strut Mounted P(t2) Probes. \n\n\tCompliance required within the next 1,800 hours' time in service after the effective date of this AD unless already accomplished. \n\n\tThere have been numerous instances of the aft edges of the turbocompressor dipstick access door, which is in front of the strut mounted P(t2) probe, becoming unfaired in flight and causing erroneous readings of the EPR (engine pressure ratio) system. To prevent erroneous readings of the EPR system, install an additional rotary latch on the aft edge of the access door in accordance with Boeing Service Bulletin No. 2143 or later FAA-approved revision or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective March 26, 1966.
2004-11-07: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, that requires implementation of a program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This action is necessary to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes. This action is intended to address the identified unsafe condition.
2012-09-12: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and - 233 airplanes; and Model A321-111, -112, and -131 airplanes; equipped with an additional center tank (ACT). That AD currently requires identifying the part number of the ACT and, for certain ACTs, replacing the outer ACT manhole cover and seal. This new AD requires modifying certain ACTs by replacing the manhole seal with a new seal; adding certain ACT equipped airplanes to the applicability; and removing Model A320-111 airplanes from the applicability. This AD was prompted by reports that the modification required by the current AD was not fully effective. We are issuing this AD to prevent fuel and/or vapor leakage, which could result in a combustible fuel vapor/air mixture in the cargo compartment, and consequent fire risk.
2021-23-16: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. 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 identifies the unsafe condition as chafing of the engine fuel feed line hoses. This AD requires inspecting the engine fuel feed line hoses and the electrical wiring and rerouting all fuel lines. The FAA is issuing this AD to address the unsafe condition on these products.
98-21-15: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires modifying the oxygen generators. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent failure of the oxygen generators caused by misalignment of the firing pin, which could result in crew incapacitation and loss of the airplane.
2004-11-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A (including C- 29A and U-125 variant) and 800B airplanes; and Model Hawker 800 (including U-125A variant) and 800XP airplanes; that requires a functional test of the engine fire extinguishing wiring for the appropriate installation; verification of the correct wiring connector installation; correction of wiring if necessary; and installation of new marker bands. This action is necessary to prevent incorrect wiring of the engine fire extinguisher bottles, which could result in one or both fire extinguisher bottles being discharged into the wrong engine nacelle. This action is intended to address the identified unsafe condition.
2021-23-19: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. This AD results from 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 identifies the unsafe condition as insufficient separation of ground terminations for individual power sources and static grounds. This AD requires inspecting and separating, if applicable, the battery and generator common ground connections on the airframe. The FAA is issuing this AD to address the unsafe condition on these products.
2021-23-09: The FAA is superseding Airworthiness Directive (AD) 2015-16-07 R1, which applied to certain Reims Aviation S.A. (type certificate now held by ASI Aviation) Model F406 airplanes. AD 2015-16-07 R1 required inspecting the left-hand and right-hand rudder control pedal torque tubes and replacing with a serviceable part as necessary. Since the FAA issued AD 2015-16-07 R1, the European Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD retains the requirements of AD 2015-16-07 R1, expands the applicability, and requires repeating the inspections using updated procedures. The FAA is issuing this AD to address the unsafe condition on these products.
73-07-08: 73-07-08 PRATT & WHITNEY: Amendment 39-1616 as amended by Amendment 39-1630. Applies to all Pratt & Whitney JT3D-1, JT3D-1-MC6, JT3D-1-MC7, JT3D-3 and JT3D-3B model engines containing fuel control to fuel return line elbow P/N 424790 and jam nut P/N 217477. Compliance required within the next 500 hours time in service after the effective date of this AD and every 1000 hours in service thereafter, or until modified in accordance with the service bulletin referenced in paragraph (b)(2) or equivalent method approved by the Chief, Engineering and Manufacturing Branch, New England Region. To prevent the possibility of fuel leakage due to loosening of fuel control to fuel pump return tube elbow P/N 424790, and jam nut P/N 217477, check jam nut torque value. (a) If found to be a minimum of 285 in-lbs., continue in service operation. (b) If the jam nut is found to be less than 285 in-lbs., break the connection and examine the mating threads of the elbow P/N 424790 and fuel control cover P/N 704972-1 on their loaded sides for wear. NOTE: The loaded side will be on the fuel side (inside) rather than the air side (outside) of the cover. (1) If the threads are not worn remake the fitting according to the instructions given in the Overhaul Manual, P/N 411568, Section 72-00, Fits and Clearances. (2) If the threads of the elbow. P/N 424790, or fuel control cover P/N 704972-1, are found worn replace with new or serviceable parts of same part number or with P/N 483848 elbow and associated hardware in accordance with Pratt & Whitney Service Bulletin No. 1511 Revision 4, dated June 20, 1969, or later FAA approved revision. (c) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust repetitive inspection intervals specified in this AD. Amendment 39-1616 became effective April 11, 1973. This amendment 39-1630 becomes effectiveupon publication in the Federal Register.
96-12-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125 series 800A and Model Hawker 800 airplanes, that requires modification of the airframe structure in the lower area of the fuselage aft of the wing rear spar. For certain airplanes, this amendment also requires a functional test to determine if a particular bolt fouls the flap control system. This amendment is prompted by reports of restricted control of the aileron due to water accumulation that froze in the area around an aileron pulley located in the lower area of the fuselage aft of the wing rear spar. The actions specified by this AD are intended to prevent such water accumulation, which could freeze and result in restricted control of the ailerons; subsequently, this could reduce the pilot's ability to initiate roll control during critical phases of flight.
2004-11-02: This amendment adopts a new airworthiness directive (AD), [[Page 31001]] applicable to certain Saab Model SAAB SF340A and Model SAAB 340B series airplanes, that requires inspections of the internal and external structure of the nacelles for cracks, deformations, or other damage, and corrective actions if necessary. This action is necessary to prevent fatigue cracks in the outer flange of the nacelle frame, which could result in reduced structural integrity of the nacelle supporting structure. This action is intended to address the identified unsafe condition.
96-12-18: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model DC-10 series airplanes and Model MD-11F airplanes. Among other things, this amendment requires repetitive leak checks of the lavatory drain system and repair, if necessary; provides for the option of revising the FAA-approved maintenance program to include a schedule of leak checks; and requires the installation of a cap on the flush/fill line. This amendment is prompted by continuing reports of damage to engines and airframes, separation of engines from airplanes, and damage to property on the ground, caused by "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent such damage associated with the problems of "blue ice."
2021-23-11: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 45 airplanes. This AD was prompted by a report of a fuel leak due to a cracked fuel line between the engine fuel control and the engine fuel flow meter. This AD requires replacing the existing fuel flow meter bracket assembly with a redesigned bracket assembly and reporting information to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
65-14-05: 65-14-05 LOCKHEED: Amdt. 39-95 Part 39 Federal Register June 26, 1965. Applies to Model 1329 Aircraft Serial Numbers 5001 through 5057. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent improper engine fire and overheat warning indications, accomplish the following: Inspect in the following manner all engine fire (forward) and overheat (aft) detector electrical systems to ascertain that each detector is properly connected to the correct fire warning control unit: (a) Disconnect electrical connector from the control unit corresponding to the detector element to be checked. (b) Connect one lead of a Simpson 260 meter, or equivalent, to pin C or D of the fire warning control unit connector, ships, wiring, and one lead to ground. (c) Set the meter to read a resistance of 10,000 Ohms or greater, depending on the unit being checked and the temperature of the unit. (d) Applyheat to a segment of the detector element being checked, using a heater blower with a temperature range of 500 degrees to 750 degrees F., or equivalent, and observe the meter reading. The blower should be held approximately 1/2 inch from the element. Make sure no wind interferes to cut down the heat conduction to the element and to assure a good meter reading. (e) In approximately 5 to 10 seconds of elapsed time after application of heat, the meter reading should decrease at a moderate rate. A decreasing resistance reading indicates correct wire connections. (f) After the above procedure is followed and the results are not as required, a complete check of the fire warning circuitry for the engine in error must be made using Lockheed Drawing No. JR156 (wiring diagram). Correct all discrepancies. (g) When all circuits are in proper operating condition, the aircraft may be returned to service. Other means of compliance with the requirements of this directive may be utilized if approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (Lockheed Alert Service Bulletins Nos. 329-202 and 329-202A cover this same subject.) This directive effective June 26, 1965.
2021-23-14: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of erratic electrical system status on the push button annunciators (PBAs) and the engine instrument and crew alerting system (EICAS). This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures to be applied during erroneous electrical status indication conditions. The FAA is issuing this AD to address the unsafe condition on these products.
67-09-03: 67-09-03 BRITISH AIRCRAFT: Amdt. 39-372 Part 39 Federal Register March 21, 1967. Applies to Model BAC 1-11 400 Series Airplanes. Compliance required as indicated. To prevent interference between the flap jack screw and flap carriage assembly, accomplish the following: (a) Within the next 500 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 1,000 hours' time in service, measure the clearance between the head of the nut on flap screw jack P/N CH526-010 and the inside faces of the lower rollers on the aft flap carriages P/N AK09 A1263 and AK09 A1265 and AK09 A1266 at all 8 screw jack positions in accordance with BAC Alert Service Bulletin 27-A-PM2469 or later ARB-approved issue. If clearance is less than 0.025 inch, rework the nut stop head radius in accordance with BAC Service Bulletin No. 27-A-PM2469 or later ARB-approved issue. (b) The repetitive inspections required in (a) may be discontinued if the airplanes are modified in accordance with BAC Service Bulletin 27-A-PM2469 paragraph (a) or (b) and PM2469 paragraph (c) and PM2469 paragraph (d) or (e) and PM2469 paragraph (f) or (g) or later ARB-approved issue. This directive effective April 20, 1967.
2004-10-15: The FAA adopts a new airworthiness directive (AD) for certain GARMIN International Inc. GTX 330/GTX 330D Mode S transponders that are installed on aircraft. This AD requires you to install GTX 330/330D Software Upgrade Version 3.03, 3.04, or 3.05. This AD is the result of observations that the GTX 330 and GTX 330D may detect, from other aircraft, the S1 (suppression) interrogating pulse below the Minimum Trigger Level (MTL) and, in some circumstances, not reply. The GTX 330/330D should still reply even if it detects S1 interrogating pulses below the MTL. We are issuing this AD to prevent interrogating aircraft from possibly receiving inaccurate replies due to suppression from aircraft equipped with the GTX 330/330D Mode S Transponders when the pulses are below the MTL. The inaccurrate replies could result in reduced vertical separation or unsafe TCAS resolution advisories.
2021-23-04: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109E helicopters. This AD was prompted by reports of cracking in the center fuselage frame assembly in the intersection of the lateral pylon and floor spar at station (STA) 1815 on the left- and right-hand sides. This AD requires repetitive inspections of the intersection of the lateral pylon and floor spar at STA 1815 for cracking and, depending on the findings, repair, 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.
2021-23-10: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW109SP helicopters. This AD was prompted by reports of an ineligible hydraulic pump being installed on Model AW109SP helicopters. This AD requires inspecting each hydraulic pump for damage and, depending on the inspections results, removing parts from service and accomplishing other corrective actions. This AD also requires removing certain parts from service before they exceed their life limits. The corrective actions are required to be accomplished 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.