Results
2017-15-14: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by a report indicating that an oxygen bottle was found loose while the clamp strap was in the locked position. This AD requires modification of the clamp strap and installation of additional shims, as applicable, to the flight crew's oxygen bottles' retaining structures. We are issuing this AD to address the unsafe condition on these products.
2005-20-37: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, - 145LR, -145XR, -145MP, and -145EP airplanes. This AD requires repetitive detailed inspections for surface bruising of the main landing gear (MLG) trailing arms and integrity of the MLG pivot axle sealant, and corrective actions if necessary. This AD also provides for optional terminating action for the repetitive detailed inspections. This AD results from a report of a fractured axle of the trailing arm of the MLG due to corrosion of the axle. We are issuing this AD to prevent a broken trailing arm and consequent failure of the MLG, which could lead to loss of control and damage to the airplane during takeoff or landing.
2017-15-15: We are superseding Airworthiness Directive (AD) 2002-19-01 for SOCATA Model TBM 700 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 flight control wheel traveling beyond normal roll control limits and jamming in a position that could cause loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
79-13-08: 79-13-08 AIRBORNE MANUFACTURING COMPANY: Amendment 39-3507. Applies to the below listed part number Dry Air Pumps installed on piston engine aircraft certificated in all categories. AIRBORNE PART NUMBER SERIAL NUMBERS 211 CC 5E9318 thru 5E9347 5E9407 thru 5E11419 211 CC-9 5E616 thru 5E715 211 CC TR 5E1264 thru 5E1406 212 CW 5E3403 thru 5E4197 5E9129E thru 5E9131E 212 CW-6 5E9 thru 5E25 242 CW-4 5E8 thru 5E11 441 CC 5E332 thru 5E401 5E450 thru 5E483 441 CC-7 5E911 thru 5E981 441 CC-9 5E75 thru 5E80 441 CC-11 5E4 441 CC-13 5E7 thru 5E12 441 CC-17 5E106 thru 5E116 442 CW 5E926 thru 5E1023 442 CW-4 5E137 thru 5E149 442 CW-6 5E765 thru 5E785 442 CW-8 5E114 442 CW-12 5E431 thru 5E435 These pumps were not available for installation before May 15, 1979, therefore, dry air pumps installed previous to that date are exempt from this AD. Compliance is required prior to next flight. To prevent catastrophic failure of the pump and subsequent loss of the vacuum system remove above listed dry air pumps from service and replace with an airworthy pump of the same part number. An airworthy pump is one which has a serial number not listed above or if listed above also has an "A" or "2" ink stamped by the manufacturer with black ink on the periphery of the body near the mounting flange. The aircraft may be flown under day VFR conditions in accordance with FAR 21.197 to a base where the corrective action can be performed. Additional information concerning disposition of the affected pumps is contained in Airborne Manufacturing Company, Aviation Products Group, Service Letter Number 22A, dated June 5, 1979. This amendment becomes effective upon publication in the Federal Register, as to all persons except those to whom it was made immediately effective by the airmail letter dated June 7, 1979, which contained this amendment.
2005-20-28: The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplane models, as specified above. This AD requires modifying the floor proximity emergency escape path marking system. This AD results from information that the existing system design for interconnection of the emergency power supply units of the floor proximity emergency escape path marking system does not provide adequate floor path lighting and marking for safe evacuation of the airplane in the event of an emergency. We are issuing this AD to prevent inadequate lighting and marking of the escape path, which could delay or impede the flightcrew and passengers when exiting the airplane during an emergency landing.
98-12-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires modifying the low pitch stop switch support. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent low pitch stop switch support displacement, which could result in an improper cockpit indication that the propeller is in the Beta range and cause loss of control of the airplane.
98-12-09: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. Model TPE331 series turboprop engines, that requires removal of suspect fuel manifold assemblies and replacement with serviceable assemblies. This amendment is prompted by an FAA investigation into Hoses Unlimited's repairs of TPE331 fuel manifolds, which were not approved by the FAA. The actions specified by this AD are intended to prevent fuel leakage at the fuel manifold fittings, resulting in fuel spraying on hot turbine components, which could result in an engine fire.
78-23-05: 78-23-05 CANADAIR: Amendment 39-3338. Applies to CL-44D4 and CL-44J airplanes, certificated in all categories. To preclude loss of elevator travel due to spline wear; (a) Within the next 100 hours in service after the effective date of this airworthiness directive, unless already accomplished within the last 900 hours in service, and thereafter at intervals not to exceed 1000 hours in service, accomplish the following: (1) Visually inspect each elevator resilient stop mechanism at spanwise stations 43 and 178 for wear, in accordance with Inspection Data paragraph of Canadair Service Information Circular (SIC) Number 406-CL44, dated May 17, 1977, or equivalent. (2) Prior to next flight, repair or replace worn parts with parts of the same part number and install in accordance with instructions outlined in Chapter 55-20-2 of the Canadair CL-44 Overhaul Manual, dated June 19, 1964, or equivalent. (b) Equivalent inspections and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance times specified in this AD. This amendment is effective November 10, 1978.
2005-20-21: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Model F27 Mark 050 airplanes. This AD requires repetitive visual checks for oil leaks of both engines between the spinner and the engine cowling, and directly behind the heated intake lip of the engine; repetitive inspections for oil leaks at the feathering pump on both engines; and corrective actions if necessary. This AD results from reports of oil leakage at the engine feathering pump. We are issuing this AD to prevent oil loss from the feathering pump, which could cause the engine to shut down in flight.
98-12-04: This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG-500M gliders. This AD requires installing a rudder gap seal and modifying the cooling liquid reservoir mount. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent rudder vibrations caused by flow separation at the rudder gap, which could result in flutter with consequent loss of rudder control.
63-06-03: 63-06-03 GENERAL DYNAMICS/CONVAIR: Amdt. 545 Part 507 Federal Register March 20, 1963. Applies to All Models 340 and 440 Series Aircraft Equipped With a Bendix Redbank Type 35E05 Fault Detection Panel. Compliance required within the next 300 hours' time in service following the effective date of this AD, unless already accomplished. To prevent the loss of electrical power, modify the type 35E05 fault detection panel by installing a blocking rectifier (G.E. IN-93 or FAA approved equivalent). Solder the negative lead to lug No. 3 of the locating relay and the positive lead to terminal No. P on the terminal board. (Convair Airgram No. 200 dated September 24, 1956, and Bendix Redbank Service Bulletin No. R-47 pertains to this same modification.) This directive effective March 20, 1963.
82-23-06: 82-23-06 FAIRCHILD SWEARINGEN: Amendment 39-4493. Applies to Models SA 226-T(B) (S/N T(B) 276, T(B) 292 through T(B) 397); SA 226-T (S/N T201 through T275 and T277 through T291); SA 226-AT (S/N AT001 through AT074); SA 226-TC (S/N TC201 through TC396) airplanes certificated in any category. COMPLIANCE: Required within the next 50 hours time-in-service unless already accomplished. To prevent the main landing gear doors from shifting and locking the gear in the up position, accomplish the following: (a) Inspect, check, and modify the main landing gear door installation in accordance with Accomplishment Instructions IIA through IIL of Fairchild Swearingen Service Bulletin SB 32-026 dated October 16, 1980, as supplemented by the instructions below. (1) When replacing the bushings and refitting the doors for final assembly, assure that the bushings are properly lubricated (do not use thin-film, spray-on liquids which will wash out the grease from the Oilite bushings; use a thick, permanent lubricant such as Lubriplate). (2) Observe standard torque for AN3 bolts. (3) Assure that the door hinge bolts clamp completely and the doors move freely. (4) Remove stripped nutplates and replace them with a castellated nut and cotter pin. Instructions for accomplishing this may be obtained from Fairchild Swearingen Corporation. Use of the drilled bolt and safety wire procedures specified in paragraphs IIG and IIJ of Fairchild Swearingen Service Bulletin SB 32-026 is not required if a castellated nut and cotter pin are used. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, Aircraft Certification Division, ASW-100, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 624-4911, extension 511. This amendment becomes effective on November 15, 1982.
2005-20-15: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an inspection of the rudder pedal torque tube assembly for cracking; an inspection of the torque tube assembly to determine the thickness of the torque tube wall, if necessary; and replacing the rudder torque tube with a new or serviceable rudder torque tube, if necessary. This AD results from a report of a broken rudder pedal torque tube. We are issuing this AD to prevent failure of a rudder pedal torque tube, which could result in loss of rudder control and nose wheel steering controlled by the rudder pedal, and consequent reduced controllability of the airplane.
98-11-24: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-30, SD3-60, SD3-SHERPA, and SD3-60 SHERPA series airplanes. This amendment requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
98-11-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and -320, and Model ATR72 series airplanes, that requires modification of the engine fuel drainage system. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fuel from overflowing into the engine nacelle, which could result in a fire in the nacelle.
2005-20-22: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model ATP airplanes. This AD requires repetitive inspections for environmental damage, including corrosion, of the fuselage and wing structure, and corrective actions if necessary. This AD results from information indicating the potential for environmental damage of the fuselage and wing structure. We are issuing this AD to detect and correct such damage, including corrosion, in the fuselage and wing structure, which could result in cracking and consequent reduced structural integrity of the fuselage and wing structure.
2002-10-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 58P, 60, A60, B60, and 65-88 airplanes. This AD requires you to install new exterior operating instruction placards for the exit doors. This AD is the result of Raytheon improving the visibility and understandability of the door operating instruction placards. This was done as a result of difficulty opening the emergency exits of a similar type design airplane. The actions specified by this AD are intended to assure that clear and complete operating instructions are visible for opening the emergency exit doors. If not visible and understandable, this could result in the inability to open the exit door during an emergency situation.
2017-15-02: We are adopting a new airworthiness directive (AD) for Bell Model 212 and Model 412 helicopters. This AD requires replacing certain oil and fuel check valves and prohibits installing them on any helicopter. This AD is prompted by a report of cracked or leaking check valves. These actions are intended to address an unsafe condition on these helicopters.
98-11-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires an inspection to determine if the latching lever pin of the speed brake passes an axial force check, and a visual inspection to determine if the staking of the latching lever pin is acceptable; and follow-on corrective action, if necessary. This amendment is prompted by reports that the speed brake handle jammed in the ground spoiler position. The actions specified by this AD are intended to prevent a jammed speed brake handle pin, which could result in retraction of the spoilers and full advancement of the left throttle during a go- around.
79-21-03: 79-21-03 BRITTEN-NORMAN (Bembridge) LTD.: Amendment 39-3588. Applies to BN-2A Mk III Series Trislander airplanes, certificated in all categories, which do not incorporate Britten-Norman modification NB/M/679. Compliance is required prior to the accumulation of 1000 hours time in service or within 200 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent failure of the elevator trim tab cable and the possible resultant trim tab flutter, replace the existing elevator trim tab cables, P/Ns NB-45-B-2333, 2231, 2229 with new cables P/Ns NB-45-B-2747, 2749, 2745, respectively, in accordance with Britten-Norman Service Bulletin BN-2/SB.75, dated June 27, 1974, or an equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium. This amendment becomes effective November 12, 1979.
2002-10-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect cracks in various areas of the fuselage internal structure, and repair, if necessary. This amendment adds new repetitive inspections for cracking of certain areas of the upper chord of the upper deck floor beams, and repair, if necessary. This amendment is prompted by the results of fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. The actions specified by this AD are intended to prevent loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane. \n\n\tThe incorporation by reference of Boeing Service Bulletin 747-53-2349, dated June 27, 1991, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 11, 1993 (58 FR 27927, May 12, 1993).
98-11-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that currently requires that the FAA-approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item, and repair of cracked structure. That AD was prompted by a structural re-evaluation by the manufacturer that identified additional structural elements where, if damage were to occur, supplemental inspections may be required for timely detection. This amendment requires additional and expanded inspections, and repair of cracked structure. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to ensure the continued structural integrity of the entire Boeing Model 727 fleet.
98-10-11: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-3, -3B, -3C, -5, -5B, and -5C series turbofan engines. This action supersedes telegraphic AD T97-25-51 that currently requires removal of one engine from an aircraft, and replacement with a serviceable engine or replacement of parts, if both engines are equipped with a specific accessory gearbox (AGB) starter gearshaft or transfer gearbox (TGB) input bevel gear, and daily checks of the AGB/TGB magnetic chip detector. This amendment is prompted by further investigation that has revealed that certain TGB output bevel gears and AGB intermediate gear assemblies on CFM56-3, -3B, and -3C series engines, and AGB gearshaft cluster spur assemblies on CFM56-5, -5B, and -5C series engines could also be affected. The actions specified by this AD are intended to prevent inflight engine shutdowns due to an AGB starter gearshaft, TGB input bevel gear, TGB output bevel gear, AGB gearshaft cluster spur assembly or AGB intermediate gear assembly failure.
98-10-12: This amendment adopts a new airworthiness directive (AD) that applies to all REVO, Incorporated (REVO) Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 airplanes. This action requires measuring for a clearance of 5/32 of an inch between the attachment fitting and the horizontal stabilizer rear beam, and a clearance of 1/16 of an inch between the attachment fitting and the stabilizer skin. If either area does not meet these minimum measurements, this AD requires removing the affected horizontal tail half from the airplane and inspecting the attachment fitting for any evidence of fretting, cracking, or corrosion. If cracks, fretting or corrosion are present, the attachment fitting must be replaced with a new fitting, and the stabilizer skin must be trimmed to provide a positive clearance for the fitting. This action is prompted by an incident report of an airplane losing control during flight after the attachment fitting to the horizontal stabilizer fractured. The actions specified by this AD are intended to prevent fatigue cracks to the horizontal and vertical stabilizer attachment fitting, which could result in loss of control of the airplane.
72-02-02: 72-02-02 GRUMMAN AIRCRAFT: Amendment 39-1374 as amended by Amendment 39-1538. Applies to Type G-164A airplanes equipped with any P&W R-1340 model engine. Compliance required within the next 25 hours in service, unless already accomplished, after the effective date of this AD. To preclude the possibility of fuel leakage resulting from cracks in the threaded area of certain aluminum alloy fuel line fittings, accomplish the following: 1. Replace two AN911-3D pipe thread nipples located in the carburetor inlet line and one AN911-3D nipple located at the outlet boss of the in-line fuel strainer mounted on the firewall bulkhead with corrosion resistant steel nipples P/N AN911-3S, AN911-3K or AN911-3J. 2. Replace the aluminum AN912-4D reducer at the carburetor fuel inlet boss with corrosion resistant steel reducers P/N AN912-4S or AN912-4K or AN912-4J. Grumman S/B No. 46 and 49 covers this same subject. Amendment 39-1374 was effective January 20, 1972. This Amendment 39-1538 is effective October 18, 1972.