Results
99-11-10: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332L2 helicopters with a certain power-loss printed circuit board (PCB) installed. This action requires replacing that power-loss PCB with an airworthy power-loss PCB. This amendment is prompted by malfunctions discovered during environmental testing of the power-loss PCB conducted by the manufacturer. The actions specified in this AD are intended to prevent incorrect engine status indications, random activation of the maximum rotor revolutions-per-minute (RPM) alarm, and failure to reset the One-Engine Inoperative (OEI) logic after an actual loss of power from one engine.
2003-03-21: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada (PWC) PW500 series turbofan engines. This action requires a one-time visual inspection and re-marking, or in lieu of inspection, replacement of certain part numbers (P/N's) of the flexible fuel tube located between the fuel/oil heat exchanger and the integral fuel control unit-fuel pump. This amendment is prompted by reports of fuel found dripping from engine nacelles caused by leaking flexible fuel tubes. The actions specified in this AD are intended to prevent a fire in the engine nacelle.
99-10-16: This amendment adopts a new airworthiness directive (AD), applicable to all Mitsubishi Model YS-11 series airplanes, that requires repetitive inspections to detect fatigue cracking in the manhole doublers of the lower wing panels; and repair, if necessary. This amendment also requires eventual modification of screw holes in the manhole doublers of the lower wing panels, which constitutes terminating action for the repetitive inspections required by this AD. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking in the manhole doublers of the lower wing panels, which could result in failure of the wing structure.
99-10-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and 747-SP series airplanes and military type E-4B airplanes, that requires repetitive inspections to detect cracking of the wing front spar web, and repair of cracked structure. This amendment also provides for optional terminating action for the repetitive inspection requirements. This amendment is prompted by reports indicating that fatigue cracks were found on the aft surface of the wing front spar web. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in a fuel leak, and consequent increased risk of a fire.
99-10-15: This amendment adopts a new airworthiness directive (AD) that is applicable to AS332L2 helicopters. This action requires inspecting each main rotor head drag damper (damper) for a tear, crack, or bonding separation in the elastomer and, if necessary, replacing the damper with an airworthy damper. This amendment is prompted by a report of increased helicopter vibration in flight that was traced to the delamination of the elastomer on a damper. This condition, if not corrected, could result in failure of a damper and subsequent loss of control of the helicopter.
84-01-52 R1: 84-01-52 R1 WESTLAND HELICOPTERS LIMITED: Amendment 39-4845. Applies to Westland Model 30 Series 100 helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent failure of the tail rotor gearbox input pitch control lever and subsequent loss of control in flight accomplish the following: (a) Prior to further flight comply with the requirements of Westland Service Bulletins W30-67-26, Revision 3, and W30-65-14 or subsequent FAA approved revisions or FAA approved equivalent. (b) Remove from service all tail rotor gearbox input pitch control levers P/N WK 3068-0037-101 with 200 hours time in service and replace with a serviceable part. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, Brussels Aircraft Certification Office, c/o United States Embassy, Brussels, Belgium. This amendment becomes effective April 16, 1984, as to all persons except those persons to whom it was made immediately effective by priority letter AD T84-01-52, issued December 30, 1983, which contained this amendment.
2000-24-03 R1: The FAA is revising an existing airworthiness directive (AD) that applies to all AvCraft Dornier Model 328-100 airplanes. That AD currently requires revising the airplane flight manual (AFM) to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. The existing AD also requires, for certain airplanes, modifying of the flap actuators of the flight controls. We issued that AD to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun. This new AD allows the removal of the AFM revisions after modifying the flap actuators of the flight controls. This AD results from the determination that the AFM revisions are not necessary after modifying the flap actuators of the flight controls. We are issuing this AD to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
2019-24-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by an investigation that identified the cargo lining gutter assembly would be unable to drain a certain quantity of water in case of leakage or rupture of certain water pipes. This AD requires modification of the cargo lining gutter assemblies, 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.
2009-15-18: We are adopting a new airworthiness directive (AD) for the products listed above. 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 describes the unsafe condition as: It was found one occurrence of a fuel booster pump circuit br[e]aker opening during an engine maintenance servicing. An inspection inside the fuel tank revealed the fuel booster pump[']s electrical harness chafing against its body, causing the loss of the electrical wiring protection and resulting in a short circuit. Further in-tank inspections have showed other fuel booster pump electrical harnesses chafing either with the pump body and/or with adjacent fuel lines, causing damage to the harness protective layers and resulting * * * [in a] possible ignition source inside the fuel tank. * * * * * We are issuing this AD to require actions to correct theunsafe condition on these products.
99-10-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires inspecting to assure that the fuel filler cap has a 2.5 millimeter (mm) diameter hole drilled through it or that a vinyl piping is connected to the filler neck inside the cabin. If neither of these items exists, this AD requires replacing the fuel filler cap with a fuel filler cap that has a 2.5 mm diameter hole drilled through it. 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 detect and correct the installation of improperly designed fuel venting system parts, which could result in an inadequate fuel supply to the engine with loss of engine power.
72-26-01: 72-26-01 BEECH: Amdt. 39-1576. Applies to 99 series (Serial Numbers U-1 thru U-148) airplanes. Compliance: Required as indicated, unless already accomplished. To reduce the possibility that baggage or cargo in the nose compartment might become a hazard by shifting, accomplish either Paragraph A or Paragraph B within 200 hours' time in service after the effective date of this AD: A) Install an additional latch on the nose compartment door as provided in Beech Kit No. 99-4019S or any FAA-approved equivalent, or B) Install a baggage/cargo restraint system in accordance with data approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective December 21, 1972.
2006-04-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A321-111, -112, and -131 series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar; and repair, if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. This AD adds inspections of three additional mounting holes and revises the thresholds for the currently required inspections. This AD results from manufacturer analysis of the fatigue and damage tolerance of the area surrounding certain mounting holes of the MLG. We are issuing this AD to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane.
2019-23-08: The FAA is superseding Airworthiness Directive (AD) 2019-03- 19, which applied to all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. AD 2019-03-19 required a functional check of certain fuel probes, and replacement with a serviceable part if necessary. This AD continues to require a functional check of certain fuel probes, and replacement with a serviceable part if necessary. This AD also revises the definition of a ``serviceable part.'' This AD was prompted by reports that certain fuel probes indicated misleading fuel quantities on the engine indicating and crew alerting system (EICAS). The FAA is issuing this AD to address the unsafe condition on these products.
2003-03-15: This amendment adopts a new airworthiness directive (AD), applicable to various Boeing and McDonnell Douglas transport category airplanes. This AD requires revising the Airplane Flight Manual (AFM) to advise the flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning horn sounds. This action is necessary to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
2006-04-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus transport category airplanes. This AD requires replacing the existing cabin altitude indicator in the cabin pressure control panel with a new, improved cabin altitude indicator. This AD results from a report of injuries occurring on in-service airplanes when crewmembers forcibly initiated opening of passenger/crew doors against residual pressure causing the doors to rapidly open. We are issuing this AD to prevent injury to crewmembers, and subsequent damage to the airplane caused by rapid opening of the door.
61-26-04: 61-26-04 PRATT & WHITNEY: Amdt. 380 Part 507 Federal Register December 21, 1961. Applies to All JT3D-1, JT3D-1-MC6, JT3D-1-MC7, and JT3D-3 Turbofan Engines. Compliance required as indicated. Due to recent inflight engine fires resulting from fuel leakage occurring at the fuel transfer points where the fuel pressurizing and dump valve attaches to the engine, the following is required: (a) All Pratt & Whitney aircraft JT3D-1, JT3D-1-MC6, JT3D-1-MC7, and JT3D-3 turbofan engines installed in Boeing aircraft. Compliance required within the next 100 hours' time in service unless already accomplished within the last 200 hours' time in service and every 300 hours' time in service thereafter until metal chevron type seals are incorporated. Replace the P/N's 443098, 379644, 371339, or 367444 fuel pressurizing and dump valve seals with new seals of the same part numbers where the pressurizing and dump valve assembly attaches to the fuel manifold inlet distributor assembly. (Pratt & Whitney Aircraft telegraphic message dated September 28, 1961, covers the same subject.) (b) All Pratt & Whitney aircraft JT3D-1, JT3D-1-MC6, JT3D-1-MC7, and JT3D-3 turbofan engines installed in Boeing and Douglas aircraft. Compliance required not later than the first engine overhaul after June 1, 1962. Rework the engine in accordance with Pratt & Whitney Aircraft Turbojet Engine Service Bulletin No. 274 which provides for metal chevron type seals. (c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective December 21, 1961. Revised March 16, 1962.
2019-23-17: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 900EX and Model FALCON 2000EX airplanes. This AD was prompted by reports of iced angle-of-attack (AoA) probes after take-off, with associated misleading airspeed indication and/or misleading stall warning. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with updated procedures related to manually activating heating of the AoA probes during line up, 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.
2019-14-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-111, -112, -115, and -131 airplanes, and Model A320-214 and -232 airplanes. This AD was prompted by a report of the fracture of a main landing gear (MLG) sliding tube axle, and an investigation that determined the cause to be an incorrect repair. This AD requires a repetitive magnetic particle inspection (MPI) of affected MLG sliding tubes for discrepancies; a one-time Barkhausen noise inspection (BNI) or alternative non-destructive test (NDT) inspection, and a detailed visual inspection of affected MLG sliding tube axles for discrepancies; and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. Accomplishing the BNI and applicable corrective actions, or replacing the affected parts, constitutes terminating action for the repetitive MPI. The FAA is issuing this AD to address the unsafe condition on these products.
99-09-09: This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASH 26E sailplanes. This AD requires inspecting the red silicone tube of the rotor interior air cooling system (just in front of the carburetor ) for oil leaks and the heat damping layer of the lower exhaust damper fairing for oil contamination, and replacing the applicable parts where oil leakage or contamination is found. 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 detect and correct any oil-contaminated exhaust damper fairing caused by oil leakage in the red silicone tube of the rotor interior air cooling system, which could result in an exhaust fire and/or an explosion.
80-07-01: 80-07-01 CESSNA: Amendment 39-3719. Applies to the following models and serial number airplanes certificated in all categories. MODEL SERIAL NUMBER TU206 series (Serial Numbers U206-0487 through U206-1444, U20601445 through U20605619) airplanes; TP206 series (Serial Numbers P206-0001, P206-0191 through P206-0603, P20600604 through P20600647) airplanes; T207 series (Serial Numbers 20700001 through 20700603) airplanes; T210 series (Serial Numbers T210-000l through T210-0454, 21058140, 21059200 through 21063954) airplanes. COMPLIANCE: Required as indicated unless already accomplished. To preclude failure of the engine oil pressure and scavenge pump drive shaft and resulting oil pressure loss caused by turbocharger oil scavenge pump ingestion of failed turbocharger thrust bearing anti-rotation pins, within the next 10 hours' time-in-service after the effective date of this AD, accomplish the following: A) Check the Cessna P/N C295001-0101 (AiResearch P/N 406610-5) turbocharger nameplate to determine if the serial number is HI0101 through HI0175. The owner/operator may perform serial number check only provided any cowling disassembly/reassembly is accomplished in accordance with applicable Cessna Service Manuals. B) If the serial number on the turbocharger nameplate is not one of those specified in Paragraph A), make an entry in the aircraft maintenance records indicating compliance with this AD and no further action is required. C) If the serial number on the turbocharger nameplate is one of those specified in Paragraph A): 1. Remove the turbocharger oil return hose and fitting and visually inspect to assure that a failed thrust bearing anti-rotation pin is not trapped in the hose, check valve, or oil scavenge pump inlet. 2. Replace the turbocharger in accordance with the applicable Cessna Service Manual with a replacement unit which is not one of those listed in Paragraph A). D) Within 24 hours time-in-service after the turbocharger replacement required by Paragraph C) of this AD, and prior to disposition of the turbocharger, contact your local Flight Standards District Office, General Aviation District Office or Engineering and Manufacturing District Office for turbocharger disposition procedure. E) Airplanes may be flown in accordance with FAR 21.197 to a location where the replacement required by Paragraph C) may be accomplished. F) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office, Federal Aviation Administration, Room 238, Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective on March 28, 1980, to all persons except those to whom it has already been made effective by airmail letter from the FAA dated February 25, 1980.
2006-04-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310-300 series airplanes. This AD requires inspecting the pilot's and co-pilot's seats to determine if a certain actuator having a certain part number is installed, and corrective action if necessary. This AD results from a production defect found in certain actuators during overhaul of the pilot's and co-pilot's seats. We are issuing this AD to prevent uncommanded movement of the pilot's or co-pilot's seat, which could result in interference with the operation of the airplane and consequent temporary loss of airplane control.
2019-22-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report of fatigue cracking in the lug root radius of a main landing gear (MLG) aft hanger link lug fitting. This AD requires repetitive surface high frequency eddy current (HFEC) inspections of the left and right side MLG aft hanger link lug fitting for cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2019-23-12: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires applying sealant to the fasteners in the fuel tanks, replacing wire bundle clamps external to the fuel tanks, and installing Teflon sleeving under the clamps. The FAA is issuing this AD to address the unsafe condition on these products.
99-09-16: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C helicopters, that currently requires a visual inspection of the main rotor blade reinforcement strips for debonding between the reinforcement strips of the blade; and a visual inspection of the main rotor blade (blade) skin for cracks or corrosion, and replacement of the blade with an airworthy blade if certain debonding or a crack or corrosion is found. This amendment requires additional inspections using a tapping method, redefines the area to be inspected, and increases the repetitive inspection interval. This amendment is prompted by an in-flight failure of a main rotor blade on a Eurocopter SE 3130 helicopter. The actions specified by this AD are intended to detect bonding separation, cracks, or corrosion in the area of the blade root reinforcement strip, and to prevent failure of a blade and subsequent loss of control of the helicopter.
61-22-04: 61-22-04 CONVAIR: Amdt. 352 Part 507 Federal Register October 21, 1961. Applies to All Model 22 (880) Aircraft. Compliance required as indicated. Reinspection of the pressurization system indicates that under certain conditions a single malfunction in the pressurization static system could cause the aircraft to be pressurized beyond the structural limits. To provide the required level of safety, the following, or FAA approved equivalent shall be accomplished within the next 250 hours' time in service after effective date of this AD: (a) Rework existing static system to provide either (1) A separate static sensing source for each cabin outflow valve, or (2) A static sensing source common to the two outflow valves and a separate static sensing source for the cabin pressure controller. (Convair Service Bulletin No. 21-23 dated March 25, 1961, covers the same subject.) This directive effective November 21, 1961.