Results
58-19-03: 58-19-03 MOONEY: Applies to Mark 20A, Items 1 and 3 to Serial Numbers 1201 Through 1275, Items 2 and 4 to Serial Numbers 1201 Through 1257, Item 5 to Serial Numbers 1201 Through 1259. Compliance required by December 1, 1958. Several cases have occurred in which the carburetor air box cross vanes P/N 6235 have cracked and broken off. This type failure could cause loss of power if the vanes are drawn into the carburetor opening. Cracking of carburetor air boxes around the neck has also been reported. The following rework is therefore necessary: 1. Remove the carburetor air box and inspect for cracks. Repair as required by welding. 2. Add an aluminum brace to each side of the air box neck. 3. Remove cross vanes located in air box neck. 4. Shorten fuel overflow drain tube on bottom of air box. 5. Enlarge fuel overflow drain tube hole in bottom of cowl and replace existing grommet. (Mooney Service Letter 20-37 covers this same subject.)
68-20-05: 68-20-05 AERONCA: Amendment 39-662. Applies to Models 15AC and S15AC, S/N's 15AC-1 and up. To be accomplished within 25 hours in service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time in service from the last inspection. As a result of a number of forced landings due to fuel exhaustion caused by a collapsed fuel tank or siphoning of fuel, accomplish the following: (a) Determine that the wing fuel cells are lying flat and follow the contour of the wing cavity. (b) Inspect fuel cell filler caps for security and identification. Aeronca unvented spring loaded cap, P/N 1-3738 or FAA approved equivalent must be installed. A drawing of P/N 1-3738 is available from Aeronca, Inc., Middletown, Ohio 45042. (c) Determine that vent lines are open to both tanks by removing vent lines at tanks and blowing air through the lines. (d) Determine that the small auxiliary vent holes are located at the same height above the wing upper surface. (e) Determine that the vent line is securely clamped and the vent line hose connection has not deteriorated. (f) Determine that angular cut-off at the termination of the main vent line faces forward. The inspection required by this AD constitutes preventive maintenance and may be accomplished by persons so authorized under FAR 43.3. Aircraft log record entry must be made to reflect AD compliance in accordance with FAR 43.9. This amendment is effective October 3, 1968.
2021-02-07: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B64, -1B64/P1, -1B64/P2, -1B67, - 1B67/P1, -1B67/P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, -1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, and -1B76A/P2 model turbofan engines. This AD was prompted by a report of a crack in the outer fuel manifold causing fuel leakage. This AD requires initial and repetitive visual inspections of the cushioned loop clamp (p-clamp) and, depending on the results of the inspection, a spot fluorescent penetrant inspection (FPI) of the outer fuel manifold. Depending on the results of the FPI, this AD may require replacement of the outer fuel manifold. This AD also requires initial and repetitive replacements of the p-clamp. The FAA is issuing this AD to address the unsafe condition on these products.
2004-02-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This action requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the aircraft maintenance manual by incorporating procedures for a functional test of the pilot input lever of the pitch feel simulator unit. This action also requires a functional test of the pilot input lever of the pitch feel simulator unit, and corrective action if necessary. This action is necessary to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
2010-06-08: This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) Model S-76C helicopters. This action requires inspecting the emergency flotation system squib connector (flotation system connector) to determine if a metallic foil shunt is installed. This amendment is prompted by a discovery that a metallic foil shunt meant to prevent inadvertent activation of a flotation system during installation was still installed in the left-hand flotation system connector of a Model S-76C helicopter. The actions specified in this AD are intended to determine if a metallic foil shunt is installed in the flotation system, which could prevent the flotation system from deploying and could prevent the helicopter from staying afloat long enough to enable emergency evacuation after a water landing.
2021-04-09: The FAA is adopting a new airworthiness directive (AD) for certain Yabora Industria Aeronautica S.A. Model EMB-135, EMB-145, -145EP, -145ER, -145LR, -145MP, -145MR, and -145XR airplanes. This AD was prompted by reports that calculations provided by the automatic takeoff thrust control system (ATTCS) are incorrect under certain conditions. This AD requires updating the software of the installed full authority digital engine control (FADEC) systems, as specified in an Agencia Nacional de Aviaco Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-21-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires modification of the support structure of the cargo liner. That AD was prompted by a report of chafing and arcing in the vacuum waste exhaust heater that caused a spark to ignite the surrounding insulation blankets. The actions specified in that AD are intended to prevent fire and/or smoke due to chafing and arcing of the vacuum waste exhaust port heater. This amendment expands the applicability of the existing rule to include additional affected airplanes. It also provides for an alternative method of modification.
2010-09-05: The FAA is superseding an existing airworthiness directive (AD) that applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. The existing AD currently requires doing a detailed inspection of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms for gaps between the swage ring and the aft attach lug, and between the spacer and the aft attach lug; trying to move or rotate the spacer using hand pressure; and replacing any discrepant elevator tab control mechanism, including performing the detailed inspection on the replacement part before and after installation. For certain airplanes, this new AD adds improved repetitive inspections for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms, and replacement if necessary. For certain other airplanes, this new AD adds a one-time inspection for discrepancies of the inboard and outboard aftattach lugs of the left and right elevator control tab mechanisms, and replacement if necessary. For airplanes on which the elevator control tab mechanism is replaced with a certain mechanism, this AD requires repetitive inspections for discrepancies of the elevator control tab mechanism and replacement if necessary. Replacing the elevator control tab mechanism with a new, Boeing-built mechanism terminates the repetitive inspections. This AD results from a report of failure of the aft attach lugs on the left elevator tab control mechanism, which resulted in severe elevator vibration; this event occurred on an airplane on which the existing AD had been done. We are issuing this AD to detect and correct a loose bearing in the aft lug of the elevator tab control mechanism, which could result in unwanted elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and aircraft control.
95-11-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires repetitive replacement of the emergency power switch in the overhead switch panel with a new switch. This amendment is prompted by a report of heavy smoke in the cockpit coming from the overhead switch panel on a Model DC-9-81 series airplane. The actions specified by this AD are intended to ensure replacement of the emergency power switch when it has reached its maximum life limit; an emergency power switch that is not replaced could fail and lead to a short in the electrical circuit, which could result in a fire in the overhead switch panel and smoke in the cockpit.
2021-02-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes and Model C-295 airplanes. This AD was prompted by cracks found on certain left- and right-hand stringers in a certain area of the fuselage. This AD requires repetitive inspections for cracking or broken rivets of certain left- and right-hand stringers and surrounding structure, and repair if necessary, 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.
73-19-08: 73-19-08 BELL: Amdt. 39-1714. Applies to Bell Model 206A, 206B, 206A-1 and 206B- 1 helicopters certificated in all categories. Compliance required as indicated. To prevent possible fatigue cracks in the main rotor retention strap fittings P/N 206-010- 155-11 and -15, and the main rotor retention strap pin, P/N 206-010-123-3, accomplish the following: a. Remove and replace retention strap fittings, P/N 206-010-155-11 and -15 and pins, P/N 206-010-123-3, with 1100 or more hours total time in service on the effective date of this AD within the next 100 hours time in service. b. Remove and replace fittings, P/N 206-010-155-11 and -15 and pins, P/N 206- 010-123-3 with less than 1100 hours total time in service on the effective date of this AD, prior to accumulating 1200 hours total time in service. c. Install replacement fittings and pins in accordance with the appropriate model maintenance and overhaul information manuals and provide corrosion protection as specified in Bell Helicopter Company, Technical Bulletin No. 206-(04-1)-73-1, dated March 9, 1973 or later FAA approved revision or as specified in an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This amendment becomes effective September 15, 1973.
2010-08-04: We are superseding an existing airworthiness directive (AD) for the products listed above. 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: Cracks have been found in the NLG steering jack piston rod adjacent to the eye-end. This was caused by excessive torque which had been applied to the eye-end during assembly of the unit. Severe cracking, if not detected and corrected, can cause the jack to fail during operation, which may lead to loss of directional control of the aeroplane during critical phases of take-off and landing. We are issuing this AD to require actions to correct the unsafe condition on these products. : This AD becomes effective May 19, 2010. On May 19, 2010, the Director of the Federal Register approved the incorporation by reference of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-JA030644, Revision No. 1, dated August 19, 2008; British Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-JM5414, dated August 6, 2004; and APPH Ltd. Bulletin 32-77, dated October 2003, listed in this AD. As of June 26, 2007 (72 FR 28587, May 22, 2007), the Director of the Federal Register approved the incorporation by reference of BAE Systems British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-JA030644, dated October 6, 2003; and APPH Ltd. Service Bulletin 32- 76, Revision 1, dated August 2003, listed in this AD. As of May 22, 2003 (68 FR 16195, April 3, 2003), the Director of the Federal Register approved the incorporation by reference of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32- JA020741, dated November 2, 2002.
2010-08-02: 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: Periodic operational check of the firewall hydraulic shutoff valves [FWSOV], made during routine maintenance, has revealed that the failure rate of that component is significantly higher than expected. Such a dormant failure, when combined with further possible failures, such as engine fire, may lead to an unacceptable reduction of safety margins. The unsafe condition is failure of the firewall hydraulic shutoff valve, which, in combination with an engine fire, could result in the spread of an engine fire beyond the firewall. We are issuing this AD to require actions to correct the unsafe condition on these products.
2004-02-04: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Falcon 900EX series airplanes. This action requires revising the airplane flight manual to advise the flightcrew about limitations on operating in icing conditions, and to require that the airplane be operated per these limitations. This action is necessary to ensure that the flightcrew is aware of the potential for reductions in climb performance in certain situations while operating in icing conditions, and the actions they must take to avoid this condition, which could result in an inability to avoid low- level obstacles during takeoff and consequent controlled flight into terrain. This action is intended to address the identified unsafe condition.
2010-08-05: 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 noticed in production that in the area between frame (FR) C53.9 and FR C55 RH [right-hand], the distance between the route 9R of the In-Flight Entertainment system and the wire harness for the Lower Deck-Mobile Crew Rest system provisions is too small. This limited distance may cause chafing between the affected electrical harness 6581VB and the harness 5495VB or 6938VB. This condition, if not corrected, could lead to the short circuit of wires dedicated to oxygen, which, in case of emergency, could result in a large number of passenger oxygen masks not being supplied with oxygen, possibly causing personal injuries. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
95-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAC 1-11-200 and -400 series airplanes, that requires various inspections to detect discrepancies of fuselage frames at certain stations, and correction of discrepancies; and rework to limit the maximum differential operating pressure of the fuselage. This amendment will also require eventual modification of fuselage frames at certain stations, which will terminate the repetitive inspection requirements. This amendment is prompted by reports of fatigue cracking in certain fuselage frames in the vicinity of the passenger door at floor level due to fatigue-related stress. The actions specified by this AD are intended to detect and prevent such fatigue-related cracking, which could result in reduced structural integrity of the fuselage pressure vessel and possible decompression of the pressurized cabin.
95-19-15: This amendment adopts a new airworthiness directive (AD) that applies to American General Aircraft Corporation (American General) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes. This action requires inspecting the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon), and replacing any damaged parts and repairing any damaged areas; and inspecting the wing spar at the center spar clearance gap for excessive clearance, and shimming the spar if excessive clearance is found. The actions specified by this AD are intended to prevent wing attach shoulder bolt failure, which, if not detected and corrected, could lead to structural damage to the wing/fuselage to the point of failure.
2021-04-05: The FAA is superseding Airworthiness Directive (AD) 2019-23- 15, which applied to certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. AD 2019-23-15 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
66-28-01: 66-28-01 AERO COMMANDER (MEYERS): Amdt. 39-305 Part 39 Federal Register November 9, 1966. Applies to Model 200 Series Airplanes. Compliance required as indicated. To prevent takeoff with excessive elevator trim set, accomplish the following: (a) Before each flight after the effective date of this AD until the elevator trim system has been modified in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region, check operation of elevator trim control for freedom of movement, and check cockpit indicator for accuracy by setting the elevator trim to neutral position as indicated on cockpit indicator, and visually checking elevator trim surface for zero deflection. (b) If trim control is not free and unbinding, or if elevator trim surface is deflected when cockpit indicator indicates neutral trim, repair before further flight in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (c) Before further flight after the effective date of this AD, until the elevator trim system has been modified in accordance with (a), attach the following placard to the instrument panel in full view of the pilot: "Before each flight ensure that elevator trim control is free and unbinding and that elevator trim surface is not defected when cockpit indicator indicates neutral trim." (d) The checks required by this AD may be performed by the pilot. This directive effective November 19, 1966.
2004-02-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires a one-time inspection of the landing gear selector dump valve (LGSDV) to determine the serial number (S/N). For any part with an affected S/N, or for any part for which the S/N cannot be determined, this action requires replacing the LGSDV with a cleaned part having an S/N within the affected range; or replacing the LGSDV with a new or serviceable part that has an S/N outside the affected range. This action is necessary to prevent uncommanded unlocking of the landing gear, which could result in collapse of the landing gear. This action is intended to address the identified unsafe condition.
95-11-02: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes and certain Model MD-11 series airplanes, that currently requires inspections to detect defects in the upper and lower lock links on the nose landing gear (NLG), and rework or replacement of any defective link with a serviceable link. The actions specified by that AD are intended to prevent collapse of the NLG. This amendment requires accomplishment of a certain inspection that constitutes terminating action for the currently required inspections.
2021-01-07: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700 series airplanes. This AD requires repetitive testing to verify correct operation of the smoke clearance mode of the equipment cooling system and low pressure environmental control system, and corrective actions if necessary. This AD also requires installing new relays and changing the wiring to the environmental control system, among other actions. This AD was prompted by a determination that a repetitive test is needed to assess the components on airplanes equipped with a certain air distribution system configuration. The FAA is issuing this AD to address the unsafe condition on these products.
70-15-04: 70-15-04 HANDLEY PAGE: Amdt. 39-1031 as amended by Amendment 39-1317 is further amended by Amendment 39-1556. Applies to all HP-137 Mark I airplanes having Turbomeca Astazou XIV series engines installed. To reduce the possibility of inflight failure of the first stage engine turbine disc and subsequent rupture of fuel and hydraulic lines, accomplish the following: (a) Before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the modification can be performed, modify the fuel and hydraulic systems by relocating the fuel and hydraulic shutoff valves from the engine nacelles to a location on the front spar inboard of the nacelle in accordance with a modification approved by the engineering and manufacturing branch of the nearest FAA regional office. (b) For first stage turbine discs, P/N 0.261.25.013.0, installed on engines that do not incorporate Turbomeca Mods. TU-123, TU-124, and TU-126, before the accumulation of 400hours total disc time in service or 1,000 cycles, whichever occurs sooner, remove the first stage turbine disc from service and replace it with a new disc of the same part number. (c) For first stage turbine discs, P/N 0.261.25.013.0 installed with less than 100 hours' time in service since new on engines that incorporate Turbomeca Mods. TU-123, TU-124, and TU-126, installed in accordance with Turbomeca Service Instructions No. 0123, dated August 27, 1970, No. 0124, dated September 16, 1970, and No. 0127, dated September 16, 1970, respectively, or FAA-approved equivalents, before the accumulation of 750 hours total disc time in service or 2,000 cycles, whichever occurs sooner, remove the first stage turbine disc from service and replace it with a disc of the same part number, which has less than 100 hours' time in service since new. (d) For the purpose of complying with this AD, a cycle constitutes: (1) Any takeoff and landing operation; (2) Any touch and go landing operation; (3) Any other operation where reduction of power is followed by application of takeoff power. Amendment 39-1031 became effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram dated May 15, 1970, which contained this amendment. Amendment 39-1317 became effective October 5, 1971. This Amendment 39-1556 becomes effective November 13, 1972.
95-19-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767 series airplanes. This action requires operators to perform visual inspections of the outer cylinder aft trunnion on the main landing gear to determine if the fillet seal is cracked or missing. This action also requires operators to inspect for evidence of corrosion in this location. Finally, this action prescribes the procedures that operators must follow if corrosion is found. This amendment is prompted by several reports of fractures of the outer cylinder aft trunnion due to stress corrosion cracking. The actions specified in this AD are intended to ensure that corrosion is not present in this location, thereby preventing future failures due to stress corrosion cracking.
2021-03-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD requires removing certain Titanium (Ti) bolts from service and prohibits installing these Ti-bolts in a critical area. This AD was prompted by a report of a broken Ti-bolt. The actions of this AD are intended to address an unsafe condition on these products.