Results
98-01-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires modification of the air outlet opening of the engine air bypass duct. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent accumulation of ice in the engine air intake duct and subsequent ingestion of ice into the engine, which could result in engine power fluctuations and reduced controllability of the airplane.
2021-12-07: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11 model turbofan engines. This AD was prompted by an investigation by RRD, which revealed a quality escape during the high-pressure turbine (HPT) stage 1 disk rim cooling air hole manufacturing process. This AD requires removing affected HPT disks from service prior to reaching specified compliance times or at the next engine shop visit, whichever occurs first. The FAA is issuing this AD to address the unsafe condition on these products.
2021-13-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD was prompted by a report of a yaw control failure that was the result of the disconnection of the tail rotor hub (TRH) pitch control rod from the tail rotor servo-control, which resulted from a seized TRH bearing. The TRH bearing had grease dissolving after contamination by leaked hydraulic fluid from the tail rotor servo- control that came through the TRH assembly boot. This AD requires repetitive inspections for hydraulic leaks, corrective actions if necessary, and an optional modification which constitutes terminating action, 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.
97-26-22: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-120 series airplanes. This action requires a one-time inspection of the movable backstop of the elevator pitch trim command system to ensure that it is installed correctly, and corrective action, if necessary. This action also requires installation of a guide to maintain the movable backstop in its correct position. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent a sudden change in pitch attitude caused by autopilot disconnect, which could result in reduced controllability of the airplane.
2004-06-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, -321, -322, -341, and -342 series airplanes; and certain Model A340 series airplanes, that requires inspecting for and repairing cracking of the wire harness slots in the inner rear spars of the wings between ribs 4 and 5, and cold-expanding crack-free wire harness slots and bolt holes. This action is necessary to prevent cracking of the wire harness slot, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
65-19-03: 65-19-03\tBOEING: Amdt 39-118 Part 39 Federal Register August 24, 1965. Applies to Models 707 and 720 Series Airplanes Listed in Boeing Service Bulletin No. 2014 (R-2). \n\tCompliance required as indicated. \n\n\t(a)\tFor Model 720 Series airplanes with 4,500 or more hours' time in service on the effective date of this AD, comply with (c) within the next 600 hours' time in service, unless accomplished within the last 600 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(b)\tFor Model 720 Series airplanes with less than 4,500 hours' time in service on the effective date of this AD, comply with (c) before the accumulation of 5,100 hours' time in service, unless accomplished after the accumulation of 3,900 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(c)\tInspect visually for cracks in the left-hand and right-hand frames at Body Stations 760 and 780 on Model 720 Series airplanes except 720-025 Series and at Body Station 800 on all Model 720 Series airplanes in the vicinity of waterline 208.1 (top of floor beam). If cracks are found, rework the frames before further flight in accordance with paragraph 3 of Boeing Service Bulletin No. 2014(R-2) or later FAA-approved revision; Boeing Structural Repair Manual D6- 1891, paragraph 53-3-5, page 1; or a method approved by the Aircraft Engineering Division, FAA Western Region. The repetitive inspections required by (a) and (b) of this AD may be discontinued when cracked frames have been reworked in accordance with this paragraph, or when uncracked frames have been reworked in accordance with Boeing Drawing 65-42173, or a method approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(d)\tFor Model 707 Series airplanes with 10,000 or more hours' time in service on the effective date of this AD, comply with (f) within the next 600 hours' time in service, unless accomplished within the last 600 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(e)\tFor Model 707 Series Airplanes with less than 10,000 hours' time in service on the effective date of this AD, comply with (f) before the accumulation of 10,600 hours' time in service, unless accomplished after the accumulation of 9,400 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection. \n\n\t(f)\tInspect visually for cracks in the left-hand and right-hand frames at Body Station 800 in the vicinity of waterline 208.1 (top of floor beam). If cracks are found, rework the frames before further flight in accordance with paragraph 3 of Boeing Service Bulletin No. 2014(R-2) or later FAA-approved revision; Boeing Structural Repair Manual D6-1649, paragraph 53-3-5, page 1, for 707-100/200 Series airplanes, and Boeing Structural Repair Manual D6-2962 for 707- 300/400 Series airplanes; or a method approved by the Aircraft Engineering Division, FAA Western Region. The repetitive inspections required by (d) and (e) of this AD may be discontinued when cracked frames have been reworked in accordance with this paragraph, or when uncracked frames have been reworked in accordance with Boeing Drawing 65-42173, or a method approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(g)\tUpon request of an operator, an FAA maintenance inspector, with prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals required by this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for the operator. \n\n\tThis directive effective September 23, 1965.
2021-14-15: The FAA is superseding Airworthiness Directive (AD) 2002-08-16 for certain Eurocopter France SA341G, SA342J, and SA-360C helicopters. AD 2002-08-16 required removing certain main rotor head torsion tie bars (tie bars) from service and revising the limitations section of the existing maintenance manual for your helicopter by adding life limits for certain other tie bars. This AD was prompted by the determination that another part-numbered tie bar is affected by the same unsafe condition. This AD continues to require removing certain tie bars from service and establishing a life limit for certain other tie bars. The FAA is issuing this AD to address the unsafe condition on these products.
72-12-04: 72-12-04 CESSNA: Amdt. 39-1459. Applies to Models 401 and 402 series airplanes. Compliance: Required within 50 hours' time in service after the effective date of this AD, unless already accomplished. To assure proper support of fuel lines and to eliminate chafing of fuel lines with possible fire hazard due to fuel leakage in the wing leading edge, accomplish the following: A) On airplanes (Serial Numbers 401-0001 thru 401-0225 and 402-0001 thru 402-0225, except 402-0171, 402-0172, 401-0189, 402-0191, 401-0197, 402-0209, 402-0210, 402-0212, 401-0214 thru 401-0225, and 402-0214 thru 402-0225), remove the engine cowling, turbo supercharger and the firewall access opening for both engines. Visually inspect the fuel crossfeed lines for chafing at the firewall vertical stiffeners. Replace chafed fuel lines with a serviceable part and install fuel line support clamps in accordance with Cessna Service Letter ME68-6, dated April 16, 1968, or later revision, or any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Maintain a minimum of .50 inch clearance between the fuel crossfeed lines and the firewall vertical stiffener. Replace firewall access plate using AN515-8R5 or equivalent screws or screws removed from firewall that do not exceed 5/16 inches in length. B) On airplanes (Serial Numbers 401-0001 thru 401A0010 and 402-0001 thru 402-0319 except 401A0001, 401A0003, 402-0218, 402-0298 and 402-0317), remove all inspection access plates in wing leading edge outboard of the engine nacelle and visually inspect main fuel supply and vapor return lines for chafing. Replace chafed fuel lines with a serviceable part and install fuel line support clamps in accordance with Cessna Service Letter ME68-27, dated December 27, 1968, or later revision, or any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. C) On airplanes (Serial Numbers 401-0226 thru 401B0216 and 402-0226 thru 402B0220: (1) Remove the engine cowling and screws from the firewall vertical stiffener as shown in Cessna Service Letter ME72-11, dated May 26, 1972, or later revision. (2) If screws removed are more than .312 inches in length, remove firewall inspection plate and inspect fuel crossfeed lines for chafing and replace any chafed fuel line with a serviceable part. (3) Replace screws removed from firewall vertical stiffener with MS35266-60 screws. Cessna Service Letter ME72-11, dated May 26, 1972, or later revision, pertains to the subject matter of this paragraph. This amendment becomes effective June 16, 1972.
70-12-02: 70-12-02 BEECH: Amdt. 39-1001. Applies to Models 36 and A36 (Serial Numbers E-1 through E-201) Airplanes. Compliance: Required as indicated, unless already accomplished. To effect compliance with a certification regulatory requirement, accomplish the following: Within 50 hours' time in service after the effective date of this AD, modify the seat tracks on the two center seats in accordance with Beechcraft Service Instructions No. 0343-314, or an equivalent method approved by the Chief, Engineering & Manufacturing Branch, FAA, Central Region. This amendment becomes effective June 9, 1970.
2011-08-11: We are superseding an existing airworthiness directive (AD) that applies to 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: During the period 2001/2002, skin cracking was found adjacent to the butt joint forward of frame 19 * * *. The cracks emanated from chemically-etched pockets on the internal surface of the skin. * * * [C]racking in multiple adjacent bays * * * could compromise the structural integrity of the fuselage in the event that the multiple cracks joined into a single crack. * * * During 2008, a further report was received at BAE Systems of a 13.78 inch crack in an AVRO 146-RJ that occurred 514 flight cycles (FC) short of the next 4 000-FC repetitive inspection interval. * * * * * * * * We are issuing this AD to require actionsto correct the unsafe condition on these products.