Results
2004-15-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a one-time inspection to determine the part number of the engine mounting frames, brace struts, and attachment fittings; and related corrective action. This action is necessary to ensure the structural integrity of the engine-to-wing load path and prevent possible separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
2022-07-02: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. Model 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters with a certain part-numbered tailboom left hand fin spar cap (spar cap) installed. This AD was prompted by reports of cracked spar caps. This AD requires inspecting each spar cap and depending on the inspection results, removing the spar cap from service. The FAA is issuing this AD to address the unsafe condition on these products.
2004-01-20: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, -524D4, -524G2, -524G3, and -524H series, and RB211-535C and -535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. This AD allows disc assemblies not modified by a certain RR service bulletin to reach their full life only after the disc assemblies are modified with anti-corrosion protection. This AD results from the manufacturer's reassessment of the corrosion risk on HPC stage 3 disc assemblies that have not yet been modified with sufficient application of anti-corrosion protection. We are issuing this AD to prevent corrosion-induced uncontained disc failure, resulting in damage to the airplane.
72-14-02: 72-14-02 SIAI-MARCHETTI: Amdt. 39-1477. Applies to SIAI Marchetti Model S.205 airplanes, Serial Nos. 001 through 003, 101 through 384, 385 through 4-255, and Model S.208 airplanes, Serial Nos. 001 through 003, 1-03 through 2-19, 369, 3-100, 4-231, 4-233, 4-256 through 4-258. Compliance is required as indicated. To prevent the entrance of fuel or fumes into areas of the wing external to the fuel tanks or into the cabin, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished within the last 40 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection until the modification specified in paragraph (c) is accomplished - (1) On Model S.205 airplanes, Serial Nos. 001 through 003 and 101 through 384, which do not incorporate scupper drains, remove the right hand and left hand wing tank fuel level transmitter access covers and visuallyinspect the fuel level transmitter supper recessed areas for water deposits or corrosion. (2) On Model S.205 airplanes, Serial Nos. 385 through 4-255, and Model S.208 airplanes, Serial Nos. 001 through 003, 1-03 through 2-19, 369, 3-100, 4-231, 4-233, and 4-256 through 4-258, which incorporate straight scupper drain tubes, remove the right hand and left hand wing tank fuel level transmitter access covers and visually inspect the welding area between the tubes and fuel level transmitter scupper recessed areas for cracks or signs of fuel seepage into the recessed areas. (b) If water deposits or corrosion are found during an inspection required by subparagraph (a)(1) or cracks or signs of fuel seepage are found during an inspection required by subparagraph (a)(2), comply with paragraph (c) before further flight, except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be made. (c) For all ModelsS.205 and S.208 airplanes, within the next 500 hours' time in service after the effective date of this AD, unless already accomplished, install new right hand and left hand wing tank fuel transmitter scupper drain tubes, P/N 205-8-112-37 and P/N 205-8- 112-38, and reinforcing washers, P/N 205-8-112-27, in accordance with SIAI Marchetti Service Bulletin No. 205B29A dated December 15, 1971, or an FAA-approved equivalent. Identify the new scupper drain tubes by painting a ring of white paint approximately 1/8 inch wide on the recessed area of the scupper around the new drain tube where it extends through the scupper. This amendment becomes effective 3 July, 1972.
2022-07-11: The FAA is superseding Airworthiness Directive (AD) 2021-17- 18, which applied to all Leonardo S.p.a. Model A109C, A109K2, A109E, A109S, and AW109SP helicopters. AD 2021-17-18 required an inspection of certain tail rotor (TR) sleeve assemblies for discrepancies, an inspection of certain TR shaft assemblies for discrepancies, a repetitive measurement of the position of the bushing of the TR sleeve assembly in relation to the pitch change slider assembly, and corrective actions if necessary. This AD retains the requirements of AD 2021-17-18, and also requires repetitive inspections of the TR sleeve assemblies, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that additional actions are required to address the unsafe condition. This AD was also prompted by a report of a crack on the TR mast. The FAA is issuing this AD to address the unsafe condition on these products.
72-19-05: 72-19-05 PITTS AVIATION ENTERPRISES, INC: Amdt. 39-1520. Applies to Pitts Model S-2A series Airplanes, S/N 2001 through 2030. Compliance required as indicated. (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, to prevent failure of the horizontal stabilizer leading edge support tube, accomplish the following: (1) Remove the left and right horizontal stabilizers as follows: NOTE: Keep track of all hardware and replace the same parts in their original locations, unless other options are indicated. (i) Disconnect the elevator trim tab push rods from the horns beneath the stabilizers (leave the rods connected to the tab horns). NOTE: Some airplanes may have AN310-1032 nuts and AN380 cotter pins installed on the AN3 bolts, instead of AN365-1032 nuts. If so, you may either reinstall the AN310-1032 nuts with new AN380 cotter pins, or use AN365-1032 self-locking nuts and undrilled AN3 bolts.(ii) Remove the two AN4 bolts through the flying wire lugs and elevator hinges, left and right. NOTE: It is not necessary to loosen the flying wires. (iii) Remove the 4 AN3 bolts through the stabilizer leading edge and trailing edge tubes, left and right. NOTE: It is not necessary to remove the stabilizer root fairings. (iv) Remove the access plates adjacent to the stabilizer trailing edge, reach inside the aft fuselage and remove the two AN3 bolts through the elevator trim control shaft. NOTE: It is not necessary to disconnect the elevator horn. (v) Remove the left and right horizontal stabilizers by pulling them straight outboard. (2) Thoroughly clean with solvent the exposed portions of the 2-2123 stabilizer leading edge support tube which protrudes from the fuselage. Dye-check this tube in the vicinity of the AN3 bolt holes, and visually inspect for cracks. (i) If cracks are found, order a replacement P/N 2-2123 assembly fromthe manufacturer. (ii) If cracks are not found, accomplish the following. (3) Cut off the outer ends of the stabilizer leading edge support tube, P/N 2- 2123, so that the dimension from the center of the AN3 bolt hole to the outer end of the tube is 1/2 inch, left and right sides. Remove all burrs and rough edges. (4) Redrill the AN3 bolt holes in the stabilizer leading edge support tube, P/N 2-2123, and through the mating holes in the stabilizer leading edge tubes with a number 10 drill (.193 to .199 diameter), left and right. (5) Apply zinc chromate to bare metal surfaces. (6) Reassemble in the reverse order of Step 1. (7) Stencil on upper surfaces of both the left and right horizontal stabilizers, near the leading edge, the words "No lift", in letters one-half inch high or higher, and in a color which contrasts sharply with the paint finish on the stabilizer. Pitts Service Bulletin Number 6 pertains to this same subject. This amendmentbecomes effective September 20, 1972.
71-04-03: 71-04-03 AMERICAN AVIATION: Amdt. 39-1155. Applies to American Aviation Corp., Model AA-1, certificated in all categories S/N AA1-0001 through AA1-0432. (a) Within the next 10 hours in service after the effective date of this AD unless already accomplished, inspect and test the nose gear strut in accordance with the procedures of American Aviation Service Bulletin No. 121A dated 1/8/71 or with an equivalent method. (b) Replace defective parts prior to further flight with a part received from the manufacturer after 1 June 1970 or inspected and tested in accordance with this directive. (c) Equivalent methods and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This airworthiness directive is effective February 25, 1971 and was effective as to all recipients of the letter dated January 12, 1971 which contained this airworthiness directive.
2004-15-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-202, -203, -223, and -243 airplanes, and A330-300 series airplanes, that requires modification of the control box of the auxiliary power unit (APU). This action is necessary to prevent uncommanded in-flight shutdown of the APU, which could result in loss of critical electrical systems when the airplane is operated in emergency electrical configuration, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
96-18-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Piaggio Model P-180 airplanes, that requires replacement of outflow/safety valves with serviceable valves. This amendment is prompted by a report of cracking and subsequent failure of outflow safety valves in the pressurization system. The actions specified by this AD are intended to prevent such cracking and subsequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
2021-03-16R1: The FAA is removing Airworthiness Directive (AD) 2021-03-16, which applied to all Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2021-03-16 required inspecting each sliding door and replacing the upper rail or front roller or removing the front roller from service if necessary. Since the FAA issued AD 2021-03-16, inspection results and further investigation have confirmed that the in-flight loss of a sliding door, which prompted AD 2021-03-16, was an isolated case resulting from incorrect operation and maintenance error. Therefore, the FAA has determined that no unsafe condition is likely to exist or develop on the sliding doors on other helicopters in the fleet. Accordingly, AD 2021-03-16 is removed.