Results
2004-15-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with low pressure (LP) compressor fan blades part number (P/N) FW18548, installed. This AD requires LP compressor fan blade replacement with new or previously reworked blades, or rework of the existing LP compressor fan blades. This AD results from a number of new production LP compressor fan blades found with surfaces formed outside of design intent. Findings included sharp edges, burrs, and damage present in the area at the top of the shear key slots. We are issuing this AD to prevent possible multiple uncontained LP compressor fan blade failure, due to cracking in the blade root caused by increased stresses in the shear key slots.
47-43-11: 47-43-11 LOCKHEED: (Was Mandatory Note 22 of AD-723-3.) Applies to All Model 18 Serial Numbers. Compliance required prior to next periodic inspection. Remove bolts connecting the elevator push-pull rod to the elevator horn and bellcrank and ascertain that the shank diameter falls within the limits of 0.248 to 0.250. Bolts outside these limits should be replaced with NAS 54-12 bolts. In view of the similarity of the Lockheed bolts with standard AN bolt, it is suggested that they be replaced with close tolerance bolts, NAS 54-12 and the push-pull rod. P/N 72149 placarded "Use NAS 54-12 bolt".
2022-11-09: The FAA is adopting a new airworthiness directive (AD) for all Viking Air Limited (Viking) (type certificate previously held by Bombardier Inc. and de Havilland, Inc.) Model DHC-6-1, DHC-6-100, DHC- 6-200, DHC-6-300, and DHC-6-400 airplanes. 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 identifies the unsafe condition as cracks and corrosion damage to the aileron internal structure. This AD requires visually inspecting the entire aileron internal structure, correcting any damage found, and reporting the inspection results to Viking. The FAA is issuing this AD to address the unsafe condition on these products.
2013-05-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of stiff operation of the elevator pitch control system and jammed elevator controls. This AD requires replacing pressure seal assemblies; doing repetitive inspections for dirt, loose particles, or blockage of the flanged tube and drain hole for the pressure seals, and corrective action if necessary; replacing the aft air-intake duct assembly with a new or modified assembly and installing a dripshield; and installing gutters on the horizontal stabilizer center section and modifying the side brace fittings. We are issuing this AD to prevent moisture from collecting and freezing on the elevator control system components, which could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability of the airplane.
2004-16-02: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires installing a new warning annunciator light on the central warning panel and revising the Normal Procedures Section of the Aircraft Flight Manual to provide the flightcrew with procedures related to the new light. This action is necessary to prevent an engine shut-down in icing conditions, which could result in loss of control of the airplane and consequent injury to flightcrew and passengers. This action is intended to address the identified unsafe condition.
72-01-03: 72-01-03 BELLANCA: Amdt. 39-1373. Applies to Models 17-30A (Serial Numbers 30394, 30395, 30396, 30397, 30398, 30399, 30400, 30401, 30402, 30403 and 30405); 17-31A (Serial Number 32-53); and 17-31ATC (Serial Numbers 31022, 31023, 31024 and 31025) Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent loss of engine power due to fuel starvation, accomplish the following: Prior to next flight replace hose Aeroquip P/N 359-8D-0153, located between the firewall and engine driven fuel pump, with hose Bellanca P/N 198003-10, or an equivalent method of compliance approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Bellanca Service Letter No. 68 dated December 3, 1971, pertains to this subject. This amendment becomes effective January 5, 1972, to all persons except those to whom it was made effective by telegram dated December 17, 1971.
69-14-03: 69-14-03 BRITISH AIRCRAFT CORPORATION: Amdt. 39-794. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required within the next 1,500 hours' time in service after the effective date of this AD, unless already accomplished. To prevent the failure of the windshield heating circuit, install 20K ohm resistors and 1 mfd capacitors into both phases of the heating circuit for pilot's and copilot's main windshield in accordance with British Aircraft Corporation Modification Bulletin No. 30-PM 3092, Revision 8, dated July 22, 1968 or later ARB-approved revision or an FAA approved equivalent. This amendment becomes effective August 10, 1969.
2022-10-02: The FAA is superseding Airworthiness Directive (AD) 2002-03- 01, which applied to certain Honeywell International, Inc. (Honeywell) T53 model turboshaft engines. AD 2002-03-01 required initial and repetitive special vibration tests of the engine and, if necessary, replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This AD was prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. This AD requires initial and repetitive special vibration tests of the engine and, depending on the results, replacement of either the reduction gearbox assembly or the engine. The FAA is issuing this AD to address the unsafe condition on these products.
2022-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA-46-600TP airplanes. This AD was prompted by testing that showed that the wing splice assembly could fail before the assembly reaches its established life limit. This AD requires revising the Airworthiness Limitations section (ALS) of the existing maintenance manual (MM) or instructions for continued airworthiness (ICA) to reduce the life limit of the wing splice assembly. The FAA is issuing this AD to address the unsafe condition on these products.
46-44-03: 46-44-03 CESSNA: (Was Mandatory Note 3 of AD-768-4.) Applies Only to 120 and 140 Aircraft Serial Numbers 8001 to 9619, Inclusive. Compliance required prior to January 1, 1947. Rework attachment of windshield upper edge by the installation of a retaining channel deeper than the original and extending the entire width of the fuselage. The channel consists of two pieces; one an 0.040-inch 24ST alclad strip, 1 7/8 inches x 42 inches, outside of the windshield and with the rear edge inserted between the fuselage top skin and the front flange of the spar "U" channel; the other an 0.032-inch 24ST alclad strip, 1 13/16 inches x 44 inches, inside of the windshield and overlapping the above-mentioned spar flange. These strips are secured to the top skin and spar flange by a single row of 44 AN 456AD4 rivets. A piece of felt, 2 3/4 inches x 44 inches x 1/16-inch thick, SAE F-55 or equivalent, should be folded over the edge of the windshield and cemented thereto to provide a seal and a tight fit in the channel. This modification is necessary to insure that the windshield will not pull out at the top and alter the airflow, thereby seriously affecting the operational characteristics of the airplane. (Cessna Service Letter No. 14-120 and 140 covers this same subject.)