Results
2007-03-15: The FAA is superseding an existing airworthiness directive (AD) for CFM International CFM56-5 and -5B series turbofan engines. That AD requires exhaust gas temperature (EGT) harness replacement or the establishment of an EGT baseline and trend monitoring. That AD also requires replacement, if necessary, of certain EGT harnesses and EGT couplings as soon as a slow and continuous EGT drift downward is noticed after the effective date of that AD. This AD requires the same actions but for an increased population of affected EGT harnesses. This AD results from CFM International adding subsequently certified engine models to the list of engines that could have affected harnesses installed. We are issuing this AD to prevent unexpected deterioration of critical rotating engine parts due to higher than desired engine operating EGTs.
2005-25-11: The FAA is superseding an existing 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. That AD currently requires LP compressor fan blade replacement with new or previously reworked blades, or rework of the existing LP compressor fan blades. This ad requires the same actions but at reduced compliance times for certain airplane and engine rating combinations and certain maximum gross weight limits. This AD results from a number of new production LP compressor fan blades found with surfaces formed outside of design intent. 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.
2007-03-13: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce plc) (RRD) Dart 528, 529, 532, 535, 542, and 552 series turboprop engines. This AD would require repetitive inspections of high pressure turbine (HPT) blade platforms and shrouds, and reworking the engines if the inspections reveal excessive gaps between blade shrouds. This AD results from reports of HPT disk rim failures. We are issuing this AD to prevent HPT disk rim failures resulting in the release of portions of the HPT disk, uncontained engine failure, and damage to the airplane.
2021-07-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that the oil used to protect the nose landing gear (NLG) main fittings for transportation and storage was not removed before final heat treatment of the affected parts, possibly generating sub-surface cavities during heat treatment of the affected parts. This AD requires replacing each affected NLG main fitting with a serviceable part, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2007-03-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus airplanes identified above. This AD requires improving the routing of certain electrical wire bundles in certain airplane zones, as applicable to the airplane model. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
61-23-01: 61-23-01 BRANTLY: Amdt. 364 Part 507 Federal Register November 3, 1961. Applies to All Model B-2 Helicopters Equipped With B2-248-53 or B2-248-53A Outboard Main Rotor Blades. Compliance required as indicated. As the result of bond separation between the skin and foam filler on the inboard end of the B2-248-53 and -53A main rotor blades and cracks around the root fitting in both the upper and lower skins the following inspections are required: (a) Within the next 10 hours' time in service unless already accomplished within the last 15 hours' time in service and at the expiration of each 25 hours' time in service thereafter, inspect the upper and lower skins of the inboard end of the B2-248-53 and -53A blades as follows: (1) Inspect for bond separation by feel or sound tests. If the skin is separated from the foam filler a sponginess will be felt or a dullness in tone will be heard when tapped with a coin. Blades with voids exceeding 12 inches in length shallbe replaced prior to further flight. (2) Inspect for cracks between rivets in the skins with a 5-power or greater magnifying glass. If any cracks are found around two or more rivets the blade must be replaced prior to further flight. (b) When blades are replaced they must be replaced with either B2-248-53M or B2- 248-101 blades. Brantly Service Letter No. 31A must be complied with when B2-248-101 blades are installed. (c) In addition to the inspection interval specified in (a), the inspection required in (a)(1) also must be made prior to each flight after the initial inspection. (d) (1) The inspections required in (a) shall be made by a person as authorized by CAR 18.11. (2) The inspections required in (c) and appropriate log book entries thereon are hereby authorized to be made by the pilot. (Brantly Service Letter No. 28A applies to this same subject.) This directive effective November 4, 1961.
2021-06-04: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Model GV airplanes. This AD was prompted by notification of corrosion present in floor beam support links. This AD requires inspecting the right butt line 6 floor beam inboard support links and bushings for corrosion. The FAA is issuing this AD to address the unsafe condition on these products.
2020-15-17: The FAA is adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation Model S-76C helicopters. This AD was prompted by reports of inaccurate main gear box (MGB) indications in flight. This AD requires updating the remote data acquisition unit (RDAU) software and re-identifying the RDAU and, for certain helicopters, updating the software of the display unit (DU) and re- identifying the DU. The FAA is issuing this AD to address the unsafe condition on these products.
2007-03-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires inspecting for discrepancies of the activation mechanism of certain chemical oxygen generators, and corrective action if necessary. This AD results from several incidents, on certain airplane models, of incorrect installation of the release pin into the safety pin hole of the activation mechanism of the chemical oxygen generator; this resulted in failure to activate the chemical oxygen generator when required. A separate incident occurred on a different airplane model during deployment of the cabin oxygen system, which resulted in failure of the release pin to activate the oxygen generator at a flight attendant station. We are issuing this AD to prevent failure of the activation mechanism of the chemical oxygen generator, which could result in the unavailability of supplemental oxygen and possible incapacitation of passengers and cabin crew during an in-flight decompression.
80-16-04: 80-16-04 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-3862. Applies to AiResearch TFE-731-2, -3, -3R engines manufactured prior to May 1980. Compliance required as indicated, unless already accomplished. To prevent separation of tie rod and potential massive engine failure, accomplish the following: (a) Within 150 operating hours after the effective date of this AD, unless previously accomplished, compliance is required with Paragraph (c) for the following TFE-731 engines: Model Serial Numbers TFE-731-2-1C 73142, 73159, 73215, 73240, 73293, 73345, 73348 thru 73361 TFE-731-2-2B 74145, 74153, 74159, 74161, 74175, 74201, 74218, 74271, 74284, 74328, 74329, 74331, 74332 thru 74336, 74339, 74341, 74342, 74344, 74348 thru 74351, 74355, 74356, 74358 thru 74362, 74375, 74431, 74448, 74821 TFE-731-3-1E 75138, 75143, 75177, 75179, 75183 thru 75186, 75190, 75191, 75192, 75214 TFE-731-3-1C 76108 TFE-731-3-1G 77166, 77167, 77174, 77176, 77177 TFE-731-3-1F/-1K 78115, 78130, 78131, 78132, 78134, 78137, 78138, 78139, 78145, 78146 TFE-731-3-1H 80107, 80118, 80121, 80176 TFE-731-2-2J 81101, 81102, 81104 (b) For all TFE-731-2, -3, -3R engines manufactured prior to May 1980, and not listed in Paragraph (a), compliance with Paragraph (c) is required at, or prior to, the next major periodic inspection (as defined in AiResearch Service Bulletin TFE-731-72-3105 or -3106), unless previously accomplished. (c) Determine the serial number identification of the tie rod, P/N 3070065-1, installed in engines covered under Paragraphs (a) or (b). This determination can be made by reference to engine build records or by disassembly of the engine sufficient to gain access to the aft end of the tie rod. All tie rods of the following listed serial numbers must be removed from service and replaced with like serviceable parts: 6P11723 6P11747 6P11771 6P11795 6P21154 6P11724 6P11748 6P11772 6P11796 6P21155 6P11725 6P11749 6P11773 6P11797 6P21156 6P11726 6P11750 6P11774 6P11798 6P21157 6P11727 6P11751 6P11775 6P11799 6P21158 6P11728 6P11752 6P11776 6P11800 6P21159 6P11729 6P11753 6P11777 6P11801 6P21160 6P11730 6P11754 6P11778 6P11802 6P21162 6P11731 6P11755 6P11779 6P11803 6P21163 6P11732 6P11756 6P11780 6P11804 6P21164 6P11733 6P11757 6P11781 6P11805 6P21165 6P11734 6P11758 6P11782 6P11806 6P21166 6P11735 6P11759 6P11783 6P11807 6P21167 6P11736 6P11760 6P11784 6P11808 6P21168 6P11737 6P11761 6P11785 6P11809 6P21169 6P11738 6P11762 6P11786 6P11810 6P21170 6P11739 6P11763 6P11787 6P11811 6P21171 6P11740 6P11764 6P11788 6P11812 6P21172 6P11741 6P11765 6P11789 6P11813 6P21173 6P11742 6P11766 6P11790 6P11814 6P21174 6P11743 6P11767 6P11791 6P11815 6P21175 6P11744 6P11768 6P11792 6P11816 7P11849 6P11745 6P11769 6P11793 6P11817 7P11850 6P11746 6P11770 6P11794 6P11818(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective August 7, 1980.