Results
2007-04-06: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-8-62, DC-8-63, DC-8-62F, and DC-8- 63F airplanes. This AD requires revising the wiring for the engine thrust brake circuit and indicating circuit and other specified actions, or rerouting the wiring at plug P1-1762A on the electrical power center generator control panel, as necessary. This AD results from the determination that the thrust reverser systems on these airplanes do not adequately preclude inadvertent deployment of the thrust reversers. We are issuing this AD to prevent inadvertent deployment of the thrust reversers during takeoff or landing, which could result in loss of control of the airplane.
2021-09-10: The FAA is superseding Airworthiness Directive (AD) 2012-04-15 for all Pratt & Whitney (PW) JT9D-3A, JT9D-7, JT9D-7A, JT9D-7AH, JT9D- 7F, JT9D-7H, JT9D-7J, JT9D-7Q, JT9D-7Q3, JT9D-7R4D, JT9D-7R4D1, JT9D- 7R4E, JT9D-7R4E1, JT9D-7R4E4, JT9D-7R4G2, JT9D-7R4H1, JT9D-20, JT9D- 20J, JT9D-59A, and JT9D-70A (JT9D) model turbofan engines. AD 2012-04- 15 required revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part opportunity. AD 2012-04-15 also required additional revisions to the ALS of the manufacturer's ICA for JT9D model turbofan engines. This AD requires revising the required inspections of selected critical life-limited parts specified in the ALS of the manufacturer's ICA and, for air carriers, to the existing continuous airworthiness air carrier maintenance program (CAMP). The FAA is issuing this AD to address the unsafe condition on these products.
2007-04-03: The FAA is superseding an existing airworthiness directive (AD), which applies to all EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. That AD currently requires repetitive inspections of the pitot static heating relay K0057 and corrective actions if necessary. That AD also requires doing a terminating modification, which ends the repetitive inspections. This new AD removes the existing repetitive inspections and instead requires a one-time detailed inspection for damage of the relay, relay socket, and silicone gasket; applicable corrective actions; and a new action to modify and re-identify the relay socket. This AD also revises the existing terminating modification--replacing/ rerouting the windowsill drain hoses--into two parts, each with a different, reduced compliance time. This AD results from a report of smoke in the cockpit. We are issuing this AD to prevent ignition of a windowsill drain hose by an overheated relay, which could cause fire and smoke in the cockpit.
2007-04-04: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD requires repetitive inspections of the wing top skin under the rib 0 joint strap, and related investigative and corrective actions if necessary. This AD results from a report of a significant crack in the wing top skin under the rib 0 joint strap. We are issuing this AD to detect and correct corrosion and cracking in that area, which could result in reduced structural integrity of the wing.
2007-04-07: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires inspecting to determine the manufacturer's date of certain V-band clamps on the engine exhaust shroud assembly, and doing related investigative/corrective actions if necessary. This AD results from a report of a discrepancy found during a maintenance inspection on a V- band clamp located on the engine exhaust duct shroud. The clamp ends were touching (although the correct fastener torque had been applied), resulting in reduced clamp force on the flanges. We are issuing this AD to prevent vibration in the duct shroud and fretting of the V-band clamp and flanges, which could result in cracking of the flanges and consequent release of hot exhaust gases from the engine tailpipe and damage to adjacent structure. This situation could trigger the fire warning system and result in an in-flight emergency, such as the flightcrew shutting down the engine and activating the fire suppression system.
2021-08-15: The FAA is adopting a new airworthiness directive (AD) for certain Garmin International (Garmin) GMN-00962 GTS processor units (GTS 825, GTS 855, GTS 8000). This AD was prompted by reports of GTS processor units issuing resolution advisories (RAs) when no risk of collision or loss of separation exists between the airplanes involved. This AD requires updating the software version of the affected GTS Processor units. The FAA is issuing this AD to address the unsafe condition on these products.
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.
2021-05-20: The FAA is superseding Airworthiness Directive (AD) 2018-16- 02, which applied to all Airbus SAS Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-211, - 212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. AD 2018-16-02 required modifying and re-identifying the 3-lug aft engine mount assemblies. This AD continues to require modifying and re-identifying the 3-lug aft engine mount assemblies, and also requires modifying and re-identifying the 4-lug aft engine mount assemblies; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. The FAA is issuing this AD to address the unsafe condition on these products.
2007-03-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections to detect cracks in the vertical beam webs of the body station (BS) 178 bulkhead, and corrective actions if necessary. This AD also requires a terminating modification for the repetitive inspections. This AD results from reports of numerous cracks in the vertical beam webs. We are issuing this AD to prevent fatigue cracks in certain vertical beam webs, which could result in loss of structural integrity of the BS 178 bulkhead, and consequently could impair the operation of the control cables for the elevators, speed brakes, and landing gear, or could cause the loss of cabin pressure.
2021-02-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC 155B and EC155B1 helicopters. This AD was prompted by a report that non-destructive tests of the main gearbox (MGB) housing may have been evaluated incorrectly during production. This AD requires replacing affected MGBs with serviceable MGBs, 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.
2007-03-01: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes. This AD requires inspecting certain power feeder wire bundles for damage, inspecting the support clamps for these wire bundles to determine whether the clamps are properly installed, and performing corrective actions if necessary. This AD results from a report that a power feeder wire bundle chafed against the number six auxiliary slat track, causing electrical wires in the bundle to arc, which damaged both the auxiliary slat track and power feeder wires. We are issuing this AD to prevent arcing that could be a possible ignition source for leaked flammable fluids, which could result in a fire. Arcing could also result in a loss of power from the generator connected to the power feeder wire bundle, and consequent loss of systems, which could reduce controllability of the airplane.
2007-02-19: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-605R airplanes and Model A310-308, -324, and -325 airplanes. This AD requires modifying the Bruce floor plan electrical emergency path marking system (FPEEPMS) and, for certain airplanes, modifying the automatic switching of the emergency lighting system. This AD results from a report that in the case of vertical separation of the fuselage forward of door 1, the FPEEPMS and the exit signs do not turn on. We are issuing this AD to prevent inadequate lighting and marking of the escape path, which could delay or impede the flightcrew and passengers when exiting the airplane during an emergency landing.
2007-02-20: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Model F27 Mark 050 and F.28 Mark 0070 and 0100 airplanes. This AD requires repetitively removing the two existing escape rope assemblies in the flight compartment and installing new escape rope assemblies. This AD results from reports of findings of small cracks in the polyester assembly block in which the cotton escape rope is stored. A test revealed that the escape ropes had deteriorated over time, and the load capability was considerably reduced. We are issuing this AD to ensure that flightcrew members safely reach the ground after exiting the flight compartment window during an emergency evacuation.
2021-04-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, AS355N and AS355NP helicopters; and certain Model AS350B3 helicopters. This AD was prompted by a report that, during an unscheduled post-flight inspection of the tail cone area, a crack was found in the spar of the upper part of the vertical fin and fractures were found in the two front attachment screws. This AD requires repetitive visual inspections of the right-hand side of the vertical fin spar for discrepancies (cracking), and corrective action 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.
2007-01-10: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 747 airplanes. That AD currently requires a one-time inspection to determine whether the outer cylinder of the wing landing gear has certain part numbers, and replacement of the outer cylinder of the wing landing gear with a new, improved, or reworked part if necessary. That AD also requires removal of the load evening system, if such a system is installed. This new AD requires, for certain airplanes, an additional one-time inspection to determine whether the outer cylinder has a certain other part number. For those certain airplanes, this new AD also requires replacement of the outer cylinder with a reworked or new, improved part and related investigative and corrective actions, if necessary. This AD results from identification of an additional unsafe part. We are issuing this AD to prevent fracture of the outer cylinder of the wing landing gear, which could result in collapse of the wing landing gear.
2007-02-21: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes (collectively called A300-600 series airplanes). This AD requires replacing the pressure limiter of the parking brake system with a new or modified pressure limiter. This AD results from a report indicating that failure of the parking brake system occurred on a Model A300-600 airplane. We are issuing this AD to prevent failure of the parking brake system and interference with emergency use of the brake pedals, which could lead to airplane collision with surrounding objects or departure from the runway.