Aircraft fuel tank must be able to withstand, without failure, the vibration, inertia, fluid, and structural loads. Tandem seat aircraft often have wider seats than side-by-side two place aircraft. The top access port 453 can include an outer top door 454 a and an inner top door 454 b. Referring to the aft tank group 114, the second master tank assembly 120 b is configured to pass through the aft cargo door 107 b and be positioned proximate to a forward bulkhead 103 b in the aft cargo compartment 108. ATL can offer a range of fuel storage options for range extension, including crashworthy rigid tanks or ultra-lightweight and easily stowable bladders . In addition, the aircraft fuel system 130 can also distribute fuel from the forward tank group 112 and the aft tank group 114 to an aerial refueling system (not shown) if the aircraft 100 includes such a refueling system. 1. LS206 (F-H) Ordering. Conversely, when it is desired to draw fuel from the master tank assembly 120 b, the pump outlet check valves 676 are opened and the fuel transfer pumps 672 pump fuel out of the master tank assembly 120 b via the fuel inlet ducts 661. Originally JCA/M47-1-01A. 11/042,731, filed Jan. 24, 2005 and issued on May 9, 2006 as U.S. Pat. In a further aspect of this embodiment, the first end wall 443 a includes two fuel outlet apertures 432 a, two fuel inlet apertures 432 b, and two vent apertures 432 c. These apertures are configured to accommodate passage of the fuel outlet manifold 230, the fuel inlet manifold 240, and the vent manifold 250, respectively, described above with reference to FIGS. The number and arrangement of auxiliary fuel tanks positioned in either the forward cargo compartment 106 or the aft cargo compartment 108 can be varied to meet particular range and/or fuel off-load requirements. 3 is an enlarged isometric view of an aft tank group of the auxiliary fuel tank system of FIG. A further known type of auxiliary fuel tank system includes a group of three tanks having individual fuel inlet, fuel outlet, and vent manifolds. The United States Of America As Represented By The Secretary Of The Air Force, The United States Of America As Represented By The Secretary Of The Navy. The basic tank systems 1160 can include the basic tank portion 660 of the fuel outlet manifold 230 (FIG. Referring next to FIG. An aircraft fuel tank body configured in accordance with one aspect of the invention includes a first end wall having at least a first aperture and a second end wall positioned opposite to the first end wall and having at least a second aperture. FIGS. 6 is an enlarged isometric view of a master tank assembly of FIG. One fit all, seat fuel tank of 25 and 33 gal. The first outlet manifold interface 679 a can be operably coupled to a corresponding first branch 675 a of the master tank portion 670. For example, outlet manifold extensions 332 a can be added to the fuel outlet manifold 230, and inlet manifold extensions 332 b can be added to the fuel inlet manifold 240. The term “auxiliary” means that the tank is secondary to the airplane’s main fuel tanks; i.e., the functions of the main tanks are immediately available and operate without immediate supervision by the flightcrew in the event of failure of inadvertent depletion of fuel in an auxiliary tank. Manufacturing a master tank assembly can include installing a first portion of a manifold in a first tank body. 4. The fuselage 102 can include a forward cargo compartment 106 having a forward cargo door 107 a and an aft cargo compartment 108 having an aft cargo door 107 b. When fuel in the tank is at or above a first fuel level 731, the float 763 maintains the valve 765 in a fully open position as shown in FIG. Removal of the top doors 454 can provide access to the interior of the tank body 225 for inspection or maintenance of one or more of the systems installed within as described in greater detail below. 11E, in yet another embodiment, the manifold extension systems 1132 can be added to the single master tank assembly 1122 to create the master tank assembly 120 described above with reference to FIGS. 2, these apertures are configured to accommodate passage of corresponding aircraft interfaces (i.e., the fuel system interface 231, the vent system interface 251, and the FMS interface 261 shown in FIG. “ TO MAKE THE OCEAN A SAFER PLACE”, DECISIVE BREAK THROUGHT IN PRECISION SEAM SEALING TECHNOLOGY FOR INFLATABLES BY INVENTIVE AUSTRALIAN ENGINEERS AND LASZLO TOROK. Alternatively, pneumatic pressure from an aircraft bleed air system can be individually provided to each of the tanks for fuel transfer. Nos. The webbing ties must be secured to strong points in the compartment. Transport category aircraft often have more than a dozen oval access panels or tank plates on the bottom surface of the wing for this purpose. Filled via a 2″ filler on lay flat hose that reaches outside the fuselage for filling and tucks back into cabin for flight. 1). Placing the pump pressure switches 674 in an accessible portion of the dry bay 458 enables them to be inspected or replaced without entering the interior portion of the master tank assembly 120 b. The first and second apertures can be configured to accommodate passage of a fuel manifold extending through the fuel tank body. An aircraft fueling manifold provides fuel to the bladders for filling. 8, the inlet manifold interfaces 678 are configured to be operably coupled to corresponding branches of the inlet manifold 240 (not shown). Enough space is provided between the first master tank assembly 120 a and the bulkhead 103 a so that maintenance personnel can access the interfaces between the forward tank group 112 and the aircraft fuel system 130, the aircraft vent system 132, and the FMS 134. If some of the end wall apertures are not used for a particular tank configuration, those apertures can be sealed with a suitable cover. Fuel tanks deform under various loads. YACHT “HUSSAR” CAPSIZED AND SEVERLY DAMAGED OFF THE EAST COAST OF AUSTRALIA. In this system, however, the separate tanks are filled in sequence with the first tank overflowing into the next and continuing until all the tanks are full. By subscribing you agree to receive emails from DART Aerospace including: product and corporate news, special offers and more. Some of our tanks have been used successfully with Avgas for just over 10 years now. 8 is an enlarged isometric view of the master tank assembly of FIG. As described above, in one embodiment, the smaller tank body 525 can be used for a master or slave tank assembly when the tank assembly is installed in a position that could be susceptible to damage from landing gear collapse. In addition, a single electric motor-driven fuel pump can be installed in each tank for transferring fuel out of the tank. In a further aspect of this embodiment, the extension portion 832 of the fuel inlet manifold 240 includes two inlet manifold extensions 332 b. In addition or as an alternative, the first master tank assembly 120 a can include reinforced tank walls to prevent a rupture in the event of a rotor burst. Originally JCA/M47-1. In yet another aspect of this embodiment, the basic tank portion 860 of the fuel inlet manifold 240 includes a first fuel outlet duct 861 a operably coupled to the first branch 873 a of the master tank portion 870 and a second fuel outlet duct 861 b operably coupled to the second branch 873 b of the master tank portion 870. Such limiting physical dimensions can include, for example, cargo compartment dimensions and door opening dimensions. PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362. Each branch 675 of the master tank portion 670 can include a pump outlet check valve 676 (identified individually as a first pump outlet check valve 676 a and a second pump outlet check valve 676 b) operably coupled in series to a fuel transfer pump 672 (identified individually as a first fuel transfer pump 672 a and a second fuel transfer pump 672 b). The auxiliary fuel tank system 110 illustrated in FIG. Cub or Van’s RV-8 etc. Fuel is added to the tanks via a main fueling manifold of the aircraft. This information can include, for example, the combined total amount of fuel remaining in all of auxiliary tanks and the individual amounts of fuel remaining in each of the tanks. What is the time signature of the song Atin Cu Pung Singsing? 1). 8), the basic tank portion 960 of the vent manifold 250 (FIG. New product samples are destruction tested and trialled in the field in the most arduous conditions before release into the market. Get professional advice for the best method to suit your aircraft and to meet the Airworthiness requirements. Humanitarian air drop. FIGS. Can be taken as baggage on commercial flights. Pneumatic pressure from an aircraft bleed air system is used to flow fuel from the auxiliary tanks into integral aircraft fuel tanks. 3, the vent manifold extensions 332 c can extend the vent manifold 250 into an adjoining fuel tank assembly, such as the mid tank assembly 121 or an end tank assembly 122 (FIGS. For example, the second master tank assembly 120 b can be at least generally similar in structure and function to the first master tank assembly 120 a. Activate aux fuel transfer and the system operates automatically. FIG. Combat fuel drop. TIME ARRIVED TO INTRODUCE A RANGE OF TANKS FOR OTHER SAILORS USE. Each branch 673 of the fuel inlet/outlet manifold 671 can include an inlet manifold interface 678 (identified individually as a first inlet manifold interface 678 a and a second inlet manifold interface 678 b). In addition, as further described in greater detail below, the FMS 134 can also control and monitor auxiliary fuel tank inlet and outlet systems (not shown). 11A-11E are schematic diagrams illustrating modular features of the present invention that enable multiple tank configurations to be assembled from a common set of components in accordance with an embodiment of the invention. Aero Enterprises specializes in manufacturing auxiliary and replacement gas and diesel tanks. We are also in the process of applying the technology to meet the new flammability regulations per FAA docket 2005-22997 and FAR 25.981. 4 shows a plan view of the left side auxiliary fuel tank 26 comprising a main body section 28 having a generally convex outer wall 30, … Filled with Avgas the total weight is 33.3 kg 73 lbs, light enough to lift the tank onto the seat. The inner top door 454 b can be positioned directly below the outer top door 454 a, and can removably cover a corresponding aperture in the inner tank skin 441. Auxiliary fuel tank systems for aircraft and methods for their manufacture and use, EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT, Arrangements in connection with fuel supply for power plant, GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS, TECHNICAL SUBJECTS COVERED BY FORMER USPC, TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION, Plural tanks or compartments connected for serial flow, With communicating opening in common walls of tanks or compartments.
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