Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Abstract: An assisted piloting method for an aircraft having at least two engines (2, 3) includes monitoring a set of parameters (Ng, T4, Tq) of the engines. A first limit indicator (10) displays information relating to a value of a limiting parameter of the engines. The limiting parameter is the parameter (Ng, T4, Tq) of the engines that is the closest to its limit. An assisted piloting mode is activated during which each parameter (Ng, T4, Tq) is maintained below a predetermined threshold whenever the first limit indicator is not in a position to display the information.

Abstract: An assisted piloting method for an aircraft having at least two engines (2, 3) for use in the event of a first limit indicator (10) breakdown down, a plurality of monitoring parameters (Ng, T4, Tq) of the engines (2, 3) of said aircraft being monitored, said first limit indicator (10) displaying information relating to a value of a limiting parameter of said engines (2, 3), the limiting parameter being that one of the monitoring parameter (Ng, T4, Tq) of the engines that is the closest to its limits. Under such circumstances, an assisted piloting mode is activated during which each monitoring parameter (Ng, T4, Tq) is maintained below a predetermined threshold whenever said first limit indicator (10) is not in a position to display said information.

Abstract: The present invention relates to an aircraft firewall (12) separating first and second compartments (1 and 2) of the aircraft, the first compartment (1) containing a plurality of elements. The firewall (12) is provided with a first wall (3) inserted in the structure (5) of the aircraft and having a first surface (3?) facing the first compartment (1), and the firewall (12) is provided with regulator elements (4, 13) for maintaining the maximum temperature of the first surface (3?) of the first wall (3) at a predetermined temperature value lower than the self-combustion temperature of the elements.

Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

Abstract: The thermal detection and visual alarm unit includes a plurality of first expansion thermal detectors (17) with normally closed contacts that are connected in series with a first lamp (15) to form a first two-terminal circuit (21, 23), a plurality of second expansion thermal detectors (18) with normally open contacts connected in parallel, a second lamp (16) connected in series with the second thermal detectors to form a second two-terminal circuit (22, 24), the first and second thermal detectors forming a plurality of cells (19) each combining a first detector and a second detector having respective contact-opening or contact-closing temperatures that are substantially equal, each of the first and second two-terminal circuits being arranged for connection to the terminals of an electrical power supply (12).

Abstract: The present invention relates to an aircraft firewall (12) separating first and second compartments (1 and 2) of said aircraft, said first compartment (1) containing a plurality of elements. The firewall (12) is provided with a first wall (3) inserted in the structure (5) of the aircraft and having a first surface (3?) facing said first compartment (1), and said firewall (12) is provided with regulator means (4, 13) for maintaining the maximum temperature of said first surface (3?) of the first wall (3) at a predetermined temperature value lower than the self-combustion temperature of said elements.

Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Abstract: The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second end (22) connected to the engine at the rearmost portion thereof.

Abstract: The thermal detection and visual alarm unit comprises a plurality of first expansion thermal detectors (17) with normally closed contacts that are connected in series with a first lamp (15) to form a first two-terminal circuit (21, 23), a plurality of second expansion thermal detectors (18) with normally open contacts connected in parallel, a second lamp (16) connected in series with the second thermal detectors to form a second two-terminal circuit (22, 24), the first and second thermal detectors forming a plurality of cells (19) each combining a first detector and a second detector having respective contact-opening or contact-closing temperatures that are substantially equal, each of said first and second two-terminal circuits being arranged for connection to the terminals of an electrical power supply (12).

Abstract: A device for blocking first and second components (1, 2) relative to one another may be provided with first and second parts (3, 4) capable of cooperating with one another in order to effect the blocking, the first part (3) being carried by the first component (1) and being provided with a duct (15) and the second part (4) being carried by the second component (2) and being provided with a blocking finger (24) capable of being introduced frictionally into the duct (15). The first part (3) may have a first pivot system (8) with a pivot (10) that can rotate relative to the first component (1); the duct may be formed by a diametral conduit (15) pierced in the pivot (10) of the first pivot system (8); and the second part (4) may include a second pivot system (23) with which the blocking finger (24) is integral so as to be capable of tilting relative to the second component (2).

Abstract: A flange system for the butt fastening of two pipes (2, 3), for example, the gas outlet pipe and the nozzle of a turboengine, the flange (5) of one of the pipes (2) having a triangular cross section. There are provided on the flange (9) of the other pipe (3) protuberances (12) which cooperate with cuneiform wedges (15) in order to form a system of jaws pressing the flange (5) of triangular cross section between them.

Abstract: An installation for connecting the output shaft of the engine and the input shaft of the transmission box together including a transmission shaft having a certain amount of flexural flexibility and including splines at one of its ends. The splined end being designed to be a sliding fit in a corresponding splined hub of the engine. Attaching the engine to the deck actualized by a system for articulated attachment which includes stand legs and rails fixed to the deck parallel to the shafts. The legs can slide with the engine after tilting.