The inboard doors are hydraulically operated while the outboard doors are mechanically operated by linkage connected to the main gear struts.

Fuel can also flow via the flapper check valves into the wing tanks, but the lower half of the fuel in the tip tanks must be transferred with the jet pump. On aircraft 25-181 and subsequent the variable volume engine driven pump delivers fluid under a pressure of 1450 psi to the system and static pressure is maintained at 1500 to 1550 psi. In 1974 the Peruvian Air Force purchased two 25Bs with a belly pod that contained an aerial survey camera. Type development continued with the Models 25D and 25G, which included more advanced CJ610-8A engines and a ceiling increase to 51,000 feet.

The Learjet 25 is similar to the Model 24 but is 1.27 m (4 ft 2 in) longer, allowing for three additional passengers. On May 17, 2017, a Learjet 25B registration XA-VMC operated by the company Aerotransportes Huitzilin S. A. de C. V. crashed at 3:26 p.m. local time shortly after taking off from Toluca International Airport, Mexico bound for Durango. Warp factor 9! The brake system incorporates four power-boosted disc-type brakes with integral anti-skid system. An audible waning horn warns of flap extension to more than 25 degrees if the landing gear is not down and locked. Starting ignition is provided by a dual output capacitor-discharge system.

The conventional airspeed scale is calibrated in knots and the Mach scale is calibrated in percentage of Mach and connected to an aneroid that moves the scale to compensate for changes in pressure altitude. In 1970 the Learjet 25B was produced along with the Learjet 25C in the same year. A rate controller enables the crew to select the rate pressurization of the cabin within preset limits. A pre-charged accumulator dampens and absorbs pressure surges. A duty cycle of 3 minutes on and a cooling period of 20 minutes off is required to avoid overheating the pump motor. Speed and altitude of flight. The large markings are graduated in 2% increments from 0% to 100% and the small dial is graduated in 1% increments from 0% to 10% to allow the pilots to accomplish more precise engine speed settings. The angle-of-attack transducer supplies a proportional voltage to the angle-of-attack of the aircraft. Many Learjet 25 aircraft remain in regular use today, particularly in the United States, Mexico, and Canada. Others charge an additional fuel surcharge which varies depending on the cost of fuel and the length of each flight.
The drag chute is attached to the aircraft with a lanyard system that releases it from the aircraft should an inadvertent deployment be made while airborne. Monobromotrifluoromethane (CF3BR) is used as extinguishing agent. The landing gear, brake, flap and spoiler systems are hydraulically operated.

Instead, one must do some digging to find various estimates. Oxygen is always available for the crew and can be made available to the passengers manually or automatically. When both angle-of-attack transducer vanes increase to 5% above stall, the pitch servo commands an aircraft nose down attitude. Cruise altitude of 30,000 feet with 34 knot headwinds. AC current is provided by two 1000 Volt-Amperes (VA) solid-state inverters. When chartering a plane, the fuel cost is typically included in the overall price quote. The aircraft is equipped with AC (Alternating Current) and DC (Direct Current) electrical systems. The two flight crew are then supplemented by either a doctor or flight nurse or both.
Typical cruising altitudes are between Flight Level 390 and Flight Level 430 which means the Learjet 25 is capable of overflying most weather systems and congested airspace. The electrically operated RPM tachometer consists of a signal generator on the engine and an indicator located in the centre of the instrument panel. The Learjet 25 also requires long runways at high altitude or ambient temperature. The use of oxygen is only required for emergency in case of depressurization of the cabin or contamination of the cabin air. The valves are controlled by the FIRE switch and activation of these valves are indicated with pinhead lights located in the cockpit next to the FIRE switch. On aircraft 25-061 through 25-180 the engine driven hydraulic pumps supply fluid under pressure of 1500 psi to the system pressure is maintained at 1250 to 1500 psi by a pressure regulator. My cruise speed was set at .65G or 390kph SOG. The fuel burn on a Falcon 20F-5 is 280 gallons per hour. Some aircraft have a 1000 VA auxiliary inverter that is used as an option for added system capacity. The Learjet 25 is an American ten-seat (two crew and eight passengers), twin-engine, high-speed business jet aircraft manufactured by Learjet.

The ICAO designator as used in flight plans for all Learjet 25 models is LJ25. The Learjet 25 is similar to the Model 24 but is 1.27 m (4 ft 2 in) longer, allowing for three additional passengers. The first Model 25 flew on August 12, 1966, and the first delivery was in November 1967. The stall warning system utilizes a stall warning vane on each side of the nose.

The vanes provide regulated voltage input to the angle-of-attack transducers, modified by a stall warning bias box to compensate for flap position. The main gear has dual wheels and brakes on each strut. An angle-of-attack indicator translates signals from the stall warning system into visual indications of the aircraft angle-of-attack and allows the crew to monitor the proximity of stall caution zone. Therefore, some reports will state fuel burn rates based upon the hour of flight. The force applied in the nose down direction is 80 pounds at the control wheel.

This point is near the aircraft centre of gravity and minimizes weathervaning when the chute is deployed under crosswind conditions. Unlike a car, a plane's burn rate is dependent upon a number of factors, including: A plane will burn more fuel during take-off and its initial ascent. When the angle-of-attack transducer vanes decrease below the stall point, the nose down command is removed. Engine bleed air is admitted through a flow control valve to a heat exchanger. The bleed air is cooled in the heat exchanger by ram air entering the dorsal fin inlet and passing through the heat exchanger. Similarly, the Embraer website offers hourly fuel burn rates for the Phenom 300 as a means of demonstrating typical burn during take-off and ascent, as compared with during subsequent flight time. As the ignition cycle is completed, the igniter plugs cease sparking and combustion becomes self-sustaining. Nose wheel steering is electronically controlled by the rudder pedals, utilizing the synchro principle. The fuel flow through a rotor-turbine at each engine causes the rotor to spin and a pickup coil emits pulses as the rotor blades pass through the coil field. The brake system utilizes hydraulic pressure for power boost. Flapper-type check valves, located in the various wing ribs, allow free fuel flow inboard but restrict outboard flow. The steering system on aircraft without variable authority nose wheel steering requires the pilot to select master or primary steering mode. Two motor-driven shutoff valves will stop hydraulic flow to the engine-driven pumps in case of an emergency. When the aircraft speed is 7% above stall, the stall warning energizes a control column shaker that produces a low-frequency buffet signal through the control column to warn the crew. Four additional shuttle valves connect the pneumatic system to the brake system for emergency braking.

The hydraulically retractable landing gear is of conventional tricycle configuration with air-hydraulic shock-type nose and main gear. A pressure switch will energize the pump if hydraulic pressure falls below a preset level and de-energize the pump when pressure returns to normal. There is no standardization within the industry as to how fuel consumption should be stated or measured, and it's a figure that many OEMs do not provide. Nose wheel steering is electrically controlled via the rudder pedals. By GreenMachine in forum MSFS Screen Shot Forum, FAQ - Frequently Asked Questions - DreamFleet 727, FAQ - Frequently Asked Questions - DreamFleet General Aviation & 737-400 Products, DreamFleet General Aviation Support Forum.

And yet, the fuel costs can be 50% or more of the annual operating costs, running from hundreds of thousands of dollars a year for a light jet, to millions of dollars a year for heavy jets. Hydraulic pressure for retraction and extension of the gear is transmitted by a system of tubing, hoses and actuating cylinders and is electrically controlled by limit switches and solenoid valves. Phantom Aero Technical – ATTC034, (1998), Johannesburg, This page was last edited on 8 October 2020, at 12:15. Taxi operations are accomplished using the electronic nose wheel steering.

The Learjet 25 is a challenging aircraft to fly in comparison with most general aviation aircraft and more modern light jets. FAA certified on September 4, 1970.

The fuselage tank can be filled by the wing boost pumps through the transfer line and the fuel transfer valve. [1], Data from Jane's All The World's Aircraft 1976–77[11], Learjet 25B/25C Pilot's Manual, Gates Learjet Corporation, Wichita, Kansas, 1971, Learn how and when to remove this template message, "For many models, market hitting the apex", Information page from Aviation Safety Network, "Aviation Safety Network Accident Description - 2 March 1996", "Plane of singer Jenni Rivera missing in Mexico. The necessary fuel for the craft and its contents will further increase the weight, and therefore the fuel burn. Actually .72MACH and about 408knots ground speed. The cabin temperature is controlled by regulating the temperature of the pressure bleed air that is routed through the cabin.

I just completed the flight KDEN to KLAS 1/2 tanks, a total of 448.1 Gallons. The Learjet 25 utilize wheel brakes as the primary method for reducing speed after landing. Over pressurization is prevented by a pressure relief valve which opens at 1700 psi. The cabin interior can be converted to several different configurations to allow for cargo and medevacs.