Engines

• -- Two pod mounted Pratt & Whitney JT15D-5B turbofan engines
• -- Advantages- Better fuel specs, Shorter Take-off, Efficiency at low altitude, reduced noise
• -- Disadvantages- Reduced efficiency at high altitudes, slower speeds
• -- Engines are monitored in cockpit by N1, ITT, N2, FF, Oil temp, Oil Press and vibration guages

• Flat rated to provide constant thrust throughout various altitudes and temperature ranges
• -- Sea level to 27°C => 2900 lbs. of thrust for 5 minutes
• Divided Flow
• -- Bypass flow (low altitude thrust) driven by N1
• -- Core flow (high altitude thrust) driven by N2
• Take-off Rated Thrust limiting factors-
• -- N1 104%, 700°C, 2900lbs thrust
• Max Continuous Thrust limiting factors- -- N1 104%, 680°C, 2900lbs thrust

• -- N1 is two stage axial compressor / two stage axial turbine
• -- 104% max continuous RPM
• -- 106% max transient RPM

• -- N2 is high pressure single stage compressor / single stage high turbine
• -- 96% max continuous RPM

• -- 12 nozzle housings that atomize fuel and 2 dual spark igniters
• -- Igniters in STBY provide spark at start, anti-ice, stick shaker up to 50,000’

--Cold nozzle configuration; bypass flow mixed with core flow for cooler exhaust temperatures

-- Mechanical device to detect aft movement of N1­ shaft and shutdown engine

-- Behind compressors, smooth and direct air flow

• (Driven by N₂ shaft)
• --DC starter generator
• -- N2 speed sensor
• -- Oil pump
• -- Fuel pump- increases fuel pressure from 15psi to 580psi max
• -- Hydromechanical Metering Unit (HMU)- sole provider of fuel up to 38%N2
• -- Hydraulic pump

--Valve opens to prevent compressor surge during engine acceleration at high AOA

• -- Cools engine
• -- ACM
• -- Hydraulic system (15psi, no bubbles)
• -- Engine and wing Anti-ice

• 2.03 gal
• 1.84 gallons drainable, synthetic oil only