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Aircraft Signal Conditioner Unit (SCU)


The Signal Conditioner Unit’s (SCU) basic function is to excite the fuel probes, compensator, and temperature sensors and scale the return signals. Each SCU can interface with up to eight (8) fuel probes with temperature detection and/or fuel probes with compensators. It will process capacitive and resistive readings to determine the fuel heights for each probe and transmit the calculated fuel volume to the cockpit.


  • Material: Nickel plated aluminum
  • Dimensions: 4.4” x 6.1” x 1.8” (11×15.5×4.5cm)
  • Weight: 1.25 lbs (565 grams)
  • EMI Filtered Connector to Aircraft: MS3114L14-19P
  • EMI Filtered Connector to Fuel Tank: MS3114L16-26P


  • Startup and Continuous Built-In-Test (SBIT and CBIT)
  • Fuel temperature measurement
  • No field calibration required when paired with LMS probes and sensors
  • Slosh filtering
  • High- and Low-Level detection


  • Up to Eight (8) Probe or Compensator Channels
  • Input: 28VDC
  • Two (2) ID bits to select up to Four (4) different tank configurations via pin strapping


  • ARINC 429 or customer specific requirement
  • Up to Two (2) Discrete Open/GND Outputs for Low and High-Level Detection

Power Requirements

  • Input: 28VDC per MIL-STD-704
  • Current Draw: < 100mA
  • Maximum Power Consumption: 7W


Section and DescriptionCategory
1Temperature & AltitudeB2
2Temperature VariationB
4Operational Shocks and Crash SafetyB
5VibrationS (Curve T)
R (Curve G)
6Explosive AtmosphereE
8Fluids SusceptibilityF
9Sand and DustS
10Fungus ResistanceF
11Salt FogS
12Magnetic EffectY
13Power InputZXX
14Voltage SpikeA
15Audio Frequency Conducted SusceptibilityZ
16Induced Signal SusceptibilityZCX
17Radio Frequency Susceptibility (Radiated and Conducted)R
18Emission of Radio Frequency EnergyM
19Lightning Induced Transient SusceptibilityA3J3L3
20Lightning Direct EffectsX
22Electrostatic Discharge (ESD)A
23Fire, FlammabilityC

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