737 MAX Flight Crew Operations Manual
Anti-Ice, Rain -
System Description
3.20.4
MN-FLT-OH-201
Probe and Sensor Heat
Pitot probes, the total air temperature probe and the alpha vanes are electrically
heated. Static ports are not heated. When operating on standby power, only the
captain’s pitot probe is heated, however, the CAPT PITOT light does not
illuminate for a failure.
Note:
The pitot probe for standby airspeed is not heated when the airplane is on
standby power.
Engine Anti–Ice System
Engine bleed air thermal anti–icing prevents the formation of ice on the engine
cowl lip and engine core.
Cowl anti–ice operation is controlled by individual ENG ANTI–ICE switches.
The cowl anti–ice system may be operated on the ground and in flight.
Core anti-ice operation is automatically controlled by the Electronic Engine
Control (EEC) with no crew input or indication of normal operation. The EEC
controls the core anti-ice system by directing bleed air to the engine core as needed
based on engine parameters and atmospheric conditions.
Engine Anti–Ice System Operation
Each cowl anti–ice valve is electrically controlled and pressure actuated.
Positioning the ENG ANTI–ICE switches to ON:
• allows engine bleed air to flow through the cowl anti–ice valve for cowl
lip anti–icing
• sets stall warning logic for icing conditions.
• sets engine idle speed per the following table:
March 1, 2021
