BOMBARDIER BD-100-1A10, Operating Manual

Page: 529 / 544

POWERPLANT
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6
18-01-13
ENGINE BLEED AIR SYSTEM
DESCRIPTION
The engine bleed air system provides intermediate pressure (IP) air to the environmental control system and the opposite
engine air turbine starter. It provides high pressure (HP) air to the wing and engine anti-icing systems.
The integrated air system management controller (IASC) controls bleed-air extraction from the engines. IASC 1 supports
L BLEED and IASC 2 supports R BLEED functions.
Bleed-air is also extracted from the compressor by the surge bleed valves to regulate airflow through the engine core and
is controlled by the FADEC.
L and R bleed-air selection, ON or OFF, is accomplished via the AIR COND/BLEED panel on the center pedestal. A cross-
bleed valve is installed between the left and right pneumatic ducts, that can be opened automatically or manually by press-
ing the XBLEED push button, to provide bleed-air for engine starting. The APU is the normal source of bleed-air that is
used for engine starting.
COMPONENTS AND OPERATION
Engine bleed-air components consists of a bleed duct, intermediate pressure valve (IPV) and intermediate check valve.
Engine bleed-air duct assembly directs compressor bleed-air to the common bleed manifold that is located in the aft equip-
ment bay. The engine compressor supplies bleed-air to operate the aircraft pneumatic system.
The nacelle bleed-air ducts are monitored for bleed-air leakage by the engine fire detection system.
Refer to Chapter 2, Air Conditioning and Pressurization , and Chapter 14, Ice and Rain Protection for more discussion on
the bleed air system.
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