DESCRIPTION
General 02−10−1
Air Conditioning System 02−10−1
Description 02−10−1
Components and Operation 02−10−1
Pressurization System 02−10−9
Description 02−10−9
Components and Operation 02−10−10
Controls and Indicators 02−10−20
General 02−10−20
EICAS Messages 02−10−23
SUMMARY
Power Supply and Circuit Breaker Summary 02−20−1
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 02−10−1 Air Conditioning Pack − Schematic 02−10−3
Figure 02−10−2 Air Conditioning Distribution 02−10−5
Figure 02−10−3 Flight Compartment Fan Sensor 02−10−6
Figure 02−10−4 AIR CONDITIONING Panel 02−10−8
Figure 02−10−5 Cabin Pressurization Schematic 02−10−12
Figure 02−10−6 Cabin Pressurization Schedule 02−10−13
Figure 02−10−7 CABIN PRESSURIZATION Panel 02−10−14
Figure 02−10−8 Typical Flight Pressurization Profile 02−10−17
Figure 02−10−9 Takeoff at Sea Level to Land at 14,000 feet 02−10−18
Figure 02−10−10 Takeoff at 14,000 feet to Land at Sea Level 02−10−19
Figure 02−10−11 AIR CONDITIONING Panel 02−10−20
Figure 02−10−12 CABIN PRESSURIZATION Panel 02−10−21
Figure 02−10−13 Air Conditioning and Pressurization Indications 02−10−22
Figure 02−10−14 Air Conditioning and Pressurization Indications 02−10−23
AIR CONDITIONING AND PRESSURIZATION
Table of Contents
Vol. 2 02−00−1
Oct 05/06
CHAPTER 2 - AIR CONDITIONING AND PRESSURIZATION
02−00−1
CL−605 Flight Crew Operating Manual
PSP 605−6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
AIR CONDITIONING AND PRESSURIZATION
Table of Contents
Vol. 2 02−00−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
THIS PAGE INTENTIONALLY LEFT BLANK
GENERAL
The air conditioning system provides temperature-regulated, conditioned air to the cockpit and
passenger cabin using two air conditioning units (ACU’s), commonly referred to as “packs”.
An electric cockpit heating system and an avionics cooling system are also provided.
Aircraft pressurization is accomplished by regulating the overboard discharge of the conditioned air
through two outflow valves. The automatic pressurization system maintains cabin pressure to provide
passenger comfort throughout all phases of flight within the limitations of the aircraft structure.
During unpressurized flight, ram air may be used to ventilate the cockpit and cabin.
AIR CONDITIONING SYSTEM
Description
The air conditioning system converts 10th-stage bleed air from the engines, APU, or an external
source into temperature-regulated pressurized air for distribution to the cockpit and cabin.
The air conditioning system consists of two packs, a temperature control system, distribution
ducting, and a ram air system for pack cooling and supplementary ventilation.
A single pack can provide sufficient air to cool and pressurize the aircraft.
Components and Operation
Packs
The packs are located in the aft equipment bay, and are referred to as the left pack and right
pack. The L (R) PACK switch/lights on the AIR CONDITIONING panel are used to operate the
respective air conditioning pack.
The packs are monitored for overtemperature and overpressure conditions and have automatic
protection for both cases.
The left pack is powered by the DC essential bus, and the right pack is powered by DC bus 2. In
the event of a double-generator failure when airborne, leading to deployment of the air-driven
generator, the left pack remains operational, enabling continued flight at high altitude.
In the event of a single-pack failure, the remaining pack can supply sufficient conditioned air to
both compartments.
Pack Pressure Regulation
When the L (R) PACK switch/light is pressed in, the corresponding pressure-regulating shutoff
valve (ACU valve) allows bleed air from the 10th-stage manifold to enter the pack. The ACU
valves operate in two different modes, low mode or high mode, according to the following
conditions:
• Low Mode: Airborne during dual-pack operation, or on the ground with the engines
supplying the bleed air, output pressure 24 psig;
AIR CONDITIONING AND PRESSURIZATION
Description
Vol. 2 02−10−1
　
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