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When the desired cabin altitude is reached, select MAN ALT to HOLD position.
S HOLD position: Disables all previous MAN ALT selections.
C. Safety Valves
Two safety valves are installed at the top of the rear pressure bulkhead. The purpose
the valves is to make sure that the cabin pressure differential does not exceed its
maximum positive and negative pressure limits. Maximum positive differential pressure
is limited to 8.6 ±0.1 psid and negative differential pressure is limited to −0.5 psid.
D. Ground Valve
The ground valve is normally open when the aircraft is on the ground and the
passenger or service doors are open. The valve is used to limit differential pressure
drop by discharging air from the avionics compartment overboard. The valve is driven
to the closed position by the CPCP as soon as the passenger and service doors are
closed and locked or when the automatic pre--pressurization sequence is initiated
Failure of the ground valve to open on the ground will be indicated by an OVBD COOL
FAIL status message on the EICAS status page
E. Cabin Altitude Limitation
Altitude limitation closes the outflow valve to prevent an increase in cabin altitude above
14,500 ±500 feet.
F. Emergency Depressurization
Electrical signals from the EMER DEPRESS switch commands the outflow valve to
open. If the airplane is at a cruise altitude (above 15,000 feet), the altitude limiters
operate to prevent cabin altitude from exceeding 15,000 feet.
Vol. 1 08--60--10
ENVIRONMENTAL CONTROL SYSTEM
Pressurization System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
G. Cabin Pressure Monitoring
Cabin pressure is monitored using data from the two cabin pressure controllers and the
cabin pressurization control panel to display the following on the EICAS displays:
S Cabin altitude
S Cabin altitude rate of change
S Cabin to ambient differential pressure
S Landing elevation
H. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Cabin
CABIN PRESS
MAN CONT
BATTERY
BUS 2 P5
Pressurization
Control
Controller CABIN PRESS
CONT 1 DC BUS 1 1 F10
CABIN PRESS
CONT 2 DC BUS 2 2 F10
Vol. 1 10--00--1
FIRE PROTECTION
Table of Contents REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
CHAPTER 10 --- FIRE PROTECTION
Page
TABLE OF CONTENTS 10--00--1
Table of Contents 10--00--1
INTRODUCTION 10--10--1
Introduction 10--10--1
FIRE DETECTION AND EXTINGUISHING (FIDEEX) 10--20--1
Fire Detection and Extinguishing (FIDEEX) 10--20--1
Engine 10--20--1
APU 10--20--7
Cargo Compartment 10--20--12
Testing 10--20--15
System Circuit Breakers 10--20--17
LAVATORY 10--30--1
Lavatory Fire Protection 10--30--1
Detection 10--30--1
Extinguishing 10--30--3
System Circuit Breakers 10--30--4
MAIN LANDING GEAR OVERHEAT DETECTION 10--40--1
Main Landing Gear Overheat Detection 10--40--1
System Circuit Breakers 10--40--4
LIST OF ILLUSTRATIONS
INTRODUCTION
Figure 10--10--1 FIDEEX System Block Diagram 10--10--2
FIRE DETECTION AND EXTINGUISHING (FIDEEX)
Figure 10--20--1 Engine Fire Detection Block Schematic 10--20--2
Figure 10--20--2 Engine Fire Push Buttons 10--20--3
Figure 10--20--3 Engine Fire Extinguishing -- Schematic 10--20--4
Figure 10--20--4 Engine Fire EICAS Indications 10--20--5
Figure 10--20--5 APU Fire Detection Block Schematic 10--20--8
Figure 10--20--6 APU Fire Pushbuttons 10--20--9
Figure 10--20--7 APU Fire Extinguishing -- Schematic 10--20--10
Figure 10--20--8 APU Fire EICAS Indications 10--20--11
Figure 10--20--9 Cargo Firex 10--20--14
Vol. 1 10--00--2
FIRE PROTECTION
Table of Contents REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Figure 10--20--10 Fire Detection and Extinguishing -- Testing 10--20--16
LAVATORY
Figure 10--30--1 Smoke Detector 10--30--2
Figure 10--30--2 Smoke Setector EICAS Indications 10--30--3
Figure 10--30--3 Lavatory Waste Compartment Extinguisher 10--30--4
MAIN LANDING GEAR OVERHEAT DETECTION
Figure 10--40--1 Landing Gear Control Panel 10--40--1
Figure 10--40--2 Landing Gear EICAS Messages 10--40--2
Figure 10--40--3 MLG Overheat Indication and Test 10--40--3
Vol. 1 10--10--1
FIRE PROTECTION
Introduction Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
1. INTRODUCTION
Fire protection consists of a fire detection and extinguishing (FIDEEX) system for detecting
and extinguish a fire in the engine nacelles, the auxiliary power unit (APU) compartment and
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