bombardier crj 00-hydraulic power

7/28/2019 Bombardier CRJ 00-Hydraulic Power

1/20

14--00--1Vol. 1

REV 56, J an 31/03HYDRAULIC POWER

Table of Contents

FlightCrew Operating Manual

CSP A--013

MASTER

CHAPTER 14 --- HYDRAULIC POWER

Page

TABLE OF CONTENTS 14--00Table of Contents 14--00--1

INTRODUCTION 14--10

Introduction 14--10--1

SYSTEMS 1 AND 2 14--20

Hydraulic Systems No.1 and No.2 14--20--1

Engine Driven Pumps 14--20--4

AC Motor Pumps (ACMP) 14--20--4

Hydraulic Shutoff Valves 14--20--5

Reservoir 14--20--5

Accumulator 14--20--5

System Circuit Breakers 14--20--8

SYSTEM 3 14--30

Hydraulic System No.3 14--30--1

AC Motor Pumps 14--30--3

System Circuit Breakers 14--30--6

LIST OF ILLUSTRATIONS

INTRODUCTIONFigure 14--10--1 Hydraulic Systems Diagram 14--10--2

Figure 14--10--2 Hydraulic Systems Overview 14--10--3

SYSTEMS 1 AND 2Figure 14--20--1 Hydraulic Systems 1 and 2 Schematic 14--20--2

Figure 14--20--2 Hydraulic Control P anel 14--20--4

Figure 14--20--3 Systems 1 and 2 -- Synoptic P age 14--20--6

Figure 14--20--4 Systems 1 and 2 -- EICAS Indications 14--20--7

SYSTEM3F igure 14--30--1 Hydraulic S ystem3 -- S chematic 14--30--2

Figure 14--30--2 Hydraulic Control P anel 14--30--3

Figure 14--30--3 System 3 -- Synoptic Page 14--30--4

Figure 14--30--4 System 3 -- EICAS Indications 14--30--5


2/20

REV 56, J an 31/03

Vol. 1 14--00--2HYDRAULIC POWER

Table of Contents

MASTERFlightCrew Operating Manual

CSP A--013

THIS PAGE INTENTIONALLY LEFT BLANK


3/20

14--10--1Vol. 1


Introduction


CSP A--013

MASTER

1. INTRODUCTION

Hydraulic power is provided by three independent systems designated No.1, No.2 and No.3.All systems operate at a nominal pressure of 3000 psi (20,685 kPa) and use synthetichydraulic fluid Skydrol.

WARNING

Skydrol is highly corrosive and can produce severeskin and eye irritation.

Systems 1 and 2 are serviced by ground service panels located in the aft equipmentcompartment. System3 is serviced by a ground service panel located on the right side ofthe fuselage, aft of the wing root.

Each systemhas two hydraulic pumps; a main pump (A) for normal power and a backuppump (B) for supplementary power. System No.1 and 2 main pumps are engine drivenpumps (EDPs). System1 EDP (1A) is driven by the left engine and system2 EDP (2A) isdriven by the right engine. System1 and 2 backup pumps (1B and 2B) are electrical ACmotor pumps (ACMPs). Both hydraulic pumps for system No.3 are ACMP s. In systemNo.3, the main pump (3A) normally runs continuously, while the backup pump (3B) isavailable during periods of high flow requirements.

The hydraulic systems supply power to operate the rudder, elevators, ailerons, spoilerons,flight spoilers, ground spoilers, wheel brakes, nosewheel steering and landing gearextension and retraction. The rudder, elevators and ailerons are powered by more than onehydraulic system to prevent loss of critical flight controls.

During a total AC power failure in flight, pump 3B will be automatically powered by the airdriven generator (ADG) when it is deployed. This will provide hydraulic pressure to thelanding gear, brakes and nosewheel steering and also provides backup hydraulic pressureto the primary flight controls.


4/20

REV 56, J an 31/03


Introduction


CSP A--013

Hydraulic Systems DiagramFigure 14---10---1

LEFT SPOILERON

RUDDER

LEFT AND RIGHTELEVATORS

NO. 1 SYSTEM

AC MOTORPUMP (1B)

ENGINEDRIVEN

PUMP (1A)

LEFT AND RIGHTOUTBOARD

GROUND SPOILERS

LEFT AND RIGHTAILERON

RUDDER


LEFT AND RIGHTINBOARD BRAKES

MAIN AND NOSE

LANDING GEAR

NOSEWHEELSTEERING

RIGHT AILERON

RUDDER


LEFT AND RIGHTFLIGHT

SPOILERS

MLG DOWNLOCKASSIST

ACTUATORS

LEFT AND RIGHTINBOARD GROUND

SPOILERS

LEFT AND RIGHTOUTBOARD BRAKES

NO. 3 SYSTEM

AC MOTORPUMP (3B)

NO. 2 SYSTEM

AC MOTORPUMP (2B)

ENGINEDRIVEN

PUMP (2A)

AC MOTORPUMP (3A)

LEFT AILERON

LEFT AND RIGHTFLIGHT SPOILERS

LEFT AND RIGHTSPOILERONS

RIGHT SPOILERON


5/20

14--10--3Vol. 1


Introduction


CSP A--013

MASTER

Hydraulic Systems OverviewFigure 14--10--2

NOSE LANDINGGEAR & STEERINGAND BRAKE CONTROL

MAIN LANDINGGEAR & INBD

BRAKES

OUTBDBRAKES

AILERON

SPOILERON

FLIGHTSPOILER OUTBDGROUNDSPOILER

INBDGROUNDSPOILER

No. 1ENGINEDRIVENPUMP

LEGEND

SYSTEM 1

SYSTEM 2

SYSTEM 3

RUDDER

No. 3AAC MOTORPUMP

No. 1BAC MOTORPUMP

No. 2ENGINEDRIVEN

PUMP

No. 3BAC MOTORPUMP

No. 2BAC MOTORPUMP


6/20

REV 56, J an 31/03


Introduction


CSP A--013

THIS PAGE IS INTENTIONALLY LEFT BLANK


7/20

14--20--1Vol. 1


Systems 1 and 2


CSP A--013

MASTER

1. HYDRAULIC SYSTEMS NO.1 AND NO.2

Each hydraulic system consists of the following components:

S Engine driven pump (EDP)

S AC motor pump (ACMP)

S Shutoff valve

S Reservoir

S Accumulator

S Pressure and return manifolds

S Filters

S Ground servicing panel.

Both No.1 and No.2 systems share a ramair heat exchanger for fluid cooling. Fluid fromeach system is not mixed with the other system as it passes through the heat exchanger. Afan within the heat exchanger assists in cooling the hydraulic fluid when the aircraft is on theground.


8/20

REV 56, J an 31/03


Systems 1 and 2


CSP A--013

Hydraulic Systems 1 and 2 SchematicFigure 14---20---1 Sheet 1

PP

S S

T

RETURNFILTER

RETURNMANIFOLD

BYPASSVALVE

GROUNDSERVICENITROGEN

ACCUMULATOR

RESERVOIRPRESSURERELIEF/BLEEDVALVE

CASEDRAINFILTER

PRESSURESWITCH

PRESSURETRANSDUCER

FILTER

CASE DRAINFILTER

ACMP 1B

PRESSURESWITCH

PRESSURERELIEFVALVE

EDP 1A

FIREWALLSOV

TO HYDRAULICSERVICES

HEATEXCHANGERAND FAN

GROUNDSUCTION

GROUNDPRESSURE

PRESSURE MANIFOLD

LEGEND

Pressure (Red).

Return (Green).

Case drain (Yellow).

Pump casefilter drain.

SYSTEM1

PRESSUREGAUGE

GROUNDSERVICE

FILLING


9/20

14--20--3Vol. 1


Systems 1 and 2


CSP A--013

MASTER

Hydraulic Systems 1 and 2 SchematicFigure 14---20---1 Sheet 2

PP

S S

T

RETURNMANIFOLD

BYPASSVALVE

ACCUMULATOR


CASEDRAINFILTER

PRESSURESWITCH

PRESSURETRANSDUCER

FILTER

CASE DRAINFILTER

ACMP 2B

PRESSURESWITCH

PRESSURERELIEFVALVE

EDP 2A

FIREWALLSOV


TO HEATEXCHANGERAT SY STEM 1

GROUNDSUCTION

GROUNDPRESSURE

PRESSURE MANIFOLD

LEGEND

Pressure (Red).

Return (Green).



SYSTEM2

FROM

OUTBOARDBRAKE

RETURNFILTER

GROUNDSERVICE

FILLINGPRESSUREGAUGE



10/20


11/20

14--20--5Vol. 1


Systems 1 and 2


CSP A--013

MASTER

C. Hydraulic Shutoff Valves

Electrically operated, normally open, hydraulic shutoff valves are installed in the suctionlines of the engine driven pumps (1A and 2A). During an engine fire condition, thecorresponding shutoff valve is motored closed when the ENG FIRE PUSH switchlight is

pressed. (See Chapter 10, Fire Protection).

Valve position is indicated on the EICAS, HYD synoptic page.

D. Reservoir

System1 and 2 reservoirs are storage tanks that hold a reserve supply of hydraulicfluid for their respective systems. The reservoirs are also partially pressurized withsystempressure to maintain a positive flow of fluid to the EDP and/or ACMP

E. Accumulator

An accumulator installed in each system stores hydraulic pressure. The accumulator is

charged with nitrogen and is used to dampen pressure surges and to maintain systempressure during momentary system demand increases.


12/20

REV 56, J an 31/03


Systems 1 and 2


CSP A--013

Systems 1 and 2 --- Synoptic PageFigure 14---20---3


13/20

14--20--7Vol. 1


Systems 1 and 2


CSP A--013

MASTER

Systems 1 and 2 --- EICAS Indications Figure 14---20---4

HYD SOV 1 or 2 CLOSED advisory (green)Indicates that corresponding shut--off valve hasbeen closed.

HYD SOV 1 or 2 OPEN caution (amber)Indicates that the respective shut--off valve isopen with an associated engine fire.

Status Page

Primary Page


14/20

REV 56, J an 31/03


Systems 1 and 2


CSP A--013

F. System Circuit Breakers

SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL

CBLOCATION

NOTES

HYD PUMP 1 AC BUS 2 A5

System 1AC PUMPCONT 1 DC BUS 2

2 G14

IND 1 G13

HYD PUMP 2 AC BUS 1 A5

System 2AC PUMPCONT 2 DC BUS 1

1 G14

y rau cSystems IND 2 G13

Fans

HYD SYSTFAN

AC BUS 1 A8

FAN CONT DC BUS 1 G12HYD SOVR ENG

1S4

uto a vesHYD SOVL ENG

S5


15/20

14--30--1Vol. 1


System 3


CSP A--013

MASTER

1. HYDRAULIC SYSTEMNO.3

Hydraulic system No.3 has the same components as systems No.1 and No.2, with theexception that No. 3 systemhas two AC motor pumps (identified as 3A and 3B) and noengine driven pump (EDP). Hydraulic systemNo.3 provides a nominal 3000 psi pressure to

the ailerons, elevators, rudder, spoilerons, landing gear actuators, inboard brakes and thenosewheel steering system. System No.3 hydraulic lines pass through the wings and arecooled by fuel.


16/20

REV 56, J an 31/03


System 3


CSP A--013

Hydraulic System 3 --- SchematicFigure 14---30---1

PP

S S

T

RETURNMANIFOLD

BYPASSVALVE

ACCUMULATOR


CASEDRAIN FILTER

PRESSURESWITCH

PRESSURETRANSDUCER

FILTER

CASE DRAINFILTER

ACMP 3B

PRESSURESWITCH

PRESSURERELIEFVALVE

ACMP 3A

FIREWALL SOV


GROUNDSUCTION

GROUNDPRESSURE

PRESSURE MANIFOLD

LEGEND

Pressure (Red).

Return (Green).



SYSTEM3

ACOUSTICFILTER

ACOUSTICFILTER

HYDRAULICTHROUGHTANKS

RETURNFILTER

GROUNDSERVICE

FILLING

PRESSUREGAUGE



17/20


18/20

REV 56, J an 31/03


System 3


CSP A--013

System 3 --- Synoptic PageFigure 14---30---3


19/20

14--30--5Vol. 1


System 3


CSP A--013

MASTER

System 3 --- EICAS Indications Figure 14---30---4

HYD PUMP 3A or 3B caution (amber)Indicates that corresponding AC motor pumphas a low pressure output ( 1800 psi).

HYD 3 HI TEMP caution (amber)Indicates that corresponding system has afluid temperature of 96 C (205 F) or greater.

HYD 3 LO PRESS caution (amber)Indicates that corresponding systempumps (both AC motor pumps) have a lowpressure output ( 1800 psi).

Primary Page

BRT


20/20

REV 56, J an 31/03


System 3

MASTERFli htC O ti M l

B. System Circuit Breakers

SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL

CBLOCATION

NOTES

HYD PUMP 3A AC BUS 2 A2PUMP CONT3A

DC BUS 22

G15

Pum s HYD PUMP 3B AC BUS 1 A2

HydraulicPUMP CONT3B

DC BUS 11

G11

ESS HYDPUMPSUPPLY

ADG BUS 3 A11

Indication HYD SYST DC BATTERYIND 3 BUS

bombardier crj 00-hydraulic power

Documents