TECHNICAL TRAINING ENGINE RUNUP
VERSION V5.01
CS130-21.10-05.01-120117
BD-500-1A10
BD-500-1A11
CUSTOMER TRAINING
Montreal Training Centre
8575 Côte-de-Liesse Road
Saint-Laurent, Québec, Canada H4T 1G5
Telephone (514) 344-6620
Toll-Free North America 1 (877) 551-1550
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Bombardier Inc., by its groups, divisions, or its corporate subsidiary Learjet Inc. (collectively "Bombardier"),
provides this information to its customers and to the government in confidence. This is proprietary confidential
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release of this information would be harmful to Bombardier or its corporate subsidiary Learjet Inc. Any intention to
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It is understood that this documentation, comprising technical data and other information in any media shall not
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purposes.
Copyright © 1999-2017 Bombardier Inc. or its subsidiaries. All rights reserved.
Bombardier and C Series are either registered trademarks or trademarks of Bombardier Inc. or its subsidiaries.
Copyright © Bombardier Inc.
CS130-21.10-05.01-120117
Engine Runup
For Training Purposes Only
Engine Runup
List of Changes
The following table details the changes applied to this revision:
SECTION
CMUI NUMBER
CHANGES APPLIED
Flight Deck Check
CS130-21.10-05.01-120117
Under engine oil level, the quantity was changed from
10 QTS to 10 L (pge 14)
Approach Idle
CS130-21.10-05.01-120117
Calculations for adjusted target N1speed changed
(pge 27)
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
LOC i
Engine Runup
Page Intentionally Left Blank
Engine Runup
CS130-21.10-05.01-120117
LOC ii
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
Table of Contents
Introduction ...........................................................................................................................1
Power Plant Runup ...............................................................................................................1
Hazard Area ...........................................................................................................................3
Jet Wake Hazard Area...........................................................................................................4
Wind Direction .......................................................................................................................5
Engine Flight Deck Controls and Indications.....................................................................6
Engine Operation Limitations ..............................................................................................9
Starter Duty Cycle ..........................................................................................................................................9
Main Oil Pressure Limits ....................................................................................................10
Rotor Bow ............................................................................................................................11
Checklist ..............................................................................................................................12
Exterior Check ..............................................................................................................................................12
Flight Deck Preparation ................................................................................................................................12
APU Start.......................................................................................................................................................13
APU Fire Procedure .....................................................................................................................................13
Flight Deck Check .........................................................................................................................................14
Automatic Start....................................................................................................................15
Manual Start.........................................................................................................................16
Discontinued Start ..............................................................................................................18
Idle Power Test ....................................................................................................................19
Power Assurance Test........................................................................................................20
Acceleration/Deceleration Test..........................................................................................26
Approach Idle ................................................................................................................................................27
N1 Accel Time ..............................................................................................................................................27
High-Pressure Ducting System Operation Test ...............................................................30
Normal Engine Shutdown...................................................................................................32
Emergency Procedure Shutdown......................................................................................33
Engine Start After Emergency Shutdown .........................................................................34
Engine Fire Procedure .........................................................................................................34
Normal Procedures .............................................................................................................35
Normal Engine Shutdown .............................................................................................................................35
Non-Normal Procedures .....................................................................................................36
Engine Start After Emergency Shutdown .....................................................................................................36
Emergency Procedures ......................................................................................................37
Emergency Procedure Shutdown .................................................................................................................37
APU Fire Procedure .....................................................................................................................................38
Engine Fire Procedure ..................................................................................................................................38
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
i
Engine Runup
List of Figures
Figure 1:
Figure 2:
Figure 3:
Figure 4:
Figure 5:
Figure 6:
Figure 7:
Figure 8:
Hazard Areas......................................................................................................... 3
Jet Wake Hazard Areas......................................................................................... 4
Wind Direction and Velocity................................................................................... 5
Engine Controls and Indications............................................................................ 6
Engine APU FIRE Panel and APU Panel Controls and Indications ...................... 7
STATUS Synoptic and OMS Brake Pressure Pages ............................................ 8
Main Oil Pressure Limits (Reference).................................................................. 10
Rotor Bow ........................................................................................................... 11
Engine Runup
CS130-21.10-05.01-120117
ii
Copyright © Bombardier Inc.
For Training Purposes Only
Power Plant Runup
Engine Runup
Introduction
Power Plant Runup
Always refer to the Power Plant Ground Run Publication (PPGRP) before performing engine ground runs.
WARNING
BE CAREFUL WHEN WORKING ON THE ENGINE AFTER SHUTDOWN. THE ENGINE AND
ENGINE OIL CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS WARNING,
INJURY CAN OCCUR.
CAUTION
In the event of oil temperature being below -40°F (-40°C) limitation for starting, it is
required that the oil be heated above -40°F (-40°C) prior to an attempted start.
The engine must remain at idle until the ENG OIL LO TEMP caution message is no longer
shown.
If the engine oil temperature is between -6° and 49°C, N1 is limited to 50%.
If idle is not selected, the engine starts regardless of the thrust lever position and thrust
rapidly increases to that demanded by the TLA, causing a hazardous situation.
With the fan cowl and thrust reverser doors open, do not advance the throttle more than
the idle position.
Do not open fan cowl and thrust reverser doors for maintenance when wind velocity is
greater than 20 kt. After fan cowl doors are opened, they can stay open for wind velocity
up to 30 kt.
An autostart can be manually aborted at any point by switching the ENG RUN SWITCH L
(R) to OFF. In the AUTOSTART mode, the automatic start abort feature is active only when
N2 is less than 54%. When N2 is greater than 54%, crew action is required to manually
abort the start.
No running engagement of starter with N2 greater than 20%.
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
1
Power Plant Runup
Engine Runup
CAUTION
For manually aborted starts, an engine dry crank must be performed for 30 seconds (not
to exceed 1 minute) to clear out trapped fuel and to provide cooling to decrease EGT.
Do not start the engine if there is ice on the fan blades. Ice on the fan blades can cause
rotor imbalance and damage to the engine.
Only authorized personnel should go near the engine only at idle power and use the
entry corridor areas.
Do not operate the engine above idle power or in reverse with people in the entry
corridor. Refer to Figure 1.
When the reverser operates, stay away from the danger areas at the front and sides of
the engine. Reversers blow fan discharge air out the sides of the engine towards the
front of the aircraft, and can suck this air back into the engine and cause damage.
Stay away from the engine exhaust area when the engine starts or operates. The jet
wake is hot and of sufficient velocity to cause a fall, injury or death. See Figure 2.
Usual starter duty cycle is three starter crank cycles for a total of 4 minutes cranking time maximum, or
4 minutes maximum continuous cranking. If three motoring duty cycles are done in a row, let the starter cool off
for at least 30 minutes.
Single engine operation is permitted at idle power only. For engine operation above idle run both engines.
NOTE
The engine start cycle incorporates an overtemperature start protection function that terminates
a ground start if the EGT limit is exceeded for 5 seconds.
If the EDP appears to be producing erratic pressures above or below normal system pressure
operation shutdown the engine.
If the vibration CAS message is indicated, return to idle. If the vibration continues to indicate
when at idle, shutdown the engine. Monitor temperature for icing conditions.
Refer to Figure 4 for engine controls and indications.
Engine Runup
CS130-21.10-05.01-120117
2
Copyright © Bombardier Inc.
For Training Purposes Only
Hazard Area
Engine Runup
Hazard Area
Takeoff Power
Inlet Hazard Area
Ground Idle
Inlet Hazard Area
2.74 m
(9 ft)
6.10 m
(20 ft)
1.83 m
(6 ft)
0.91 m
(3 ft)
30°
61 m
(200 ft)
183 m
(600 ft)
LEGEND
30°
Figure 1: Hazard Areas
Copyright © Bombardier Inc.
For Training Purposes Only
S1_CS3_71ARU_003
Inlet Hazard Area
Entry Corridor
Exhaust Danger Area (Aft of Exhaust Nozzle):
61.0 m (200 ft) – Ground Idle (20 kt Headwind)
183.0 m (600 ft) – Takeoff Power (20 kt Headwind)
Engine Runup
CS130-21.10-05.01-120117
3
Jet Wake Hazard Area
Engine Runup
Jet Wake Hazard Area
18.0 m
(60 ft)
15.0 m
(50 ft)
12.0 m
(40 ft)
9.0 m
(30 ft)
6.0 m
(20 ft)
3.0 m
(10 ft)
Gound Idle Thrust
0 m (0 ft)
0
3.0 m
(10 ft)
6.0 m
(20 ft)
9.0 m
(30 ft)
12.0 m
(40 ft)
15.0 m
(50 ft)
18.0 m
(60 ft)
Maximum Takeoff Thrust
0 m (0 ft)
415 kt (477 mph)
10 m (33 ft)
355 kt (409 mph)
16 m (51 ft)
295 kt (341 mph)
19 m (63 ft)
60 kt (68 mph)
21 m (68 ft)
235 kt (273 mph)
24 m (78 ft)
175 kt (204 mph)
30 m (98 ft)
30 kt (34 mph)
38 m (124 ft)
120 kt (137 mph)
42 m (138 ft)
17 kt (20 mph)
61 m (199 ft)
60 kt (68 mph)
76 m (248 ft)
30 kt (34 mph)
145 m (475 ft)
LEGEND
Figure 2: Jet Wake Hazard Areas
Engine Runup
CS130-21.10-05.01-120117
4
S1_CS3_71ARU_019
Exhaust Danger Area (AFT of Exhaust Nozzle)
Copyright © Bombardier Inc.
For Training Purposes Only
Wind Direction
Engine Runup
Wind Direction
Wind direction and velocity can change engine stability. Where possible, operate engine with intake pointed into
the wind. Wind velocities shown are for constant wind conditions only. Reduce maximum wind velocity limits
shown for gusty velocities. Refer to Figure 3:
Starting:
• 35 kt Max crosswind
• 15 kt Max tailwind
Stop engine operation if:
• N1 speed is not stable
• At a steady state, inlet noise increases or changes to a blow torch sound
• At a steady state, engine vibration increases
0º
Headwind
320º
40º
Crosswind 270º
90º
Crosswind
NOTE
The wind velocities provided include wind gust conditions.
Tailwind
GROUND OPERATIONS AT IDLE
INDICATION
GROUND OPERATIONS UP TO THE
MAXIMUM N1 GROUND SPEED
No limit.
No limit.
Permitted 35 Kt. maximum wind velocity.
Unrestricted up to 25 Kt. maximum wind
velocity. Rolling take off procedure required
between 25 and 35 Kt. maximum wind velocity.
Permitted 15 Kt. maximum wind velocity.
Unrestricted up to 10 Kt. maximum wind
velocity. Rolling take off procedure required
between 10 and 15 Kt. maximum wind velocity.
CS1_CS3_71ARU_020
INDICATION
Figure 3: Wind Direction and Velocity
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
5
Engine Flight Deck Controls and Indications
Engine Runup
Engine Flight Deck Controls and Indications
B
A
CLB
MAX
MAX
92.2
92.2
73.0
73.3
Right Engine
Thrust Lever
N1
Left Engine
Thrust Lever
IDLE
IDLE
718
722
EGT
R ENG
ON
ON
OFF
Continuous
Ignition
Normal
86.5
1090
124
116
OFF
ENGINE
NE
CONT
IGNITION
START
L
ENG
CRANK
AUTO
R
ENG
CRANK
PILOT
EVENT
ON
N2
FF (PPH)
OIL TEMP
OIL PRESS
A
Engine Start
L or R Crank
B
Engine Run
Switches
Figure 4: Engine Controls and Indications
Engine Runup
CS130-21.10-05.01-120117
6
EICAS
86.6
1110
124
116
_CS3_71ARU_010
L ENG
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Flight Deck Controls and Indications
Engine Runup
L ENG
APU
R ENG
F IIRE
FI RE
FI RE
BTL 1
BTL 2
BTL
BTL 1
BTL 2
AVAIL
AVAIL
AVAIL
AVAIL
AVAIL
ENGINE AND APU FIRE PANEL
APU
OFF
RUN
START
PULL
TURN
CS1_CS3_7100_020
APU PANEL
Figure 5: Engine APU FIRE Panel and APU Panel Controls and Indications
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
7
Engine Flight Deck Controls and Indications
Engine Runup
STATUS
AIR
DOOR
ELEC
FLT CTRL
FUEL
HYD
AVIONIC
INFO
CB
MAINT MENU
RETURN TO
LRU/SYS OPS
BCS-Brake Data
Write Maintenance Reports
15 °C
15 °C
TAT
SAT
L Thrust Lever Angle
R Thrust Lever Angle
L
R
L
R
ENGINE
103
113
21.8
103
113
21.8
OIL TEMP (°C)
OIL PRESS (PSI)
OIL QTY (L)
APU
RPM
EGT
DOOR
100 %
312 °C
OPEN
OIL TEMP
OIL PRESS
OIL QTY
75 °C
NORM
NORM
TIRE PRESSURE (PSI)
150
208
150
208
208
209
BRAKE
00
00
TEMP
01
01
Pilot BRK Pedal Pos
Pilot BRK Pedal Pos
CoPilot BRK Pedal Pos
CoPilot BRK Pedal Pos
BDCU 1
22
BDCU 2
001 /002
Units
22
0
0
0
0
0
0
0
0
%
%
%
%
LOB
LOB
LOB
LOB
LOB
BRK
EMA
EMA
EMA
EMA
Force
1 BRK
2 BRK
3 BRK
4 BRK
Average
Force
Force
Force
Force
11499
11499
11499
11499
11499
11499
11499
11499
11499
11499
LBS
LBS
LBS
LBS
LBS
LIB
LIB
LIB
LIB
LIB
BRK
EMA
EMA
EMA
EMA
Force
1 BRK
2 BRK
3 BRK
4 BRK
Average
Force
Force
Force
Force
11499
11499
11499
11499
11499
11499
11499
11499
11499
11499
LBS
LBS
LBS
LBS
LBS
RIB
RIB
RIB
RIB
RIB
BRK
EMA
EMA
EMA
EMA
Force
1 BRK
2 BRK
3 BRK
4 BRK
Average
Force
Force
Force
Force
11499
11499
11499
11499
11499
11499
11499
11499
11499
11499
LBS
LBS
LBS
LBS
LBS
ROB
ROB
ROB
ROB
ROB
BRK
EMA
EMA
EMA
EMA
Force
1 BRK
2 BRK
3 BRK
4 BRK
Average
Force
Force
Force
Force
11499
11499
11499
11499
11499
11499
11499
11499
11499
11499
LBS
LBS
LBS
LBS
LBS
CS1_CS3_7100_021
SYNOPTIC PAGE - STATUS
Figure 6: STATUS Synoptic and OMS Brake Pressure Pages
Engine Runup
CS130-21.10-05.01-120117
8
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Operation Limitations
Engine Runup
Engine Operation Limitations
Table 1: Engine Operation Limitations
OPERATING CONDITIONS
Thrust Setting
OPERATING LIMITS
Time Limit
MAX ITT
N2 100%=24,470 RPM
N1 100%=10,600 RPM(*1)
Oil Pressure
(*2)
Oil
Temperature
(*3)
(minutes)
°C (°F)
RPM
%
RPM
%
PSIG
°C (°F)
Maximum
Takeoff
5 (*4)
1054
(1929)
24,470
100
10,600
100
Refer to
Figure 5
49 to 168
(120 to 335)
(*5)
Maximum
Continuous
(*6)
Continuous
1006
(1842)
24,470
100
10,600
100
Refer to
Figure 5
49 to 168
(120 to 335)
(*6)
Reverse
Thrust
As Required
1054
(1929)
24,470
100
10,600
100
Refer to
Figure 5
49 to 168
(120 to 335)
GND Idle
(SL)
Continuous
-
-
-
-
-
Refer to
Figure 5
-40 to 168
(-40 to 335)
Flight Idle
Continuous
-
-
-
-
-
Refer to
Figure 5
-40 to 168
(-40 to 335)
Starting
(*7)
Continuous
1054
(1929)
-
-
-
-
Refer to
Figure 5
-40 to 168
(-40 to 335)
NOTE
1. Fan ratio is 3.0625 NFan equals 1 N1 or 10,600 N1 is equivalent to 3.461 NFan.
2. Maximum oil pressure is for up to 10 minutes. See Figure 5.
3. Maximum oil temperature of 174°C (345°F) is for up to 20 minutes. Total operation between
163°C (325°F) up to 174°C (345°F) must not exceed 20 minutes.
4. Time limit may be extended to 10 minutes for one engine inoperative (OEI) contingency.
5. Minimum oil temperature for operation above idle is 49°C (120°F).
6. Maximum continuous (MCT) is the maximum thrust approved for continuous operation.
7. Starting sequence begins when the start switch is pressed ON (or start sequence is
initiated), and continues until stable idle speed is achieved (stabilized EGT and N2 speed).
Starter Duty Cycle
Usual starter duty cycle is three started crank cycles for a total of 4 minutes maximum cranking time or 4 minutes
maximum continuous cranking time.
After three motoring cycles, one after another, starter off time period must be 30 minutes. Maintain off time period
before each subsequent duty cycle.
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
9
Main Oil Pressure Limits
Engine Runup
Main Oil Pressure Limits
200
MAIN OIL PRESSURE (PSIG)
on
perati
mal O
Nor
ximum
Ma
150
Minimum
100
peration
Normal O
m Limit
Minimu
50
0
13000
(53)
14000
(57)
15000
(61)
16000
(65)
17000
(69)
18000
(74)
19000
(78)
20000
(82)
21000
(86)
22000
(90)
23000
(94)
24000
(98)
CS1_CS3_71ARU_004
HIGH ROTOR N2 SPEED – MECHANICAL RPM
(% RPM)
Figure 7: Main Oil Pressure Limits (Reference)
Engine Runup
CS130-21.10-05.01-120117
10
Copyright © Bombardier Inc.
For Training Purposes Only
Rotor Bow
Engine Runup
Rotor Bow
The motor-to-start time for rotor bow prevention is based on an altitude/outside air temperature (OAT)
graph. Within the altitude/OAT envelope, the motor-to-start time is 30 seconds. As the distance outside
the altitude/OAT envelope increases, the motor-to-start time increases.
An ENG START DELAY advisory message is displayed anytime an engine start is initiated outside of
the envelope. The message clears when the motor-to-start phase is complete.
ALT
14000 ft
30 Second
Motor-To-Start Time
5000 ft
ENG START DELAY
ENG START DELAY
-2000 ft
OAT
-5°C
+43°C
CS1_CS3_7100_022
-17°C
Figure 8: Rotor Bow
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
11
Checklist
Engine Runup
Checklist
Exterior Check
ACTION
RESULT
Chocks on Main Landing Gear
IN POSITION FWD AND AFT OF WHEELS
Gear Pins
INSTALLED
Fan Rotation
FREE
Engine Inlet/Exhaust
CLEAR AND NO ICE
Engine Cowls and Access Panels
SECURED
Engine Direct Inlet/Exhaust Ramp Area
CLEAR AND NO FOD
Ground Fire Extinguisher
POSITIONED WITH PERSONNEL
Pilot/Static Ports
COVERS REMOVED
Compartments and Access Doors
CLOSED
Cabin Doors
CLOSED (except for crew access)
GPU
AS REQUIRED (safe position)
Direct Aircraft Surrounds
CLEAR OF EQUIPMENT AND FOD
Blast Area
SAFE ZONE DIRECTION
Make sure the recommended wind velocity is met. Refer to Figure 3.
Aircraft MUST be more than 60 m (200 ft) away from any wall or blast fence at idle. Data is invalid when the test
is performed with the engine exhaust directed towards a wall or blast fence.
Flight Deck Preparation
ACTION
RESULT
On the CENTER MAIN INSTRUMENT PANEL:
LD GEAR HANDLE
DN
On the CENTER PEDESTAL:
L(R) Thrust Levers
L(R) ENGINE RUN Switch
CONT IGNITION Switch
ENGINE START Switch
SPOLIER Lever
SLAT/FLAP Lever
ALT FLAP
PARK BRAKE
IDLE
OFF
PBA OUT
AUTO
RET
POS 0
NORM
ON
Engine Runup
CS130-21.10-05.01-120117
12
Copyright © Bombardier Inc.
For Training Purposes Only
Checklist
Engine Runup
APU Start
ACTION
RESULT
BATT 1 and BATT 2
AUTO
Ground Power if required:
GPU
(BD500-A-J24070-00-00AAA-34DB-A)
EXT PWR PBA in
AVIONIC Synoptic Page AVIO Tab:
Select FIRE test
DONE shown beside FIRE
Start APU
Pull and turn the APU switch to the START position and
release to RUN
On the STATUS synoptic page:
APU DOOR indicates open
APU RPM increases
On EICAS:
APU GEN OFF caution message
APU IN START status message
On the FUEL synoptic page:
APU feed SOV open
APU flow line green
APU fuel filter green
At 70% rpm:
APU IN START status message off
APU ON status message on
On STATUS synoptic page at 100% rpm:
RPM 91 to 100%
EGT less than 950°C
DOOR OPEN
OIL TEMP NORM
OIL PRESS NORM
OIL QTY FULL
NOTE
The APU start from battery shall only be allowed if there are two batteries available and TRU 3 is
not available. A battery start is allowed with one battery available and a TRU feeding the DC
BUSES when TRU 3 is not available.
Time limits for operating the APU with access doors open are 10 minutes maximum APU not
loaded, and 5 minutes maximum APU loaded.
If the APU is operated with the access doors open, make sure that fire fighting equipment is
available.
APU Fire Procedure
CONTROL
SETTING
APU Fire
APU Switch
APU FIRE PBA
APU BTL
OFF
PRESS
PRESS
Evacuate the aircraft if necessary.
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
13
Checklist
Engine Runup
Flight Deck Check
ACTION
RESULT
On rear bulkhead MAINTENANCE PANEL:
AIRCRAFT and BATT PWR knob
CHAN switch
AS REQUIRED
OFF
CBs/SSPCs
ALL IN (except those pulled INOP systems)
AVIONIC Synoptic Page, AVIO Tab:
Select AURAL Test
Select LAMP Test
Select ICE DETECT Test
Select FIRE Test
DONE shown beside AURAL
DONE shown beside LAMP
PASS shown beside ICE DETECT
DONE shown beside FIRE
Engine Oil Level
On STATUS synoptic page
MIN OIL LEVEL 10 L
On the OVERHEAD PANEL:
PBAs
HYD Rotary Switches
FUEL MAN XFR
L(R) BOOST PUMP
XBLEED
APU BLEED
L(R) COWL and WING ANTI-ICE
ELT
EQUIP COOLING EXHAUST
EMER DEPRESS
AUTO PRESS
MAN RATE knob
EMER, EXT, LDG LTS
WING LIGHTS
No White Light EXCEPT EXT PWR
ACMP 2B ON, 3A and 3B AUTO
OFF
AUTO
AUTO
AS REQUIRED
OFF
ARM
AUTO
PBA IN (ON light ON)
PBA IN (MAN light ON)
12 O’CLOCK POS
OFF
AS REQUIRED
On the CENTER MAIN INSTRUMENT PANEL:
ALTN GEAR
GEAR AURAL, ALTN BRAKE
AUTOBRAKE
NOSE STEER
NORM
PBAs OUT NO LIGHT
OFF
PBA OUT NO LIGHT
EICAS
NO ENGINE Alerts/Warnings Displayed
Audio Control Panel
VHF 1
VHF 2
INTERPHONE
Set one radio to EMERGENCY FREQUENCY
Set second radio to local applicable FREQUENCY
Check with ground crew
BEACON
ON
NOTE
ACMP 2B is selected on to ensure hydraulic power is available for steering.
Record fuel quantity before and after runup and uplift (if applicable).
Engine Runup
CS130-21.10-05.01-120117
14
Copyright © Bombardier Inc.
For Training Purposes Only
Automatic Start
Engine Runup
Automatic Start
(BD500-A-J71-00-00-00AAA-130A-A_001)
CONTROL
SETTING
L(R) Thrust Levers
Set to MIN idle
Bleed Air Pressure
40 psi
Ground personnel check
OK to start engine (s)
CAUTION: MAX EGT 1054°C (Normal start EGT range 550°C)
L(R) ENG RUN Switch
ON
Monitor EICAS:
N2
Greater than 18% N2:
FUEL FLOW
EGT
Oil Pressure
N1 and N2
50 to 55% N2
L(R) START displayed
ENGINE START DELAY displayed if
motor-to-start cycle is > 30 seconds
Engine dry cranks 7% - 13% N2 for a minimum
of 30 seconds
ENGINE START DELAY off at the end of
motor-to-start cycle
INCREASING
IGN displayed
Indicates 90 kg/hr rising
Rising
Rising
Increasing
IGN goes OFF
START goes OFF
If oil pressure is < 70 psi after 30 seconds at MIN IDLE, shutdown the engine.
CONFIRM ENGINE OPERATING WITHIN TABLE 1 AND FIGURE 5 PARAMETERS
EICAS
HYD Synoptic Page:
Hydraulic pressure system no. 1 (2)
EDP 1 (2) Outline
EDP 1 (2) Flow Line
EICAS
After 5 minutes at MIN Idle, record the following:
NOT SHOWN:
L(R) ENG STARTER FAIL
L(R) ENGINE FAULT
FUEL INERTING FAULT
ENG CONT IGNITION
3000+/-200 psi within 30 seconds
Changes from white to green
Change from white to green
NOT SHOWN:
HYD 1 (2) LO PRESS
HYD EDP 1A FAIL
ENG 1
ENG 2
N1
-------------EGT
%
-----------------------°C
N2
------------FUEL FLOW
%
-----------------------kg/hr
(pph)
°C
OIL TEMP
-------------
°C
------------------------
psi
OIL PRESS
psi
psi
HYD PRESS
psi
%
---------------------°C
%
--------------------kg/hr
(pph)
---------------------
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
15
Manual Start
Engine Runup
Manual Start
CONTROL
SETTING
L(R) Thrust Levers
Set to MIN idle
Bleed air pressure
40 psi
CONT IGNITION
PBA in
Ground personnel check
OK to start engine(s)
CAUTION: MAX EGT 1054°C (Normal start EGT range 550°C)
WARNING: In manual start mode, automatic abort feature is not active and you MUST manually
abort the starting sequence.
ENGINE START Switch
Hold in L(R) ENG CRANK
ENGINE START DELAY displayed if
motor-to-start cycle is > 30 seconds
Engine dry cranks 7% - 13% N2 for a minimum
of 30 seconds
ENGINE START DELAY off at the end of
motor-to-start cycle
EICAS Confirm
N2
RISING
At max motoring (not less than 18% N2)
Set L(R) ENG RUN switch to ON
Monitor EICAS:
L(R) START displayed
IGN displayed
Fuel Flow
EGT
OIL PRESSURE
N1 and N2
50 to 55% N2, ENG START Switch
INDICATE 90 kg/hr RISING
RISING
RISING
INCREASING
Released to AUTO
IGN goes OFF
START goes OFF
IGN (white) ON
CONT IGNITION PBA OUT
If oil pressure <70 psi after 30 seconds at MIN IDLE, shutdown the engine.
Engine Runup
CS130-21.10-05.01-120117
16
Copyright © Bombardier Inc.
For Training Purposes Only
Manual Start
Engine Runup
ENGINE OPERATING WITHIN TABLE 1 AND FIGURE 5 PARAMETERS
EICAS
HYD Synoptic Page:
Hydraulic pressure system no. 1 (2)
EDP 1 (2) Outline
EDP 1 (2) Flow Line
EICAS
NOT SHOWN:
L(R) ENG STARTER FAIL
L(R) ENGINE FAULT
FUEL INERTING FAULT
ENG CONT IGNITION
3000+/-200 psi within 30 seconds
Changes from white to green
Change from white to green
NOT SHOWN:
HYD 1 (2) LO PRESS
HYD EDP 1A FAIL
After 5 minutes at MIN Idle, record the
following:
ENG 1
ENG 2
N1
-------------EGT
%
----------------------°C
N2
------------FUEL FLOW
%
----------------------kg/hr
(pph)
°C
OIL TEMP
-------------
°C
----------------------
psi
OIL PRESS
psi
psi
HYD PRESS
psi
%
--------------------°C
%
--------------------kg/hr
(pph)
---------------------
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
17
Discontinued Start
Engine Runup
Discontinued Start
Abort start if:
• No N1 rotation by +/- 30% N2
• N2 fails to reach stabilized idle speed within 120 seconds
• No EGT rise after 20 seconds from positive fuel flow indication
• Oil pressure does not increase within 30 seconds
• EGT greater than 1054°C (Hot Start)
In automatic start, the automatic abort feature is active only when the starter is engaged and N2< 54%. If N2 is
greater than this value, start MUST be manually discontinued as follows:
ENGINE START DISCONTINUED (IN AUTO MODE)
L(R) ENG RUN SWITCH
Set to OFF
ENGINE START DISCONTINUED (IN MANUAL MODE)
L(R) ENG RUN SWITCH (If ON)
ENGINE START SWITCH
When L(R) Engine N2 <20%:
CONT IGNITION
ENGINE START SWITCH
ENGINE START SWITCH
Set to OFF
Release to AUTO
EEC WILL automatically engage starter for
30 seconds, after a start AUTO abort when:
No EGT increase (no light OFF)
No acceleration (hung start)
High EGT (hot start)
EEC WILL NOT automatically engage starter after a
start AUTO abort when:
No N1 indication after N2 > 30%
Loss of EGT indication
Inability to control fuel flow
EEC unable to command either igniter in EEC channels
Failure/unsuccessful automatic restart
Engine Runup
CS130-21.10-05.01-120117
18
PBA out NO LIGHT
Turn and hold to L(R) ENG CRANK for 30 seconds.
Release to AUTO
Copyright © Bombardier Inc.
For Training Purposes Only
Idle Power Test
Engine Runup
Idle Power Test
This test provides the procedure for doing an operation check of the engine and a check of the fuel and oil
systems for leaks. The engine is to be operated at MIN IDLE power only for this test.
CAUTION
When the engine operates with the cowl doors open, the fire department personnel must
be at the engine. The aircraft fire extinguishing system does not operate with the cowl
doors open.
Do not operate the engine with the cowl doors open if the wind velocity is more than
20 kt. If you do, damage to the cowl doors can occur.
When the cowl doors are open, you must operate the engine at minimum idle power only.
If you operate the engine at a higher power, you can cause damage to the cowl doors.
NOTE
The fuel system can contain air after the replacement of fuel components and tubes. If this is the
first engine start after the replacement of fuel components or tubes, the fuel flow can change
quickly while the air is purged from the fuel system. This temporary condition is usual and
satisfactory.
Start Engine (s)
Maintain MIN IDLE for 5 minutes
Do a GVI of engine drain system for leaks
ENG 1
RECORD ENGINE PARAMETERS
ENG 2
N1
%
%
EGT
°C
°C
N2
%
%
FUEL FLOW
kg/hr
PPH
kg/hr
PPH
OIL TEMPERATURE
°C
°C
OIL PRESSURE
PSI
PSI
Perform engine shutdown
Do a GVI of fuel, oil, hydraulic tubing system
for leaks
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
19
Power Assurance Test
Engine Runup
Power Assurance Test
(BD500-A-J71-00-00-01AAA-320B-A_002)
This test provides the procedure for a power assurance test of the engine. All engines complete an acceptance
test procedure prior to delivery. The test confirms that an engine generates certified thrust level.
This procedure may be used to verify that an installed engine meets the rated takeoff thrust within EGT, N2, and
fuel flow limits.
Pressure altitude of the test location must be between -2,000 ft and 14,500 ft.
To display brake pressure while doing high power engine runs, select the OMS, DATA, MAINTENANCE,
LRU/ SYS OPS, and BRAKE CONTROL. The brake pressure will be displayed in real time.
NOTE
Test is to be performed one engine at a time.
Use OAT to find N1 speed target value in Table 2, and record data in the expected value column below.
POWER ASSURANCE DATA
EXAMPLE
OAT
°C
Barometric Pressure
Set to 29.92 in
OAT
15°C
Barometric Pressure
Set to 29.92 in
Record Pressure Altitude
ft
Record Pressure Altitude
Wind Direction
°
Wind Direction
240°
Wind Speed
10/kt
Aircraft Heading
240°
Wind Speed
/kt
Aircraft Heading
°
Expected Value
150 ft
Expected Value
N1 Target
%
N1 Target
78.3%
N2 (min)
%
N2 (min)
88.7%
N2 (max)
%
N2 (max)
89.6%
EGT Minimum
°C
EGT Minimum
760°C
EGT Maximum
°C
EGT Maximum
816°C
Fuel Flow Minimum
kg/hr
(pph)
Fuel Flow Minimum
1807 kg/hr
3983 (pph)
Fuel Flow Maximum
kg/hr
(pph)
Fuel Flow Maximum
2013 kg/hr
4438 (pph)
Cowl Anti-Ice (circle)
Engine Runup
CS130-21.10-05.01-120117
20
ON
OFF
Cowl Anti-Ice (circle)
ON
OFF
Copyright © Bombardier Inc.
For Training Purposes Only
Power Assurance Test
Engine Runup
POWER ASSURANCE TEST
%
Record N1 Target:
Start engines (auto or manual mode)
L(R) GEN
OFF for the test engine.
L(R) Wing Anti-Ice (WAI)
OFF for the tested engine.
L(R) Cowl Anti-Ice (CAI)
OFF for the test engine (ON if rain or snow are present,
or fog visibility <1. 6 km (1 mile).
L(R) BLEED
OFF for the tested engine.
After idling for 15 minutes, slowly increase thrust of test engine to N1 target and stabilize for 5 minutes.
If necessary for aircraft static stability, bring the untested engine above forward (FWD) idle.
RECORD ACTUALS
ENG 1
ENG 2
N1 Actual
%
%
EGT Actual
°C
°C
N2 Actual
%
%
kg/hr
(pph)
kg/hr
(pph)
Oil Temperature Actual
°C
°C
Oil Pressure Actual
psi
psi
Fuel Flow Actual
L(R) Thrust Levers
Slowly retard to MIN IDLE for
5 minutes
Perform engine shutdown
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
21
Power Assurance Test
Engine Runup
Correct the recorded engine data before comparing with the
power assurance limits in Table 2.
EXAMPLE
N1%= 78.7, N1% target= 78.3, EGT= 803°C, N2%= 89.3
Fuel Flow= 1863 KG/HR, Press. Alt.= 150 ft, NAI= OFF
EGT, N2 and Fuel Flow correction
EGT (actual)
°C
For pressure altitudes above sea level,
subtract 1.5°C (1.8°F) for each 1000 ft
(305 m) above sea level
-
For pressure altitudes below sea level, add
1.5°C (1.8°F) for each 1000 ft (305 m) below
sea level
+
.225
For errors in N1 setting, subtract 9°C (16.2°F)
for each percent above the target
For errors in N1 setting, add 9°C (16.2°F) for
each percent below the target
+
If Nacelle Anti-Ice ON, subtract 8°C
(14.4°F)
-
Corrected EGT =
N2 (actual)
803°C
3.6
---
°C
799.2°C
%
89.3%
No adjustment necessary for pressure altitude
or use of nacelle anti-ice
---
For errors in N1 setting, subtract 0.33% for
each percentage above the target
-
For errors in N1 setting, add 0.33% for each
percent below the target
+
Corrected N2 =
Fuel Flow (actual)
%
---
%
89.2%
pph
1863
kg/hr
For pressure altitudes below sea level, subtract
125 pph for each 1000 ft (305 m) below sea
level
For pressure altitudes above sea level, add
125 pph for each 1000 ft (305 m) above sea
level
+
For errors in N1 setting, subtract 145 pph for
each percent above the target
-
0.132%
kg/hr
For pressure altitudes below sea level,
subtract 57 kg/hr for each 1000 ft (305 m)
below sea level
---
For pressure altitudes above sea level,
add 57 kg/hr for each 1000 ft (305 m)
above sea level
8.55
For errors in N1 setting, subtract 66 kg/hr
for each percent above the target
26.4
For errors in N1 setting, add 145 pph for each
percent below the target
+
---
For errors in N1 setting, add 66 kg/hr for
each percent below the target
-
---
If Nacelle Anti-Ice was ON, subtract
23 kg/hr
If Nacelle Anti-Ice was ON, subtract 50 pph
Corrected Fuel Flow =
pph
1845.2
kg/hr
kg/hr
Perform engine shutdown
Engine Runup
CS130-21.10-05.01-120117
22
Copyright © Bombardier Inc.
For Training Purposes Only
Power Assurance Test
Engine Runup
Table 2: Power Assurance Test
OAT
PERCENT
N1
PERCENT N2
EGT (°C)
WF PPH
WF -KG/HR
Deg C
Target
Minimum
Maximum
Minimum
Maximum
Minimum
Maximum
Minimum
Maximum
-54
68.3
77.3
78.2
552
578
3389
3776
1537
1713
-53
68.4
77.5
78.4
526
582
3398
3786
1541
1717
-52
68.6
77.7
78.6
529
585
3407
3795
1545
1722
-51
68.8
77.9
78.7
533
589
3415
3805
1549
1726
-50
68.9
78.0
78.9
536
592
3424
3815
1553
1730
-49
69.1
78.2
79.1
540
596
3433
3825
1557
1735
-48
69.2
78.4
79.3
543
600
3442
3835
1561
1739
-47
69.4
78.6
79.4
547
603
3451
3844
1565
1744
-46
69.5
78.7
79.6
551
607
3459
3854
1569
1748
-45
69.7
78.9
79.8
554
610
3468
3864
1573
1753
-44
69.8
79.1
80.0
558
614
3477
3874
1577
1757
-43
70.0
79.3
80.1
561
617
3486
3884
1581
1762
-42
70.1
79.4
80.3
565
621
3494
3893
1585
1766
-41
70.3
79.6
80.5
568
624
3503
3903
1589
1771
-40
70.4
79.8
80.7
572
628
3512
3913
1593
1775
-39
70.6
79.9
80.8
576
632
3521
3923
1597
1779
-38
70.7
80.1
81.0
579
635
3530
3933
1601
1784
-37
70.9
80.3
81.2
583
639
3539
3943
1605
1788
-36
71.0
80.4
81.3
586
642
3548
3953
1609
1793
-35
71.2
80.6
81.5
590
646
3556
3963
1613
1797
-34
71.3
80.8
81.7
593
649
3565
3972
1617
1802
-33
71.5
81.0
81.8
597
653
3574
3982
1621
1806
-32
71.6
81.1
82.0
601
657
3583
3992
1625
1811
-31
71.8
81.3
82.2
604
660
3592
4002
1629
1815
-30
71.9
81.5
82.4
608
664
3601
4012
1633
1820
-29
72.1
81.6
82.5
611
667
3610
4022
1637
1834
-28
72.2
81.8
82.7
615
671
3619
4032
1641
1829
-27
72.4
82.0
82.9
618
675
3628
4042
1645
1833
-26
72.5
82.1
83.0
622
678
3637
4052
1649
1838
-25
72.7
82.3
83.2
626
682
3645
4062
1654
1842
-24
72.8
82.5
83.4
629
685
3654
4071
1658
1847
-23
73.0
82.6
83.5
633
689
3663
4081
1661
1851
-22
73.1
82.8
83.7
636
692
3671
4090
1665
1855
-21
73.2
82.9
83.9
639
695
3680
4100
1669
1860
-20
73.4
83.1
84.0
643
699
3688
4109
1673
1864
-19
73.5
83.3
84.2
646
702
3696
4118
1677
1868
-18
73.7
83.4
84.4
650
706
3705
4128
1680
1872
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
23
Power Assurance Test
Engine Runup
OAT
PERCENT
N1
PERCENT N2
EGT (°C)
WF PPH
WF -KG/HR
Deg C
Target
Minimum
Maximum
Minimum
Maximum
Minimum
Maximum
Minimum
Maximum
-17
73.8
83.6
84.5
653
709
3713
4137
1664
1877
-16
74.0
83.8
84.7
656
712
3721
4146
1688
1881
-15
74.1
83.9
84.9
660
716
3730
4156
1692
1885
-14
74.3
84.1
85.0
663
719
3739
4165
1696
1889
-13
74.4
84.2
85.2
667
723
3747
4175
1700
1894
-12
74.5
84.4
85.3
670
726
3756
4185
1704
1898
-11
74.7
84.6
85.5
674
730
3764
4194
1707
1902
-10
74.8
84.7
85.7
677
733
3773
4204
1711
1907
-9
75.0
84.9
85.8
680
736
3782
4213
1715
1911
-8
75.1
85.1
86.0
684
740
3790
4223
1719
1918
-7
75.3
85.2
86.2
687
743
3799
4233
1723
1920
-6
75.4
85.4
86.3
691
747
3808
4243
1727
1925
-5
75.5
85.5
86.5
694
750
3817
4253
1731
1929
-4
75.7
85.7
86.6
698
754
3825
4262
1735
1933
-3
75.8
85.9
86.8
701
757
3834
4271
1739
1937
-2
76.0
86.0
87.0
704
760
3842
4281
1743
1942
-1
76.1
86.2
87.1
707
763
3850
4290
1746
1946
0
76.2
86.3
87.3
711
767
3859
4299
1750
1950
1
76.4
86.5
87.4
714
770
3867
4308
1754
1954
2
76.5
86.6
87.6
717
773
3875
4318
1758
1958
3
76.7
86.8
87.8
720
776
3884
4327
1762
1963
4
76.8
87.0
87.9
724
780
3892
4336
1765
1967
5
76.9
87.1
88.1
727
783
3900
4346
1769
1971
6
77.1
87.3
88.2
730
788
3909
4355
1773
1975
7
77.2
87.4
88.4
734
790
3917
4364
1777
1979
8
77.3
87.6
88.6
737
793
3925
4373
1780
1984
9
77.5
87.7
88.7
740
796
3933
4382
1784
1988
10
77.6
87.9
88.9
743
799
3942
4392
1788
1992
11
77.8
88.1
89.0
746
803
3950
4401
1792
1996
12
77.9
88.2
89.2
750
806
3958
4410
1795
2000
13
78.0
88.4
89.3
753
809
3966
4419
1799
2004
14
78.2
88.5
89.5
756
812
3975
4428
1803
2009
15
78.3
88.7
89.6
760
816
3983
4438
1807
2013
16
78.4
88.8
89.8
763
819
3991
4447
1810
2017
17
78.6
89.0
89.9
766
822
4000
4456
1814
2021
18
78.7
89.1
90.1
769
825
4008
4466
1818
2026
19
78.8
89.3
90.3
773
829
4016
4475
1822
2030
20
79.0
89.4
90.4
776
832
4025
4484
1826
2034
Engine Runup
CS130-21.10-05.01-120117
24
Copyright © Bombardier Inc.
For Training Purposes Only
Power Assurance Test
Engine Runup
OAT
PERCENT
N1
PERCENT N2
EGT (°C)
WF - PPH
WF -KG/HR
Deg C
Target
Minimum
Maximum
Minimum
Maximum
Minimum
Maximum
Minimum
Maximum
21
79.1
89.6
90.6
779
835
4034
4494
1830
2039
22
79.2
89.7
90.7
783
839
4043
4504
1834
2043
23
79.4
89.9
90.9
786
842
4052
4514
1838
2048
24
79.5
90.0
91.0
789
845
4061
4524
1842
2052
25
79.6
90.2
91.2
793
849
4069
4534
1846
2057
26
79.8
90.3
91.3
796
852
4078
4544
1850
2061
27
79.9
90.5
91.5
800
856
4087
4554
1854
2066
28
80.0
90.6
91.6
803
859
4096
4564
1858
2070
29
80.2
90.8
91.8
806
863
4105
4574
1862
2075
30
80.3
90.9
91.9
810
866
4114
4584
1866
2079
31
80.4
91.1
92.1
813
869
4123
4594
1870
2084
32
80.6
91.2
92.2
817
873
4132
4604
1874
2088
33
80.7
91.3
92.4
820
876
4141
4614
1878
2093
34
80.8
91.5
92.5
824
880
4150
4624
1883
2098
35
81.0
91.6
92.7
827
883
4160
4635
1887
2102
36
81.1
91.8
92.8
831
887
4169
4645
1891
2107
37
81.2
91.9
93.0
834
890
4178
4655
1895
2111
38
81.4
92.1
93.1
837
894
4187
4665
1899
2116
39
81.5
92.2
93.2
841
897
4196
4678
1903
2121
40
81.6
92.4
93.4
844
900
4206
4685
1908
2125
41
81.8
92.5
93.5
848
904
4215
4696
1912
2130
42
81.9
92.7
93.7
851
907
4224
4707
1916
2135
43
82.0
92.8
93.8
855
911
4233
4717
1920
2140
44
82.1
92.9
94.0
858
914
4242
4727
1924
2144
45
82.3
93.1
94.1
862
918
4251
4736
1928
2148
46
82.4
93.2
94.3
865
921
4259
4745
1932
2152
47
82.5
93.4
94.4
869
925
4268
4756
1936
2157
48
82.7
93.5
94.6
872
928
4277
4766
1940
2162
49
82.8
93.7
94.7
876
932
4286
4775
1944
2166
50
82.9
93.8
94.8
879
935
4294
4784
1948
2170
51
83.0
93.9
95.0
883
939
4302
4794
1951
2174
52
83.2
94.1
95.1
886
942
4311
4803
1955
2179
53
83.3
94.2
95.3
889
945
4319
4812
1959
2183
Compare corrected values of the EGT, N2, and Fuel Flow to the limits in Table 2 at the recorded OAT. If any of
these three parameters are out of limits, the engine may be limited at takeoff power.
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
25
Acceleration/Deceleration Test
Engine Runup
Acceleration/Deceleration Test
(BD500-A-J71-00-00-01AAA-320A-A)
This accel/decel test provides the procedure for checking the correct engine acceleration and deceleration
operation within permitted time limits.
Both engine running, stabilized at MIN IDLE thrust for 5 minutes.
Check that all the engine parameters are with the permitted limits. Refer to Table 1 and Figure 5.
Set the nacelle anti-ice (NAI) to OFF for the test engine. Set NAI to ON for test engine when either of these
weather conditions exist:
• Rain or snow is present
• Fog is present that limits visibility below 1.6 km (1 mile)
When operation of the test engine with anti-icing system ON is necessary, proceed as follows:
NOTE
Engine operation must be stable before proceeding.
•
•
•
•
•
Turn the anti-icing system OFF for the last 30 seconds before acceleration and deceleration tests
Turn the anti-icing system ON after acceleration and deceleration tests
For the engine that does not require a test, slowly move the thrust lever to around 65% N1
Check that the hydraulic EDP load is minimal
Operate non tested engine to 65% N1 to achieve thrust balance and provide sufficient hydraulic pressure to
system users
CAUTION
If engine surges during this test, retard the thrust lever to MIN IDLE within 1 second of
surge. Keep engine at MIN IDLE for 5 minutes if there is no EGT overtemperature. If not,
do an emergency shutdown and dry motor the engine until EGT is less than 250°C.
Engine Runup
CS130-21.10-05.01-120117
26
Copyright © Bombardier Inc.
For Training Purposes Only
Acceleration/Deceleration Test
Engine Runup
Approach Idle
Use table 3 to find N1 approach idle target. (example: 15°C, test site alt.= 150ft, Takeoff N1%=89%)
Record
Test site altitude:
ft
OAT:
°C
Determine the N1 approach idle target using OAT in the Table 3:
Record N1 app. Idle Target:
%
Calculate the adjusted approach idle target N1% (for altitude adjustment above sea level):
Adjusted target N1 speed = (target N1 from Table 3) + (0.6 x target N1 from Table 3) x (altitude/1000)
Adjusted target_______%N1= _________________________%N1 + 0.6 x ____________%N1 x (_________________/1000)
Example: Adjusted target _____%N1= 27% N1 + 0.6 x 27% N1 x (150ft/1000)
Example: Adjusted target 29.43 %N1= 27% N1 + 16.2 N1 x 0.15
Record adjusted approach idle target N1:
%
N1 Accel Time
Calculate the timed accel N1 target at which the timer is stopped when N1 passes through this value.
Calculated timed accel %N1 target:___________________% = 0.97 x (takeoff %N1 - adjusted app. idle %N1) + adjusted app. idle %N1
___________%N1 = 0.97 x (__________-_________________) +________________
Example: ____%N1 = 0.97 x(89% - 27.09) + 27.09
Example: 87.14 %N1 = (0.97 x 61.91) + 27.09
Record calculated timed accel N1:
%
NOTE
Takeoff %N1 is found on the EICAS page above the N1 indicator.
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
27
Acceleration/Deceleration Test
Engine Runup
ACCELERATION TEST
CONTROL
CHECK
SETTING
L(R) BLEED
OFF (test engine)
L(R) GEN
OFF (test engine)
L(R) THRUST LEVER
Slowly move test engine to TAKEOFF power while
moving non test engine to about 65% N1.
Stabilize for 3 minutes
ENG 1
RECORD ACTUAL ENGINE PARAMETERS
ENG 2
N1
%
%
EGT
°C
°C
N2
%
%
FUEL FLOW
kg/hr (pph)
kg/hr (pph)
OIL TEMPERATURE
°C
°C
OIL PRESSURE
PSI
PSI
THRUST LEVERS
Slowly retard levers back to MIN IDLE
Test engine THRUST LEVER
Slowly advance to adjusted Approach Idle N1 target
Let engine stabilize for 15 minutes
Non Test engine
Leave at idle power
If NAI is ON
Switch NAI OFF for 30 seconds
Acceleration test
Adjusted approach idle N1 target;_______%N1
Calculated timed accel. N1 target:.______%N1
Quickly advance thrust lever from adjusted app. idle N1%
to TAKEOFF N1 (in less than 1 second) and start timer
ENG 1
Record actual accel. time through calculated
accel timed N1 target:
ENG 2
Seconds
Seconds
Acceleration time limit for altitude of less than 1524 m (5,000 ft) must be less than 5.5 seconds. For an
altitude above 1524 m (5,000 ft), the acceleration time must be less than this calculation:
Accel Time = 5.5 + (altitude - 5,000)/1,000 x 0.2)
Ex: @ 7,000 ft alt, accel. Time= 5.5 + (7,000-5000) / 1,000 x 0.2) = 5.9 seconds
DECELERATION TEST
L(R) THRUST LEVER
Run test engine at TAKEOFF N1% for 1 minute
Quickly retard thrust lever from TAKEOFF N1% to MIN
IDLE (in less than 1 second) and start timer
ENG 1
Record actual decel. time from TAKEOFF N1%
to adjusted approach N1 target:
(decel. time must be less than 10.5 seconds
Both engines
ENG 2
Seconds
Seconds
Stabilize at MIN IDLE for 5 minutes
NAI ON if necessary
Perform engine shutdown
Engine Runup
CS130-21.10-05.01-120117
28
Copyright © Bombardier Inc.
For Training Purposes Only
Acceleration/Deceleration Test
Engine Runup
Table 3: Approach Idle Target Speed
OAT °C
N1 TARGET
OAT °C
N1 TARGET
OAT °C
N1 TARGET
OAT °C
N1 TARGET
-54
24
-53
24
-52
24
-51
24
-50
24
-49
24
-48
24
-47
24
-46
24
-45
24
-44
24
-43
24
-42
24
-41
24
-40
24
-39
24
-38
24
-37
25
-36
25
-35
25
-34
25
-33
25
-32
25
-31
25
-30
25
-29
25
-28
25
-27
25
-26
25
-26
25
-24
25
-23
25
-22
25
-21
25
-20
25
-19
25
-18
26
-17
26
-16
26
-15
26
-14
26
-13
26
-12
26
-11
26
-10
26
-9
26
-8
28
-7
26
-6
26
-5
26
-4
26
-3
26
-2
26
-1
26
0
26
1
26
2
26
3
27
4
27
5
27
6
27
7
27
8
27
9
27
10
27
11
27
12
27
13
27
14
27
15
27
16
27
17
27
18
27
19
27
20
27
21
27
22
27
23
27
24
28
25
28
26
28
27
28
28
28
29
28
30
28
31
28
32
28
33
28
34
28
35
28
36
28
37
28
38
28
39
28
40
28
41
28
42
28
43
28
44
28
45
28
46
29
47
29
48
29
49
29
50
29
51
29
52
29
53
29
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
29
High-Pressure Ducting System Operation Test
Engine Runup
High-Pressure Ducting System Operation Test
APU AND ENGINE BLEED TEST
CONTROL
SETTING
AIR Control Panel:
All PBAs
FWD/AFT CARGO knobs
FWD and AFT CABIN/COCKPIT knobs
XBLEED
Push APU BLEED PBA
EICAS
No WHITE lights
Set to VENT position
12 o’clock position (CTR)
Set to AUTO
APU BLEED PBA OFF light is ON
APU BLEED OFF message shows.
APU control knob
Set to START and release
APU BLEED PBA
Push PBA
APU BLEED PBA OFF light goes OFF
EICAS
APU BLEED OFF CAS message not shown.
Get access to the AIR synoptic page
L PACK and R PACK
L BLEED and R BLEED manifolds
CKPT, FWD and AFT temperatures
Operate
Bleed air pressurized
Show 24°C
L PACK PBA
Push PBA
L PACK PBA OFF light comes ON.
EICAS
PACK FLOW HI message shows
After 1 minutes, bleed pressure and cabin airflow
increase.
L PACK PBA
(Repeat last 2 steps for R PACK)
Push PBA
L PACK PBA OFF light goes OFF.
Start the engines
AIR synoptic page
L PACK/R PACK/TRIM AIR stop automatically during
engine start and restart 30 seconds after engine start
terminated.
APU BLEED PBA
Push PBA
APU BLEED PBA OFF light comes ON.
EICAS
AIR synoptic page
APU BLEED OFF messages shows
L PACK/R PACK bleed supply change from APU to
engine bleed.
ENGINE BLEED PORT SWITCHING TEST (ONE ENGINE AT A TIME)
CONTROL
SETTING
Engines
Thrust levers at MIN IDLE.
AIR synoptic page
L(R) BLEED press. 39-44 psi
L(R) thrust lever
Slowly advance until L (R) BLEED pressure becomes
stable at 39-44 psi
AIR synoptic page
Confirm that source of L(R) BLEED is the high-pressure
port of L(R) engine.
L(R) thrust lever
Continue to increase L(R) thrust lever until source of
L(R) BLEED changes to the low pressure port.
AIR synoptic page
L(R) BLEED pressure is 38-45 psi
L(R) thrust lever
Slowly retard until the system switches to the
high-pressure port.
Engine Runup
CS130-21.10-05.01-120117
30
Copyright © Bombardier Inc.
For Training Purposes Only
High-Pressure Ducting System Operation Test
Engine Runup
ENGINE BLEED PORT SWITCHING TEST (ONE ENGINE AT A TIME)
AIR synoptic page
Confirm source of L(R) BLEED changes to the
high-pressure port of the L(R) engine and the
L(R) BLEED pressure decreases below 37 psi, then
stabilizes at 38-45 psi
L(R) thrust lever
Retard L(R) thrust lever to MIN IDLE.
AIR synoptic page
Confirm L(R) BLEED pressure is at 39-45 psi
Repeat above steps for opposite engine
SINGLE BLEED OPERATION TEST (BOTH ENGINES RUNNING)
(Perform test on one side at a time)
AIR control panel
EICAS
Push L BLEED PBA
L BLEED PBA OFF light comes ON
L BLEED OFF status message shows
AIR synoptic page
Confirm:
CBV opens
L and R PACK operate
L and R BLEED pressure is 37+/- 2 psi (TBD)
AIR control panel
EICAS
Turn XBLEED knob to MAN CLSD
XBLEED MAN CLSD message shows
AIR synoptic page
Confirm:
CBV closed
R PACK operates
L PACK does not operate
R BLEED pressure is 37+/-2 psi (TBD)
AIR control panel
Push L BLEED PBA
L BLEED PBA OFF light goes OFF
EICAS
L BLEED OFF status message not shown.
AIR synoptic page
L PACK operates
AIR control panel
Turn XBLEED knob to AUTO
EICAS
XBLEED MAN CLSD message not shown.
AIR synoptic page
Confirm:
CBV closed
Land R PACK operate
L and R BLEED Pressure is 30+/-5 psi (TBD)
Repeat previous steps for the opposite side
Perform engine shutdown
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
31
Normal Engine Shutdown
Engine Runup
Normal Engine Shutdown
(BD500-A-J71-00-00-03AAA-130A-A)
CONTROL
SETTING
APU
ON
Bleed Air
Available
L(R) Thrust Levers
Set to MIN idle for 5 minutes
CENTER PEDESTAL
L(R) ENG RUN Switch
Set to OFF
Monitor EICAS:
EGT decreasing
Fuel flow stops
N1 spools down
N2 spools down
NOTE
Ensure APU is running to provide bleed air incase of a tailpipe fire.
Engine Runup
CS130-21.10-05.01-120117
32
Copyright © Bombardier Inc.
For Training Purposes Only
Emergency Procedure Shutdown
Engine Runup
Emergency Procedure Shutdown
(Reference BD500-A-J71-00-00-02AAA-140A-A_001)
Do the following emergency shutdown procedures:
EMERGENCY SHUTDOWN
Thrust levers
Quickly and immediately retard to minimum idle.
L(R) ENG RUN Switch
OFF (this stops the fuel supply to the engine).
If engine has a tail fire with N2 <20% on EICAS
SET ENG RUN switch to OFF (if ON)
Dry motor engine with starter until fire goes out.
*Do not obey the starter time limits.
If the engine was operated within the limits and there was no damage to the engine, do the steps that follow:
• In less than 5 minutes of the emergency shutdown (or when N2 < 20%), dry motor the engine as follows:
DRY MOTORING
CONT IGNITION
PBA out NO LIGHT
ENGINE START Switch
AUTO
ENGINE START Switch
Turn and hold to L(R) ENG CRANK.
Hold rotary switch in the ENG CRANK position as long
as desired to motor the engine until EGT is < 250°C or
for 4 minutes (whichever comes first).
When EGT < 250°C or after 4 minutes
Release ENGINE START Switch.
Verify the following:
N1 and N2
Decrease to 0.
Pneumatic air supply
Disconnect ground air supply or shutdown auxiliary
power unit (APU).
ENGINE SURGE OR STALL BUT RECOVERS AT IDLE (EGT AND OTHER PARAMETERS WITHIN LIMITS)
L(R) Thrust Lever
Quickly retard to MIN IDLE.
Check that there has been no engine parameter limits
exceedance
Run engine at MIN IDLE for 5 minutes and continue
normal engine operation
ENGINE SURGE OR STALL (EGT INCREASING OR OUT OF LIMITS)
L(R) Thrust Lever
Quickly retard to MIN IDLE.
L(R) ENG RUN SWITCH
Set to OFF.
When L(R) Engine N2<20%
Turn and hold in the L(R) ENG CRANK position as long
as desired to motor the engine until EGT <180°C or for
4 minutes (whichever comes first).
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
33
Engine Start After Emergency Shutdown
Engine Runup
Engine Start After Emergency Shutdown
Find and correct the cause of the emergency shutdown before attempting an engine start.
ENGINE WAS OPERATING WITHIN LIMITS WITHOUT DAMAGE AND WAS DRY MOTORED:
Start the engine in less than 2 minutes after last dry
motoring:
CONTROL
SETTING
L(R) Thrust Levers
Set to MIN idle
L(R) ENG RUN Switch
ON
Monitor EICAS:
L(R) START displayed
INCREASING
N2
Around 18% N2:
FUEL FLOW
EGT
Oil Pressure
N1 and N2
At around 55% N2
‘IGN displayed
Indicates 90 kg/hr rising
Rising
Rising
Increasing
Start valve close (AIR SYN)
IGN goes OFF
START goes OFF
If oil pressure is < 70 psi after 30 seconds at MIN IDLE, shutdown the engine.
Run the engine at MIN IDLE for 5 minutes.
After 5 minutes, you can operate the engine above MIN IDLE.
IF THE ENGINE CAN NOT BE DRY MOTORED WITHIN 5 MINUTES OF AN EMERGENCY SHUTDOWN, DO NOT
TRY TO START THE ENGINE AGAIN FOR A MINIMUM OF 90 MINUTES
REFER TO AMP (BD500-A-J71-00-00-00AAA-140A-A) FOR FURTHER TROUBLESHOOTING STEPS
Engine Fire Procedure
CONTROL
SETTING
L(R) ENG FIRE
Thrust levers
L (R) ENG run
L (R) ENG run
L (R) ENG FIRE PBA
L (R) ENG BTL 1
L (R) ENG BTL 2
IDLE
OFF
OFF
PRESS
PRESS
PRESS
Evacuate the aircraft if necessary.
Engine Runup
CS130-21.10-05.01-120117
34
Copyright © Bombardier Inc.
For Training Purposes Only
Normal Procedures
Engine Runup
Normal Procedures
Normal Engine Shutdown
(BD500-A-J71-00-00-03AAA-130A-A)
CONTROL
SETTING
APU
ON
Bleed Air
Available
L(R) Thrust Levers
Set to MIN idle for 5 minutes
CENTER PEDESTAL
L(R) ENG RUN Switch
Set to OFF
Monitor EICAS:
EGT decreasing
Fuel flow stops
N1 spools down
N2 spools down
NOTE
Ensure APU is running to provide bleed air in case of a tailpipe fire.
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
35
Non-Normal Procedures
Engine Runup
Non-Normal Procedures
Engine Start After Emergency Shutdown
Find and correct the cause of the emergency shutdown before attempting an engine start.
ENGINE WAS OPERATING WITHIN LIMITS WITHOUT DAMAGE AND WAS DRY MOTORED:
Start the engine in less than 2 minutes after last dry
motoring:
CONTROL
SETTING
L(R) Thrust Levers
Set to MIN idle
L(R) ENG RUN Switch
ON
Monitor EICAS:
N2
Around 18% N2:
FUEL FLOW
EGT
Oil Pressure
N1 and N2
At around 55% N2
L(R) START displayed
INCREASING
‘IGN displayed
Indicates 90 kg/hr rising
Rising
Rising
Increasing
Start valve close (AIR SYN)
IGN goes OFF
START goes OFF
If oil pressure is < 70 psi after 30 seconds at MIN IDLE, shutdown the engine.
Run the engine at MIN IDLE for 5 minutes.
After 5 minutes, you can operate the engine above MIN IDLE.
IF THE ENGINE CAN NOT BE DRY MOTORED WITHIN 5 MINUTES OF AN EMERGENCY SHUTDOWN, DO NOT
TRY TO START THE ENGINE AGAIN FOR A MINIMUM OF 90 MINUTES
REFER TO AMP (BD500-A-J71-00-00-00AAA-140A-A) FOR FURTHER TROUBLESHOOTING STEPS
Engine Runup
CS130-21.10-05.01-120117
36
Copyright © Bombardier Inc.
For Training Purposes Only
Emergency Procedures
Engine Runup
Emergency Procedures
Emergency Procedure Shutdown
(Reference BD500-A-J71-00-00-02AAA-140A-A_001)
Do the following emergency shutdown procedures:
EMERGENCY SHUTDOWN
Thrust levers
Quickly and immediately retard to minimum idle.
L(R) ENG RUN Switch
OFF (this stops the fuel supply to the engine).
If engine has a tail fire with N2 <20% on EICAS
SET ENG RUN switch to OFF (if ON)
Dry motor engine with starter until fire goes out.
*Do not obey the starter time limits.
If the engine was operated within the limits and there was no damage to the engine, do the steps that follow:
• In less than 5 minutes of the emergency shutdown (or when N2 < 20%), dry motor the engine as follows:
DRY MOTORING
CONT IGNITION
PBA out NO LIGHT
ENGINE START Switch
AUTO
ENGINE START Switch
Turn and hold to L(R) ENG CRANK.
Hold rotary switch in the ENG CRANK position as long
as desired to motor the engine until EGT is < 250°C or
for 4 minutes (whichever comes first).
When EGT < 250°C or after 4 minutes
Release ENGINE START Switch.
Verify the following:
N1 and N2
Decrease to 0.
Pneumatic air supply
Disconnect ground air supply or shutdown auxiliary
power unit (APU).
ENGINE SURGE OR STALL BUT RECOVERS AT IDLE (EGT AND OTHER PARAMETERS WITHIN LIMITS)
L(R) Thrust Lever
Quickly retard to MIN IDLE.
Check that there has been no engine parameter limits
exceedance
Run engine at MIN IDLE for 5 minutes and continue
normal engine operation
ENGINE SURGE OR STALL (EGT INCREASING OR OUT OF LIMITS)
L(R) Thrust Lever
Quickly retard to MIN IDLE.
L(R) ENG RUN SWITCH
Set to OFF.
When L(R) Engine N2<20%
Turn and hold in the L(R) ENG CRANK position as long
as desired to motor the engine until EGT <180°C or for
4 minutes (whichever comes first).
Copyright © Bombardier Inc.
For Training Purposes Only
Engine Runup
CS130-21.10-05.01-120117
37
Emergency Procedures
Engine Runup
APU Fire Procedure
CONTROL
SETTING
APU Fire
OFF
PRESS
PRESS
APU Switch
APU FIRE PBA
APU BTL
Evacuate the aircraft if necessary.
Engine Fire Procedure
CONTROL
SETTING
L(R) ENG FIRE
Thrust levers
L (R) ENG run
L (R) ENG run
L (R) ENG FIRE PBA
L (R) ENG BTL 1
L (R) ENG BTL 2
IDLE
OFF
OFF
PRESS
PRESS
PRESS
Evacuate the aircraft if necessary.
Engine Runup
CS130-21.10-05.01-120117
38
Copyright © Bombardier Inc.
For Training Purposes Only