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CRJ-700
Operation Manual Part 1
50 pgs7.48 Mb13
Operation Manual Part 2
126 pgs17.03 Mb14
Quick Reference Guide
140 pgs9.18 Mb20
FMS Guide
78 pgs6.09 Mb15

Aerosoft CRJ-700 Quick Reference Guide

Aerosoft – Digital Aviation
CRJ-700 CRJ-900
QUICK REFERENCE GUIDE
VOL
2
Rev #
Date
Author
Change
Version
001
21-Sept-2015
MK
Start of project
0.90
002
08-Jan-2016
DJ
Data check
0.91
003
27-Dec-2016
MK
Reformatting / completing
0.92
004
18-Apr-2017
MK
Final checks and corrections
1.00
005
02-May-2017
MK
Final formatting
1.00
On behalf of Authority
Aerosoft – Digital Aviation
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TABLE OF CON TENTS
INTRODUCTION .................................................................................................................................................. 5
PROCEDURES ...................................................................................................................................................... 6
NORMAL TAKE-OFF ........................................................................................................................................ 6
ILS APPROACH ................................................................................................................................................ 7
NON-PRECISION-APPROACH........................................................................................................................... 8
VISUAL APPROACHES ..................................................................................................................................... 9
CIRCLING APPROACH .................................................................................................................................... 10
GO-AROUND ................................................................................................................................................ 11
TOUCH-AND-GO ........................................................................................................................................... 12
CHECKLISTS ...................................................................................................................................................... 13
PRIOR TO START ........................................................................................................................................... 13
SAFETY CHECK .......................................................................................................................................... 13
CABIN INSPECTION ................................................................................................................................... 13
EXTERNAL WALKAROUND ........................................................................................................................ 13
ORIGINATING CHECK ................................................................................................................................ 14
BEFORE START CHECK .............................................................................................................................. 15
CLEARED TO START CHECK ....................................................................................................................... 15
PRIOR TO TAKE-OFF...................................................................................................................................... 16
AFTER START CHECK ................................................................................................................................. 16
TAXI CHECK .............................................................................................................................................. 16
BEFORE TAKE-OFF CHECK ......................................................................................................................... 16
AFTER TAKE-OFF ........................................................................................................................................... 17
CLIMB CHECK ........................................................................................................................................... 17
PRIOR TO LANDING ...................................................................................................................................... 17
DESCENT CHECK ....................................................................................................................................... 17
APPROACH CHECK .................................................................................................................................... 17
BEFORE LANDING CHECK ......................................................................................................................... 17
GO-AROUND PROCEDURE ............................................................................................................................ 18
AFTER LANDING ........................................................................................................................................... 18
AFTER LANDING CHECK ............................................................................................................................ 18
SHUTDOWN CHECK .................................................................................................................................. 18
TERMINATING CHECK ............................................................................................................................... 19
LIMITATIONS .................................................................................................................................................... 20
STRUCTURAL WEIGHT LIMITATIONS ............................................................................................................. 20
OPERATING LIMITATIONS (ALTITUDE AND TERMPERATURE) ........................................................................ 20
OPERATION IN ICING CONDITIONS ............................................................................................................... 21
COWL ANTI-ICE SYSTEM ............................................................................................................................... 21
WING ANTI-ICE SYSTEM................................................................................................................................ 21
RUNWAY SLOPES .......................................................................................................................................... 21
TAILWIND CONDITIONS ................................................................................................................................ 21
MINIMUM FLIGHT CREW .............................................................................................................................. 21
MAXIMUM OCCUPANTS ............................................................................................................................... 21
CARGO ......................................................................................................................................................... 21
POWER PLANT .............................................................................................................................................. 21
ENGINES INDICATIONS ............................................................................................................................. 21
THRUST MANAGEMENT DATA ................................................................................................................. 22
ENGINE WARM-UP ................................................................................................................................... 23
CONTINUOUS ENGINE IGNITION .............................................................................................................. 24
STARTER CRANKING LIMITS ...................................................................................................................... 24
ENGINE RELIGHT ...................................................................................................................................... 25
FUEL ............................................................................................................................................................. 25
FUEL TEMPERATURE ................................................................................................................................ 26
FUEL CROSSFLOW .................................................................................................................................... 26
AUXILLIARY POWER UNIT, APU ..................................................................................................................... 26
APU BLEED AIR ......................................................................................................................................... 27
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APU GENERATOR ..................................................................................................................................... 27
APU INDICATIONS .................................................................................................................................... 27
ENGINE OPERATING PROCEDURE LIMITS DUE TO WIND ............................................................................... 28
OPERATING SPEEDS ...................................................................................................................................... 28
RVSM MAXIMUM CRUISE MACH NUMBER ............................................................................................... 28
DESIGN MANEUVERING SPEED................................................................................................................. 28
FLAPS EXTENDED SPEED ........................................................................................................................... 29
MAXIMUM LANDING GEAR OPERATING SPEED ........................................................................................ 29
TIRE LIMIT SPEED ..................................................................................................................................... 29
MAXIMUM AIRSPEED FOR ADG OPERATION ............................................................................................ 29
TURBULENCE PENETRATION SPEED .......................................................................................................... 29
MINIMUM OPERATING LIMIT SPEED ........................................................................................................ 29
WINDSHIELD WIPER OPERATION ............................................................................................................. 29
MANEUVERING LOADS ............................................................................................................................. 29
SYSTEM LIMITATIONS ................................................................................................................................... 30
AIR-CONDITIONING & PRESSURIZATION .................................................................................................. 30
AUTOMATIC FLIGHT CONTROL SYSTEM.................................................................................................... 30
ELECTRICAL SYSTEMS ............................................................................................................................... 30
FLIGHT CONTROLS – LIFT / DRAG DEVICES ............................................................................................... 31
STALL PROTECTION SYSTEM ..................................................................................................................... 31
THRUST REVERSERS ................................................................................................................................. 31
TAXI LIGHTS ............................................................................................................................................. 31
MINIMUM DESCENT ALTITUDE, MDA ....................................................................................................... 31
TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) ................................................................... 31
INTEGRATED STANDBY INSTRUMENT (ISI) ................................................................................................ 32
PNEUMATIC SYSTEM ................................................................................................................................ 32
FLIGHT DECK DOOR .................................................................................................................................. 32
CRJ 700 ............................................................................................................................................................. 33
LOADSHEET .................................................................................................................................................. 33
PERFORMANCE ............................................................................................................................................ 36
V-SPEED-TABLES....................................................................................................................................... 36
STABILIZER TRIM TAKE-OFF SETTING - FLAPS 8 ......................................................................................... 61
STABILIZER TRIM TAKE-OFF SETTING - FLAPS 20 ....................................................................................... 62
NORMAL TAKE-OFF THRUST SETTINGS (ALL ENGINES OPERATING) %N1 – STATIC TO 65KIAS ................... 63
GO-AROUND THRUST SETTINGS (ALL ENGINES OPERATING) %N1 ............................................................. 65
GO-AROUND THRUST SETTINGS (ONE ENGINE INOPERATIVE) %N1 .......................................................... 67
MAXIMUM CONTINUOUS THRUST (ONE ENGINE INOPERATIVE), %N1 – 170KIAS ..................................... 69
MAXIMUM CONTINUOUS THRUST (ONE ENGINE INOPERATIVE), %N1 – 230 KIAS .................................... 70
V2 GO-AROUND SPEEDS, FLAPS 8 ............................................................................................................. 72
LANDING DATA, LANDING GEAR DOWN, FLAPS 45 ................................................................................... 73
LANDING DATA, LANDING WITH FLAPS OTHER THAN FLAPS 45 ................................................................ 74
FLIGHT PLANNING ........................................................................................................................................ 75
CLIMB (FL-050 TO FL-190) ........................................................................................................................ 75
CLIMB (FL-200 TO FL-290) ........................................................................................................................ 76
CLIMB (FL-300 TO FL-390) ........................................................................................................................ 77
CRUISE (FL-100 TO FL-240) ....................................................................................................................... 78
CRUISE (FL-250 TO FL-390) ....................................................................................................................... 79
DESCENT (FL-050 TO FL-190) .................................................................................................................... 80
DESCENT (FL-200 TO FL-290) .................................................................................................................... 81
DESCENT (FL-300 TO FL-390) .................................................................................................................... 82
CRJ 900 ............................................................................................................................................................. 83
LOADSHEET .................................................................................................................................................. 83
PERFORMANCE ............................................................................................................................................ 87
V-SPEED-TABLES....................................................................................................................................... 87
STABILIZER TRIM TAKE-OFF SETTING – FLAPS 8 ...................................................................................... 118
STABILIZER TRIM TAKE-OFF SETTING – FLAPS 20 .................................................................................... 119
NORMAL TAKE-OFF THRUST SETTINGS (ALL ENGINES OPERATING), %N1 - STATIC TO 65 KIAS ................ 120
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GO-AROUND THRUST SETTINGS %N1 ALL ENGINES OPERATING - 140 KIAS ............................................ 121
GO-AROUND THRUST SETTINGS %N1 (ONE ENGINE INOPERATIVE) – 140 KIAS ....................................... 123
MAXIMUM CONTINUOUS THRUST SETTINGS %N1 (ONE ENGINE INOPERATIVE) – 170 KIAS ................... 125
MAXIMUM CONTINUOUS THRUST SETTINGS %N1 (ONE ENGINE INOPERATIVE) – 230 KIAS ................... 126
V2 Go-Around Speeds, FLAPS 8 ............................................................................................................... 128
LANDING DATA, LANDING GEAR DOWN, FLAPS 45 (IMPERIAL) .............................................................. 129
LANDING DATA, LANDING GEAR DOWN, FLAPS 45 (METRIC) ................................................................. 130
LANDING DATA, LANDING WITH FLAPS OTHER THAN FLAPS 45 (IMPERIAL) ........................................... 131
LANDING DATA, LANDING WITH FLAPS OTHER THAN FLAPS 45 (METRIC) .............................................. 132
FLIGHT PLANNING ...................................................................................................................................... 133
CLIMB (FL-050 TO FL-190) ...................................................................................................................... 133
CLIMB (FL-200 TO FL-290) ...................................................................................................................... 134
CLIMB (FL-300 TO FL-370) ...................................................................................................................... 135
CRUISE (FL-100 TO FL-230) ..................................................................................................................... 136
CRUISE (FL-240 TO FL-370) ..................................................................................................................... 137
DESCENT (FL-050 TO FL-190) ................................................................................................................. 138
DESCENT (FL-200 TO FL-290) ................................................................................................................. 139
DESCENT (FL-300 TO FL-370) ................................................................................................................. 140
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INT R ODUCTION
This Quick Reference Handbook, (QRH), contains checklists and performance tables to be used with Aerosoft / Digital Aviation’s representation of the CRJ. This QRH is basically split up in 4 major parts:
• Procedures: Graphical representations of how you are supposed to fly a certain set of procedures,
• Checklists: The checklists for normal operations,
• Limitations: Describes the limitations for the CRJ700 and 900 in one chapter. In case
different limitations are valid both are provided in the QRH,
• Aircraft-specific information: This chapter will be split up in CRJ 700 and CRJ 900-specific information like performance charts.
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PROCEDURES
NORMAL TAKE-OFF
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ILS APPROACH
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NON- PRECISION -APPROACH
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VISUAL APPROACHES
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CIRCLING APPROACH
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GO-AROUND
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TOUCH-AND-GO
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CHE CKLISTS
PRIOR TO STA RT
SAFE TY CHECK
1 Circuit breakers ....................................CLOSED
2 N/W steering switch ............................OFF
3 Hydraulic pumps ..................................OFF
4 Landing gear lever................................DOWN
5 flight spoiler lever ................................0
6 Slats / flaps lever ..................................SET (TO ACTUAL FLAP POSITION)
7 radar .....................................................OFF
8 ADG manual release ............................STOWED
9 Emergency flap switch .........................NORMAL
10 Battery master switch ..........................ON
Note: To prevent BLEED MISCONFIG caution messages during APU start, ensure that the wing and cowl anti-ice switches are OFF prior to APU START.
11 APU / AC electrics ................................AS REQUIRED / ESTABLISHED
12 IRS ........................................................NAV
13 Emergency Equipment .........................CHECKED
14 Gear and safety pins ............................ON-BOARD
15 Airplane documents.............................CHECKED
16 Hydraulic 3A pump ..............................AS REQUIRED
17 FMS initialization .................................COMPLETE
CABIN INSPECTION
1 Cabin inspection ..................................ACCOMPLISH
EXTERNAL WALK AROUND
1 walk around inspection .......................ACCOMPLISH
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ORIGINATING CHECK
1 Internal and external
prefight checks .....................................COMPLETE
2 Pedals, seat and harness......................ADJUSTED
3 Crew oxygen and masks .......................CHECKED / QUANTITY
only first flight of the day
4 Audio warning panel ............................CHECKED
5 Electrical power panel .........................CHECKED
6 Fire detection / firex monitor test .......COMPLETE
only first flight of the day
7 External lights panel ............................CHECKED
8 Fuel panel ............................................CHECKED
9 Bleed air panel .....................................CHECKED
10 APU panel ............................................AS REQUIRED
11 Start panel............................................CHECKED
12 Hydraulic panel ....................................CHECKED
13 ELT switch .............................................ARM / RESET
14 CABIN PRESS panel ..............................CHECKED
15 Air conditioning panel..........................CHECKED
16 Ice detector tests .................................COMPLETE
only first flight of the day
17 WSHLD switches ..................................LOW
18 EMER LTS switch ..................................ARM
19 Standby compass .................................CHECKED
20 STALL test .............................................COMPLETE
only first flight of the day
21 N/W STRG switch .................................OFF
22 Clocks ...................................................SET
23 EFIS Control panels ..............................CHECKED
24 Instrument panels ................................CHECKED
25 EICAS and Standby instrument ............CHECKED
26 Anti-Skid test........................................COMPLETE
only first flight of the day
27 MLG BAY OVHT TEST ............................COMPLETE
only first flight of the day
28 Upper pedestal ....................................CHECKED
29 Thrust lever quadrant ..........................CHECKED
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30 Avionics ................................................CHECKED
31 Trims ....................................................CHECKED
32 YAW DAMPER .......................................ENGAGE
33 Source Select panel ..............................NORM
34 Lower pedestal.....................................CHECKED
BEFORE START CHECK
1 PASS SIGNS ...........................................ON
2 LDG ELEV ..............................................SET
3 BOOST PUMPS .....................................ON / Checked
Monitor centre tank quantity for not less than 10 minutes’ centre tank fuel
quantity must not increase by more than 68kg (150lb) after both boost pumps are
selected on
4 Altimeters ............................................SET
5 FMS / IRS ..............................................SET
6 Radios and Nav aids .............................SET FOR DEPARTURE
7 take-off briefing ...................................COMPLETE
CLE A RED TO START CHECK
1 APU / AC electrics ................................ON / CHECKED
2 Papers ..................................................ON BOARD
3 Take-off data ........................................SET
4 Doors ....................................................CLOSED / LOCKED
5 Beacon .................................................ON
6 Fuel pumps and quantity .....................ON (QTY)
7 Hydraulic pumps ..................................AUTO / ON
8 Parking brake .......................................AS REQUIRED
Note: Releasing the parking brake and turn off nose wheel steering if push-back is required. Audio and visual communications with the ground crew must be maintained always during push-back.
9 Engines .................................................START
10 Fuel Feed Check Valve test ..................COMPLETE
First flight of the day
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PRIOR TO TAKE -OFF
AFTER START CHECK
Note: Do not accelerate engine until oil pressure is in the normal operating range.
1 GEN 1 and GEN 2 .................................AUTO
2 BLEED valves and packs .......................AUTO / ON
3 Anti-Ice .................................................AS REQUIRED
4 Probes ..................................................ON
5 Electrics ................................................CHECKED
6 Rudder .................................................CHECKED
7 N/W STRG ............................................ARMED
TAX I CHECK
Note: At airports where runway structural repair or debris is known to exist, use thrust reversers with extreme caution to preclude the possibility of foreign object damage (fod) from occurring.
1 Flaps .....................................................___ ° INDICATING
2 Flight controls ......................................CHECKED
3 Trims ....................................................GREEN AND ____°
4 Thrust reversers ...................................ARMED
5 Flight instruments ................................CHECKED
6 FMS ......................................................AUTOTUNE
7 BRAKE TEMP ........................................CHECKED
BEFORE TAKE-OFF CHECK
1 Lights and strobes ................................AS REQUIRED
2 Fuel, XFLOW .........................................MAN AND OFF
3 IGNITION / ANTI-ICE ............................AS REQUIRED
4 Flight attendant ...................................ADVISED
5 Transponder / TCAS .............................ON / AS REQUIRED
6 Radar / terrain display .........................AS REQUIRED
7 CAS .......................................................CHECKED AND CLEARED
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AFTER TAKE-OFF
CLI MB CHECK
1 Fuel, XLFOW .........................................AUTO
2 Bleeds and APU ....................................SET
3 Lights and PASS SIGNS .........................AS REQUIRED
4 Thrust reversers ...................................OFF
5 CAS .......................................................CHECKED AND CLEARED
PRIOR TO LAN DING
DESCENT CHECK
1 LDG ELEV ..............................................SET
2 Fuel ......................................................CHECKED
3 TCAS .....................................................AS REQUIRED
4 Radar ....................................................AS REQUIRED
5 Terrain display ......................................AS REQUIRED
6 CAS .......................................................CHECKED AND CLEARED
7 Landing data ........................................SET
8 Approach briefing ................................COMPLETE
APPROACH CHECK
1 Altimeters ............................................___ . ___ SET
2 APU and Bleeds ....................................SET
3 Lights and PASS SIGNS .........................AS REQUIRED
BEFORE LANDING CHECK
1 Flight attendant ...................................ADVISED
2 PASS SIGNS ...........................................ON
3 Thrust reversers ...................................ARMED
4 LDG GEAR .............................................DN / DOWN
5 Flaps .....................................................___ ° INDICATING
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GO-AROUND PROCEDURE
Caution: A go-around manoeuvre should not be attempted after the thrust reverser have been deployed.
Note: The minimum fuel quantity for go-around is 272kg (600lb) per wing (with the airplane level) and assuming a maximum airplane climb attitude of 10° nose up.
1 Radios and nav aids .............................SET FOR GO AROUND
2 Thrust Levers / TOGA switch ................ADVANCE TO TOGA / PRESS
Advance thrust levers to the TOGA detent, then press TOGA switch
3 Airplane ................................................ROTATE SMOOTHLY TOWARDS THE FLIGHT
DIRECTOR BAR
4 Flaps .....................................................8
5 Pitch attitude ........................................ADJUST TO ACHIEVE AN AIRSPEED OF
V
2GA
+10 OR HIGHER AS FLAPS ARE RETRACTED TO 8° When positive rate of climb is achieved:
6 Landing gear.........................................RETRACT / UP
7 Airspeed ...............................................MAINTAIN V
2GA
+10 OR HIGHER
8 Normal climb out procedures ..............ACCOMPLISH
AFTER LANDING
AFTER LANDING CHECK
1 APU ......................................................AS REQUIRED
2 Transponder / radar .............................STBY / OFF
3 Flaps .....................................................UP
4 Lights and strobes ................................AS REQUIRED
5 Probes ..................................................OFF
SHUTDOWN CHECK
Caution: Inform ground crew of 'hot' brakes condition as soon as possible.
Note: Thrust reversers must be stowed prior to engine shutdown.
1 Chocks and Brakes ...............................AS REQUIRED
2 Electrics ................................................SET
3 Fuel and Check valve test ....................COMPLETE
3 Thrust levers ........................................SHUT OFF
4 Seat Belts .............................................OFF
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5 ANTI ICE ...............................................OFF
6 Fuel pumps ..........................................OFF
7 Hydraulic 3A pump ..............................AS REQUIRED
8 Beacon .................................................OFF
9 N/W STRG switch .................................OFF
TERMINATING CHECK
1 Chocks and Brakes ...............................IN / OFF
2 IRS ........................................................OFF
3 Thrust levers ........................................OFF
4 EMER LTS switch ..................................OFF
5 WSHLD switch ......................................OFF
6 AFT CARGO switch ...............................OFF
7 HYDRALIC pumps .................................OFF
8 EXTERNAL LTS switches ........................OFF
9 APU START / STOP ................................OFF
10 APU PWR FUEL .....................................OFF
11 DC SERVICE switch ...............................OFF
12 BATTERY MASTER switch .....................OFF
13 DOME LIGHT switch .............................OFF
14 Boarding lights .....................................OFF
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LIMITATIONS
The CRJ is certified for day and night operation, VFR, IFR and flight in icing conditions.
STRUCTURAL WEIGHT LIMITATIONS
The simulated aircraft in this package are the CRJ700ER and CRJ900ER.
CRJ700ER
CRJ900ER
Maximum passengers
70
90
Dry Operating Weight
20‘290kg
44‘731lbs
22‘131kg
48‘790lbs
Maximum zero fuel weight (MZFW)
28‘259kg
62‘300lbs
31‘751kg
70‘000lbs
Maximum Payload
8‘190kg
18‘055lbs
9‘907kg
21‘840lbs
Cargo Weight
2‘438kg
5‘375lbs
2‘756kg
6‘075lbs
Maximum Ramp Weight
34‘133kg
75‘250lbs
37‘735kg
82‘750lbs
Maximum take-off weight (MTOW)
34‘019kg
75‘000lbs
37‘421kg
82‘500lbs
Maximum landing weight (MLW)
30‘391kg
67‘000lbs
33‘340kg
73‘500lbs
OPERATING LIMITATIONS (ALTITUDE AN D TEMPERATURE)
• Maximum airport pressure altitude for take-off and landing is 8‘000 feet.
• Maximum operating altitude is 41’000 feet.
• Maximum ambient air temperature approved for take-off and landing is ISA+35°C
• Minimum ambient temperature approved for take-off is -40°C (-40 °F).
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OPERATION IN ICING CONDITIONS
The anti-ice system must be activated when encountering icing conditions. Ice being detected by the ice detector or visible moisture like fog, clouds, any form of precipitation and TAT of 10°C and less require the activation of the anti-ice systems, except the SAT is -40°C (-40°F) or below.
COWL ANTI-ICE SYSTEM
Ground Operations: OAT of 10°C (50°F) or below and visible moisture in any form (fog with visibility of 1,500 meters (one mile) or less, rain, precipitation), or operating on contaminated (snow, rain, slush, …) runways/aprons/taxiways require the COWL anti-ice system to be activated.
Flight Operations: The cowl anti-ice system must be activated in the following two cases; when in icing conditions, or in case ICE accumulation is annunciate by the ice detection system.
WING ANTI-ICE SYSTEM
Ground Operations: OAT of 5°C (41°F) or below and visible moisture in any form (fog with visibility of 1,500 meters (one mile) or less, rain, precipitation), or operating on contaminated (snow, rain, slush, …) runways/aprons/taxiways require the WING anti-ice system to be activated.
Flight Operations: The wing anti-ice system must be ON when ICE is annunciated by the ice detection system, or when in icing conditions and the airspeed is less than 230 KIAS.
Do not hold in icing conditions with the flaps / slats extended.
RUNWAY SLOPES
The maximum runway slopes approved for take-off and landing are: +2% (uphill) -2% (downhill).
TAILWIND CON D ITIONS
The maximum tailwind component approved for take-off and landing is 10kts.
MINIMUM FLIGHT CREW
The minimum flight crew is one Captain and one First Officer.
MAXIMUM OCCUPANTS
The total number of passengers carried shall not exceed: 70 (CRJ-700) 90 (CRJ-900).
CARGO
Flight must be within 60 minutes of a suitable airport, if cargo is carried in either cargo compartment
POWER PLANT
Type: General Electric CF34-8C5B1
ENGINES INDICATIONS
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The engine limit display markings on the EICAS must be adhered to in any case. Depending on the customer and the respective settings displayed on the EICAS might differ and be more conservative from the limitations described here. The indications on the EICAS must be used nevertheless.
RED – indicates maximum and minimum Limitations
AMBER - caution range
GREEN - Normal operating range
CF34-8C5B1
Indication
Red
Amber
Green
N1 % RPM
99,5
-
0 to 99,4
N2 % RPM
99,4
-
0 to 99,3
ITT ˚C
Variable*
-
Variable*
OIL TEMP˚C
164
156 to 163
-40 to 155
OIL PRESS psi
0 to 24
Variable
Variabe
*The respective ITT limit will be calculated automatically and displayed on the EICAS.
THRUST MANAGEMENT DAT A
The crew must verify, that the target N1 values stay within ±1.0% tolerance of the values provided on the thrust setting charts. See the respective sections in the performance chapter of this QRH.
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ENGINE WARM-UP
The engine is supposed to be run in IDLE until oil pressure reaches the normal operating range.
The following 2 minutes after engine start N1 may not exceed 75% unless all operating indications are in normal range already.
Engine operating limits
Limit
Ground
Start
Assisted Air
Start
Windmill
Start
Idle
Max.
Continuous
Normal
Take-off
(TOGA)
APR (Max
Power)
N1 - -
-
20 - 25%
99,50%
99,50%
99,50%
ITT
815°C
815°C
927°C
-
960°C
923°C (2
min)
1‘006°C (2
min)
N2
0-45%
0-45%
55-65%
98,00%
99,40%
99,40%
Oil Temp
-40°C
(minimum)
155°C
163°C (15
min)
163°C (15
min)
Oil Press
182 psi
95 psi (after
10 min)
182 psi
95 psi (after
10 min)
182 psi
95 psi (after
10 min)
25-60 psi
25--95 psi
(oil temp <
60 °C)
45-95 psi
45-95 psi
45-95 psi
Minimum Oil
Level for
Flight
40%
minimum
with
affected
engine not
started
- - - - -
-
[1] Normal take-off power and Maximum power (two engines) is limited to 5 minutes. [2] APR power (one engine) is limited to 10 minutes. [3] ITT must be below 120°C before attempting to ground start engine. [4] Maximum oil pressure is limited to 156 psi when oil temperature transient is less than 60°C. [5] Oil pressures (above IDLE) between 25 psi and 45 psi require oil temperature monitoring. [6] Oil pressure should show positive value during start and may peak beyond 182 psi (max display value). Oil pressures above 182 psi are displayed as amber dashes. Oil pressure may be greater than 95 psi for a maximum of 10 minutes. [7] For further details, refer to the Airplane Operating Manual [8] ITT must be below 90°C before attempting to air start engine.
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CON T INUOUS ENGINE IG NITION
Continuous engine ignition must be activated when encountering either of the following conditions:
• Take-offs and landings on contaminated runways
• Flight through moderate or heavier intensity rain
• Flight through moderate or heavier intensity turbulence
• Flight near thunderstorms.
STARTER CRAN KING LIMIT S
The starter may not be used if indicated N2 rpm exceeds 45%. The engine starters may not be activated longer than certain time limits. The time limits are shown on the following tables.
ENGINE START (GROUND)
START
MAX TIME ON
FOLLOWED BY
1 & 2
90 seconds
10 seconds cool down 3 through 5
90 seconds
5 minutes cool down
ENGINE START OR MOTORING (IN FLIGHT)
START
MAX TIME ON
FOLLOWED BY
1
120 seconds
10 seconds cool down 2 through 5
60 seconds
5 minutes cool down
MOTORING (GROUND)
START
MAX TIME ON
FOLLOWED BY
1
90 seconds
5 minutes cool down 2 through 5
30 seconds
5 minutes cool down
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ENGINE RELIGHT
RELIGHT TYPE
ENVELOPE
CRJ700
CRJ900
Wind milling
Altitude from 21’000 feet to 10’000 feet: Speed 290 KIAS to VMO and 7.2% N2 minimum.
Altitude from 25’000
feet to sea level: Speed 250 KIAS to VMO and 7.2% N2 minimum.
Wind milling
Altitude from 10’000 feet to sea level: Speed 250 KIAS to VMO and 7.2% N2 minimum.
Starter-assisted
Altitude from 21’000 feet to sea level: Speed from V
REF
up to VMO and from 0 to 45% N2.
All-Engine-Out Rapid Relight
Altitude from 10’000 feet to sea level: FADEC rapid relight capability has been demonstrated at 200 KIAS for up to 15-second fuel interruptions
FUE L
The maximum permissible fuel imbalance between main left tank and the main right tank:
• During Take-off: 136 kg (300 lb)
• All other phases of flight: 363 kg (800 lb)
As soon as a tank’s quantity indicator reads zero fuel, the remaining fuel is not useable. The following table shows the maximum useable fuel quantity per tank (based on 6.75 lb per US gal, and 2’046 lb per kg conversion factors):
Pressure Refueling
Gravity Refueling
Left main tain
3‘398 kg (7,492 lb)
3‘306 kg (7,290 lb)
Right main tank
3‘398 kg (7,492 lb)
3‘306 kg (7,290 lb)
Centre tank
2‘091 kg (4,610 lb)
Total
8‘887 kg (19‘594 lb)
6‘612 kg (14‘580 lb)
Take-off with a fuel load more than 227 kg (500 lb) in the centre tank is only permitted under certain conditions:
• each main wing tank is above 1‘996 kg (4‘400 lb), or
• each main wing tank is above 907 kg (2’000 lb), and
• the allowable zero fuel weight is reduced by the weight of the fuel in the centre tank more
than 227 kg (500 lb); and
• the centre of gravity (CG) in this configuration is verified to be within the allowable CG envelope as calculated from the Load sheet.
The minimum fuel quantity for go-around is 272 kg (600 lb) per wing (with the aircraft level) and assuming a maximum aircraft climb attitude of 10 degrees nose up.
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FUE L TEMPERATURE
• Take-off with engine fuel temperature indications below 5°C (41 °F) is prohibited.
• Take-off with bulk fuel temperature indications below the limits stated is prohibited.
• During flight, bulk fuel temperature must remain above the applicable bulk fuel freezing
point.
FUEL
BULK FUEL TAKE-OFF LIMIT MINIMUM TEMPERATURE
BULK FUEL FREEZING POINT ASTM D 1‘655 Jet A
-30°C
-40°C
ASTM D 1‘655 JET A1
-37°C
-47°C
FUE L CROSSFLOW
Powered crossflow and gravity crossflow must be off for take-off.
AUXILLIARY POWER UNIT, A PU
TYPE: Allied Signal RE 220 (RJ) MAXIMUM RPM: 106%
STARTING:
1. Minimum ambient temperature for starting a cold soaked APU on the ground is -40°C
2. Maximum EGT (dependent upon altitude and temperature): 692 °C to 1‘038 °C
3. Maximum amount of start attempts in one hour: 3
A two-minute delay must be observed between cranking attempts to allow for cooling of starter
and starter contactor and for APU drainage.
OPERATING RANGE:
• Maximum EGT on ground: 682°C to 789 °C
• Maximum EGT in flight: 773 °C to 806 °C
• Maximum EGT: 1‘038°C (not to be exceeded under any conditions).
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APU BLEED AIR
APU BLEED AIR LIMITATIONS
System / Condition
Limitation
Bleed air extraction
not permitted above 25’000.
Engine-start during ground operations
No bleed air extraction limitation. Each engine may be started using the APU as a bleed air source.
APU GENERATOR
The maximum permissible load on the APU generator is 40 kVA.
APU INDICATIONS
The APU limit display markings on the EICAS must be used to determine compliance with the maximum limit and precautionary ranges. If EICAS markings show more conservative limitation those specified below, the limit markings on the EICAS should be used.
INDICATION
RED
GREEN
APU EGT °C
807
0 to 806
APU % RPM
107
0 to 106
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ENGINE OPERATING PROCEDURE LIMITS DUE TO WIND
Wind and fan speed limitations as shown in the illustration below must be observed:
Wind Condition
Limitation
NOTE 1
Within 30° on either direction of the airplane nose; no wind speed limit OR >30° in either direction of the airplane nose; <5 knots wind speed.
No limitation – TOGA thrust may be applied before brakes released.
NOTE 2
>30° in either direction of the airplane nose, between 5 and 30 knots wind speed
Apply maximum of 75% N1 before brakes released, then TOGA thrust.
NOTE 3
>30° in either direction of the airplane nose; >30 knots wind speed
Apply maximum of idle / taxi thrust before brakes released, then TOGA thrust.
OPERATING SPE EDS
The maximum operating speed is not to be exceeded during any phase off light (i.e. climb, cruise, descent).
RVSM MAXIMUM CRUISE MACH NUMBER
The maximum cruise MACH number when operating in RVSM airspace: 0.83.
DESIGN MANEUVERING SPEED
Full deflection of rudder and aileron, or manoeuvres that involve angles of attack near the stall, must be performed at speeds below VA.
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Avoid large and alternating control inputs, especially in combination with large changes in pitch, roll,
or yaw large side slip angles) as they may cause structural failure at any speed, including below VA.
FLAPS EXTENDED SPEED
The maximum speeds at which the flaps may be extended are:
• FLAPS 1: 230 KIAS
• FLAPS 8: 230 KIAS
• FLAPS 20: 230 KIAS
• FLAPS 30: 185 KIAS
• FLAPS 45: 170 KIAS
MAXIMUM LAND ING GEAR OPERATING SPEED
• Maximum speed to extend the landing gear is: 220 KIAS.
• Maximum speed to fly with landing gear extended and locked: 220 KIAS
• Maximum speed at which the landing gear needs to be retracted: 200 KIAS
TIRE LIMIT SPEED
The tire limit on the ground is 182 kts (CRJ700) The tire limit on the ground is 195 kts (CRJ900)
MAXIMUM AIRSPEED FOR ADG OPERATION
The maximum speed to operate the Air Driven Generator, ADG VMO / MMO.
TURBULENCE PENETRATION SPEED
The maximum airspeed for turbulence penetration: 280 KIAS or 0.75 Mach, (whichever is higher.)
MINIMUM OPERATING LIMIT SPEED
As soon as the stick shaker is activated a further speed reduction is prohibited.
WIND SHIELD WIPER OPERATION
Maximum windshield wiper operation speed: 250 KIAS. In case the windshield wiper has failed in a non-parked position, the airplane speed must not exceed 250 KIAS. To prevent the wipers from jamming using the INT mode is prohibited.
MANEUVERING LOADS
MANEUVERING LIMIT LOAD FACTORS
Maximum load factor during manoeuvres, turns etc - Flaps up: -1.0G to 2.5G Maximum load factor during manoeuvres, turns etc - Flaps down: 0.0G to 2.0G
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SIDE SLIP MANUEVERS
Avoid unnecessary and large side slips during low speed high altitude cruise.
SYST E M LIMITATIONS
AIR-CONDITIONING & PR E SSURIZATION
• Maximum relief differential pressure 8.7psi
• Maximum negative differential pressure -0.5psi
• Max. pressure differential during taxi, take-off and landing 0.1psi
• CRJ700 Maximum altitude for single pack operation 31’000 feet
• CRJ900 Maximum altitude for single pack operation 25’000 feet
The airplane must be completely depressurized prior to opening any of the airplane doors.
The EMER DEPRESS button may not be used above 15’000ft to prevent possible harm to crew
and/or passenger ‘s ears
AUTOMATIC FLIGHT CONTROL SYSTEM
The following tables shows the minimum heights to which autopilot usage is approved depending on the flight phase and glide path angle respectively.
FLIGHT PHASE
GLIDEPATH ANGLE Airport elevation
MINIMUM USE HEIGHT
≤ 4‘000 feet
> 4‘000 feet
Take-off
- - -
600 feet AGL
Non-precision approach
-
Approved
Approved
400 feet AGL
Precision appoach
≤ 3.5°
Approved
Approved
80 feet AGL
> 3.5° ≤ 4.0°
Approved
Approved
120 feet AGL
ELECTRICAL SYSTEMS
PERMISSIBLE LOADS ON AC SYSTEM
The following table shows the maximum individual AC generator loading:
AC LOAD LIMIT (KVA)
ALTITUDE (FEET)
MAIN GENERATOR (EACH)
APU GENERATOR
0 – 41’000
40
40
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