Quick Reference Guide

Aerosoft – Digital Aviation
CRJ-700 CRJ-900
QUICK REFERENCE GUIDE
VOL
2
2-1-25
02-May-2017
ENGINE RELIGHT
RELIGHT TYPE
ENVELOPE
CRJ700
CRJ900
Wind milling
Altitude from 21’000 feet to 10’000 feet:
Speed 290 KIAS to V
MO
and 7.2% N
2
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 V
MO
and 7.2% N
2
minimum.
Starter-assisted
Altitude from 21’000 feet to sea level:
Speed from V
REF
up to V
MO
and from 0 to 45% N
2
.
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
FUEL
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.