Appendix 1 – Acceptable ODR Tables

From: Transport Canada

Definitions
(HO) = Handout
(ST) = Slide/tape presentations
(TCBI) = Tutorial computer based instruction
(SU) = Stand-up Instructors
(VT) = Video tapes
(ICBI) = Interactive computer based instruction
(CSS) = Cockpit system simulators
(CPT) = Cockpit procedures trainers
(PTT) = Part task trainers
(FTD 2-5) = Flight training devices (level 2-5)
(FTD 6-7) = Flight training devices (level 6-7)
(SIM A-B) = Simulators (level A or B)
(SIM C-D) = Simulators (level C or D)
(ACFT) = Aircraft
(C*) = Requires use of training devices specified in 
            “TRAINING LVL C” column of ODR table.

Appendix 1 Operator Differences Requirements (ODRs)

DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
106 ft, 8 in. (32.51 m)
Increase of 18 ft, 10 in.  (5.74 m)

Wingspan:
76 ft, 3 in. (23.25 m)
Increase of 6 ft, 9 in. (2.04 m)
Tail span:
28 ft (8.54 m)
Increase of 7 ft, 8 in.  (2.34 m)
Height:
24 ft, 10 in. (7.57 m)
Increase of 4 ft, 2 in.  (1.27 m) 		No No HO       A A
Aircraft General Performance
Max T.O. Weight:
75,000 lb. (34,020 kg)
Increase of 22,000 lb.  (9,979 kg)
Max Landing Weight:
67,000 lb. (30,390 kg)
Increase of 20,000 lb.  (9,072 kg)
Fuel Capacity:
2902 U.S. gal.  (10,977 L)
Increase of 751 gal  (2,835 L) 		No No HO       A A
Aircraft General Wheel Base
Main Wheel Track:
13 ft, 6 in. (4.0 m)
Increase of 3 ft, 2 in.  (0.96 m)
Nose to Main Wheels:
40 ft, 10 in. (12.44 m)
Increase of 4 ft, 6 in.  (1.37 m) 		No No HO       A A
Aircraft General Powerplant
GE CF34-8C1 or
GE CF34-8C5B1
13,790 lb. of thrust, APR
Increase of 4,570 lb. of thrust 		No No HO       A A
Aircraft General Forward cargo bay No Yes
Emerg. 		HO       A A
Aircraft General Increase of 20 passengers in payload capacity No No HO       A A
Aircraft General Addition of second Flight Attendant position No No HO       A A
24 Electrics Revised architecture No Yes
Normals 		  ST, TCBI, SU, VT     A A
27 Flight Controls Three panel slats on each wing Minor Yes
Normals 		  ST, TCBI, SU, VT     A A
49 APU Tail cone mounted No Minor Normals HO       A A
52 Doors Forward cargo bay door No Minor Normals HO       A A
Limitations APU operating limits;
Engine parameters;
Gear extension speed;
These are not all inclusive. 		No Yes
Limits 		  ST, TCBI, SU, VT     B B
DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
21 ECS Recirculated air distribution system with fan control switch No Minor
Normals 		HO HO     A A
21 ECS No dedicated fan for avionics bay cooling No Minor
Normals 		HO HO     A A
21 ECS No dedicated standby fan for EFIS cooling.  Backup cooling is via ECS airflow. No Minor
Normals 		HO HO     A A
21 ECS Selected and actual temp displayed on ECS synoptic page No Minor
Normals 		HO HO     A A
21 ECS Revised architecture.  No dedicated cargo bay fan No No HO HO     A A
21 ECS Revised architecture. One electrically operated outflow valve, two safety valves, one ground valve No No HO HO     A A
24 Electrics CB panels 3 and 4 removed;
40 KVA generator (no load shedding for failed generator);
Generator switches (3) always left in AUTO;
AC utility buses removed;
ACPC controls switching automatically;
4 - 120A TRUs instead of 5 - 100A TRUs;
Bus Ties are automatic (controlled by DCPC). Switchlights removed on electrical power panel;
Service bus powered from DC bus 2;
One DC utility bus;
DC external power plug and DC External switchlight removed;
New ADG bus installed.
AC electric synoptic changes
ADC (no lamp test)
Battery chargers and battery location 		No Minor Normals   ST, TCBI, SU, VT     B B
26 Fire/Ovht Simplified testing procedure. Automatic BITE and MDC interface No Minor
Normals 		HO HO     A A
26 Fire/Ovht No jetpipe overheat detection No No HO HO     A A
26 Fire/Ovht Fire suppression for forward cargo area.  Common Halon system used to supply both compartments. Three cargo smoke detectors. No Minor
Normals 		HO HO     A A
27 Flight Controls No dedicated spoiler on control surface.  Multifunction spoilers act as flight spoiler or spoiler on or ground lift dump. No No   ST, TCBI, SU, VT     A A
27 Flight Controls No flutter dampers on elevators No No HO HO     A A
27 Flight Controls Rudder limiter incorporated, function of speed and flap position controlled by SSCU No No   ST, TCBI, SU, VT     A A
27 Flight Controls The power up BITE test starts only when all three hydraulic systems are fully powered.  A SPLR/STAB IN TEST advisory message is posted on EICAS during this test - All flight control systems are inoperative during the test No Minor
Normals 		HO HO     A A
27 Flight Controls For redundancy, emergency slat/flap switch added to drive slats to 25 degrees and flaps to 20 degrees with a slat/flap selector failure No Yes
Abnormal 		  ST, TCBI, SU, VT     B B
27 Flight Controls Slat/Flap lever has 6 positions No Minor
Normals 		HO HO     A A
28 Fuel No gravity refuel capability on center tank No Yes HO HO     A A
28 Fuel Dedicated cross-flow pump No No HO HO     A A
28 Fuel Bulk fuel temperature sensor in right main tank No No HO HO     A A
28 Fuel Fuel synoptic changes No No HO HO     A A
29 Hydraulics 1B/2B pump is not load shed when respective engine GEN is not operating No Minor
Abnormal 		HO HO     A A
29 Hydraulics Thrust reversers are powered by hydraulics No No HO HO     A A
29 Hydraulics Hydraulic SOV switches added to isolate EDP during low pressure condition without shutting down the engine No Minor
Normals
Abnormal 		  ST, TCBI, SU, VT     B B
30 Ice and Rain No cowl anti-ice blow out plug on engines No Minor
Normals 		HO HO     A A
30 Ice and Rain Revised architecture for cowl anti-icing duct leak detection in pylon area No Minor
New msg. 		HO HO     A A
30 Ice and Rain Simplified cowl and wing anti-ice synoptic page No No HO HO     A A
30 Ice and Rain Air data probes and sensor anti-icing tested before flight with ICE DET switchlight No Minor
Normals 		HO HO     A A
30 Ice and Rain Revised architecture for wing OVHT protection.  No STBY mode for wing anti-ice required. No No HO HO     A A
30 Ice and Rain Windshield wiper has intermittent position. No No HO HO     A A
30 Ice and Rain Variable white arcs on the N2 gauges. Range of arc varies with engine bleed condition. No No   ST, TCBI, SU, VT     B B
30 Ice and Rain Wing anti-ice system tested continuously.  No test switch (automatic function) No Minor
Normals 		HO HO     A A
32 Landing gear Nose doors are mechanical No No HO HO     A A
32 Landing gear Cantilever assemblies on main gear with shimmy dampers No Minor
Normals 		HO HO     A A
32 Landing gear No main gear dust pin covers No No HO HO     A A
32 Landing gear No FLT/NORM switch installed on forward external service panel No Minor
Normals 		HO HO     A A
32 Landing gear No anti-skid test switch. Revised anti-skid test procedure. No Yes Normals   ST, TCBI, SU, VT     B B
32 Landing gear NWS deflection is +/- 80 degrees with tiller and rudder pedal movement will deflect NW +/- 8 degrees No No HO HO     A A
33 Lighting Overhead panel dome lights installed No No HO HO     A A
33 Lighting Single nose landing light No No HO HO     A A
33 Lighting Three exterior lights per side for emergency exit lighting No No HO HO     A A
33 Lighting No EMER LTS OFF light on panel.  EMER LTS OFF caution message only No Minor
Normals
Abnormal 		HO HO     A A
34 Flight Instr. No mach transducer or selector valves in Pitot Static system No Minor
Normals 		HO HO     A A
34 Flight Instr. One electronic integrated standby instrument provides airspeed, altitude, attitude, slip/skid, and localizer/glideslope information No Minor
Normals 		HO HO     A A
35 Oxygen Overboard discharge indicator located on left side of fuselage No No HO HO     A A
36 Pneumatics New flight deck bleed air panel.  Engine bleed air taken from either 6th or 10th stage to supply common manifold.
Bleed air selection is automatic when in AUTO mode.  Provisions for manual switching. 		No Yes Normals/ Abnormal   ST, TCBI, SU, VT     B B
36 Pneumatics Power On automatic bleed air leak detection test No Minor
Normals 		HO HO     A A
49 APU 40 KVA generator
No APU Intake Door 'MID' EICAS indication
Dedicated APU fuel pump
APU Fuel supply, left collector tank
AVAIL light = ready for electrical loading, ECU determines when pneumatic loading is available. No fire horn. Start cycle. 		No No   ST, TCBI, SU, VT     A A
70 Powerplant FADEC controlled No Minor Normals     ICBI, CSS, CPT, FTD 2-5   B B
70 Powerplant N1 and N2 sync control panel No Minor
Normals
Abnormal 		HO HO     A A
70 Powerplant FADEC controlled start cycle for ATS and windmill starts No Minor Normals     ICBI, CSS, CPT, FTD 2-5   B B
70 Powerplant Thrust reversers hydraulically-actuated. No thrust lever retarder control system No No   ST, TCBI, SU, VT     B B
70 Powerplant No emergency stow PBAs No Minor
Normals 		  ST, TCBI, SU, VT     B B
70 Powerplant High power schedule PBA No Yes   ST, TCBI, SU, VT     B B
70 Powerplant FADEC generated thrust limits for:  (automatic with thrust levers in respective detent)
Takeoff (TO)
Flex (FLX)
Climb (CLB)
GoAround (GA)
Max Continuous Thrust (MCT)
Cruise (CRZ) - manually set in the cruise range 		No No   ST, TCBI, SU, VT     B B
70 Powerplant Engine oil test panel removed.  Engine oil level quantities provided on menu page No Minor
Normals 		HO HO     A A
DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
AFCS Initial take off pitch target is optimized to takeoff V speeds entered No No   ST, TCBI, SU, VT     B B
Takeoff Rotation rate is 3-5 degrees per second towards target FD No No   ST, TCBI, SU, VT     A A
Takeoff Throttles placed in "TOGA" detent and thrust is set into N1 caret by FADEC
Throttles placed in "CLB" detent and thrust is set into N1 caret by FADEC 		No No     CSS, PTT, FTD2-5   B B
Takeoff Flap retraction:
Flaps 8 takeoff - Flaps retracted to '1' from '8' at V2 + 12 and to '0' from '1' at VT -15 kts
Flaps 20 takeoff - Flaps retracted to '8' from '20' at V2 + 12 and to '1' from '8' at V2 + 20 and then to '0' from '1' at VT -15 		No Yes Normals     CSS, PTT, FTD2-5   C* B
Approach Approach Attitude Comparison
CRJ200                         CRJ700
Single Engine                Normal        
N/A                                Flapless (Slats 25)
Normal                          Slatless (Flaps 45)
Flapless                         Single Engine 		Yes No   VT     B A
Landing More pronounced flare Yes No   VT     B B
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
87 ft, 10 in.  (26.77 m)
Decrease of 18 ft, 10 in.  (5.74 m)
Wingspan:
69 ft, 6 in.  (21.21 m) 
Decrease of 6 ft, 9 in.  (2.04 m)
Tailspan:
20 ft, 4 in.  (6.2 m) 
Decrease of 7 ft, 8 in.  (2.34 m)
Height:
20 ft, 8 in. (6.3 m) 
Decrease of 4 ft, 2 in.  (1.27 m) 		No No HO HO     A A
Aircraft General Performance
Max T.O. Weight:
53,000 lb. (24,041 kg)
Decrease of 22,000 lb.  (9,979 kg)
Max Landing Weight:
47,000 lb. (21,319 kg)
Decrease of 20,000 lb. 
(9,072 kg)
Fuel Capacity:
2151 U.S. gal.  (8,142 L)
Decrease of 751 gal. (2,835 L) 		No No HO HO     A A
Aircraft General Wheel Base
Main Wheel Track:
10 ft, 4 in.  (3.1 m)
Decrease of 3 ft, 2 in.  (0.96 m)
Nose to Main Wheels:
36 ft, 4 in.  (11.07 m)
Decrease of 4 ft, 6 in.  (1.37 m) 		No No HO HO     A A
Aircraft General Powerplant
GE CF34-3B1
9,220 lb. of thrust, APR
Decrease of 4,570 lb. of thrust 		No No HO HO     A A
Aircraft General No forward cargo bay No Minor HO HO     A A
Aircraft General Decrease of 20 passengers in payload capacity No No HO HO     A A
Aircraft General One Flight Attendant position No No HO HO     A A
24 Electrics Architectural differences No Minor (Ext. DC)   ST, TCBI, SU, VT     A A
27 Flight Controls No slats on wings Minor Yes
Normals 		HO HO     A A
49 APU Located in aft equipment bay
Intake/exhaust/Hazard areas 		No Minor
Normals 		HO HO     A A
52 Doors No forward cargo bay door No Minor
Normals 		HO HO     A A
Limitations APU operating limits;
Engine parameters, Gear extension speed, windshield wipers, single pack ops., crosswind, cargo (fire), cold soak (T/R’s). These are not all inclusive. 		No Yes
Limits 		  ST, TCBI, SU, VT     B B
  DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
21 ECS No recirculation feature No Minor
Normals 		HO HO     A A
21 ECS Dedicated avionics bay cooling system with fan control No Minor Normals   ST, TCBI, SU, VT     B A
21 ECS Cabin actual temperature indications only No Minor
Normals 		HO HO     A A
21 ECS Dedicated cargo bay fan No Minor
Msg. 		HO HO     A A
21 ECS Architectural differences:  two pneumatically controlled outflow/safety valves, overboard and inboard ground valves No No HO HO     A A
24 Electrics CB panels 3 and 4 in Flight Deck;
30 KVA generator (load shedding for failed generator);
Generator switches (3) manually selected from OFF to ON after engine start;
Two AC utility busses, load shed under certain conditions;
No ACPC installed, individual relays accomplish switching;
5 - 100A TRUs instead of 4 - 120A TRUs;
Bus Ties 1 and 2 are automatic.  ESS Tie is manually selected.  Switchlights on electrical power service panel;
Service bus powered from SERV TRU;
Two DC utility busses;
DC external power plug with External DC Switchlight on electrical panel;
ADG feeds directly to AC Essential Bus.
System affected during AC power transfer (loss of AC Bus 2).
Battery charger; battery location. 		No Minor Normals, Abnormal, Emergency   ST, TCBI, SU, VT     B B
26 Fire/Ovht Non-automated testing procedure. No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
26 Fire/Ovht JETPIPE OVHT detection
Emergency Procedure (Recall) 		No Msg.   ST, TCBI, SU, VT     B B
27 Flight Controls Dedicated spoileron control surface and dedicated flight spoiler control surface No No HO HO     A A
27 Flight Controls Flutter dampers on elevators No No HO HO     A A
27 Flight Controls No rudder limiter No No HO HO     A A
27 Flight Controls No power up Bite test or SPLR/STAB IN TEST advisory message No Minor
Normals 		HO HO     A A
27 Flight Controls No emergency flap switch No Yes
Abnorm 		HO HO     A A
27 Flight Controls Flap lever has 5 positions No Minor
Normals 		HO HO     A A
28 Fuel Gravity refuel capability on center tank No Yes HO HO     A A
28 Fuel Shared APU and crossflow fuel pump No No HO HO     A A
28 Fuel Bulk fuel temperature sensor in left main tank No No HO HO     A A
29 Hydraulics 1B/2B pump is load shed when opposite GEN is not operating No Minor
Abnorm 		HO HO     A A
29 Hydraulics No hydraulic SOV switches No Minor
Abnorm 		HO HO     A A
30 Ice and Rain Cowl anti-icing valves pressure regulated with overpressure protection (Anti-ice blow out plug on engines) No Minor
Normals 		HO HO     A A
30 Ice and Rain Revised architecture for cowl anti-icing duct leak detection in pylon area No Minor HO HO     A A
30 Ice and Rain Air data probes and sensor anti-icing not tested No No HO HO     A A
30 Ice and Rain Wing anti-icing two operating temperature modes NORM and STBY are manually selectable No Minor Abnorm   ST, TCBI, SU, VT     B A
30 Ice and Rain Amber arcs on the N2 gauges. Range from
0 -78% 		No No HO HO     A A
30 Ice and Rain Wing anti-ice system test switch No Minor Normals   ST, TCBI, SU, VT     B B
30 Ice and Rain Architectural differences on synoptic page No No HO HO     A A
30 Ice and Rain Cowl and wing anti-ice deactivated during thrust reverser deployment No No HO HO     A A
32 Landing gear Nose doors are powered by hydraulics No Minor Normals     FTD 2-5   B A
32 Landing gear Trailing link assemblies on main gear without shimmy dampers No No HO HO     A A
32 Landing gear Main gear pin dust cover No Minor
Normals 		HO HO     A A
32 Landing gear FLT/NORM switch on forward external service panel No Minor Normals   ST, TCBI, SU, VT     B A
32 Landing gear Anti-skid test switch
Parking brake OFF. 		No Yes Normals   ST, TCBI, SU, VT     B A
32 Landing gear NWS deflection is +/- 70 degrees with tiller and rudder pedal movement will deflect NW +/- 5 degrees No No HO HO     A A
33 Lighting No overhead panel dome lights No No HO HO     A A
33 Lighting Dual nose landing lights No No HO HO     A A
33 Lighting Four exterior lights per side for emergency exit lighting No No HO HO     A A
33 Lighting EMER LTS OFF light on the EMER LTS panel illuminates coincident with the EMER LTS OFF caution message No Minor
Normals 		HO HO     A A
34 Flight Instr Mach transducer and selector valves in pitot static system No Minor
Abnorm 		HO HO     A A
34 Flight Instr Two separate standby instruments provide airspeed, altitude, attitude, slip/skid, and localizer/glideslope information No Minor
Normals 		  ST, TCBI, SU, VT     B B
35 Oxygen Overboard discharge indicator located on right side of fuselage No No HO HO     A A
36 Pneumatics Thrust reversers are powered by 14th stage bleed air No No   ST, TCBI, SU, VT     B B
36 Pneumatics 10th and 14th stage bleed air systems controlled by manual manipulation of bleed air switches with APU interlock protection system No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
36 Pneumatics 10th stage manifold services: air conditioning, engine starting.
14th stage manifold services: anti-ice systems. Single pack ops. 		No Yes Abnorm   ST, TCBI, SU, VT     B B
36 Pneumatics Bleed air leak detection test conducted first flight of the day No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
49 APU 30KVA generator
APU intake door EICAS indications:  CLSD, MID and OPEN
Shared APU and Crossflow fuel pump
Fuel supply, both wing tanks
AVAIL light = ready for pneumatic loading, APU GCU determines when electrical loading is available.
Fire horn; Start cycle. 		No Yes
Normals
Abnorm
&
Emerg 		  ST, TCBI, SU, VT     B A
70 Powerplant Hydro-mechanically and N1 speed governing No No   ST, TCBI, SU, VT     A A
70 Powerplant APR and ENG SPEED control panel No Yes Normals   ST, TCBI, SU, VT     A A
70 Powerplant Thrust lever retarder control system No No   ST, TCBI, SU, VT     B B
70 Powerplant Emergency stow PBAs for thrust reversers No Yes Normals
Emergency 		    FTD 2-5   C B
70 Powerplant Pilot-managed start cycles for ATS and windmill starts No Yes
Normals 		HO HO     A A
70 Powerplant FMS generated thrust limits for:  manually set, no detents
Takeoff (TO)
Flex (FLX)
Climb (CLB)
GoAround (GA)
Max Continuous Thrust (MCT)
Cruise (CRZ) 		No Minor Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
70 Powerplant No high power schedule PBA No Yes HO HO     A A
70 Powerplant Oil level test panel No Minor
Normals 		  ST, TCBI, SU, VT     B A
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
AFCS FD target pitch attitude on takeoff is 15 degrees up and GA or SE takeoff is 10 degrees up No No   ST, TCBI, SU, VT     B A
Takeoff Rotation rate is 3 degrees per second towards target FD No No HO HO     A A
Takeoff Throttles manually placed in thrust caret, set by FMS No No     ICBI, CSS, CPT, PTT, FTD 2-5   B B
Takeoff No Flap 1 position:
No requirement to monitor Vt -15 airspeed for flap retraction from flap 8 to flap1 		No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   B B
Approach Approach Attitude Comparison
CRJ700                           CRJ200
Normal                            Single Engine
Flapless (Slats 25)           N/A
Slatless (Flaps 45)           Normal
Single Engine                  Flapless 		Yes No   VT     B B
Landing Minimal flare required Yes No   VT     B B
DIFFERENCE AIRCRAFT: CL-600-2D24
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
118 ft, 11 in.  (36.24 m)
Increase of 31 ft, 1 in.  (9.47 m) 
Wingspan:
81 ft, 7 in. (24.87m)
Increase of 12 ft, 1 in.  (3.66 m)
Tailspan:
28 ft.  (8.54 m)
Increase of 7 ft, 8 in.  (2.23 m)
Height:
24 ft, 7 in. (7.49 m)
Increase of 3 ft, 11 in.  (1.19 m) 		No No HO HO     A A
Aircraft General Performance
Max T.O. Weight:
84,500 lb. (38,329 kg)
Increase of 31,500 lb.  (14,288 kg)
Max Landing Weight:
75,100 lb. (34,065 kg)
Increase of 28,100 lb.  (12,746 kg)
Fuel Capacity:
2902 U.S. gal.  (10,977 L)
Increase of 751 gal.  (2,835 L) 		No No HO HO     A A
Aircraft General Wheel Base
Main Wheel Track:
13 ft, 6in.  (4.0 m)
Increase of 3 ft, 2 in.   (0.96 m)
Nose to Main Wheels:
48 ft, 4 in. (14.73 m)
Increase of 12 ft.  (3.66 m) 		No No HO HO     A A
Aircraft General Powerplant
GE CF34-8C5
14,510 lb. of thrust, APR
Increase of 5,290 lb. of thrust 		No No HO HO     A A
Aircraft General Forward cargo bay No Yes
Emerg. 		HO HO     A A
Aircraft General Increase of 40 passengers in payload capacity No No HO HO     A A
Aircraft General Addition of second Flight Attendant position No No HO HO     A A
24 Electrics Revised architecture No Yes
Normals 		  ST, TCBI, SU, VT     A A
27 Flight Controls Three panel slats on each wing Minor Yes
Normals 		  ST, TCBI, SU, VT     A A
49 APU Tailcone mounted No Minor Normals HO HO     A A
52 Doors Two additional forward cargo bay doors No Minor Normals HO HO     A A
52 Doors Four overwing emergency exits No No HO HO     A A
Limitations APU operating limits;
Engine parameters;
Gear extension speed.
Taxi turning radius.
These are not all inclusive. 		No Yes
Limits 		  ST, TCBI, SU, VT     B B
Limitations MMO above FL340 is 0.84M
Decrease of 0.01 m 		No Yes
Limits 		HO HO     A A
DIFFERENCE AIRCRAFT: CL-600-2D24
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
  (POI)____________________________
  		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
21 ECS Recirculated air distribution system with fan control switch No Minor
Normals 		HO HO     A A
21 ECS No dedicated fan for avionics bay cooling No Minor
Normals 		HO HO     A A
21 ECS No dedicated standby fan for EFIS cooling.  Backup cooling is via ECS airflow. No Minor
Normals 		HO HO     A A
21 ECS Selected and actual temp displayed on ECS synoptic page No Minor
Normals 		HO HO     A A
21 ECS Revised architecture.  No dedicated cargo bay fan No No HO HO     A A
21 ECS Revised architecture. One electrically operated outflow valve, two safety valves, one ground valve No No HO HO     A A
24 Electrics CB panels 3 and 4 removed;
40 kVA generator (no load shedding for failed generator);
Generator switches (3) always left in AUTO;
AC Utility buses removed;
ACPC controls switching automatically;
4 - 120A TRUs instead of 5 - 100A TRUs;
Bus Ties are automatic (controlled by DCPC). Switchlights removed on electrical power panel;
Service bus powered from DC bus 2;
One DC utility bus;
DC external power plug and DC External switchlight removed;
New ADG bus installed.
AC Electric synoptic changes
ADC (no lamp test)
Battery chargers and battery location 		No Minor Normals   ST, TCBI, SU, VT     B B
26 Fire/Ovht Simplified testing procedure. Automatic BITE and MDC interface No Minor
Normals 		HO HO     A A
26 Fire/Ovht No jetpipe overheat detection No No HO HO     A A
26 Fire/Ovht Fire suppression for forward cargo area.  Common Halon system used to supply both compartments. Three cargo smoke detectors. No Minor
Normals 		HO HO     A A
27 Flight Controls No dedicated spoileron control surface.  Multifunction spoilers act as flight spoiler or spoileron or ground lift dump. No No   ST, TCBI, SU, VT     A A
27 Flight Controls No flutter dampers on elevators No No HO HO     A A
27 Flight Controls Rudder limiter incorporated, function of speed and flap position controlled by SSCU No No   ST, TCBI, SU, VT     A A
27 Flight Controls The power up BITE test starts only when all three hydraulic systems are fully powered.  A SPLR/STAB IN TEST advisory message is posted on EICAS during this test - All flight control systems are inoperative during the test No Minor
Normals 		HO       A A
27 Flight Controls For redundancy, emergency slat/flap switch added to drive slats to 20 degrees and flaps to 20 degrees with a slat/flap selector failure No Yes Abnorm   ST, TCBI, SU, VT     B B
27 Flight Controls Slat/Flap lever has 6 positions No Minor
Normals 		HO       A A
28 Fuel No gravity refuel capability on centre tank No Yes HO       A A
28 Fuel Dedicated cross-flow pump No No HO       A A
28 Fuel Bulk fuel temperature sensor in right main tank No No HO       A A
28 Fuel Fuel synoptic changes No No HO       A A
29 Hydraulics 1B/2B pump is not load shed when respective engine GEN is not operating No Minor
Abnorm 		HO       A A
29 Hydraulics Thrust reverser are powered by hydraulics No No HO       A A
29 Hydraulics Hydraulic SOV switches added to isolate EDP during low pressure condition without shutting down the engine No Minor
Normals
Abnormal 		  ST, TCBI, SU, VT     B B
30 Ice and Rain No cowl anti-ice blow out plug on engines No Minor
Normals 		HO       A A
30 Ice and Rain Revised architecture for cowl anti-icing duct leak detection in pylon area No Minor
New msg. 		HO       A A
30 Ice and Rain Simplified cowl and wing anti-ice synoptic page No No HO       A A
30 Ice and Rain Air data probes and sensor anti-icing tested before flight with ICE DET switchlight No Minor
Normals 		HO       A A
30 Ice and Rain Revised architecture for wing OVHT protection.  No STBY mode for wing anti-ice required. No No HO       A A
30 Ice and Rain Windshield wiper has intermittent position. No No HO       A A
30 Ice and Rain Variable white arcs on the N2 gauges. Range of arc varies with engine bleed condition. No No   ST, TCBI, SU, VT     B B
30 Ice and Rain Wing anti-ice system tested continuously.  No test switch (automatic function) No Minor
Normals 		HO       A A
32 Landing gear Nose doors are mechanical No No HO HO     A A
32 Landing gear Cantilever assemblies on main gear with shimmy dampers No Minor
Normals 		HO HO     A A
32 Landing gear No main gear dust pin covers No No HO HO     A A
32 Landing gear No FLT/NORM switch installed on forward external service panel No Minor
Normals 		HO HO     A A
32 Landing gear No anti-skid test switch. Revised anti-skid test procedure. No Yes Normals   ST, TCBI, SU, VT     B B
32 Landing gear NWS deflection is +/- 80 degrees with tiller and rudder pedal movement will deflect NW +/- 8 degrees No No HO HO     A A
32 Landing gear Increased tire speed limit No No HO HO     A A
33 Lighting Overhead panel dome lights installed No No HO HO     A A
33 Lighting Single nose landing light No No HO HO     A A
33 Lighting Three exterior lights per side for emergency exit lighting No No HO HO     A A
33 Lighting No EMER LTS OFF light on panel.  EMER LTS OFF caution message only No Minor
Normals
Abnormal 		HO HO     A A
34 Flight Instr. No mach transducer or selector valves in Pitot Static system No Minor
Normals 		HO HO     A A
34 Flight Instr. One electronic integrated standby instrument provides airspeed, altitude, attitude, slip/skid, and localizer/glideslope information No Minor
Normals 		HO HO     A A
35 Oxygen Overboard discharge indicator located on left side of fuselage No No HO HO     A A
36 Pneumatics New flight deck bleed air panel.  Engine bleed air taken from 6th or 10th stage to supply common manifold.
Bleed air selection is automatic when in AUTO mode.  Provisions for manual switching. 		No Yes Normals/ Abnorm   ST, TCBI, SU, VT     B B
36 Pneumatics Power On automatic bleed air leak detection test No Minor
Normals 		HO HO     A A
49 APU 40 kVA generator
No APU Intake Door 'MID' EICAS indication
Dedicated APU fuel pump
APU Fuel supply, left collector tank
AVAIL light = ready for electrical loading, ECU determines when pneumatic loading is available. No fire horn. Start cycle. 		No No   ST, TCBI, SU, VT     A B
52 Doors Four over wing emergency exits
Minor changes to Doors synoptic page and EICAS messages 		No Minor Messages HO HO     A A
70 Powerplant FADEC controlled No Minor Normals     ICBI, CSS, CPT, FTD 2-5.   B B
70 Powerplant N1 and N2 sync control panel No Minor
Normals
Abnormal 		HO HO     A A
70 Powerplant FADEC controlled start cycle for ATS and windmill starts No Minor Normals     ICBI, CSS, CPT, FTD 2-5   B B
70 Powerplant Thrust reversers hydraulically actuated. No thrust lever retarder control system No No   ST, TCBI, SU, VT     B B
70 Powerplant No emergency stow PBAs No Minor
Normals 		  ST, TCBI, SU, VT     B B
70 Powerplant High power schedule PBA No Yes   ST, TCBI, SU, VT     B B
70 Powerplant FADEC generated thrust limits for:  (automatic with thrust levers in respective detent)
Takeoff (TO)
Flex (FLX)
Climb (CLB)
Go Around (GA)
Max Continuous Thrust (MCT)
Cruise (CRZ) – manually set in the cruise range 		No No   ST, TCBI, SU, VT     B B
70 Powerplant Engine oil test panel removed.  Engine oil level quantities provided on menu page No Minor
Normals 		HO HO     A A
DIFFERENCE AIRCRAFT: CL-600-2D24
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
AFCS Initial take off pitch target is optimized to takeoff V speeds entered No No   ST, TCBI,
SU, VT 		    B B
Taxi Turning radius increased No No HO HO     A A
Takeoff Rotation rate is 3-5 degrees per second towards target FD No No   ST, TCBI, SU, VT     A A
Takeoff Throttles placed in "TOGA" detent and thrust is set into N1 caret by FADEC
Throttles placed in "CLB" detent and thrust is set into N1 caret by FADEC 		No No     CSS, PTT, FTD2-5   B B
Takeoff Flap retraction:
Flaps 8 takeoff - Flaps retracted to '1' from '8' at V2 + 12 and to '0' from '1' at VT -15 kts
Flaps 20 takeoff - Flaps retracted to '8' from '20' at V2 + 12 and to '1' from '8' at V2 + 20 and then to '0' from '1' at VT -15 		No Yes Normals     CSS, PTT, FTD2-5   C* B
Approach Approach Attitude Comparison
CRJ200               CRJ900                      
Single Engine       Normal
N/A                     Flapless (Slats 20)                                                                
Normal                Slatless (Flaps 45)
Flapless              Single Engine 		Yes No    VT     B A
Landing More pronounced flare Yes No    VT     B B
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2D24
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
87 ft, 10 in. (26.77 m)
Decrease of 31 ft, 1 in.  (9.47 m) 
Wingspan:
69 ft, 6 in. (21.21 m) 
Decrease of 12 ft, 1 in.  (3.66 m)
Tailspan:
20 ft, 4 in (6.20 m) 
Decrease of 7 ft, 8 in.  (2.23 m)
Height:
20 ft, 8 in. (6.30 m) 
Decrease of 3 ft, 11 in.  (1.19 m) 		No No HO HO     A A
Aircraft General Performance
Max T.O. Weight:
53,000 lb.  (24,041 kg)
Decrease of 31,500 lb.  (14,288 kg)
Max Landing Weight:
47,000 lb.  (21,319 kg)
Decrease of 28,100 lb.  (12,746 kg)
Fuel Capacity:
2151 U.S. gal.  (8,142 L)
Decrease of 751 gal. (2,835L) 		No No HO HO     A A
Aircraft General Wheel Base
Main Wheel Track:
10 ft, 4 in.  (3.15 m)
Decrease of 3ft, 2 in.  (0.96 m)
 
Nose to Main Wheels:
36 ft, 4 in.  (11.07 m)
Decrease of 12 ft.  (3.66 m) 		No No HO HO     A A
Aircraft General Powerplant
GE CF34-3B1
9,220 lb. of thrust, APR
Difference of 5,290 lb. of thrust 		No No HO HO     A A
Aircraft General No forward cargo bay No Minor HO HO     A A
Aircraft General Decrease of 40 passengers in payload capacity No No HO HO     A A
Aircraft General One Flight Attendant position No No HO HO     A A
24 Electrics Architectural differences No Minor
(Ext. DC) 		  ST, TCBI, SU, VT     A A
27 Flight Controls No slats on wings Minor Yes
Normals 		HO HO     A A
49 APU Located in aft equipment bay
Intake/exhaust/Hazard Areas 		No Minor
Normals 		HO HO     A A
52 Doors No forward cargo bay door No No HO HO     A A
52 Doors 2 fewer over wing emergency exits No No HO HO     A A
Limitations APU operating limits;
Engine parameters, Gear extension speed, windshield wipers, single pack ops., crosswind, cargo (fire), cold soak (T/R’s).
These are not all inclusive 		No Yes
Limits 		  ST, TCBI, SU, VT     B B
Limitations MMO above FL340 is 0.85M
Increase of 0.01 M 		No Yes
Limits 		HO HO     A A
21 ECS No recirculation feature No Minor
Normals 		HO HO     A A
21 ECS Dedicated avionics bay cooling system with fan control No Minor Normals   ST, TCBI, SU, VT     B A
21 ECS Cabin actual temperature indications only No Minor
Normals 		HO HO     A A
21 ECS Dedicated cargo bay fan No Minor
Msg. 		HO HO     A A
21 ECS Architectural differences:  two pneumatically controlled outflow/safety valves, overboard and inboard ground valves No No HO HO     A A
24 Electrics CB panels 3 and 4 in flight deck;
30 kVA generator (load shedding for failed generator);
Generator switches (3) manually selected from OFF to ON after engine start;
Two AC utility busses, loadshed under certain conditions;
No ACPC installed, individual relays accomplish switching;
5 - 100A TRUs instead of 4 - 120 A TRUs;
Bus Ties 1 and 2 are automatic.  ESS Tie is manually selected.  Switchlights on electrical power service panel;
Service bus powered from SERV TRU;
Two DC utility busses;
DC external power plug with external DC Switchlight on electrical panel;
ADG feeds directly to AC essential bus.
System affected during AC power transfer (loss of AC Bus 2).
Battery and battery charger location. 		No Minor Normals, Abnormal, Emergency   ST, TCBI, SU, VT     B B
26 Fire/Ovht Non-automated testing procedure. No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C D
26 Fire/Ovht JETPIPE OVHT detection
Emergency Procedure (Recall) 		No Msg.   ST, TCBI, SU, VT     B B
27 Flight Controls Dedicated spoileron control surface and dedicated flight spoiler control surface No No HO HO     A A
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2D24
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
27 Flight Controls Flutter dampers on elevators No No HO HO     A A
27 Flight Controls No rudder limiter No No HO HO     A A
27 Flight Controls No power up Bite test or SPLR/STAB IN TEST advisory message No Minor
Normals 		HO HO     A A
27 Flight Controls No emergency flap switch No Yes
Abnormal 		HO HO     A A
27 Flight Controls Flap lever has 5 positions No Minor
Normals 		HO HO     A A
28 Fuel Fuel synoptic changes No No HO HO     A A
28 Fuel Gravity refuel capability on center tank No Yes HO HO     A A
28 Fuel Shared APU and crossflow fuel pump No No HO HO     A A
28 Fuel Bulk fuel temperature sensor in left main tank No No HO HO     A A
29 Hydraulics 1B/2B pump is load shed when opposite GEN is not operating No Minor
Abnormal 		HO HO     A A
29 Hydraulics No hydraulic SOV switches No Minor
Abnormal 		HO HO     A A
30 Ice and Rain Cowl anti-icing valves pressure regulated with overpressure protection (Anti-ice blow out plug on engines) No Minor
Normals 		HO HO     A A
30 Ice and Rain Revised architecture for cowl anti-icing duct leak detection in pylon area No Minor HO HO     A A
30 Ice and Rain Air data probes and sensor anti-icing not tested No No HO HO     A A
30 Ice and Rain Wing anti-icing two operating temperature modes NORM and STBY are manually selectable No Minor Abnormal   ST, TCBI, SU, VT     B A
30 Ice and Rain Amber arcs on the N2 gauges. Range from
0 -78% 		No No HO HO     A A
30 Ice and Rain Wing anti-ice system test switch No Minor Normals   ST, TCBI, SU, VT     B B
30 Ice and Rain Architectural differences on synoptic page No No HO HO     A A
30 Ice and Rain Cowl and wing anti-ice deactivated during thrust reverser deployment No No HO HO     A A
32 Landing gear Nose doors are powered by hydraulics No Minor
Normals 		    FTD
2-5 		  B A
32 Landing gear Trailing link assemblies on main gear without shimmy dampers No No HO HO     A A
32 Landing gear Decreased tire speed limit No No HO HO     A A
32 Landing gear Main gear pin dust cover No Minor
Normals 		HO HO     A A
32 Landing gear FLT/NORM switch on forward external service panel No Minor Normals   ST, TCBI, SU, VT     B A
32 Landing gear Anti-skid test switch
Parking brake OFF. 		No Yes Normals   ST, TCBI, SU, VT     B A
32 Landing gear NWS deflection is +/- 70 degrees with tiller and rudder pedal movement will deflect NW +/- 5 degrees No No HO HO     A A
33 Lighting No overhead panel dome lights No No HO HO     A A
33 Lighting Dual nose landing lights No No HO HO     A A
33 Lighting Four exterior lights per side for emergency exit lighting No No HO HO     A A
33 Lighting EMER LTS OFF light on the EMER LTS panel illuminates coincident with the EMER LTS OFF caution message No Minor
Normals 		HO HO     A A
34 Flight Instr Mach transducer and selector valves in pitot static system No Minor
Abnormal 		HO HO     A A
34 Flight Instr Two separate standby instruments provide airspeed, altitude, attitude, slip/skid, and localizer/glideslope information No Minor
Normals 		  ST, TCBI, SU, VT     B B
35 Oxygen Overboard discharge indicator located on right side of fuselage No No HO HO     A A
36 Pneumatics Thrust reversers are powered by 14th stage bleed air No No   ST, TCBI, SU, VT     B B
36 Pneumatics 10th and 14th stage bleed air systems controlled by manual manipulation of bleed air switches with APU Interlock Protection System No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
36 Pneumatics 10th stage manifold services: air conditioning, engine starting.
14th stage manifold services: anti-ice systems. Single pack ops. 		No Yes Abnormal   ST, TCBI, SU, VT     B B
36 Pneumatics Bleed air leak detection test conducted first flight of the day No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
49 APU 30 kVA generator
APU Intake Door EICAS Indications:  CLSD, MID and OPEN
Shared APU and Crossflow fuel pump
Fuel supply, both wing tanks
AVAIL light = ready for pneumatic loading, APU GCU determines when electrical loading is available 		No Yes
Normals
Abnormal
Emergency 		  ST, TCBI, SU, VT     B A
52 Doors Two over wing emergency exits
Minor changes to Doors synoptic page and EICAS messages 		No Minor Messages HO HO     A A
70 Powerplant Hydro-mechanically and N1 speed governing No No   ST, TCBI, SU, VT     A A
70 Powerplant APR and ENG SPEED control panel No Yes Normals   ST, TCBI, SU, VT     A A
70 Powerplant Thrust Lever retarder control system No No   ST, TCBI, SU, VT     B B
70 Powerplant Emergency stow PBAs for thrust reversers No Yes Normals
Emergency 		    FTD
2-5 		  C B
70 Powerplant Pilot-managed start cycles for ATS and windmill starts No Yes
Normals 		HO HO     A A
70 Powerplant FMS generated thrust limits for:  manually set, no detents
Takeoff (TO)
Flex (FLX)
Climb (CLB)
GoAround (GA)
Max Continuous Thrust (MCT)
Cruise (CRZ) 		No Minor Normals     ICBI, CSS, CPT, PTT,
FTD 2-5 		  C B
70 Powerplant No high power schedule PBA No Yes HO HO     A A
70 Powerplant Oil level test panel No Minor
Normals 		  ST, TCBI, SU, VT     B A
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2D24
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
AFCS FD target pitch attitude on takeoff is 15 degrees up and GA or SE takeoff is 10 degrees up No No   ST, TCBI, SU, VT     B A
Taxi Turning radius decreased No No HO HO     A A
Takeoff Rotation rate is 3 degrees per second towards target FD No No HO HO     A A
Takeoff Throttles manually placed in thrust caret, set by FMS No No     ICBI, CSS, CPT, PTT, FTD 2-5   B B
Takeoff No Flap 1 position:
No requirement to monitor Vt -15 airspeed for flap retraction from flap 8 to flap1 		No Yes
Normals 		    ICBI, CSS, CPT, PTT, FTD 2-5   B B
Approach Approach Attitude Comparison
CRJ900                     CRJ200
Normal                      Single Engine
Flapless (slats 20)     N/A
Slatless (flaps 45)      Normal
Single Engine            Flapless 		Yes No   VT     B B
Landing Minimal flare required Yes No   VT     B B
DIFFERENCE AIRCRAFT: CL-600-2D24
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
118 ft, 11 in. (36.24 m)
Increase of 12 ft, 3 in.  (3.73 m) 

Wingspan:
81 ft, 7 in. (24.87m)
Increase of 5 ft, 4 in.  (1.62 m)
Tailspan:
28 ft. (8.54 m)
No Change
Height:
24 ft, 7 in. (7.49 m)
Decrease of 0 ft, 3 in.  (0.08 m) 		No No HO HO     A A
Aircraft General Performance
Max T.O. Weight:
84,500 lb.  (38,329 kg)
Increase of 9,500 lb. (4,309 kg)
Max Landing Weight:
75,100 lb.  (34,065 kg)
Increase of 8,100 lb. (3,674 kg)
Fuel Capacity:
2902 U.S. gal.  (10,977 L)
No Change 		No No HO HO     A A
Aircraft General Wheel Base
Main Wheel Track:
13 ft, 6 in. (4.0 m)
No Change
Nose to Main Wheels:
48 ft, 4 in. (14.73 m)
Increase of 7 ft, 6 in. (2.29 m) 		No No HO HO     A A
Aircraft General Powerplant
GE CF34-8C5
14,255 lb. of thrust, APR
Increase of 720 lb. of thrust 		No No HO HO     A A
Aircraft General Increase of 20 passengers in payload capacity No No HO HO     A A
52 Doors Two forward cargo bay door (2 total) No Minor Normals HO HO     A A
52 Doors Four over wing emergency exits
Minor EICAS changes 		No No HO HO     A A
Limitations Engine parameters;
Flap 20 VFE
Tire speed
Ground turning radius
These are not all inclusive. 		No Yes
Limits 		HO HO     A A
Limitations MMO above FL340 is 0.84M
Decrease of 0.01 m 		No Yes
Limits 		HO HO     A A
DIFFERENCE AIRCRAFT: CL-600-2D24
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
27 Flight Controls Slat/flap relationship:
When flap lever is selected to 20 degrees, slats are at 20 degrees and flaps are at 20 degrees 		No No HO       A A
27 Flight Controls Emergency Flap when selected, slats move to 20 degrees and flaps are at 20 degrees No No HO       A A
32 Landing gear Increase in tire speed No No HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D24
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Taxi Increase in taxi turning radius No No HO HO     A A
Landing More pronounced flare No No HO HO     A A
DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2D24
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
106 ft, 8 in.  (32.51 m)
Decrease of 12 ft, 3 in.  (3.73 m) 
Wingspan:
76 ft, 3 in.  (23.25 m)
Decrease of 5 ft, 4in.  (1.62 m)
Tailspan:
28 ft, 0 in.  (8.54 m)
No Change
Height:
24 ft, 10 in.  (7.57 m)
Increase of 0 ft, 3 in.  (0.08 m) 		No No HO HO     A A
Aircraft General Performance
Max T.O. Weight:
75,000 lb.  (34,020 kg)
Decrease of 9,500 lb.  (4,309 kg)
Max Landing Weight:
67,000 lb.  (30,390 kg)
Decrease of 8,100 lb.  (3,674kg)
Fuel Capacity:
2902 U.S. gal.  (10,977 L)
No change 		No No HO HO     A A
Aircraft General Wheel Base
Main Wheel Track:
13 ft, 6 in.  (4.0 m)
No Change
Nose to Main Wheels:
40 ft, 10 in.  (12.44 m)
Decrease of 7 ft, 6 in.  (2.29 m) 		No No HO HO     A A
Aircraft General Powerplant
GE CF34-8C1 or
GE CF34-8C5B1
13,790 lb. of thrust, APR
Decrease of 720 lb. of thrust 		No No HO HO     A A
Aircraft General Decrease of 20 passengers in payload capacity No No HO HO     A A
52 Doors One forward cargo bay door No Minor Normals HO HO     A A
52 Doors Two over wing emergency exits
Minor EICAS changes 		No No HO HO     A A
Limitations Engine parameters;
Flap 20 VFE
Tire speed
Ground turning radius
These are not all inclusive. 		No Yes
Limits 		HO HO     A A
Limitations MMO is 0.85M above FL340
Increase of 0.01M 		No Yes
Limits 		HO HO     A A
DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2D24
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
27 Flight Controls Slat/flap relationship:
When flap lever is selected to 20 degrees, slats are at 25 degrees and flaps are at 20 degrees 		No No HO       A A
27 Flight Controls Emergency Flap when selected, slats move to 25 degrees and flaps are at 20 degrees No No HO       A A
32 Landing gear Tire speed reduced No No HO       A A

DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2D24
  APPROVED BY
  (POI)____________________________

COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Taxi Decrease in taxi turning radius No No HO       A A
Landing Less pronounced flare No No HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D24
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
118 ft, 11 in. (36.24 m)
Increase of 12 ft, 3 in.  (3.73 m) 

Wingspan:
81 ft, 7 in. (24.87m)
Increase of 5 ft, 4 in.  (1.62 m)
Tailspan:
28 ft. (8.54 m)
No Change
Height:
24 ft, 7 in. (7.49 m)
Decrease of 0 ft, 3 in.  (0.08 m) 		No No HO       A A
Aircraft General Performance
Max T.O. Weight:
84,500 lb.  (38,329 kg)
Increase of 9,500 lb. (4,309 kg)
Max Landing Weight:
75,100 lb.  (34,065 kg)
Increase of 8,100 lb. (3,674 kg)
Fuel Capacity:
2902 U.S. gal.  (10,977 L)
No Change 		No No HO       A A
Aircraft General Wheel Base
Main Wheel Track:
13 ft, 6 in. (4.0 m)
No Change
Nose to Main Wheels:
48 ft, 4 in. (14.73 m)
Increase of 7 ft, 6 in. (2.29 m) 		No No HO       A A
Aircraft General Powerplant
GE CF34-8C5
14,255 lb. of thrust, APR
Increase of 720 lb. of thrust 		No No HO       A A
Aircraft General Increase of 20 passengers in payload capacity No No HO       A A
52 Doors Two forward cargo bay door (2 total) No Minor Normals HO       A A
52 Doors Four over wing emergency exits
Minor EICAS changes 		No No HO       A A
Limitations Engine parameters;
Flap 20 VFE
Tire speed
Ground turning radius
These are not all inclusive. 		No Yes
Limits 		HO       A A
Limitations MMO above FL340 is 0.84M
Decrease of 0.01 m 		No Yes
Limits 		HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D15
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
(POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
21 ECS Recirculated air distribution system with fan control switch No Minor
Normals 		HO       A A
21 ECS No dedicated fan for avionics bay cooling No Minor
Normals 		HO       A A
21 ECS No dedicated standby fan for EFIS cooling.  Backup cooling is via ECS airflow. No Minor
Normals 		HO       A A
21 ECS Selected and actual temp displayed on ECS synoptic page No Minor
Normals 		HO       A A
21 ECS Revised architecture.  No dedicated cargo bay fan No No HO       A A
21 ECS Revised architecture. One electrically operated outflow valve, two safety valves, one ground valve No No HO       A A
24 Electrics CB panels 3 and 4 removed;
40 kVA generator (no load shedding for failed generator);
Generator switches (3) always left in AUTO;
AC Utility buses removed;
ACPC controls switching automatically;
4 - 120A TRUs instead of 5 - 100A TRUs;
Bus Ties are automatic (controlled by DCPC). Switchlights removed on electrical power panel;
Service bus powered from DC bus 2;
One DC utility bus;
DC external power plug and DC external switchlight removed;
New ADG bus installed;
AC Electric synoptic changes;
ADC (no lamp test);
Battery chargers, battery location. 		No Minor Normals   ST, TCBI, SU, VT     B B
26 Fire/Ovht Simplified testing procedure. Automatic BITE and MDC interface No Minor
Normals 		HO       A A
26 Fire/Ovht No jetpipe overheat detection No No HO       A A
26 Fire/Ovht Fire suppression for forward cargo area.  Common Halon system used to supply both compartments. Three cargo smoke detectors. No Minor
Normals 		HO       A A
27 Flight Controls No dedicated spoileron control surface.  Multifunction spoilers act as flight spoiler or spoileron or ground lift dump. No No   ST, TCBI, SU, VT     A A
27 Flight Controls No flutter dampers on elevators No No HO       A A
27 Flight Controls Rudder limiter incorporated, function of speed and flap position controlled by SSCU No No   ST, TCBI, SU, VT     A A
27 Flight Controls Power up BITE test starts only when all three hydraulic systems are fully powered.  A SPLR/STAB IN TEST advisory message is posted on EICAS during this test - All flt control systems are inoperative during the test No Minor
Normals 		HO       A A
27 Flight Controls For redundancy, emergency slat/flap switch added to drive slats to 20 degrees and flaps to 20 degrees with a slat/flap selector failure No Yes
Abnorm 		  ST, TCBI, SU, VT     B B
27 Flight Controls Slat/flap lever has 6 positions No Minor
Normals 		HO       A A
28 Fuel No gravity refuel capability on center tank No Yes HO       A A
28 Fuel Dedicated cross-flow pump No No HO       A A
28 Fuel Bulk fuel temperature sensor in right main tank No No HO       A A
28 Fuel Fuel synoptic changes No No HO       A A
29 Hydraulics 1B/2B pump is not load shed when respective engine GEN is not operating No Minor
Abnorm 		HO       A A
29 Hydraulics Thrust reversers are powered by hydraulics No No HO       A A
29 Hydraulics Hydraulic SOV switches added to isolate EDP during low pressure condition without shutting down the engine No Minor
Normals
Abnormal 		  ST, TCBI, SU, VT     B B
30 Ice and Rain No cowl anti-ice blowout plug on engines No Minor
Normals 		HO       A A
30 Ice and Rain Revised architecture for cowl anti-icing duct leak detection in pylon area No Minor
New msg. 		HO       A A
30 Ice and Rain Simplified cowl and wing anti-ice synoptic page No No HO       A A
30 Ice and Rain Air data probes and sensor anti-icing tested before flight with ICE DET switchlight No Minor
Normals 		HO       A A
30 Ice and Rain Revised architecture for wing OVHT protection.  No STBY mode for wing anti-ice required. No No HO       A A
30 Ice and Rain Windshield wiper has intermittent position. NO No HO       A A
30 Ice and Rain Variable white arcs on the N2 gauges. Range of arc varies with engine bleed condition. No No   ST, TCBI, SU, VT     B B
30 Ice and Rain Wing anti-ice system tested continuously.  No test switch (automatic function) No Minor
Normals 		HO       A A
32 Landing gear Nose doors are mechanical No No HO       A A
32 Landing gear Cantilever assemblies on main gear with shimmy dampers No Minor
Normals 		HO       A A
32 Landing gear No main gear dust pin covers No No HO       A A
32 Landing gear No FLT/NORM switch installed on forward external service panel No Minor
Normals 		HO       A A
32 Landing gear No anti-skid test switch. Revised anti-skid test procedure. No Yes Normals   ST, TCBI, SU, VT     B B
32 Landing gear NWS deflection is +/- 80 degrees with tiller and rudder pedal movement will deflect NW +/- 8 degrees No No HO       A A
32 Landing gear Increased tire speed limit No No HO       A A
33 Lighting Overhead panel dome lights installed No No HO       A A
33 Lighting Single nose landing light No No HO       A A
33 Lighting Three exterior lights per side for emergency exit lighting No No HO       A A
33 Lighting No EMER LTS OFF light on panel.  EMER LTS OFF caution message only No Minor
Normals
Abnormal 		HO       A A
34 Flight Instr. No mach transducer or selector valves in pitot static system No Minor
Normals 		HO       A A
34 Flight Instr. One electronic integrated standby indicator provides airspeed, altitude, attitude, slip/skid, and localizer/glideslope information No Minor
Normals 		HO       A A
35 Oxygen Overboard discharge indicator located on left side of fuselage No No HO       A A
36 Pneumatics New flight deck bleed air panel.  Engine bleed air taken from either 6th or 10th stage to supply common manifold.
Bleed air selection is automatic when in AUTO mode.  Provisions for manual switching. 		No Yes Normals
/ Abnorm 		  ST, TCBI, SU, VT     B B
36 Pneumatics Power On automatic bleed air leak detection test No Minor
Normals 		HO       A A
49 APU 40 kVA generator;
No APU intake door 'MID' EICAS indication;
Dedicated APU fuel pump;
APU Fuel supply, left collector tank;
AVAIL light = ready for electrical loading, ECU determines when pneumatic loading is available;
No fire horn;
Start cycle. 		No No   ST, TCBI, SU, VT     A B
52 Doors Four overwing emergency exits.
Minor changes to doors synoptic page and EICAS messages 		No Minor Messages HO       A A
70 Powerplant FADEC controlled No Minor Normals     ICBI, CSS, CPT,
FTD 2-5 		  B B
70 Powerplant N1 and N2 sync control panel No Minor
Normals
Abnormal 		HO       A A
70 Powerplant FADEC controlled start cycle for ATS and windmill starts No Minor Normals     ICBI, CSS, CPT,
FTD 2-5 		  B B
70 Powerplant Thrust reversers hydraulically-actuated. No thrust lever retarder control system No No   ST, TCBI, SU, VT     B B
70 Powerplant No emergency stow PBAs No Minor
Normals 		  ST, TCBI, SU, VT     B B
70 Powerplant High power schedule PBA No Yes   ST, TCBI, SU, VT     B B
70 Powerplant FADEC generated thrust limits for:  (automatic with thrust levers in respective detent)
Takeoff (TO)
Flex (FLX)
Climb (CLB)
Go Around (GA)
Max Continuous Thrust (MCT)
Cruise (CRZ) – manually set in the cruise range 		No No   ST, TCBI, SU, VT     B B
70 Powerplant Engine oil test panel removed.  Engine oil level quantities provided on menu page No Minor
Normals 		HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D15
  BASE AIRCRAFT: CL-600-2B19
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
AFCS Initial takeoff pitch target is optimized to takeoff V speeds entered No No   ST, TCBI, SU, VT     B B
Taxi Turning radius increased No No HO       A A
Takeoff Rotation rate is 3-5 degrees per second towards target FD No No   ST, TCBI, SU, VT     A A
Takeoff Throttles placed in "TOGA" detent and thrust is set into N1 caret by FADEC.
Throttles placed in "CLB" detent and thrust is set into N1 caret by FADEC. 		No No     CSS, PTT, FTD
2-5 		  B B
Takeoff Flap retraction:
Flaps 8 takeoff - Flaps retracted to '1' from '8' at V2 + 12 and to '0' from '1' at VT -15 kts.
Flaps 20 takeoff - Flaps retracted to '8' from '20' at V2 + 12 and to '1' from '8' at V2 + 20 and then to '0' from '1' at VT -15 kts. 		No Yes
Normals 		    CSS, PTT, FTD2-5   C* B
Approach Approach Attitude Comparison
CRJ200                CRJ705
Single Engine      Normal        
N/A                       Flapless (Slats 20)
Normal                Slatless (Flaps 45)
Flapless               Single Engine 		Yes No   VT     B A
Landing More pronounced flare Yes No   VT     B B
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2D15
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
87 ft, 10 in. (26.77 m)
Decrease of 31 ft, 1 in.  (9.47 m) 
Wingspan:
69 ft, 6 in. (21.21 m) 
Decrease of 12 ft, 1 in.  (3.66 m)
Tailspan:
20 ft, 4 in (6.20 m) 
Decrease of 7 ft, 8 in.  (2.23 m)
Height:
20 ft, 8 in. (6.30 m) 
Decrease of 3 ft, 11 in.  (1.19 m) 		No No HO       A A
Aircraft General Performance
Max T.O. Weight:
53,000 lb. (24,041 kg)
Decrease of 31,500 lb.  (14,288 kg)
Max Landing Weight:
47,000 lb. (21,319 kg)
Decrease of 28,100 lb.  (12,746kg)
Fuel Capacity:
2151 U.S. gal.  (8,142 L)
Decrease of 751 gal.  (2,835L) 		No No HO       A A
Aircraft General Wheel Base
Main Wheel Track:
10 ft, 4 in.  (3.15 m)
Decrease of 3 ft, 2 in,  (0.96 m)
Nose to Main Wheels:
36 ft, 4 in.  (11.07 m)
Decrease of 12 ft.   (3.66 m) 		No No HO       A A
Aircraft General Powerplant
GE CF34-3B1
9,220 lb. of thrust, APR
Decrease of 5,290 lb. of thrust 		No No HO       A A
Aircraft General No forward cargo bay No Minor HO       A A
Aircraft General Decrease of 25 passengers in payload capacity No No HO       A A
Aircraft General One Flight Attendant position No No HO       A A
24 Electrics Architectural differences No Minor (Ext. DC)   ST, TCBI, SU, VT     A A
27 Flight Controls No slats on wings Minor Yes
Normals 		HO       A A
49 APU Located in aft equipment bay
Intake/exhaust/hazard areas 		No Minor
Normals 		HO       A A
52 Doors Two overwing emergency exits No No HO       A A
Limitations APU operating limits;
Engine parameters; Gear extension speed; Windshield wipers; Single pack ops.; Crosswind; Cargo (fire); Cold soak (T/R’s);
These are not all inclusive 		No Yes
Limits 		  ST, TCBI, SU, VT     B B
Limitations MMO above FL340 is 0.85M
Increase of 0.01 m 		No Yes
Limits 		HO       A A
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2D15
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
21 ECS No recirculation feature No Minor
Normals 		HO       A A
21 ECS Dedicated avionics bay cooling system with fan control No Minor Normals   ST, TCBI, SU, VT     B A
21 ECS Cabin actual temperature indications only No Minor
Normals 		HO       A A
21 ECS Dedicated cargo bay fan No Minor
Msg. 		HO       A A
21 ECS Architectural differences:  two pneumatically controlled outflow/safety valves
overboard and inboard ground valves 		No No HO       A A
24 Electrics CB panels 3 and 4 on flight deck;
30 kVA generator (load shedding for failed generator);
Generator switches (3) manually selected from OFF to ON after engine start;
Two AC Utility busses, loadshed under certain conditions;
No ACPC installed, individual relays accomplish switching;
5 - 100A TRUs instead of 4 - 120A TRUs;
Bus Ties 1 and 2 are automatic.  ESS Tie is manually selected.  Switchlights on electrical power service panel;
Service bus powered from SERV TRU;
Two DC utility busses;
DC external power plug with external DC switchlight on electrical panel;
ADG feeds directly to AC essential bus;
System affected during AC power transfer (loss of AC Bus 2).
Battery chargers, Battery location. 		No Minor Normals, Abnormal, Emergency   ST, TCBI, SU, VT     B B
26 Fire/Ovht Non-automated testing procedure. No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
26 Fire/Ovht JETPIPE OVHT detection;
Emergency Procedure (Recall) 		No Msg.   ST, TCBI, SU, VT     B B
27 Flight Controls Dedicated spoileron control surface and dedicated flight spoiler control surface No No HO       A A
27 Flight Controls Flutter dampers on elevators No No HO       A A
27 Flight Controls No rudder limiter No No HO       A A
27 Flight Controls No power up BITE test or SPLR/STAB IN TEST advisory message No Minor
Normals 		HO       A A
27 Flight Controls No emergency flap switch No Yes
Abnorm 		HO       A A
27 Flight Controls Flap lever has 5 positions No Minor
Normals 		HO       A A
28 Fuel Gravity refuel capability on center tank No Yes HO       A A
28 Fuel Shared APU and crossflow fuel pump No No HO       A A
28 Fuel Bulk fuel temperature sensor in left main tank No No HO       A A
29 Hydraulics 1B/2B pump is load shed when respective GEN is not operating No Minor
Abnormal 		HO       A A
29 Hydraulics No hydraulic SOV switches No Minor
Abnormal 		HO       A A
30 Ice and Rain Cowl anti-icing valves pressure regulated with overpressure protection (Anti-ice blowout plug on engines) No Minor
Normals 		HO       A A
30 Ice and Rain Revised architecture for cowl anti-icing duct leak detection in pylon area No Minor HO       A A
30 Ice and Rain Air data probes and sensor anti-icing not tested No No HO       A A
30 Ice and Rain Wing anti-icing two operating temperature modes NORM and STBY are manually selectable No Minor Abnormal   ST, TCBI, SU, VT     B A
30 Ice and Rain Amber arcs on the N2 gauges. Range from 0 -78% No No HO       A A
30 Ice and Rain Wing anti-ice system test switch No Minor Normals   ST, TCBI, SU, VT     B B
30 Ice and Rain Architectural differences on synoptic page No No HO       A A
30 Ice and Rain Cowl and wing anti-ice deactivated during thrust reverser deployment No No HO       A A
32 Landing gear Nose doors are powered by hydraulics No Minor Normals     FTD 2-5   B A
32 Landing gear Trailing link assemblies on main gear without shimmy dampers No No HO       A A
32 Landing gear Decreased tire speed limit No No HO       A A
32 Landing gear Main gear pin dust cover No Minor
Normals 		HO       A A
32 Landing gear FLT/NORM switch on forward external service panel No Minor Normals   ST, TCBI, SU, VT     B A
32 Landing gear Anti-skid test switch
Parking brake OFF. 		No Yes
Normals 		  ST, TCBI, SU, VT     B A
32 Landing gear NWS deflection is +/- 70 degrees with tiller and rudder pedal movement will deflect NW +/- 5 degrees No No HO       A A
33 Lighting No overhead panel dome lights No No HO       A A
33 Lighting Dual nose landing lights No No HO       A A
33 Lighting Four exterior lights per side for emergency exit lighting No No HO       A A
33 Lighting EMER LTS OFF light on the EMER LTS panel illuminates coincident with the EMER LTS OFF caution message No Minor
Normals 		HO       A A
34 Flight Instr. Mach transducer and selector valves in pitot static system No Minor
Abnormal 		HO       A A
34 Flight Instr. Two separate standby instruments provide airspeed, altitude, attitude, slip/skid, and localizer/glideslope information No Minor
Normals 		  ST, TCBI, SU, VT     B B
35 Oxygen Overboard discharge indicator located on right side of fuselage No No HO       A A
36 Pneumatics Thrust reversers are powered by 14th stage bleed air No No   ST, TCBI, SU, VT     B B
36 Pneumatics 10th and 14th stage bleed air systems controlled by manual manipulation of bleed air switches with APU interlock protection system No Yes
Normals 		    ICBI, CSS, CPT, PTT, FTD 2-5   C B
36 Pneumatics 10th stage manifold services: air conditioning, engine starting.
14th stage manifold services: anti-ice systems.
Single pack ops. 		No Yes
Abnormal 		  ST, TCBI, SU, VT     B B
36 Pneumatics Bleed air leak detection test conducted first flight of the day No Yes
Normals 		    ICBI, CSS, CPT, PTT, FTD 2-5   C B
49 APU 30kVA generator;
APU Intake Door EICAS Indications:  CLSD, MID and OPEN;
Shared APU and Crossflow fuel pump;
Fuel supply, both wing tanks;
AVAIL light = ready for pneumatic loading, APU GCU determines when electrical loading is available.
Fire horn; start cycle. 		No Yes
Normals
Abnormal
Emergency 		  ST, TCBI, SU, VT     B A
52 Doors Two overwing emergency exits
Minor changes to doors synoptic page and EICAS messages 		No Minor Messages HO       A A
70 Powerplant Hydro-mechanical and N1 speed governing No No   ST, TCBI, SU, VT     A A
70 Powerplant APR and ENG SPEED control panel No Yes Normals   ST, TCBI, SU, VT     A A
70 Powerplant Thrust lever retarder control system No No   ST, TCBI, SU, VT     B B
70 Powerplant Emergency stow PBAs for Thrust Reversers No Yes Normals
Emergency 		    FTD 2-5   C B
70 Powerplant Pilot-managed start cycles for ATS and windmill starts No Yes
Normals 		HO       A A
70 Powerplant FMS generated thrust limits for:  manually set, no detents
Takeoff (TO)
Flex (FLX)
Climb (CLB)
GoAround (GA)
Max Continuous Thrust (MCT)
Cruise (CRZ) 		No Minor Normals     ICBI, CSS, CPT, PTT, FTD 2-5   C B
70 Powerplant High power schedule PBA No Yes HO       A A
70 Powerplant Oil level test panel No Minor
Normals 		  ST, TCBI, SU, VT     B A
DIFFERENCE AIRCRAFT: CL-600-2B19
  BASE AIRCRAFT: CL-600-2D15
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
AFCS FD target pitch attitude on takeoff is 15 degrees up and GA or SE takeoff is 10 degrees up No No   ST, TCBI, SU, VT     B A
Taxi Turning radius decreased No No HO       A A
Takeoff Rotation rate is 3 degrees per second towards target FD No No HO       A A
Takeoff Throttles manually placed in thrust caret, set by FMS No No     ICBI, CSS, CPT, PTT, FTD 2-5   B B
Takeoff No Flap 1 position:
no requirement to monitor Vt -15 airspeed for flap retraction from flap 8 to flap1 		No Yes Normals     ICBI, CSS, CPT, PTT, FTD 2-5   B B
Approach Approach Attitude Comparison
CRJ705                             CRJ200
Normal                              Single Engine
Flapless (slats 20)            N/A
Slatless (flaps 45)             Normal
Single Engine                    Flapless 		No No   VT     B B
Landing Minimal flare required No No   ST, TCBI, SU, VT     B B
DIFFERENCE AIRCRAFT: CL-600-2D15
  BASE AIRCRAFT:  CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
118 ft, 11 in.  (36.24 m)
Increase of 12 ft, 3 in.  (3.73 m) 
Wingspan:
81 ft, 7 in.  (24.87 m)
Increase of 5 ft, 4 in.  (1.62 m)
Tailspan:
28 ft.  (8.54 m)
No change
Height:
24 ft, 07 in. (7.49 m)
Decrease of 3 in.  (0.08 m) 		No No HO       A A
Aircraft General Performance
Max T.O. Weight:
84,500 lb.  (38,329 kg)
Increase of 9,500 lb.  (4,309 kg)
Max Landing Weight:
75,100 lb.  (34,065 kg)
Increase of 8,100 lb.  (3,674 kg)
Fuel Capacity:
2902 U.S. gal.  (10,977 L)
No change 		No No HO       A A
Aircraft General Wheel Base
Main Wheel Track:
13 ft, 6 in. (4.0 m)
No change
Nose to Main Wheels:
48 ft, 4 in. (14.73 m)
Increase of 7 ft, 6 in. (2.29 m) 		No No HO       A A
Aircraft General Powerplant
GE CF34-8C5
14,510 lb. of thrust, APR
Increase of 720 lb. of thrust 		No No HO       A A
Aircraft General Increase of 5 passengers in payload capacity No No HO       A A
52 Doors Additional forward cargo bay doors
(2 Total) 		No Minor Normals HO       A A
52 Doors Two additional overwing emergency exits
(4 total)
Minor EICAS changes 		No No HO       A A
Limitations Engine parameters;
Flap 20 VFE;
Tire speed;
Ground turning radius;
These are not all inclusive 		No Yes
Limits 		HO       A A
Limitations MMO above FL340 is 0.84 M
Decrease of 0.01 M 		No Yes
Limits 		HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D15
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Larger winglets No No HO       A A
27 Flight Controls New slat/flap 20 relationship.
When flap 20 selected, slats are 20 degrees 		No No HO       A A
27 Flight
Controls 		When emergency slats/flaps switch selected, slats are driven to 20 degrees and flaps to 20 degrees No No HO       A A
32 Landing gear Tire speed increased No No HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D15
  BASE AIRCRAFT: CL-600-2C10
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Taxi Increased taxi turning radius No No HO       A A
Landing More pronounced flare No No HO       A A
DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT:  CL-600-2D15
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Fuselage
Length:
106 ft, 8 in. (32.51 m)
Decrease of 12 ft, 3 in.  (3.73 m) 
Wingspan:
76 ft, 3 in. (23.24 m)
Decrease of 5 ft, 4 in.  (1.62 m)
Tailspan:
28 ft, 0 in.  (8.54 m)
No change
Height:
24 ft, 10 in.  (7.57 m)
Increase of 3 in.  (0.08 m) 		No No HO       A A
Aircraft General Performance
Max T.O. Weight:
75,000 lb. (34,020 kg)
Decrease of 9,500 lb.  (4,309 kg)
Max Landing Weight:
67,000 lb. (30,390 kg)
Decrease of 8,100 lb.  (3,674 kg)
Fuel Capacity:
2902 U.S. gal.  (10,977 L)
No change 		No No HO       A A
Aircraft General Wheel Base
Main Wheel Track:
13 ft, 2 in. (4.0 m)
No Change
Nose to Main Wheels:
40 ft, 10 in. (12.44 m)
Decrease of 7 ft, 6 in. (2.29 m) 		No No HO       A A
Aircraft General Powerplant
GE CF34-8C1 or
GE CF34-8C5B1
13,790 lb. of thrust, APR
Decrease of 720 lb. of thrust 		No No HO       A A
Aircraft General Decrease of 5 passengers in payload capacity No No HO       A A
52 Doors One forward cargo bay door No Minor Normals HO       A A
52 Doors Two fewer overwing emergency exits
(2 total)
Minor EICAS changes 		No No HO       A A
Limitations Engine parameters;
Flap 20 VFE;
Tire speed;
Ground turning radius.
These are not all inclusive 		No Yes
Limits 		HO       A A
Limitations MMO is 0.85M above FL340
Increase of 0.01M 		No Yes
Limits 		HO       A A
DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2D15
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
SYSTEM REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Smaller winglets No No HO       A A
27 Flight Controls New slat/flap 20 relationship.
When flap 20 selected, slats are 25 degrees 		No No HO       A A
27 Flight Controls When emergency slats/flaps switch is selected, the slats are driven to 25 degrees and flaps to 20 degrees No No HO       A A
32 Landing gear Tire speed reduced No No HO       A A
DIFFERENCE AIRCRAFT: CL-600-2C10
  BASE AIRCRAFT: CL-600-2D15
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
MANEUVER REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Taxi Decreased taxi turning radius No No HO       A A
Landing Less pronounced flare No No HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D24     
  BASE AIRCRAFT: CL-600-2D15
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Increase of 15 passengers in payload capacity No No HO       A A
DIFFERENCE AIRCRAFT: CL-600-2D15
  BASE AIRCRAFT: CL-600-2D24
  APPROVED BY
  (POI)____________________________ 		COMPLIANCE METHOD
TRAINING CHKG/CURR
DESIGN REMARKS FLT
CHAR 		PROC
CHNG 		LVL
A 		LVL
B 		LVL
C 		LVL
D 		CHK CURR
Aircraft General Decrease of 15 passengers in payload capacity No No HO       A A

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