# TCDS A21EA: Bombardier Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Bombardier Inc.
- Revision: 52
- Revised: July 29, 2026
- Product: Aircraft, Large Airplane
- Certification basis: Part 25
- Registered aircraft: 598, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/ad/19/ad195be08f73bf96df65ffbfcd54d5d0cb87251d73a0f78c6374ac1c8000c31b
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID100778240620260729183548.0001
- Page: https://openairdocs.org/tcds/A21EA

## Models (5)

As the data sheet lists them.

- CL-600-1A11 (600)
- CL-600-2A12 (601)
- CL-600-2B16 (601-3A Variant)
- CL-600-2B16 (601-3R Variant)
- CL-600-2B16 (604 Variant)

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 
Rev No. 52 43 43 43 43 43 42 43 43 52 52 52 49 47 47 47 47 52 52 52 
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DEPARTMENT OF TRANSPORTATION  FEDERAL AVIATION ADMINISTRATION 
 
A21EA 
Revision No. 52 
Bombardier Inc. 
CL-600-1A11 (600) 
CL-600-2A12 (601) 
CL-600-2B16 (601-3A Variant) 
CL-600-2B16 (601-3R Variant) 
CL-600-2B16 (604 Variant) 
CL-600-2B19 (Regional Jet Series 100 & 440)* 
CL-600-2C10 (Regional Jet Series 700, 701 & 702)*  
CL-600-2C11 (Regional Jet Series 550)* 
CL-600-2D15 (Regional Jet Series 705)* 
CL-600-2D24 (Regional Jet Series 900)* 
CL-600-2E25 (Regional Jet Series 1000)* 
 
* Administratively transferred to TCDS A21EA-1 Revision 
No. IR on November 26, 2019 (See Note 17) 
 
July 29, 2026 
 
TYPE CERTIFICATE DATA SHEET NO. A21EA 
 
This data sheet, which is part of Type Certificate No. A21EA prescribes conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder: Bombardier Inc. 
400 Côte-Vertu Road West 
Dorval, Quebec, Canada  
H4S 1Y9 
 
I - Model CL-600-1A11 (600) (Transport Category), Approved November 7, 1980, by the FAA and August 10, 1980, by the 
Canadian Department of Transport (DOT). 
 
Engines Two AVCO L ycoming ALF-502L or ALF-502L-2 
   
Fuel T ype S pecifications 
  Canada U.S.A. U.K. China Russia/Ukraine 
 Jet A CAN2-3.23 ASTM D1655 - - - 
 Jet A-1 CAN2-3.23 ASTM D1655 DEF STAN 
91-91 
No. 3 Jet TS-1* or RT 
 Grade JP-5 - MIL-DTL-5624 DEF STAN 
91-86 
- - 
 Grade JP-8 - MIL-DTL-83133 DEF STAN 
91-87 
- - 
 Jet B CAN2-3.22 ASTM D6615 D. En g. RD2486 - - 
 JP-4 CAN2-3.22 MIL-DTL-5624 D. Eng. RD2454 - - 
 Jet A and Jet A-1 fuels must contain an approved anti-icing additive unless Canadair Modification Summar y
600-702 and Lycoming Service Bulletin ALF-502-79-0007 are incorporated. 
 *Refer to a ppropriate AFM listed in Approved Publication section when usin g TS-1. 
  
Oil Engine, APU, Generator Adapter: 
MIL-L-7808 (Type I) or MIL-L-23699 (Type II) or other approved oils as identified in the Maintenance 
Manual (refer to Approved publications). 
  
Engine Limits  SL Static Thrust (lb.) Compressor RPM Interturbine  Temperature  
   LP HP    
   %N1 %N2 °C °F Time Limit 
 Max. Takeoff   7500 96.0 98.2 904 1660  5 minutes

Page 2 of 20  A21EA 
 
 
 
 Max. Continuous 7100 96.0 96.4 877 1610 - 
 Starting Maximum    823 1513 10 seconds above 
793°C (1460°F) 
  
  
Oil Temperature   °C °F  
 Maximum Permissible 143 290  
 Transient* 170 338  
 *Permitted during power reduction.  Normal temperature must be achieved within two minutes of achieving 
steady state operation. 
  
Oil Pressure Maxi mum Sea Level 120 p.s.i. 
 Minimum At steady state low 
or high idle 
30 p.s.i. 
    
APU Limits Maximum RPM 110%    
 Maximum EGT: °C °F   
 Starting (10 seconds) 974 1785   
 Running 732 1349   
      
Airspeed Limits (CAS) V mo and Mmo (maximum operating) m.p.h. Knots Mach  
(See NOTE 1) Sea level to 10000 ft.  345 300 -  
 a bove 10000 ft. 368 320 0.79  
 V fe (Flaps extended) 20° 265 230 -  
  30° 226 196 -  
  45° 193 168 -  
 V a (maneuvering)     
 (See AFM for variation of V a with altitude and aircraft weight). 
 V 1o (Landing Gear Operation) 225 196 -  
 V 1e (Landing Gear Extended) 288 250 -  
    
C.G. Range  Forward Limit Aft Limit 
(See NOTE 1) Weight, l b. % MAC (Sta.) % MAC (Sta.) 
 24000 to 31300 16% (+502.848) - - - 
 36500 18% (+504.701) 28% (+513.965) 
 25800 - - - 33% (+518.598) 
 24000 - - - 33% (+518.598) 
 Straight line variation between points given. 
  
Datum Fuselage station 0, located 375 inches forward of weighing datum jig point 
  
Mean Aerodynamic Chord 
(MAC) 
92.644 in. (Leading edge of MAC from datum at +488.025 in.) 
   
Leveling Means Target plate and plumb bob bracket within rear fuselage, at fuselage station 718. 
  
Maximum Weights  l b. * 
(See NOTE 1) Ram p 36500 
 Takeoff 36000 
 Landin g 30500 
 Zero Fuel 25800 
 Mini mum flight weight 24000 
 *Certain ai rcraft are eligible for operation at an increased weight. See AFM as in approved publications. 
  
Minimum Crew Two (Pilot an d Co-pilot) 
  
Maximum Occupants 
(See NOTE 1) 
Twenty-one (includes crew)

Page 3 of 20  A21EA 
 
 
 
Fuel Capacity  U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in. 
 2 main tanks (each) 732.5 611.3 2259.1 4981 (+506.5) 
 1 cente r tank 751 625.8 2316.1 5107 (+457.5) 
 Total 2216 1848.4 6834.3 15069 - - - 
       
 Usa ble      
 2 main tanks (each) 725 605 2236 4930 (+506.5) 
 1 cente r tank 750 625 2313 5100 (+457.5) 
 Total 2200 1835 6785 14960 - - - 
 See NOTE 1(b) for system fuel. 
       
Oil Capacity  U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in. 
 2-engines (each) 3.69 3.07 12.88 28.4 (+ 623) 
 Total 7.38 6.14 25.76 56.8 (+623) 
       
 Usa ble      
 2-engines (each) 1.94 1.61 6.76 14.9 (+ 623) 
 Total 3.87 3.22 13.52 29.8 (+623) 
 See NOTE 1(c) fo r system oil. 
       
 APU      
 Usa ble .408 .340 1.43 3.144 (+675) 
 Total .714 .594 2.49 5.5 (+675) 
       
 Unusa ble .306 .254 1.06 2.356 (+675) 
       
Maximum Operating  Ta keoff and landing: 5000 ft.  
Altitude (See NOTE 1) En route: 40000 ft.  
  41000 ft. with Canadair Limited Modification Summaries 600-1923 
and 600-8330 incorporated 
    
Control Surface  R udder 20° (+1.0°, -0.5°) Left 20° (+1.0°, -0.5°) Right 
Movements Elevato r 23.6° (+ or - 1.0°) Up 18.4° (+ or - 1.0°) Down 
 Horizontal Sta bilizer 0° (+0.5° or -0.25° )LE Up -9° (+ o r - 0.5°) LE Down 
 Aile ron 20.8° (+ or - 1.0°) Up 21.3° (+ or - 1.0°) Down 
 Fla p  – Inboard  0° - 45° (+ o r - 1.0°) Down 
  – Outboard  0° - 46.7° (+ or - 1.0°) Down 
 Flight S poiler 0° - 40°(+3°, -0°)Up  
    
Serial Numbers Eligible 1002, 1004 to 1085   
    
Service Information Service Bulletins, structural repair manuals, and aircraft flight manuals which contain a statement that th e 
document is Transport Canada approved or Transport Canada approved through the Manufacturers Design 
Approval Representative are accepted by the FAA and are considered FAA approved. These approvals 
pertain to the type design only. 
 
II - Model CL-600-2A12 (601) (Transport Category), Approved March 11, 1983, by the FAA and February 25, 1983, by the 
Canadian Department of Transport (DOT). 
 
Engines Two Gene ral Electric CF-34-1A or * 
   
Fuel Type Specifications 
  Canada U.S.A. U.K. China Russia/Ukraine 
 Jet A CAN2-3.23 ASTM D1655 - - - 
 Jet A-1 CAN2-3.23 ASTM D1655 DEF STAN  
91-91 
No. 3 Jet TS-1* or RT 
 Grade JP-5 - MIL-DTL-5624 DEF STAN  
91-86 
- - 
 Grade JP-8 - MIL-DTL-83133 DEF STAN  
91-87 
- - 
 Jet B CAN2-3.22 ASTM D6615 D. En g. RD2486 - -

Page 4 of 20  A21EA 
 
 
 
 JP-4 CAN2-3.22 MIL-DTL-5624 D. En g. RD2454 - - 
 *Refer to appropriate AFM listed in Appr oved Publication section when using TS-1. 
  
Oil Engine, APU, Generator Adapter: 
MIL-L-7808 (Type I) or MIL-L-23699 (Type II) or other approved oils as identified in the 
Maintenance Manual (refer to Approved Publications). 
  
Engine Limits  SL Static Thrust (lb.) Compressor RPM Interturbine  Temperature**  
   LP HP    
   %N1 %N2 °C °F Time Limit 
 Max. takeoff  9140 98.6 99.4 857 1575 5 minutes 
 Normal takeoff 8650 96.2 98.3 842 1548 5 minutes 
 Max. continuous 8920 98.6 99.2 838 1540  
 Idle range   62.9-64.0    
 Min. Idle in icin g conditions   64.0    
 T ransient:       
 Max. takeoff    886 1627 2 minutes 
 Normal takeoff    864 1587 2 minutes 
 Start/ relight    930 1706 16 seconds 
     889 1632 50 seconds 
        
 * One - General Electric CF-34-3A and one CF-34-3A2 or 
One - General Electric CF-34-1A and one CF-34-3A or 
One - General Electric CF-34-1A and one CF-34-3A2 or 
Two - General Electric CF-34-3A or 
Two - General Electric CF-34-3A2 
Aircraft with two CF34-3A or CF34-3A2 engines inst alled, improved performance is not available until 
Canadair Service Bulletin 601-0238 - Modification - Engines - Use of 3A  engines at 3A power settings, 
is incorporated. 
 **See AFM as liste d in Approved Publications for CF-34-3A and CF-34-3A2 engines ITT limits. 
  
 NOTE 
 1. Above 40000 feet, en gine anti-ice bleed or air conditioning unit must be selected ON for each engine. 
 2. Engine Limits with APR Operating are only applicable  to Outside Air Temperatures of - 4°F (- 20°C) and above. 
  
Oil Temperature   °C °F  
 Maxi mum Permissible (15 minutes Maximum) +163 325  
 Maxi mum for Single Engine Climb (60 minutes maximum) +155 311  
 Maxi mum Continuous +150 302  
 Mini mum for Starting -40 -40  
  
Oil Pressure Maxi mum Transient Cold Start 100 psi  (Six minutes maximum) 
 Maxi mum Continuous 95 psi  
 Minimum at Steady State Idle 25 psi  
 Minimum at Takeoff (power): 40 psi  
    
APU Limits Maximum RPM 110%    
 Maximum EGT: °C °F   
 Starting (10 seconds) 974 1785   
 Running 732 1350   
      
Airspeed Limits (CAS) V mo and Mmo (maximum operating) m.p.h. Knots Mach  
 Sea level to 10000 ft.  345 300 -  
 10000 ft. to 21420 ft.  420 365 -  
 21420 ft. to 25740 ft. - - 0.80  
 25740 ft. to 28640 ft. 385 335 -  
 a bove 28640 ft. - - 0.85  
 V fe (Flaps extended) 20° 265 230 -  
  30° 226 196 -  
  45° 215 187 -

Page 5 of 20  A21EA 
 
 
 
 V a (maneuvering)     
 (See AFM for variation of V a with altitude and aircraft weight). 
 V 1o (Landing Gear Operation) 226 196 -  
 V 1e (Landing Gear Extended) 288 250 -  
C.G. Range  Forward Limit Aft Limit 
(See NOTE 1) Weight, l b. % MAC (Sta.) % MAC (Sta.) 
 25000 to 42250 16% (+502.848) - - - 
 42250 - - - 30% (+515.818) 
 31000 - - - 35% (+520.450) 
 25000 - - - 35% (+520.450) 
 Straight line variation between points given. 
  
Datum Fuselage station 0, located 375 inches forward of weighing datum jig point. 
  
Mean Aerodynamic Chord 
(MAC) 
92.644 in. (Leading edge of MAC from datum at +488.025 in.) 
  
Leveling Means Target plate and plumb bob bracket within rear fuselage, at fuselage station 718. 
  
Maximum Weights  l b. * 
(See NOTE 1) Ramp 42250 
 Takeoff 42100 
 Landing 36000 
 Zero Fuel 29500 
 Mini mum flight weight 25000 
 *Certain aircraft are eligible for operation at an increased weight. See AFM as in approved 
publications. 
  
Minimum Crew Two (Pilot an d Co-pilot) 
  
Maximum Occupants 
(See NOTE 1) 
Twenty-two (includes crew). 
  
Fuel Capacity  U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in. 
 2 main tanks (each) 721 600.4 2224 4903 (+506.6) 
 Auxiliar y Tanks 1012 842.7 3121 6882 (+455.6) 
 Total 2454 2043.4 7569 16688 - - - 
       
 Usa ble      
 2 main tanks (each) 720 600 2221 4896 (+506.6) 
 Auxiliary Tan ks 1011 842 3118 6875 (+455.6) 
 Total 2451 2042 7560 16667 - - - 
 See NOTE 1(b) for system fuel. 
       
Oil Capacity  U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in. 
 2-engines (each) 1.70 1.42 6.21 13.7 (+ 645.4) 
 Total 3.40 2.83 12.42 27.4 (+645.4) 
       
 Usa ble      
 2-engines (each) 1.38 1.14 5.04 11.11 (+ 645.4) 
 Total 2.75 2.29 10.08 22.22 (+645.4) 
 See NOTE 1(c) fo r system oil. 
       
 APU      
 Usa ble .408 .340 1.43 3.144 (+646.0) 
 Total .714 .594 2.49 5.5 (+646.0) 
       
 Unusa ble .306 .254 1.06 2.356 (+646.0)

Page 6 of 20  A21EA 
 
 
 
Maximum Operating  Ta keoff and landing: 10000 ft.  
Altitude En route: 41000 ft.  
    
Control Surface  R udder 25° (+1.0°, -0.5°) Left 25° (+1.0°, -.5°) Right 
Movements Elevato r 23.6° (+ or - 1.0°) Up 18.4° (+ or - 1.0°) Down 
 Horizontal Sta bilizer 0° (+0.5° or -0.25°) LE Up -9° (+ o r - 0.5°) LE Down 
 Aile ron 20.8° (+ or - 1.0 °) Up 21.3° (+ or - 1.0°) Down 
 Fla p  – Inboard  0° - 45° (+ o r - 1°) Down 
  – Outboard  0° - 46.7° (+ or - 1°) Down 
 Flight S poiler 0° - 40° (+3°, -0°) Up  
    
Serial Numbers Eligible 3001 to 3066   
  
Service Information Service Bulletins, structural repair manuals, and aircraft flight manuals which contain a statement that th e 
document is Transport Canada approved or Transport Canada approved through the Manufacturers Design 
Approval Representative are accepted by the FAA and are considered FAA approved.  These approvals 
pertain to the type design only. 
 
III - Model CL-600-2B16 (Transport Category), Approved April 30, 1987, by the FAA and April 21, 1987, by the 
Canadian Department of Transport (DOT). 
 
Engines (601-3A Variant) Two General Electric CF-34-3A or CF-34-3A2 or 
  One Gene ral Electric CF-34-3A and one CF-34-3A2 
   
 (601-3R Variant) Two General Electric CF-34-3A1 (Serial Number 5135 to 5194) Approved by the FAA 15 July 1995. 
   
 (604 Variant) Two General Electric CF 34-3B (Serial Number 5301 and subsequent) Approved by the FAA 31 May 1995. 
   
Fuel Type Specifications 
  Canada U.S.A. U.K. China Russia/Ukraine 
 Jet A CAN2-3.23 ASTM D1655 - - - 
 Jet A-1 CAN2-3.23 ASTM D1655 DEF STAN  
91-91 
No. 3 Jet TS-1* or RT 
 Grade JP-5 - MIL-DTL-5624 DEF STAN  
91-86 
- - 
 Grade JP-8 - MIL-DTL-83133 DEF STAN  
91-87 
- - 
 Jet B CAN2-3.22 ASTM D6615 D. En g. RD2486 - - 
 JP-4 CAN2-3.22 MIL-DTL-5624 D. Eng. RD2454 - - 
 *Refer to a ppropriate AFM listed in Approved Publication section when usin g TS-1. 
       
Oil Engine, APU, Generator Adapter: 
MIL-L-7808 (Type I) or MIL-L-23699 (Type II) or other approved oils as identified in the Maintenance 
Manual (refer to Approved publications). 
        
601-3A & 3R Variants        
Engine Limits  SL Static Thrust (lb.) Compressor RPM Interturbine  Temp.**  
   LP HP    
   %N1 %N2 °C °F Time Limit 
 Max. takeoff 9140 98.6 99.4 871 1600 5 minutes 
 Normal takeoff 8650 96.2 98.3 856 1573 5 minutes 
 Max. continuous 8920 98.6 99.2 860 1580  
 Idle range   62.9-64.0    
 Min. Idle in icing conditions   64.0    
 Transient:       
 Max. takeoff    900 1652 2 minutes 
 Normal takeoff    878 1612 2 minutes 
 Start/ relight    930 1706 16 seconds

Page 7 of 20  A21EA 
 
 
 
     903 1657 50 seconds 
 ** See AFM as liste d in Approved Publications for CF-34-3A and CF-34-3A2 engines ITT limits. 
  
 NOTE 
 1. A bove 40000 feet, engine anti-ice bleed or air conditioning unit must be selected ON for each engine. 
  
2. Engine Limits with APR Operating are only applicable to Outside Air Temperatures of -4°F (-20°C) and 
above. 
Oil Temperature   °C °F  
 Maxi mum Permissible (15 minutes Maximum): +163 325  
 Maxi mum for Single Engine Climb (60 minutes maximum): +155 311  
 Maxi mum Continuous: +150 302  
 Mini mum for Starting: -40 -40  
      
      
Oil Pressure Maxi mum Transient Cold Start: 100 psi (6 min. maximum) 
 Maxi mum Continuous: 95 psi  
 Mini mum at Steady State Idle: 25 psi  
 Mini mum at Takeoff (power): 40 psi  
      
APU Limits Maximum RPM 110%    
 Maximum EGT: °C °F   
 Starting (10 seconds) 974 1785   
 Running 731 1348   
      
Airspeed Limits (CAS) V mo and Mmo (maximum operating) m.p.h. Knots Mach  
 Sea level to 10000 ft.  346 301 -  
 10000 ft. to 21330 ft.  414 360 -  
 21330 ft. to 25640 ft.  - - 0.79  
 25640 ft. to 28720 ft.  380 330 -  
 a bove 28720 ft. - - 0.835  
 V fe (Flaps extended) 20° 267 232 -  
  30° 228 198 -  
  45° 218 190 -  
 V a (maneuvering)     
 (See AFM for variation of V a with altitude and aircraft weight). 
 V 1o (Landing Gear Operation) 226 197 -  
 V 1e (Landing Gear Extended) 288 250 -  
    
C.G. Range  Forward Limit Aft Limit 
(See NOTE 1) Weight, l b. % MAC (Sta.) % MAC (Sta.) 
 25000 to 42250 16% (+502.848) -  -  - 
 43250 -  -  - 30% (+515.818) 
 31000 -  -  - 35% (+520.450) 
 25000 -  -  - 35% (+520.450) 
 Straight line variation between points given. 
  
Datum Fuselage station 0, located 375 inches forward of weighing datum jig point 
  
Mean Aerodynamic Chord  
(MAC) 
92.644 in. (Leading edge of MAC from datum at +488.025 in.) 
   
Leveling Means Target plate and plumb bob bracket within rear fuselage, at fuselage station 718. 
  
Maximum Weights  l b. * 
(See NOTE 1) Ram p 43250 
 Takeoff 43100 
 Landin g 36000 
 Zero Fuel 29500 
 Mini mum 25000

Page 8 of 20  A21EA 
 
 
 
 *Certain aircraft are eligible for operation at different weights. See AFM as in approved publications.  601-3 R
Variant for aircraft S/N 5135 and subsequent. 
  
Minimum Crew Two (Pilot an d Co-pilot) 
  
Maximum Occupants Twent y-two (includes crew). 
  
 
604 Variant        
Engine Limits CF34-3B SL Static Thrust (lb.) Compressor RPM Interturbine Temp.  
   LP HP    
   %N1 %N2 °C °F Time Limit 
 Max. takeoff  9220  98.6 99.4 899 1650 5 minutes 
 Normal takeoff  8729 96.2 98.3 884 1623 5 minutes 
 Max. continuous 9140 98.6 99.2 899 1650  
 Idle range   62.9-64.0    
 Min. Idle in icin g conditions   64.0    
 Transient:       
 Max. Takeoff    928 1702 2 minutes 
 Normal Takeoff     906 1663 2 minutes 
 Start/ relight    930 1706 16 seconds 
     903 1657 50 seconds 
 NOTE 
 1. Above 40000 feet, en gine anti-ice bleed or air conditionin g unit must be selected ON for each en gine. 
  
 2. Engine Limits with APR Operating are only applicab le to Outside Air Temperatures of -4°F (-20°C) and 
above. 
      
Oil Temperature   °C °F  
 Maxi mum Permissible (15 minutes Maximum): +163 325  
 Maxi mum for Single Engine Climb (60 minutes maximum): +155 311  
 Maxi mum Continuous: +150 302  
 Mini mum for Starting: -40 -40  
      
      
Oil Pressure Maxi mum Transient Cold Start: 115 psi (10 min. maximum) 
 Maxi mum Continuous: 95 psi  
 Mini mum at Steady State Idle: 25 psi  
 Mini mum at Takeoff (power): 45 psi  
      
APU Limits      
 Maximum RPM 110%    
 Maximum EGT: °C °F   
 Starting (10 seconds) 974 1785   
 Running 731 1348   
      
Airspeed Limits (CAS) V mo and Mmo (maximum operating) m.p.h. Knots Mach  
 Sea level to 8000 ft.  345 300 -  
 8000 ft. to 22160 ft.  400 348 -  
 22160 ft. to 26570 ft.  - - 0.78  
 26570 ft. to 30997 ft.  366 318 -  
 a bove 30997 ft. - - 0.85  
      
 V fe (Flaps extended) 20° 266 231 -  
  30° 227 197 -  
  45° 217 189 -  
 V a (maneuvering)     
 (See AFM for variation of V a with altitude and aircraft weight). 
 V 1o (Landing gear operation) 227 197 -

Page 9 of 20  A21EA 
 
 
 
 V 1e (Landing gear extended) 288 250 -  
C.G. Range  Forward Limit Aft Limit 
(See NOTE 1) Weight, l b. % MAC (Sta.) % MAC (Sta.) 
 26000 to 38000 20% (+506.553) - - - 
 39500 to 44750 16% (+502.847) - - - 
 47700 20% (+506.553) - - - 
 47700 to 43000 - - - 38% (+523.228) 
 38000 to 26000 - - - 35% (+520.449) 
 Straight line variation between points given. 
  
Datum Fuselage station 0, located 375 inches forward of weighing datum jig point. 
   
Mean Aerodynamic Chord  
(MAC) 
92.644 in. (Leading edge of MAC from datum at +488.025 in.) 
   
Leveling Means Target plate and plumb bob bracket within rear fuselage, at fuselage station 718. 
   
Maximum Weights  l b. * 
(See NOTE 1) Ramp 47700 
 Takeoff 47600 
 Landing 38000 
 Zero Fuel 32000 
 Mini mum 26000 
 *Certain aircraft are eligible for operation at different weights. See AFM as in approved publications.  601-3 R
Variant for aircraft S/N 5135 and subsequent 
   
Minimum Crew Two (Pilot an d Co-pilot) 
Maximum Occupants Twent y-two (includes crew). 
  
601-3A Variant       
Fuel Capacity  U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in.
 Usa ble 
 2 main tanks (each) 727 605 2227 4909 (+506.6) 
 Fusela ge tanks 1017 847 3115 6868 (+455.6) 
 Total 2472 2059 7569 16686  
 See NOTE 1 (b) for system fuel. 
       
601-3R Variant       
Fuel Capacity  U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in.
 Usa ble 
 2 main tanks (each) 727 605 2227 4909 (+506.6) 
 Fusela ge tanks 1010 841 3115 6868 (+455.6) 
 Tail tan k 187.7 156.24 579 1276 (+816.7) 
 Total 2651.7 2207.24 8148 17962  
 See NOTE 1 (b) for system fuel. 
  
604 Variant       
Fuel Capacity  U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in.
 Usa ble      
 2 main tanks (each) 720 600 2205 4860 (+506.6) 
 Auxiliar y tank 1062 884 3251 7168 (+450.6) 
 Tail tan k 461 384 1411 3112 (+771.7) 
 Total 2963 2467 9072 20000  
 See NOTE 1( b) for system fuel. 
       
Oil Capacity 601-3A Variant* U.S. Gal. Imp. Gal. Kg. Weight, lb. Mom.Arm-in.
 2-en gines (each) 1.70 1.42 5.94 13.09 (+653.0) 
 Total 3.40 2.83 11.88 26.18 (+653.0) 
 Usa ble      
 2-engines (each) 1.38 1.14 4.80 10.59 (+ 653.0) 
 Total 2.75 2.29 9.60 21.18 (+653.0)

Page 10 of 20  A21EA 
 
 
 
 See NOTE 1 (c) for system oil. 
       
 APU      
 Usable .408 .340 1.43 3.144 (+646.0) 
 Total .714 .594 2.49 5.5 (+646.0) 
 Unusable .306 .254 1.06 2.356 (+646.0) 
 *601-3R Variant & 604 Variant - same as 601-3A, except as listed in the AFM approved 
publication. 
Maximum Operating 
Altitude 
Takeoff and landing: 
En route: 
10000 ft. 
41000 ft. 
 
    
Control Surface Movements Rudder 25° (+1°, -0.5°) Left 25° (+1° or -0.5°) Right 
 Elevato r 23.6° (+ o r - 1.0°) Up 18.4° (+ o r - 1.0°) Down 
 Horizontal Sta bilizer 0° (+ or - 0.3°) LE Up -9° (+ or - 0.3°) LE Down 
 Aile ron 20.8° (+ o r - 1°) Up 21.3° (+ o r - 1°) Down 
 Fla p  – Inboard  0° - 45° (+ or - 1°) Down 
  – Outboard  0° - 46.7° (+ o r - 1°) Down 
 Fli ght Spoiler 0° - 40° (+3°, -0°) Up  
    
Serial Numbers Eligible 5001 an d subsequent 
    
Service Information Service Bulletins, structural repair manuals, and aircraft flight manuals which contain a statement that th e 
document is Transport Canada approved or Transport Canada approved through the Manufacturers Design 
Approval Representative are accepted by the FAA and are considered FAA approved.  These approvals 
pertain to the type design only. 
 
  
 Data Pertinent to all Models 
   
Approved 
Publications 
Model CL-600-1A11 (600) 
 (a) Airplane Flight Manual, Cana dair Publication RAG-600-101, Issue 2 (PSP 600 (U.S.) FAA, and PSP 600-1 
(U.S.) for the appropriate configuration, (See NOTE 1) and approved revisions. 
 (b) Drawin g List, Canadair Publicati on RAL-600-105, and later a pproved revisions. 
   
 Model CL-600-2A12 (601) 
 (a) Airplane Flight Manual, Cana dair Publication PSP 601-1A, PSP 601-1A-1, PSP 601-1B and PSP 601-1B-1 for 
the appropriate weight configuration, (See NOTE 1) and approved revisions. 
 (b) Drawin g List, Canadair Publicati on RAL-601-105, and later a pproved revisions. 
   
 Model CL-600-2B16 (601-3A, 601-3R, & (604 Variants (from S/N 5301 to 5699))) 
 (a) Airplane Flight Manual, Cana dair Publication PSP 601A-1, PSP 601A-1 -1 and PSP 604-1 for the appropriate 
weight configuration, (See NOTE 1) and approved revisions. 
 (b) Drawing List, Canadair Public ation RAL-601A-105 (3A & 3R Varian ts) and RAL-604-0001 (604 Variant), 
and later approved revisions. 
   
 Model CL-600-2B16 (604 Variant (from S/N 5701 to 5990)) 
 (a) Airplane Flight Manual, Canadair  Publication PSP 605-1 for the appropriate weight configuration, (See NOTE 
1&9) and approved revisions. 
 (b) Drawing List, Canadair Publ ication RAL-604-0001 (604 Variant) , and later approved revisions. 
   
 Model CL-600-2B16 (604 Variant (from S/N 6050 & Subs)) 
 (a) Airplane Flight Manual, Canadair  Publication PSP 650-1 for the appropriate weight configuration, (See NOTE 
1&14) and approved revisions. 
 (b) Drawin g List, Canadair Publication RAL-604-0001 (604 Variant), and later approved revisions. 
   
 
Import Eligibility 
 
Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used 
aircraft based on the scope of the agreement, to identif y any required statements by the exporting authority on the 
export certificate of airworthiness (or equivalent documen t), and for procedures for coordinating exceptions to 
conformity statements on these doc uments. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for 
requirements of an airworthiness certificate for imported aircraft.

Page 11 of 20  A21EA 
 
 
 
   
Certification 
Basis 
Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A & 3R Variants) 
 FAR Part 25 dated February 1, 1965, including Amendments 25-1 through 25-37, plus 
FARs 25.675(a), 25.685(a), 25.733(c), 25.775(e), 25.787(c),  25.815, 25.841(b), 25.951(a), 25.979(d) and (e), 25.1041, 
25.1143(e), 25.1303(a), 25.1322, 25.1385(c), 25.1557(b), 25.1583(a), of Amendment 25-38; 
FARs 25.901(b) and (c), 25.903(c) and (e), 25.933(a), 25.943, 25.959, 25.1091(a) and (d), 25.1145(c), 25.1199(b) and 
(c), 25.1207, 25.1549, 25.1585(a)(9) of Amendment 25-40; and  
FAR 25.1309 of Amendment 25-41;  
FAR 25.1353(c) of Amendment 25-42;  
FAR's25.571 and 25.629(d)(4) (v) of Amendment 25-45;  
FARs 25.351 and 25.603 of Amendment 25-46. 
   
 Model CL-600-2B16 (604 Variant) 
 FAR Part 25 dated February 1, 1965, including Amendmen ts 25-1 through 25-78 with the following exceptions:  
FAR Part 25 at Amendments 25-1 through Amendment 25-3 7 for paragraphs: 109, 149, 365, 561, 625, 701, 772, 783 
(except 783(f)), 785 (except 785(g)), 789, 791, 801, 803, 807, 809, 811, 812, 813, 831, 853, 855, 857, 1307, 1359, 1415, 
& 1419;  
FAR Part 25 at Amendment 25-37 for existing installations and Amendment 25-78 for new installations for paragraphs: 
963, 965, 994, 997, and 1438;  
FAR Part 25 at Amendment 25-38 for paragraphs 787 and 1439;  
FAR Part 25 at Amendment 25-40 for paragraph 25.973;  
FAR Part 25 at Amendment 25-37 for paragraph 25.109 (see Note 7);  
FAR Part 25 at Amendment 25-44 for paragraph 25.1413;  
FAR Part 25 at Amendment 25-54 for paragraph 851;  
FAR Part 25 at Amendment 25-80 for paragraph 1316.  
New FAR Part 25 requirements 562, 810, 819, 832, 858, 869, (a) & (b), 1421, 1423 and 1450 are not part of the 
certification basis. 
    
 Additional FAA Requirements 
    
 (a) Model CL-600-1A11 (600) 
  (1) FAR Part 36 dated December 1, 1969, as amended throu gh Amendment 36-9 inclusive. 
  (2) SFAR 27 dated Februar y 1, 1974, as amended throu gh Amendment SFAR 27-2. 
  (3) Special Conditions: 
- No. 25-94-EA-12 dated March 26, 1980, (FAA Docket No. 16921) and Amendment No. 1 dated 
September 11, 1981. 
- No. 25-666-SC Non-Rechargeable Lithium Batterie s, effective to design changes applied for 
after May 9, 2017. See the applicability section of  this special condition for more information on 
which design change must meet it. 
    
  Date of application for Ty pe Certificate August 3, 1976. 
Type Certificate A21EA i ssued November 7, 1980. 
    
 
 (b) Model CL-600-2A12 (601) 
  (1) FAR Part 36 dated December 1, 1969, as amende d through Amendments 36-9 in clusive. (See Note 18) 
  (2) SFAR 27 dated Februar y 1, 1974, as amended throu gh Amendment SFAR 27-2. 
  (3) Special Conditions: 
- No. 25-ANM-1 dated March 8, 1983.  
- No. 25-666-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for 
after May 9, 2017. See the applicability section of  this special condition for more information on 
which design change must meet it. 
   
  Date of application for amendment to Type Certificate May 1, 1981. 
Type Certificate A21EA amended March 11, 1983.

Page 12 of 20  A21EA 
 
 
 
 (c) Model CL-600-2B16 (601-3A & 3R Variants) 
  (1) FAR Part 36 dated December 1, 1969, as amende d through Amendments 36-9 inclusive.  (See Note 18) 
  (2) SFAR 27 dated Februar y 1, 1974, as amended throu gh Amendment SFAR 27-2. 
  (3) Special Conditions: 
- No. 25-ANM-1 dated March 8, 1983. 
- No. 25-666-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for 
after May 9, 2017. See the applicability section of  this special condition for more information on 
which design change must meet it. 
  Date of application for amendment to Type Certificate March 3, 1986. 
Type Certificate A21EA amended April 30, 1987. 
    
 (d) Model CL-600-2B16 (604 Variant) 
  (1)  From S/N 5301 to 5990, FAR Part 36 dated December 1, 1969, as am ended through Amendments 36-
20 inclusive. (See Note 18) 
  (2) From S/N 6050 and subsequent:  
 FAR Part 36 dated December 1, 1969, as amen ded through Amendments 36-28 inclusive  
 14 CFR Part 38 effective April 16, 2024, Airplane  Fuel Efficiency Certification, Amendment 
38-1, §38.17(b)(5) 
  (3) FAR Part 34 dated Au gust 25, 1990 as amended throu gh Amendment 34-1.  
  (4) Special Conditions: 
- No. 25-ANM-109 dated October 31, 1995 (HIRF). 
- No. 25-666-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for 
after May 9, 2017. See the applicability section of  this special condition for more information on 
which design change must meet it. 
  Date of application for Change to Type Design June 14, 1993.  
Change to Type Design approved November 2, 1995. 
    
 Equivalent safety has been established for the following requirements:  
  
 (a) CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A & 3R Variants). 
  (1) FAR 25.773 (b)(2) DV Window 
  (2) 25.955(a)(4) Blocke d Flow Meter Fuel Flow Requirements 
  (3) FAR 25.201 Stall Dete rmination 
   
 (b) CL-600-2B16 (604 Variant) 
  (1) FAR 25.955 (a)(4) Blocke d Flow Meter Fuel Flow Requirements 
  (2) Seve ral FAR’s for the use of Reduced Minimum Operating Speed Factors 
  (3) FAR 25.125(a) Increased Flare Height, fo r Steep Approach Landing Ops. at London City 
   
 (c) CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 3R, & 604 Variant) 
  (1) Ditchin g provisions of 14 CFR 25.801 
  (2) Ice P rotection of 14 CFR 25.1419 
    
Equipment The basic equipment as prescribed in the applicable airworthiness requirements (See Certification Basis) 
must be installed in the aircraft for certification. 
    
Part 26 – 
Continued 
Airworthiness 
and Safety 
Improvements 
for Transport 
Category 
Airplanes 
Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A & 3R Variants)  
Based on § 21.101(g) for changes to TCs, applicable provisions of Part 26 are included in the certification basis. For any 
future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. 
  
 Exemption 9947 
This exemption grants relief to Bo mbardier Model CL-600-1A11 (600), CL-600-2A12 (601), and CL- 600-2B16 (601-
3A & 3R Variants) from having to meet the airworthiness requirements of §§ 26.11, 26.33, 26.35, 26.43, 26.45, and 26.49. 
(See Note 10 for a list of related operational requirements and associated considerations)

Page 13 of 20  A21EA 
 
 
 
Model CL-600-2B16 (604 Variant) 
 Based on § 21.101(g) for changes to TCs, applicable provisions  of Part 26 are included in the certification basis. For any 
future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. 
  
 Exemption 9947 
This exemption grants relief to Bombardier Model CL-600-2B16 (604 Variant) from having to meet the airworthiness 
requirements of §§ 26.11, 26.33, 26.35, 26.43, 26.45, and 26.49. 
(See Note 10 for a list of related operational  requirements and associated considerations) 
  
NOTE 1  This Aircraft Type Certificate Data Sheet defines a configuration which does not include passenger provision for the CL-
600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 3R & 604 Variants) models. Carriage of persons in 
the cabin is permitted when an approved seating arrangement and related required passenger provisions are incorporated. 
  
 (a) Current weight and balanc e report including the list of equipment included in the certificated empty weight, and 
loading instructions when necessary, must be provided for each aircraft at the time of original certification. 
   
 ( b) Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 3R & 604 Variants) 
  System fuel, which must be included in the empty weight, is the amount of fuel required to fill the system 
plumbing and tanks to the undrainable level plus unusable fuel in the fuel tanks. The total amount of “system 
fuel” for the following Challenger variants is: 
  Model: Total Unusable (system fuel) 
  CL-600-1A11 (600), 2A12 (601) 16.0 gal. total, 109 lb., (arm +500.00) 
  CL-600-2B16 (601-3A & 3R Variants) 17.5 gal. total, 119 l b., (arm +524.80) 
  CL-600-2B16 (604 Variant) 19.0 gal. total, 129 lb., (arm +536.60) 
   
 (c) Model CL-600-1A11 (600) 
  System oil, which must be included in the empty weig ht, is the amount of oil necessary for engine lubrication. 
The total amount of "s ystem oil" is as follows: 
  7.38 U.S. gal. (total)  56.8 lb., (arm +623) 
  Model CL-600-2A12 (601) and CL-600-2B16 (601-3A, 3R and 604 Variant ) 
  System oil, which must be included in the empty weig ht, is the amount of oil necessary for engine lubrication. 
The total amount of "s ystem oil" is as follows: 
  6.1 U.S. gal. (total), 47 l b., (arm +680.5) 
   
 (d) Model CL-600-1A11 (600) 
  Aircraft which incorporate Canadair Limited Modification Summaries: 
1) 600-556 Modified main landing gear wheel, 
2) 600-592 Modified main landing gear sidestay, 
3) 600-1933 Revised airspeed limitation placard. 
May be operated to the following limitations (eligible Serial Numbers 1002, 1004 through 
1037): 
    
  Maxi mum Weight lb. 
   Ram p 38650 
   Takeoff 38500 
   Landing 32500 
   Zero Fuel 28500 
   
  Maximum Occupants Twenty-two (includes crew) 
  C.G. Range 
    Fo rward Limit Aft Li mit 
   Weight, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 38650 16 % (+502.848) -  -  - 
   38650 -   -   - 28%  (+513.965) 
   25800 -   -   - 33%  (+518.598) 
   24000 -   -   - 33%  (+518.598) 
   St raight line variation between points given. 
      
  Maxi mum Operating Altitude 
   Takeoff an d landing 10000 ft.  
   En route 40000 ft.

Page 14 of 20  A21EA 
 
 
 
41000 ft. with Canadair Limited Modification Summaries 600-1923 & 
600-8330 incorporated. 
      
 (e) Model CL-600-1A11 (600) 
  Aircraft which incorporate Canadair Limited Modification Summaries: 
1) 600-594 Landing gear for 40400 lb. takeoff weight aircraft, 
2) 600-616 Wheels and brakes for the 40400 lb. takeoff weight aircraft, 
3) 600-643 Structural reinforcem ent at wing B.L. O rib, 
4) 600-752 Modified anti-skid unit, 
5) 600-817 Stall protection syst em computer for the 40400 lb. takeoff weight aircraft, 
6) 600-8150 Placard for the 40400 lb. takeoff weight aircraft, 
7) 600-760 Drop down passenger door-production improvement (required only on 
S/N 1024 & subsequent). 
May be operated to the following limitations (eligible Serial Numbers 1002, 1004 and subse quent): 
     
  Maxi mum Weight lb.  
   Ramp 40550  
   Takeoff 40400  
   Landing 36000  
   Zero fuel 28500  
      
  Maxi mum Occupants Twenty-two (includes crew) 
      
  C.G. Ran ge (Aircraft without Canadair Modification Summary 600-8265 incorporated) 
    Fo rward Limit Aft Li mit 
   Wei ght, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 40550 16 % (+502.848) - 
   40550 - 27%  (+513.039) 
   38000 - 31%  (+516.745) 
   31000 - 31%  (+516.745) 
   27500 - 33%  (+518.598) 
   24000 - 33%  (+518.598) 
   St raight line variation between points given. 
      
  C.G. Range (Aircraft with Canadair Modification Summary 600-8265 incorporated) 
    Fo rward Limit Aft Li mit 
   Weight, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 40550 16 % (+502.848) - 
   40550 - 27%  (+513.039) 
   38000 - 31%  (+516.745) 
   31000 - 31%  (+516.745) 
   28500 - 35%  (+520.450) 
   24000 - 33%  (+520.450) 
   St raight line variation between points given. 
      
  Maxi mum Operating Altitude   
   Takeoff an d landing 10000 ft.  
   En route 40000 ft.  
    41000 ft. with Canadair Modification Summaries 600-1923 & 600-8330 
incorporated 
     
 (f) Model CL-600-1A11 (600)   
     
  Airs peed Limits (CAS)   
  Aircraft which, in addition to the Canadair Modifica tion Summaries essential for operation at a maximum takeoff 
weight of 40400 lb., also incorporate the following Canadair Modification Summary: 
1) 600-665 Revised Vmo/Mmo outputs of ADC and limitations placard may be operated at the following 
limitations: 
      
   V mo and Mmo (maximum operating) m.p.h. Knots Mach. 
   Sea level to 10000 feet 345 300 - 
   A bove 10000 feet 420 365 0.835

Page 15 of 20  A21EA 
 
 
 
  Extension of the flight spoilers at airspeeds above Ma ch = 0.79 is not permitted unless the following additional 
Canadair Modification Summ aries are incorporated: 
1) 600-512 Prevention of spoiler asymmetry 
2) 600-809 Dormant failure protection of the flight spoiler detent 
3) 600-8212 Hydraulic pipe routing to suit spoiler detent mechanism. 
      
 (g) Model CL-600-1A11 (600)  
  Aircraft Serial Numbers 1086 and subseque nt and aircraft incorporated the following: 
  1 ) Either  
   a)  Canadair Service Bulletin 
600-0378 – Modification - Stall Protection System - Stall Strip Removal and Altitude 
Compensation 
  or b) Supplementary Type Certificate SA99NE - Wing Stall Strip Removed 
  an d    
  2)  Canadair Service Bulletin 
600-0379 - Modification - Tires and Airs peed Limitation Placards – 41100 Pounds Takeoff Wei ght. 
  May be operated to the following limitations (eligible Serial Numbers 1002, 1004 and subsequent) 
   
  Maxi mum Weight lb.  
   Ram p 41250  
   Takeoff 41100  
   Landin g 36000  
   Zero fuel 28500  
      
  Maxi mum Occupants Twenty-two (includes crew).  
   
C.G. Range Aircraft 1004, 1009, 1053 to 1056, 1066 an d subsequent and Aircraft incorporating Canadair 
Service Bulletin 600-0221 or 600-0486 
    Fo rward Limit Aft Li mit 
   Wei ght, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 41250 16% (+502.848) - 
   41250 - 26% (+512.112) 
   38000 - 31% (+516.745) 
   31000 - 31% (+516.745) 
   28500 - 35% (+520.450) 
   24000 - 35% (+520.450) 
   St raight line variation between points given. 
      
  C.G. Range (Othe r Aircraft) 
    Fo rward Limit Aft Li mit 
   Weight, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 41250 16% (+502.848) - 
   41250 - 26% (+512.112) 
   38000 - 31% (+516.745) 
   31000 - 31% (+516.745) 
   27500 - 33% (+518.598) 
   24000 - 33% (+518.598) 
   St raight line variation between points given. 
    
  Maxi mum Operating Altitude  
   Takeoff an d landing 10000 ft.  
   En route 41000 ft.  
      
  Airs peed Limits (CAS)   
   V mo and Mmo (maximum operating) m.p.h. Knots Mach. 
   Sea level to 10000 feet 345 300 - 
   A bove 10000 feet 420 365 0.835 
   Extension of the flight spoilers  at airspeeds above Mach = 0.80 is not permitted on Aircraft S/N 1005 to 
1008, 1010 to 1052, 1057 to 1066 not incorporating Canadair Service Bulletin 600-0086 Modification - 
Spoilers - Ground Spoiler Activation and Flight Spoiler Detent Mechanism.

Page 16 of 20  A21EA 
 
 
 
 (h) Model CL-600-1A11 (600)   
  Ai rcraft incorporating the following Canadair Service Bulletins 
  a)  600-0350 Modification - Engine Speed Indicating- N1 Fan Speed Indicator  
b) 600-0379 Modification - Tires and Airspeed Li mitation Placards - 41100  lb. Takeoff Weight. 
c) 600-0401 Modification - Win glets - Addition 
  With Aircraft Serial Numbers 1005 to 1008 and 1010 to 1051 incorporating the following additional Canadair 
Service Bulletins 
  eithe r 600-0096 Modification - Nose Landing Gear Steering  
  or 600-0380 Modification - Nose Gear - Steer b y Wire. 
  May be operated to the following limitations (eligible Serial Numbers 1002, 1004 and subsequent). 
      
  Maxi mum Weight lb.  
   Ramp 41250  
   Takeoff 41100  
   Landing 36000  
   Zero Fuel 28500  
      
  Maxi mum Occupants Twenty-two (includes crew).  
      
  C.G. Range Aircraft 1004, 1009, 1053 to 1056, 1066 and Subsequent and Aircraft Incorporating Canadair 
Service Bulletin 600-0221 or 600-0486 
    Fo rward Limit Aft Li mit 
   Wei ght, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 41250 16% (+502.848) - 
   41250 - 26% (+512.112) 
   38000 - 31% (+516.745) 
   31000 - 31% (+516.745) 
   28500 - 35% (+520.450) 
   24000 - 35% (+520.450) 
   St raight line variation between points given. 
   
C.G. Range (Other Aircraft) 
 
    Fo rward Limit Aft Li mit 
   Wei ght, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 41250 16% (+502.848) - 
   41250 - 26% (+512.112) 
   38000 - 31% (+516.745) 
   31000 - 31% (+516.745) 
   27500 - 33% (+518.598) 
   24000 - 33% (+518.598) 
   St raight line variation between points given. 
      
  Maxi mum Operating Altitude  
   Takeoff an d landing 10000 ft.  
   En route 41000 ft.  
    
  Airspeed Limits (CAS)  
   V mo and Mmo (maximum operating) m.p.h. Knots Mach 
   Sea level to 10000 feet 345 300 - 
   10000 ft. to 21420 ft. 420 365 - 
   21420 ft. to 25740 ft. - - 0.79 
   25740 ft. to 28640 ft. 385 335 - 
   a bove 28640 ft. - - 0.835 
    
   Vfe (Flaps extended) 
    20° 265  230  
    30° 226  196  
    45° 215 187  
   Extension of the flight spoilers at airspeeds a bove Mach = 0.79 is not permitted on Aircraft S/N 1005 
to 1008, 1010 to 1052, 1057 to 1066 not incorporating Canadair Service Bulletin 600-0086 
Modification - Spoilers - Ground Spoiler Acti vation and Flight Spoile r Detent Mechanism.

Page 17 of 20  A21EA 
 
 
 
 (i) Model CL-600-1A11 (600) 
  Ai rcraft incorporating the following Canadair Service Bulletins 
  a)  600-0350 Modification - Engine Speed Indicating- N1   Fan Speed Indicator 
b) 600-0446 Modification - Placard-41250 lb. Take-off Weight (Aircraft with Winglets).  
c) 600-0401 Modification - Winglets - Addition 
  With Aircraft Serial Numbers 1005 to 1008 and 1010 to 1051 incorporating the following additional Canadair 
Service Bulletins 
  eithe r 600-0096 Modification - Nose Landing Gear Steering 
  o r 600-0380 Modification - Nose Gea r - Steer by Wire. 
  May be operated to the following limitations (eligible Serial Numbers 1002, 1004 and subsequent). 
       
  Maxi mum Weight lb.   
   Ramp 41400   
   Takeoff 41250   
   Landing 36000   
   Zero Fuel 28500   
       
  Maximum Occu pants Twenty-two (includes crew).  
       
  C.G. Range Aircraft 1004, 1009, 1053 to 1056, 1066 and Subsequent and Aircraft Incorporating Canadair 
Service Bulletin 600-0221 
    Fo rward Limit Aft Li mit 
   Weight, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 41400 16% (+502.848) - 
   41400 - 26% (+512.112) 
   38000 - 31% (+516.745) 
   31000 - 31% (+516.745) 
   28500 - 35% (+520.450) 
   24000 - 35% (+520.450) 
   St raight line variation between points given. 
   
  C.G. Ran ge (Other Aircraft) 
    Fo rward Limit Aft Li mit 
   Wei ght, lb. % MAC (Sta.) % MAC (Sta.) 
   24000 to 41400 16% (+502.848) - 
   41400 - 26% (+512.112) 
   38000 - 31% (+516.745) 
   31000 - 31% (+516.745) 
   27500 - 33% (+518.598) 
   24000 - 33% (+518.598) 
   St raight line variation between points given. 
    
  Maxi mum Operating Altitude 
   Takeoff an d landing 10000 ft.   
   En route 41000 ft.   
     
  Airs peed Limits (CAS)   
   V mo and Mmo (maximum operating) m.p.h Knots Mach 
   Sea level to 10000 feet 345 300 - 
   10000 ft. to 21420 ft. 420 365 - 
   21420 ft. to 25740 ft. - - 0.79 
   25740 ft. to 28640 ft. 385 335 - 
   a bove 28640 ft. - - -0.835 
   
   Vfe (Flaps extended)    
    20° 265  230  
    30° 226  196  
    45° 215 187  
   Extension of the flight spoilers  at airspeeds above Mach = 0.79 is not permitted on Aircraft S/N 1005 to 
1008, 1010 to 1052, 1057 to 1066 not incorporating Canadair Service Bulletin 600-0086 Modification 
– Spoilers - Ground Spoiler Activation and Fli ght Spoiler Detent Mechanism.

Page 18 of 20  A21EA 
 
 
 
       
 (j) Model CL-600-2A12 (601)    
  Aircraft Serial Numbers 3018 and subsequent and aircraft incorporating the following Canadair Service Bulletin 
601-0032 - Modification - Tires and Airspeed Limitation Placards 43100 lb. Takeoff Weight may be operated to 
the following limitations (eligible Serial Numbers 3001 and subsequent) 
       
  Maxi mum Weight lb.   
   Ra mp 43250   
   Takeoff 43100   
       
  Maximum Occupants Twenty-two (includes crew).   
       
  C.G. Range   
    Fo rward Limit Aft Li mit 
   Weight, lb. % MAC (Sta.) % MAC (Sta.) 
   25000 to 43250 16% (+502.848) - 
   43250 - 30% (+515.818) 
   31000 - 35% (+520.450) 
   25000 - 35% (+520.450) 
   St raight line variation between points given. 
  
NOTE 2 Model CL-600-1A11 (600) 
 All placards must be installed in accordance with Canadair Limited Drawings:  600-40402, 600-40452, 600-51000, 600-
51002, 600-51004 
  
 Model CL-600-2A12 (601) 
 All placards must be installed in accordance with Canadair Limited Drawings:  601-40402, 601-40452, 600-51000, 600-
51002, 601-51004. 
  
 Model CL-600-2B16 (601-3A, 3R and 604 Variants ) 
 All placards must be installed in accordance with Canadair Limited Drawings:  601-40402, 601-40452, 601A51000, 
601A51002, 601A51004.(601-3A & 3R Variants) 601-40402, 601-40452 & 604-51000 (604 Variant) 
  
NOTE 3 Model CL-600-1A11 (600) 
 The airplane life limits and repetitive inspections for components and equipment are listed in Canadair Time 
Limits/Maintenance Checks, PSP 605.  These limitations may not be changed without FAA Engineering approval.  This 
document with Canadair Maintenance Manual, PSP 602 and Job Inspection Card Manual PSP 622, NDT-612 contain all 
information essential for proper maintenance. 
  
 Model CL-600-2A12 (601) 
 The airplane life limits and repetitive inspections for components and equipment are listed in Canadair Time 
Limits/Maintenance Checks, PSP 601-5.  These limitations may not be changed without FAA Engineering approval.  This 
document with Canadair Maintenance Manual, PSP 601-2 and Job Inspection Card Manual PSP 601-22, NDT-612 
contain all information essential for proper maintenance. 
  
 Model CL-600-2B16 (601-3A, 3R and 604 Variants) 
 The airplane life limits and repetitive inspections for components and equipment are listed as follows: 
1. 601 3A and 3R Variants: Canadair Time Limits/Maintenance Checks, PSP 601A-5; 
2. 604 Variant (s/n 5301 to 5699): Time Limits/Maintenance Checks, Identification No. CH 604 TLMC, Section 
5-10; 
3. 604 Variant (s/n 5701 to 5990): Time Limits/Maintenance Checks, Identification No. CH 605 TLMC, Section 
5-10. 
4. 604 Variant (s/n 6050 and subsequent): Time Limits/Maintenance Checks, Identification No. CH 650 TLMC, 
Section 5-10. 
 These limitations may not be changed without FAA Engineering approval.  These documents and the associated Canadair 
Maintenance Manual: 
1. 601 3A and 3R Variants: Aircraft Maintenance Manual PSP 601-2 Identification No. CH 601MM; 
2. 604 Variant (s/n 5301 to 5699): Aircraft Maintenance Manual Identification No. CH 604 MM; 
3. 604 Variant (s/n 5701 to 5990): Aircraft Maintenance Manual Identification No. CH 605 MM; 
4. 604 Variant (s/n 6050 and subsequent): Aircraft Maintenance Manual Identification No. CH 650MM; 
 and/or Job Inspection Card Manuals PSP601A-22 (601-3A Variant) and/or PSP 601R-22 (601-3R Variant), PSP604-22 
(604 Variant), NDT604-12 contain all information essential for proper maintenance.

Page 19 of 20  A21EA 
 
 
 
  
NOTE 4 RESERVED 
  
NOTE 5 RESERVED 
  
NOTE 6 RESERVED 
  
NOTE 7 Model CL-600-2B16 (604 Variant) 
 The following additional requirements must be included with FAR 25.109 at Amendment 
25-37: 
1. Airplane Flight Manual information, in the form of guidance material, must be provided for supplementary 
operating procedures and performance information for operating on wet and contaminated runways. 
2. The accelerate-stop distance and landing distance must be determined using the braking performance which is 
obtained with the brake conditions that are expected in service. 
  
NOTE 8 RESERVED 
  
NOTE 9 The Challenger 605 is a marketing designation for the Ch allenger CL-600-2B16 (604 Variant) with Modsums 604DX10000, 
604DX20000 and 604DX30000 incorporated, beginning with aircraft s/n 5701 to s/n 5990.  This designation is for marketing 
purposes only. 
  
NOTE 10 This exemption does not grant relief from th e related operational requirements contained in §§ 
121.1109, 121.1111, 121.1117, 125.509, 129.109, 129.111 or 129.117.  Should a person choose to operate a Bombardier 
Model CL-600-1A11 (600), CL-600-2A12 (601), CL-600-2B16 (601-3A Variant), CL-600-2B16 (601-3R Variant) or CL-
600-2B16 (604 Variant) airplane under part 121, 125, or part 129 beyond the operational compliance deadlines as stated in 
§§ 121.1109, 121.1111, 121.1117, 125.509, 129.109, 129.111 or 129.117, that person will be required to comply with those 
operational requirements. 
  
NOTE 11 RESERVED 
  
NOTE 12 RESERVED 
  
NOTE 13 RESERVED 
  
NOTE 14 The Challenger 650 is a marketing designation for the Challenger CL-600-2B16 (604 Variant) beginning with aircraft s/n 
6050 and subsequent. This designation is for marketing purposes only. 
  
NOTE 15 RESERVED 
  
NOTE 16 RESERVED 
 
 
 
NOTE 17 The following models were previously recorded on Revisi on No. 48 of this TCDS A21EA and have been administratively 
transferred to TCDS A21EA-1 Revision No. IR on November 26, 2019 pursuant to 14 CFR § 21.47: 
• CL-600-2B19 (Regional Jet Series 100 & 440) 
• CL-600-2C10 (Regional Jet Series 700, 701 & 702) 
• CL-600-2C11 (Regional Jet Series 550) 
• CL-600-2D15 (Regional Jet Series 705) 
• CL-600-2D24 (Regional Jet Series 900)  
• CL-600-2E25 (Regional Jet Series 1000) 
 
Existing manufactured Regional Jet Series aircraft have iden tification data plates which still refer to this FAA Type 
Certificate A21EA since the approved type design was reco rded on this FAA Type Certificate A21EA at the time of 
manufacture. Since both FAA Type Certificates A21EA and A21EA-1 cross-reference each other via a record on the first 
page of both FAA Type Certificate Data Sheets, these aircraft will not require Supplemental aircraft identification data plates 
to comply with 14CFR §§ 21.182, 45.11, & 45.13. 
 
FAA Airworthiness Directives (ADs) and any associated Alternate Means of Compliance (AMOCs) that refer to this FAA 
Type Certificate A21EA and apply to any of the approved Regional Jet Series aircraft models listed above, continue to remain 
applicable following this administrative change.

Page 20 of 20  A21EA 
 
 
 
 
 
Model Variant Designation Marketing Designation Serial Number 
CL600-1A11   CL600  1002, 1004-1085  
CL600-2A12   CL601  3001-3066  
CL600-2B16  601-3A  CL601-3A  5001-5134  
CL600-2B16  601-3R  CL601-3R  5135-5194  
CL600-2B16  604 CL604  5301-5699  
CL600-2B16  604 CL605  5701-5990  
CL600-2B16  604 CL650 6050-6999  
 
 
...END... 
Existing FAA Supplemental Type Certificates (STCs), Part Manufacturing Approvals (PMAs), Airworthiness Directives 
(ADs) or Alternate Means of Compliance (AMOCs) that refer to this FAA Type Certificate A21EA and list any of the 
approved Regional Jet Series aircraft models listed above, are not required to be revised following this administrative change. 
When revising FAA STCs or PMAs for any other reason in the future, the STCs or PMAs may directly refer to both Type 
Certificates.  
  
NOTE 18 Noise certification basis is revised to 14 CFR Part 36 Am endment 36-28; additional modifications essential to meet the 
requirements or needed to attain the certificated noise levels are met through Service Bulletins as specified: 
 
• CL-600-2A12 (601 Variant) – SB 601-0638 
• CL-600-2B16 (601-3A/3R Variant) - SB 601-0638 
• CL-600-2B16 (from S/N 5301 to 5699) - SB 604–11–016 
• CL-600-2B16 (from S/N 5701 to 5990) - SB 605–11–003
```

## ADs (168, first 50, in force first)

- [AD 2026-14-09](https://openairdocs.org/ad/2026-14-09): Time Limits/Maintenance Checks · Bombardier CL-600-1A11 (600), CL-600-2B16 (601-3A Variant), CL-600-2B16 (601-3R Variant) and 2 more. Effective Aug 18, 2026
- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [AD 2026-07-01](https://openairdocs.org/ad/2026-07-01): Landing gear · Bombardier CL-600-1A11 (600), CL-600-2A12 (601), CL-600-2B16 (601-3A Variant) and 2 more. Effective May 8, 2026
- [AD 2025-24-11](https://openairdocs.org/ad/2025-24-11): Auxiliary Power · Bombardier CL-600-2A12 (601), CL-600-2B16 (601-3A Variant), CL-600-2B16 (601-3R Variant) and 1 more. Effective Jan 16, 2026
- [AD 2025-22-04](https://openairdocs.org/ad/2025-22-04): Flight Controls · Bombardier CL-600-2B16 (604 Variant). Effective Dec 23, 2025
- [AD 2025-07-09](https://openairdocs.org/ad/2025-07-09): Oxygen · Bombardier CL-600-1A11 (600), CL-600-2A12 (601), CL-600-2B16 (601-3A Variant) and 2 more. Effective Jul 2, 2025
- [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025
- [AD 2024-13-01](https://openairdocs.org/ad/2024-13-01): Fuel · Bombardier CL-600-2B16 (604 Variant). Effective Aug 16, 2024
- [AD 2024-07-10](https://openairdocs.org/ad/2024-07-10): Landing gear · Bombardier CL-600-2B16 (604 Variant). Effective Jun 6, 2024
- [AD 2024-03-06](https://openairdocs.org/ad/2024-03-06): Landing gear · Bombardier CL-600-2B16 (CL-604). Effective Apr 16, 2024
- [AD 2023-26-08](https://openairdocs.org/ad/2023-26-08): Flight Controls · Bombardier CL-600-2B16 (CL-604). Effective Mar 20, 2024
- [AD 2023-24-05](https://openairdocs.org/ad/2023-24-05): Oxygen System · Bombardier CL-600-2B16 (CL-604). Effective Jan 22, 2024
- [AD 2023-22-16](https://openairdocs.org/ad/2023-22-16): Pneumatic · Bombardier Aerospace CL-600-2B16 (CL-604). Effective Jan 5, 2024
- [AD 2023-17-06](https://openairdocs.org/ad/2023-17-06): Flight Controls · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Oct 19, 2023
- [AD 2023-16-01](https://openairdocs.org/ad/2023-16-01): Oxygen · Bombardier CL-600-2B16 (CL-604) with STC ST02355NY. Effective Aug 23, 2023
- [AD 2023-07-04](https://openairdocs.org/ad/2023-07-04): Auto flight · Bombardier CL-600-2B16 (CL-604). Effective May 30, 2023
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2023-06-02](https://openairdocs.org/ad/2023-06-02): Equipment/furnishings · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective May 18, 2023
- [AD 2023-06-04](https://openairdocs.org/ad/2023-06-04): Oxygen System · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective May 18, 2023
- [AD 2023-25-13](https://openairdocs.org/ad/2023-25-13): Oxygen · Bombardier CL-600-2B16 (CL-604). Effective Feb 7, 2023
- [AD 2022-20-05](https://openairdocs.org/ad/2022-20-05): Flight Controls · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Nov 25, 2022
- [AD 2022-12-13](https://openairdocs.org/ad/2022-12-13): Auto flight · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 1 more. Effective Oct 19, 2022
- [AD 2022-15-08](https://openairdocs.org/ad/2022-15-08): Information systems · Airbus A318-111, A318-112, A319-111 and 49 more. Effective Aug 12, 2022
- [AD 2022-10-10](https://openairdocs.org/ad/2022-10-10): Ice and Rain Protection · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Jul 5, 2022
- [AD 2022-09-01](https://openairdocs.org/ad/2022-09-01): Ice and Rain Protection, Potable Water System · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective May 31, 2022
- [AD 2021-26-23](https://openairdocs.org/ad/2021-26-23): Fuel · Bombardier CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and CL-600-2B16 (CL-604). Effective Feb 25, 2022
- [AD 2021-25-13](https://openairdocs.org/ad/2021-25-13): Time Limits/Maintenance Checks · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Feb 15, 2022
- [AD 2021-13-12](https://openairdocs.org/ad/2021-13-12): Time Limits/Maintenance Checks · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Sep 9, 2021
- [AD 2021-07-06](https://openairdocs.org/ad/2021-07-06): Navigation · Bombardier CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and CL-600-2B16 (CL-604). Effective May 11, 2021
- [AD 2021-05-17](https://openairdocs.org/ad/2021-05-17): NAVIGATION SYSTEM · Rockwell Collins FDSA-6500, CL-600-2B16 (CL-604), 525B and 7 more. Effective Apr 29, 2021
- [AD 2019-21-03](https://openairdocs.org/ad/2019-21-03): Navigation · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 1 more. Effective Dec 18, 2019
- [AD 2019-15-01](https://openairdocs.org/ad/2019-15-01): Main landing gear · Bombardier CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and CL-600-2B16 (CL-604). Effective Sep 19, 2019
- [AD 2019-10-01](https://openairdocs.org/ad/2019-10-01): Wings · Bombardier CL-600-2A12 (CL-601). Effective Jul 18, 2019
- [AD 2019-08-08](https://openairdocs.org/ad/2019-08-08): Hydraulic power · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Jun 27, 2019
- [AD 2018-20-21](https://openairdocs.org/ad/2018-20-21): Lights · Bombardier CL-600-2B16 (CL-604). Effective Nov 20, 2018
- [AD 2018-17-02](https://openairdocs.org/ad/2018-17-02): Flight controls · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Sep 19, 2018
- [AD 2018-09-17](https://openairdocs.org/ad/2018-09-17): Flight Controls · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Jun 25, 2018
- [AD 2018-06-06](https://openairdocs.org/ad/2018-06-06): Autopilot System · Bombardier CL-600-2B16 (CL-604). Effective Apr 19, 2018
- [AD 2017-23-09](https://openairdocs.org/ad/2017-23-09): Periodic inspections · Bombardier CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and 1 more. Effective Dec 26, 2017
- [AD 2017-22-11](https://openairdocs.org/ad/2017-22-11): Navigation · Bombardier CL-600-2B16 (CL-604). Effective Dec 20, 2017
- [AD 2017-22-14](https://openairdocs.org/ad/2017-22-14): Navigation · Bombardier BD-100-1A10 (Challenger 300), BD-500-1A10, BD-500-1A11 and 13 more. Effective Dec 20, 2017
- [AD 2017-20-11](https://openairdocs.org/ad/2017-20-11): Fuselage · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 1 more. Effective Nov 15, 2017
- [AD 2017-19-06](https://openairdocs.org/ad/2017-19-06): Wings · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 2 more. Effective Oct 27, 2017
- [AD 2017-16-13](https://openairdocs.org/ad/2017-16-13): Oxygen · Bombardier CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and CL-600-2B16 (CL-604). Effective Sep 25, 2017
- [AD 2017-13-09](https://openairdocs.org/ad/2017-13-09): Engine Exhaust · Bombardier CL-600-1A11 (CL-600). Effective Aug 3, 2017
- [AD 2016-20-09](https://openairdocs.org/ad/2016-20-09): Fuel · Bombardier CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and 1 more. Effective Jan 9, 2017
- [AD 2016-21-06](https://openairdocs.org/ad/2016-21-06): Wings · Bombardier CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A) and 1 more. Effective Dec 19, 2016
- [AD 2016-13-09](https://openairdocs.org/ad/2016-13-09): Flight Controls · Bombardier CL-600-2B16 (CL-604). Effective Aug 16, 2016
- [AD 2016-10-10](https://openairdocs.org/ad/2016-10-10): Fuel · Bombardier CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and CL-600-2B16 (CL-604). Effective Jun 23, 2016
- [AD 2016-08-15](https://openairdocs.org/ad/2016-08-15): Wings · Bombardier CL-600-2B16 (CL-601-3A), CL-600-2B16 (CL-601-3R) and CL-600-2B16 (CL-604). Effective Jun 6, 2016

All 168: https://openairdocs.org/tcds/A21EA/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Bombardier CL-600-2B16](https://openairdocs.org/model/bombardier-cl-600-2b16): 388 aircraft (registry code 1390009)
- [Canadair CL-600-2B16](https://openairdocs.org/model/canadair-cl-600-2b16): 134 aircraft (registry code 1900305)
- [Bombardier CL-600-2B16(CL-604)](https://openairdocs.org/model/bombardier-cl-600-2b16-cl-604): 42 aircraft (registry code 1900314)
- [Canadair CL-600-2A12](https://openairdocs.org/model/canadair-cl-600-2a12): 19 aircraft (registry code 1900304)
- [Canadair CL-600-1A11](https://openairdocs.org/model/canadair-cl-600-1a11): 5 aircraft (registry code 1900308)
- [Canadair CL600-2B16(CL601-3A)](https://openairdocs.org/model/canadair-cl600-2b16-cl601-3a): 3 aircraft (registry code 1900306)
- [Canadair CL600-1A11](https://openairdocs.org/model/canadair-cl600-1a11): 2 aircraft (registry code 1900316)
- [Bombardier Aerospace CL-600-2B16 (CL-604)](https://openairdocs.org/model/bombardier-aerospace-cl-600-2b16-cl-604): 1 aircraft (registry code 1390065)
- [Bombardier CL-600-2A12](https://openairdocs.org/model/bombardier-cl-600-2a12): 1 aircraft (registry code 1390018)
- [Bombardier CL600-2B16 (CL601-3A](https://openairdocs.org/model/bombardier-cl600-2b16-cl601-3a): 1 aircraft (registry code 1390024)
- [Canadair Bombardier CL-600-2B16](https://openairdocs.org/model/canadair-bombardier-cl-600-2b16): 1 aircraft (registry code 1900307)
- [Canadair CL-600-2A12(CL-601)](https://openairdocs.org/model/canadair-cl-600-2a12-cl-601): 1 aircraft (registry code 1900312)
- [Bombardier CL-600-2B16 (CL-605)](https://openairdocs.org/model/bombardier-cl-600-2b16-cl-605): 0 aircraft (registry code 1390026)

## STCs approved under this data sheet (1,520, first 50)

- [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc
- [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center
- [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems
- [STC ST12422IB](https://openairdocs.org/stc/ST12422IB): Water System Modifications. Bombardier Inc.
- [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc.
- [STC ST04735NY](https://openairdocs.org/stc/ST04735NY): Installation of LAI Windshields. Lee Aerospace Inc.
- [STC ST12339IB](https://openairdocs.org/stc/ST12339IB): Installation of Cabin CMS Upgrade, Seat Replacement, and Miscellaneous Interior Modifications. Flying Colours Corp.
- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC ST12328IB](https://openairdocs.org/stc/ST12328IB): Demonstration of TPED Tolerance. Bombardier Inc.
- [STC ST11216DS](https://openairdocs.org/stc/ST11216DS): Installation of automatic dependent surveillance-broadcast (ADS-B) out on Part 25 aircraft. BHE & Associates Ltd.
- [STC ST11291DS](https://openairdocs.org/stc/ST11291DS): Installation of new Bulkhead Display Units (BDUX) monitors. BHE & Associates.
- [STC ST11292DS](https://openairdocs.org/stc/ST11292DS): Installation of a new wireless access point (WAP-6000) and local antenna unit (ANT-200). BHE & Associates Ltd.
- [STC ST12196IB](https://openairdocs.org/stc/ST12196IB): Installation of the Gogo Galileo HDX High-Speed Internet System. Sky Service F.B.O. Inc.
- [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc.
- [STC ST04115NY](https://openairdocs.org/stc/ST04115NY): Installation of Mission Equipment. Delta Engineering Corporation
- [STC ST01642NY](https://openairdocs.org/stc/ST01642NY): Installation of Safe Flight P/N C88627-1 throttle quadrant in place of P/N FE341000000 Throttle Quadrant. Safe Flight Instrument LLC
- [STC ST03292CH](https://openairdocs.org/stc/ST03292CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development, Inc.
- [STC ST10973SC](https://openairdocs.org/stc/ST10973SC): Activation of a high power cabin telecommunication router. BHE & Associates LTD
- [STC ST01408LA](https://openairdocs.org/stc/ST01408LA): Installation of a reinforced cockpit door.. Safran Cabin Inc.
- [STC ST01415LA](https://openairdocs.org/stc/ST01415LA): Installation of a reinforced cockpit door.. Safran Cabin Inc.
- [STC ST01621LA](https://openairdocs.org/stc/ST01621LA): Installation of C&D Interiors Overhead Stowage Bin Installation, PSU Panel Installation, Ceiling Panel Installation, L/H Wardrobe Installation, Underbin Stowage Unit Installation, Passenger Seat & Track Cover.. Safran Cabin Inc.
- [STC ST01849LA](https://openairdocs.org/stc/ST01849LA): C&D Interiors Interior Installation. Safran Cabin Inc.
- [STC ST01985LA-D](https://openairdocs.org/stc/ST01985LA-D): Modification and installation of stowage bins, class dividers, ceiling panels, passenger seats, passenger service units and filler panels, seat track covers, passenger floor coverings, floor proximity lighting strips, and seat row placards.. Safran Cabin Inc.
- [STC ST01987LA-D](https://openairdocs.org/stc/ST01987LA-D): Interior Installations and Modifications.. Safran Cabin Inc.
- [STC ST01988LA-D](https://openairdocs.org/stc/ST01988LA-D): Interior Installations and Modifications.. Safran Cabin Inc.
- [STC ST01994LA-D](https://openairdocs.org/stc/ST01994LA-D): Installation of Decorative Material Replacement Modifications. Safran Cabin Inc.
- [STC ST01996LA-D](https://openairdocs.org/stc/ST01996LA-D): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST01999LA-D](https://openairdocs.org/stc/ST01999LA-D): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST02001LA-D](https://openairdocs.org/stc/ST02001LA-D): C&D Zodiac, Inc. Interior Installations and Modifications per C&D Zodiac, Inc., Index List No. E821, Revision A, dated November 11, 2011, or later FAA approved revisions.. Safran Cabin Inc.
- [STC ST02004LA](https://openairdocs.org/stc/ST02004LA): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST02005LA](https://openairdocs.org/stc/ST02005LA): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST02383LA](https://openairdocs.org/stc/ST02383LA): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST02396LA](https://openairdocs.org/stc/ST02396LA): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST02401LA](https://openairdocs.org/stc/ST02401LA): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST02562LA](https://openairdocs.org/stc/ST02562LA): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST01930WI](https://openairdocs.org/stc/ST01930WI): Installation of SmartSky Networks 4G System. L2 Aviation
- [STC ST00431WI-D](https://openairdocs.org/stc/ST00431WI-D): Installation of a Fairchild F-1000 Data Flight Data Recorder System.. KGB Aviation Solutions LLC
- [STC ST04201AT](https://openairdocs.org/stc/ST04201AT): Installation of the Avionics Innovations DMP500 PRAM (Pre-Recorded Announcement Machine). Chippewa Aerospace Inc
- [STC ST04371AT](https://openairdocs.org/stc/ST04371AT): Installation of a Second (No. 2) Rockwell Collins Flight Management System (and Optional GPS). Chippewa Aerospace Inc
- [STC SA6011NM](https://openairdocs.org/stc/SA6011NM): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace Inc.
- [STC SA02358LA](https://openairdocs.org/stc/SA02358LA): Installation of Main Landing Gear Wire Harness Assemblies. NIACC Avitech Technologies
- [STC ST11293DS](https://openairdocs.org/stc/ST11293DS): The installation of an AirSync flight data monitoring system. BHE & Associates Ltd.
- [STC ST209CH](https://openairdocs.org/stc/ST209CH): Installation of a model TCAS 791 TCAS I.. Acron Aviation Inc.
- [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc.
- [STC ST09940AC](https://openairdocs.org/stc/ST09940AC): Installation of an Aspire 400 Satcom System. L2 Aviation
- [STC ST01117DE](https://openairdocs.org/stc/ST01117DE): Installation of the Gogo ATG C1.. Peregrine
- [STC ST01698NY](https://openairdocs.org/stc/ST01698NY): Installation of Safe Flight Autopower (Autothrottle) System.. Safe Flight Instrument LLC
- [STC ST11850CH](https://openairdocs.org/stc/ST11850CH): Installation of SpaceX Starlink Aviation System. Nextant Aerospace
- [STC ST03810NY](https://openairdocs.org/stc/ST03810NY): Installation of the INGENIO Cockpit Tripod Electronic Flight Bag (EFB) Mount. Ingenio Aerospace Inc.
- [STC ST00690DE](https://openairdocs.org/stc/ST00690DE): Installation of Electronic Cable Specialists, ECS EZMount Arm of Bombardier CL-600 Series Aircraft.. Amphenol Cable and Interconnect Technologies Inc.

All 1,520: https://openairdocs.org/tcds/A21EA/stcs.md

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