TCDS A21EA

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 Page N o . R e v N o . P a g e N o . R e v N o . 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: