TCDS 1A20

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 6 - - - - - - - - - - - - - - - - 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A20 Revision 6 Bombardier CL-44D4 CL-44J March 24, 1998 TYPE CERTIFICATE DATA SHEET NO.1A20 This data sheet which is a part of type certificate No. 1A20 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. P.O. Box 6087, Station Centre-ville Montreal, Quebec, Canada H3C 3G9 I - Model CL-44D4 (Transport Category), Approved 24 May 1961 by the FAA and 23 May 1961 by the Canadian Department of Transport (DOT). Engines 4 Rolls-Royce Tyne 515 (Turboprop) Reduction gearing 0.064:1 Fuel For approved fuels additives and deviations to fuel specifications see DOT approved Airplane Flight Manual. Oil (Engine & Gearbox) Esso Aviation Turbo oil 35 Enco Turbo oil 35 Humble Turbo oil 35 Penola Turbo oil 35 Castrol 98 (Constant Speed Drive) MIL-L-7808 Engine limits Static Sea Level Ratings Max. TGT °C when Shaft Jet Max. Engine Max. TGT Rolls Royce Modi- Horse- Thrust Speed °C fication No. 1426 power (lb.) (r.p.m.) is incorporated. LP HP Takeoff (5 min.) 5095 1065 15250 18150 735* 665** Max. continuous 4685 940 14500 17950 715* 645** Max. transient for starting (5 sec.) 800 725 Max. Reverse Pitch: Braking (1 min.) 13250 16600 685* 620 * These limits are applicable at sea level. Above sea level, the limits increase by 2 1/2°C per 1000 ft. altitude. ** TGT limits are applicable at sea level. Above sea level the limits increase by 2 1/2°C per 1000 ft. altitude if fuel trimmer control is used, or by 1 1/2°C per 1000 ft. if fuel control is used. il Inlet Temperature Minimum for starting -30°C Minimum for opening up -15°C Maximum allowable: With Castrol 98 105°C With any other approved oil 100°C 1A20 2 Engine limits (cont'd) Oil Pressure Limits: Normal (at 90°C): 40-65 p.s.i. at 14,500 LP r.p.m. Minimum (at 100°C): 40 p.s.i. at 14,500 LP r.p.m. Minimum to complete flight: 38 p.s.i. at 11,000 LP r.p.m. and above, 30 p.s.i. at all r.p.m. below 11,000 LP r.p.m. Air Turbine Starter (At ground air connection) Maximum pressure .34 p.s.i.g. Maximum temperature 270°C Minimum temperature 20°C Normal Operating Time 30 Sec. Maximum Operating Time Limit 40 Sec. Starter Inlet Temperature and Corresponding Pressure Limits: Maximum 310°C (26 p.s.i.g.) Intermediate 150°C (32 p.s.i.g.) Minimum -30°C (32 p.s.i.g.) Propeller and 4 DeHavilland propellers Model PD 228/476/2, four blades propeller limits Diameter: 16 ft. (+0.14 in., -1.00 in.) Pitch settings at Station 72.0 in.: Maximum reverse - 17° Ground Idle - 7° Flight Idle +12° Feather +83° Airspeed limits (CAS) Maximum Operating Limitation Vmo/Mmo Altitude in 10,000 ft. S.L. to 10 10 to 15 15 to 20 20 to 25 25 to 30 Zero Fuel Weight m.p.h. (knots) Mach 155,000 288 (250) 290 (252) 292 (254) 296 (257) .62 to (See Note 7) 160,000 153,000 290 (252) 292 (254) 294 (256) 298 (259) .62 151,000 293 (255) 296 (257) 298 (259) 301 (262) .62 149,000 296 (257) 298 (259) 300 (261) 304 (264) .62 147,000 299 (260) 301 (262) 304 (264) 307 (267) .62 145,000 301 (262) 304 (264) 306 (266) 309 (269) .62 143,000 305 (265) 307 (267) 309 (269) 313 (272) .62 141,000 307 (267) 309 (269) 312 (271) 315 (274) .62 139,000 311 (270) 313 (272) 315 (274) 319 (277) .62 137,000 313 (272) 315 (274) 317 (276) 321 (279) .62 135,000 316 (275) 319 (277) 321 (279) 324 (282) .62 or less Vfe (Flaps extended 5°) 264 m.p.h. (230 knots) (Mach .50) Vfe (Flaps extended 15°) 264 m.p.h. (230 knots) Vfe (Flaps extended 30°) 228 m.p.h. (198 knots) Vfe (Flaps extended 45°) 172 m.p.h. (150 knots) Va (Maneuvering) 241 m.p.h. (210 knots) Vlo (Landing gear operating) 207 m.p.h. (180 knots) Vle (Landing gear extended) 211 m.p.h. (184 knots) Vmca (Minimum control, air) S.L. ISA 118 m.p.h. (103 knots) Maximum landing light operating speed 190 m.p.h. (165 knots) Maximum landing light extended speed 241 m.p.h. (210 knots) Maximum spoiler operating speed 230 m.p.h. (200 knots) Maximum fuel dump chute extended speed 241 m.p.h. (210 knots) 3 1A20 C.G. range Center-of gravity limits, with landing gear extended, are shown in the following tables; straight line variations exist between the quoted values. Gear retraction moment is +237,609 in.-lb.; retraction of the gear moves the C.G. aft approximately 1% MAC. C.G. Envelope for Aircraft with Basic Configuration, Zero Fuel Weight of 155,000 lb. or less. CENTER OF GRAVITY - PERCENT M.A.C. 95 120 127.4 135 145 155 205 210 688.9 690.4 692.7 699.1 700.5 702.0 717.4 725.5 12.0 17.3 18.0 18.8 26.8 31.012.8 14.0 Zero Fuel Wt. 145,000 lb. to 155,000 lb. Zero Fuel Wt. 135,000 lb. to 145,000 lb. Zero Fuel Wt. 135,000 lb. or less WEIGHT 1,000 lb. DISTANCE FROM C.G. DATUM - INCHES C.G. Envelope for Aircraft with Modified Swing Tail Compartment, Zero Fuel Weight of 155,000 lbs. or less CENTER OF GRAVITY - PERCENT M.A.C. 95 127.5 135 145 155 205 210 717.4 725.5 26.8 31.0 Zero Fuel Wt. 145,000 lb. to 155,000 lb. Zero Fuel Wt. 135,000 lb. to 145,000 lb. Zero Fuel Wt. 135,000 lb. or less WEIGHT 1,000 lb. DISTANCE FROM C.G. DATUM - INCHES 703.5 709.7 710.5 710.9 19.6 22.8 23.3 23.4 1A20 4 C.G. Envelope for Aircraft with Basic Configuration of Modified Swing Tail Compartment, Zero Fuel Weight Between 155,000 lb. and 160,000 lb. 689.7 95 120 140 160 185 205 210 696.7 699.7 704.2 711.7 717.7 723.6 725.1 12.4 14.0 17.6 19.9 23.8 27.0 30.0 30.8 DISTANCE FROM C.G. DATUM - INCHES CENTER OF GRAVITY - PERCENT M.A.C. WEIGHT 1,000 LB. FORWARD LIMIT: (a) Basic Interior Configuration: Gross Weight Limits Zero Fuel 95,000 14.0% MAC (Sta. 692.7) Weight 120,000 14.0% MAC (Sta. 692.7) 135,000 lb. 135,000 12.8% MAC (Sta. 690.4) or less 145,000 13.6% MAC (Sta. 692.0) 155,000 14.4% MAC (Sta. 693.5) 165,000 15.3% MAC (Sta. 695.2) 205,000 18.4% MAC (Sta. 701.2) 210,000 (see NOTE 8) 18.8% MAC (Sta. 702.0) Zero Fuel 135,000 12.8% MAC (Sta. 690.4) Weight 145,000 12.0% MAC (Sta. 688.9) 135,000 lb. 155,000 13.0% MAC (Sta. 690.8) to 165,000 13.9% MAC (Sta. 692.5) 145,000 lb. 205,000 17.6% MAC (Sta. 699.7) 210,000 (see NOTE 8) 18.0% MAC (Sta. 700.5) Zero Fuel 145,000 12.0% MAC (Sta. 688.9) Weight 155,000 12.0% MAC (Sta. 688.9) 145,000 lb. 165,000 13.0% MAC (Sta. 690.8) to 205,000 16.8% MAC (Sta. 698.1) 155,000 lb. 210,000 (see NOTE 8) 17.3% MAC (Sta. 699.1) Zero Fuel 155,000 12.4% MAC (Sta. 689.7) Weight 160,000 12.4% MAC (Sta. 689.7) 155,000 lb. 205,000 17.1% MAC (Sta. 698.7) to 210,000 17.6% MAC (Sta. 699.7) 160,000 (see NOTE 7) 5 1A20 (b) Modified Swing Tail Compartment for aircraft incorporating Canadair Service bulletin CL-44D4-245, and CL-44D4-303. The following limits apply when the swing-tail cargo load is in excess of 3,000 lb. on airplanes with the standard swing-tail compartment configuration or in excess of 1,000 lb. on airplanes with the swing-tail compartment modified to incorporate the dropped floor with passenger service facilities. Gross Weight Limits Zero Fuel 95,000 19.6% MAC (Sta. 703.5) Weight 120,000 19.6% MAC (Sta. 703.5) 135,000 lb. 135,000 19.6% MAC (Sta. 703.5) or less 145,000 20.2% MAC (Sta. 704.7) 155,000 20.6% MAC (Sta. 705.9) 165,000 21.2% MAC (Sta. 706.9) 205,000 23.2% MAC (Sta. 710.5) 210,000 (see NOTE 8) 23.4% MAC (Sta. 710.9) Zero Fuel 135,000 19.6% MAC (Sta. 703.5) Weight 145,000 19.6% MAC (Sta. 703.5) 135,000 lb. 155,000 20.2% MAC (Sta. 704.7) to 165,000 20.8% MAC (Sta. 705.8) 145,000 lb. 205,000 23.0% MAC (Sta. 710.1) 210,000 (see NOTE 8) 23.3% MAC (Sta. 710.5) Zero Fuel 145,000 19.6% MAC (Sta. 703.5) Weight 155,000 19.6% MAC (Sta. 703.5) 145,000 lb. 165,000 20.2% MAC (Sta. 704.7) to 205,000 22.5% MAC (Sta. 709.1) 155,000 lb. 210,000 (see NOTE 8) 22.8% MAC (Sta. 709.7) Zero Fuel 155,000 19.9% MAC (Sta. 704.2) Weight 160,000 19.9% MAC (Sta. 704.2) 155,000 lb. 205,000 23.4% MAC (Sta. 710.9) to 210,000 23.8% MAC (Sta. 711.7) 160,000 (see NOTE 7) AFT LIMIT: (a) Aircraft operating with Zero Fuel Weight up to 155,000 lb. Gross Weight Limits 95,000 26.8% MAC (Sta. 717.4) 127,400 31.0% MAC (Sta. 725.5) 205,000 31.0% MAC (Sta. 725.5) 210,000 (See NOTE 8) 31.0% MAC (Sta. 725.5) (b) Aircraft operating with Zero Fuel Weight between 155,000 lb. and 160,000 lb. (See NOTE 7). Gross Weight Limits 95,000 27.0% MAC (Sta. 717.7) 120,000 30.0% MAC (Sta. 723.6) 185,000 30.8% MAC (Sta. 725.1) 205,000 30.8% MAC (STA. 725.1) 210,000 30.8% MAC (Sta. 725.1) Datum The datum for the center-of-gravity limits is at Station 0, which is 633.0 inches forward of a jig point located on the underside of the fuselage immediately forward of the front spar on the aircraft center line. The jig point is a Philips head screw in the skin joint. 1A20 6 Mean Aerodynamic Chord 192.86 inches (L.E. of M.A.C. is 665.72 inches aft of Station 0). (MAC) Maximum weight Taxi 206,000 lb. 211,000 lb. (See NOTE 8) Take-off 205,000 lb. 210,000 lb. (see NOTE 8) Landing 165,000 lb. Maximum Zero Fuel 155,000 lb. 160,000 lb. (See NOTE 7) All weights in excess of zero fuel weight must consist of usable fuel. See Airspeed Limits for variation of limit airspeeds with zero-fuel weight. Minimum crew 3: Pilot, Co-pilot and System Operator. Maximum passengers Certification of original type design for cargo only. Maximum Supplemental Type Certificate configuration approved prior to FAR 25.2 is for 178 passengers. Maximum cargo Permissible cargo load and distribution varies with interior configuration. See NOTE 2 for permissible loading for approved configuration. See NOTE 4(a) for cargo compartment classification. Fuel capacity Total gal. Usable gal. Imp. U.S. Imp. U.S. ARM 2 outboard main tanks 3810 4575 3760 4516 734.5 2 inboard main tanks 3802 4566 3736 4486 709.0 c/s auxiliary tank 1636 1965 1626 1954 695.4 2 outboard auxiliary 874 1050 870 1044 765.5 Total 10122 12156 9992 12000 See CL-44D4 NOTE 1(c) for "Systems fuel" data. Oil capacity Total pt. Usable pt. Imp. U.S. lb. Imp. U.S. lb. ARM 2 outboard engines 124 148.8 150 40 48.0 48.4 (555.0) 2 inboard engines 124 148.8 150 40 48.0 48.4 (513.0) See CL-44D4 NOTE 1(d) for "System oil" data. Maximum approved 30,000 ft. if suitable supplementary oxygen dispensing units are provided for operating altitude flight altitudes above 10,000 ft. If no oxygen dispensing units are provided, maximum operating flight altitude is 10,000 ft. Other operating This aircraft must be operated in accordance with the limitations listed in the limitations Department of Transport Approved Airplane Flight Manual. Control surface movements Elevators UP 30° Down 15° (from neutral) L.H. Elevator servo tabs UP 14° Down 26° (rig 1° down) R.H. Elevator servo tabs UP 16° Down 24° (rig 1° up) Elevator trim tabs UP 17-1/2° Down 22-1/2° (from neutral) Rudder Right 16° Left 16° (from neutral) Rudder servo tabs Right 18° Left 18° (from neutral) Rudder connected tabs UP 22° Down 18° (rig 2° up) Aileron UP 21° Down 15° (from neutral) Aileron servo tabs UP 25° Down 21° (rig 2° up) Flaps UP 0° Down 45° Spoilers UP 48° Down 0° Tab angles measured with control surfaces neutral. 7 1A20 Serial Nos. eligible 9, 14 to 39. The Canadian Department of Transport Certificate of Airworthiness for export endorsed as noted under "Import Eligibility" must be submitted for each individual aircraft for which application for certification is made. Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian Department of Transport "Certificate of Airworthiness for Export" signed by the Minister of Transport or his authorized representative. This form must contain the following statement: This certifies that the aircraft described below has been manufactured in conformity with data forming the basis for D.O.T. Type Approval No. A55 (FAA Type Certificate No. 1A20)." Certification basis CAR 4b dated 31 December 1953; amendments 4b-1 through 4b-10; amendment 4b-11 with the exception of items 6, 9, 17, 26, 27, 28, 33 and 44; and special regulation SR-422B. Type Certificate No. 1A20 issued 24 May 1961. Date of Application for Type Certificate 1 August 1957. Compliance with the following optional requirements has been established: Ditching, CAR 4b.361--Structural approval only-- eligible for ditching approval when the required ditching equipment and storage provisions are approved. Ice Protection, CAR 4b.640. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification including DOT approved Flight Manual (Canadair Service Publication No. 153 latest approved revision for the CL44D4). Canadair Report No. RAL-44-102 latest revised "Equipment Qualification List for CL44D4", lists all required equipment that must be installed as well as optional equipment installations approved by DOT. In addition the following items of equipment are required: Stall warning devise as follows: Drawing No. Part P/N 44-53055 Transducer 44-50750-8 44-53013 Potentiometer 44-50750-10 44A-51410 Stick Shaker 44-50750-2 44D-51061 Computer 44-50750-162 II - Model CL-44J (Transport Category), Approved 28 January 1972 by the FAA and 8 July 1970 by the Canadian Department of Transport (DOT). Engines 4 Rolls-Royce Tyne 515 (Turboprop) Reduction gearing 0.064:1 Fuel For approved fuels additives and deviations to fuel specifications see DOT approved Airplane Flight Manual Oil (Engine & Gearbox) Esso Aviation Turbo oil 35 Enco Turbo oil 35 Humble Turbo oil 35 Penola Turbo oil 35 Castrol 98 (Constant Speed Drive) MIL-L-7808 1A20 8 Engine limits Static Sea Level Ratings Max. TGT °C when Shaft Jet Max. Engine Max. TGT Rolls Royce Modi- Horse- Thrust Speed °C fication No. 1426 power (lb.) (r.p.m.) is incorporated. LP HP Takeoff (5 min.) 5095 1065 15250 18150 735* 665** Max. continuous 4685 940 14500 17950 715* 645** Max. transient for starting (5 sec.) 800 725 Max. Reverse Pitch: Braking (1 min.) 13250 16600 685* 620 *These limits are applicable at sea level. Above sea level, the limits increase by 2 1/2°C per 1000 ft. altitude. **TGT limits are applicable at sea level. Above sea level the limits increase by 2 1/2°C per 1000 ft. altitude if fuel trimmer control is used, or by 1 1/2°C per 1000 ft. if fuel control is used. Oil Inlet Temperature Minimum for starting - 30°C Minimum for opening up -15°C Maximum allowable: With Castrol 98 105°C With any other approved oil 100°C Oil Pressure Limits: Normal (at 90°C): 40-65 p.s.i. at 14,500 LP r.p.m. Minimum (at 100°C): 40 p.s.i. at 14,500 LP r.p.m. Minimum to complete flight: 38 p.s.i. at 11,000 LP r.p.m. and above, 30 p.s.i. at all r.p.m. below 11,000 r.p.m. Air Turbine Starter (At ground air connection) Maximum pressure .34 p.s.i.g. Maximum temperature 270°C Minimum temperature 20°C Normal Operating Time 30 Sec. Maximum Operating Time Limit 40 Sec. Starter Inlet Temperature and Corresponding Pressure Limits: Maximum 310°C (26 p.s.i.g.) Intermediate 150°C (32 p.s.i.g.) Minimum -30°C (32 p.s.i.g.) Propeller and 4 DeHavilland propellers Model PD 228/476/2, four blades propeller limits Diameter: 16 ft. (+0.14 in., -1.00 in.) Pitch settings at Station 72.0 in.: Maximum reverse -17° Ground Idle - 7° Flight Idle +12° Feather +83° 9 1A20 Airspeed limits Maximum Operating Limitation Vmo/Mmo (CAS) (a) With Landing Fuel Weight of 25,000 lb. or less. Altitude in 10,000 ft. S.L. to 10 10 to 15 15 to 20 20 to 25 Lesser of Vmo Mmo Zero Fuel Weight m.p.h. (knots) Mach 160,000 288 (250) 290 (252) 292 (254) 296 (257) (.62) (b) With Landing Fuel Weight of 25,000 lbs. or less and Canadair Service Bulletin CL44-476 Incorporated. Altitude in 10,000 ft. S.L. to 10 10 to 15 15 to 20 20 to 25 Lesser of Vmo Mmo Zero Fuel Weight m.p.h. (knots) Mach 160,000 288 (250) 290 (252) 292 (254) 296 (257) (.62) 158,000 290 (252) 292 (254) 295 (256) 298 (259) (.62) 155,000 293 (255) 296 (257) 298 (259) 301 (262) (.62) 153,000 296 (257) 298 (259) 300 (261) 304 (264) (.62) 150,000 299 (260) 301 (262) 304 (264) 307 (267) (.62) 147,000 303 (263) 305 (265) 307 (267) 311 (270) (.62) 145,000 305 (265) 307 (267) 309 (269) 313 (272) (.62) 143,000 307 (267) 309 (269) 312 (271) 315 (274) (.62) 140,000 311 (270) 313 (272) 315 (274) 319 (277) (.62) 138,000 313 (272) 315 (274) 318 (276) 321 (279) (.62) 135,000 316 (275) 319 (277) 321 (279) 324 (282) (.62) or less (c) With landing fuel weight between 25,000 lbs. and 30,000 lbs. (with Canadair SB CL44-477 Incorporated). Altitude in 10,000 ft. S.L. to 10 10 to 15 15 to 20 20 to 25 Lesser of Vmo Mmo Zero Fuel Weight m.p.h. (knots) Mach 160,000 288 (250) 290 (252) 292 (254) 296 (257) (.62) 155,000 288 (250) 290 (252) 292 (254) 296 (257) (.62) 153,000 290 (252) 292 (254) 295 (256) 298 (259) (.62) 150,000 293 (255) 296 (257) 298 (259) 301 (262) (.62) 147,000 297 (258) 299 (260) 301 (262) 305 (265) (.62) 145,000 299 (260) 301 (262) 304 (264) 307 (267) (.62) 143,000 301 (262) 304 (264) 306 (266) 309 (269) (.62) 140,000 305 (265) 307 (267) 309 (269) 313 (272) (.62) 138,000 307 (267) 309 (269) 312 (271) 315 (274) (.62) 135,000 311 (270) 313 (272) 315 (274) 319 (277) (.62) Vfe (Flaps extended 5°) 264 m.p.h. (230 knots) (Mach .50) Vfe (Flaps extended 15°) 264 m.p.h. (230 knots) Vfe (Flaps extended 30°) 228 m.p.h. (198 knots) Vfe (Flaps extended 45°) 172 m.p.h. (150 knots) Va (Maneuvering) 241 m.p.h. (210 knots) Vlo (Landing gear operating) 207 m.p.h. (180 knots) Vle (Landing gear extended) 211 m.p.h. (184 knots) Vmca (Minimum control, air) S.L. ISA 118 m.p.h. (103 knots) Maximum landing light operating speed 190 m.p.h. (165 knots) Maximum landing light extended speed 241 m.p.h. (210 knots) Maximum spoiler operating speed 230 m.p.h. (200 knots) Maximum fuel dump chute extended speed 241 m.p.h. (210 knots) 1A20 10 C.G. range Center-of gravity limits, with landing gear extended, are shown in the following tables; straight line variations exist between the quoted values. Gear retraction moment is +237,609 in.-lb.; retraction of the gear moves the C.G. aft approximately 1% MAC. C.G. Envelope for CL-44J Cargo Configuration (See NOTE 4(b)) CENTER OF GRAVITY - % M.A.C. 95 120 135 145 203 210 809.9 813.7 819.5 821.5 823.5 832.5 844.6 12.0 17.0 18.0 19.0 30.814.0 Zero Fuel Wt. 160,000 lb. Zero Fuel Wt. 145,000 lb. Zero Fuel Wt. 135,000 lb. W E IG H T 1 ,0 0 0 lb . DISTANCE FROM C.G. DATUM - INCHES 160 185 165 175 23.5 30.0 846.1 FORWARD LIMIT: (Geardown) Cargo Configuration (see Note 4 (b) Gross Weight Limits Zero Fuel 95,000 14.0% MAC (Sta. 813.7) Weight 120,000 14.0% MAC (Sta. 813.7) 135,000 lb. 135,000 12.8% MAC (Sta. 811.4) or less 145,000 13.7% MAC (Sta. 813.1) 160,000 15.1% MAC (Sta. 815.8) 203,000 19.0% MAC (Sta. 823.5) Zero Fuel 135,000 12.8% MAC (Sta. 811.4) Weight 145,000 12.0% MAC (Sta. 809.9) 135,000 lb. 160,000 13.4% MAC (Sta. 812.5) to 203,000 17.4% MAC (Sta. 820.4) 145,000 lb. 210,000 18.0% MAC (Sta. 821.5) Zero Fuel 145,000 12.0% MAC (Sta. 809.9) Weight 160,000 12.0% MAC (Sta. 809.9) 145,000 lb. 203,000 16.4% MAC (Sta. 818.5) to 210,000 17.0% MAC (Sta. 819.7) 160,000 lb. 210,000 AFT LIMIT (Gear Down) Cargo Configuration (See Note 4 (b).) Zero Fuel 95,000 23.5% MAC (Sta. 832.5) Weight 145,000 30.0% MAC (Sta. 844.6) 135,000 lb. 165,000 30.8% MAC (Sta. 846.1) or less 175,000 30.8% MAC (Sta. 846.1 185,000 30.8% MAC (Sta. 846.1) 203,000 30.8% MAC (Sta. 846.1) 11 1A20 AFT LIMIT (Gear Down) (cont'd) Cargo Configuration (See Note 4 (b).) Zero Fuel 95,000 23.5% MAC (Sta. 832.5) Weight 145,000 30.0% MAC (Sta. 844.6) 135,000 lb. 165,000 30.0% MAC (Sta. 844.6) to 175,000 30.8% MAC (Sta. 846.1) 145,000 lb. 185,000 30.8% MAC (Sta. 846.1) Zero Fuel 95,000 23.5% MAC (Sta. 832.5) Weight 145,000 30.0% MAC (Sta. 844.6) 145,000 lb. 165,000 30.0% MAC (Sta. 844.6) to 175,000 30.0% MAC (Sta. 844.6) 160,000 lb. 185,000 30.8% MAC (Sta. 846.1) 203,000 30.8% MAC (Sta. 846.1) 210,000 30.8% MAC (Sta. 846.1) Datum The datum for the center-of-gravity limits is at Station 0, which is 754.00 inches forward of a jig point located on the underside of the fuselage immediately forward of the front spar on the aircraft center line. The jig point is a Philips head screw in the skin joint. Mean Aerodynamic Chord 192.86 inches (L.E. of M.A.C. is 786.72 inches aft of Station 0). (MAC) Maximum weight Taxi 211,000 lb. Take-off 210,000 lb. Landing 175,000 lb. Maximum Zero Fuel 160,000 lb. All weights in excess of zero fuel weight must consist of usable fuel. See Airspeed Limits for variation of limit airspeeds with zero-fuel weight. Minimum crew 3: Pilot, Co-pilot and System Operator. Maximum passengers Certification of original type design for cargo only. Maximum cargo Permissible cargo load and distribution varies with interior configuration. See NOTE 2 for permissible loading for approved configuration. See NOTE 4(b) for cargo compartment classification. Fuel capacity Total Gal. Usable Gal. Imp. U.S. Imp. U.S. ARM 2 outboard main tanks 3,810 4,575 3,760 4,516 855.5 2 inboard main tanks 3,802 4,566 3,736 4,486 830.0 2 outboard auxiliary 874 1,050 870 1,044 786.5 Total 8,486 10,191 8,366 10,046 See CL-44J NOTE 1(c) for "System fuel" data. Oil capacity Total Gal. Usable pt. Imp Pts. (lb.) Imp. Pts. (lb.) ARM 2 outboard engines 124 150 40 48.4 676.0 2 inboard engines 124 150 40 48.4 634.0 See CL-44J NOTE 1(d) for "System oil" data. Maximum approved 25,000 ft. if suitable supplementary oxygen dispensing units are provided for flight operating altitude altitudes above 10,000 ft. If no oxygen dispensing units are provided, maximum operating flight altitude is 10,000 ft. 1A20 12 Other operating This aircraft must be operated in accordance with the limitations listed in the limitations Department of Transport Approved Airplane Flight Manual. Serial Nos. eligible 9, 14 to 39. The Canadian Department of Transport Certificate of Airworthiness for export endorsed as noted under "Import Eligibility" must be submitted for each individual aircraft for which application for certification is made. Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian Department of Transport "Certificate of Airworthiness for Export" signed by the Minister of Transport or his authorized representative. This form must contain the following statement: This certifies that the aircraft described below has been manufactured in conformity with data forming the basis for D.O.T. Type Approval No. A55 (FAA Type Certificate No. 1A20)." Certification basis CAR 4b dated 31 December 1953; amendments 4b-1 through 4b-10; amendment 4b-11 with the exception of items 6, 9, 17, 26, 27, 28, 33 and 44; and special regulation SR- 422B. Type Certificate No. 1A20 issued 24 May 1961. Date of Application for Type Certificate 1 August 1957. Compliance with the following optional requirements has been established: Ditching, CAR 4b.361--Structural approval only-- eligible for ditching approval when the required ditching equipment and storage provisions are approved. Ice Protection, CAR 4b.640. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification including DOT approved Flight Manual (Canadair Service Publication No. 188, latest approved revision for the CL-44J). Canadair Report No. RAL-44-102 latest revised "Equipment Qualification List for CL-44J", lists all required equipment that must be installed as well as optional equipment installations approved by DOT. In addition the following items of equipment are required: Stall warning devise as follows: Drawing No. Part P/N 44-53055 Transducer 44-50750-8 44-53013 Potentiometer 44-50750-10 44A-51410 Stick Shaker 44-50750-2 44D-51061 Computer 44-50750-162 DATA PERTINENT TO ALL MODELS Leveling means Plumb bob suspension point in the roof of crew compartment over a target plate fixed in the floor, (Ref.: Sta. 198.3). Control surface movements Elevators UP 30° Down 15° (from neutral) L.H. Elevator servo tabs UP 14° Down 26° (rig 1° down) R.H. Elevator servo tabs UP 16° Down 24° (rig 1° up) Elevator trim tabs UP 17-1/2° Down 22-1/2° (from neutral) Rudder Right 16° Left 16° (from neutral) Rudder servo tabs Right 18° Left 18° (from neutral) Rudder connected tabs UP 22° Down 18° (rig 2° up) Aileron UP 21° Down 15° (from neutral) Aileron servo tabs UP 25° Down 21° (rig 2° up) Flaps UP 0° Down 45° Spoilers UP 48° Down 0°