TCDS A41EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. A41EU This data sheet which is part of Type Certificate No. A41EU 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: De Havilland Aircraft of Canada Limited 4100 Westwinds Drive NE Calgary, Alberta Canada T3J 4L2 Type Certificate Holder Record Viking Air Limited 1959 de Havilland Way Sidney, British Columbia Canada V8L 5V5 Viking Air Limited transferred A41EU to De Havilland Aircraft of Canada Limited August 1, 2024 Shorts Brothers PLC transferred A41EU to Viking Air Limited June on 28, 2019 Shorts Brothers Limited transferred A41EU to Shorts Brothers PLC on February 16, 1988 I. Model SD 3-30 Variant 200 (Transport Category Aircraft), approved June 18, 1976. (Model C23A, See Note 13 regarding Certification and Configuration Identification.) Engines. 2 Pratt & Whitney, Aircra ft of Canada Limited, PT6A-45A (See Note 10) Reduction Gear Ratio: 0.0568 : 1 or 2 Pratt & Whitney Aircraft of Canada Limited PT6A-45B Reduction Gear Ratio: 0.0568 : 1 or 2 Pratt & Whitney Aircraft of Canada Limited PT6A-45R Reduction Gear Ratio: 0.0568 : 1 Fuel. Specifications, latest issue may be used. American British ASTM D1655-70 MIL-T-5624L MIL-T83133A Jet A NONE Jet B NONE Jet A-1 Def. Standard 91-87 JP-4 Def. Standard 91-87 JP-5 Def. Standard 91-87 JP-8 Def. Standard 91-87 For fuel additives see NOTE 4. Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No. 15 12 12 12 12 12 9 12 12 9 12 12 11 12 13 13 11 12 12 Page No. 20 21 22 23 24 25 26 27 28 29 30 Rev. No. 12 13 12 12 9 9 9 9 11 12 12 A41EU Revision 15 De Havilland SD3-30 SD3-60 SD3-SHERPA SD3-60 SHERPA October 19, 2026 2 A41EU Engine Ratings. Static, sea level, Intern ational Standard Atmospheric conditions. No bleed extraction or accessory loads, compressor intake screen installed. RATINGS SHP JET THRUST AIR INLET TEMPERATURE PT6A-45A: Takeoff (dry) (5 min.) 1173 136 lb. to 46ºF Takeoff (wet) (5 min.) 1173 136 lb. to 69ºF Maximum Continuous 1020 127 lb. to 79ºF Reverse 900 - to 59ºF JET AIR RATINGS SHP THRUST INLET TEMPERATURE PT6A-45B: Takeoff (dry) (5 min.) 1173 140 lb to 52ºF Takeoff (wet) (5 min.) 1173 140 lb. to 84ºF Maximum Continuous 1020 127 lb. to 84ºF Reverse 900 - to 59ºF PT6A-45R: Takeoff (5 min.) 1197 141 lb. to 73ºF Alternate Takeoff (5 min.) 1173 140 lb. to 52ºF Maximum Continuous 1020 127 lb. to 92ºF Reverse 900 - to 59ºF Engine Limits. Inter Turbine Temperature: PT6A-45A PT6A-45B PT6A-45R Takeoff (dry or wet) 800ºC(1472ºF) 800ºC(1472ºF) - Takeoff - Alternate Takeoff - - - 845ºC(1553ºF) 800ºC(1472ºF) Maximum Continuous 800ºC(1472º F) 800ºC(1472ºF) 812ºC(1494ºF) Starting Transient (5 sec) 1000ºC(1832ºF) 1000ºC(1832ºF) 1000ºC(1832ºF) Transient 850ºC(1562ºF) 850ºC(1562ºF) 900ºC(1652ºF) Speed Limits - Gas Generator: Maximum Takeoff ( 5 min.) 104%(39,000) 104%(39,000) 104%(39,000) Maximum Continuous 104%(39,000) 104%(39,000) 104%(39,000) Maximum Transient (20 sec.) 104%(39,000) 104%(39,000) 104%(39,000) Speed Limits - Propeller - RPM: * Maximum Permissible 1685 1695 1695 Maximum Transient 1870 1870 1870 Maximum Reverse 1650 1650 1650 Minimum Flight 1200 1200 1200 For other engine limits refer to NOTE 11 or to engine TCDS Number E4EA. * Ground operation at stabilized speed between 1,170 and 1,400 RPM is prohibited. Propeller and Propeller Limits. 2 Hartzell HC-B5MP-3A reversible propeller. Blades: 5, model M10282AB + 6 Diameter limits: * Maximum 111 inches Minimum allowable for repairs 110.7 inches * No further reduction permitted, without aircraft performance penalty. Pitch setting at 30 in. radius station. Ground Fine + 4 Flight Fine + 21º Feathered 89º Full Reverse - 1º (Reverse thrust authorized for Ground Maneuvering only). For other propeller limits refer to propeller Type Certificate Data Sheet No. P44GL Spinner: Hartzell D-3434-8 Propeller Deicer: B.F. Goodrich 451601-7 Governors: Woodward 8210-009 or 8210-209 3 A41EU I. Model SD 3-30 Variant 200 (Transport Category Aircraft) (cont’d) Airspeed Limits. Speed Knots IAS Speed MPH IAS VMO (Maximum Operating Speed) 198 228 VA (Maneuvering Speed) 13,000 lb 22,900 lb 13,000 lb 22,900 lb (Linear variation between points) 121 157 139 181 V MCA * (Minimum Control Speed 77 (4º flaps) 89 (4º flaps) Takeoff Climb) 77 (8º flaps) 89 (8º flaps) 76 (15º flaps) 88 (15º flaps) V MCG * (Minimum Control Speed on or near ground) 76 88 VFE VLE Speed) VLO (Landing Gear Operating 148 170 Speed) * See NOTE 7 Center of Gravity (C.G.) Range C.G. Limit Landing Gear Exte nded Landing Gear Retracted Takeoff and Landing Enroute Aft of Datum (in.) % SMC Aft of Datum (in.) % SMC Forward Limit at 16,500 lb 29.85 16.0 27.89 13.3 Forward Limit at Maximum Landing Weight 30.72 17.2 28.76 14.5 (See NOTES 6, 8 & 12) Forward Limit at Maximum Takeoff Weight 30.80 17.3 28.83 14.6 (See NOTES 6, 8 & 12) Aft Limit all Weights 43.67 35.0 45.78 37.9 Landing Gear Retraction moment change +4,000 in. lb. Datum. The C.G. datum is at fuselage station 200 on the center line of aircraft and is marked on the underside of the fuselage. Standard Mean Chord. Length: 72.72 in. (SMC) The leading edge of SMC is 18.215 in. aft of datum (Sta. 200). Leveling Means. For determination of the center of gravity the aircraft should be brought to datum horizontal attitude. This is checked horizontally using a clinometer with a straight edge placed on pegs inserted in the holes in the two leveling plates on the fuselage port side at Sta. 212 and Sta. 291.12. The lateral level is checked using the two floor seat rails at the front spar frame in the passenger compartment. * (Wing Flaps Extended) (4º)(8 º)(15º)(35º) (4º)(8º)(15º)(35º) 148 148 138 125 170 170 159 144 * (Landing Gear Extended 161 185 4 A41EU I. Model SD 3-30 Variant 200 (Transport Category Aircraft) (cont’d) Maximum Weights. * Max imum Ramp Weight: 22,100 lb. Maximum Takeoff Weight: 22,000 lb. Maximum Landing Weight: 21,700 lb. *See NOTES 6, 8 & 12 for increased weight limitations. Minimum Crew. The minimum fl ight crew is two pilots. Maximum Passengers. 39 As limited by FAR 25 Emergency Exit Requirements. 30 As limited by approved seating arrangement. Baggage Compartments Class D modified to meet the requirements of FAR 121.314(c) when Short Brothers Mod P4816 is embodied. See NOTE 60 Maximum Baggage. Baggage must be loaded in acco rdance with the approved Weight and Balance Manual Ref. SD3/WB/200. Maximum Cargo Load. Cargo must be loaded in accordance with the approved Weight and Balance Manual Ref. SD3/WB/200. See Note 19 for operational limitations. Fuel Capacity. Volume, weight, a nd balance arm of fuel for each tan assuming there are 6.662 lbs per U.S Gallon of fuel (0.8 SG). Usable U.S. Gal. Weight lb. Arm about C.G. Datum (in.) Forward Aft Forward tank 288.2 1920 28.33 Aft tank 288.2 1920 98.33 Total usable in tank 576.4 3840 35.00 Unusable Forward tank 2.2 14.7 Aft tank 2.0 13.3 Total 4.2 28.00 Total Capacity 580.6 U.S. Gal. See NOTE 1(b). For increased fuel capacities, refer to Note 18. Oil Capacity. Volume, weight, a nd balance arm of engine oil. Usable U.S. Gal Weight lb. Arm about C.G. Datum (in.) Forward Aft Left tank 1.5 11.5 14 Right tank 1.5 11.5 14 Total 3.0 23.0 14 Unusable Left tank .55 4.0 - Right tank .55 4.0 - System 2.90 21.0 - Total 4.00 29.0 Total Capacity 7.0 U.S. Gal. See NOTE 1 (c) 5 A41EU I. Model SD 3-30 Variant 200 (Transport Category Aircraft) (cont’d) Maximum Operating Altitude. 20,000 ft. Control Surface Movements. Elevator 25 ½º ± 1º up 14 ½º ± ½º down Elevator trim tab 9º ± ½º up 14 ½º ± ½º down Rudder 29º ± 1º left 29º ± 1º right Left rudder trim tab 13 ½º ± ½º left 13 ¼º ± ¾º right Right rudder trim tab 22 ½ ± 1º left 22 ½º ± 1º right Left aileron 22 ¾º ± ¼º up 13 ¼º ± ¼º down Right aileron 23 ¾º ± ¼º up 12 ¾º ± ¼º down Aileron trim tab 13º ± ½º up 13º ± ½º down NOTE: Aileron reflex 1 ¼º ± ¼º The above angles are all measured from the neutral position. Flaps inner and outer: Nominal - 0º Enroute, all engines operating. * 8º Down - Enroute, one engine inoperative. * Takeoff and discontinued approach. * 15º Down - Takeoff and approach. * 35º Down - Landing. For details of flap setting tolerances refer to the approved Maintenance Manual Doc. SD3/MM/200 Chapter 27. * See NOTE 7 II. Model SD3-60, VARIANT 200 (TRANSPORT CATEGORY AIRCRAFT), approved October 29, 1982. Engines. 2 Pratt and Whitney of Canada Limited PT6A-65R Reduction Gear Ratio 0.0568: 1; or 2 Pratt and Whitney of Canada Limited PT6A-65AR Reduction Gear Ratio 0.0568: 1 or 2 Pratt and Whitney of Canada Limited PT6A-67R Reduction Gear Ratio 0.0568: 1. Fuel. Specifications, latest issued may be used. American British ASTM D1655-70 Jet A NONE Jet B NONE Jet A-1 Def Stan 91-87 MIL-T-5624L JP4 Def Stan 91-87 JP5 Def Stan 91-87 MIL-T-83133A JP8 Def Stan 91-87 Engine Ratings. Static, sea level, Intern ational Standard Atmospheric conditions. No bleed extraction or accessory loads, compressor intake screen installed. PT6A-65R SHP JET AIR THRUST INLET TEMPERATURE Take-off (5 min) 1376 209 lb. to 82ºF Alternate take-off (5 min) 1230 195 lb. to 76ºF Maximum Continuous 1173 189 lb. to 84ºF * Reverse 900 to 59ºF * See Note 14. 6 A41EU II. Model SD3-60, VARIANT 200 (TRANSPORT CATEGORY AIRCRAFT) (cont’d) PT6A-65AR SHP JET AIR THRUST INLET TEMPERATURE Take-off (5 min) 1424 214 lb. to 82ºF Alternate take-off (5 min) 1230 195 lb. to 84ºF Maximum Continuous 1220 194 lb. to 101ºF Reverse PT6A-67R 900 SHP JET to 59ºF AIR THRUST INLET TEMPERATURE Take-off (5 min) 1424 212 lb. to 99ºF Alternate take-off (5 min) 1281 192 lb. to 91ºF Max. Continuous 1220 184 lb. to 119ºF Reverse 900 Inter Turbine Temperature. PT6A-65R PT6A-65AR PT6A-67R Take-off (5 min) 845ºC(1553º F) 855ºC(1571ºF) 855ºC(1571ºF) Alternate take-off (5 min) 810º C(1490ºF) 820ºC(1508ºF) 825ºC(1517ºF) Maximum Continuous 810ºC(1490ºF) * 840ºC(1544ºF) 840ºC(1544ºF) Starting Transient (5 sec) 1000º C(1832ºF) 1000ºC(1832ºF) 1000ºC(1832ºF) Transient (20 sec) 870ºC(1598º F) 870ºC(1598ºF) 870ºC(1598ºF) * See NOTE 14 Speed Limits - Gas Generator Maximum Take-off (5 min) 104% (39,000) Maximum Continuous 104% (39,000) Maximum Transient 104% (39,000) Speed Limits - Propeller RPM Maximum Permissible 1700 (Up to 150 knots IAS) Maximum Transient 1450 (Above 150 knots IAS) 1870 Maximum Reverse 1650 Minimum Flight 1200 For other engine limits refer to Engine TCDS No. E4EA for PT6A-65R and -65AR engines and TCDS No. E26NE for PT6A-67R engines. Engine Ratings. (Continued). Ground operations using Ha rtzell HC-B5MP-3C propellers at stabilized speeds between 400 and 900 PRPM and 1170 and 1400 PRPM is prohibited. Ground operations using Hartzell HC-A6A-3 propellers at stabilized speeds between 500 and 950 PRPM and 1250 and 1450 PRPM is prohibited. Propeller and Propeller Limits. Propeller:HC-B5MP-3C HC-A6A-3 No of Blades: 5, Model M 10876ASK 6, Model A10460E or A10460K(See NOTE 53) Max Diameter: 111.0 inches 108.0 inches Min Diameter: 110.7 inches * 107.875 inches * * No further reduction permitted. Pitch Setting (42 inch radius) For other propeller limits refer to propeller TCDS No. P44GL or P14N for HC-B5MP-3C and HC-A6A-3, respectively. Ground Fine : -5º±30' -10º±30' Flight Fine : +16.5º±12' +12.5º±12' Feathered : +79º±30' 75.5º±30' Full Reverse : -11±30' -16º±30' 7 A41EU II. Model SD3-60, VARIANT 200 (TRANSPORT CATEGORY AIRCRAFT) (cont’d) Propeller and Propeller Limits Sp inner : Hartzell D-3434-8 D-5311 Propeller De-Icer: 4E-2595-7 Governors : Woodward 8210-049 8210-190 Airspeed Limits SPEED KNOTS IAS SPEED MPH IAS VMO (Maximum Operating Speed) 196 226 VA (Maneuvering Speed) 16000 lb. 26000 lb. 16000 lb. 26000 lb. (Linear variation 129 159 148 183 between points) 26453 lb. 27100 lb. 26453 lb. 27100 lb. 160 158 184 182 VMCA (Minimum Control Speed 83 (5º flaps) 95.6 (5º flaps) Take-off climb) 82 (15º flaps) 94.4 (15º flaps) VMCG (Minimum Control Speed 83 (5º flaps) 95.6 (5º flaps) on or near ground) 82 (15º flaps) 94.4 (15º flaps) VFE (Wing Flaps Extended) (5º) (15º) (30º) (5º) (15º) (30º) 150 145 135 172.7 167.0 155.5 VLE (Landing Gear Extended 162 186 Speed) VLO (Landing Gear Operating 150 173 Speed) Center of Gravity. C.G. Limit Take-off an d Landing En Route (C.G. Range) Inches about % Inches about % Forward limit up to 16500 lb Trim Datum -5.15 (fwd) SMC 16.0 Trim Datum -7.33 (fwd) SMC 13.0 Forward limit at 20000 lb - - -7.33 (fwd) 13.0 *Forward limit at max land- ing weight -3.62 (fwd) 18.10 - - *Forward limit at max take- off weight -3.57 (fwd) 18.17 -5.65 (fwd) 15.31 Aft limit up to 19000 lb +8.30 (aft) 34.5 +10.85 (aft) 38.0 Aft limit at 24,000 lb +9.39 (aft) 36.0 +12.30 (aft) 40.0 Aft limit at max take-off weight +9.39 (aft) 36.0 +12.30 (aft) 40.0 Landing gear retraction moment change +6000 in. lb * See NOTES 15 and 23 for Increased Weight Limitations. Trim Datum. This is a vertical lin e located at fuselage Station 271. Standard Mean Chord (SMC) Length : 72.72 inches Leading Edge : Station 254.215 Leveling Means. For determination of the center of gravity the aircraft should be brought to datum horizontal attitude. This is checked horizontally using a clinometer with a straight edge placed on pegs inserted in the holes in the two leveling plates on the fuselage left side at Sta. 255 and Sta. 335. The lateral level is checked using the two floor seat rails at the front spar frames in the passenger compartment. Maximum Weights. *Maximum Ramp Weight : 26100 lb Maximum Take-off Weight : 26000 lb Maximum Landing Weight : 25700 lb See NOTES 15 and 23 for Increase Weight Limitations. 8 A41EU II. Model SD3-60, VARIANT 200 (TRANSPORT CATEGORY AIRCRAFT) (cont’d) Minimum Crew. The minimum fl ight crew is two pilots. Maximum Passengers. 39 As limited by FAR 25 Emergency Exit Requirements. 39 As limited by approved seating arrangement. Baggage Compartments Class D modified to meet the requirements of FAR121.314(c) when Short Brothers Mod A8703 is embodied. See NOTE 60 Maximum Baggage. Baggage must be loaded with the approved Weight and Balance Manual Ref. 360/WBM/200. Fuel Capacity. Volume, weight, and balance arm of fuel for each tank, assuming there are 6.662 lbs per US Gallon of Fuel (0.8 SG). Usable Forward Aft Total Capacity 581.1 U.S. Gal. See NOTE 1(b) Oil Capacity. U.S. Gal. Weight Arm About Trim lb. Datum (in.) Usable Forward Aft Left tank 1.5 11.5 21 - Right tank 1.5 11.5 21 - Total 3.0 23.0 21 Unusable Left tank .55 4.0 Right tank .55 4.0 System 2.90 21.0 Total 4.00 29.0 Total Capacity 7.0 U.S.Gal. See NOTE 1 (c) Maximum Operating Altitude. 20,000 ft. Control Surface Movements. Elevator 22º ± ½º up 12º + 0º - ¼º down Elevator trim 7º ± 1 ¼º up 13º ± 1 ¼º down Rudder 21º ± ½º to left and right Rudder trim tab 2 ¼º ± ¼º biased to left with rudder and trimmer control neutral 12º ± ¾º to left and right from biased position Ailerons 27 ¾º ± ¼º up 14 ¾º ± ¼º down Ailerons Trim Tab 8 ½º ± ½º up 8 ½º ± ½º down NOTE: * Both ailerons drooped 3º ± ¼º with control wheel neutral. The aileron angles are all measured from the 3º drooped position. All other angles are measured from the neutral position. U.S. Gal Weight lb. Arm About Trim Datum (in.) Forward tank 288.2 1920 63.33 Aft tank 288.2 1920 63.33 Total usable in tanks 576.4 3840 - - Unusable Forward tank 2.5 16.7 Aft tank 2.2 15.3 Total 4.7 32.0 9 A41EU II. Model SD3-60, VARIANT 200 (TRANSPORT CATEGORY AIRCRAFT) (cont’d) Flaps inner and outer Nominal - Enroute, all engine operating 0 Down - Enroute, one e ngine inoperative 5º Take-off and discontinued approach *5º Down - Take off and approach 15º Down - Landing 30º For details of flap setting tolerances, refer to the Maintenance Manual. Doc. Ref. 360/MM. *5º not used for take-off with PT6A-65AR and PT6A-67R engines aircraft. See NOTE 24 for aircraft with Aileron droop deleted. III. Model SD3-SHERPA Variant 200 (Mod. K2009) (Transport Category Aircraft) approved August 30, 1990. Engines. 2 Pratt & Whitney, Aircra ft of Canada Limited, PT6A-65AR Reduction Gear Ratio: 0.0568 : 1 Fuel. Specifications, latest issued may be used. American British ASTM D1655-70 JET A NONE JET B NONE JET A-1 Def Stan 91-87 MIL-T-5624L JP4 Def Stan 91-87 JP5 Def Stan 91-87 MIL-T-83133A JP8 Def Stan 91-87 For fuel additives see NOTE 4. Engine Rating. Static, sea leve l, International Standard Atmospheric conditions. No bleed extraction or accessory loads, compressor intake screen installed. PT6A-65AR SHP JET TH RUST AIR INLET TEMP Take-off (5 min) 1424 214 lb. to 82ºF Alternative Takeoff (5 min) 1230 195 lb. to 84ºF Maximum Continuous 1220 194 lb. to 101ºF Reverse 900 - to 59ºF Engine Limits. Interturbine Temperature PT6A-65AR Take-off (5 min) 855ºC (1571ºF) Alternate take-off (5 min) 820ºC (1508ºF) Maximum Continuous 840ºC (1544ºF) Starting Transient (5 sec) 1000ºC (1832ºF) Transient (20 sec) 870ºC (1598ºF) Speed Limits - Gas Generator Maximum Take-off (5 min) 104% (39,000) Maximum Continuous 104% (39,000) Maximum Transient 104% (39,000) Speed Limits - Propeller RPM Maximum Permissible 1700 (Up to 150 knots IAS) 1450 (Above 150 knots IAS) Maximum Transient (20 sec) 1870 Maximum Reverse 1650 Minimum Flight 1200 10 A41EU III. Model SD3-SHERPA Variant 200 (Mod. K2009) (Transport Category Aircraft) (cont’d) Engine Limits For other engine limits refer to Engine TCDS No. E4EA. Ground operations using Hartzell HC-B5MP-3C propellers at stabilized speeds between 400 and 900 PRPM and 1170 and 1400 PRPM is prohibited. Propeller and Propeller Limits. 2 Hartzell HC-B5MP-3C reversible propellers. Propeller : HC-B5MP-3C Blades : 5, Model M10876ASK Max Diameter : 111.0 inches Min Diameter : 110.7 inches* * No further reduction permitted. PITCH SETTING 42 inch radius Ground Fine : -5º ± 30' Flight Fine : +12º ± 30' Feathered: +79º ± 30' Full Reverse : -11º ± 30' (Reverse thrust authorized for ground maneuvering only) other propeller limits refer to propeller TCDS No. P44GL. Spinner Assembly : Hartzell D-3434-8 Propeller Deicer : Goodrich 4E-2595-7 Governors : Woodward 8210-049 Airspeed Limits. Speed Knots IAS Speed MPH IAS VMO (Max Operating Speed) 196 226 VA (Maneuvering Speed) 15700 lb 25600 lb 15700 lb 25600 lb (Linear variation between points) 124 161 143 185.7 VMCA (Minimum Control 80 (10º flaps) 93.3 (10º flaps) Speed takeoff climb) 80 (15º flaps) 92.3 (15º flaps) VMCG (Minimum Control Speed on or near ground) 80 92.3 VFE (Wing Flaps (5º) (10º) (15º) (35º) (5º) (10º) (15º) (35º) Extended) 150 145 140 130 173 167.2 161.5 149.9 VLE (Landing Gear 160 184.5 Extended Speed) VLO (Landing Gear 150 173 Operating Speed) Center of Gravity. (C.G. Range) C.G. LIMIT TAKE-OFF & LANDING EN ROUTE Inches about Trim Datum % SMC Inches about Trim Datum % SMC Forward limit up to 29.85 Aft 16.00 27.89 Aft 13.30 16 500 lbs (7485 kg) Forward limit at 22.900 lbs 30.95 Aft 17.51 29.01 Aft 14.84 (10115 kg) Forward limit at max 33.77 Aft 21.39 29.37 Aft 15.34 landing weight Forward limit at max 34.41 Aft 22.27 29.45 Aft 15.45 Aft limit at all weights 43.67 Aft 35.00 45.78 Aft 37.90 11 A41EU III. Model SD3-SHERPA Variant 200 (Mod. K2009) (Transport Category Aircraft) (cont’d) Datum. This is located at fuselage Station 200 on the center line of the aircraft and is marked by a datum plate on the underside of the aircraft. Standard Mean Chord (SMC). Length : 72.72 inches Leading Edge : Station 218.21 Leveling Means. For determination of the center of gravity the aircraft should be brought to datum horizontal attitude. This is checked horizontally using a clinometer with a straight edge placed on pegs inserted in the holes in the two leveling plates on the fuselage left side at Sta. 212 and Sta. 291.12. The lateral level is checked using the two floor seat rails at the front spar frame in the passenger compartment. Maximum Weights. Maximum Ramp Weight : 25,700 lb Maximum Take-off Weight : 25,600 lb Maximum Landing Weight : 25,100 lb Minimum Crew. The minimum fl ight crew is two pilots. Maximum Passengers. 39 As limited by FAR 25 Emergency Exit Requirements 30 As limited by appr oved seating arrangement. Baggage Compartment Class D Maximum Baggage. Baggage must be loaded in acco rdance with the approved Weight and Balance Manual Ref. SD3 SHERPA/WB. Maximum Cargo Load. Cargo must be loaded in accordance with the approved Weight and Balance Manual Ref. SD3 SHERPA/WB. Fuel Capacity. Volume, weight and balance arm of fuel for each tank assuming there are 6.5 lbs per US Gallon of fuel. (0.78 SG) U.S. Gal Weight Arm About lb. Datum (in.) Forward Aft Usable Forward tank 336 2184 22 Aft tank 336 2184 122 Total usable in tanks 672 4368 Systems and Sumps 2.3 15 39 Total Usable 674.3 4383 Unusable Forward tank 2.2 14.3 Aft tank 2.2 14.3 4.4 28.6 Total Capacity 678.7 U.S. Gallons See NOTE 1(b) Oil Capacity. U.S. Gal. Weight Arm About lb. Datum (in) Usable Forward Aft Left tank 1.5 11.5 21 - Right tank 1.5 11.5 21 - TOTAL 3.0 23.0 21 Unusable Left tank 0.55 4.0 Right tank 0.55 4.0 System 2.90 21.0 TOTAL 4.00 29.0 Total oil capacity 7.0 US gals See NOTE 1 (c) 12 A41EU III. Model SD3-SHERPA Variant 200 (Mod. K2009) (Transport Category Aircraft) (cont’d) Maximum Operating Altitude. 20,000 ft. Control Surface Movements. Elevator 22º ± ½º up 14 ½º ± ½º down - 1º Elevator trim tab 9º ± 1º up 14 ½º ± 1º down Rudder 29º ± 1º left 29º ± 1º right Left rudder trim tab13 ½º ± 1º left 13 ½º ± 1º right Right rudder trim tab 22º ± 1 ½º left 22 ½º ± 1 ½º right Left aileron 22 ¾º ± ½º up 13 ¼º ± ½º down Right aileron 23 ¾º ± ½º up 12 ¾º ± ½º down Aileron Trim tab 13º ± 1º up 13º ± 1º down NOTE: Aileron reflex: 1 ¼º ± ¼º up The above angles are all measured from the neutral position. Flaps inner and outer: Nominal Designation 0º flaps Flaps retracted 5º flaps Single engine en-route 10º flaps Take-off, preliminary approach and discontinued approach 15º flaps Take-off, approach and landing 35º flaps Landing For details of flap setting tolerances refer to Maintenance Manual Ref. SD3 SHERPA/MM. IV. Model SD3-60 SHERPA Variant 200 (Mod K6001) (Transport Category Aircraft) approved April 19, 1996 Engines. 2 Pratt & Whit ney Aircraft of Canada Limited, PT6A-65AR Reduction Gear Ratio: 0.0568 : 1 Fuel. Specifications, latest issue may be used. American British ASTM D1655-70 Jet A NONE Jet B NONE Jet A-1 Def Stan 91-87 MIL-T-5624L JP4 Def Stan 91-87 JP5 Def Stan 91-87 MIL-T-83133A JP8 Def Stan 91-87 For fuel additives see NOTE 4. Engine Ratings. Static, sea level, International Standard Atmospheric conditions. No bleed extraction or accessory loads, compressor intake screen installed. PT6A-65AR SHP JET THRUST AIR INLET TEMP Takeoff (5 min.) 1424 214 lb. to 82ºF Alternate takeoff (5 min) 1230 195 lb. to 84ºF Maximum Continuous 1220 194 lb. to 101ºF Reverse 900 - to 59ºF 13 A41EU IV. Model SD3-60 SHERPA Variant 200 (Mod K6001) (Transport Category Aircraft) (cont’d) Engine Limits. Interturbine Temperature PT6A-65AR Take-off (5 min) 855ºC (1571ºF) Alternate Takeoff (5 min) 820ºC (1508ºF) Maximum Continuous 840ºC (1544ºF) Starting Transient (5 sec) 1000ºC (1832ºF) Transient (20 sec) 870ºC (1598ºF) Speed Limits - Gas Generator Maximum Take-off (5 min) 104% (39,000) Maximum Continuous 104% (39,000) Maximum Transient 104% (39,000) Speed Limits - Propeller RPM Maximum Permissible 1700 (Up to 150 knots IAS) 1450 (Above 150 knots IAS) Maximum Transient (20 sec) 1870 Maximum Reverse 1650 Minimum Flight 1200 For other engine limits refer to Engine TCDS No. E4EA.