# TCDS A41EU: De Havilland Aircraft of Canada Limited - Type: Type certificate data sheet - Status: Current - Holder: De Havilland Aircraft of Canada Limited - Revision: 15 - Revised: October 19, 2026 - Product: Aircraft, Large Airplane - Certification basis: Part 21, Part 25 - Registered aircraft: 5, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/f1/83/f183918427ac0d801c6d74385e999fff6d8255d5e06b53b24ba076d048f737da - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID189189915020261019143358.0001 - Page: https://openairdocs.org/tcds/A41EU ## Models (4) As the data sheet lists them. - SD3-30 Variant 200 - SD3-60 SHERPA Variant 200 - SD3-SHERPA Variant 200 - SD3-60 Variant 200 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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. 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) For other propeller limits refer to propeller TCDS No. P44GL. Spinner : Hartzell D-3434-8 Propeller De-Icer : Goodrich 4E-2595-7 Governors : Woodward 8210-049 Airspeed Limits. Speed Knots IAS Speed MPH IAS VMO (Maximum Operating Speed) 196 226 VA (Maneuvering Speed) 15700 lb 25600 lb 15700 lb 25600 lb (Linear variation between points) 126 163 145.3 188 VMCA (Minimum Control Speed 80 (10º flaps) 93.3 (10º flaps) Takeoff Climb) 80 (15º flaps) 92.3 (15º flaps) VMCG *(Minimum Control Speed 80 92.3 on or near ground) VFE * (Wing Flaps Extended) (5º) (10º) (15º) (35º) (5º) (10º) (15º) (35º) 150 150 140 135 173 173 161.1 155.8 VLE * (Landing Gear Extended 160 184.5 Speed) VLO (Landing Gear Operating 150 173 Speed) 14 A41EU IV. Model SD3-60 SHERPA Variant 200 (Mod K6001) (Transport Category Aircraft) Center of Gravity (C.G. Range). (cont’d) C.G. LIMIT TAKE-OFF & LANDING EN-ROUTE Inches about % Inches About % Trim Datum SMC Trim Datu m SMC Forward limit up to 29.85 Aft 16.00 27.89 Aft 13.30 16 500 lbs (7485 kg) Forward limit at 22900 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 take off weight Aft limit at all weights 43.67 Aft 35.00 45.78 Aft 37.90 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. Length: 72.72 in (SMC) 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 ch ecked horizontally using a clinom eter 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 la teral 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 Takeoff 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 approved seating arrangement Baggage Compartment Class D Maximum Baggage. Baggage must be loaded in acco rdance with the approved Weight and Balance Manual Ref. SD3-60 SHERPA/WB. Maximum Cargo Load. Cargo must be loaded in accordance with the approved Weight and Balance Manual Ref. SD3-60 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. Usable U.S. Gal. Weight Arm about lb. Datum (in) Forward Aft Forward tank 336 2184 22 Aft tank 336 2184 122 Total usable in tank 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. Gal See NOTE 1(b). 15 A41EU IV. Model SD3-60 SHERPA Variant 200 (Mod K6001) (Transport Category Aircraft) (cont’d) Oil Capacity. U.S. Gal. Weight Arm about lb. Datum (in) Forward Aft Usable 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 U.S. Gal See NOTE 1(c) 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 the Maintenance Manual Ref. SD3-60 SHERPA/MM DATA PERTINENT TO ALL MODELS. Serial Numbers Eligible. The United Kingdom (CAA) Ce rtificate of Airworthiness for Export, endorsed as noted under "Import Requirements" below must be submitted for each individual aircraft for which application for certification is made. Import Requirements. a. The FAA can issue a U.S. airworthiness certificate based on a National Aviation Authority Export Certificate of Airworthiness (Export C of A) signed by a representative of the United Kingdom on behalf of the European Community. The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to conform with Type Design approved under U.S. Type Certificated No. A41EU and be in a condition for safe operation. b. The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). Maximum Operating Altitude. Control Surface Movements. 20,000 ft. Elevator 22º ± ½ 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 ri ght Right rudder trim tab 22º ± 1½° 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: 1¼º ± ¼º up 16 A41EU Transition Statement. The United Kingdom’s Civil Avia tion Authority (CAA) originally type certificated the SD3-30, SD3-60, SD3-Sherpa, and SD3-60 Sherpa Airplanes under its type certificate Number BA11. The FAA validated these products under U.S. Type Certificate Number A41EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom. Certification Basis. SD3-30 Airplanes: FAR 21.29, FAR 25, effective February 1, 1965 including amendments 25-1 through 25-30 and Special Conditions No. 25-70-EU-22 dated June 8, 1976; with amendment No. 1 thereto, dated June 11, 1976; plus FAR 25, amendments 25-31 through 25-34 elected by the applicant, except FAR 25.807 as amended by amendment 25-32. Compliance with the following optional requirements has been established: - Ditching provisions 25.801 (overwater operations can be approved when the aircraft has been equipped and installation has been approved according to FAR 25.801). - Ice protection provisions 25.1419 (See NOTE 9). Compliance has been shown with FAR 36 effective December 1, 1969 including amendments as follows:- 1) 36-1 for airplanes with P&WA Model PT6A-45A engines and takeoff weight of 22,000 pounds. 2) 36-6 for airplanes with P&WA Model PT6A-45A engines and takeoff weight of 22,400 pounds. 3) 36-8 for airplanes with P&WA Model PT6A-45B engines and takeoff weight of 22,600 pounds 4) 36-9 for airplanes with P&WA Model PT6A-45R engines and takeoff weight of 22,900 pounds. Compliance with SFAR 27 has been shown. Equivalent safety in lieu of compliance with FAR 25.773(b)(2)(i) has been established. Type Certificate A41EU issued June 18, 1976. Date of Application for Type Certificate: November 12, 1971. Certification Basis (Continued). SD3-60 Airplanes. FAR 21.29 United Kingdom Certification Basis as defined in CAA TCDS No. BA11, plus FAA additional validation requirements (AVR's) as defined in paper project No. CT184EU dated October 31, 1973. This is equivalent to FAR Part 25, effective February 1, 1965 including amendments 25-1 through 25-34, plus FAR 25.1351 as amended by amendment 25-41. FAA Special Conditions No. 25-70-EU-22 dated June 8, 1976 with amendment No. 1 thereto dated June 11, 1976. FAR Part 36, effective December 1,1969 including amendments 36-1 through 36-12. SFAR 27 effective January 1, 1975. Equivalent safety in lieu of compliance with FAR 25.773(b)(2)(i) has been established. The following additional FAA requirements have been voluntarily complied with: FAR 25.785 to Amendment 51 Standar d FAR 25.812 " " 46 " FAR 25.851 " " 54 " FAR 25.853 " " 51 " FAR 25.1326 " " 43 " FAR 25.1351 " " 41 " FAR 25.1411 " " 53 " FAR 25.1457 " " 41 " FAR 25.1459 " " 41 " - Ditching Provisions 25.801 (Overwater operations can be approved when the airplane has been equipped and installation has been approved according to 17 A41EU FAR 25.801). - Ice protection provisions 25.1419. Type Certificate A41EU amended October 29, 1982. SD3 SHERPA (Mod K2009) Airplanes: FAR 21.29 United Kingdom Certification Basis as defined in CAA TCDS No. BA11, plus FAA additional validation requirements (AVR's) as listed below. FAR Part 25, effective February 1, 1965 as amended by Amendments 25-1 through 25-35, 25-37 through 25-39, 25-43, 25-44, 25-47, 25-49 through 25-53, 25-55, 25-56, 25-58 through 25-63, 25-66 and 25-36 Except for paragraphs .1019 and .1305, 25-40 except for paragraphs .1093 and .1145, 25-41 except for paragraphs .1353, 25-42 except for paragraphs .109, .177, .181, .255, .703, 25-45 except for paragraph .571 25-46 except for paragraphs .331, .351, .361, .629, .773, .1329, .1416, 25-48 except for paragraphs .735, 25-54 except for paragraphs .305, .783, .1529, 25-57 except for paragraphs .997, .1093, 25-64 except for paragraphs .561, .562, .785, 25-65 except for paragraphs .1457, .1459. Certification Basis (Continued). Part 36 of the Federal Aviation Regulations as amended by Amendment 36-1 through the latest Amendment 36-17, which was in effect at time of TC and SFAR 27 as amended by Amendments 27-1 through the latest Amendments 27-6 in effect at the time of TC and Any exemptions petitioned for by the applicant and granted by the Federal Aviation Administration. Short Brothers has elected to show compliance with the following optional requirements in the TC basis. - Ditching provisions Section 25.801 (overwater operations can be approved when the aircraft is equipped and installation is approved in accordance with Section 25.801). - Ice protection provisions Section 25.1419. Type Certificate A41EU amended August 30, 1990. SD3-60 SHERPA (Mod K6001) Airplanes: FAR 21.29 United Kingdom Certification Basis as defined in CAA TCDS No. BA11, plus FAA additional validation requirements (AVR's) as listed below: FAR Part 25, effective February 1, 1965 as amended by Amendments 25-1 through 25-35, 25-37 through 25-39, 25-43, 25-44, 25-47, 25-49 through 25-53, 25-55, 25-56, 25-58 through 25-60and 25-62 through 25-63, 25-69 and 25-36 except for paragraphs .1019 and .1305, 25-40 except for paragraphs .1145, 25-41 except for paragraphs .1353, 25-42 except for paragraphs .109, .177, .181, .255, .703, 25-45 except for paragraphs .571, 25-46 except for paragraphs .331, .351, .361, .629, .773, .1329, .1416, 25-48 except for paragraphs .735, 25-54 except for paragraphs .305, .783, .1529, 25-57 except for paragraphs .997 25-61 (See Note 58) 18 A41EU 25-64 except for paragraphs .561, .562, .785, 25-65 except for paragraphs .1457, .1459, 25-66 (See Note 58), and FAR 25.1419, Amendment 25-72, ice protection (airframe) FAR 25.801, Amendment 25-72, Ditching provisions (overwater operations can be approved when the aircraft is equipped and installation is approved in accordance with Section 25.801), and Part 36 of the Federal Aviation Regulations as amended by Amendment 36-1 through the latest Amendment 36-20, which was in effect at time of TC and FAR 34 Subpart B effective 10 September 1990, and FAA Special Condition No. 25-70-EU-22, (Engine Ignition System & Operation Without Normal Electrical Power), dated June 8, 1976, with Amendment No. 1 (Special Flight & Propulsion Conditions), thereto dated June 11, 1976, and Equivalent safety in lieu of compliance with FAR 25.773 (b)(2)(i), (Pilot Compartment View, Precipitation Conditions), which has been established. Any exemptions petitioned for by the applicant and granted by the Federal Aviation Administration. Type Certificate A41EU amended 19 April 1996. Equipment. The basic required equipment as prescr ibed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. In addition the following items of equipment are required: For SD3-30 airplanes, documents No. SBH 3.3 and SBH 3.6 are the approved, basic airplane Flight Manuals. When a specific Short Brothers CMC Mod. XXXX is incor- porated on a Model SD3-30 variant 200 airplane the approved supplement of particular amendment (P/-), associated with the modification, as listed herein, must be incorpo- rated into the appropriate basic document. CMC MOD. SEE NOTE MODEL OF ENGINE INSTALLED AIRPLANE BASIC NO. FLIGHT MANUAL AND SUPPLEMENT OR AMENDMENT NO 5192 6 PT6A-45A PT6A-45B SBH 3.3 SBH 3.3 P/1 P/1, P/8, P/9, P11, P12 5423 7 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 SUPP. 6 P/8, P/11, P/12 - 5600 8 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 P/1, P/5 P/1, P/5, P/8, P/11, P/12 P/1 5539 9 PT6A-45A SBH 3.3 P/3, P/4, P/7 PT6A-45B SBH 3.3 P/10, S/14, P/3, P/7, P/8, P/11, P/10, P/12 S/12, S/14 SBH 3.6 P/15 5656 ONLY 10A PT6A-45B SBH 3.3 P/1, P/8, P/9, P/11, P/12 5600 8 PT6A-45B SBH 3.3 P/1, P/5, P/8, 5656 10A P/11, P/12 5600 8 PT6A-45R SBH 3.6 P/1 6031 10B 6031 10B PT6A-45R SBH 3.6 - 6036 12 6504 17 PT6A-45R SBH 3.6 P/8, P/6 19 A41EU CMC MOD. SEE NOTE MODEL OF ENGINE INSTALLED AIRPLANE BASIC NO. FLIGHT MANUAL AND SUPPLEMENT OR AMENDMENT NO 6689 6867 18 PT6A-45R SBH 3.6 P/7 6700 19 PT6A-45R SBH 3.6 P/6 5952 6786 21 PT6A-45R SBH 3.6 S/9 4731 35 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 P/15 P/15 P/11 4751 39 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 P/16, P/17 P/16, P/17 P/12, P/13 6910 6946 40 PT6A-45R SBH 3.6 P/9 5763 41 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 SUPP 11 SUPP 11 SUPP 3 4778 59 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 P/18 P/18 P/14 4816 60 PT6A-45R SBH 3.6 P/16 4817 61 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 P/19 P/19 P/17 4818 63 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 P/20 P/20 P/18 4820 62 PT6A-45A PT6A-45B PT6A-45R SBH 3.3 SBH 3.3 SBH 3.6 P/21 P/21 P/19 4825 64 PT6A-45R SBH 3.6 SUPP 15 For SD3-60 airplanes Documents No. SB.4.3, SB 4.6 and SB 4.8 are the approved basic Flight Manuals. When a specific Short Brothers CMC Mod XXXX is incorporated on a model SD3-60 Variant 200 airplane, the approved supplement or particular amendment (P/-), associated with the modification, as listed herein, must be incorporated into the appropriate basic document. CMC MOD . SEE NOTE MODEL OF ENGINE INSTALLED AIRPLANE BASIC NO. FLIGHT MANUAL AND SUPPLEMENT OR AMENDMENT NO. 7260 14 PT6A-65R SB.4.3 P/4 7544 15 PT6A-65R PT6A-65AR SB.4.3 SB.4.6 P/9, P/4 - 7543 16 PT6A-65AR SB.4.6 7734 22 PT6A-65AR PT6A-67R SB.4.6 SB.4.8 P/7, P/9 - 7914 20 PT6A-65AR SB.4.6 P/1 A8096 23 PT6A-67R SB.4.8 - A8064 24 PT6A-67R SB.4.8 A8077 25 PT6A-67R SB.4.8 A8059 26 PT6A-67R SB.4.8 7784 27 PT6A-67R SB.4.8 A8062 28 PT6A-67R SB.4.8 20 A41EU CMC MOD . SEE NOTE MODEL OF ENGINE INSTALLED AIRPLANE BASIC NO. FLIGHT MANUAL AND SUPPLEMENT OR AMENDMENT NO. A8310 29 PT6A-67R SB.4.8 P/1 A8123 30 PT6A-67R SB.4.8 P/6 SUPP NO. 10 A8283 31 PT6A-67R SB.4.8 SUPP NO 11 A8268 32 PT6A-67R SB.4.8 P/3 A8320 33 PT6A-67R SB.4.8 P/4 A8428 34 PT6A-67R SB.4.8 P/5 A8286 36 PT6A-67R SB.4.8 P/10 7264 43 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/6 - - 7114 44 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/8 - - 7985 45 PT6A-65R SB 4.3 P/11 7767 46 PT6A-65R PT6A-65AR SB 4.3 SB 4.6 P/15 P/4 8243 35 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/18 P/11 P/8 8611 39 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/19, P/20 P/12, P/13 P/14, P/15 7986 47 PT6A-65AR SB 4.6 P/2 7583 48 PT6A-65AR PT6A-67R SB 4.6 SB 4.8 P/3 - 7479 49 PT6A-65R PT6A-65AR SB 4.3 SB 4.6 P/17 P/10 8574 50 PT6A-67R SB 4.8 P/9 8575 51 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/21 P/14 P/12 8633 59 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/22 P/15 P/13 8703 60 PT6A-65AR PT6A-67R SB 4.6 SB 4.8 P/17/ P/21 8700 61 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/31 P/18 P/18 8707 63 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/32 P/20 P/19 8709 62 PT6A-65R PT6A-65AR PT6A-67R SB 4.3 SB 4.6 SB 4.8 P/33 P/21 P/20 For SD3 SHERPA airplanes Document No. SB. 5.2 is the approved basic Flight Manual. When a specification Shorts Brothers CMC Mod XXXX is incorporated on a model SD3 Sherpa Variant 200 airplane, the approved supplement or pa rticular amendment (P/-), associated with the modifi cation, as listed herein, must be incorporated into the basic document. 21 A41EU CMC MOD SEE NOTE MODEL OF ENGINE INSTALLED AIRPLANE BASIC NO. FLIGHT MANUAL AND SUPPLEMENT OR AMENDMENT NO. K2098 37 PT6A-65AR SB.5.2 P/1 - 38 PT6A-65AR SB.5.2 SUPP No 11 K2061 42 PT6A-65AR SB.5.2 SUPP No 2 or 13 K2161 52 PT6A-65AR SB.5.2 SUPP No 14 K2219 59 PT6A-65AR SB.5.2 P/2 K2242 61 PT6A-65AR SB.5.2 P/4 K2245 63 PT6A-65AR SB.5.2 P/5 K2247 62 PT6A-65AR SB.5.2 P/6 For SD3-60 SHERPA airplanes Document No SB 6.2 is the approved basic Flight Manual. When a specific Short Brothers CMC Mod XXXX is incorporated on a Model SD3-60 Sherpa Variant 200 airplane, the approved supplement or particular amendment (P/-), associated with the modification, as listed herein, must be incorporated into the basic document. CMC MOD SEE NOTE MODEL OF ENGINE INSTALLED AIRPLANE BASIC NO. FLIGHT MANUAL AND SUPPLEMENT OR AMENDMENT NO. - 54 PT6A-65AR SB 6.2 SUPP NO 11 K 6033 55 PT6A-65AR SB 6.2 SUPP NO 1 K 6043 56 PT6A-65AR SB 6.2 SUPP NO 12 57 PT6A-65AR SB 6.2 BASIC - 59 PT6A-65AR SB 6.2 BASIC K6112 61 PT6A-65AR SB 6.2 P/2 K6115 63 PT6A-65AR SB 6.2 P/3 K6117 62 PT6A-65AR SB 6.2 P/4 Service Information. Each of the documents listed belo w that contain a statement that it is approved by the European Aviation Safety Agency (EASA) – or for approval s made before September 28, 2003 – by the United Kingdom are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Short Brothers PLC under the authority of EASA approved Design Organization EASA.21J.068 – or for approval made before September 28, 2003 – under the authority of Bombardier Aerospace Shorts Approval Number DAI /1665/40 or CAA.JA.02246 are considered FAA approved. These approval pertain to the type design only. Shorts Service bulletins, Structural repair manuals, Vendor manuals, Aircraft flight manuals, Repair instructions, Overhaul and maintenance manuals. Note: Design changes that are contained in Shorts Service Bulletins and that are classified as Level 1 Major in accordance with either the US/UK or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. 22 A41EU NOTES. NOTE 1. (a) Current weight and balanc e report, including list of equipment included in certificated empty weight, and loading instructions when necessary must be in each aircraft at the time of original certification. (b) Unusable fuel and system oil and all hydraulic fluid, must be included in the certified empty weight. (c) System oil is the amount of oil required to fill the oil system and tanks up to its normal level. Dipstick readings calibrated in U.S. quarts indicate the quantity required to fill the tank to normal level, i.e. 1 U.S. quart (0.833 Imperial quarts) below maximum level. NOTE 2. All placards required in the limitations section of th e FAA-approved Airplane Flight Manual must be installed. NOTE 3. (a) The service life limits for airplane structural parts which are fatigue critical are listed in Chapter 5 of the approved Maintenance Manual Document Ref. SD3/MM/200 for Model SD3-30, Chapter 5 of the approved Maintenance Manual Document Ref. 360/MM for Model SD3-60 and Chapter 5 of the approved Maintenance Manual Document Ref SD3 SHERPA/MM for Model SD3 Sherpa and Chapter 5 of the approved Maintenance Manual Document Ref SD3-60 Sherpa/AMM and must be replaced as indicated herein. (b) The engine life limited parts are listed in the P&WA CL Engine Service Bulletin Nos. 1002, 3002 and 4002 as revised. (c) The engine life limited parts for the 65 series engines are listed in P&WC Engine Service Bulletin Nos. 13002 and 13003 as revised. NOTE 4. Fuel Additives Only the following additives may be used with the specified fuels. U.S.A. CANADA U.K. MIL-I-27686E3-GP-526a Def Stan 68-252 provided that the concentration does not exceed 0.15% by volume. NOTE 5. Methanol/Water for SD3-30 airplane s incorporating the -45A and -45B engines, the approved methanol water for use in this particular installation is to the latest approved issue of the following specifications: U.S.A. CANADA U.K. Shell methanol/Water CPW-328 Def Stan 68-253 mixture 45/55/0 The methanol/Water mixture shall be in the ratio of 45% methanol 55% water when both fluids are at 15.6ºC. For Methanol/Water limitations and operating procedures, refer to approved Airplane Flight Manual. NOTE 6. SD3-30 airplanes incorporating Short Brothers CM C Mod. 5192* may be operated at the following maximum weights: Maximum ramp weight 22,500 lb Maximum takeoff weight 22,400 lb Maximum landing weight 22,100 lb * Refer to Equipment in this data sheet for airplane flight manual required. 23 A41EU Forward C.G. Limits: The following revised forward C.G. limits must be observed when operating at the above weights: T.O. & Landing Enroute Landing Gear Extended Landing Gear Retracted Aft of Datum % SMC Aft of Datum % SMC (in) (in) Forward Limit At Maximum: Landing Weight 30.80 17.3 28.83 14.6 Take-off Weight 30.87 17.4 28.90 14.7 All other CG limits are unchanged. NOTE 7. Airplanes incorporating Short Brothers CM C Mod 5423* have an additional flap setting of 4º. This setting may be used for takeoff and enroute one engine inoperative flight. * Refer to Equipment for Airplane Flight Manual required. NOTE 8. SD3-30 airplanes incorporating Short Brothers CM C Mod. 5600* may be operated at the following maximum weights: Maximum ramp weight 22,700 lb Maximum takeoff weight 22,600 lb Maximum landing weight 22,300 lb * Refer to Equipment in this data sheet for Airplane Flight Manual required. Forward C.G. limits: The following revised forward C.G. limits must be observed when operating at the above weights: T.O & Landing Enroute Landing Gear Extended Landing Gear Retracted Aft of Datum % SMC Aft of Datum % SMC (in.) (in.) Forward Limit at Maximum: Landing Weight 30.85 17.37 28.88 14.67 Take-off Weight 30.92 17.47 28.95 14.77 All other C.G. limits are unchanged. NOTE 9. SD3-30 airplanes with airframe de-icing provisions re moved in accordance with Short Brothers CMC Mod. 5539* are not approved for flight in icing conditions. *Refer to Equipment for Airplane Flight Manual required. NOTE 10. On SD3-30 Airplanes: A. 2 Pratt & Whitney aircraft of Canada Limited Model PT6A-45B engines may be installed in lieu of the Model PT6A-45A engines in accordance with Short Brothers CMC Mod. No. 5656. Short Service Bulletin No. SD3-71-05 and SD3-71-06 refers to this subject. B. 2 Pratt & Whitney aircraft of Canada Limited Model PT6A-45R engines may be installed in lieu of the Model PT6A-45A or PT6A-45B engines in accordance with Short Brothers PLC Modification No. 6031. Shorts Service Bulletin No. SD3-71-11refers to this subject. 24 A41EU NOTE 11. A. For approved engine oils for SD3-30, SD3-60 and SD3 Sherpa airplanes see P&W Service Bulletin 13001. B. Oil Temperature Limits ºC Oil Temperature Limits ºC for SD3-30 for SD3-60 and SD3 Sherpa. Minimum -40 Minimum -40 Minimum for take-off 20 Minimum for take-off 20 Normal operating 60 to 100 Normal operating 20 to 99 Maximum (5 min) 104 Maximum (5 min) 110 (Takeoff) C. Oil pressure limits (psi) Oil Pressure Limits for for SD3-30 SD3-60 and SD3 Sherpa. Minimum for takeoff 90 Minimum for takeoff 90 Minimum for flight 60 Minimum for flight 90 Maximum normal (Normal) operating 135 60 (if torque kept below Maximum transient during 2000 lb ft) cold starts 200 Maximum normal operating 135 Maximum transient 200 NOTE 12. SD3-30 airplanes incorporating Short Brothers CMC Mod. 6036* may be operated at the following maximum weights: Maximum ramp weight 23,000 lb Maximum takeoff weight 22,900 lb Maximum landing weight 22,600 lb * Refer to Equipment in this Data Sheet for Airplane Flight Manual Required. Forward C.G. Limits: The following revised forward C.G. limits must be observed when operating at the above weights: T.O. & Landing Enroute Landing Gear Extended Landing Gear Retracted Aft of Datum (in) Forward Limit at Maximum: % SMC Aft of Datum (in) % SMC Landing Weight 30.90 17.44 28.95 14.77 Take-off Weight 30.95 17.51 29.01 14.84 All other C.G. Limits are unchanged. NOTE 13. The Model C23A airplanes are the same as the basic model SD3-30 Variant 200 except for the FAA approved modifications listed in Shorts Brothers Report No. SB/C23A/mods/001and the deviations from the US Type Design as listed on the Certificate of Airworthiness for Export. A model C23A airplane is eligible for a US Airworthiness Certificate provided: a) A Certificate of Airworthiness for Export has been issued, and is available for the airplane, by the CAA-UK. b) All deviations listed in the Certificate of Airworthiness for export have been eliminated. c) The maintenance, overhaul and modifications records of each airplane are available, have been reviewed for changes made by the military services that affect the US Type Design of the airplane, and any Modifications, changes of equipment and repairs which affect the Type Design have been approved by the FAA. d) All applicable Airworthiness Directives have been complied with. 25 A41EU e) A modification nameplate has been installed adjacent to the original nameplate containing the following information: Modifiers Name Civil Model SD3-30 Variant 200 Date of Modification f) A CAA approved, on behalf of FAA, Airplane Flight Manual applicable to the Model SD3-30 Variant 200 dated has been provided. NOTE 14. On SD3-60 airplanes incorporating Short Br others CMC Mod 7260 the Maximum Continuous Engine Rating is available up to a Temperature of 101ºF and the Maximum Continuous Inter Turbine Temperature Limit is increased to 835ºC (1535ºF). All other Engine Ratings and Limits remain unchanged. NOTE 15. SD3-60 airplanes incorporating Short Brothers CMC Mod 7544* may be operated at the following maximum weights: Maximum ramp weight 26,553 lb Maximum take-off weight 26,453 lb Maximum landing weight 26,100 lb * Refer to Equipment in this data sheet for SD3-60 Airplane Flight Manual required. Forward C.G. Limits: The following revised forward C.G. limits must be observed when operating at the above weights. Forward Limit at: T.O. & Landing Enroute Landing Gear Extended Landing Gear Retracted Fwd of Datum % SMC Fwd of Datum % SMC (in) (in) 26,000 lb Maximum Landing -3.57 18.17 Weight -3.28 18.57 Maximum Take-off Weight -2.24 20.00 -5.53 15.48 NOTE 16. On SD3-60 Airplanes: 2 Pratt and Whitney aircraft of Canada Limited Model PT6A-65AR engines may be installed in lieu of the Model PT6A-65R engines in accordance with Short Brothers PLC Modification 7453. Shorts Service Bulletin No's SD360-51-03 and SD360-71-09 refer to the subject. NOTE 17. SD3-30 airplanes which have embodied Short Brothers CMC Mod 6700 (Rear Ramp Door) and CMC Mod 6504* may be operated in the Cargo Role using the main cabin compartment as a Class "E" Cargo Compartment. * Refer to Equipment in this data sheet for the SD3-30 Airplane Flight Manual Required. NOTE 18. SD3-30 airplanes incorporating Short Brot hers CMC Models 6689 (SD3-30)* or 6867 (C23A)* may be operated with the following maximum fuel capacity: Volume, weight and balance arm of fuel for each tank assuming there are 6.5 lbs per US Gallon of fuel. Forward Aft U.S. Gal. Weight lb. Arm About C.G. Datum (in.) Usable Forward Tank 336 2184 22 Aft Tank 336 2184 122 Total usable in tanks 672 4368 26 A41EU U.S. Gal. Weight Arm About C.G. lb. Datum (in.) Forwar d Aft 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). *Refer to Equipment in this data sheet for the SD3-30 Airplane Flight Manual Required. NOTE 19. SD3-30 airplanes incorporating Short Brothers CMC M od 6700* may be operated at the following maximum weights. Maximum ramp weight 23,000 lbs Maximum take-off weight 22,900 lbs Maximum landing weight 22,600 lbs Maximum Payload 7,000 lbs Forward CG Limits: The following revised forward CG limits must be observed when operating at the above weights: T.O & Landing En-Route Landing Gear Extended Landing Gear Retracted Fwd of Datum % SMC Fwd of Datum % SMC (in) (in) Forward Limit at Maximum: Landing Weight 30.90 17.44 28.95 14.77 Take-off Weight 30.95 17.51 29.01 14.84 All other CG limits are unchanged. * Refer to Equipment in this data sheet for the SD3-30 Airplane Flight Manual Required. NOTE 20. SD3-60 airplanes with airframe de-icing provi sions removed in accordance with Short Brothers CMC Mod 7914* are not approved for Flight in icing conditions. * Refer to Equipment for Airplane Flight Manual required. NOTE 21. SD3-30 airplanes incorporating Short Brothers CMC Mod 5952 (SD3-30)* or 6786(C23A)* may be operated using a Collins APS-65 Autopilot adhering to the limitation and procedures detailed in the Airplane Flight Manual. * Refer to Equipment for Airplane Flight Manual required. NOTE 22. SD3-60 airplanes incorporating Short Brothers CMC Mod 7734* "Installation of a Low Pressure Tire, must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual." * Refer to Equipment for Airplane Flight Manual required. 27 A41EU NOTE 23. SD3-60 airplanes incorporating Short Brothers CMC Mod A8096 may be operated at the following maximum weights: Maximum ramp weight 27,200 lbs Maximum take-off weight 27,100 lbs Maximum landing weight 26,500 lbs *Refer to Equipment in this data sheet for the SD3-60 Airplane Flight Manual required. Forward CG Limits: The following revised forward CG limits must be observed when operating at the above weights: T.O & Landing En-Route Landing Gear Extended Landing Gear Retracted Fwd of Datum % SMC Fwd of Datum % SMC (in) (in) Forward Limit at: Maximum Landing -2.97(Fwd) 19.0 Weight Maximum Take-off Weight -2.24(Fwd) 20.0 -5.35(Fwd) 15.72 NOTE 24. SD3-60 airplanes incorporating Short Brothers CM C Mod A8064 have the following aileron control surfaces movement: Aileron 27 ¼º ± ½º up 14 ¼º ± ½º down Aileron Trim 8 ½º ± 1º up 8 ½º ± 1º down NOTE 25. On SD3-60 Airplanes: 2 Pratt and Whitney aircraft of Canada Limited Model PT6A-67R engines may be installed in accordance with Short Brothers PLC CMC Mod No. A8077. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 26. On SD3-60 Airplanes: 2 Hartzell HC-A6A-3/A10460E propellers may be installed in accordance with Short Brothers PLC CMC Mod No *A8059 * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 27. On SD3-60 Airplanes: Cambered Struts may be installed in accordance with Short Brothers PLC CMC Mod No. 7784. NOTE 28. On SD3-60 Airplanes: Collins Pro-line 2 Avionics may be installed in accordance with Short Brothers PLC CMC Mod No A8062. NOTE 29. SD3-60 Airplanes incorporating Short Brot hers CMC Modification A8310, "Air conditioning: To introduce Freon Cooling for in flight use", must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 30. SD3-60 Airplanes incorporating Short Brothers CM C Modification A8123, "Installation of a Collins APS-65 Autopilot", must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 31. SD3-60 Airplane incorporati ng Short Brothers CMC Modification A8123 and A8283 which install a Collins APS65 Autopilot without Yaw Damper installation, must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. 28 A41EU NOTE 32. SD3-60 Airplanes incorporating Short Brothers CMC M odification A8268, "Electrics: Revised color markings on oil temperatures/pressure gauge" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. The temperature limits given in Note 11 still apply. NOTE 33. SD3-60 Airplanes incorporating Short Brothers CM C Modification A8320, "Electrics: Revised Torque Gauge Markings" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 34. SD3-60 Airplanes incorporating Short Brothers CMC M odification A8428, "To alter the Flight Idle/Flight Fuel Gas Generator Speed on the Engine Limitation Label" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual." * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 35. SD3-30 Airplanes or SD3-60 Airplanes incorpor ating Short Brothers CMC Modification No. 4731or A8243 respectively, "Electrics: Revised Power Source for Pitot Static Heaters", must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 36. SD3-60 Airplanes incorporating Short Brothers CM C Modification A8286, "Electrics: Automatic switch off for emergency lighting" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 37. SD3 Sherpa airplanes that have an IFF Transponder AN/APX 100(V) installed in the nose baggage compartment must not carry cargo exceeding 400 lbs in the nose baggage compartment and must have the appropriate loading limitations placard installed in accordance with the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 38. SD3 Sherpa airplanes that are to be operated with the rear ramp door open in flight must be operated in accordance with the limitations and procedures detailed in Supplement 11 of the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 39. SD3-30 Airplanes or SD3-60 Airplanes incorpora ting Short Brothers CMC Modification No. 4751 or A8611 respectively "To prevent inadvertent operation of the L.P. fuel levers" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 40. SD3-30 Airplanes incorporating e ither Short Brothers CMC Modification No. 6910 or 6946 (C-23A) "Introduction of low fuel level warning system" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. *Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 41. SD3-30 Airplanes incorporating Short Brothers CMC Modification No. 5763 "Installation of Collins 562-8F yaw damper" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 42. SD3 Sherpa Airplanes incorporating Short Brothers CMC Modification No. K2061 relating to the introduction of a long range ferry fuel system must be operated in accordance with the limitations and procedures detailed in the appropriate Airplane Flight Manual Supplement No. 2 relates to the two tank installation and Supplement No. 13 relates to the one tank installation. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 43. SD3-60 Airplanes incorporating Short Brothers CMC Modification No. 7264 "To provide indication of propeller heating in the transfer mode" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. 29 A41EU NOTE 44. SD3-60 Airplanes incorporating Short Brothers CMC Modification No A7114 "Revised illumination of the Fire warning light on the L.P. fuel levers" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 45. SD3-60 Airplanes incorporating Short Brothers CM C Modification No. A7985 "Revised elevator trim indicator markings" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 46. SD3-60 Airplanes incorporating Short Brothers CMC M odification No A7767 "Installation of a low fuel level warning system" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 47. SD3-60 Airplanes incorporating Short Brothers CMC Modification No A7986 "Revised elevator trim indicator markings" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 48. SD3-60 Airplanes incorporating Short Brothers CMC M odification No A7583 "Installation of Safe Flight 796-2 stall warning vane" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 49. SD3-60 Airplanes which have been upgraded by th e installation of PT6A-65AR engines under Modification No A7543 (refer to NOTE 16) and which have not incorporated Short Brothers CMC Modification No A7479 "Installation of Graviner Firewire System" or SD3-60 Airplanes with PT6A-65R engines which have incorporated CMC Modification No A7479 must be operated in accordance with the limitations and procedures detailed in the respective Airplane Flight Manual. * Refer to Equipment in this data sheet for the respective Airplane Flight Manual standard required. NOTE 50. SD3-60 Airplanes incorporating Short Brothers CM C Modification No. A8574 "Engine propeller speed tolerance change" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 51. SD3-60 Airplanes incorporating Short Brothers CMC Modification No A8575 "Introduction of Autofeather disarm feature on final approach" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual standard required. NOTE 52. SD3 Sherpa Airplanes incorporating Short Brothe rs CMC Modification No K2161 "Installation of UNS-1A Flight Management System" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual Supplement. * Refer to Equipment in this data sheet for the Airplane Flight Manual Supplement required. NOTE 53. SD3-60 Airplanes using HC-A6A-3 propellers are a pproved for operation with the following blade models installed. A10460E An internal de-icing element only is installed. A10460K An internal de-icing element only is installed. A10460EK An external de-icing element is installed under Hartzell Service Instruction No 187. Blade model A10460E must not be intermixed with A10460EK or A10460K models on the same propeller. Blade models A10460K and A10460EK may be intermixed on the same propeller as long as their weights (for balance) are compatible. NOTE 54. SD3-60 Sherpa Airplanes that are to be operated with the rear ramp door open in flight must be operated in accordance with the limitations and procedures detailed in Supplement 11 of the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual Supplement required. 30 A41EU NOTE 55. SD3-60 Sherpa Airplanes incorporating Short Brothers CMC Modification No K6033 relating to the introduction of a long range ferry fuel system must be operated in accordance with the limitations and procedures detailed in Supplement No. 1 of the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual Supplement required. NOTE 56. SD3-60 Sherpa Airplanes incorporating Short Br others CMC Modification No K6043 "Installation of UNS- 1A Flight Management System" must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Supplement Manual. NOTE 57. SD3-60 Sherpa airplanes that have an IFF Transponder AN/APX 100(V) installed in the nose baggage compartment must not carry cargo exceeding 400 lbs in the nose baggage compartment and must have the appropriate loading limitations placard installed in accordance with the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual required. NOTE 58. SD3-60 Sherpa airplanes (Mod K6001) Certificati on Basis as defined by this TCDS includes Amendment 25.61 and Amendment 25.66. This requirement is applied to all new furnishings introduced by the modifications for conversion of the aircraft but not applied to the existing furnishings being refitted to the SD3-60 Sherpa aircraft (Mod K6005). NOTE 59. SD3-30, SD360 and SD3 Sherpa Airplanes incorp orating Short Brothers CMC Modification No. P4778, A8633, and K2219 respectively “Introduction of changes to fire extinguishing point placards” must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. *Refer to Equipment in this data sheet for the Airplane Flight Manual Standard required. NOTE 60. SD3-30 and SD3-60 Airplanes incorporating Short Brothers CMC Modification No 4816 and 8703 respectively “Introduction of a Flight Deck operated baggage bay fire suppression system”, to meet the requirements of FAR 121.314(c) must be operated in accordance with the limitations an procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual Standard required. NOTE 61. SD3-30, SD360, SD3 Sherpa and SD360 Sherpa Airp lanes incorporating Short Brothers CMC Modification No. P4817, A8700 K2242 and K6112 respectively “Introduction of a supplemental pressure caution system in the pneumatic de-icing system” must be operated in accordance with the limitations and procedure detailed tin the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual Standard required. NOTE 62. SD3-30, SD360, SD3 Sherpa and SD360 Sherpa Airp lanes incorporating Short Brothers CMC Modification No. P4820, A8709, K2247, and K6117 respectively “Introduction of a modified fire extinguisher adapter” must be operated in accordance with the limitations and procedure detailed in the Airplane Flight Manual NB Supercedes Shorts Brothers CMC Modifications, P4778, A8633, and K2219 when embodied. * Refer to Equipment in this data sheet for the Airplane Flight Manual Standard required. NOTE 63. SD3-30, SD360, SD3 Sherpa and SD360 Sherpa Airp lanes incorporating Short Brothers CMC Modification No. 4818, 8707, K2245 and K6115 respectively “Introduction of an ice vane annunciator on the central warning panel”, must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual. * Refer to Equipment in this data sheet for the Airplane Flight Manual Standard required. NOTE 64. SD3-30, Airplanes approved for operating on gravel runways, must be operated in accordance with the limitations and procedures detailed in the Airplane Flight Manual, reference document No. SBH.3.6 Supplement No. 15 “Limitations, Procedures, and information association with gravel runway operations Mod P4825” * Refer to Equipment in this data sheet for the Airplane Flight Manual Standard required. .....END..... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Short Bros SD3-60 VARIANT 200](https://openairdocs.org/model/short-bros-sd3-60-variant-200): 4 aircraft (registry code 8100633) - [Short Brothers SD3-SHERPA VAR 200](https://openairdocs.org/model/short-brothers-sd3-sherpa-var-200): 1 aircraft (registry code 8110609) ## STCs approved under this data sheet (77, first 50) - [STC SA2797CE](https://openairdocs.org/stc/SA2797CE): Removal of left rear side door and replace with an inward opening door assembly.. Exclusive Aviation Services, Inc. - [STC ST00055WI](https://openairdocs.org/stc/ST00055WI): Install Tail Cone door. Exclusive Aviation Services, Inc. - [STC ST04328NY](https://openairdocs.org/stc/ST04328NY): The Manufacture and Installation of Exterior Placards, Labels and Signs is to be performed, installed. Libellule Monde Inc - [STC ST03875NY](https://openairdocs.org/stc/ST03875NY): Installation of interior placards, signs and markings. Libellule Monde Inc. - [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 ST02800SE](https://openairdocs.org/stc/ST02800SE): Removal of performance penalty when operating with jump door wind deflector installed. P4 Engineering PLLC - [STC ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC - [STC ST03536AT](https://openairdocs.org/stc/ST03536AT): Installation of a Universal Avionics UNS-1L Flight Management System and associated hardware.. Woven Electronics, LLC - [STC SA910GL](https://openairdocs.org/stc/SA910GL): Install Aircraft Wheel and Brake nose wheel conversion kit 199-139.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC ST11285DS](https://openairdocs.org/stc/ST11285DS): An update to the existing Collins Aerospace Integrated Flight Information System (IFIS) FSU-5010 and upgrade the existing XMWR-1000 to a XMWR-1000S (Sirius XM) in Part 25.. BHE & Associates Ltd. - [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS - [STC ST04185NY](https://openairdocs.org/stc/ST04185NY): Installation of LAI Heated Windshield Assemblies. Aerospace Design & Compliance LLC - [STC ST04423AT](https://openairdocs.org/stc/ST04423AT): Modification of Short Brothers SD3-60 Sherpa to include incorporation of OEM static line and support structure, paratroop door modification, seating configuration, door edge protector and battery vent tube. U.S. Department of Agriculture--Forest Service - [STC ST11071SC](https://openairdocs.org/stc/ST11071SC): Demonstration of aircraft critical equipment and antenna systems tolerance of radio frequency interference (RFI) from intentional or spurious transmissions from certain Portable Electronic Devices (PEDs). Liberty Partners Inc - [STC SA03973NY](https://openairdocs.org/stc/SA03973NY): Replacement of existing TCAS 7.0 by TCAS 7.1. Scandinavian Avionics Design ApS - [STC ST00423WI](https://openairdocs.org/stc/ST00423WI): Installation of Keddeg Company 21BC111 Coalescer Assembly.. Purolator Facet, Inc - [STC ST00881WI-D](https://openairdocs.org/stc/ST00881WI-D): Modification of a TCAS II system installation to Change 7.0 or Change 7.1. Rockwell Collins Inc - [STC ST01790WI](https://openairdocs.org/stc/ST01790WI): Installation of the Garmin TCAS II System.. 3S Certification LLC - [STC ST00365CH](https://openairdocs.org/stc/ST00365CH): Install Class E cargo compartment. Air Cargo Carriers LLC - [STC ST01675WI](https://openairdocs.org/stc/ST01675WI): Modification of a Rockwell Collins, Inc. File Server Unit (FSU) installation. Rockwell Collins Inc - [STC ST03149CH](https://openairdocs.org/stc/ST03149CH): Installation of sensor mounting support structures on the nose of the Shorts SD3-60 model aircraft. FedEx Express - [STC SA3965NM](https://openairdocs.org/stc/SA3965NM): Installation of a de-icing system on the Dunlop P/N ACA1192 engine inlet cowl .. ROBERT W. MURRAY - [STC SA3705SW](https://openairdocs.org/stc/SA3705SW): Installation of Floor Proximity Lighting System in accordance with Vista Manufacturing, Inc. Drawing number SD3-1000, Revision B, dated December 2, 1986, or later FAA approved revision.. BF Goodrich Aerospace - [STC ST01708LA](https://openairdocs.org/stc/ST01708LA): Installation of MASS Systems fire extinguisher, P/N M57331-009, as a replacement for the Graviner fire extinguisher, P/N 57331-009 in the above-noted airplane model. This fire extinguisher is in accordance with MASS Systems Drawing No. M57331-009, Fire Extinguisher, 52 cu-in , Revision B, dated November 19, 2004, or later FAA approved revisions.. AMETEK AMERON LLC d/b/a MASS Systems - [STC ST01202WI-D](https://openairdocs.org/stc/ST01202WI-D): Modification of an existing FAA approved Collins TPR-720, TPR-900 or TPR-901 Mode S transponder installation in Part 25 Aircraft using Collins Drawing Index as listed on AML No. ST01202WI-D, latest FAA approved revision.. Rockwell Collins Inc - [STC ST02891CH](https://openairdocs.org/stc/ST02891CH): Installation of a Surveillance System according to FedEx Express Master Drawing Lists document number 10-037, Rev. A dated 9-16-2010 or later FAA approved revisions.. Air Cargo Carriers Inc - [STC ST00054MC-D](https://openairdocs.org/stc/ST00054MC-D): Installation of Rockwell Collins, Inc. Pro Line 21 Avionics System. Rockwell Collins Inc - [STC ST00718WI-D](https://openairdocs.org/stc/ST00718WI-D): Installation of Dual Universal UNS-1K Flight Management System.. Duncan Aviation Inc - [STC SA2669CE-D](https://openairdocs.org/stc/SA2669CE-D): Installation of Rockwell Collins Traffic Alert and collistion Aviodance System (TCAS II).. Rockwell Collins Inc - [STC SA5207NM](https://openairdocs.org/stc/SA5207NM): Installation of Honeywell Mode S Transponder.. Learjet Inc - [STC SA5208NM](https://openairdocs.org/stc/SA5208NM): Installation of Honeywell vertical speed indicator/traffic resolution advisory (VSI/TRA) displays. STC SA4596NM-D required for provisions installment.. Learjet Inc - [STC SA5209NM](https://openairdocs.org/stc/SA5209NM): Installation of Honeywell TCAS II system. STC SA4596NM-D required for provisions installment. STC SA5207NM and SA5208NM required for Mode S transponder and VSI/TRA displays installation.. Learjet Inc - [STC SA1094GL](https://openairdocs.org/stc/SA1094GL): Installation of Grimes floor proximity lighting system, P/N 10-1309-37 in SD3-30 airplanes and P/N 10-1309-57 in SD3-60 airplanes.. Honeywell International Inc. - [STC SP00400SE](https://openairdocs.org/stc/SP00400SE): Installation of various propeller electrical de-icer models. SMR Technologies - [STC ST01468CH](https://openairdocs.org/stc/ST01468CH): Installation of various SMR Technologies electrical propeller deicer models.. SMR Technologies - [STC ST00844WI-D](https://openairdocs.org/stc/ST00844WI-D): Modification of Collins TCAS II or TCAS-94 (TCAS II) system installation with Collins TTR-920 Change 7.0 Receiver Transmitter to a Collins TCAS II or TCAS-94 OTCAS II) system installation with Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS Receiver Transmitter.. Rockwell Collins Inc - [STC ST01307WI-D](https://openairdocs.org/stc/ST01307WI-D): Modification of a Collins TVI-920/TVI-920D Vertical Speed/TCAS Indicator installation. Rockwell Collins Inc - [STC ST03080AT](https://openairdocs.org/stc/ST03080AT): Installation of a Honeywell MK VI Enhanced Ground Proximity Warning Systems (EGPWS).. Chippewa Aerospace, Inc. - [STC ST00906SE](https://openairdocs.org/stc/ST00906SE): Interior and flight deck modifications in accordance with Aero Air, LLC Master Drawing List AEA 330-0001, Revision I, dated April 9, 2001, and avionics Master Drawing List AEA 330-3000, Revision E, dated April 9, 2001, or later FAA approved revisions. Additionally, an all cargo interior is approved per Arctic Air Group, Inc. Drawing ACA237-91, Revision IR, dated August 7, 2003, or later FAA approved revisions. (SD3-30 Variant 200). Arctic Air Group Inc. - [STC ST01835NY](https://openairdocs.org/stc/ST01835NY): Installation of Enhanced Security Cockpit Doors.. TAG Aerospace Inc. - [STC SA00823CH](https://openairdocs.org/stc/SA00823CH): Installation of various de-icer wire harnesses.. SMR Technologies - [STC SA4596NM-D](https://openairdocs.org/stc/SA4596NM-D): Installation of provisions for Honeywell TCAS/Mode S/VSI/TRA system.. Learjet Inc - [STC ST01069SE](https://openairdocs.org/stc/ST01069SE): Removal of a Cockpit Voice Recorder and Flight Data Recorder in accordance with Corporate Air Instructions for Accomplishment, dated March 29, 2002, or later FAA approved revision.. Corporate Air - [STC SA00970CH](https://openairdocs.org/stc/SA00970CH): Installation of various SMR Technologies electrical propeller de-icer models.. SMR Technologies - [STC SA01384CH](https://openairdocs.org/stc/SA01384CH): Installation of various de-icer harnesses.. SMR Technologies - [STC SA3749SW](https://openairdocs.org/stc/SA3749SW): Installation of air conditioning system.. AAR Airframe and Accessories Group - [STC ST01615AT](https://openairdocs.org/stc/ST01615AT): Installation of a Class E cargo compartment interior.. Sky Way Enterprises, Inc - [STC ST00718WI](https://openairdocs.org/stc/ST00718WI): Installation of the Dual Universal UNS-1K Flight Management System in the Shorts Brothers PLC, SD 3-30 Variant 200 and SD3-60 Variant 200 Airplanes.. Duncan Aviation, Inc - [STC SA4972SW](https://openairdocs.org/stc/SA4972SW): Installation of DeVore 'TEL-TAIL' tail floodlights.. DeVore Aviation Corporation of America, a New Mexico Corporation - [STC ST00882AT-D](https://openairdocs.org/stc/ST00882AT-D): Installation and operation of a B.F. Goodrich TCAS 791 System.. Freedom Air All 77: https://openairdocs.org/tcds/A41EU/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.