TCDS A43EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. No. 11 8 8 8 8 8 8 8 8 8 8 8 8 8 12 9 8 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A43EU Revision 12 Airbus Defense and Space S.A. Model: C-212-CB C-212-CC C-212-CD C-212-CE C-212-CF C-212-DF C-212-DE July 23, 2021 TYPE CERTIFICATE DATA SHEET NO. A43EU This data sheet, which is a part of Type Certificate No. A43EU, 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 Airbus Defense and Space S.A. (formerly known as Construcciones Aeronauticas, S.A.) Apartado 193 Madrid, Spain I - Model C-212-CB (Transport Category Airplane) approved February 22, 1977 Engines 2- Garrett Turbine Engine Co. Model TPE331-5-251C Turboprop engines. Fuel Prop. Shaft/Eng. Rotor Ratio: 1/26.2287. See Airplane Flight Manual for approved fuels, alternate fuels and approved fuel additives. Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and Type II). See approved AFM for a list of approved engine lubricating oils. Engine Limits Conditions SHP ESHP RPM (%) ITT (°C) Takeoff (5 minutes) 750 808 100 923 Max. Continuous 715 776 100 923 Transient temperature (ITT) limit (1 sec.) 1149°C. Transient overspeed limits: 105.5% for 30 sec.; 106% for 5 sec. 100% RPM is defined as 41,730 engine rotor speed, 1591 propeller shaft speed. See INTA-approved Airplane Flight Manual, Document D.T. 76-2501, for additional information. Propeller and Propeller Limits 2 Hartzell Model HC-B4TN-5CL, constant speed hydraulic full feathering reversible propellers. Blades: 4, Model LT 10282 HB + 4 Diameter: 107.5 in. Hard and soft alloy blades of the same model designation may not be intermixed. For % R. P.M. at windmilling see INTA-approved Airplane Flight Manual Document D.T. 76-2501. A 43EU 2 I - Model C-212-CB (cont’d) Blade angle measured at 30-in. radius station: Feathered 89.0° ± 1.0° Flight Idle 13.5° ± 0.2° Start Locks 2.5° + 0° - 0.5° Full Reverse -6.5° ± 0.5° Speed Knots IAS Airspeed Limits VMO (Max. Operating) (S.L. -25000 ft) 200 VA (Maneuvering) 146 VFE (Flaps Extended) Takeoff 25% 125 Approach 50% 120 Landing 100% 100 VMC (Min. control speed) 78 C.G. Range Weight (lb) FWD % MAC AFT % MAC 14332 17.4 30.0 13781 16.9 30.0 12678 16.0 30.0 Straight line variation between points given. Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of the fuselage. The C.G. reference datum is situated 43.90 in. forward of the jig point. M.A.C. Length is 86.22 in. The leading edge of M.A.C. is 215.04 in. aft of datum. Leveling Means Plumb-bob provision on aft face of aft cockpit compartment bulkhead. Maximum Weights Takeoff: 14332 lb. Landing: 13781 lb. MZFW: 13230 lb. Minimum Crew The minimum flight crew is two pilots. Maximum Passengers 19 - limited by Emergency Exit Requirements of FAR 25.807 (c) Maximum Baggage Aft baggage comp: 662 lb. total - maximum floor loading: 120 lb/sq. ft 470 lb/linear ft. Baggage and/or cargo load must comply with loading limitations of approved Airplane Flight Manual, and must be loaded in accordance with loading instructions of Weight and Balance Supplement to the INTA-approved Airplane Flight Manual. Fuel Capacity Total Capacity: 548.00 U.S. gal. in two wing tanks Usable fuel: 528.00 U.S. gal. Unusable fuel: 20.00 U.S. gal. (See NOTE I (b) and I (c) for data on system fuel and oil) Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank Unusable oil: (NONE) Maximum Approved Operating Altitude 25,000 ft. A43EU 3 I - Model C-212-CB (cont’d) Control Surface Movement Elevator 30° Up 20° Down Elevator trim tab 15.5° Up 21° Down Rudder 25° Right 25° Left Rudder trim tab 17.5° Right 19° Left Aileron 20° Up 20° Down Aileron trim tab 15° Up 15° Down Flaps, Inner and Outer 10° Down - takeoff 20° Down - approach 40° Down - landing All measurements taken at trailing edge from neutral position. For details of tolerance on control surface movement refer to document D.T. 77.2101. II. Model C-212-CC (Transport Category Airplane) approved May 16, 1980 The C-212-CC Model is similar to the C-212-CB Model except for powerplant installation, gross weight and seating capacity. Engines 2 - Garrett Turbine Engine Co. Model TPE331-10-501C or TPE331-10R -501C Turboprop engines, or 2 - Model TPE331-10-511c or TPE311-10R -511C Turboprop engine. Prop. Shaft/Eng. Rotor Ratio: 1/26.2287 Fuel See AFM for approved fuels, alternate fuels and approved fuel additives. Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and Type II). See approved AFM for a list of approved engine lubricating oils. Engine Limits Conditions SHP ESH P % RPM EGT (°C) Takeoff (initial) (5 minutes) 900 944 100 650 Takeoff (APR on) (5 minutes) 900 944 100 650 Max. Continuous 900 944 100 650 Transient overspeed limits: 105.5% for 30 sec.; 106% for 5 sec. 100% RPM is defined as 41,730 rpm engine rotor speed, 1591 rpm propeller shaft speed. Transient temperature (EGT) limit (1 sec.): 770°C See INTA-approved Airplane Flight Manual, Document D.T. 78-2501, for additional information. Propeller and Propeller Limits 2 Hartzell Model HC-B4MN-5AL, constant speed hydraulic full feathering, reversible propellers. Blades: 4, Model LM 10585 B + 4 Diameter: 110 in. For %RPM as windmilling see INTA-approved Airplane Flight Manual, Document D.T. 78-2501. Blade angle measured at 42- in. radius station: Feathered 83.0° ± 1.0° Flight Idle 7.0° ± 0.3° Start Locks -1.5° ± 0.2° Full Reverse -10° ± 0.5° A 43EU 4 II. Model C-212-CC (cont’d) Speed Knots IAS Airspeed Limits VMO (Max. Operating) (S.L. -25.000 ft) 200 VA (Maneuvering) 146 VFE (Flaps extended) Takeoff 25% 135 Approach 37.5% 130 Landing 100% 115 VMC (Min. Control) 85 C.G. Range Weight (lb) FWD % MAC AFT % MAC 16,976 16.00 30.00 16,424 15.90 30.00 11,051 15.00 30.00 9,481 15.00 30.00 Straight line variation between points given. Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of the fuselage. The C.G. reference datum is situated 43.90 in. forward of the jig point. M.A.C. Length is 86.22 in. The leading edge of M.A.C. is 215.04 in. aft of datum. Leveling Means Plumb-bob provisions on aft fact of aft cockpit compartment bulkhead. Maximum Weights Ramp: 17,086 lb. Takeoff: 16,976 lb. Landing: 16,424 lb. MZFW: 15,653 lb. Minimum Crew The minimum flight crew is two pilots Maximum Baggage Aft baggage comp.: 882 lb. Total - maximum floor loading: 120 lb/sq. ft. 470 lb/linear ft. Baggage and/or cargo load must comply with loading limitations of approved Airplane Flight Manual, and must be loaded in accordance with loading instructions of Weight and Balance Supplement to the INTA-approved Airplane Flight Manual. Fuel Capacity Total capacity: 548.00 U.S. gal. in two wing tanks Usable fuel: 528.00 U.S. gal. Unusable fuel: 20.00 U.S. gal. (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank Unusable oil: (NONE) Maximum Approved Operating Altitude 25,000 ft. A43EU 5 II. Model C-212-CC (cont’d) Control Surface Movements Elevator 30° Up 20° Down Elevator Trim Tab 15.5° Up 21° Down Rudder 27.5° Right 27.5° Left Ruddeer Trim Tab 12.5° Right 19° Left Aileron 20° Up 15° Down Aileron Trim Tab 15° Up 15° Down Flaps, Inner and Outer 10° Down - Takeoff 15° Down - Approach 40° Down - Landing All measurements taken at trailing edge from neutral position. For details of tolerances on control surface movement refer to document D.T. 77-2101. Maximum Passengers 28 - limited by space available for accommodation. III. Model C-212-CD (Transport Category Airplane) approved September 6, 1985 The C-212-CD model is similar to the C-212-CC Model except for powerplant installation. Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-502C or TPE331-10R-512C (See NOTES 5 & 6) Turboprop engines. Prop. Shaft/Eng. Rotor Ratio: 1/26.2287 Fuel See AFM for approved fuels, alternate fuels and approved fuel additives. Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and Type II). See approved AFM for a list of approved engine lubricating oils. Engine Limits Conditions SHP ESHP % RPM EGT (°C) Takeoff (initial) (5 minutes) 900 944 100 650 Takeoff (APR on) (5 minutes) 900 944 100 650 Max. Continuous 900 944 100 650 Transient overspeed limits: 105.5% for 30 sec.; 106% for 5 sec. 100% RPM is defined as 41.730 rpm engine rotor speed, 1591 rpm propeller shaft speed. Transient temperature (EGT) limit (1 sec.): 770°C. See INTA-approved Airplane Flight Manual, Document D.T. 83-2501, for additional information. Propeller and Propeller Limits 2 Dowty Rotol Model (c) R.334/4-82-F/13 hydraulic full feathering, constant speed reversible propellers. Blades: 4, serial number 660709314 Diameter: 110 in. For % RPM at windmilling see INTA-approved Airplane Flight Manual, Document D.T. 83-2501. Blade angle measured at 35.333 in radius station: Feathered 82°30’ ± 20’ Flight Idle 9° ± 20’ Start Locks -1°45’ ± 0°30’ Full Reverse -13° ± 1° A 43EU 6 III. Model C-212-CD (cont’d) Speed Knots IAS Airspeed Limits VMO (Max. Operating) (S.L. -25,000 ft.) 200 VA (Maneuvering) 146 VFE (Flaps Extended) Takeoff 25% 135 Approach 37.5% 130 Landing 100% 115 VMC (Min. Control) 85 C.G. Range Weight (lb) FWD % MAC AFT % MAC 16,976 16.0 30.0 16,424 15.9 30.0 11,051 15.0 30.0 9,481 15.0 30.0 Straight line variation between points given. Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of the fuselage. The C.G. reference datum is situated 43.90 in. forward of the jig point. M.A.C. Length is 86.22 in. The leading edge of M.A.C. is 215.04 in. aft of datum. Leveling Means Plumb-bob provisions on aft face cockpit compartment bulkhead. Maximum Weights Ramp: 17,086 lb. Takeoff: 16,976 lb. Landing: 16,424 lb. MZFW: 15,653 lb. Minimum Crew The minimum flight crew is two pilots. Maximum Baggage Aft baggage comp.: 882 lb. Total - maximum floor loading: 120 lb/sq. ft. 470 lb/linear ft. Baggage and/or cargo load must comply with loading limitations of approved Airplane Flight Manual, and must be loaded in accordance with loading instructions of Weight and Balance Supplement to the INTA-approved Airplane Flight Manual. Fuel Capacity Total capacity: 548.00 U.S. Gal. in two wing tanks Usable fuel: 528.00 U.S. Gal. Unusable fuel: 20.00 U.S. Gal. (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). Oil Capacity Usable Oil: 5.25 U.S. quarts in each engine tank Unusable Oil: None Maximum Approved Movement 25,000 ft. Control Surface Movement Elevator 30° Up 20° Down Elevator Trim Tab 15.5° Up 31° Down Rudder 27.5° Right 27.5° Left Rudder Trim Tab 12.5° Right 19° Left Aileron 20° Up 20° Down Aileron Trim Tab 15° Up 15° Down Flaps, Inner and Outer 10° Down - Takeoff 15° Down - Approach 40° Down - Landing All measurements taken at trailing edge from neutral position. For details of tolerances on control surface movement refer to document D.T. 77-2101. Maximum Passengers 28 - limited by space available for accommodation. A43EU 7 IV. Model C-212-CE (Transport Category Airplane) approved September 9, 1985 The C-212-CE model is similar to the C-212-CD model except for incorporation of CASA Modification No. PP0956 or PP1012 which enables engine operation at a higher Takeoff (APR on) rating. Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-502C or TPE331-10R-512C (See NOTES 5 & 6) Turboprop engines. Prop. Shaft/Eng. Rotor Ratio: 1/26.2287 Fuel See AFM for approved fuels, alternate fuels and approved fuel additives Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and Type II). See approved AFM for a list of approved engine lubricating oils. Engine Limits Conditions SHP ESHP % RPM EGT (°C) Takeoff (initial) (5 minutes) 900 944 100 650 Takeoff (APR on) (5 minutes) 925 970 100 650 Max. Continuous 900 944 100 650 Transient overspeed limits: 105.5% for 30 sec.; 106% for 5 sec. 100% is defined as 41,730 rpm engine rotor speed, 1591 rpm propeller shaft speed. Transient temperature (EGT) limit (1 sec.): 770°C. See INTA-approved Airplane Flight Manual, Document D.T. 84-2501, for additional information. Propeller and Propeller Limits 2 Dowty Rotol Model (c) R.334/4-82-F/13 hydraulic full feathering, constant speed reversible propellers. Blades: 4, serial number 660709314 Diameter: 110 in. For % RPM at windmilling see INTA-approved Airplane Flight Manual, Document D.T. 84-2501. Blade angle measured at 35.333 in radius station: Feathered 82°30’ ± 20’ Flight Idle 9° ± 20’ Start Locks -1°45’ to 0°30’ Full Reverse -13° ± 1° Speed Knots IAS Airspeed Limits VMO (Max. Operating) (S.L. -25.000 ft) 200 VA (Maneuvering) 146 VFE (Flaps extended) Takeoff 25% 135 Approach 37.5% 130 Landing 100% 115 VMC (Min. Control) 88 C.G. Range Weight (lb) FWD % MAC AFT % MAC 16,976 16.0 30.0 16,424 15.9 30.0 11,051 15.0 30.0 9,481 15.0 30.0 Straight line variation between points given. A 43EU 8 IV. Model C-212-CE (cont’d) Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of the fuselage. The C.G. reference datum is situated 43.90 in. forward of the jig point. M.A.C. Length is 86.22 in. The leading edge of M.A.C. is 215.04 in. aft of datum. Leveling Means Plumb-bob provisions on aft fact of aft cockpit compartment bulkhead. Maximum Weights Ramp: 17,086 lb. Takeoff: 16,976 lb. Landing: 16,424 lb. MZFW: 15,653 lb. Minimum Crew The minimum flight crew is two pilots. Maximum Baggage Aft baggage comp.: 882 lb. Total - Maximum floor loading: 120 lb/sq. ft. 470 lb/linear ft. Baggage and/or cargo load must comply with loading limitations of approved Airplane Flight Manual, and must be loaded in accordance with loading instructions of Weight and Balance Supplement to the INTA-approved Airplane Flight Manual. Fuel Capacity Total capacity: 548.00 U.S. Gal. in two wing tanks Usable fuel: 528.00 U.S. Gal. Unusable fuel: 20.00 U.S. Gal. (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank Unusable oil: None Maximum Approved Operating Altitude 25,000 ft. Control Surface Movements Elevator 30° Up 20° Down Elevator Trim Tab 15.5° Up 31° Down Rudder 27.5° Right 27.5° Left Rudder Trim Tab 12.5° Right 19° Left Aileron 20° Up 20° Down Aileron Trim Tab 15° Up 15° Down Flaps, Inner and Outer 10° Down - Takeoff 15° Down - Approach 40° Down - Landing All measurements taken at trailing edge from nuetral position. For details of tolerance on control surface movement refer to document D.T. 77-2101. Maximum Passengers 28 - limited by space available for accommodation. A43EU 9 V. Model C-212-CF (Transport Category Airplane) approved December 6, 1985 The C-212-CF model is similar to the C-212-CC model with the same engine except for incorporation of CASA Modification No. PP0956 or PP1012 which enables engine operation at a higher Takeoff (APR on) rating. Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-501C or TPE331-10R-511C Turboprop engines. Prop. Shaft/Eng. Rotor Ratio: 1/26.2287 Fuel See AFM for approved fuels, alternate fuels and approved fuel additives. Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and Type II). See approved AFM for a list of approved engine lubricating oils. Engine Limits Conditions SHP ESHP % RPM EGT (°C) Takeoff (initial) (5 minutes) 900 944 100 650 Takeoff (ARP on) (5 minutes) 925 970 100 650 Max. Continuous 900 944 100 650 Transient overspeed limits: 105.5% for 30 sec.; 106% for 5 sec. 100% is defined as 41,730 rpm engine rotor speed, 1591 rpm propeller shaft speed. Transient temperature (EGT) limit (1 sec.): 770°C. See INTA-approved Airplane Flight Manual, Document D.T. 84-2502, for additional information. Propeller and Propeller Limits 2 - Hartzell Model HC-B4MN-5AL, constant speed, hydraulic, full feathering, reversible propellers. Blades: 4, Model LM10585B + 4 Diameter: 110 in. For % RPM at windmilling see INTA-approved Airplane Flight Manual, Document D.T. 84-2502. Blade angle measured at 42 in. radius station: Feathered 83.0° ± 1.0° Flight Idle 7.0° ± 0.3° Start Locks -1.5° ± 0.2° Full Reverse -10° ± 0.5° Speed Knots IAS Airspeed Limits VMO (Max. Operating) (S.L. -25,000 ft.) 200 VA (Maneuvering) 146 VFE (Flaps Extended) Takeoff 25% 135 Approach 37.5% 130 Landing 100% 115 VMC (Min. Control Speed) 88 C.G. Range Weight (lb) FWD % MAC AFT % MAC 16,976 16.0 30.0 16,424 15.9 30.0 11,051 15.0 30.0 9,481 15.0 30.0 Straight line variation between points given. A 43EU 10 V. Model C-212-CF (cont’d) Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of the fuselage. The C.G. reference datum is situated 43.90 in. forward of the jig point. M.A.C. Length is 86.22 in. The leading edge of M.A.C. is 215.04 in aft of datum. Leveling Means Plumb-bob provisions on aft face of act cockpit compartment bulkhead. Ramp: 17,086 lb. Takeoff: 16,976 lb. Landing: 16,424 lb. MZFW: 15,653 lb. Minimum Crew The minimum flight crew is two pilots Maximum Baggage Aft baggage comp.: 882 lb. Total - Maximum floor loading: 120lb/sq. ft. 470 lb/linear ft. Baggage and/or cargo load must comply with loading limitations of approved Airplane Flight Manual, and must be loaded in accordance with loading instructions of Weight and Balance Supplement to the INTA-approved Airplane Flight Manual. Fuel Capacity Total capacity: 548.00 U.S. Gal in two wing tanks Usable fuel: 528.00 U.S. Gal. Unusable fuel: 20.00 U.S. Gal. (See NOTE 1 (b) and 1 (c) for data on system fuel oil). Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank. Unusable oil: None Maximum Approved Operating Altitude 25,000 ft. Control Surface Movements Elevator 30° Up 20° Down Elevator Trim Tab 15.5° Up 31° Down Rudder 27.5° Right 27.5° Left Rudder Trim Tab 12.5° Right 19° Left Aileron 20° Up 20° Down Aileron Trim Tab 15° Up 15° Down Flaps, Inner and Outer 10° Down - Takeoff 15° Down - Approach 40° Down - Landing All measurements taken at trailing edge from neutral position. For details of tolerance on control surface movement refer to document D.T. 77-2101. Maximum Passengers 28 - limited by space available for accommodation. VI. Model C-212-DF (Transport Category Airplane) approved March 30, 1989 The C-212-DF model is similar to the C-212-CE except by the modification in the nose, wingtips and vertical tail. Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-502C or TPE331-10R-512C or (See NOTE 7 & 8) TPE331-10R-513C. Prop. Shaft/Eng Rotor Ratio: 1/26.2287. A43EU 11 VI. Model C-212-DF (cont’d) Fuel See AFM for approved fuels, alternate fuels and approve fuel additives. Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and Type II). See approved AFM for a list of approved engine lubricating oils. Engine Limits Conditions SHP ESHP % RPM EGT (°C) Takeoff (initial)(5 minutes) 900 944 100 650 Takeoff (APR on) (5 minutes) 925 970 100 650 Max. Continuous 900 944 100 650 Transient overspeed limits: 105.5% for 30 sec.; 106% for 5 sec. 100% RPM is defined as 41,730 rpm engine rotor speed, 1591 rpm propell er shaft speed. Transient temperature (EGT) limit (1 sec.): 770°C. See DGAC-approved Airplane Flight Manual, Document D.T. 88-2509 for additional information. Propeller and Propeller Limits 2 Dowty Rotol Ltd, Model (c) R.334/4-82-F/13, hydraulic full feathering, constant speed, reversible propellers. Blades: 4, serial number 660709314 Diameter: 110 in. For % RPM at windmilling see DGAC-approved Airplane Flight Manual, Document D.T. 88-2509. Blade angle measured at 35.333-in. radius station: Feathered 82°32’ ± 20’ Flight Idle 9° ± 20’ Start Locks -1°45’ ± 0°30’ Full Reverse -13° ± 1° Speed Knots IAS Airspeed Limits VMO (Max. Operating) (S.L. -25,000 ft.) 200 VA (Maneuvering) 146 VFE (Flaps Extended) Takeoff 25% 135 Approach 25% 135 Landing 100% 115 VMC (Min. Control) 76 C.G. Range Weight (lb) FWD % MAC AFT % MAC 16,976 16.0 30.0 16,424 15.9 30.0 11,051 15.0 30.0 9,481 15.0 30.0 Straight line variation between points given. Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of the fuselage. The C.G. reference datum is situated 43.90 in. forward of the jig point. M.A.C. Length is 86.22 in. The leading edge of M.A.C. is 215.04 in. aft of datum A 43EU 12 VI. Model C-212-DF (cont’d) Leveling Means Plumb-bob provisions on aft face of aft cockpit compartment bulkhead. Maximum Weight Ramp: 17,086 lb. Takeoff: 16,976 lb. Landing: 16,424 lb. MZFW : 15,653 lb. Minimum Crew The minimum crew is two pilots. Maximum Baggage Aft baggage comp.: 882 lb. Total - maximum floor loading: 120 lb/sq. ft. 470 lb/linear ft, Fwd baggage comp.: 309 lb. total Baggage and/or cargo load must comply with loading limitations of approved Airplane Flight Manual, and must be loaded in accordance with loading instructions of Weight and Balance Supplement to the DGAC-approved Airplane Flight Manual. Fuel Capacity Total Capacity: 548.00 U.S. Gal. in two wing tanks Usable Fuel: 528.00 U.S. Gal. Unusable Fuel: 20.00 U.S. Gal. (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank Unusable oil: None Maximum Approved Operating Altitude 25,000 ft. Control Surface Movements Elevator 30° Up 20° Down Elevator Trim Tab 15.5° Up 31° Down Rudder 20° Right 24° Left Rudder Trim Tab 14° Right 14° Left Aileron 20° Up 20° Down Aileron Trim Tab 15° Up 15° Down Flaps, Inner and Outer 10° Down - Takeoff 10° Down - Approach 40° Down - Landing All measurements taken at trailing edge from neutral position. For details of tolerances on control surface movement refer to document D.T. 77-2101. Maximum Passengers 28 - Limited by space available for accommodation. VII. Model C-212-DE (Transport Category Airplane) approved October 1, 1991 Engines 2 - Pratt and Whitney Canada, Model PT6A-65B turboprop engines Propeller Shaft Gear Ratio: 0.0568:1 Fuel Refer to Engine Service Bulletin No. 3032845-72-44 (PWC SB 13044) for listing of approved fuels Oil Refer to Engine Service Bulletin No. 3032845-72-1 (PWC SB 13001) for listing of approved oils. A43EU 13 VII. Model C-212-DE (cont’d) Engine Limits Conditions SHP ESHP PROP % RPM ITT (°C) Takeoff (initial) (5 minutes) 1000 1069 100 820 Max. Continuous 1000 1069 100 810 100% NG is defined as 37,468 rpm. 100% NP is defined as 1,700 rpm (which means a Power Turbine Speed of 29,894 rpm (NF)). Transient temperature (ITT) limit: 1000°C for 5 seconds. See DGAC-approved Airplane Flight Manual, Document D.T. 88-2518, for additional information. Propeller and Propeller Limits 2 McCauley Model 4HFR34C756/106LM, constant speed, hydraulic full feathering, reversible, propellers. Blades: 4, Model 106LM Diameter: 106 in.