TCDS A-765

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 78 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Rev. No. 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 70 Page No. 41 42 43 44 45 46 47 48 Rev. No. 70 70 70 70 70 72 73 77 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-765 Revision 78 Textron Aviation 3N E18S-9700 3NM C-45G,TC-45G 3TM C-45H, TC-45H JRB-6 TC-45J or D18C UC-45J (SNB-5) D18S RC-45J (SNB-5P) E18S G18S H18 November 27, 2017 TYPE CERTIFICATE DATA SHEET NO. A-765 This data sheet which is a part of Type Certificate No. A-765 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 Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016 I. Model D18S, 10 PCLM, Approved April 26, 1946 Engines Two (2) P&W Wasps Jr. SB-3 with one 4-1/2N and one 9N damper each See Item 113 for optional engines Fuel 80/87 minimum grade aviation gasoline Engine Limits Maximum continuous (See Item 605 for (Sea level) 34.5 in. Hg. 2200 rpm (400 hp.) higher limits) Straight line manifold pressure variation with altitude to 5000 ft. 33.5 in. Hg, 2200 rpm (400 hp.) Takeoff (one minute) 36.5 in. Hg, 2300 rpm (450 hp.) A-765 2 Rev. 78 I. Model D18S (cont’d) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 257 mph. (223 knots) Flaps extended 120 mph. (104 knots) Landing gear extended 125 mph. (109 knots) (See Item 208 for higher speed) C.G. Range (Landing (+109.8) to (+117.7) Gear Extended) Moment due to retraction of landing gear is +12000 in.-lb. See Item 605 for higher weight Maximum Weight 8500 lb. with Item 1 installed; 8750 lb. with Item 2 or 5 installed See Item 605 for higher weight No. of Seats Maximum 10 (2 crew at +87). See loading instructions for passenger loading. Anti-ice Fluid 3 gal. (20 lb. at +97) Capacity See Item 502 for optional installation Maximum Baggage Nose compartment: 600 lb. at +28. When auxiliary fuel tank is installed combined weight of fuel and baggage may not exceed 600 lb. Rear compartment: 300 lb. at +243 See Item 407 for additional baggage provisions. See NOTES 2 and 5 Fuel Capacity 202 gal. usable (four tanks in wings, two 76 gal. tanks at +126, two 25 gal. tanks at +155). See Items 108, 115 and 122 for optional fuel tanks. See NOTE 1 for data on system fuel Oil Capacity 17 gal. usable at +93 with Item 1 or 5 14 gal. usable at +94 with Item 2 (8½ gal. total capacity tank in each nacelle. With Item 2, total capacity includes 9.5 lb. feathering oil in each tank) See NOTE 1 for data on system oil Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18° Down 13° Elevator Up 35° Down 25° Aileron trim tab Up 22° Down 19° Aileron Up 38.5° Down 21° Rudder trim tab (S/N A-1 through Right 31° Left 32° A-68 one tab and rudder bungee) Rudder trim tab (S/N A-1 Right 28° to 33° Left 28° to 33° through A-68 left hand rudder tab extension per Dwg. 404-001071 "B" revision. No bungee) Rudder trim tabs (S/N A-69 Right 28° to 33° Left 28° to 33° and up two tabs and no bungee) Rudder Right 25° Left 25° Serial Nos. Eligible A-1 through A-1035 (See rudder trim tab control surface movements). CA-57 only (formerly Canadian Model 3N eligible for certification and redesignation as a D18S when modified per Bristol Aerospace Limited E.R. 2227 except BAL Dwg. 112-84012 not eligible). Required Equipment Items 1 or 2 or 5 or 7 or 8 or 9, 101, 102, 103, 104, 105, 109, 201, 202, 301, 302, 401(a). (Item 105 not required when Item 2 or 5 or 7 or 8 or 9 installed). Rev. 78 3 A-765 II. Model D18C, 10 PCLM, Approved July 16, 1947 Engines Two (2) Continental R9-A Fuel 91 minimum grade aviation gasoline Engine Limits Maximum continuous (Sea level) 41.5 in. Hg, 2300 rpm (500 hp.) Straight line manifold pressure variation with altitude to 4000 ft. 40.0 in. Hg, 2300 rpm (500 hp.) Takeoff (2 minutes) 43.0 in. Hg, 2300 rpm (525 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 256 mph. (222 knots) Flaps extended 120 mph. (104 knots) Landing gear extended 134 mph. (117 knots) C.G. Range (Landing (+109.8) to (+117.7) at 9000 lb. Gear Extended) (+105.0) to (+117.7) at 6487 lb. or less Moment due to retraction of landing gear is +12000 in.-lb. Maximum Weight 9000 lb. No. of Seats Maximum 10 (2 crew at +87). See loading instructions for passenger loading. Anti-icer Fluid Capacity 3 gal. (20 lb. at +97) Maximum baggage Nose compartment: 600 lb. at +28. When auxiliary fuel tank is installed combined weight of fuel and baggage may not exceed 600 lb. Rear compartment: 300 lb. at +243. See Item 407 for additional baggage provisions. See NOTES 2 and 5 Fuel capacity 202 gal. usable (four tanks in wings, two 76 gal. tanks at +126, two 25 gal. tanks at +155). See NOTE 1 for data on unusable fuel Oil capacity 14 gal. usable at +93 (8½ gal. total capacity tank in each nacelle includes 9.5 lb. feathering oil in each tank). See NOTE 1 for data on unusable oil Control surface movements Wing flaps Down 25° or 45° Elevator trim tab Up 20° Down 14° Elevator Up 35° Down 25° Aileron trim tab Up 20° Down 20° Aileron Up 37.5 Down 20° Rudder trim tab Right 30° Left 30° Rudder Right 25° Left 25° Serial Nos. Eligible AA-1 through AA-31 Required Equipment Items 2 or 5 or 7 or 8 or 9, 101, 102, 104, 112, 114, 201, 202, 302, 306, 401(a), 6 00 A-765 4 Rev. 78 III. Model E18S, 10 PCLM, Approved July 19, 1954 Engines Two (2) P&W Military R-985-AN-14B with one 4-1/2N and one 9N damper each (Crankshaft modified for hydraulic propeller, Item 2) See Item 128 for optional engines Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations: Sea level 36.5 in. Hg, 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude to 3500 ft. 35.5 in. Hg, 2300 rpm. (450 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 256 mph. (222 knots) Flaps extended 120 mph. (104 knots) Landing gear extended 160 mph. (139 knots) C.G. Range (landing (+109.8) to (+117.7) at 9300 lb. gear extended) (+107.0) to (+117.7) at 8600 lb. or less Straight line variation between points given Moment due to retraction of landing gear is +12000 in.-lb. Maximum Weight 9300 lb. See Items 126 and 611 for increased weights No. of Seats Maximum 10 (2 crew at +87). See loading instructions for passenger loading. Anti-icer Fluid Capacity 3 gal. (20 lb. at +97). See Item 502 for optional installation. Maximum Baggage Rear compartment: 300 lb. at +271 See NOTES 2 & 5 Fuel Capacity 275 gal. usable (four tanks in wing, two 76 gal. tanks at +126, two 23 gal. tanks at +155; one nose tank 77 gal. at +32) See Item 122 for optional fuel tanks See NOTE 1 for data on unusable fuel Rev. 78 5 A-765 III. Model E18S (cont’d) Oil Capacity 14 gal. usable at +93 with Item 2 17 gal. usable at +93 with Item 5 (8½ gal. total capacity oil tank in each nacelle) With Item 2, total capacity includes 9.5 lb. feathering oil each tank. See NOTE 1 for data on unusable oil Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18 Down 13° Elevator Up 35° Down 25° Aileron trim tab Up 22° Down 19° Aileron Up 33-1/2° Down 21° Rudder trim tab Right 29° Left 29° Rudder Right 25° Left 25° Serial Nos. Eligible BA-1 through BA-402 and BA-497 (See Item 611 for eligibility to convert these airplanes to the Model E18S-9700) Required Equipment Items 2 or 5 or 7 or 8, 101, 102, 103, 104, 109, 117 with Item 2 or 120 with Item 5, 201, 202, 301, 308, 401(a), 415, 601 IV. Model C-45G, TC-45G, C-45H, TC-45H, Approved March 3, 1958; TC-45J or UC-45J (SNB-5), Approved April 10, 1962; RC-45J (SNB-5P), Approved January 14, 1969; 10 PCLM Engines Two (2) P&W Military R-985-AN-14B with one 4-1/2N and one 9N damper each See Item 113 for optional engines Fuel 80/87 minimum grade aviation gasoline Engine (See Item 605 Maximum continuous for higher limits) Sea level 34.5 in. Hg, 2200 rpm. (400 hp.) Straight line manifold pressure variation with altitude to 5000 ft. 33.5 in. Hg, 2200 rpm. (400 hp.) Takeoff (one minute) 36.5 in. Hg, 2300 rpm. (450 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 257 mph. (223 knots Flaps extended 120 mph. (104 knots) Landing gear extended 125 mph. (109 knots) (See Item 208 for higher speed) C.G. Range (landing (+109.8) to (+117.7) gear extended) Moment due to retraction of landing gear is +12000 in.-lb. See Item 605 for revised limits No. of Seats Maximum 10 (2 crew at +87). See loading instructions for passenger loading. Maximum Weight 8500 lb. with Item 1 installed 8750 lb. with Item 2 or 5 installed See Items 605 and 616 for higher weights; TC-45J not eligible Anti-icer Fluid Capacity 3 gal. (20 lb. at +97). See Item 502 for optional installation. A-765 6 Rev. 78 IV. Models C-45G, TC-45G, C-45H, TC-45H (cont’d) Maximum Baggage Nose compartment: 600 lb. at +28. When auxiliary fuel tank is installed combined weight of fuel and baggage may not exceed 600 lb. Rear compartment: 300 lb. at +243. See Item 407 for additional baggage provisions See NOTES 2 & 5 Fuel Capacity 202 gal. usable (four tanks in wings, two 76 gal. tanks at +126, two 25 gal. tanks at +155) See NOTE 1 for data on unusable fuel Oil Capacity 16 gal. usable at +93 with Item 1 or 5 13 gal. usable at +93 with Item 2 (8 gal. capacity tank in each nacelle) With Item 2, total capacity includes 9.5 lb. feathering oil in each tank See NOTE 1 for data on unusable oil Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18° Down 13° Elevator Up 35° Down 25° Aileron trim tab Up 22° Down 19° Aileron Up 38.5° Down 21° Rudder trim tab Right 28° to 33° Left 28° to 33° Rudder Right 25° Left 25° Serial Nos. Eligible See NOTE 4. Required Equipment Items 1 or 2 or 5 or 7 or 8 or 9, 101, 102, 103, 104, 109, 125, 201, 202, 301, 302, 401(a). (Item 125 not required when Item 2 or 5 or 7 or 8 or 9 installed). V. Model E18S-9700, 10 PCLM, Approved January 19, 1959 Engines Two (2) P&W Military R-985-AN-14B with one 4-1/2N and one 9N damper each See Item 128 for optional engines Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations: Sea level 36.5 in. Hg, 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude to 3500 ft. 35.5 in. Hg, 2300 rpm. (450 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 256 mph. (222 knots) Flaps extended - power off 140 mph. (121 knots) - power on 120 mph. (104 knots) Landing gear extended 160 mph. (139 knots) C.G. Range (landing (+111.4) to (+120.5) at 9700 lb. (maximum takeoff weight) gear extended) (+110.2) to (+120.5) at 9400 lb. (maximum landing weight) (+107.0) to (+120.5) at 8600 lb. or less Straight line variation between points given Moment due to retraction of landing gear is +12000 in.-lb. C.G. diagram same as Section VI Rev. 78 7 A-765 V. Model E18S-9700 (cont’d) Maximum Weight 9700 lb., takeoff weight (See Item 126 for increased weight) 9400 lb., landing weight No. of Seats Maximum 10 (2 crew at +87). See loading instructions for passenger loading. Anti-icing Fluid Capacity 6 gal. (40 lb. at +152) Maximum Baggage Rear compartment: 300 lb. at +271 See NOTE 2 Fuel Capacity 198 gal. usable (4 tanks in wings, two 76 gal. tanks at +126, two 23 gal. tanks at +155) See Items 108 and 122 for optional fuel tanks See NOTE 1 for data on unusable fuel Oil Capacity 17 gal. usable at +93 (8½ gal. total capacity tank in each nacelle) See NOTE 1 for data on unusable oil Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18° Down 13° Elevator Up 35° Down 25° Aileron trim tab Up 22° Down 19° Aileron Up 38-1/2° Down 21° Rudder trim tab Right 29° Left 29° Rudder Right 25° Left 25° Serial Nos. Eligible BA-403 through BA-460, except BA-434 Required Equipment Items 2 or 5 or 7 or 8 or 9, 101, 102, 103, 104, 109(c), 120, 201, 202, 301, 308, 40 1(a), 415, 601 VI. Model G18S, 10 PCLM, Approved October 8, 1959 Engines Two (2) P&W Military R-985-AN-14B with one 4-1/2N and one 9N damper each See Item 128 and 129 for optional engines Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations: Sea level 36.5 in. Hg, 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude to 3500 ft. 35.5 in. Hg, 2300 rpm. (450 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 256 mph. (222 knots) Flaps extended - power off 140 mph. (121 knots) - power on 120 mph. (104 knots) Landing gear extended 160 mph. (139 knots) A-765 8 Rev. 78 VI. Model G18S (cont’d) C.G. Range (landing (+111.4) to (+120.5) at 9700 lb. (maximum takeoff weight) gear extended) (+110.2) to (+120.5) at 9400 lb. (maximum landing weight) (+107.0) to (+120.5) at 8600 lb. or less Straight line variation between points given Moment due to retraction of landing gear is +12000 in.-lb. Maximum Weight 9700 lb., takeoff weight (See Item 126 for increased weight) 9400 lb., landing weight No. of Seats Maximum 10 (2 crew at +87). See loading instructions for passenger loading. Anti-icing Fluid Capacity 6 gal. (40 lb. at +152) Maximum Baggage Rear compartment: 300 lb. at +271; Nose compartment (when Item 615 is installed): 300 lb. at +28; Inboard wing baggage compartment (when Item 618 is installed): 100 lb. left, 10 lb. right at +155 See NOTE 2 Fuel Capacity 318 gal. usable (six tanks in wings - two 76 gal. tanks at +126, two 23 gal. tanks at +155, two 60 gal. tanks at +139) 272 gal. usable (when Item 618 installed) (four tanks in wings, two 76 gal. tanks at +126, two 60 gal. tanks at +139) See NOTE 1(e) for data on unusable fuel Oil Capacity 17 gal. usable at +93 (8½ gal. total capacity tank in each nacelle) See NOTE 1 for data on unusable oil Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18° Down 13° Elevator Up 35° Down 15° Aileron trim tab Up 22° Down 19° Aileron Up 38-1/2° Down 21° Rudder trim tab Right 29° Left 29° Rudder Right 25° Left 25° Serial Nos. Eligible BA-434, BA-461 through BA-617, except BA-563 (See Item 619) and BA-580 and BA-497 Required Equipment Items 2 or 5 or 7 or 8, 101, 102, 103(b) and 109(c), 120, 201, 202, 301, 308, 401(a), 415 and 601 Rev. 78 9 A-765 VII. Model H18, 11 PCLM, Approved July 11, 1962 Engines Two (2) P&W Military R-985-AN-14B with one 4-1/2N and one 9N damper each Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations: Sea level 36.5 in. Hg, 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude to 3500 ft. 35.5 in. Hg, 2300 rpm. (450 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 256 mph. (222 knots) Flaps extended - power off 140 mph. (121 knots) - power on 120 mph. (104 knots) - 30° position 160 mph. (139 knots) (with Item 639 only) - 15° position 180 mph. (156 knots) (with Item 639 only) Landing gear extended 160 mph. (139 knots) C.G. Range (landing (+112.2) to (+120.5) at 9900 lb. (maximum takeoff weight) gear extended) See Item 126 for increased weight (+110.6) to (+120.5) at 9500 lb. (maximum landing weight) (+107.0) to (+120.5) at 8600 lb. or less Straight line variation between points given Moment due to retraction of landing gear is +8200 in.-lb. Maximum Weight 9900 lb. takeoff weight (See Item 126 for increased weight) 9500 lb. landing weight No. of Seats Maximum 11 (2 crew at +87). See loading instructions for passenger loading. Anti-icing Fluid Capacity 6 gal. (40 lb. at +152) Maximum Baggage Rear compartment: 300 lb. at +271; Nose compartment (when Item 615 is installed): 300 lb. at +28 See NOTES 2 & 5 A-765 10 Rev. 78 VII. Model H18 (cont’d) Fuel Capacity 318 gal. usable (six tanks in wings - two 76 gal. tanks at +126, two 23 gal. tanks at +155 and two 60 gal. tanks at +139) OR 318 gal. usable (four tanks in wings - two 99 gal. tanks at +128 and two 60 gal. tanks at +139) See NOTE 1 for data on unusable fuel. Oil Capacity 14 gal. usable at +93 (8½ gal. total cap. tank in each nacelle) See NOTE 1 for data on unusable oil. Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18° Down 13° Elevator Up 35° Down 15° Aileron trim tab Up 22° Down 19° Aileron Up 38-1/2° Down 21° Rudder trim tab Right 29° Left 29° Rudder Right 25° Left 25° Serial Nos. Eligible BA-580, BA-618 through BA-765 Required Equipment Items 2 or 7 or 8, 101(b), 102(w), 102(x), 103(b), 109(c), 122, 201(c) and 202 or 632, 301(a) or 307(d) or 309, 308, 401(v) or (w), 415, 601 VIII. Model JRB-6, 10 PCLM, Approved August 30, 1963 Engines Two (2) P&W Military R-985-AN-14B with one 4-1/2N and one 9N damper each See Item 113 for optional engines. Fuel 80/87 minimum grade aviation gasoline Engine Limits Maximum continuous Sea level 34.5 in. Hg, 2200 rpm. (400 hp.) Straight line manifold pressure variation with altitude to 5000 ft. 33.5 in. Hg, 2200 rpm. (400 hp.) Takeoff (one minute) 36.5 in. Hg, 2300 rpm. (450 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 257 mph. (223 knots) Flaps extended 120 mph. (104 knots) Landing gear extended 125 mph. (109 knots) C.G. Range (landing (+109.8) to (+117.7) gear extended) Moment due to retraction of landing gear is +12000 in.-lb. See Item 605 for revised limits Maximum Weight 8240 lb. (takeoff) 7850 lb. (landing) See Item 631 for higher weights No. of Seats Maximum 10 (2 crew at +87). See loading instructions for passenger loading. Anti-icer Fluid Capacity 3 gal. (20 lb. at +97) Maximum Baggage Nose compartment, 600 lb. at +28. Rear compartment, 300 lb. at +243 See NOTES 2 & 5 Rev. 78 11 A-765 VIII. Model JRB-6 (cont’d) Fuel Capacity 202 gal. usable (4 tanks in wings, two 76 gal. tanks at +126, two 25 gal. tanks at +155). See NOTE 1 for data on unusable fuel Oil Capacity 16 gal. usable at +93 with Item 1 13 gal. usable at +93 with Item 2 (8 gal. tank in each nacelle) With Item 2, total capacity includes 9.5 lb. feathering oil in each tank See NOTE 1 for data on unusable oil Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18° Down 13° Elevator Up 35° Down 25° Aileron trim tab Up 22° Down 19° Aileron Up 38.5° Down 21° Rudder trim tab Right 28° to 33° Left 28° to 33° Rudder Right 25° Left 25° Serial Nos. Eligible See NOTE 4 Required Equipment Items 1 or 2, 101, 102, 103, 104, 109, 201(d), 202(b), 301, 302, 612 (Item 105 or 125 required when Item 1 installed) IX. Models 3N, 3NM, 3TM, 10 PCLM, Approved January 31, 1968 Engines Two (2) P&W Military R-985-AN-14B with one 4-1/2N and one 9N damper each See Item 113 for optional engines Fuel 80/87 minimum grade aviation gasoline Engine Limits Maximum continuous Sea level 34.5 in. Hg, 2200 rpm. (400 hp.) Straight line manifold pressure variation with altitude to 5000 ft. 33.5 in. Hg, 2200 rpm. (400 hp.) Takeoff (one minute) 36.5 in. Hg, 2300 rpm. (450 hp.) Airspeed Limits Maneuvering 153 mph. (133 knots) (TIAS) Cruising 205 mph. (178 knots) Never exceed 257 mph. (223 knots) Flaps extended 120 mph. (104 knots) Landing gear extended 125 mph. (109 knots) C.G. Range (landing (+109.8) to (+117.7) gear extended) Moment due to retraction of landing gear is +12000 in.-lb. Maximum Weight 8750 lb. Anti-icer Fluid Capacity 3 gal. (20 lb. at +97) Maximum Baggage Nose compartment: 600 lb. at +28. When auxiliary fuel tank installed, combined weight of fuel and baggage may not exceed 600 lb. Rear compartment: 300 lb. at +243 See NOTES 2 & 5 FuelCcapacity 282 gal. usable (four tanks in wings, two 76 gal. tanks at +126, two 25 gal. tanks at +155, one nose tank, 80 gal. at +32) See NOTE 1 for data on system fuel A-765 12 Rev. 78 IX. Models 3N, 3NM, 3TM (cont’d) Oil Capacity 16 gal. usable at +93 with Item 5 or 7 13 gal. usable at +93 with Item 2 (8 gal. capacity tank in each nacelle) With Item 2, total capacity includes 9.5 lb. feathering oil in each tank. See NOTE 1 for data on unusable oil Control Surface Movements Wing flaps Down 45° Elevator trim tab Up 18° Down 13° Elevator Up 35° Down 25° Aileron trim tab Up 22° Down 19° Aileron Up 38.5° Down 21° Rudder trim tab Right 28° to 35° Left 28° to 33° Rudder Right 25° Left 25° Serial Nos. Eligible See NOTE 4 Required Equipment Items 2 or 5 or 7 or 8 or 9, 101, 102, 103, 104, 109, 201, 202, 301 or 307, 308(l) or (m), 401(x) Specifications Pertinent to All Models Datum 102 inches forward of centerline of main wing spar (placard denoting datum installed on bottom of fuselage) Leveling Means Models 3N, 3NM, 3TM, SNB-5, JRB-6, D18C, D18S, and C-45 Series - leveling lugs on top of fuselage, forward of cabin. Models E18S, E18S-9700, G18S and H-18 - two extended screws on right side of airplane at bulkhead No. 8, aft of emergency exit. Plumb bob is used to level. Certification Basis Part 03 of the Civil Air Regulations effective November 13, 1945, and Part 3 effective November 1, 1949, as amended by 3-14 (paragraph 3.242) (Normal Category) Type Certificate No. A-765 issued April 26, 1946 Production Basis Production Certificate No. 8 Models G18S and H18: Delegation Option Manufacturer No. CE-2 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Required Equipment A plus (+) or minus (-) sign preceding the weight of an item of equipment indicates net weight change when that item is installed. Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). This symbol denotes that approval has been obtained by someone other than the aircraft manufacturer. An item so marked may not have been manufactured under an FAA monitored or approved quality control system. Conformity must be determined if the item is not identified by Form FAA-186, PMA or other evidence of FAA production approval. Rev. 78 13 A-765 Specifications Pertinent to All Models (cont’d) Propeller and Propeller Accessories (excepting Deicing Equipment) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 1. Two Ham. Std. constant speed propeller installation (a) Hubs 2D30 with (1) Blades 6167-15 X X X Pitch settings at 42 in. sta.: high 29 , low 14 157 lb. ea. (+35) or (2) Blades 6101-21 Pitch settings at 42 in. sta.: high 28 , low 13 162 lb. ea. (+35)