# TCDS A-765: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 78 - Revised: November 27, 2017 - Product: Aircraft, Small Airplane - Certification basis: Part 3, Part 21, CAR 3 - Registered aircraft: 259, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/d7/5d/d75d78e5aa9ef9d3cbf81cd59c018b334a7cd693ceeeb3a95f9b6b90c49946c7 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4236317DA0946BB2862581EF0060CD6B.0001 - Page: https://openairdocs.org/tcds/A-765 ## Models (17) As the data sheet lists them. - 3TM - 3N - E18S-9700 - TC-45J - TC-45G - C-45H - C-45G - 3NM - G18S - E18S - TC-45H - H18 - D18S - D18C - JRB-6 - UC-45J (SNB-5) - RC-45J (SNB-5P) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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) For interchangeable blade models, see Propeller Spec. 206 (Note 6) Diameter: max. 8’3-1/8”, min. allowable for for repairs 8’ 7/8”. No further reduction permitted. and (b) Governor - Hamilton Standard 1A2 X X X 5 lb. ea. (+66) and (c) Controls installation X X X 11 lb. (+68) 2. Two Hamilton Standard hydromatic full-feathering propeller instln. (required with Item 605 or 637) (a) Hubs 22D30, blades 6531-15 (Model D18S, E18S and C-45) or blades 6533-21, 6533-21S or 6533-22S (Model D18S, C-45, 3N, 3NM, 3TM only) X X X X X X X X X X 176 lb. ea. (+34) For interchangeable blade models, see Propeller Spec. 736 (Note 6) Pitch settings at 42 in. sta.: 6531-15 blades: high 86, low 13 6533-21 blades: high 84, low 12 Diameter: max. 8’ 3-3/8”, min. allowable for repairs 8’ 1/8”. No further reduction permitted. and (b) Governor - Hamilton Standard 4B2 X X X X X X X X 5 lb. ea. (+66) and (c) Two feathering pumps X X X X LH - One Beech 900-189071-2 (Pesco 1E-521-DC) or 404-189075 (Pesco 1E-521-HC or HAC) 11 lb. ea. (+103) or Ham Std 66166-12 (Pesco 1E-777-BLB-1) X X X X 11 lb. ea. (+103) or Beech 404-189080 (Pesco 1E-VR-280-BHC) X X X X 20 lb. (+103) and RH - One Beech 900-189071-4 (Pesco 1E-521-DC) X X X X 11 lb. ea. (+103) or Hamilton Standard 66094-1 (Pesco) 1E521-HC or HAC) X X X X or Hamilton Standard 66166-12 (Pesco) 1E-777-BLB-1) 11 lb. (+103) or Pesco 1E-VR-280-BHC X X X X 20 lb. (+103) and (d) Controls installation X X X X 32 lb. (+79) Beech 404-189804 oil tank standpipe is required with this propeller. A-765 14 Rev. 78 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 3. Two spinner installations (with Item 1 only) X X (a) Air Associates, HC-1027 5 lb. ea. (+31) or (b) Harry F. Montgomery Metal Spinning Works Model E-236 X X 12 lb. ea. (+34) or (c) Beech 734-189071 X X X 5 lb. ea. (+31) 4. Two Hamilton Standard hydromatic full feathering propeller installations (a) Hubs 22D30, blades 6597-21 X For interchangeable blade models, see Prop. Spec. No. 736 (Note 6) Pitch settings at 42 in. sta.: high 86 , low 14 Diameter: maximum 8’3-1/2”, min. allowable for repairs 7’ 10” No further reduction permitted. When diameter exceeds 8’ 0”, following placard is required; “Avoid continuous operation between 1850 and 2000 rpm.” 176 lb. ea. (+30) and (b) Governor - Ham. Std. 4G8-P30M or 4G8-P63M X 7 lb. ea. (+38) and (c) Feathering pump X One Beech 900-189071-2 (LH) and One Beech 900-189071-4 (RH) 11 lb. ea. (+103) 5. Two Hartzell 3-blade full-feathering propeller installations per Dwg. 404-001058 or 414-189070 (a) Hub and blade assemblies (1) HC-B3Z30-2 series hubs with 10160-6 blades and 836-16 spinner X X X X X X 132 lb. ea. (+ 35) or 10160B-6 blades and 836-17 spinner X X X X X X 133 lb. ea. (+ 35) or (2) HC-B3W30-2E hub with W10160-6 blades and 836-16 spinner X 132 lb. ea. (+ 35) or W10160B-6 blades and 836-16 spinner modified per Item 506 X 133 lb. ea. (+ 35) Pitch settings at 30 in. sta.: high 87 , low 17 Diameter: 95 in. No cutoff permitted Engine tachometer is to be marked with red arc between 1600 and 1800 rpm. indicating restriction against continuous operation in this range. and (b) Governor - Hartzell C-3 or Woodward 210205, 210402, 210494, 210495 or 210496 X X X X X X 6 lb. ea. (+ 66) (c) Deleted June 9, 1960 Rev. 78 15 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 (d) Controls installation X X X X X X Beech 404-189804 oil tank standpipe is not to be used with this propeller 32 lb. (+79) Item 401(a) revised January 30, 1961, Model E18S, and (k); or (g) and (k); or (h) and (k); or (i) and (k) required with Item 5(a). 6. Propeller unfeathering systems Two unfeathering pumps X X X X X X (LH) One Pesco 111059-011-01 7 lb. ea. (+ 103) or Beech 900-189071-2 (Pesco 1E-521-DC) or 404-189075 (Pesco 1E-521-HC or HAC) or Ham. Std. 66166-12 (Pesco 1E-777-BLB-1) 11 lb. ea. (+ 103) or Beech 404-189080 (Pesco 1E-VR-280-BHC) 20 lb. ea. (+ 103) and (RH) One Pesco 111059-011-01 7 lb. ea. (+ 103) or Beech 900-189071-4 (Pesco 1E-521-DC) or Ham. Std. 66094-1 (Pesco 1E-521-HC or HAC) or 66166-12 (Pesco 1E-777-BLB-1) 11 lb. ea. (+ 103) or (Pesco 1E-VR-280-BHC) 20 lb. ea. (+ 103) or Unfeathering accumulators (one 210362 and 210384 accumulator installation (Woodward)) X 9 lb. (+ 66) 7. Two Hartzell 3-blade full-feathering propeller installations per Dwg. 18-960000, 414-189070 or 414-001068 (a) Hub and blade assemblies (1) HC-B3Z30-2E with 10152-5-1/2 blades and 836-16 spinner X X X X X X X 129 lb. ea. (+ 35) or 10152B-5-1/2 blades and 836-17S spinner X X X X X X X 130 lb. ea. (+ 35) (2) HC-B3W30-2E hubs with W10152-5-1/2 blades and 836-16 spinner X X X X X X 129 lb. ea. (+ 35) or W10152B-5-1/2 blades and 836-16 spinner modified per Item 506 X X 130 lb. ea. (+ 35) Pitch settings at 30 in. sta.: high 87 , low 17 Diameter: 95-1/2 in. No cutoff permitted. Engine tachometer to be marked with yellow arc between 1500 and 1700 rpm. and between 2100 and 2275 r pm. indicating restriction against continuous operation in this range. (b) Governor - Woodward 210402 or 210404 X X X X X X X or Hartzell C3 except for H18 6 lb. ea. (+ 66) A-765 16 Rev. 78 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 (c) Controls installation X X X X X X X 32 lb. (+ 79) AFM Supplement P/N 130225 dated September 5, 1962, or April 15, 1963, or April 14, 1964 (D18S, C-45G and H, and TC-45G and H, E18S-9700) or P/N130352 dated April 12, 1963 (G18S) required. 8. Two Hartzell 3-blade full feathering propeller installations per Dwg. 404-001058, 414-001068, 414-189070 or 18-960000 (a) Hub and blade assemblies HC-B3R30-2E hubs with R10152-5-1/2 blades and 836-16 spinner X X X X X X X 135 lb. ea. (+ 35) or R10152B-5-1/2 blades and 836-17S spinner X X X X X X X 136 lb. ea. (+ 35) or R10152B-5-1/2 blades and 836-16 spinner modified per Item 506 X X 136 lb. ea. (+ 35) Pitch settings at 30 in. sta.: high 87 , low 17 Diameter: 95-1/2 in. No cutoff permitted. Engine tachometer to be marked with yellow arc between 1500 and 1700 rpm. and between 2100 and 2275 rpm. indicating restriction against continuous operation in this range. (b) Governor, Hartzell C-3 or Woodward 210205, 210494, 210495 or 210496 X X X X X X or Woodward 210402 or 210404 X X X X X X X 6 lb. ea. (+ 66) (c) Controls installation X X X X X X X +32 lb. (+ 79) AFM Supplement P/N 130705 dated March 13, 1967 (G18S and H18) or P/N 130713 dated March 14, 1967 (D18S, E18S, E18S-9700, C-45G, TC-45G, C-45H, TC-45H, TC-45J) required 9. Two Hartzell 3-blade full-feathering propeller installations per Dwg. 414-001068. (a) Hub and blade assemblies HC-B3P30-2E hubs with P10152-5-1/2 blades and 836-16 spinner X X X X X X X 135 lb. ea. (+ 35) or P10152B-5-1/2 blades and 836-17S spinner X X X X X X X 136 lb. ea. (+ 35) or P10152B-5-1/2 blades and 836-16 spinner modified per Item 506 X X X X X X X 136 lb. ea. (+ 35) Pitch settings at 30 in. sta.: high 87 , low 17 Diameter: 95-1/2 in. No cutoff permitted. Tachometer to be marked with yellow arc between 1500 and 1700 rpm. and between 2100 and 2275 rpm. indicating restriction against continuous operation in this range. (b) Governor - Hartzell C-3 except H-18 X X X X X X or Woodward 210205, 210494, 210495, 210496, 210402, or 210404 X X X X X X X 6 lb. ea. (+ 66) Rev. 78 17 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 (c) Controls installation X X X X X X 32 lb. (+ 79) AFM Supplement P/N 130225 dated August 18, 1967 Engine and Engine Accessories - Fuel and Oil Systems 101.(a) Two 7” x 9” oil radiators with intake system (G & 0) X X X X X X X X 20 lb. ea. (+ 80) or Two 7” x 9” oil radiators with intake system (Harrison) X X X X X X X X 15 lb. ea. (+ 80) (b) Two 7” x 9” thermostatically controlled oil coolers X 10 lb. ea. (+ 80) 102.Fuel pumps (a) Two wobble-United Aircraft U-550-BE X X X X 4 lb. ea. (+86) or (b) Two wobble-United Aircraft U-550-BO X X X X 4 lb. ea. (+ 86) or (c) Two wobble-Romec Pump Co. RXD-1563-1 X X X X 4 lb. ea. (+ 86) or (d) Two wobble-Army Type D-11 X X X X 4 lb. ea. (+ 86) or (r) Two electric booster - Beech X X X X X X 694-189641-4 (Adel 24000-3) 694-189641-8 (Adel 26900-3) 694-189641-12 (Adel 27447) Pesco 122799-120 3 lb. ea. (+ 126) (Modified main fuel tanks, a revised fuel system and Item 401. FAA Approved Flight Manual Rev. November 25, 1952, or a later date, required with this item for D18S and C-45 only) (t) Two electric booster Pesco 122799-120 installed per Beech Dwg. 404-001069 X 3 lb. ea. (+ 56) (u) Two electric booster pumps - Adel 70146 X X X X (with Items 128 and 129 only) 3 lb. ea. (+ 126) (v) Two engine-driven Beech 50-921560-5 X X X (with Item 128 only) 3 lb. ea. (+ 62) or (w) Two engine-driven Beech 50-921560-3 or -23 X X 3 lb. ea. (+ 62) or (x) Two electric booster pumps - Pesco 122799-120-01 or -02 or Adel 28550-1 X X X X 3 lb. ea. (+ 128) or (y) Two engine-driven Beech 50-921560-9 or -29 X X or Beech 50-389141-11 (with Item 129 only) 3 lb. ea. (+ 62) and (s) One electric fuel booster pump in nose tank. Beech 694-189641-12 or Adel 28550 or 28550-1, Pesco 122799-120 X and (e) Two engine-driven Army Type G6 X X X X X X X 3 lb. ea. (+ 62) or (f) Two engine-driven - AN-4100-1 X X X X X X X 3 lb. ea. (+ 62) A-765 18 Rev. 78 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories - Fuel and Oil Systems D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM or (g) Two engine-driven - Romec RD-3890 X X X X X X X 3 lb. ea. (+ 62) or (h) Two engine-driven - Pesco 2P-R400-BRD X X X X X X X X 3 lb. ea. (+ 62) or (i) Two engine-driven - Pesco 2P-R400-BRS X X X X X X X X 3 lb. ea. (+ 62) or (j) Two engine-driven - Pesco 2P-R400-BR X X X X X X X X 3 lb. ea. (+ 62) or (k) Two engine-driven - Chandler Evans 9141 X X X X X X X X 3 lb. ea. (+ 62) or (l) Two engine-driven - Chandler Evans 9105 X X X X X X X X 3 lb. ea. (+ 62) or (m) Two engine-driven - Chandler Hill H2E3 or CH4502-1 or CH4502-11 X X X X X X X 3 lb. ea. (+ 62) or (n) Two engine-driven - TFD-400-1 or TF-400-1 X X X X X X X X 3 lb. ea. (+ 62) or (o) Two engine-driven Thompson TFD-400 or TF-400 X X X X X X X X 3 lb. ea. (+ 62) or (p) Two engine-driven - Thompson TFD-900-1, TF-900-1 or TF-900-3 X X X X X X X X 3 lb. ea. (+ 62) or (q) Two engine-driven - Romec RD-4190 X X X X X X X X 3 lb. ea. (+62) 103.Two carburetor air heaters (weight and arm for the air scoop valve and one set of heater muffs) (a) For use with 109(a) or (b) X X X X X 21 lb. ea. (+ 62) 16 lb. ea. (+ 61) (on E18S) (b) For use with 109(c) X X X X 15 lb. ea. (+ 61) 104.Two oil radiator by-pass valves - S80 X X X X X X X X 1 lb. (+ 79) 105.Exhaust collector gas analyzer - Combridge No. 10555-1 X X 10 lb. (+ 77) 106.Two vacuum pumps. At the engine cruising rpm. the output of each pump should be sufficient to provide the recommended pressure in each instrument case to supply the air flow requirements for all the instruments connected to the system. (a) Type B-12 X X X X X X X X 5 lb. ea. (+ 64) or (b) Eclipse-Pioneer 683-3 X X X X X X X X 5 lb. ea. (+ 64) or (c) Eclipse-Pioneer 683-4 X X X X X X X X 5 lb. ea. (+ 64) or (d) Eclipse-Pioneer 549-5 X X X X X X X 5 lb. ea. (+ 64) or (e) Pesco 3P-207-JA X X X X X X X X 5 lb. ea. (+ 64) or (f) Pesco 3P-207-J or 3P-207-JE X X X X X X X X 5 lb. ea. (+ 64) Rev. 78 19 A-765 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories - Fuel and Oil Systems D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM or (g) Aro Equipment 207-JA X X X X X X X X 5 lb. ea. (+ 64) or (h) Aro Equipment A-505-DD or A-505-CDD X X X X X X X X X 5 lb. ea. (+ 64) or (i) Romec RD-3880 X X X X X X X X 5 lb. ea. (+ 64) or (j) Beech 50-380090 or 50-380090-1 X X 5 lb. ea. (+ 64) 107.Starters - Eclipse E-80, Army Type J-1 or Eclipse 756-21C or 756-9C X X X X X X X X X 20 lb. ea. (+ 70) 108.77 gal. (80 gal. in D18S & D18C) aux. fuel tank in nose baggage compartment. Combined weight of baggage and fuel must not exceed 600 lb. at +32. (No baggage permitted E18S or E18S-9700). X X X X X X 23 lb. (+ 36) 109.Carburetor air intake system (a) With filters X X X X 14 lb. ea. (+ 45) or (b) Without filters 4 lb. ea. (+ 48) X X X X 6 lb. ea. (+ 50) X or (c) Carburetor ram air scoop and air valve per Dwg. 404-001024 or 414-185906 or 18-910013 (G18S and H18 only) X X X X X X X -3 lb. (+ 27) 110.Engine compartment pressure fire extinguisher and system with (a) Walter Kidde 7-1/4 lb. CO2 X X X X X X X X 33 lb. (+ 56) or (b) Walter Kidde 5 lb. CO2 X (Including detector system) 57 lb. (+ 111) or (c) Walter Kidde or American LaFrance X X X X X X X X (8 lb. CB) 39 lb. (+ 114) 111.Oil dilution system 2 lb. ea. (+ 79) (1 lb. ea. (+ 79) (on D18C) X X X X X X X X X 112.Two carburetor air heater installations. X 9 lb. ea. (+ 59) A-765 20 Rev. 78 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories - Fuel and Oil Systems D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 113.Engine (must have one 4-1/2N and one 9N damper) Use act. wt. change on all engine changes. (a) P&W Wasp Jr. SB-2 (limits same as for SB-3 and R985-AN-14B) X X X X or (b) Military R-985-AN-4 (limits same as for SB-3 and R-985-AN-14B) X X X X or (c) Military R-985-AN-14B (limits same as for SB-3) X X X X or (d) P&W Wasp Jr. B-5 (same power limits as for SB-3 if Best Power Mixture used) X X X or (e) Military R-985-AN-1 (limits same as for R-985-AN-14B) for engines with NAR9A or NAR9B or NAR9CE carburetors X X or (f) Military R-985-AN-3 (limits same as for R-985-AN-1) X X or (g) Military R-985-39 (limits same as for R-985-AN-1) X X or (h) P&W Wasp Jr. SB-3 (limits same as for R-985-AN-14B) X X X or (i) Military R985-AN-1M1 when Item 5 used (limits same as for R985-AN-14B) X X X or (j) Military R985-AN-2 when Item 5 used (limits same as for R985-AN-14B) X X X or (k) Military R985-AN-10 when Item 5 used (limits same as for R985-AN-14B) X X X 114.Two carburetor air filters X 2 lb. ea. (+ 73) 115.47 gal. aux. fuel tank in nose baggage compt. This installation must be modified per Beech Dwg. 404-001101-3 (C-45), 404-001101-1 (TC-45J) to be eligible for certification. Combined weight of baggage and fuel must not exceed 600 lb. (arm of fuel + 38) X X X 45 lb. (+ 38) *116.Engine cooling air outlet baffles installation per Continental Motors Dwg. 516935 X 1 lb. (+ 50) 117.Fuel flowmeter installation (with Pioneer 9054-5A transmitters and 6007 indicator or Beech 414-180824 transmitters and 414-180838 indicator) (a) With separate inverter X 24 lb. (+ 77) or (b) Powered from radio inverter X 18 lb. (+ 75) 118.Jet stack installation (E18 type per Dwg. 404-001019) X X -45 lb. (+80) 119.Cowl support brackets, improved type per Dwg. 404-001029 X X X 2 lb. (+ 46) 120.Fuel flowmeter installation per Dwg. 404-001020 or 414-180804 (See Item 124) (a) With separate inverter X X X X X X X 25 lb. (+ 123) (D18S, C-45G, etc.) 25 lb. (+ 77) (All other) or (b) Powered from radio inverter X X X X X X X 18 lb. (+ 78) (D18S, C-45G, etc.) 18 lb. (+ 75) (All other) Rev. 78 21 A-765 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories - Fuel and Oil Systems D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 121.Improved oil radiator cooling air valve per Dwg. 404-001025 X X X Negligible weight 122.Auxiliary wing fuel cells, 60 gal., bladder type, per Dwg. 404-001027 or 414-920000 (arm of fuel + 139) (Nose tanks, Item 108 or 115 to be removed if installed). AFM Supplement, P/N 404-001055 dated June 19, 1958, or AFM Supplement P/N 404-001049 dated June 20, 1958 , required. X X X X X 96 lb. (+ 137) (a) With landing lights relocated per Dwg. 404-001027 X X 0 lb. ea. (+ 100 in. - lb.) 123.Improved engine crankcase vent per Dwg. 404-001032 X X X 5 lb. (+ 82) 124 Fuel flowmeter dial face, P/N 414-180838-11 (converts Item 125 to 120) X No change in weight 125.Fuel flowmeter installation (with Beech 414-180824 transmitter and 404-001036 indicator) (a) With separate inverter X 25 lb. (+ 123) or (b) Powered with radio inverter X 18 lb. (+ 78) 126.Two Aerojet 15NS-250 or 12NS-350 or 12NS-350CBA Rocket Engine installations (per Dwg. 414-18911 or Kit Dwg. 404-001059) Note: Model 18 aircraft with tricycle gears (STC SA111WE) not eligible for this installation. X X X X X X X X (a) 15NS-250 charged 100 lb. (+ 125) (b) 12NS-350 or 12NS-350CBA charged 108 lb. (+ 125) (c) 15NS-250 expended 58 lb. (+ 124) (d) 12NS-350 or 12NS-350CBA expended 64 lb. (+ 124) (e) Engines removed 16 lb. (+ 120) For 15NS-250 AFM Supplement 404-001065 dated April 16, 1961, or Item 401(f) required. X X X X X X For 12NS-350, AFM Supplement 404-001065 dated February 27, 1964, or 12NS-350CBA AFM Supplement dated March 10, 1965, required for D18S, C-45G, TC-45G, C-45H, TC-45H and TC-45J at the standard gross weight of 8750 lb. or as modernized per Item 605, 616, 617, 620, 621 or per STC SA4-113 and amended March 24, 1959, or per STC SA2-820 amended January 14, 1960. X X 404-001065 dated July 1, 1964, or March 10, 1965, required for: D18S, C-45G, TC-45G, C-45H, TC-45H and TC-45J at the standard gross weight of 8750 lb. or as modernized per Item 605, 616, 617, 620, 621, 622, 624, 627, 628, 629, 635, 636 or per STC SA4-113 and amended March 24, 1959, or per STC SA2-820 amended January 14, 1960 X X 18-001032 dated February 26, 1964, required for E18S and E18S-9700 at standard gross weights of 9300 and 9700 lb. respectively 18-001032 dated July 2, 1964, or March 11, 1965, required for E18S and E18S-9700 at standard gross weights of 9300 and 9700 lb. respectively or modernized per Item 611, 623, 630 or 633. X X A-765 22 Rev. 78 Specifications Pertinent to All Models (cont’d) Engine and Engine Accessories - Fuel and Oil Systems D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 18-001032 dated July 2, 1964, or March 11, 1965, required for E18S and E18S-9700 at standard gross weights of 9300 and 9700 lb. respectively or modernized per Item 611, 623, 630 or 633. X X 18-001021 dated February 25, 1964, required for G18S and H18 at standard gross weights of 9700 and 9900 lb. respectively. X X 18-001021 dated July 3, 1964, or March 12, 1965, required for G18S and H18 at standard gross weights of 9700 and 9900 lb. respectively or G18S modernized per Item 630. X X For 12NS-350CBA, Supplement required is 404-001065 dated March 10, 1965 for: X X D18S, C-45G, TC-45G, C-45H, TC-45H, TC-45J at standard gross weight of 8750 lb. or as modernized per Item 605, 616, 617, 620, 621, 622, 624, 627, 628, 629, 635 or 636 or per STC SA4-113 and SA4-113 amended March 25, 1959, or per STC SA2-820 amended January 14, 1960. 18-001032 dated March 11, 1965, for E18S and E18S -9700 at standard gross weights of 9300 and 9700 lb. respectively or modernized per Item 611, 623, 630 or 633. X X 18-001021 dated March 12, 1965, for G18S and H18 at standard gross weights of 9700 and 9900 lb. respectively or G18S modernized per Item 630. X X 127.Heated fuel tank vents X X X X X (a) Wing fuel tanks, Beech Dwg. 404-001073 Negligible weight (b) Nose fuel tank, Beech Dwg. 404-001075 Negligible weight 128.P&W Military R985-AN-14B with one 4-1/2N and one 9N damper each and one fuel injection system per STC SE3-612 installed per Beech Dwg. 18-91001 or 414-001036, Item 401(u) required for G18S in lieu of 401(a). AFM Supplement 414-001042 dated April 12, 1961, required for E18S and E18S-9700. X X X Use act. wt. change 129.Two P&W Military IR985-AN-14B with one 4-1/2N and one 9N damper each per STC SE4-1136 installed per Beech Dwg. 18-920002 and STC SA4-1427. Bendix AFM Supplement dated February 1, 1962, required for G18S and AFM Supplement dated July 18, 1962, required for H18. X X Use act. wt. change 130.Power pkg. installation (H18 type per Dwg. 414-001088) X X X Use act. wt. change 131.Power pkg. installation (H18 type per Dwg. 414-000013) X X X X X Use act. wt. change Rev. 78 23 A-765 Specifications Pertinent to All Models (cont’d) Landing Gear D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 201.(a) Main gear, Goodyear L12HBM, 11.00-12, Type III, wheel-brake assembly with 11.00-12 8-ply tires and tubes X X X X X X X Wheel assembly 530884-M or 530884-G Brake assembly 530886-M or 530886-SG 95 lb. ea. (+ 92) or (b) Main gear, Goodyear L12HBM, 11.00-12 Type III, wheel-brake assembly with 11.00-12 8-ply rating nylon tubeless tires. Tubeless wheel assembly 9531432, brake 9531637 or 530886-SG X X X X X X 79 lb. ea. (+ 92) or (c) Main gear, Goodyear PD185-10 or PD185-12, Type III wheel-brake assembly with 8.50-10 10-ply rating nylon tubeless tires. X X Wheel assembly 9532489 or 9542623 Brake assembly 9532491 55 lb. ea. (+ 92) or (d) Two main gear, 33 in. smooth contour wheels (Bendix B-4) with 13-2-1/2 brakes (Bendix 59799) and 8-ply tires X X 104 lb. ea. (+ 92) 202.(a) 14.50 tail wheel (Hayes Industries or B.F. Goodrich D-3-180M) with 6-ply S.C. tire and tube X X X X X X X X X 14 lb. (+ 354) or (b) 12 x 5-3 tail wheel and tire (Goodyear) X X 8 lb. (+ 354) 203.Hand operated parking brakes X X X X X X X X X 3 lb. (+ 51) 204.Landing gear oleo drag leg assembly (404-188027) replacing standard drag legs (404-118405) X X X 24 lb. (+ 100) 205.Martin landing oleo drag leg assembly (90-1000003) replacing standard drag legs (404-188405) X X X 21 lb. (+ 100) 206.Cross-wind gear (a) Installation 414-188003-1, -2 replacing standard installation (414-188000) X X X 17 lb. (+ 86) (b) Installation 414-188003-103, -104, replacing standard installation (18-800000-1, and -2) X 17 lb. (+ 86) 207.Cross-wind gear installation 414-188003-101, -102, replacing standard gear installation 404-188000 or 694-188000. Item 207 not to be used when Item 204 or 205 is installed. X X 17 lb. (+ 86) 208.Improved landing gear doors (E18 Type), Dwg. 404-001021. Landing gear ext. airspeed limit 160 mph. (139 knots) X X 35 lb. (+ 111) A-765 24 Rev. 78 Specifications Pertinent to All Models (cont’d) Electrical 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 301.Two 50 a. generators (a) Leece Neville 24506 X X X X X X X X 20 lb. ea. (+ 64) or (b) Beech 404-189240 X X X X X X X 20 lb. ea. (+ 64) 302.Two batteries (a) 24 v. (17 a. hr. min.) X X X X 49 lb. ea. (+ 87) or (b) 24 v. Sonotone batteries P/N 18A26 per Beech Dwg. 404-001060-5 X X 58 lb. ea. (+ 87) or (c) One 24 v. Sonotone battery, P/N 18A26 per Beech Dwg. 404-001060-7 X X 58 lb. (+ 87) 305.Landing lights (a) Grimes G-3001 X X X X X 7 lb. ea. (+ 139) or (b) GE 4557 X X X X X 2 lb. ea. (+ 105) or (c) Leading edge landing & taxiing light installation per Dwg. 404-001033 X X X X 14 lb. (+ 104) Landing Gear 306.Two 75 a. generators (a) Eclipse Type 1298-1 X 23 lb. ea. (+ 67) 307.Two 100 a. generators (a) Leece Neville 24501, Type 0-3 X X X X 32 lb. ea. (+ 64) or (b) Leece Neville 2473-G12, 15482, Type 0-5 X X X 32 lb. ea. (+ 64) or (c) Eclipse-Pioneer, Type 30E16-1 (-A, -B, etc.) X X X X X X 39 lb. ea. (+ 64) or (d) Beech Dwg. 414-180515-13 X X X X X X 39 lb. ea. (+ 64) Rev. 78 25 A-765 Specifications Pertinent to All Models (cont’d) Landing Gear D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 308.Battery (a) Two Reading R-33, 12 v. 33 a. hr. with Beech case X X X X 50 lb. (+ 87) or (b) Four Reading R-33, 12 v. 33 a. hr. with two Beech cases X X X 118 lb. (+ 102) or (c) Two Reading R-33, 12 v. 33 a. hr. with Beech case (not eligible when nose fuel tank installed) X X X X 59 lb. (+ 4) or (d) One Saft AV02022, 24 v. with Beech case, Item 307(c) required X X X 59 lb. (+ 4) or (e) One Gulton AV02022, 24 v., Item 307(c) or (d) required X X X 54 lb. (+ 4) Relay, cables, support structure and misc. hardware X X X 5 lb. (+ 4) or (f) One Gulton AV02022, 24 v., Item 307(c) or (d) required X X X 54 lb. (+ 87) Relay, cables, support structure and misc. hardware 3 lb. (+ 87) or (g) Two Sonotone, (1) 22000 Type CA24A and (1) 22000 Type CA24B in Beech battery box per Mod. C.O. B41524 or per Beech Dwg. 404-001060-1. (Not eligible with nose fuel tank installed) X X X X 55 lb. (+ 4) or (h) Two Sonotone (1) 22000 Type CA24A and (1) 22000 Type CA24B in Beech battery box per Mod. C.O. B41264 per Beech Dwg. 404-001060-3 X X X X 55 lb. (+ 87) or (i) Two Reading R-33, 12 v. 33 a. hr. with Beech case; optional with Item 632 X 59 lb. (+ 6) or (j) Two Sonotone, (1) 22000 Type CA24A and (1) 22000 Type CA24B with Beech case; optional with Item 632 X 55 lb. (+ 6) or (k) Two General Electric (1) RB211-1 and (1) RB212-1 with Beech case X 52 lb. (+ 87) or (l) Two Reading R-33, 12 v. 33 a. hr. or equivalent when installed per AC 43.13-2, Change 3 (use actual weight) X or (m) Two AR-12-36, 12 v. 36 a. hr. X 31 lb. (+ 87) 309.Two 140 a. Westinghouse 976J162-3 or Beech 18-380024 alternator-rectifiers (a) Installed per Beech Dwg. 414-001090 X X X X X X X 30 lb. (+ 64) (b) Installed per Beech Dwg. 18-361011 X 30 lb. (+ 64) A-765 26 Rev. 78 Specifications Pertinent to All Models (cont’d) Interior 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 401.(a) FAA Approved Airplane Flight Manual and pertinent revisions applicable to the particular model and serial number 2/9/48 Rev. 11/25/52 7/16/47 Rev. 7/12/48 7/19/54 Rev. 10/21/58 or 10/10/61 2/28/58 or 4/10/62 1/16/59 Rev. 1/30/61 9/29/59 or Rev. 1/30/61 6/22/62 3/8/63 (b) FAA Approved Airplane Flight Manual required with Item 605 6/20/58 6/19/58 (d) FAA Approved Airplane Flight Manual Supplement No. 2 required with Item 108 installed with Item 605 6/20/58 6/19/58 (e) FAA Approved Airplane Flight Manual Supplement No. 3 6/20/58 Rev. 12/16/60 6/19/58 Rev. 12/16/60 (f) FAA Approved Airplane Flight Manual Supplement required with Item 126 Rev. 6/18/59 Rev. 11/15/60 Rev. 11/6/59 11/6/59 or 6/8/62 (g) FAA Approved Airplane Flight Manual Supplement No. 4 required with Item 5 on D18S and C-45 Series (maximum weight 8750 lb.) 1/14/59 Rev. 7/29/60 or Rev 1/30/61 1/14/59 Rev. 7/29/60 or Rev. 1/30/61 (h) FAA Approved Airplane Flight Manual Supplement No. 1 required with Item 5 on C-45 Series (maximum weight 8750 lb.) 1/12/59 or Rev. 1/30/61 (i) FAA Approved Airplane Flight Manual Supplement No. 1 required with Item 5 in D18S (maximum weight 8750 lb.) 1/13/59 or Rev. 1/30/61 (j) FAA Approved Airplane Flight Manual Supplement required with Item 613 12/11/59 12/11/59 12/11/59 12/11/59 12/11/59 (k) FAA Approved Airplane Flight Manual Supplement required when Item 6 not installed 12/30/59 12/30/59 12/30/59 12/30/59 (n) FAA Approved Airplane Flight Manual required with Item 617 5/31/60 Rev. 1/30/61 6/1/60 Rev. 1/30/61 (t) FAA Approved Airplane Flight Manual Supplement 130017 required with Item 421 11/3/61 11/3/61 11/3/61 (u) FAA Approved Airplane Flight Manual P/N 118682 required with Item 128 when installed on G18S. 4/8/61 (v) FAA Approved Airplane Flight Manual P/N 18-001027-5 (BA-580, BA-618 through BA-631) 6/14/63 (w) FAA Approved Airplane Flight Manual P/N 18-001027-7 (BA-632 and up) 6/14/63 or 1/31/64 or 3/24/66 (x) FAA Approved Airplane Flight Manual P/N 404-001164 10/31/67 (y) FAA Approved Airplane Flight Manual P/N 130721 4/26/67 402.Two 3-min. parachute flares - International 23 lb. ea. (+ 261) X X X 23 lb. ea. (+ 290) X X X Rev. 78 27 A-765 Specifications Pertinent to All Models (cont’d) Interior 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 403.Two portable fire extinguishers (a) Pilot’s compartment Fyr-Fyter A-2 X X X X X X 7 lb. (+ 79) Passenger compartment Fyr-Fyter A-2 X X X X X X 7 lb. (+ 227) or (b) Pilot’s compartment Stop Fire MM-45 X 1 lb. (+ 102) Passenger compartment Stop Fire AT22A X 10 lb. (+ 227) or (c) Pilot’s compartment Stop Fire MM-45 X X 1 lb. (+ 102) Passenger compartment Kidde 8900 X X 7 lb. (+ 214) or (d) Pilot’s compartment Stop Fire MM-45 X X X 1 lb. (+ 102) Passenger compartment Kidde 8900 X X X 7 lb. (+ 177) 404.Chemical toilet 7 lb. (+ 249) X X X X X 7 lb. (+ 242) X X X X Placard: “THIS ROOM NOT TO BE OCCUPIED DURING TAKEOFF AND LANDING” (required on door on D18S, D18C, C-45, JRB-6 and on No. 9 bulkhead on E18S, E18S-9700, G18S and H18. 405.Air conditioning system including cabin heater 50 lb. (+ 121) X X X (Models D18S, D18C and C-45 using engine exhaust heat exchangers) 82 lb. (+ 131) X X X X (Models E18S, E18S-9700, G18S and H18 equipped with Surface Combustion 93A22 fuel burning heaters) 407.Passenger cabin baggage rack and tie-down provision installation. 6 lb. (+ 205) X X X 5 lb. (+ 205) X X X Cabin rack 400 lb. (+ 205). Cabin tie -down provisions in accordance with Dwg. 901-180204, 400 lb. (+ 205) with bulkhead 9 web removed maximum baggage forward of bulkhead 9 must be reduced to 200 lb. 408.Eclipse-Pioneer Type A-10 automatic pilot installation. (a) Operating unit installation X 70 lb. (+ 67) and (b) Aileron servo installation (Model EP-2-15-1-A) X 16 lb. (+ 77) and (c) Elevator servo installation (Model EP-2-15-1-A) X 12 lb. (+ 59) and (d) Rudder servo installation (Model EP-2-15-1-A) X 13 lb. (+ 43) 409.Lear Autopilot Model L201 (Lear installation Dwg. No. 34900) 61 lb. (+ 22) X 410.Windshield wiper - Marquette 11 lb. (+ 43) X X X X X X X X A-765 28 Rev. 78 Specifications Pertinent to All Models (cont’d) Interior 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 411.Control system lock 1 lb. (+ 62) X X X X X X X X X 412.Sperry A-12 Autopilot Model S1-104-20-B (Sperry Dwgs. 5245-90027, -90028, -90044, -90045) X 194 lb. (+ 150) 413.Lear automatic pilot installation (See also Item 409) *(a) Model 1101A (L-5) installed per Lear Dwg. list of June 6, 1949, and Dwg. 78749. Airplane Flight Manual should be supplemented to include the following: “Before takeoff, check that automatic pilot is ‘OFF’. During flight, to engage automatic pilot, X X (1) Center ‘Turn’ manual control (2) Turn automatic pilot switch to ‘Ready” (3) Turn automatic pilot switch to ‘ON’ (It will not be possible to turn switch to ‘ON’ until automatic switch is ready for operation). To disengage automatic pilot, turn automatic switch to ‘OFF’. Before landing, check that automatic pilot is ‘OFF’.” 76 lb. (+ 247) *(b)Model L-2C and optional equipment installed per Lear Dwg. as follows: (1) 91250C X X 55 lb. (+ 200) Servo stall torque measured at servo on ground: Aileron 75 5 in. - lb. Rudder 75 5 in. - lb. Elevator 75 5 in. - lb. Servo drum pitch diameters for all three axes are 1.375 in. Item 413(b)(6) required. (2) 95658 and 95658G X X 58 lb. (+ 209) Servo stall torque measured at servo on ground: Aileron 150 5 in. - lb. Elevator 150 5 in. - lb. Rudder 150 5 in. - lb. Servo drum pitch diameters for all three axes are 2.67 in. Item 413(b)(6) required. (3) Model 1404B altitude controller installation per Lear Dwg. 95658 (optional) X X 2 lb. (+ 283) (4) Model 2203 altitude controller installation per Lear Dwg. 95658G (optional) X X 2 lb. (+ 283) (5) Model 1305B approach coupler installation per Lear Dwg. 95658G (optional equip.) Item 413(b)(7) required. X X Use act. wt. & arm Rev. 78 29 A-765 Specifications Pertinent to All Models (cont’d) Interior 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 (6) Lear FAA Approved Airplane Flight Manual Supplement dated April 5, 1951, or revisions dated September 2, 1952, or November 29, 1954. Following placards required on airplane with Flight Manual Supplements dated April 5, 1951, or revision dated September 2, 1952: “DO NOT USE AUTOPILOT BELOW 300 FEET ABOVE TERRAIN IN CRUISE CONFIGURATION.” “DO NOT USE AUTOPILOT BELOW 100 FEET ABOVE TERRAIN IN APPROACH CONFIGURATION.” (7) Lear FAA Approved Airplane Flight Manual Supplement dated November 29, 1954 (with approach coupler) (c) Model L-2 installed per Beech Dwg. 414-187260 80 lb. (+ 152) X X X Rev. A (similar to Lear Kit 703292) rudder, aileron and elevator stall torques, 150 5 in. - lb., pulley p.d. 2.67 in. Lear Airplane Flight Manual Supplement dated July 17, 1956, required. (d) Model L-2 installed per following Beech Dwgs. (similar to Lear Kit 703292). (1) 414-187260 Rev. A (with Approach Coupler and Altitude Control) 80 lb. (+ 152) X X X (2) 414-187260-35 Rev. A (less Approach Coupler with Altitude Control, add sub. box 702893-02) 75 lb. (+ 160) X X X (3) 414-187260-37 Rev. A (with Approach Coupler, less Altitude Control) 77 lb. (+ 147) X X X (4) 414-187260-39 Rev. A (less Approach Coupler and Altitude Control, add sub. box 702893-02) 72 lb. (+ 154) X X X Slip Clutch Torque Settings Rudder: 150 +5 -15 in. -lb. Elevator: 150 +5 - 15 in. -lb. Aileron: 100 +15 -5 in. -lb. Pulley p.d. 2.67 in. Lear Airplane Flight Manual Supplement dated June 11, 1959, required. *414.Retractable entry step per Installation Procedure and Dwg. 62149 and 50 for kit installation by the Reed Company, Municipal Airport, 3200 Dewey Street, Santa Monica, Calif. Flite Step 9 lb. (+ 208) X X Power Unit 5 lb. (+ 221) X X 415.Electrically heated stall warning indicator installation X X X X X X X (a) Safe-Flight indicator No. 180F 2 lb. (+ 75) or (b) Safe-Flight indicator No. 180A 2 lb. (+ 75) Per Beech Dwg. 414-180611 or 404-001046 This item required with Items 616, 617, 620, 621 and 622. A-765 30 Rev. 78 Specifications Pertinent to All Models (cont’d) Interior 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 416.High pressure oxygen system (a) Beech Dwg. 414-180480 and 414-180074 68 lb. (+ 258) X (b) Beech Dwg. Mod. C.O. T5259 58 lb. (+ 53) X (c) Beech Dwg. 414-189720 and 414-180074 68 lb. (+ 51) X X X (d) Beech Dwg. 18-410011 or Beech Dwg. 404-001088-3 and -1 68 lb. (+ 48) X X X X (e) Beech Dwg. 404-001088-2 and -1 73 lb. (+ 123) X X X (f) Beech Dwg. 414-001046-1, -3 or -5 and 414-001058 or 414-001059 Use actual weight change X X X 417.Collins autopilot, Model AP-101, with flight dir. FD-104 Servo stall torque measured at servo clutch: Aileron 24 in. - lb. max., 19 in. - lb. min. Rudder 24 in. - lb. max., 19 in. - lb. min. Elevator 24. in. - lb. max., 19 in. - lb. min. Pulley Diameter 4 in., all three axes (a) Collins Dwg. 49-0018-40F-2 Rev. 3 153 lb. (+ 45.5) X 334C-2 servos are acceptable substitute for 334C-1 servos Collins Airplane Flight Manual Supplement required November 21, 1995 (334C-1 Servos) November 17, 1958 (334C-2 Servos) (b) Collins Dwg. 49-0022-126F Collins Airplane Flight Manual Supplement dated March 23, 1956, required. 155 lb. (+ 46.5) X *418.Collins radar weather mapping Model WP-101, Collins Dwg. 49-002-123D Use actual weight change 419.Combustion heater installation (a) Surface combustion 93A22 fuel burning heater with heat and vent modifications per Dwg. 404-001023 and 404-001031 62 lb. (+ 122) X X (b) Two Stewart-Warner Model 8253A (Beech P/N 404-001039-1) fuel burning heaters installation with defroster modification per Dwg. 404-001030 Sheets 1 and 2 75 lb. (+ 124) X X (c) One Stewart Warner 8253A (Beech P/N 404-001039-1) fuel burning heater installation with defroster modification per Dwg. 404-001030 Sheets 1 and 2 40 lb. (+ 124) X X 420.Collins autopilot AP-102 with flight director FD-107 installed per Beech Dwg. Mod. C.O. B47947 and Collins STC SA3-417 as amended December 22, 1959. Collins FAA Approved Airplane Flight Manual Supplement as revised December 22, 1959, required for E18S and E18S-9700. DMCR Approved Flight Manual Supplement Rev. April 12, 1960 140 lb. (+ 50) X Rev. 78 31 A-765 Specifications Pertinent to All Models (cont’d) Interior 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 421.Sperry SP-3 automatic pilot installation Item 401(t), AFM Supplement dated November 3, 1961, required (E18S, E18S-9700). AFM Supplement dated March 28, 1962, required (G18S, H18). (a) Installed per Beech Dwg. 18-500000 or 414-001035 X X X X 33 lb. (+ 202) (b) With altitude hold installed per Beech Dwg. 18-500000-101 or 414-001035 X X X X 38 lb. (+ 213) (c) With course director coupler installed per Beech Dwg. 18-500000. Eligible with Item 421(a) or (b) when used in conjunction with ARC-CD-4 course directors. X X X X 5 lb. (+ 288) 422. Cabin floor provisions, high density seating (9 chairs) (a) Per Beech Dwg. Mod. C.O. T5250 or 414-001053 X X X X X X Use act. wt. change (b) Per Beech Dwg. 404-001128 X X X X X X 423.Beech H-14 autopilot installation AFM Supplement 130043 dated August 10, 1962, or 18-001031 dated January 17, 1964, or March 5, 1964, or July 10, 1964 (G18S or H18); or 130346 dated March 15, 1963, or 18 -001033 dated August 19, 1964 (E18S and E18S-9700) required. Item 106(h) or (j) required on left engine. Installation per Beech Dwg. 18-500002 or 414-001067 for basic autopilot and accessories and Dwg. 414-001105 for optional autopilot modification. X X X X (a) Autopilot - basic (with or without Items 504 and/or 632) 50 lb. (+ 164) (b) Altitude controller (accessory) 1 lb. (+ 41) (c) Autotrim (accessory) 2 lb. (+ 263) (d) ILS coupler (accessory) 1 lb. (+ 41) 424.Air conditioner X X X X X X X 88 lb. (+ 110) Item 307 generators required with this installation. Fuel vent system must be modified on aircraft equipped with nose fuel tank. (a) Installed per Beech Dwg. 414-001064 or 18-554001. AFM Supplement 130073 dated May 25, 1962, required. (b) Installed per Beech Dwg. 414-001064. AFM Supplement 130074 dated May 10, 1962, required. 425.Cargo honeycomb floorboard installation per Beech Dwg. 404-001130 (use actual weight change) X X X X X X Allowable loadings are as follows: Bulkhead Maximum Concentrated 5 to 6 650 100 PSF 6 to 7 650 100 7 to 8 650 100 8 to 9 350 100 9 to 10 300 100 A-765 32 Rev. 78 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 501.Surface deicers (a) Two wing boots (removable) Goodrich Type 2, Model 270 X X X 14 lb. ea. (+ 109) (b) Two stabilizer boots (removable) Goodrich Type 2, Model 270 X X X X 5 lb. ea. (+ 350) (c) Deicer installation (fixed position) X X X X 41 lb. (+ 117) (d) Two wing boots (removable) Goodrich Type W, Model 270 with Beech 407-180483 (LH) and 407-180484 (RH) stall strips in lieu of Item 600 X X 14 lb. (+ 109) 502.Propeller anti-icer (a) 3 gal. fluid tank, pump and lines X X X X X X 11 lb. (+ 85) or (d) 6 gal. fluid tank, pump and lines, per Dwg. 414-189692 or 404-001064 X X X X X X X 13 lb. (+ 123) and (b) Two slinger rings - Air Associates HC-469-M-1 or HC-469 (for use with propeller Item 1) X X X 1 lb. (+ 40) or (c) Two slinger rings - Ham. Std. 54884C or Beech Mod. C.O. 69206 or Beech 644-189656 (for use with propeller Item 2 or 4). Only (a) or (d) eligible with Item 5(a)(1). X X X X X X 1 lb. (+ 40) 503.Windshield deicing system X X X X X X X X 1 lb. (+ 55) 504.Surface deicers (a) Two wing boots (removable) Goodrich Type 12, Model 270 X X X 12 lb. ea. (+ 109) (b) Two stabilizer boots (removable) Goodrich Type II, Model 270 X X X X X X X X X 5 lb. ea. (+ 350) (c) Deicer installation (fixed position) X X X X X X X X X 41 lb. (+ 117) (D18S, D18C & C-45 Series) 41 lb. (+ 109) (All others) (d) Two wing boots (removable) Goodrich Type 12, Model 270 with Beech 407-180483 (LH) and 407-180484 (RH) stall strips in lieu of Item 600 X 14 lb. ea. (+ 109) (e) Four wing boots (removable) Two Goodrich 12-270-13-1 X or Two Goodrich 12-270-14-1 X X X X and Two Goodrich 12-270-12-1 with Beech 414-181011-3 and 115101-02400 (LH) and 414-181011-4 and 115101 02400 (RH) stall strips in lieu of Item 601 27 lb. (+ 108) (f) Two vertical fin boots (removable) Goodrich Type II, Model 270 X X X X X X X X 11 lb. (+ 352) Rev. 78 33 A-765 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 505.Deicer system modifications including rubber stall strips required on aircraft equipped with deicer boots when installing Modernization Kits per (a) Dwg. 404-001040-1, -4 required with Items 305(c), 419 and 603 X X 9 lb. (+ 122) (b) Dwg. 404-001040-2, -4 required with Items 419 and 603 X X 9 lb. (+ 122) (c) Dwg. 404-001040-3, -4 required with Items 305(c) and 419 X X 7 lb. (+ 119) (d) Dwg. 404-001050-5 required with Item 208 X X 1 lb. (+ 300) (e) Dwg. 404-001040-6 required with Item 305(c) X Negligible weight 506.B.F. Goodrich electrical propeller deicing system (a) Installation per Beech Dwg. 18-960013 X X 11 lb. (+ 45) AFM Supplement P/N 130068 dated April 13, 1962, required (b) Installation per Beech Dwg. 18-960013-1, B.F. Goodrich AFM Supplement P/N 60-732 dated September 22, 1960, required X X 11 lb. (+ 45) 507.Electrically heated windshields (a) Pilot’s (P/N 18-380019-1) installed per Beech Dwg. 414-001100 X X 10 lb. (+ 63) (b) Co-pilot’s (P/N 18-380019-2) installed per Beech Dwg. 414-001100 X X 6 lb. (+ 66) (c) Pilot’s (P/N 18-380019-1) and Co-pilot’s (P/N 18-380019-2) installed per Beech Dwg. 414-001100 X X 16 lb. (+ 64) (d) Pilot’s (P/N 18-380018-1) installed per Beech Dwg. 414-001092 X X X X 7 lb. (+ 61) Miscellaneous (not listed above) 600.Metal stall strips, Beech installation 407-181211 (LH) and 407-181212 (RH) X Negligible weight 601.Metal stall strips, Beech installation 414-181011-1 and -3 (LH) and 414-181011-2 and -4 (RH) X X X X 1 lb. (+ 80) 602.Stabilizer angle of incidence change per Dwg. 404-001018 X X 2 lb. (+ 367) A-765 34 Rev. 78 Specifications Pertinent to All Models (cont’d) Miscellaneous (not listed above) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 603.Extended wing tips (E18 Type) and stall warning system per Dwg. 404-001028 and 404-001046 (Item 401(e) required) X X 22 lb. (+ 140) NOTE: This item is not eligible at a gross weight in excess of 9000 lb. unless the modifying agency complies with the limitations and inspections set forth by Beech Dwg. 404-000015. If this item has been installed in conjunction with Item 122, and if structural limitation placard (Beech P/N 404-001084) is installed, the aircraft does not have to comply with Beech Dwg. 404-000015. If, however, the inspection and limitations set forth in Dwg. 404-000015 and complied with, the placard (P/N 404-001084) may be omitted. 604.Rudder return spring installation, per Dwg. 404-001051 X X Negligible weight Deicing Equipment (Propellers, Wing and Windshield 605.Modernization kits covering basically X X (1) Installation Model E18S power plant and fuel burning heater (2) Revisions to stabilizer, rudder return spring and landing gear doors per Dwg. 404-000011 Engine limits: For all operations Sea level 36.5 in. HG. 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude 3500 ft. 35.5 in. HG. 2300 rpm. (450 hp.) Fuel: 80/87 min. grade aviation fuel with Item 2 or 5 C.G. range (landing gear extended) (+ 109.8) to (+ 117.7) at 9000 lb. (+ 107.0) to (+ 117.7) at 8600 lb. or less Straight line variation between points given Moment due to retraction of landing gear is +1200 in. - lb. Maximum weight 9000 lb. Required equipment: Items 2 or 5 or 8 or 9, 109(c), 118, 120, 208, 401(b), 602, 604 (Item 600 is required on S/N’s A-1 through A-68) Use actual weight change (Not eligible for TC-45J) 606.Right hand rudder tab installation per Dwg. 404-000010, Sheet 6 (required on D18S aircraft prior to S/N A-69 when Item 605 is installed. See Item 612. X X 7 lb. (+ 378) Rev. 78 35 A-765 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 607.Stall strips for use on aircraft with or without deicer boots (a) Stall strip installation per Dwg. 404-001048-1 (required when Item 605 installed without Item 603) X X Negligible weight (b) Stall strip installation per Dwg. 404-001048-2 (required when Item 603 installed with Item 602, or when Item 602 installed with Item 605) X X 1 lb. (+ 80) (c) Stall strip installation per Dwg. 404-001048-3 (required when Item 616 or 617 or 620 or 622 is installed) X X Negligible weight 608.Extended tail wheel installation per Dwg. 404-001054 X X 5 lb. (+ 351) 609.Nose section radio shelf installation per Dwg. 414-001021 (nose tanks, Items 108 or 115, to be removed if installed) X 19 lb. (+ 26) 610.E18S type nose section installation per Dwg. 404-001057 X X 24 lb. (+ 17) 611.Conversion from E18S to E18S-9700 per Dwg. 414-001028 (applicable to E18S S/N BA-2 and up). All E18S-9700 (Part V) limitations applicable. X Use actual weight change 612.Left hand rudder tab extension per Beech Dwg. 404-001071 (this item may be installed in lieu of Item 606 on C-45 Series) X X 1 lb. (+ 370) 613.Emergency static source installation per Beech Dwg. 404-001070 (See Item 401(j) required with this item) X X X X X X X X 1 lb. (+ 61) 614.E18S type removable nose installation per Beech Dwg. 404-001080 X X 25 lb. (+ 22) (a) With 77 gal. auxiliary fuel tank per Dwg. 404-001080 X X Combined weight of fuel and baggage must not exceed 600 lb. (arm of fuel + 32) 55 lb. (+ 30) Approved AFM Supplement P/N 118698 dated June 23, 1961, required. 615.Nose baggage provisions per Beech Dwg. 18-410012 or 18-041004 X X X X 5 lb. (+ 37) Placard: “LOAD IN ACCORDANCE WITH AIRPLANE FLIGHT MANUAL. MAXIMUM STRUCTURAL CAPACITY 600 LB.” required. 616..9300 lb. gross weight basic modernization kit per Beech Dwg. 404-000012 covering basically: X X (1) Modification of power plant package and installation of Hartzell 3-blade full-feathering propellers (2) Revisions to stabilizer, rudder return spring and landing gear doors. (3) Limitations: Structural: To be eligible for this item or Item 617 below, all D18S airplanes S/N’s A-1 through A-471 and A-474 through A-482 must have the center section truss reinforcements, P/N 513412-10 and -11, per Beech Dwg. 404-001081, or Beech Service Bulletin D18-58 A-765 36 Rev. 78 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM Engine limits: For all operations: Sea level 36.5 in. Hg 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude (3500 ft.) 35.5 in. Hg 2300 rpm. (450 hp.) Fuel: 80/87 min. grade aviation gasoline C.G. range (landing gear extended): (+ 109.8) to (+ 120.5) at 9300 lb., (+ 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: 9300 lb. (takeoff or landing) Required equipment: Item 5 or 8 or 9, 109(c), 118, 208, 415, 602, 604, 607(c), 612 (on aircraft without dual rudder tabs) Use actual weight change AFM P/N 404-001062 dated May 26, 1961, or AFM P/N 404-001089 dated May 29, 1961, required (Not eligible for TC-45J) 617. 9500 lb. gross weight modernization kit per Beech Dwg. 404-000013 covering basically X X (1) Modification of power plant package and installation of Hartzell three-blade full-feathering propellers (2) Revisions to stabilizer, rudder return spring and landing gear doors (3) Installation of E18S type wing tips (4) Limitations: Structural: To be eligible for this item, aircraft must comply with the limitations and inspections set forth in Beech Dwg. 404-000015. NOTE: Aircraft previously modified per earlier revisions of Beech Dwg. 404-000013, which incorporate the outboard wing auxiliary fuel cells and the 404-001084 structural limitation placard, do not have to comply with Beech Dwg. 404-000015. If, however, the inspections and limitations set forth in Dwg. 404-000015 are complied with, the placard (P/N 404-001084) may be omitted. Engine limits: For all operations: Sea level 36.5 in. Hg 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude (3500 ft.) 35.5 in. Hg 2300 rpm. (450 hp.) Fuel: 80/87 min. grade aviation gasoline C.G. range (landing gear extended) (+ 110.6) to (+ 120.5) at 9500 lb. At 8600 lb. or less (+ 107.0) to (+ 120.5) Straight line variation between points given Moment due to retraction of landing gear is +12000 in.-lb. Maximum weight: Landing 9400 lb., takeoff 9500 lb. Required equipment: Items 5 or 8 or 9, 109(c), 118, 208, 415, 602, 603, 604, 607(c), 612 (on aircraft with dual rudder tabs) Use actual weight change 401(n) or FAA Approved Airplane Flight Manual 118687 dated May 12, 1961, or Airplane Flight Manual P/N 118688 dated May 15, 1961, as required Rev. 78 37 A-765 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 618.Luggage and/or radio compartment in inboard wings installed per Beech Mod. C.O. B41277 in lieu of aft fuel tanks. Combined weight of luggage and/or radio equipment must not exceed 200 lb. (100 lb. each wing) X 24 lb. (+ 155) AFM as revised July 1, 1960, is required when this item is used. 619.Serial BA-563, G18S-Modified 9150 lb. gross weight, equipped with Modification Contract Order B54995, internal carburetor filter air induction installation 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.) Fuel: 80/87 minimum grade aviation gasoline C.G. range (landing gear extended): (+ 109.2) to (+ 120.5) at 9150 lb. (+ 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. Airplane Flight Manual Supplement P/N18-590012, dated December 22, 1960, required. Maximum weight 9150 lb. Required equipment: Items 5 or 8 or 9, 101, 102, 103(a), 109(a), 120, 210, 202, 301, 308, 401(u), 415, 601. 620.8950 lb. gross weight basic modernization kit per Beech Dwg. 404-000016 covering basically: X X X (1) Installation of E18S type wing tips (2) Limitations: Engine limits, fuel grade and C.G. range are the same as set forth in Section I and IV of this specification Maximum weight: 8950 lb. (takeoff or landing) Required equipment: Items 2 or 5 or 8 or 9, 101, 102, 103, 104, 109, 201, 202, 301, 302 (AFM dated June 7, 1961, or January 26, 1968, P/N 118691) (or dated October 13, 1966, P/N 130651, TC-45J only), 415, 603, 607(c), 612 (on aircraft without dual rudder tabs). Use actual weight change 621.9000 lb. gross weight basic modernization kit per Beech Dwg. 404-000017 covering basically: X X (1) Modification to power plant package by installing jet exhaust stacks (2) Installation of stabilizer angle of incidence change A-765 38 Rev. 78 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM (3) Limitations: Engine, for all operations: Sea level 36.5 in. Hg 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude 3500 ft. 35.5 in. Hg 2300 rpm. (450 hp.) Fuel: 80/87 minimum grade aviation gasoline C.G. range (landing gear extended) (+ 108.6) to (+ 120.5) at 9000 lb. (+ 107.0) to (+ 120.5) at 8500 lb. or less. Straight line variation between points given. Moment due to retraction of landing gear +12000 in.-lb. Maximum weight: 9000 lb. (takeoff or landing) Required equipment: Items 2 or 5 or 8 or 9, 101, 102, 103, 104, 109, 118, 201, 202, 301, 302, (AFM dated June 8, 1961, P/N 118693) (or dated October 14, 1966, P/N 130652, TC-45J only), 415, 604, 607(c), 612 (on aircraft without dual rudder tabs). Use actual weight change 622.9200 lb. gross weight basic modernization kit per Beech Dwg. 404-000018 covering basically: X X (1) Modification to power plant package by installing jet exhaust stacks. (2) Installation of stabilizer angle of incidence change. (3) Installation of E18S type wing tips (4) Limitations: to be eligible for this item aircraft must comply with limitations and inspections set forth in Beech Dwg. 404-000015. Engine limits, for all operations: Sea level 36.5 in. Hg 2300 rpm. (450 hp.) Straight line manifold pressure variation with altitude 3500 ft. 35.5 in. Hg 2300 rpm. (450 hp.) Fuel: 80/87 min. grade aviation gasoline. C.G. range (landing gear extended): (+ 109.4) to (+ 120.5) at 9200 lb. (+ 107.0) to (+ 120.5) at 8600 lb. or less Straight line variation between points given. Moment due to retraction of landing gear +12000 in.-lb. Maximum weight: 9200 lb. (takeoff or landing) Required equipment: Items 2 or 5 or 8 or 9, 101, 102, 103, 104, 109, 118, 201, 202, 301, 302 (AFM dated June 9, 1961, P/N 118692) (or dated October 17, 1966, P/N 130653, TC-45J only), 415, 603, 604, 607(c), 612 (on aircraft without dual rudder tabs.) Use actual weight change Rev. 78 39 A-765 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 623.9600 lb. gross weight modernization per Beech Dwg. 404-000020 Engine limits and fuel grade same as E18S-9700 C.G. range (landing gear extended): (+111.4) to (+120.5) at 9600 lb. (+107.0) to (+120.5) at 8600 lb. or less. Straight line variation between points given. Moment due to retraction of landing gear +12000 in.-lb. Maximum weight: 9600 lb. (takeoff), 9400 lb. (landing). Required equipment: Items 2, 101, 102, 103, 104, 109(c), 201, 202, 301, 308. Use actual weight change. Approved AFM P/N 130029 dated September 21, 1961, required. X 624. 9600 lb. gross weight basic modernization kit per Beech Dwg. 404-000019 covering basically: X X (1) Modification to power plant package by installing jet exhaust stacks and carburetor ram air scoop and mixer valve. (2) Installation of stabilizer angle of incidence change. (3) Installation of E18S type wing tips (4) Installation of improved landing gear doors (5) Limitations: Structural: to be eligible for this item aircraft must comply with limitations and inspections set forth in Beech Dwg. 404-000015. Engine limits and fuel grade same as E18S-9700. C.G. range (landing gear extended): (+ 111.0) to (+ 120.5) at 9600 lb. (+ 107.0) to (+ 120.5) at 8600 lb. or less Straight line variation between points given. Moment due to retraction of landing gear +12000 in.-lb. Maximum weight: 9600 lb. (takeoff), 9400 lb. (landing) Required equipment: Items 2 or 5 or 8 or 9, 101, 102, 103, 104, 109(c), 118, 201, 202, 208, 301, 302 (AFM dated September 21, 1961, P/N 404-001112) (or dated October 18, 1966, P/N 130654, TC-45J only), 415, 603, 604, 607(c), 612 (on aircraft without dual rudder tabs), required. Use actual weight change. 625.Cargo door installation per (a) Kit 726-1, Beech Dwg. 414-001051 X X (b) Kit 18-4010, Beech Dwg. 18-4010 X X X X Following data applies to both cargo doors: Approved for flight with or without cargo door panel and cabin entrance door installed. Beech placards 414-001057, 414-001074 and 414-001075 Use actual weight change. 626.Rear center section baggage bays (two) per Dwg. 404-001122 in lieu of rear auxiliary fuel tanks. X X X X X X X -24 lb. (+ 155) AFM Supplement dated October 26, 1962 (Beech P/N 18-001028) required A-765 40 Rev. 78 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 627.8950 lb. gross weight modernization kit per Beech Dwg. 404-000024 covering basically: X X (1) Installation E18S type wing tips (2) Installation of stabilizer angle of incidence change (3) Limitations: Engine limits and fuel grade are the same as set forth in Sections I and IV of this specification. C.G. range (landing gear extended): (+108.4) to (+120.5) at 8950 lb. (+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 8950 lb. (takeoff or landing) Required equipment: Item 2 or 5 or 8 or 9, 101, 102, 103, 104, 109, 201, 202, 301, 302, 415, 602, 603, 607(c), 612 (on aircraft without dual rudder tabs) Use actual weight change. AFM dated December 3, 1962, P/N 18-001029, (or dated October 20, 1966, P/N 130656, TC-45J only), required. 628.9800 lb. gross weight modernization kit per Beech Dwg. 404-000021 covering basically: X X X (1) Installation of E18S type wing tips (2) Installation of stabilizer angle of incidence change (3) Installation of H18 type power package (4) Installation of improved landing gear doors (5) Limitations: Structural: To be eligible for this item, aircraft must comply with the limitations and inspections set forth in Beech Dwg. 404-000015. Engine limits and fuel grade same as H18. C.G. range (landing gear extended): (+111.8) to (+120.5) at 9800 lb., (+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: 9800 lb. (takeoff), 9400 lb. (landing). Required equipment: Items 2 or 5 or 7 or 8, 101, 102, 103, 104, 109(c), 130, or 131, 201, 202, 208, 301, 302, 415, 603, 604, 607(c), 612 (on aircraft without dual rudder tabs) Use actual weight change. AFM dated May 3, 1963, P/N 414-001089 used with Models D18S, C-45G and H and TC-45G and H; or AFM dated February 5, 1964, used with all applicable models. 629.9900 lb. gross weight basic modernization kit per Beech Dwg. 404-000022 covering: X X X (1) Installation of E18S wing tips (2) Installation of stabilizer angle of incidence change (3) Installation of improved landing gear doors (4) Installation of H18 type power package (5) Installation of Hartzell 5-1/2 propellers Rev. 78 41 A-765 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM (6) Limitations: Structural: to be eligible for this item, aircraft must comply with the limitations and inspections set forth in Beech Dwg. 404-000015 Engine limits and fuel grade same as H18 C.G. range (landing gear extended) (+112.2) to (+120.5) at 9900 lb. (+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: 9900 lb. (takeoff), 9405 lb. (landing) Required equipment: Items 7 or 8 or 9, 101, 102, 103, 104, 109(c), 122, 130 or 131, 201, 202, 208, 301, 302, 415, 603, 604, 607(c), 612 (on aircraft without dual rudder tabs) AFM dated May 6, 1963, or January 29, 1968, P/N 404-001154 (or dated October 19, 1966, P/N 130655, TC-45J only). Use actual weight change. 630.9900 lb. gross weight basic modernization kit per Beech Dwg. 414-000014 covering: X X X (1) Installation of H18 type power package (2) Installation of Hartzell 5-1/2 propellers (3) Limitations: Engine limits and fuel grade same as H18 C.G. range (landing gear extended) (+ 112.2) to (+ 120.5) at 9900 lb. (+ 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: 9900 lb. (takeoff), 9405 lb. (landing) Required equipment: Items 7 or 8 or 9, 101, 102, 103, 104, 109(c), 122, 130 or 131, 201, 202, 208, 301, 302, 415, 603, 604, 607(c), 612 (on aircraft w ithout dual rudder tabs) Use actual weight change AFM dated May 7, 1963, P/N 414-001095 X X AFM dated May 8, 1963, P/N 414-001099 X A-765 42 Rev. 78 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 631.8750 lb. gross weight modification per Beech Dwg. 404-000026 covering: X (1) Installation of D18 type main landing gear and tail gear (2) Limitations: All limitations of Section I are applicable. Use actual weight change AFM P/N 404-001022 dated September 4, 1963, is required 632.Volpar Mark IV tricycle landing gear per Volpar Dwg. 728 (Ref. STC SA111WE) or per Beech Dwg. 18-800001 or Mod. C.O. B73831. This item eligible with any gross weight increase kit on this Specification. Use actual weight change BA-722 and after, AFM Supplement 18-001038 dated January 25, 1965, required when Goodrich multiple disc brake and wheel assembly and 8.50 x 10 8-ply or 10-ply rating type III tires are installed on main gears of the H18 according to Beech Mod. C.O. B87000A or 18-800001. X X X X X X X 633.9800 lb. gross weight basic modernization kit per Beech Dwg. 414-000015 covering: X (1) Installation of carburetor ram air scoops (2) Installation of H18 type power package (3) Limitations: Engine limits and fuel grade same as H18. C.G. range (landing gear extended): (+ 111.8) to (+ 120.5) at 9800 lb., (+ 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 9800 lb. (takeoff), 9400 lb. (landing) Required equipment: Items 2 or 5 or 7 or 8 or 9, 101, 102, 103, 104, 109(c), 130 or 131, 201, 202, 301, 308, 415, 601 Use actual weight change AFM dated October 30, 1963, P/N 130395. 634.9200 lb. gross weight basic modernization kit per Beech Dwg. 404-001160, covering: X X X (1) Installation of power package (H18 type) (2) Installation of stabilizer angle of incidence change (3) Limitations: Engine limits and fuel grade same as H18. C.G. range (landing gear extended) (+ 109.4) to (+ 120.5) at 9200 lb. (+ 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 9200 lb. (takeoff or landing). Required equipment: Items 2 or 5 or 7 or 8 or 9, 101, 102, 103, 104, 109(b), 130, 201, 202, 301, 302, 415, 602, 604, 607(c), 612 (on aircraft without dual rudder tabs). AFM dated September 26, 1963, or January 30, 1968, P/N 130377 (or dated October 24, 1966, P/N 130657 , TC-45J only) Use actual weight change. Rev. 78 43 A-765 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM 635.9400 lb. gross weight basic modernization kit per Beech Dwg. 404-001159 covering: X X X (1) Installation of power package (H18 type) (2) Installation of stabilizer angle of incidence change (3) Installation of E18S type wing tips (4) Limitations: Engine limits and fuel grade: same as H18 C.G. range (landing gear extended) (+ 110.2) to (+ 120.5) at 9400 lb. (+ 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 9400 lb. (takeoff and landing) Required equipment: Items 2 or 5 or 7 or 8 or 9, 101, 102, 103, 104, 109(b), 130, 201, 202, 301, 302, 415, 602, 603, 604, 607(c), 612 (on aircraft without dual rudder tabs). AFM dated September 25, 1963, or January 31, 1968, P/N 130375 (or dated October 21, 1966, P/N 130658, TC-45J only). Use actual weight change 636.Two 7” x 9” thermostatically controlled oil coolers and related oil system vent installation per Beech Dwg. 414-001102 X X X X X X X 10 lb. (+ 72) 637.Hamilton Standard hydromatic propeller installation and gross weight revision on Model H18, G18S and E18S-9700, Series aircraft per Beech Dwg. 18-9008 for H18, Dwg. 18-9010 for E18S-9700, and Dwg. 18-9009 for G18S X X X Limitations: All data in Section V (E18S-9700), Section VI (G18S) and Section VII (H18) apply except as noted: (a) E18S-9700 and G18S, C.G. limits, C.G. range (landing gear extended): (+ 111.0) to (+ 120.5) at 9600 lb. (max. takeoff wt.) (+ 110.2) to (+ 120.5) at 9600 lb. (max. landing wt.) (+ 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. (b) H18, C.G. limits, C.G. range (landing gear extended) (+ 111.8) to (+ 120.5) at 9800 lb. (max. takeoff wt.) (+ 110.6) to (+ 120.5) at 9500 lb. (max. landing wt.) (+ 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. (c) Maximum weight, E18S-9700, 9600 lb., H18, 9800 lb., G18S, 9600 lb. A-765 44 Rev. 78 Specifications Pertinent to All Models (cont’d) Deicing Equipment (Propellers, Wing and Windshield) D18S D18C E18S C-45G TC-45G C-45H TC-45H TC-45J RC-45J E18S- 9700 G18S H18 JRB-6 3N 3NM 3TM (d) Oil capacity, E18S-9700, 14 gal. usable at +93. (8-1/2 gal. total capacity oil tank in each nacelle, including 9.5 lb. feathering oil in each nacelle. See Note 1(c) for unusable oil. Oil capacity G18S and H18, 14 gal. usable at +93. (8-1/2 gal. total capacity oil tank in each nacelle, including 9.5 lb. feathering oil in each tank). See Note 1(c) for unusable oil. (e) Required equipment, E18S-9700, Items 2, 101, 102, 103, 104, 109(c), 120, 201, 202, 301, 308, 415, 601 and AFM 130693 dated March 3, 1967, replacing 414 -180191 dated January 30, 1961. G18S, Items 2, 101, 102, 103(b) and 109(c), 120, 201, 202, 301, 308, 415, 601, and AFM 130691 dated March 1, 1967, replacing AFM 118682 dated April 8, 1961, or AFM 130692 dated March 2, 1967, replacing AFM 18-001020 dated September 29, 1959, or revised January 30, 1961. H18, Items 2, 101(b), 102(w) and (x), 103(b), 109(c), 122, 201(c), 202 or 632, 301(b) or 307(d), 308, 415, 601, and AFM 130689 dated February 27, 1967, replacing 18-001027-7 dated June 14, 1963, or January 31, 1964, or March 24, 1966, S/N BA-632 and after or AFM 130690 dated February 28, 1967, replacing 18-001027-5 dated June 14, 1963 638.9800 lb. gross weight basic modernization kit per Beech Dwg. 18-4023 covering: X (1) Installation of power package (H18 type) (2) Limitations: Engine limits and fuel grade same as H18 C.G. range (landing gear extended): (+ 111.8) to (+ 120.5) at 9800 lb. (+ 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 9800 lb. (takeoff), 9400 lb. (landing). Required equipment: Items 2 or 5 or 7 or 8 or 9, 101, 102, 103(b) and 109(c), 120, 201, 202, 301, 308, 401(y), 415 and 601 Use actual weight change AFM dated April 26, 1967 (P/N 130721) and/or AFM dated August 18, 1965 (P/N 130225) 639.Four-position flap switch lever installed per Beech Mod. C.O. C43649. AFM Supplement 130771 dated December 18, 1967, when this item is used. X Rev. 78 45 A-765 NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include the following unusable fuel and oil (not included in the usable oil capacity or usable fuel capacity): (a) Model D18S, C-45G, C-45H, TC-45G, TC-45H, TC-45J, JRB-6, 3N, 3NM, 3TM Fuel (two 76 and two 25 gal. wing tanks) 6 lb. (+122) Fuel (47 gal. nose) None Fuel (80 or 77 gal. nose) 4 lb. (+ 32) Fuel (two 60 gal. wing tanks) 7 lb. (+145) Oil with Item 1 27 lb. (+ 60) Oil (includes 9.5 lb. feathering oil in each 52 lb. (+ 68) tank) with Item 2 Oil with Item 5 30 lb. (+ 59) (b) Model D18C Fuel 24 lb. (+131) Oil (includes 9.5 lb. feathering oil in each tank) 43 lb. (+ 70) (c) Model E18S or E18S-9700 Fuel (two 76 and two 23 gal. wing tanks) 6 lb. (+122) Fuel (77 gal. nose tank) 4 lb. (+ 32) Fuel (two 60 gal. wing tanks) 7 lb. (+145) Oil with Hamilton Std. propeller, Item 2, 52 lb. (+ 68) (includes 9.5 lb.feathering oil in each tank) Oil with Hartzell propeller, Item 5 30 lb. (+ 59) (d) Model G18S Fuel (two 76 and two 23 gal. wing tanks) 6 lb. (+122) Fuel (two 60 gal. wing tanks) 7 lb. (+145) Oil with Hartzell propeller Item 5 30 lb. (+ 58) (e) Model G18S (with Item 618 installed) Fuel (two 76 gal. wing tanks) 6 lb. (+122) Fuel (two 60 gal. wing tanks) 7 lb. (+145) Oil with Hartzell propeller, Item 5 30 lb. (+ 58) (f) Model H18 Fuel (two 76 and two 23 gal. wing tanks) 6 lb. (+122) or Fuel (two 99 gal. wing tanks) 32 lb. (+128) and Fuel (two 60 gal. wing fuel tanks) 7 lb. (+145) and Oil 30 lb. (+ 58) NOTE 2. The following placards must be displayed: (a) Instrument panel, in full view of pilot: (1) "This airplane must be operated in compliance with the Operating Limitations Section of the FAA Approved Airplane Flight Manual." (2) "All intentional acrobatic maneuvers prohibited." (3) When the diameter of the propeller (Item 4) exceeds 8'0", the following placard must be installed and the tachometer marked accordingly: "Avoid continuous operation between 1850 and 2000 r.p.m." (b) Toilet compartment (when installed): "This room not to be occupied during takeoff and landing." (c) On window sill adjacent to 18-534018-1, -2, -3 cabin chairs, when installed facing aft, "Fully recline aft facing seats during takeoff and landing." (d) At aft baggage compartment: "Maximum 150 lb./shelf, 300 lb. total. See loading schedule." (With shelf installed). "Baggage loading, maximum 300 lb. See loading schedule." (Without shelf installed). (e) On airplanes with nose baggage provisions, on inner side of nose door: "Load in accordance with Airplane Flight Manual. Maximum structural capacity of nose 600 lb." NOTE 3. Engine nameplate: When any of the eligible military engines are installed, the following information must be added to the engine nameplate: "FAA Specification No. 5E1". A-765 46 Rev. 78 NOTE 4. Prior to civil certification, C-45G, C-45H, TC-45G and TC-45H aircraft which have been operated by the military services must be modified in accordance with Beech Dwg. 404-001011 and Beech Spec. BS-2466; TC-45J or RC-45J aircraft which have been operated by military services must be modified in accordance with Beech Dwg. 404-001100. JRB-6 aircraft which have been operated by the military services must be modified in accordance with Beech Dwg. 404-001139. 3N, 3NM and 3TM aircraft which have been operated by the Canadian Government must be modified in accordance with Beech Dwg. 18-5011. Serial Nos. Eligible (use manufacturer's Serial Nos. when available) C-45G and H Beech Serial Nos. AF Serial Nos. AF-1 through AF-60 51-11444 through 51-11503 AF-157 through AF-468 51-11600 through 51-11911 AF-469 through AF-900 52-10539 through 52-10970 TC-45G and H Beech Serial Nos. AF Serial Nos. AF-61 through AF-156 51-11504 through 51-11599 BuAer Serial Nos. All TC-45J or UC-45J serial numbers contain five digits except for the first group listed. All JRB-6 serial numbers contain five digits. For brevity, when the first three digits of a group of serials are identical, the first three numbers are listed only once. A dash between adjacent numbers shows a consecutive group of serials. TC-45J or UC-45J 3554, 3555, 3557, 3558, 3561, 4711 -4716, 4718-4721, 4725, 9771 12355, 64, 66, 67, 70-72, 74, 76-79, 81-83, 86, 88, 89 23759, 63, 68, 70, 72-74, 76, 79, 83, 86, 88, 90, 91, 95, 97, 98 23800, 02, 04, 06, 11, 15, 16, 18 -25, 27 - 29, 31, 33-37, 39-47, 49, 51-54, 56 29551, 53-59, 61, 64, 65, 68-72, 75, 76, 78, 79, 81, 82, 84, 87, 88, 90 -95, 97, 99 29602, 03, 08, 09, 13, 17, 19 -23, 25-27, 29-33, 35-42, 44, 46-52, 55, 57, 59-64 39195, 97 39202, 05, 06, 08, 12, 13, 19, 24 - 30, 32, 33, 35, 37, 39-41, 43-57, 60, 62-67, 69, 72-78, 80-82, 84, 86, 87, 89, 90 39749, 50, 52, 54, 58-62, 65, 67, 68, 72, 73, 75 -78, 82, 88, 89, 93, 97, 99 39801, 03, 04, 06, 07, 09, 10, 12, 13, 15 16, 22, 27, 29, 38, 40 -42, 47, 50, 51, 53, 54, 56, 62, 63, 65-67, 69, 70, 75, 77, 81-83, 85-87, 89, 98, 99 39902, 04, 06, 08-10, 15, 16, 20, 22, 23, 27, 28, 30, 31, 34 -39, 41-43, 45, 47, 48 51, 56, 58, 59, 61, 63, 65, 66, 68-70, 73, 76, 77, 80, 82, 83, 88, 90, 94 44555, 60, 65, 76, 78 - 81, 83, 88, 99 44605, 07, 10, 17, 24, 55, 58, 62, 77 48247 51026-29, 31, 32, 34, 36, 38, 39, 41, 45 -47, 53-57, 61, 64-66, 68-79, 81, 83-86, 89-92, 94, 96, 98 51100, 01, 04, 05, 07, 08-10, 12, 14-22, 24-26, 28, 30-32, 35, 37-41, 43-52, 54-58, 60, 61, 63-73, 76, 78, 80-83, 85-89, 91, 92, 94 - 98 51200, 01, 04, 06, 07-11, 13, 16, 19, 20, 24-26, 28-30, 32, 35, 37-41, 43-52, 53-57, 59-63, 68, 70-75, 77-81, 84, 85, 87 - 91, 93 - 99 51300, 02, 03, 07, 08, 11, 12, 14, 15, 17 -19, 23, 27, 30, 33-35, 38, 39, 42-46, 49 66429, 31, 43, 48, 64, 70 67103, 05, 07, 11, 12, 14 - 20, 22, 23, 26, 28, 29, 58, 59, 61 - 63, 65 - 68, 70, 74 - 77, 79, 81-85, 87, 88, 90, 91, 93, 94, 97, 98 67200-14, 18-24, 27, 28, 30, 34 - 36, 56, 61-63, 65, 67-69, 71, 74, 75, 77-81, 85, 87, 88, 93, 94, 96 -98 67300, 02, 03, 05, 11-14, 16, 17, 19 - 26, 29, 35, 37, 44 - 47, 49, 55, 61, 63, 82, 83 76740-42, 45, 46, 50, 53, 55-58, 62, 64, 65, 71, 73, 74, 76 85100, 06, 10, 15, 21, 35 89466, 67-71, 73-75, 77-79, 81-85, 87, 88, 91, 93, 94 90522, 36, 49, 69, 74, 81 140987-140991 Rev. 78 47 A-765 NOTE 4 (cont’d) JRB-6 39763, 69, 71, 79-81, 83, 87, 95, 96 39814, 17, 20, 23, 30, 32, 33, 45, 46, 52, 57 -59, 71, 79, 84 39901, 03, 21, 32, 40, 52, 53, 62, 64, 74, 79, 85 -87, 91-93, 95-97 51035, 37, 48, 60, 67, 80, 82 67248, 76, 82-84, 86 67328, 32-36, 38-40, 43, 48, 50, 52, 57, 58, 60, 66, 74, 76, 79 -81 3N Beech Serial Nos. Canadian Serial Nos. A-601 through A-700 CA-1 through CA-100 3NM Beech Serial Nos. Canadian Serial Nos. A-702 through A-715 CA-102 through CA-115 A-736 through A-755 CA-136 through CA-155 A-767 through A-769 CA-176 through CA-194 A-780, A-782, A-784 CA-201 through CA-280 A-786, A-788 A-790 through A-800 A-851 through A-930 3TM Beech Serial Nos. Canadian Serial Nos. A-701 CA-101 A-716 through A-735 CA-116 through CA-135 A-756 through A-766 CA-156 through CA-175 A-770 through A-779 CA-195 through CA-200 A-781, A-783, A-785 CA-281 A-787, A-789, A-931 RC-45J 4715, 4718 09771 12354, 73, 75, 85 23789, 93 23801, 13 29566, 80, 83, 85 29604, 18, 45 39196 39203, 10, 17, 31, 34, 58 51129, 90 51214, 18, 33, 51, 67, 69 51329 66459 67108, 24, 27 67217, 32, 33 A-765 48 Rev. 78 NOTE 5. Cargo loadings for standard cabin floorboard (bulkhead 5 is just aft of pilot's compartment at fuselage sta. 104.0) Bulkhead Maximum Concentrated 5 to 6 450 100 PSF 6 to 7 450 100 7 to 8 450 100 8 to 9 300 100 9 to 10 300 100 Cargo loadings for cabin floorboard that has been modified per Beech Dwg. 414-001051 or 18-4010 (with or without honeycomb floorboard) (bulkhead 5 is just aft of pilot's compartment at fuselage sta. 104.0) Bulkhead Maximum Concentrated 5 to 6 650 100 PSF 6 to 7 650 100 7 to 8 650 100 8 to 9 350 100 9 to 10 300 100 NOTE 6. Prior to civil certification of any military airplane, install wing spar strap which reinforces the lower spar cap from LWS 181 to RWS 181. Consult STC Summary or applicable AD's for eligible installation. ---- END ---- ``` ## ADs (28, in force first) - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 99-05-13 R1 WD](https://openairdocs.org/ad/99-05-13-R1-WD): Withdrawal of AD 99-05-13 · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Jul 5, 2000 - [AD 81-18-07](https://openairdocs.org/ad/81-18-07): Tricycle Landing Gear · Textron 3N, 3NM, 3TM and 13 more. Effective Sep 10, 1981 - [AD 72-16-02 R3](https://openairdocs.org/ad/72-16-02-R3): Volpar Nose Landing Gear Fork · Volpar Mark IV tricycle landing gear (Southwestern Aero Exchange STC SA111WE or 2 others). Effective Apr 16, 1981 - [AD 75-27-09 R2](https://openairdocs.org/ad/75-27-09-R2): Wing Structure · Textron 18A, 18D, 18S (Army C-45C) and 27 more. Effective Aug 21, 1980 - [AD 78-10-01](https://openairdocs.org/ad/78-10-01): Lower Rudder Torque Tube · United Aircraft of Canada Ltd. PT6 series engines (Staggerwing Museum Foundation STC SA1016WE or 2 others). Effective May 17, 1978 - [AD 77-19-07](https://openairdocs.org/ad/77-19-07): Control Column Assembly · Textron 18A, 18D, 18S (Army C-45C) and 27 more. Effective Sep 29, 1977 - [AD 72-25-06](https://openairdocs.org/ad/72-25-06): Nose Gear Extension · Volpar Mark IV tricycle landing gear (Southwestern Aero Exchange STC SA111WE or 2 others). Effective Dec 9, 1972 - [AD 68-23-06](https://openairdocs.org/ad/68-23-06): Internal Portion of Beech Center Section Wing Truss Assembly · Textron C-45G, C-45H, D18C and 9 more. Effective Dec 19, 1968 - [AD 67-26-04](https://openairdocs.org/ad/67-26-04): Altimeters · Bell Helicopter Textron Canada 206A, 150G, 172H (USAF T-41A) and 36 more - [AD 66-30-01](https://openairdocs.org/ad/66-30-01): Static Pressure Line · Volpar Mark IV tricycle landing gear (Southwestern Aero Exchange STC SA111WE or SA4-1531) - [AD 65-03-01](https://openairdocs.org/ad/65-03-01): Gap Seal Strips · Recertification under subparts B &G of CAR 3 and installation… (Staggerwing Museum Foundation STC SA2-1016 or 7 others) - [AD 60-16-01](https://openairdocs.org/ad/60-16-01): Emergency Electric Switch/Seats · Textron C-45G, C-45H, TC-45G and 1 more - [AD 47-33-05](https://openairdocs.org/ad/47-33-05): Horizontal Stabilizer Spar · Textron Army AT-11, C18S and D18S - [AD 47-33-06](https://openairdocs.org/ad/47-33-06): Stabilizer Spar Replacement · Textron D18C, D18C-T and D18S - [AD 47-33-07](https://openairdocs.org/ad/47-33-07): Alternate Static Source · Textron D18C, D18C-T and D18S - [AD 47-34-01](https://openairdocs.org/ad/47-34-01): Expansion Type Filler Cap · Textron D18C and D18S - [AD 47-34-02](https://openairdocs.org/ad/47-34-02): Tail Cone Drain Holes · Textron D18C, D18C-T and D18S - [AD 47-34-03](https://openairdocs.org/ad/47-34-03): Fuel Cell Seal · Textron D18C and D18S - [AD 48-13-01](https://openairdocs.org/ad/48-13-01): Generator Control Box Insulation · Textron D18C and D18S - [AD 48-34-01](https://openairdocs.org/ad/48-34-01): Stabilizer Attachment Fittings · Textron Army AT-11, C18S, D18C and 2 more - [AD 49-29-02](https://openairdocs.org/ad/49-29-02): Rudder Spring Bushings · Textron D18C, D18C-T and D18S - [AD 53-26-01](https://openairdocs.org/ad/53-26-01): Ignition Switch · Briggs & Stratton Ignition Switches, Army AT-11, C18S and 3 more - [AD 56-20-01](https://openairdocs.org/ad/56-20-01): Tailwheel Axle · Textron E18S - [AD 59-18-02](https://openairdocs.org/ad/59-18-02): Fuel Line Modification · Textron C-45G, C-45H, D18S and 2 more - [AD 99-05-13](https://openairdocs.org/ad/99-05-13) (historical): Fuel Tank Selector · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Apr 19, 1999 ## Registered aircraft by registry model (OpenAirDocs) - [Beech D18S](https://openairdocs.org/model/beech-d18s): 55 aircraft (registry code 1151004) - [Beech E18S](https://openairdocs.org/model/beech-e18s): 51 aircraft (registry codes 1151006, 1151007) - [Beech C-45H](https://openairdocs.org/model/beech-c-45h): 50 aircraft (registry codes 1151018, 1151019) - [Beech H-18](https://openairdocs.org/model/beech-h-18): 28 aircraft (registry code 1151012) - [Beech G18S](https://openairdocs.org/model/beech-g18s): 23 aircraft (registry code 1151010) - [Beech 3NM](https://openairdocs.org/model/beech-3nm): 11 aircraft (registry code 1151044) - [Beech C-45G](https://openairdocs.org/model/beech-c-45g): 9 aircraft (registry code 1151014) - [Beech UC-45J](https://openairdocs.org/model/beech-uc-45j): 9 aircraft (registry code 1150911) - [Beech E18S-9700](https://openairdocs.org/model/beech-e18s-9700): 7 aircraft (registry code 1151008) - [Beech TC-45J](https://openairdocs.org/model/beech-tc-45j): 5 aircraft (registry code 1151022) - [Beech RC-45J](https://openairdocs.org/model/beech-rc-45j): 4 aircraft (registry code 1151021) - [Beech 3 TM](https://openairdocs.org/model/beech-3-tm): 3 aircraft (registry code 1151040) - [Beech 3N](https://openairdocs.org/model/beech-3n): 2 aircraft (registry code 1151042) - [Beech TC-45G](https://openairdocs.org/model/beech-tc-45g): 2 aircraft (registry code 1151016) - [Beech C45G VOLPAR TURBO](https://openairdocs.org/model/beech-c45g-volpar-turbo): 0 aircraft (registry code 1151017) - [Beech D18C](https://openairdocs.org/model/beech-d18c): 0 aircraft (registry code 1151002) - [Beech JRB-6](https://openairdocs.org/model/beech-jrb-6): 0 aircraft (registry code 1151026) - [Beech TC-45H](https://openairdocs.org/model/beech-tc-45h): 0 aircraft (registry code 1151020) - [Beechcraft UC-45J](https://openairdocs.org/model/beechcraft-uc-45j): 0 aircraft (registry code 4210120) ## STCs approved under this data sheet (532, first 50) - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA7965SW](https://openairdocs.org/stc/SA7965SW): Application of fabric and polyurethane finishing system.. Shady Aviation LLC - [STC SA01240SE](https://openairdocs.org/stc/SA01240SE): Installation of secondary voltage indication system. Visual Instruments LLC - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc. - [STC SA1222GL](https://openairdocs.org/stc/SA1222GL): Replace existing main wheels and brakes with Cleveland 40-211/30-170.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA788GL](https://openairdocs.org/stc/SA788GL): Installation of Cleveland wheels and brakes conversion kit #199-127.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA829GL](https://openairdocs.org/stc/SA829GL): Installation of Cleveland wheels and brakes conversion kit No. 199-129.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc. - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC - [STC SA02430SE](https://openairdocs.org/stc/SA02430SE): Fabrication and installation of a camera housing. Airborne Sensor LLC - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA5190NM](https://openairdocs.org/stc/SA5190NM): Installation of Gustin Aviation chip detector light system.. A & L Aircraft Parts Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA377NW](https://openairdocs.org/stc/SA377NW): Installation of Hartzell HC-B3W30-2E/W10160R-6 and/or W10160-6 propellers, governors, and spinners on Pratt and Whitney R-985 series engines. Kenmore Air Harbor Inc - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA02503AK](https://openairdocs.org/stc/SA02503AK): Installation of AMSAFE State of the Art Restraint System (SOARS) inflatable restraints. AMSAFE Inc. - [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation - [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments - [STC SA6070NM](https://openairdocs.org/stc/SA6070NM): Installation of a 'quick-disconnect drain plug' on the engine rocker sump for the oil drain retrieval system after engine shutdown.. West Coast Air Creations - [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments - [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation - [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation - [STC SA207CE](https://openairdocs.org/stc/SA207CE): Pratt & Whitney R-985-APS engines per STC SE4-864 in aircraft with Beech 9,900 lbs. gross weight kit 766-1.. Textron Aviation Inc - [STC SA00944CH](https://openairdocs.org/stc/SA00944CH): Replace Janitrol combustion heater Model 81D94-X (XX) with C&D Associates combustion heater Model CD25K, CD35K, and CD45K. Hartzell Engine Technologies, LLC - [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc - [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [STC SA01229SE PAGE 2](https://openairdocs.org/stc/SA01229SE%20PAGE%202): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc - [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC - [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02930NY](https://openairdocs.org/stc/SA02930NY): Installation of Insight Instrument Corporation Graphic Engine Monitor (GEM 610C) models G3, G2, and G1 and 1200C model G4 as primary Cylinder Head Temperature (CHT), Exhaust Gas Temperature (EGT), and Turbine Inlet Temperature (TIT) Instruments. Insight Instrument Corporation All 532: https://openairdocs.org/tcds/A-765/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.