TCDS 1A3

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev No. 40 35 35 35 38 35 35 35 35 36 35 35 35 35 35 35 35 38 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A3 Revision 40 BELLANCA AIRCRAFT 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31 17-31TC March 5, 2024 AIRCRAFT SPECIFICATION NO. 1A3 Type Certificate Holder Bellanca Aircraft, Inc. 3620 Sacramento Drive, Suite 100 San Luis Obispo, CA 93401 Type Certificate Holder Record Bellanca Aircraft Corp. transferred TC 1A3 to Viking Aviation, Inc. on March 26, 1982 Viking Aviation, Inc. transferred TC 1A3 to Bellanca, Inc. on June 11, 1982 Bellanca, Inc. transferred TC 1A3 to Alexandria Aircraft LLC on May 30, 2002 Alexandria Aircraft LLC . transferred TC 1A3 to Bellanca Aircraft, Inc. on March 5, 2024 I - Model 14-19, 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved September 26, 1949 Engine Lycoming O-435-A Fuel 80 minimum grade aviation gasoline Engine limits For all operations, 2550 r.p.m. (190 hp.) Airspeed limits Never exceed 226 m.p.h. (197 knots) True Ind. Maximum structural cruising 167 m.p.h. (145 knots) True Ind. Maneuvering (Normal Category) 115 m.p.h. (100 knots) True Ind. Maneuvering (Utility Category) 124 m.p.h. (108 knots) True Ind. Flaps extended 86 m.p.h. ( 75 knots) True Ind. Landing gear extended 167 m.p.h. (145 knots) True Ind. Landing gear operation 125 m.p.h. (108 knots) True Ind. C.G. range (landing) Normal Category (+19.9) to (+24.4) at 2600 lb. gear extended) Utility Category (+19.8) to (+24.4) at 2400 lb. Both Categories (+16.4) to (+24.4) at 1800 lb. or less Straight line variation between points given 1A3 Page 2 of 19 1 6 1 8 2 0 2 2 INCHES 2 8 0 0 2 4 0 0 1 6 0 0 1 4 0 0 LB. FWD. LIM IT 1 8 0 0 2 0 0 0 2 2 0 0 2 6 0 0 REA R LIM IT 2 4 Empty weight C.G. range None Maximum weight Normal Category 2600 lb. Utility Category 2400 lb. I - Model 14-19 (con'd) No. of seats 4 (2 at +20, 2 at +53) Maximum baggage Normal Utility Category Category Without auxiliary fuel tank 198 lb. (+84) 171 lb. (+84) With empty auxiliary fuel tank 186 lb. (+84) 159 lb. (+84) (item 104) (see loading schedule) Fuel capacity Main wing tanks 40 gal. (+29). See items 104, 105 and 106 for auxiliary tanks. Oil capacity 12 qt. (-35) Control surface movements Elevator trim tab Up 12° Down 29° (within + 1°) Elevator Up 22° Down 15° Aileron Up 20° Down 20° Rudders Right 22° Left 22° Flaps Down 46° Serial Nos. eligible 2000, 2002 thru 4000 Required equipment Items 1 or 2, 102, 103, 110(c), 201, 202(a), 204(a) and 401(a) II - Model 14-19-2, 4 PCLM (Normal Category), Approved January 7, 1957 Engine Continental O-470-K Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2600 r.p.m. (230 hp.) Airspeed limits Never exceed 226 m.p.h. (197 knots) True Ind. Maximum structural cruising 167 m.p.h. (145 knots) True Ind. Maneuvering 115 m.p.h. (100 knots) True Ind. Flaps extended 86 m.p.h. ( 75 knots) True Ind. Landing gear extended 167 m.p.h. (145 knots) True Ind. Landing gear operation 124 m.p.h. (108 knots) True Ind. C.G. range (landing) (+20.5) to (+24.4) at 2700 lb. gear extended) (+16.4) to (+24.4) at 1800 lb. or less Straight line variation between points given Page 3 of 19 1A3 1 6 2 8 0 0 1 8 2 0 22 2 4 INCHES 2 6 0 0 2 4 0 0 2 2 0 0 2 0 0 0 1 8 0 0 LB. FWD. LIM IT REA R LIM IT Empty weight C.G. range None Maximum weight 2700 lb. No. of seats 4 (2 at +20, 2 at +53) Maximum baggage (see Without auxiliary fuel tank: 198 lb. (+84) loading schedule) With empty auxiliary fuel tank (item 105): 186 lb. (+84) 1A3 Page 4 of 19 II - Model 14-19-2 (cont'd) Fuel capacity Main wing tanks 40 gal. (+29). See item 105 or item 112 for auxiliary tank and NOTE 1 for data on system fuel. Oil capacity 12 qt. (-35), 7 qt. usable. See NOTE 1 for data on system oil. Control surface movements Elevator trim tab Up 12° Down 29° (within + 1°) Elevator Up 22° Down 15° Aileron Up 20° Down 20° Rudders Right 22° Left 22° Flaps Down 46° Serial Nos. eligible 4001 thru 4105 Required equipment Items 3 or 4, 107, 108, 201, 202(a), 204(a), 401(b) or (c) and 403 III - Model 14-19-3, 4 PCLM (Normal Category), Approved February 20, 1959 Engine Continental IO-470-F Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 2625 r.p.m. (260 hp.) Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS Maximum structural cruising 167 m.p.h. (145 knots) CAS Maneuvering 115 m.p.h. (100 knots) CAS Flaps extended 110 m.p.h. ( 96 knots) CAS Landing gear extended 167 m.p.h. (145 knots) CAS Landing gear operation 124 m.p.h. (108 knots) CAS C.G. range (landing) (+20.5) to (+24.4) at 2700 lb. gear extended) (+17.5) to (+24.4) at 2200 lb. or less Straight line variation between points given 1 6 2 8 0 0 1 8 2 0 22 2 4 INCHES 2 6 0 0 2 4 0 0 2 0 0 0 1 9 0 0 LB. FWD. LIM IT2 1 0 0 2 2 0 0 2 3 0 0 2 5 0 0 2 7 0 0 REA R LIM IT Empty weight C.G. range None Maximum weight 2700 lb. No. of seats 4 (2 at +20, 2 at +53) Maximum baggage 186 lb. (+84). (See loading schedule). Fuel capacity Main wing tanks 39.2 gal. (+29). See item 112 for auxiliary tank and NOTE 1 for data on system fuel. O il capacity 12 qt. (-35), 7 qt. usable. See NOTE 1 for data on system oil. Control surface movements Elevator trim tab Up 12° Down 29° (within +1°) Elevator Up 22° Down 15° Aileron Up 20° Down 20° Rudder Right 22° Left 22° Flaps Down 46° Serial Nos. eligible 4106 thru 4228 Required equipment Items 5 or 6, 107, 108, 201(c) or (d), 202(a) or (c), 205(a), (b) or (e) and (c) or (d) or 205(f) and (g), 401(d) and 403 IV - Model 14-19-3A, 4 PCLM (Normal Category), Approved March 1, 1963 Page 5 of 19 1A3 Engine Continental IO-470-F Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 2625 r.p.m. (260 hp.) Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS Maximum structural cruising 190 m.p.h. (165 knots) CAS Maneuvering 142 m.p.h. (123 knots) CAS Flaps extended 120 m.p.h. (104 knots) CAS Landing gear extended 167 m.p.h. (145 knots) CAS Landing gear operation 140 m.p.h. (122 knots) CAS C.G. range (landing) (+19.8) to (+23.0) at 3000 lb. gear extended) (+17.75) to (+23.0) at 2350 lb. or less Straight line variation between points given 1 7 1 9 2 1 2 3 INCHES 3 2 0 0 2 8 0 0 2 0 0 0 1 8 0 0 LB. FWD. LIM IT 2 2 0 0 2 4 0 0 2 6 0 0 3 0 0 0 REA R LIM IT 2 5 Empty weight C.G. range None Maximum weight 3000 lb. No. of seats 4 (2 at +20, 2 at +53) Maximum baggage 186 lb. (+84). (See loading schedule). Fuel capacity 58 gal. usable (2 wing tanks 19 gal. each at +29, and 1 auxiliary tank in fuselage 20 gal. at +72). See item 113 for optional auxiliary tanks in outboard wing panels and NOTE 1 for data on system fuel. Oil capacity 12 qt. (-35), 7 qt. usable. See NOTE 1 for data on system oil. Control surface movements Elevator trim tab Up 7° Down 34.5° (within +1°) Elevator Up 22° Down 15° Aileron Up 20° Down 20° Rudder Right 22° Left 22° Flaps Down 46° Serial Nos. eligible 4229 thru 4342 Required equipment Items 7, 107, 108, 201(c) or (d), 202(a) or (c), 205(f) and (h), 401(e) and 403 V - Model 17-30, 4 PCLM (Normal Category), Approved September 23, 1966 Engine Continental IO-520-D Fuel 100/130 minimum grade aviation gasoline Engine limits Takeoff: 2850 r.p.m. (300 hp.) (5 min. maximum) Max. continuous operation: 2700 r.p.m (285 hp.) Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS Maximum structural cruising 190 m.p.h. (165 knots) CAS Maneuvering 142 m.p.h. (123 knots) CAS Flaps extended 120 m.p.h. (104 knots) CAS Landing gear extended 167 m.p.h. (145 knots) CAS Landing gear operation 140 m.p.h. (122 knots) CAS 1A3 Page 6 of 19 V - Model 17-30 (cont'd) C.G. range (landing) (+19.8) to (+24.0) at 3000 lb. gear extended) (+17.75) at 2400 lb. or less Straight line variation between points given 1 7 1 9 2 1 2 3 INCHES 3 2 0 0 2 8 0 0 2 0 0 0 1 8 0 0 LB. FWD. LIM IT 2 2 0 0 2 4 0 0 2 6 0 0 3 0 0 0 REA R LIM IT 2 5 Empty weight C.G. range None Maximum weight 3000 lb. (See NOTE 4 for 3200 lb. airplanes) No. of seats 4 (2 at +20, 2 at +53) Maximum baggage 186 lb. (+84), 35 lb. min. (See loading schedule). Fuel capacity 58 gal. usable (2 wing tanks, 19 gal. ea. at +29, and 1 auxiliary tank in fuselage 20 gal. at +72). See item 113 for optional auxiliary tanks in outboard wing panels and NOTE 1 for data on system fuel. Oil capacity 12 qt. (-41), 6.3 qt. usable. See NOTE 1 for data on system oil. Control surface movements Elevator trim tab Up 7° Down 34.5° (within +1°) Elevator Up 22° Down 15° Aileron Up 20° Down 20° Rudder Right 22° Left 22° Flaps Down 46° Serial Nos. eligible 30001 thru 30262 excluding 30004 Required equipment Items 8 or 9 or 10 or 11, 101(d) or (f), 107(c) or (d) or (g), 108(b), 110(c), 111(a), 201(d), 202(c), 205(f) and (h), 301(c) or 304(b), 302(f) or (g), 401(f) and 403. VI - Model 17-31TC, 4 PCLM (Normal Category), Approved February 20, 1969 Engine Lycoming IO-540-G1E5, with two (2) Rajay Model 315A10-2 Turbochargers per STC SE6WE Fuel 100/130 minimum grade aviation gasoline Engine limits Non turbo charged: all operations 2575 RPM (290 hp.) Turbo charged: all operations 2400 RPM 27.0 in. Hg (250 hp) Turbocharger used only with throttle full open Minimum turbocharger - 2200 RPM Maximum operating 24,000 ft with oxygen 12,000 ft. without oxygen Altitude Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS Below 15,000 ft. Maximum structural cruising 190 m.p.h. (165 knots) CAS Maneuvering 142 m.p.h. (123 knots) CAS Flaps extended 120 m.p.h. (104 knots) CAS Landing gear extended 167 m.p.h. (145 knots) CAS Landing gear operation 140 m.p.h. (122 knots) CAS Above 15,000 ft. Same as below 15,000 ft. except Never exceed 200 m.p.h. (174 knots) CAS Maximum structural cruising 165 m.p.h. (144 knots) CAS C.G. range (landing) (+19.8) to (+24.0) at 3000 lb. gear extended) (+17.75) to (+24.0) at 2400 lb. or less Straight line variation between points given VI - Model 17-31TC (cont'd) Page 7 of 19 1A3 1 6 1 8 2 0 2 2 INCHES 3 0 0 0 2 8 0 0 2 4 0 0 2 3 0 0 LB. FORWA RD LIM ITS 2 5 0 0 2 6 0 0 2 7 0 0 2 9 0 0 A FT. LIM ITS 2 4 Empty weight C.G. range None Maximum weight 3000 lb. (See NOTE 4 for 3200 lb. airplanes) No. of seats 4 (2 at +20, 2 at +53) Maximum baggage 166 lb. max. (+84), 35 lb. min. (See loading schedule). Fuel capacity 72 gal. usable (2 wing tanks, 19 gal. ea. at +29, and 2 auxiliary tanks in ` wing, 17 gal. each at +29). See NOTE 1 for data on unusable fuel. Oil capacity 12 qt. (-42), 9 1/4 qt. usable. See NOTE 1 for data on undrainable oil. Control surface movements Elevator trim tab Up 7° Down 34.5° (within +1°) Elevator Up 22° Down 15° Aileron Up 20° Down 20° Rudder Left 22° Right 22° Flaps Down 46° Serial Nos. eligible 31001 thru 31003 Required equipment Items 12, 101(e), 107(e), 107(f) or (g), 108(c), 111(a), 113, 114, 201(e), 202(d), 205(b) and (j), 302(g), 304, 401(g) and 403. Item 404 is required for flight above 12,000 ft. VII - Model 17-31, 4 PCLM (Normal Category), Approved April 29, 1969. Engine Lycoming IO-540-G1B5 (except IO-540-G1E5 for S/N 32-1 only) Fuel 100/130 minimum grade aviation gasoline Engine limits All operations 2575 RPM (290 hp) Airspeed limits Never exceed 226 m.p.h. (197 knots) CAS Maximum structural cruising 90 m.p.h. (165 knots) CAS Maneuvering 142 m.p.h. (123 knots) CAS Flaps extended 120 m.p.h. (104 knots) CAS Landing gear extended 167 m.p.h. (145 knots) CAS Landing gear operation 140 m.p.h. (122 knots) CAS C.G. range (landing) (+19.8) to (+24.0) at 3000 lb. gear extended) (+17.75) TO (+24.0) at 2400 lb. or less Straight line variation between points given 1 7 19 2 1 2 3 INCHES 3 0 0 0 2 8 0 0 2 4 0 0 2 3 0 0 LB. FORWA RD LIM ITS 2 5 0 0 2 6 0 0 2 7 0 0 2 9 0 0 A FT. LIM ITS 2 5 1A3 Page 8 of 19 VII - Model 17-31 (cont'd) Empty weight C.G. range None Maximum weight 3000 lb. (See NOTE 4 for 3200 lb. airplanes) No. of seats 4 (2 at +20, 2 at +53) Maximum baggage 166 lb. max. (+84), 35 lb. min. (See loading schedule). Fuel capacity 58, 72 or 92 gal. (2 wing tanks, 19 gal. each at +29), plus [item 112 (20 gal. at +72) or item 113 (2-17 gal. each at +29)] or [items 112 and 113 (92 gal.)]. See NOTE 1 for data on unusable fuel. Oil capacity 12 qt. total (-42), 9 1/4 qt. usable. See NOTE 1 for data on undrainable oil. Control surface movements Elevator trim tab Up 7° Down 34.5° (within -1°) Elevator Up 2 2° Down 15° Aileron Up 20° Down 20° Rudder Left 22° Right 22° Flaps Down 46° Serial Nos. eligible 32-1 thru 32-14 Required equipment Items 12, 101(e), 107(e), 107 (g), 108(c),112 or 113, 111(b), 114, 201(e), 202(d), 205(b) and (j), 302(g), 304(a), 401(h) and 403. Specifications Pertinent to All Models Datum Leading edge of Rib No. 1 (23.5 in. outboard of airplane center line). For reference: (1) Datum is 10.75 in. forward of fuselage station 2; (2) Forward face of firewall is 17.05 in. forward of datum, when aircraft is leveled. Leveling means Lugs at fuselage stations 2 and 3 in cabin on right side (wing spar station). Certification basis Model 14-19: Part 03 of the Civil Air Regulations dated December 15, 1946 Model 14-19-2: Part 03 of the Civil Air Regulations dated December 15, 1946 as amended by 03-1 through 03-4 Model 14-19-3: Part 03 of the Civil Air Regulations dated December 15, 1946 as amended by 03-1 thru 03-4; plus amendment 3-4 (paragraphs 3.80, 3.84A, 3.85a, 3.87, 3.112(c), 3.120 and 3.124(a) only) and amendment 3-6 to CAR 3 dated November 1, 1949 Model 14-19-3A: Same as Model 14-19-3 plus amendments 3-7 and 3-13 (paragraph 3.74 only) to CAR 3 dated November 1, 1949 and amendment 3-2 (paragraph 3.75(c) only) to CAR 3 dated May 15, 1956 Model 17-30: Same as Model 14-19-3A Model 17-31: Same as Model 14-19-3A Model 17-31TC: Same as Model 17-31 plus amendment 3-5 paragraph 3.638(a) only) to CAR 3 dated May 15, 1956 Type Certificate No. 1A3 issued September 26, 1949 Production basis None. Prior to original certification of each aircraft an FAA representative must perform a detailed inspection for workmanship, materials and conformity with the approved technical data, and a check of the flight characteristics. Equipment: A plus (+) or minus (-) sign preceding the weight of an optional item indicates the net weight change when that item is installed. Page 9 of 19 1A3 Propellers and Propeller Accessories 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 1. (a) Propeller - Koppers Aeromatic, hub x model 220-1, blade model 0-74A, Parts list Assembly 4329-1. In- stalled in accordance with Koppers Co. Adjustment Instructions and Operating Limitations No. 31 Pitch settings at 30 in. sta. Low 12.5° Static r.p.m. at maximum permissible throttle setting not over 2500, not under 2450. No additional tolerance permitted. 51 lb. (-58) (b) Koppers Aeromatic Altitude x Control Assembly 4349-L 11 lb. (-50) 2. Propeller - Hartzell controllable (a) Hub model HC-12x20-8, blade model x 8428-6 Pitch settings at 30 in. sta. Low 9.2°, high 21.8° Diameter not over 78 in., not under 75 in. 68 lb. (-58) (b) Hub model HC-12x20-8C, blade model x 8433-6 Pitch settings at 30 in. sta. Low 11°, high 22° Diameter not over 78 in., not under 76.5 in. 61 lb. (-58) (c) Hartzell propeller control x 1 lb. (-6) 3. Propeller - Hartzell Constant Speed (a) Hub model HC-82XF-1, blade model x 8433-6 Pitch settings at 30 in. sta. Low 12-1/2°, high 25-1/2° Diameter not over 78.5 in., not under 78 in. 62 lb. (-58) (b) Governor, Woodward D210105 or x D210340 4 lb. (-49) (c) Spinner, Hartzell 835-3 x 3 lb. (-58) 4. Propeller - McCauley Constant Speed (a) Hub model 2A36C18,, blade model x 90M-12 Pitch settings at 36 in. sta. Low 10°, high 23° Diameter not over 78 in., not under 76 in. 62 lb. (-58) Supplement to Item 401(b) dated x July 11, 1957 required 1A3 Page 10 of 19 Propellers and Propeller Accessories (contd.) 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 (b) Governor, Woodward D210105 or x D210345 4 lb. (-49) (c) Spinner and dome kit, McCauley x AK8053-21 4 lb. (-58) 5. Propeller - McCauley (a) Hub model B2A36C31, blade model x 90M-8 Pitch settings at 36 in. sta. Low 11°, high 27.3° Diameter not over 82 in., not under 80 in. 60 lb. (-57.5) (b) Governor, Woodward D210105 or x D210345 4 lb. (-49.5) (c) McCauley spinner installation x 3 lb. (-57.5) (1) Kit AK8053-21 (McCauley B-2792) adapter ring or 0752004-5 bulk- head required with hub models in items 5(d) and 5(e) (2) D-2771 spinner installation (eligible with hub models in items 5(d) and 5(e) only) (d) Hub model D2A36C31, blade model x 90M-8 Pitch settings at 36 in. sta. Low 11°, high 26.3° Diameter not over 82 in., not under 80 in. 60 lb. (-57.5) Revision to item 401(d) dated May 10, 1960, required (e) Hub model D2A36C33, blade model x 90M-8 Pitch settings at 36 in. sta. Low 10.8°, high 25.8° Diameter not over 82 in., not under 80 in. 60 lb. (-57.5) Revision to item 401(d) dated May 10, 1960, required 6. Propeller - Hartzell Constant Speed (a) Hub model HC-A2XF-1, blade model x 8433-2 or -4 P itch settings at 30 in. sta. Low 14°, high 27° Diameter not over 82 in., not under 80 in. 63 lb. (-57) Revision to item 401(d) dated November 24, 1959 required (b) Governor, Woodward D210105 or x D210340 4 lb. (-49) Page 11 of 19 1A3 Propellers and Propeller Accessories (cont'd.) 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 (c) Spinner, Hartzell 835-13 x 4 lb. (-58) 7. Propeller - Hartzell Constant Speed (a) Hub model HC-C2YF-1A, blade model x x 8468-4 Pitch settings at 30 in. sta. Low 13.4°, high 31° Diameter not over 80 in., not under 80 in. 51 lb. (-57) (b) Governor, Woodward H210452G x x 3 lb. (-49) (c) Spinner and dome - Hartzell 835-23 x x 5 lb. (-58) 8. Propeller - McCauley Constant Speed (a) Hub model D3A32C90, blade model x x 82NC-4 Pitch settings at 30 in. sta. Low 11.7+.2°°, high 28.1°+.5° Diameter not over 78 in., not under 76 in. 64 lb. (-63.5) (b) Governor, Woodward Model P210452G x x 3 lb. (-55) (c) Spinner and dome - McCauley x x model D3669 or D3867 5 lb. (-64) 9. Propeller - McCauley Constant Speed (a) Hub model D2A34C58, blade model x 90AT-10 Pitch settings at 36 in. sta. Low 8.2+0.1°°, high 27.3°+.5° Diameter not over 80 in., not under 78 in. 53 lb. (-63.5) Revision 1 to item 401(f) dated May 18, 1967 required (b) Governor, Woodward Model P210452G x 3 lb. (-55) (c) Spinner and dome-McCauley x Model D2771 or D3766 4.5 lb. (-64) 10. Propeller - Hartzell Constant Speed (a) Hub model HC-C3YF-1, blade model x 8468-8R Pitch settings at 30 in. sta. Low 10.0°, high 32.5° Diameter not over 78 in., not under 76 in. 76 lb. (-63.5) Revision 7 to item 401(f) dated August 10, 1968 required (b) Governor, Woodward P210452 x 3 lb. (-55) (c) Spinner and dome - Hartzell x model C3535 4 lb. (-64) 1A3 Page 12 of 19 Propellers and Propeller Accessories (cont'd.) 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 11. Propeller - Hartzell Constant Speed (a) Hub model HC-C2YF-1, blade model x 8475-6 Pitch settings at 30 in. sta. L ow 11.1°, high 36.2° Diameter not over 78 in., not under 76 in. 53 lb. (-63.5) Revision to item 401(f) dated August 10, 1968 required (b) Governor, Woodward Model P210452 x 3 lb. (-55) (c) Spinner and dome - Hartzell x model C3533 4 lb. (-64) 12. Propeller - Hartzell Constant Speed (a) Hub model HC-C3YR-1, blade model x x 4 68-6R Pitch settings at 30 in. sta. Low 13°, high 38° Diameter not over 80 in., not under 78 in. 75 lb. (-64) (b) Governor, Woodward Model B210460 x x 3 lb. (-55) (c) Spinner and dome - Hartzell x x model C3552 4.5 lb. (-64) Engine and Engine Accessories - Fuel and Oil Systems 101. (a) Starter, Delco-Remy model 1109652 x 18 lb. (-21) (b) Starter, Delco-Remy model 1109678 x x x 18 lb. (-21) (c) Starter, Delco-Remy model 1109684 x x 18 lb. (-21) (d) Starter, Delco-Remy model 1108249 or 1109926 18 lb. (-21) x 18 lb. (-27) x (e) Starter-Prestolite model MZ4206 x x 18 lb. (-51.5) (f) Starter-Prestolite model MCL6501, x CMC P/N 634592 18 lb. (-27) 102. Fuel pump, AC Type AH No. 1539722 x 3 lb. (-20) 103. Oil Cooler, Heat Exchangers, Inc. x No. 102C 7 lb. (-45) 104. Auxiliary fuel tank 25 gal. Eligible x only when installed in accordance with Bellanca dwg. 18046 and 18175 12 lb. (+77) See NOTE 2(c) for placard required Page 13 of 19 1A3 Engines and Engine Accessories-Fuel (cont'd.) 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 and Oil Systems 105. Auxiliary fuel tank 14 gal. Eligible x x only when installed in accordance with Bellanca dwg. 18183 and 18184 8 lb. (+70) See NOTE 2(d) for placard required 106. Auxiliary fuel tanks, 32.5 gal.: One 14 gal. tank x 8 lb. (+70) One 18.5 gal. tank x 9 lb. (+77) eligible only when installed in accordance with Bellanca dwg. 18207 and 18199 and Airplane Flight Manual is revised to include pages 4 and 4(a) dated July 3, 1951 See NOTE 2(e) for placard required 107. Fuel pumps (a) Engine-driven, Lear ROMEC x RD-7420-A1 3 lb. (-20) (b) Hand emergency, AN-4009-D2 x 3 lb. (+ 2) (c) Electric Auxiliary fuel pump, x x x Weldon 4020A2A 4 lb. (+6.5) (d) Electric auxiliary fuel pump, x Bendix 480531 2 lb. (+18) (e) Engine driven fuel pump, Titan x x 4101B68, Type G6 2.5 lb. (+23.5) (f) Electric auxiliary fuel pump, x Lear ROMEC P2688-D 4 lb. (+18) (g) Electric auxiliary fuel pump, x x x Airborne Mfg. Co. 286-9 4 lb. (+18) (h) Engine-drive, Lear ROMEC x x RG17980D 2.5 lb. (-23.5) 108. (a) Oil radiator, Continental x x x Motors P/N 8520912 5 lb. (-49) (b ) Oil radiator, GMC Model x AP13AV10-02 5 lb. (-55) (c) Oil radiator, Harrison Radiator x x Div. GMC, Model AP13AV06-01, P/N 8534108 5 lb. (-20.5) 109. Vacuum pump, Pesco B-11 x x x 4 lb. (-20) 110. Hydraulic pumps (a) New York Air Brake model 67B025 x x x 2 lb. (-20) (b) Pesco No. 1P-677 x x x 2 lb. (-20) 1A3 Page 14 of 19 Engines and Engine Accessories-Fuel (cont'd.) 14-19 14-19-2 14-19-3 14-19-3A 17-30 17-31TC 17-31 and Oil Systems (c) E astern Industries model 102-129 or 1235HBG 2 lb. (-20) x x x x 2 lb. (-26) x 111. (a) Dry vacuum pump, Airborne Mechanisms, Model 10-113-A2, 113A5 or 200 CW 4 lb. (-20) x x x 4 lb. (-26) x (b) Dry vacuum pump, Airborne Mechanisms Model 200 CCW 4 lb. (-26) x x 112. Auxiliary fuel tank 20 gal. Installed x x x x x in accordance with Bellanca dwg. 19643 11 lb. (+72) See NOTE 2(f) for placard required For the 14-19-2 only Flight Manual Supplement dated February 27, 1970 is required Revision to item 401(f) dated April 10, x 1968 required 113. Outboard wing auxiliary fuel tanks: x x x x (17 gal. each) Installed in accordance with Bellanca dwg. 192500 39 lb. (+29) See NOTE 2(g) for placard required Revision to Item 401(e) dated x April 10, 1968 required Revision to Item 401(f) dated x May 18, 1967 required