TCDS 3A15

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 100 81 90 78 60 88 88 90 67 78 83 83 72 90 90 90 90 93 Page No. 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 Rev. No. 93 83 77 93 94 99 99 99 99 86 90 93 100 100 90 90 90 90 Page No. 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 Rev. No. 93 99 94 93 99 90 90 90 90 90 83 83 86 86 90 91 96 98 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A15 Revision 100 Textron Aviation 35-33 J35 35-A33 K35 35-B33 M35 35-C33 N35 35-C33A P35 E33 S35 E33A V35 E33C V35A F33 V35B F33A 36 F33C A36 G33 A36TC H35 B36TC G36 December 16, 2025 TYPE CERTIFICATE DATA SHEET NO. 3A15 Manufacturer: 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 H35, Bonanza, 4 PCLM (Utility Category), approved December 1, 1956 Engine Continental O-470-G See Item 108 for optional engine. *Fuel 91/96 minimum grade aviation gasoline *Engine Limits For all operations 2600 rpm (240 hp) 3A15 2 Rev. 100 I. Model H35 (cont’d) *Airspeed Limits (TIAS) Maneuvering 142 mph (123 knots) Maximum structural cruising 175 mph (152 knots) Never exceed 210 mph (182 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 140 mph (122 knots) *C.G. Range (landing gear (+ 82.1) to (+84.7) at 2900 lbs. extended) (+77.6) to (+85.7) at 2525 lbs. (+77.0) to (+85.7) at 2475 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 2900 lbs. No. of Seats 4 (2 at +85, 2 at +118) Maximum Baggage 270 lbs. (+140). For weight and balance information, see Flight Manual. With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lbs. (+135) On and forward of spar cover 200 lbs. (+108) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 20 ea. 17 ea. +75 Optional fuel system (Item 106) Wing aux. system 20 19 +94 See NOTE 1 for data on unusable fuel. Oil Capacity 9 qt. (+26) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Elevator tab Up 4.5  Down 23  "V" tail elevator action Up 22.5  Down 17.5  "V" tail rudder action Up 21  Down 21  "V" tail max. combination Up 35  Down 30  rudder elevator action Serial Nos. Eligible D-4866 thru D-5330 (except D-5062) Required Equipment Items 1(a) and (b) or (c) or 2(a) and (b) or 8(a) and (b) and (c) or 10(a) and (b) and (d) or 11(a) and (b) or 1(c) or 8(b) and 11(c), 101(a) and (b) or (c), 102(a) or (b), 103, 201(a) or (b) or (g), 202(a) or (b), 205(a) or (b) or (d) or (e), 206(a) or (b), 301(a) or (b) or (c) or (g), 302(a) or (d), 304(a) or (b) or (e), 403(am), 601(a), 622. Rev. 100 3 3A15 II. Model J35, Bonanza, 4 PCLM (Utilit y Category), approved November 13, 1957 Engine Continental IO-470-C *Fuel 91/96 minimum grade aviation gasoline *Engine Limits For all operations 2600 rpm (250 hp) *Airspeed Limits Maneuvering 142 mph (123 knots) (TIAS) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 140 mph (122 knots) *C.G. Range (landing (+82.1) to (+84.7) at 2900 lbs. gear extended) (+77.6) to (+85.7) at 2525 lbs. (+77.0) to (+85.7) at 2475 lbs. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight 2900 lbs. No. of Seats (2 at +85) (2 at +118) Maximum Baggage 270 lb. (+140). For weight a nd balance information, see Flight Manual. With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lb. (+135) On and forward of spar cover 200 lb. (+108) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R Main 20 ea. 17 ea. +75 Optional fuel system (Item 106) Wing Aux. System 20 19 +94 See NOTE 1 for data on unusable fuel. Oil Capacity 9 qt. (+26) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Elevator tab Up 4.5  Down 23  "V" tail elevator action Up 22.5  Down 17.5  "V" tail rudder action Up 21  Down 21  "V" tail max. combination Up 35  Down 30  rudder elevator action Serial Nos. Eligible D-5062, D-5331 thru D-5725 Required Equipment Items 3(a) and (b) or 4(a) and (b) or 9(a) and (b) and (c) or 11(a) and (c) and 3(b), 101(d) and (e) or (g), 102(a) or (b), 103, 201(a) or (b) or (g), 202(a) or (b), 205(a) or (b) or (d) or (e), 206(a) or (b), 301(b) or (c) or (g), 302(a) or (d), 304(a) or (b) or (e), 403(an), 601(a), 622. 3A15 4 Rev. 100 III. Model K35 Bonanza, 4 or 5 PCLM (Uti lity Category), approved October 29, 1958 Model M35 Bonanza, 4 or 5 PCLM (Ut ility Category), approved October 2, 1959 Engine Continental IO-470-C *Fuel 91/96 minimum grade aviation gasoline *Engine Limits For all operations 2600 rpm (250 hp) *Airspeed Limits Maneuvering 142 mph (123 knots) (TIAS) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 140 mph (122 knots) *C.G. Range (landing (+82.1) to (+84.7) at 2950 lbs. gear extended) (+77.5) to (+85.7) at 2525 lbs. (+77.0) to (+85.7) at 2475 lbs. Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 2950 lbs. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +119, 1 at +140) when Item 604 installed. Maximum Baggage 270 lbs. (+140). For weight and balance information, see Flight Manual. With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lbs. (+135) On and forward of spar cover 200 lbs. (+108) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R Main 25 ea. 22 ea. +75 Optional fuel system (Item 106) Wing Aux. System 20 19 +94 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (+26) See NOTE 1 for data on system fuel. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Elevator tab Up 4.5  Down 23  "V" tail elevator action Up 22.5  Down 19  "V" tail rudder action L.H. Up 23  Down 26  R.H. Up 26  Down 23  "V" tail max. combination rudder elevator action L.H. Up 44  Down 37  R.H. Up 42  Down 40  Serial Nos. Eligible M odel K35: D-5726 thru D-6161 Model M35: D-6162 thru D-6561 Required Equipment Items 3(a) and (b) or 4(a) and (b) or 9(a) and (b) and (c) or 11(a) and (c) and 3(b) or 4(b) or 9(b), 101(d) and (e) or (g), 102(a) or (b), 103, 201(a) or (b) or (g), 202(a) or (b), 205(a) or (b) or (d) or (e), 206(a) or (b), 301(b) or (c) or (g), 302(a) or (b) or (d), 304(a) or (b) or (e), 403(ak), 601(a), 622. Rev. 100 5 3A15 IV. Model 35-33, Debonair, 4 PCLM (Utili ty Category), approved November 13, 1959 Engine Continental IO-470-J (see Item 112 for optional engine). *Fuel 80/87 minimum grade aviation gasoline *Engine Limits For all operations 2600 rpm (225 hp) *Airspeed Limits (TIAS) Maneuvering 142 mph (123 knots) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 140 mph (122 knots) *C.G. Range (landing gear (+ 82.1) to (+85.7) at 2900 lbs. extended (+78.0) to (+86.6) at 2550 lbs. (+78.0) to (+86.7) at 2525 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 2900 lbs. No. of Seats 4 (2 at +85, 2 at +118) Maximum Baggage 270 lbs. (+140) For weight and balance info rmation, see Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 25 ea. 22 ea. +75 Optional fuel system (Item 106) Wing. aux system 20 19 +94 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (+26) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 25  Right 25  Elevator tab Up 10  Down 21  Elevator Up 25  Down 15  Serial Nos. Eligible CD-1 thru CD-224 CD-233, CD-234, CD-236, CD-241 CD-246 thru CD-250 Required Equipment Items 5(a) and (b) or (c) and (d) or 7( a) and (b) or (d) and (c) or 10(a) and (b) or (c) and (d) or 11(a) and (b) and (c), 101(d) or (k) and (e) or (h), 102(a) or (b), 103, 201(a) or (b) or (c) or (d) or (g), 202(a) or (b) or (c), 205(b) or (c) or (d) or (e), 206(a) or (b), 301(c) or (d) or (g), 302(a), 304(b) or (c) or (e), 403(j) or (o), 403(ac) (when two 22 gal. main fuel cells are installed per Item 616), 601(a). 3A15 6 Rev. 100 V. Model N35, Bonanza, 4 or 5 PCLM (Ut ility Category), approved November 3, 1960 Engine Continental IO-470-N *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine limits For all operations 2625 rpm (260 hp) *Airspeed limits Maneuvering 147 mph (128 knots) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 140 mph (122 knots) *C.G. Range (landing (+82.1) to (+85.7) at 3125 lbs. gear extended) (+77.0) to (+85.7) at 2800 lbs. or less Straight line variation between points given Empty Weight C.G. Range None *Maximum Weight 3125 lbs. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +140) when Item 605 installed Maximum Baggage 270 lbs. (+140) For weight and balance information, see Flight Manual. With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lbs. (+135) On and forward of spar cover 200 lbs. (+108) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 25 ea. 22 ea. +75 Optional fuel system (Item 111) L&R main 39 37 +75 See Note 1 for data on unusable fuel. Oil Capacity 10 qt. (+26) See Note 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Elevator tab Up 5.5  Down 23  "V" tail elevator action Up 22.5  Down 19  "V" tail rudder action L.H. Up 23  R.H. Down 26  R.H. Up 26  L.H. Down 23  "V" tail max. combination rudder elevator action L.H. Up 44  Down 37  R.H. Up 42  Down 40  Serial Nos. Eligible D-6562 thru D-6841 Required Equipment Items 6(a) and (b) or 9(a) and (b) a nd (c) or 11(a) and (b) and (c), 101(d) and (e) or (g), 102(a) or (b), 103, 201(a) or (b) or (g), 202(a) or (b), 205(a) or (b) or (d) or (e), 206(a) or (b), 301(b) or (c) or (g), 302(a) or (b) or (c), 304(a) or (b) or (e), 403(ao), 601(a), 622. Rev. 100 7 3A15 VI. Model 35-A33, 4 PCLM (Utility Category, approved November 3, 1960 Engine Continental IO-470-J (s ee Item 112 for optional engine) *Fuel 80/87 minimum grade aviation gasoline *Engine limits For all operations 2600 rpm (225 knots) *Airspeed limits Maneuvering 147 mph (128 knots) (TIAS) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 140 mph (122 knots) *C.G. Range (landing (+82.1) to (+86.7) at 3000 lbs. gear extended) (+77.0) to (+86.7) at 2500 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 3000 lbs. No. of Seats 4 (2 at +85, 2 at +118) Maximum Baggage 270 lbs. (+140) For weight and balance info rmation, see Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 25 ea. 22 ea. +75 Optional fuel system (Item 106) Wing aux. sys. 20 19 +94 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (+26) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 25  Right 25  Elevator tab Up 10  Down 21  Elevator Up 25  Down 15  Serial Nos. Eligible CD-225 thru CD-232 CD-235 CD-237 thru CD-240 CD-242 thru CD-245 CD-251 thru CD-387 Required Equipment Items 5(a) and (b) or (c) and (d) or 7( a) and (b) or (d) and (c) or 10(a) and (b) or (c) and (d) or 11(a) and (b) and (c), 101(d) or (k) and (e) or (h), 102(b), 103, 201(a) or (b) or (c) or (d) or (g), 202(a) or (b) or (c), 205(b) or (c) or (d) or (e), 206(a) or (b), 301(c) or (d) or (g), 302(a) or (b) or (c), 304(b) or (c) or (e), 403(k), 403(ac) (when 22 gal. main fuel cells are installed per Item 616), 601(a). 3A15 8 Rev. 100 VII. Model 35-B33, 4 PCLM (Utility Category), approved October 3, 1961 Engine Continental IO-470-K *Fuel 80/87 minimum grade aviation gasoline *Engine limits For all operations 2600 rpm (225 hp) *Airspeed limits (TIAS) Maneuvering 147 mph (128 knots) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 165 mph (143 knots) *C.G. Range (landing (+82.1) to (+86.7) at 3000 lbs. gear extended) (+77.0) to (+86.7) at 2500 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 3000 lbs. No. of Seats 4 (2 at +85, 2 at +118) Maximum Baggage 270 lbs. (+140) For weight and balance info rmation, see Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 22 ea. 22 ea. +75 Optional fuel system (Item 111) L&R main 39 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (+26) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 25  Right 25  Elevator tab Up 10  Down 21  Elevator Up 25  Down 15  Serial Nos. Eligible CD-388 thru CD-813 Required Equipment Items 5(a) and (b) or (c) and (d) or 7( a) and (b) or (d) and (c) or 10(a) and (b) or (c) and (d) or 11(a) and (b) and (c), 101(d) or (k) and (e) or (f) or (h), 102(b), 103, 201(a) or (b) or (c) or (d) or (e) or (f) or (g) or (h), 202(a) or (b) or (c) or (d) or (e) or (f), 205(b) or (c) or (d) or (e), 206(a) or (b), 301(c) or (d) or (g), 302(c), 304(b) or (c) or (e), 403(m), 403(ac) (when two 22 or 37 gal. main fuel cells are installed per Item 606), 601(a). Rev. 100 9 3A15 VIII. Model P35, 4 or 5 PCLM (Utility Category), approved October 20,1961 Engine Continental IO-470-N *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine limits For all operations 2625 rpm (260 hp) *Airspeed limits Maneuvering 148 mph (129 knots) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) Landing gear extended (normal) 165 mph (143 knots) *C.G. Range (landing (+82.1) to (+85.7) at 3125 lbs. gear extended) (+77.0) to (+85.7) at 2800 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 3125 lbs. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +140) when Item 605 installed. Maximum Baggage 270 lbs. (+140) For weight and balance information, see Flight Manual. With rear seats removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lbs. (+135) On and forward of spar cover 200 lbs. (+108) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 22 ea. 22 ea. +75 Optional fuel system (Item 111) L&R main 39 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (+26) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Elevator tab Up 5.5  Down 23  "V" tail elevator action Up 22.5  Down 19  "V" tail rudder action L.H. Up 23  Down 26  R.H. Up 26  Down 23  "V" tail max. combination rudder elevator action L.H. Up 44  Down 37  R.H. Up 42  Down 40  Serial Nos. Eligible D-6842 thru D-7309, except D-7140 Required Equipment Items 6(a) and (b) or 9(a) and (b) a nd (c) or 11(a) and (b) and (c), 101(d) and (e) or (f) or (g), 102(a) or (b), 103, 201(a) or (b) or (e) or (f) or (g) or (h), 202(a) or (b) or (d) or (f), 205(a) or (b) or (d) or (e), 206(a) or (b), 301(b) or (c) or (g), 302(c), 304(a) or (b) or (e), 403(ao), 601(a), 622. 3A15 10 Rev. 100 IX. Model S35, Bonanza, 4 or 5 or 6 PCLM (Utility Category), approved January 3, 1964 Engine Continental IO-520-B or IO-520-BA (see Item 114 or 120 for optional engine) *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine Limits For all operations 2700 rpm (285 hp) *Airspeed Limits (TIAS) Maneuvering 152 mph (132 knots) Maximum structural cruising 190 mph (165 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 130 mph (113 knots) Landing gear extended (normal) 165 mph (143 knots) *C.G. Range (landing (+82. 1) to (+84.7) at 3300 lbs. gear extended) (+79.0) to (+85.7) at 3000 lbs. (+77.0) to (+85.7) at 2800 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 3300 lbs. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +150) (when Item 607(a) installed) or 6 (2 at +85, 2 at +121, 2 at +150) (when Item 607(b) installed) Maximum Baggage 270 lbs. (+150) For weight and balance information, see Flight Manual. With rear seats removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lbs. (+145) On and forward of spar cover 200 lbs. (+108) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 25 ea. 22 ea. +75 Optional fuel system (Item 113) L&R main 40 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. (+25) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Elevator tab Up 5.5  Down 23  "V" tail elevator action Up 22.5  Down 19  "V" tail rudder action L.H. Up 23  R.H. Down 26  R.H. Up 26  L.H. Down 23  "V" tail max. combination rudder elevator action L.H. Up 44  Down 37  R.H. Up 35  Down 40  Serial Nos. Eligible D-7140 D-7310 thru D-7976 Required Equipment Items 11(a) and (d) and (e) or 12(a) and (b) and 11(e) or 14(a) and (c) and 11(e), 101(i) and (j), 102(c) or (d), 103, 201(b) or (e) or (f) or (g) or (h), 202(a) or (b) or (d) or (f), 205(b), or (d) or (e), 206(a) or (b), 301(e) or (f), 302(c), 304(d), 403(al), 601(a), 622. Rev. 100 11 3A15 X. Model 35-C33, Debonair, 4 or 5 PCLM (Utility Category), approved December 2, 1964 Model E33, Bonanza, 4 or 5 PCLM (Utility Category), approved October 10, 1967 Model F33, Bonanza, 4 or 5 PCLM (Uti lity Category), approved October 24, 1969 Engine Continental IO-470-K *Fuel 80/87 minimum grade aviation gasoline *Engine Limits For all operations 2600 rpm (225 hp) *Airspeed Limits Maneuvering 147 rpm (128 knots) Maximum structural cruising 185 mph (161 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 120 mph (104 knots) (with Item 403(s) thru 130 mph (113 knots) CD-1118 and CD-1119 thru CD-1199) CD-1200 and On 140 mph (122 knots) Landing gear extended (normal) 165 mph (143 knots) CD-1200 and On 175 mph (152 knots) *C.G. Range (landing (+81.5) to (+86.7) at 3050 lbs. gear extended) (+77.0) to (+86.7) at 2700 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 3050 lbs. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +142) Maximum Baggage 270 lbs. (+140) (for weight and balance information, see Flight Manual) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R main 25 ea. 22 ea. +75 Optional fuel system (Item 113) L&R main 40 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (+26) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 25  Right 25  Elevator tab Up 10  Down 21  Elevator Up 25  Down 15  Serial Nos. Eligible Model 35-C 55: CD-814 thru CD-1118 (except CD-982) Model E33: CD-1119 thru CD-1234 Model F33: CD-1235 thru CD-1254 3A15 12 Rev. 100 X. Model 35-C33, Model E33, Model F33 (cont'd) Required Equipment Model 35-C33: (see Item 611 for Items 5(a) and (b) or (c) and (d) or 7(a) and (b) or (d) and (c) or 10(a) and (b) or (c) and replacements and (d) or 11(a) and (b) and (c) or 13(a) and (b) and (c) or 14(a) and (b) and 11(b), 101(d) or additions with (k) and (e) or (f) or (h), 102(b), 103, 201(a) or (b) or (c) or (d) or (e) or (f) or (g) or (h) operational 24v. or (j), 202(a) or (b) or (c) or (d) or (e) or (f), 205(b) or (c) or (e), 206(a) or (b), 301(c) or system) (d) or (g) or (h), 302(c), 304(b) or (c) or (e), 403(q) or (s), 403(ac) (when two 22 or 37 gal. main fuel cells are in stalled per Item 616), 601(a). Model E33: 11(a) and (b) or (e) or (f) and (c), 101(d) or (k) and (e) or (f) or (h), 102(b), 103, 201(j) or (k), 202(e) or (f), 205(b) or (c) or (e) or (f), 206(a) or (b), 301(d) or (g), 302(c), 304(b) or (c) or (e), 403(u) (S/N CD-1119 thru CD-1199), (v) (S/N CD-1200 thru CD-1234), 403(ac) (when two 22 or 37 gal. main fuel cells are installed per Item 606), 601(a). Model F33: 11(a) and (b) or (f) and (c), 101(d) or (k) and (e) or (f) or (h), 102(b), 103, 201(j) or (k), 202(e) or (f), 205(b) or (c) or (e) or (f), 206(a) or (b), 301(d) or (g), 302(c), 304(b) or (c) or (e), 403(z), 403(ac), 601(a). XI. Model V35, Bonanza, 4 or 5 PCLM (U tility Category), approved October 22, 1965 Model V35A, Bonanza, 4 or 5 or 6 PCLM (Utility Category), approved October 6, 1967 Model V35B, Bonanza, 4 or 5 or 6 PCLM (Utility Category), approved October 24, 1969 Engine Continental IO-520B or IO-520-BA; IO-520-BB (D-10179 and On) (see Item 114, 116, or 120 for optional engine) *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine limits (For all airplanes prio r to D-10313 and airplanes D-10313 and On, equipped with Items 14(a) or 18(a)): For all operations 2700 rpm (285 hp) (For airplanes D-10313 and On, equipped with Item 11(a)): Takeoff and continuous power 2700 rpm (285 hp) Normal operating power 2550 rpm (275 hp) *Airspeed limits CAS CAS IAS Maneuvering 152 mph (132 knots) (134 knots) Maximum structural cruising 190 mph (165 knots) (167 knots) Never exceed 225 mph (195 knots) (197 knots) Flaps extended (15) 175 mph (152 knots) (154 knots) (D-10179 and On) Flaps extended (normal) 130 mph (113 knots) (D-8872 and On) 140 mph (122 knots) (123 knots) Landing gear extended (normal) 165 mph (143 knots) (D-8872 and On) 175 mph (152 knots) (154 knots) *C.G. Range (landing (+82.1) to (+84.4) at 3400 lbs. gear extended) (+78.0) to (+85.7) at 3000 lbs. (+77.0) to (+85.7) at 2900 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 3400 lbs. Rev. 100 13 3A15 XI. Model V35, Mode l V35A, Model V35B (cont'd) No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 607(a) installed. or 6 (2 at +85, 2 at +121, 2 at +150) when Item 607(b) installed. Maximum Baggage 270 lbs. (+150) (for weight and balance information, see Flight Manual) With rear seats removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lbs. (+145) On and forward of spar cover 200 lbs. (+108) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm (Prior to D-10303) L&R main 25 ea. 22 ea. +75 Optional fuel system (Item 113) L&R main 40 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. (D-10303 and On) Standard Fuel System L&R main 40 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 10 qt. (+25) See NOTE 1 for data on system oil. Control Surface Movements Wing Flaps Approach 15  Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Elevator tab Up 5.5  Down 23 