# TCDS 3A15: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 100 - Revised: December 16, 2025 - Product: Aircraft, Small Airplane - Certification basis: Part 23, CAR 3 - Registered aircraft: 8,829, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/1a/71/1a719e365e951197f60ddd48f033c5cc1729d21d46b751a17f9fd02b3fe8f76f - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID190592526520251217192752.0001 - Page: https://openairdocs.org/tcds/3A15 ## Models (27) As the data sheet lists them. - G36 - 35-C33A - 35-A33 - M35 - E33A - E33C - V35B - N35 - K35 - B36TC - 36 - V35 - E33 - A36 - F33A - J35 - 35-C33 - 35-33 - S35 - G33 - A36TC - P35 - F33C - H35 - F33 - 35-B33 - V35A ## 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 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  "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 35  Down 40  Serial Nos. Eligible M odel V35: D-7977 thru D-8598 Model V35A: D-8599 thru D-9068 Model V35B: D-9069 and On Required Equipment D-7977 thru D-10119, except D-10097 (14-volt system) Items 11(a) and (d) and (e) or 12(a) and (b) and (c) 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) or (j) or (k) or (l), 202(a) or (b) or (d) or (e) or (f), 205(b) or (d) or (e) or (f), 206(a) or (b), 301(e) or (f) or (h), 302(c), 304(d) or (f) or (g) or (h), 403(at) (D-7977 thru D-9947), 403(bb) (S/N D-9948 thru D-10119, except D-10097), 601(a), 622. D-10097, D-10120 and On (28-volt system) Items 11(a) and (d) and (e) or (g) or 14(a) and (c) and 11(e) or (g) or 17(a) or (with IO- 520-BB engine only) 18(a) and (b) and 11(e) or (g), 102(c) or (d), 103, 117(a) and (c) prior to D-10179, 117(a) and (d) S/N D-10179 and up; 201(k), 202(f), 205(f), 206(a), 309(a) or (b) or (c) or (d), 310(a), 312(a) or (b), 403(bb), 601(a), 622. 3A15 14 Rev. 100 XII. Model 35-C33A, Debonair, 4 or 5 PCLM (Utility Category), approved January 20, 1966 Model E33A, Bonanza, 4 or 5 PCLM (U tility Category), approved October 10,1967 Model E33C, Bonanza, 4 or 5 PCLM (Uti lity Category), approved September 9, 1968 See NOTE 5 for eligibility in Acrobatic Category. Engine Continental IO-520-B or IO-520- BA (see Item 120 for optional engine) *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine Limits For all operations 2700 rpm (285 hp) *Airspeed Limits Utility Categor y (Models 35-C33A, E33A, E33C) (*CAS) 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) (CE-249 & On and CJ-14 & On) 140 mph (122 knots) Landing gear extended (normal) (Models 35-C33, E33A) 165 mph (143 knots) (Models E33A (CE-249 & On), E33C) 175 mph (152 knots) Acrobatic Category (Model E33C) Maneuvering 165 mph (143 knots) Maximum structural cruising 190 mph (165 knots) Never exceed 234 mph (203 knots) Flaps extended (normal) 130 mph (113 knots) (S/N CJ-14 & On) 140 mph (122 knots) Landing gear extended (normal) 175 mph (152 knots) *C.G. Range (landing Utility Category gear extended) (+82.1) to (+86.7) at 3300 lbs. (+77.0) to (+86.8) at 2800 lbs. Straight line variation between points given. Acrobatic Category (+78.5) to (+81.0) at 2800 lbs. Empty weight C.G. Range None *Maximum Weight Utility Category: 3300 lbs. Acrobatic Category: 2800 lbs. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +142) when Item 607(c) installed See NOTE 2(b). 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 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. Rev. 100 15 3A15 XII. Model 35-C33A, Model E33A, Model E33C (cont'd) Control Surface Movements Wing Flaps Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 25  Right 25  Rudder (E33C in acrobatic category) Left 25  Right 20  Elevator tab Up 10  Down 27  Elevator Up 25  Down 15  Serial Nos. Eligible Mode l 35-C33A: CE-1 thru CE-179 Model E33A: CE-180 thru CE-289 Model E33C: CJ-1 thru CJ-25 Required Equipment Model 35-C33A: Items 11(a) and (d) and (e) or 12(a) and (b) and (c) or 14(a) and (c) and 11(e), 101(i) and (j), 102(c) or (d), 103, 201(a) or (b) or (c) or (d) or (e) or (f) or (g) or (h) or (j) or (k), 202(a) or (b) or (c) or (d) or (e) or (f), 205(b) or (c) or (e), 206(a) or (b), 301(e) or (f), 302(c), 304(d) or (f) or (g) or (h), 601(a). Model E33A: 11(a) and (d) and (e) or 12(a) and (b) and (c) or 14(a) and (c) and 11(e), 101(i) and (j), 102(c) or (d), 103, 201(j) or (k), 202(e) or (f), 205(b) or (c) or (e) or (f), 206(a) or (b), 301(e) or (f) or (h), 304(d) or (f) or (g) or (h), 601(a). Model E33C: 11(a) and (d) and (e), 101(i), (j), and (o), 102(c) or (d), 103, 201(j) or (k), 202(e) or (f), 205(b) or (c) or (e), 206(a) or(b), 301(e) or (f) or (h), 302(c), 304(d) or (f) or (g) or (h), 601(a). XIII. Model 36, Bonanza, 4 to 6 PCLM (U tility Category), approved May 1, 1968 Model A36, Bonanza, 4 to 6 PCLM (Ut ility Category), approved October 24, 1969 (See Item 624 for reduced ex terior noise configuration) Engine E-1 thru E-1370 Continental IO-520-B or IO-520-BA (see Item 120 for optional engine) E-1371 thru E-2110, except E-1946 and E-2104 Continental IO-520-BB E-1946, E-2104, E-2111 thru E-3635, except E-3630 Continental IO-550-B *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine Limits (For airplanes E-1 thru E-1608 and E-1609 thru E-2110 (except E-1946 and E-2104) equipped with Item 14(a) or 18(a)): For all operations 2700 rpm (285 hp) (For airplanes E-1609 thru E-2110 (except E-1946 and E-2104) equipped with Item 11(a)): Takeoff and continuous power 2700 rpm (285 hp) Normal operating power 2550 rpm (275 hp) (For airplanes E-1946, E-2104, E-2111 thru E-3635, except E-3630): For all operations 2700 rpm (300 hp) 3A15 16 Rev. 100 XIII. Model 36, Model A36 (cont'd) *Airspeed Limits E-1 thru E-2110, except E-1946 and E-2104 CAS CAS IAS Maneuvering 160 mph (139 knots) (140 knots) Maximum structural cruising 190 mph (165 knots) (167 knots) Never exceed 234 mph (203 knots) (204 knots) E-1371 thru E-2110, except E-1946 and E-2104 Flaps extended (15) 175 mph (152 knots) (153 knots) Flaps extended (normal) 140 mph (122 knots) (123 knots) Landing gear extended (normal) 175 mph (152 knots) (153 knots) E-1946, E-2104, E-2111 thru E-3635, except E-3630 Maneuvering 160 mph (139 knots) (141 knots) Maximum structural cruising 190 mph (165 knots) (166 knots) Never exceed 234 mph (203 knots) (205 knots) Flaps extended (12) 175 mph (152 knots) (154 knots) Flaps extended (normal) 140 mph (122 knots) (124 knots) Landing gear extended (normal) 175 mph (152 knots) (154 knots) *C.G. Range (landing (+81.0) to (+87.7) at 3600 lbs. E-1 thru E-2110, except E-1946 and E-2104. gear extended) (+81.0) to (+87.7) at 3650 lb s. E-1946, E-2104, E-2111 thru E-3635, except E-3630. (+74.0) to (+87.7) at 3100 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight 3600 lbs. E-1 th ru E-2110, except E-1946 and E-2104. 3650 lbs. E-1946, E-2104, E-2111 thru E-3635, except E-3630. Number of Seats E-1 thru E-1370 4 (2 at +75, 2 at +115) or 5 (2 at +75, 2 at +115, 1 at +148) or 6 (2 at +75, 2 at +115, 2 at +148) E-1371 thru E-3635, except E-3630 4 (2 at +75, 2 at +115) or 5 (2 at +75, 2 at +115, 1 at +152) or 6 (2 at +75, 2 at +115, 2 at +152) Maximum Baggage E-1 thru E-1370 (Structural Limits) 400 lbs. (+150) (see NOTE 2(c)) With rear seats removed for cargo, maximum baggage is as follows: Aft of rear spar (see NOTE 2(c)) 400 lbs. (+145) On and forward of spar cover 200 lbs. (+108) E-1371 thru E-3635, except E-3630 Rear compartment (aft to Sta. 170) 400 lbs. (+145) On and forward of rear spar 200 lbs. (+108) cover with center seats removed Aft of rear spar cover to Sta. 170 400 lbs. (+145) with 3rd, 4th, 5th, 6th, seats removed Aft baggage compartment 70 lbs. (+180) (Sta. 170 to Sta. 190) Rev. 100 17 3A15 XIII. Model 36, Model A36 (cont'd) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm (E-1 thru E-1593) 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. (E-1594 thru E-3635, except E-3630) Standard Fuel System L&R main 40 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. (+15) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (E-1 thru E-1370) Down 30  Wing flaps (E-1371 thru E-2110, except E-1946 and E-2104) Approach 15  Down 30  Wing flaps (E-1946, E-2104, E-2111 thru E-3635, except E-3630) Approach 12  Down 30  Right aileron tab Fixed Left aileron tab (E-1 thru E-2110, except E-1946 and E-2104) Fixed Left aileron tab (E-1946, E-2104, E-2111 thru E-3635, except E-3630) Up 9  Down 9  Aileron Up 20  Down 20  Rudder tab Fixed Rudder (E-1 thru E-2110, except E-1946 and E-2104) Left 25  Right 25  Rudder (E-1946, E-2104, E-2111 thru E-3635, except E-3630) Left 25  Right 23  Elevator tab (E-1 thru E-2110, except E-1946 and E-2104) Up 10  Down 27  Right elevator tab (E-1946, E-2104, E-2111 thru E-3635, Up 10  Down 25  except E-3630 Left elevator tab (E-1946, E-2104, E-2111 and On) Up 8  Down 27  Elevator (S/N E-1 thru E-2110, except E-1946 and E-2104) Up 23  Down 20  Elevator (S/N E-1946, E-2104, E-2111 thru E-3635, except E-3630) Up 25  Down 20  Serial Nos. Eligible Model 36: E-1 thru E-184 Model A36: E-185 thru E-3635, except E-3630 (see NOTE 6) Required Equipment E-1 thru E-1240, except E-1111 (14-volt system) Items 11(a) and (d) and (e) or 14(a) and (c) and 11(e), 101(i) and (j) or (n), 102(c) or (d), 103, 201(j) or (k), 202(f), 205(f), 206(a), 301(f) or (h), 302(c), 304(g) or (h), 410(d) or 403(ag) (A36 S/N E-185 thru E-363, except E-357, E-358, and E-361), 403(ag) (A36 S/N E-357, E-358, E-361 and E-364 thru E-926), 403(aq) or (bc) (A36 S/N E-927 thru E-1240, except E-1111) and 601(a). 3A15 18 Rev. 100 XIII. Model 36, Model A36 (cont'd) Required Equipment (cont'd) E-1111, E-1241 thru E-3635, except E-3630 (28-volt system) Items 11(a) and (d) and (e) or (g) or 14(a) and (c) and 11(e) or (g) or 17(a) or (with IO- 520-BB engine only), 18(a) and (b) and 11(e) or (g) (E-1111, E-1241 thru E-2110 except E-1946 and E-2104), or 20(a) and (b) and 11(e) or (g) or 22 (E-1946, E-2104, E-2111 thru E-3635, except E-3630), 102(c) or (d), 103, 117(a) and (c) (prior to E-1371), 117(a) and (d) (E-1371 thru E-2110 except E-1946 and E-2104), 117(i) and (j) (E-1946, E-2104, E-2111 thru E-2419), 117(k) and (j) (E-2420 thru E-2749), 117(l) and (j) (E-2750 thru E-3635, except E-3630), 201(k), 202(f), 205(f), 206(a), 309(a) or (b) or (c) or (d) (prior to E-2111 except E-1946 and E-2104), 309(e) or (f) (E-1946, E-2104, E-2111 thru E-3635, except E-3630), 310(a), 312(a) or (b), or (c), 403(bc) (prior to E-2111 except E-1946 and E-2104), 403(bj) (E-1946, E-2104, E-2111 thru E-3635, except E-3630), 601(a). XIV. Model F33A, Bonanza, 4 or 5 PCLM (U tility Category), approved October 24, 1969 Model F33C, Bonanza, 4 or 5 PCLM (U tility Category), approved October 24,1969 Model F33C, Bonanza, 2 PCLM (Acrobat ic Category), approved October 24, 1969 Engine Continental IO-520-B or IO-520-BA; IO-520-BB (CE-816 and On, CJ-149 and On) (see Item 120 for optional engine) *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine Limits (For all airplanes prior to CE-891 and CJ-156, and airplanes CE-891 and On and CJ-156 and On, equipped with Item 14(a) or 18(a)) For all operations 2700 rpm (285 hp) (For airplanes CE-891 and On and CJ-156 and On, equipped with Item 11(a)) Takeoff and continuous power 2700 rpm (285 hp) Normal operating power 2550 rpm (275 hp) *Airspeed Limits Utility Category (Models F33A, F33C) 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) (CE-816 and On) (CJ-150 and On) Flaps extended (normal) 140 mph (122 knots) (123 knots) Landing gear extended (normal) 175 mph (152 knots) (154 knots) Acrobatic Category (Model F33C) CAS CAS IAS Maneuvering 165 mph (143 knots) (145 knots) Maximum structural cruising 190 mph (165 knots) (167 knots) Never exceed 234 mph (203 knots) (204 knots) Flaps extended (12) 175 mph (152 knots) (154 knots) (CJ-150 and On) Flaps extended (normal) 140 mph (122 knots) (123 knots) Landing gear extended (normal) 175 mph (152 knots) (154 knots) *C.G. Range (Landing Utility Category: gear extended) (+82.1) to (+86.7) at 3400 lbs. (+77.0) to (+86.7) at 2800 lbs. Straight line variation between points given. Acrobatic Category: (+78.5) to (+81.0) at 2800 lbs. Rev. 100 19 3A15 XIV. Model F33A, Model F33C, Model F33C (cont'd) Empty Weight C.G. Range None *Maximum Weight Utility Category: 3400 lbs. (Models F33A, F33C) Acrobatic Category: 2800 lbs. (Model F33C) Number of Seats CE-290 thru CE-315, CJ-26 and On: 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +142) when Item 607(c) is installed. (see NOTE 2(b)) CE-316 and On: 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +154) when Item 607(c) is installed. or 6 (2 at +85, 2 at +121, 2 at +154) when Item 607(b) is installed. Maximum Baggage 270 lbs. (+140) 270 lbs. (+150) (CE-316 and On) See weight and balance data. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm (Prior to CE-884 and CJ-156) 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. (CE-884 and On and CJ-156 and On) Standard Fuel System 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 Approach 15  Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 25  Right 25  Rudder (F33C in acrobatic category) Left 25  Right 20  Elevator tab Up 10  Down 27  Elevator Up 25  Down 15  Serial Nos. Eligible Model F33A: CE-290 and On Model F33C: CJ-26 and On Required Equipment Model F33A (CE-290 thru CE-771, except CE-748 (14-volt system)): Items 11(a) and (d) and (e) or 12(a) and (b) and (c) or 14(a) and (c) and 11(e), 101(i) and (j), 102(c) or (d), 103, 201(j) or (k), 202(e) or (f), 205(b) or (c) or (e) or (f), 206(a) or (b), 301(h), 302(c), 304(f) or (g) or (h), 410(c), 403(az) (S/N CE-290 thru CE-400, except CE-394 and CE-395), 403(az) (S/N CE-394, CE-395, CE-401 and CE-673), 403(ar) or (az) (S/N CE-674 thru CE-771 except CE-748), and 601(a). 3A15 20 Rev. 100 XIV. Model F33A, Model F33C, Model F33C (cont'd) Required Equipment Model F33A (CE- 748, CE-772 and On (28-volt system)): Items 11(a) and (d), and (e) or (g) or 14(a) and (c) and 11(e) or (g) or 17(a) or (with IO-520-BB engine only) 18(a) and (b) and 11(e) or (g), 102(c) or (d), 103, 117(a) and (c) (prior to CE-816), 117(a) and (d) (S/N CE-816 and On), 201(k), 202(f), 205(f), 206(a), 309(a) or (b) or (c) or (d), 310(a), 312(a) or (b), 403(ar), and 601(a). Model F33C (CJ-26 thru CJ-148 (14-volt system)): Items 11(a) and (d) and (e) or 14(a) and (c) and 11(e), 101(i), (j), and (o), 102(c) or (d), 103, 201(j) or (k), 202(e) or (f), 205(b) or (c) or (e) or (f), 206(a) or (b), 301(h), 302(c), 304(h). Utility Category: 410(c) and 403(ar) or (az) (CJ-26 thru CJ-30), 403(ar) or (az) (CJ-31 thru CJ-128), 403(ar) (CJ-129 thru CJ-148), and 601(a). Acrobatic Category: 410(c) and 403(ar) and (ba) or (az) and (ba) (CJ-26 thru CJ-30), 403(ar) and (ba) or (az) and (ba) (CJ-31 thru CJ-128), 403(ar) and (as) (CJ-129 thru CJ-148) and 601(a). Model F33C (CJ-149 and On (28-volt system)): Items 11(a) and (d) and (e) or (g) or 14(a) and (c) and 11(e) or (g), 102(c) or (d), 103, 117(a) and (b) and (d), 201(k), 202(f), 205(f), 206(a), 309(a) or (b) or (c) or (d), 310(a), 312(a) or (b). Utility Category: 403(ar) and 601(a). Acrobatic Category: 403(ar) and (as) and 601(a). XV. Model G33, Bonanza, 4 or 5 PCLM (Utility Category), approved March 17, 1971 Engine Continental IO-470-N Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations 2625 rpm (260 hp) Airspeed limits Maneuvering 152 mph (132 knots) (TIAS) Maximum structural cruising 190 mph (165 knots) Never exceed 225 mph (195 knots) Flaps extended (normal) 140 mph (122 knots) Landing gear extended (normal) 175 mph (152 knots) C.G. Range (landing (+81.3) to (+86.7) at 3300 lbs. gear extended) (+77.0) to (+86.7) at 2800 lbs. Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight 3300 lbs. Number of Seats 4 (2 at +85, 2 at +117) or 5 (2 at +85, 2 at +117), 1 at +144) Maximum Baggage 270 lbs. (+140) See weight and balance data. 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. Rev. 100 21 3A15 XV. Model G33 (cont'd) 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 27  Elevator Up 25  Down 15  Serial No. Eligible CD-1255 thru CD-1304 Required Equipment Items 11(a) or (b) or (c), 101(d) and (j), 102(b), 103, 201(j) or (k), 202(e) or (f), 205(e) or (f), 206(a), 301(g), 302(c), 304(e), 403(ab) and (ac) or (ad), and 601(a). XVI. Model A36TC, Bonanza, 4 to 6 PCLM (U tility Category), approved December 7, 1978 Engine Continental TSIO-520-U or TSIO-520-UB *Fuel Aviation gasoline Grade 100LL or 100 minimum *Engine Limits Takeoff and maximum continuous power: 2700 rpm (36 in. Hg. MAP) (300 hp) *Airspeed Limits Maneuvering 139 knots (160 mph) (IAS) Maximum structural cruising 165 knots (190 mph) (Decrease 3 knots per 1,000 feet above 16,000 feet) Never exceed 203 knots (234 mph) (Decrease 4 knots per 1,000 feet above 16,000 feet) Maximum flaps extended (15) 152 knots (175 mph) (Above 20,000 feet) 137 knots (158 mph) Maximum flaps extended (30) 123 knots (142 mph) Maximum gear extended and operation 152 knots (175 mph) (Above 20,000 feet) 137 knots (158 mph) *C.G. Range (landing (+81.0) to (+87.7) at 3650 lbs. gear extended) (+74.0) to (+87.7) at 3100 lbs. Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight Takeoff and landing 3650 lbs. No. of Seats 4 (2 at +75, 2 at +115) or 5 (2 at +75, 2 at +115, 1 at +152) or 6 (2 at +75, 2 at +115, 2 at +152) Maximum Baggage Rear Compartment (Aft to Sta. 170) 400 lbs. (+150) (Structural Limits) On and forward of rear spar cover 200 lbs. (+108) with center seats removed Aft of rear spar cover to Sta.170 with 3rd, 4th, 5th, 6th, seats removed 400 lbs. (+145) Aft baggage compartment 70 lbs. (+180) (Sta. 170 to Sta. 190) 3A15 22 Rev. 100 XVI. Model A36TC cont'd) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm (Prior to EA-33) 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. (EA-33 and On) Standard Fuel System L&R Main 40 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. (+15) See NOTE 1 for data on system oil. Maximum Operating Altitude 25,000 feet Control Surface Movements Wing Flaps Approach 15  Down 30  Aileron tab Fixed Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 25  Right 25  Elevator tab Up 10  Down 27  Elevator Up 23  Down 20  Serial No. Eligible EA-1 thru EA-241 EA-243 thru EA-272 Required Equipment Items 14(c) and (d) and 11(e) or (g) or 16(a) and (b) and 11(e) or (g) and 403(bg), 102(d), 103, 117(e) and (g) (S/N EA-1), 117(e) and (f) or (h) (S/N EA-2 and On), 201(k), 202(f), 205(f), 206(a), 309(a) or (c) or (d), 310(a), 312(a) or (b), 403(bf), 601(a). XVII. Model B36TC, Bonanza, 4 to 6 PCLM (Utility Category), approved January 15, 1982 Engine Continental TSIO-520-UB *Fuel Aviation gasoline grade 100LL or 100 minimum *Engine Limits Takeoff and maximum continuous power 2700 rpm (36 in. Hg. MAP) (300 hp) *Airspeed Limits (IAS) Maneuvering 141 knots (162 mph) Maximum structural cruising 168 knots (193 mph) (Decrease 3 knots per 1,000 feet above 16,000 feet) Never exceed 206 knots (237 mph) (Decrease 4 knots per 1,000 feet above 16,000 feet) Maximum flaps extended (15) 154 knots (177 mph) (above 20,000 feet) 139 knots (160 mph) Maximum flaps extended (30) 125 knots (144 mph) Maximum gear extended and operation 154 knots (177 mph) (above 20,000 feet) 139 knots (160 mph) *C.G. Range (landing (+80.0) to (+87.7) at 3850 lbs. gear extended) (+74.0) to (+87.7) at 3200 lbs. Straight line variation between points given. Rev. 100 23 3A15 XVII. Model B36TC (cont’d) Empty Weight C.G. Range None *Maximum Weight Takeoff and landing 3850 lbs. No. of Seats 4 (2 at +75, 2 at +115) or 5 (2 at +75, 2 at +115, 1 at +152) or 6 (2 at +75, 2 at +115, 2 at +152) Maximum Baggage Rear Compartment (Aft. to Sta. 170) 400 lbs. (+150) (Structural Limits) On and forwar d of rear spar 200 lbs. (+108) cover with center seats removed Aft of rear spar cover to Sta. 170 400 lbs. (+145) with third, fourth, fifth, and sixth seats removed Aft baggage compartment 70 lbs. (+180) (Sta. 170 to Sta. 190) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L&R (two interconnected 54 ea. 51 ea. +75 leading edge tanks on each side) See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. (+15) See NOTE 1 for data on system oil. Maximum Operating Altitude 25,000 feet Control Surface Movements Wing flaps Approach 15  Down 30  Right aileron tab Fixed Left aileron tab (EA-242, EA-273 thru EA-388 except EA-320) Fixed Left aileron tab (EA-320, EA-389 and On) Up 9  Down 9  Aileron Up 20  Down 20  Rudder tab Fixed Rudder Left 20  Right 20  Elevator tab (EA-242, EA-273 thru EA-388 except EA-320) Up 10  Down 27  Right elevator tab (EA-320, EA-389 and On) Up 10  Down 25  Left elevator tab (EA-320, EA-389 and On) Up 8  Down 27  Elevator Up 23  Down 25  Serial No. Eligible EA-242, EA-273 and On (See NOTE 6) Required Equipment Items 19(a) and (b) and 11(e) or (g), 102(d), 103, 117(e) and (h), 201(k), 202(f), 205(f), 206(a), 309(c) or (d), 310(a), 311(a), 312(a) or (b), 403(bi) (prior to S/N EA-389 except EA-320), 403(bk) (S/N EA-320, EA-389 and On), 601(b). 3A15 24 Rev. 100 XVIII. Model G36, Bonanza, 6 PCLM (Utilit y Category), approved November 2, 2005 Model G36, Bonanza, 6 PCLM (Normal/Uti lity Category), approved September 28, 2022 Engine Continental IO-550-B *Fuel Aviation gasoline Grade 100LL or 100 minimum and Chinese aviation gasoline RH- 95/130 and RH-100/130 *Engine Limits For all operations 2700 rpm (300hp) *Airspeed Limits CAS CAS IAS Maneuvering 162 mph (139 knots) (141 knots) Maximum structural cruising 190 mph (165 knots) (167 knots) Never exceed 234 mph (203 knots) (205 knots) Flaps extended (12°) 175 mph (152 knots) (154 knots) Flaps extended (normal) 140 mph (122 knots) (124 knots) Landing gear extended (normal) 175 mph (152 knots) (154 knots) Utility Category Maneuvering (3650 lbs.) 162 mph (139 knots) (141 knots) Maneuvering (3200 lbs.) 160 mph (137 knots) (139 knots) Maneuvering (2800 lbs.) 151 mph (129 knots) (131 knots) Normal Category Maneuvering (3805 lbs.) 159 mph (136 knots) (138 knots) Maneuvering (3200 lbs.) 148 mph (127 knots) (129 knots) Maneuvering (2800 lbs.) 140 mph (120 knots) (122 knots) *C.G. Range Utility Category (landing gear (+81.0) to (+87.7) at 3650 lbs. extended) (+74.0) to (+87.7) at 3100 lbs. or less Straight line variation between points given. Normal Category (+81.0) to (+87.7) at 3805 lbs. (+81.0) to (+87.7) at 3650 lbs. (+74.0) to (+87.7) at 3100 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight Utility Category 3650 lbs. Normal Category 3805 lbs. Number of Seats 6 (2 at +75, 2 at +106, 2 at +152) Maximum Baggage Rear compartment (aft to Sta. 170) 400 lbs. (+150) (Structural Limits) with 5 th and 6th seat removed Rear compartment (aft of Sta. 170) 200 lbs. (+150) with only 5th or 6th seat removed Between spar carry thrust with 200 lbs. (+108) aft facing or center seats removed Aft baggage compartment 70 lbs. (+180) (Sta. 170 to Sta. 190) Rev. 100 25 3A15 XVIII. Model G36 (cont’d) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm Standard Fuel System L&R main 40 ea. 37 ea. +75 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. (+15) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps Approach 12° Down 30° Right aileron tab Fixed Left aileron tab Up 9° Down 9° Aileron Up 20° Down 20° Rudder tab Fixed Rudder Left 25° Right 23° Right elevator tab Up 10° Down 25° Left elevator tab Up 8° Down 27° Elevator Up 25° Down 20° Serial No. Eligible: Utility Category: E-3630 E-3636 thru E-4020 E-4022 thru E-4146 Normal/Utility Category: E-4021 E-4147 & On Required Equipment: Utility Category: Items 22, 102(d), 103, 117(j) and (l), 201(k), 202(f), 205(f), 206(a), 309(e) and (g), 310(a) and (b), 312(c) and (d), 403(bn) and 601(b). Normal/Utility Category: Items 22, 102(d), 103, 117(j) and (l), 201(k), 202(f), 205(f), 206(a), 309(e) and (g), 310(a) and (b), 312(c) and (d), 403(bo) and 601(b). Specifications Pertinent to All Models Datum 83.1 inches forward of jack pads on front spars Leveling Means Two external screws in bulkhead aft of baggage compartment on left side. (Use plumb bob.) Certification Basis Part 3 of the Civil Air Regulatio ns as amended to May 15, 1956, and Amendment 3-8. (except Model G36) Models A36TC and B36TC only, paragraphs 23.909, 23.1043, 23.1527(b), and 23.1583(a) as amended by Amendment 23-7, and paragraphs 23.959, 23.967(a)(5), and 23.1121(b) as amended by Amendment 23-18 of the Federal Aviation Regulations, Part 23, dated February 1, 1965. Model B36TC only, paragraph 23.1545(a) as amended by Amendment 23-23 of the Federal Aviation Regulations, Part 23, dated February 1, 1965. Part 36 through Amendment 36-10 of the Federal Aviation Regulations, Model F33A (CE-891 and On), Model V35B (D-10313 and On), Model F33C (CJ-156 and On), Model A36 (E-1609 thru E-3635, except E-3630, E-2581 equipped with Item 624), Model A36TC (EA-1 thru EA-241 and EA-243 thru EA-272), Model B36TC (EA-242, EA-273 and On). Part 36 thru Amendment 36-18 of the Federal Aviation Regulations, Model A36 (E-2581 thru E-3635, except E-3630 equipped with Item 624). 3A15 26 Rev. 100 Specifications Pertinent to All Models (cont’d) Certification Basis (cont’d) Equiva lent Safety Findings: CAR 3.663 and CAR 3.757 for Model V35B (D-9948 (except Model G36) and On), Model A36 (E- 927 thru E-3635, except E-3630), Model F33A (CE-674 and On), Model F33C (CJ-129 and On), Model A36TC (all serials); CAR 3.387 for Models V35B, A36, F33A, F33C, A36TC, B36TC (all serials). Application for Type Certificate dated July 6, 1956. Type Certificate No. 3A15 issued December 1, 1956, obtained by the manufacturer under delegation option procedures. Certification Basis (cont’d) Part 3 of the Civil Air Regul ations as amended to May 15, 1956, and Amendment 3-8. (Model G36 only) Part 36 thru Amendment 36- 18 of the Federal Aviation Regulations, Model G36 (E-3636 thru E-4020, E-4022 thru E-4146). Part 36 thru Amendment 36-31 of the Federal Aviation Regulations, Model G36 (E-4021, E-4147 and On). Equivalent Safety Findings: CAR 3.663, CAR 3.757, and CAR 3.387 Additional requirements for Garmin G1000 avionics installation: 23.303, 23.307(a), 23.601, 23.607, 23.609, 23.619, 23.625, 23.1367 all subparagraphs, 23.1381 all subparagraphs at original issue; 23.395(a)(1), 23.689 all subparagraphs through Amendment 23-7; 23.771(a) through Amendment 23-14; 23.685(a) through Amendment 23-17; 23.1301 all subparagraphs, 23.1327 all subparagraphs, 23.1335 all subparagraphs through Amendment 23-20; 23.1501, 23.1541(a)(b) through Amendment 23-21; 23.603 all subparagraphs, 23.605 (a) through Amendment 23-23; 23.1529 through Amendment 23-26; 23.1523 all subparagraphs through Amendment 23-34; 23.1322 all subparagraphs, 23.1331 all subparagraphs, 23.1357(a)(b)(c)(d) through Amendment 23- 43; 23.305(a)(b), 23.397 all subparagraphs, 23.613(a)(b)(c)(d), 23.773(a)(2), 23.1525, 23.1549(a)(b)(c) through Amendment 23-45; 23.301(a)(b)(c), 23.561(a)(b)(3), 23.611 all subparagraphs thru Amendment 23-48; 23.1303(a)(b)(c)(f), § 23.1307, 23.1309(a)(1)(2) (b)(c)(1)(2)(iii)(3)(d), 23.1311 All subparagraphs, 23.1321(a)(c)(d)(e), 23.1323(a)(c), 23.1329 All subparagraphs, 23.1351(a)(1)(2)(i)(b)(1)(2)(3) (c)(4)(d)(1)(g), 23.1353(a)(d)(e)(h), 23.1359(c), 23.1365(a)(b)(c)(d)(e), 23.1431(a)(b)(e) through Amendment 23-49; 23.143 all subparagraphs, 23.1325(b)(1)(i)(ii)(iii (2)(i), 23.1543(b)(c), 23.1545(a) (b)(1)(2)(3)(4), 23.1553, 23.1555(a)(b)(e)(2), 23.1563(a)(b), 23.1581(a)(b)(2)(3)(c)(f), 23.1583(h)(m)(n), 23.1585(j) through Amendment 23-50; 23.777(a)(b), 23.1337(b)(1) thru Amendment 23-51; 23.1305(a)(1)(2)(3)(b)(2)(3)(i) (4)(i)(5) through Amendment 23-52, Additional requirements for Garmin GI 275 avionics installation: 23.303, 23.307(a), 23.601, 23.609, 23.671, 23.1381(a)(b) at original issue; 23.771(a) through Amendment 23-14; 23.1301, 23.1327 through Amendment 23-20; 23.1501 through Amendment 23-21; 23.603(a)(1)(2)(b), 23.605(a) through Amendment 23-23; 23.1529 through Amendment 23-26; 23.1523(b) through Amendment 23-34; 23.1322, 23.1331, 23.1357(a)(b)(c) through Amendment 23-43; 23.305(a)(b), 23.613(a)(b), 23.1525 through Amendment 23-45; 23.301(a)(b), 23.561(b)(3) through Amendment 23-48; 23.1303(a)(b (f), 23.1309(a)(1)(2)(b)(c)(1)(2)(iii)(3) (d) (e), 23.1311(a)(b), 23.1321(a)(c)(d)(e), 23.1323(a)(c), 3.1351(a)(1)(2)(i), 23.1353(h), 23.1359(c), 23.1365(a)(d)(e), 23.1431(a)(b) through Amendment 23-49; 23.1325(a)(b)(1)(2)(i) 23.1543(b)(c), 23.1545(a)(b)(1)(2)(3)(4), 23.1555(a)(b), 23.1581(a)(1)(2) through Amendment 23-50; 23.777(a)(b) through Amendment 23-51; 23.1308(a)(b)(c) through Amendment 23-57; 23.1306(a)(b) through Amendment 23-61; 23.2010, 23.2510 through Amendment 23-64. Serial Effectivity: E-4021, E-4147 and On. Rev. 100 27 3A15 Specifications Pertinent to All Models (cont’d) Certification Basis (cont’d) Application fo r Type Certificate dated April 11, 2005. (Model G36 only) Special Conditions: Garmin AT STC SA01595SE included HIRF Special Condition, 23-172-SC. Type Certificate No. 3A15 issued November 2, 2005, obtained by the manufacturer under delegation option procedures Production Basis Production Certificate No. 8. Delegation Option Manufacturer No. DOA-230339-CE Authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. E-4071 thru E-4081, E-4083 thru E-4088, E-4090, E-4091, E-4094 thru E-4098: Manufactured under Production Certificate No. 4 by Textron Aviation, Inc., under license agreement between Beechcraft Corporation and Textron Aviation, Inc. E-3954, E-4082, E-4089, E-4092, E-4093, E-4099 and On: Manufactured under Production Certificate No. 4 by Textron Aviation Inc. Organization Delegation Authorization No. ODA-100129-CE is authorized to issue airworthiness certificates under the provisions of 14 CFR Part 21 and Part 183 of the Federal Aviation Regulations. Equipment A plus (+) or minus (-) sign preceding th e weight of an item of equipment indicates net weight changes when that item is installed. Approval of the installation of all items of equipment listed herein have been obtained by the aircraft manufacturer except those items preceded by a double 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 and therefore conformity must be determined if the item is not identified by a Form FAA-186, PMA or other evidence of FAA production approval. Propeller and Propeller Accessories (except Deicing Equipment) 1. Beech constant speed propeller installation (a) Beech 278-100 hub with 278-208-84 blades 69 lbs. (+ 1) Diameter: not over 84 in., not under 83 in. Pitch settings at 33 in. sta.: Low 13, high not under 30 (b) Woodward hydraulic governor (210175) 3 lbs. (+10) or (c) Woodward hydraulic governor (210235A) or any later rev. letter 3 lbs. (+10) 2. Beech constant speed propeller installation (a) Beech 278-100-7 hub with 278-209-84 blades 73 lbs. (+ 1) Diameter: Not over 84 in., not under 83 in. Pitch settings at 33 in. sta.: low 13, high not under 30 (b) Woodward hydraulic governor (210172H) 3 lbs. (+10) 3. Beech constant speed propeller installation (a) Beech 278-100-7 hub with 278-214-82 blades 69 lbs. (+ 1) Diameter: Not over 82 in., not under 81.5 in. Pitch settings at 33 in. sta.: low 13.5, high not under 30 (b) Woodward hydraulic governor (210235) all revisions 3 lbs. (+10) 4. Beech constant speed propeller installation (a) Beech 278-100-7 hub with 278-213-82 blades 73 lbs. (+ 1) Diameter: Not over 82 in., not under 81.5 in. Pitch settings at 33 in. sta.: low 13.5, high not under 30 (b) Woodward hydraulic governor (210235A) or any later rev. letter 3 lbs. (+10) 3A15 28 Rev. 100 Specifications Pertinent to All Models (cont’d) Propeller and Propeller Accessories (except Deicing Equipment) (cont’d) 5. Hartzell constant speed propeller installation (a) Hartzell BHC-92ZF-1D1 hub with 8447 blades 68 lbs. (+ 1) Diameter: not over 84 in., not under 82 in. Pitch settings at 33 in. sta.: low 11, high not under 26 (b) Hartzell hydraulic governor (B4-3) 4 lbs. (+10) or (c) Woodward hydraulic governor (210335) 3 lbs. (+10) (d) Hartzell propeller spinner (837-3) 2 lbs. (+ 1) 6. Beech constant speed propeller installation (a) Beech 278-100-11 or 278-100-13 hub with 278-214-82 blades 69 lbs. (+ 1) Diameter: 82 in., no cutoff permitted Pitch settings at 33 in., sta.: Low 13.5, high not under 30 and (b) Woodward hydraulic governor (210235 or 210350) 3 lbs. (+10) 7. Flottorp constant speed propeller installation (a) Flottorp F12A-4 with 8400- 0 blades 65 lbs. (+ 1) Diameter: Not over 84 in., not under 82 in. Pitch settings at 33 in. sta.: low 11.7  .2 each blade within .2 of each other, high 30 minimum (b) Flottorp IF-1 (34-825 Garwin) governor 5 lbs. (+10) (c) Flottorp FS 200 spinner 5 lbs. (+ 1) (d) Woodward governor (210452) (maximum rpm set at 2600) 3 lbs. (+10) 8. Flottorp constant speed propeller installation (H35 only) (a) Flottorp F12A-4 with 8400- 0 blades 65 lbs. (+ 1) Diameter: Not over 84 in., not under 83 in. Pitch settings at 33 in. sta.: low 13, high 30 minimum Airplane Flight Manual Supplement (AFMS) dated May 16, 1962 or August 30, 1962, P/N 35-590106, required. (b) Woodward governor (210452) (maximum rpm set at 2600) 3 lbs. (+10) (c) Flottorp FS 200 spinner assembly 5 lbs. (+ 1) 9. Flottorp constant speed propeller installation (J35, K35, M35, N35, P35) (a) Flottorp F12A-3 with 8400- 2 blades 65 lbs. (+ 1) Diameter: (J35, K35, M35 only) - not over 82 in., not under 81-1/2 in. (N35, P35 only) - not over or under 82 in. (No cutoff permitted) Pitch settings at 33 in. sta.: Low 13.5, high 30 minimum AFMS dated August 30, 1962, P/N 35-590106, required; or P/N 35-590101-7 dated May 1976 or later required, N35, P35. (b) Woodward governor (210452) 3 lbs. (+10) (Maximum rpm at 2600 for J35, K35, M35) (Maximum rpm at 2625 for N35, P35) (c) Flottorp FS 200-1 spinner assembly 5 lbs. (+ 1) 10. Flottorp constant speed propeller installation (H35, 35-33, 35-A33, 35-B33) (a) Flottorp F12A-5 with 8400- 0 blades 65 lbs. (+ 1) Diameter: (Model H35 only), not over 84 in., not under 83 in. (Models 35-33, 35-A33, 35-B33 only), not over 84 in., not under 82 in. Pitch settings at 33 in. sta.: Low: (Model H35 only) 13  (Models 35-33, 35-A33, 35-B33 only) 11.7  .2 each blade within .2 of each other High: (H35, 35-33, 35-A33, 35-B33 only) 30  minimum Model H35: AFMS dated August 30, 1962, P/N 35-590106, required when this propeller is used. (b) Woodward governor (210452) (maximum rpm set at 2600) 3 lb. (+10) (c) Flottorp IF-1 (34-825 Garwin) governor 5 lb. (+10) (d) Flottorp FS 200-1 spinner assembly 5 lb. (+ 1) Rev. 100 29 3A15 Specifications Pertinent to All Models (cont’d) Propeller and Propeller Accessories (except Deicing Equipment) (cont’d) 11. McCauley constant sp eed propeller installation (Models H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, E33, F33, G33, E33A, F33A, E33C, F33C, 36, A36) (a) McCauley 2A36C23 hub with 84B-0 blades 62 lbs. (+ 1) (Model 36) 62 lbs. (- 9) Diameter: Not over 84 in., not under 82 in. Pitch settings at 30 in. sta.: Low: (Models S35, V35, V 35A, V35B, 35-C33A, E33A, F33A, E33C, F33C, G33, N35, P35, 36, A36 only) 13.3  (35-33, 35-A33, 35-B33, 35-C33, E33, F33 only) 12.0  (Models J35, K35, M35 only) 13.0  (Model H35 only) 12.7  High: 29.2  minimum AFMS, P/N 35-001111, required as follows: Models N35, P35, 35-B33: AFMS dated June 21, 1963, or later, or Models N35, P35: P/N 35-590101- 9 dated May 1976 or later. Models 35-33, 35-A33, 35-B33: AFMS dated June 21, 1963 (for airplanes with IO-470-K engines only) or December 18, 1963, or later, or P/N 35-590101-9 dated June 1977. Models H35 (with O-470-G engine only), J35, K35, M35 (IO-470-C engine only): AFMS dated May 14, 1968. (b) Woodward governor (210452 or A210680) 3 lbs. (+10) (c) McCauley D3290A spinner assembly 4 lbs. (+ 1) (d) McCauley D2822 or D3396 spinner assembly 5 lbs. (+ 1) (Models 36, A36) 5 lbs. (- 9) (e) Woodward governor (C210452 or D210680) 3 lbs. (+10) (Models 36, A36, A36TC, B36TC) 3 lbs. ( 0) (f) Flottorp 1F1 (34-825 Garwin) governor 5 lbs. (+10) (g) McCauley governor C290D3-X/T23 3 lbs. (+10) (Models A36, A36TC, B36TC) 3 lbs. ( 0) 12. Hartzell constant speed 3-bladed propeller installation (Models S35, V35, V35A, V35B, 35-C33A, E33A, F33A) (a) Hartzell PHC-A3VF-4 hub with V8433-2R or V8433-4R blades 88 lbs. (+ 1) (Models S35, V35, 35-C33A, E33A, F33A), V8433-4R blades (Models V35A, V35B) Diameter: Not over 82 in., not under 78-1/4 in. Pitch settings at 30 in. sta.: Low: 10.5  for V8433-2R 11.2 for V8433-4R High: 30.8  for V8433-2R and V8433-4R (b) Hartzell 837-8 spinner assembly 6 lbs. (+ 1) (c) Woodward governor (C210452 or D210680) 3 lbs. (+10) 13. Hartzell constant speed 3-bladed propeller installation (Model 35-C33) (a) Hartzell PHC-A3VF-4 hub with V8433- 4R (D) blades 88 lbs. (+ 1) Diameter: Not over 80 in., not under 78-1/4 in. Pitch settings at 30 in. sta.: Low: 10.8   .2 High: 32  minimum (b) Hartzell 837-9 spinner assembly 6 lbs. (+ 1) (c) Woodward governor (210452) 3 lbs. (+10) 3A15 30 Rev. 100 Specifications Pertinent to All Models (cont’d) Propeller and Propeller Accessories (except Deicing Equipment) (cont’d) 14. McCauley constant speed 3-bladed prope ller (Models S35, V35, V35A, V35B, 35-C33, 35-C33A, E33A, F33A, F33C, 36, A36, A36TC) (a) McCauley 3A32C76 hub with 82NB-2 blades 66 lbs. (+ 1) (Models 36, A36) 66 lbs. (- 9) Diameter: Not over 80 in., not under 78-1/2 in. Pitch settings at 30 in. sta.: Low: (Models S35, V35, V35A, V35B, 35- C33A, E33A, F33A, F33C, 36, A36) 13.3   .2 (Model 35-C33) 12.5   .2 High: (Models S35, V35, V35A, V35B, 35-C33, 29.0   .5 35-C33A, E33A, F33A, F33C, 36, A36) Pitch settings at 30 in. sta. when used with Item 114 (Models S35, V35, V35A, V35B): Low: 14.2   .2 High: 34.0   .5 (b) McCauley D3600 spinner assembly 4 lbs. (+ 1) (c) McCauley D3584 spinner assembly 4 lbs. (+ 1) (Model 36, A36, A36TC) 4 lbs. (- 9) (d) McCauley 3A32C76U hub with 82NB-2 blad es (Model A36TC) 66 lbs. (- 9) Diameter: Not over 80 in., not under 78-1/2 in. Pitch settings at 30 in. Sta.: Low: 15.0   .2 High: 34.5   1.0 AFMS 130532, dated February 17, 1966, required for 35-C33. AFMS 130533, dated February 18, 1966, required for S35 and V35 or 35-590110-21, dated October 1975 or later, required for S35. AFMS 130605, dated June 17, 1966, required for S35 and V35 when used with the optional Item 114 engine installation. 15. McCauley constant speed 2-bladed propeller (a) McCauley 2A36C82 hub with 84B-2 blades 62 lbs. (+ 1) Diameter: 82 in. Pitch settings at 30 in. sta.: Low: 14.3   .2 High: 34.5   .5 16. Hartzell constant speed 3- bladed propeller installation (a) Hartzell PHC-C3YF-1RF hub with F8468A-6R or F8468AK-6R blades (A36TC) 75 lbs. (- 9) Diameter: Not over 80 inches, not under 78 inches Pitch settings at 30 in. sta.: Low: 13.0   2.0 High: 36.0   1.0 (b) Hartzell A2295-1P spinner assembly 5 lbs. (+ 1) (Models A36, A36TC) 5 lbs. (- 9) 17. Hartzell constant speed 3-bladed propeller installation (V35B, F33A, A36) (a) Hartzell PHC-C3YF-1RF/F8468A-6R installed per Beech Dwg. 36-960001 and Hartzell Flight Manual dated February 26, 1980, or later (STC SA785CE). Required equipment: Items 16(b) and 11(e) or (g) and 403(bh) (Models V35B, F33A) 75 lbs. (+ 1) (Model A36) 75 lbs. (- 9) Rev. 100 31 3A15 Specifications Pertinent to All Models (cont’d) 18. McCauley constant speed 3- bladed propeller (V35B, F33A, A36 (a) McCauley 3A32C406-/X/ hub with /X/-82NDB-2 blades (Models V35B, F33A) 63 lbs. (+ 1) (Model A36) 63 lbs. (- 9) The letters appearing in the place of the /x/ represent minor variations in the propeller hub or blades. They do not affect eligibility or interchangeability. Diameter: Not over 80 in., not under 78-1/2 in. Pitch settings at 30 in. sta.: Low: 13.3   .2 High: 29.0   .5 (b) McCauley D5259 or D5541 or D7168 spinner assembly (Models V35B, F33A) 5 lbs. (+ 1) (Model A36) 5 lbs. (- 9) 19. McCauley constant speed 3-bladed propeller (a) McCauley 3A32C406-/X/ hub with /X/- 82NDB-4 blades 63 lbs. (- 9) The letters appearing in the place of the /X/ represent minor variations in the propeller hub or blades. They do not affect eligibility or interchangeability. Diameter: Not over 78 in., not under 77 in. Pitch settings at 30 in. sta.: Low: 15.8   .2 High: 34.9   .5 (b) McCauley D5259 or D5541 or D7168 spinner assembly 5 lbs. (- 9) 20. McCauley constant speed 3-bladed propeller (a) McCauley D3A32C409-/X/ hub with /X/-82NDB-2 blades 63 lbs. (- 9) The letters appearing in the place of the /X/ represent minor variations in the propeller hub or blades. They do not affect eligibility or interchangeability. Diameter: Not over 80 in., not under 78-1/2 in. Pitch settings at 30 in. station: Low: 13.7   .2 High: 28.8   .5 (b) McCauley D5259 or D5541 or D7168 spinner assembly 5 lbs. (- 9) 21. Hartzell constant speed 3-blad ed propeller used with Item 624 (a) Hartzell PHC-C3YF-1RF hub with F7663-2R blades 70 lbs. (- 9) Diameter: Not over 76 in., not under 75.5 in. Pitch settings at 30 in. station: Low: 17.5   .1 High: 33.0   1.0 (b) Hartzell A-2295-1P spinner assembly 5 lbs. (- 9) (c) McCauley C290D3/X/T37 governor 3 lbs. ( 0) The letters appearing in the place of the/X/ represent minor variations in the governor. They do not affect eligibility or interchangeability. 22. Deleted. Referenced propeller approved by STC and installed via PLR. 3A15 32 Rev. 100 Specifications Pertinent to All Models (cont’d) 23. McCauley constant speed 3-bladed propeller (Model G36) (a) McCauley D3A34C444-/X/ hub with /X /-78MLA-0 blades 78.4 lbs. (- 10) The letters appearing in the place of /X/ represent minor variations in the propeller hub or blades. They do not affect eligibility or interchangeability. Diameter: Not over 78 in., not under 76 in. Pitch Setting at 30 in. station: Low: 12.5 ± 0.2 degrees High: 31.6 ± 0.5 degrees (b) McCauley E-8318 spinner assembly 6.4 lbs. (- 7) Engine and Engine Accessories - Fuel and Oil System 101. Fuel pumps (14-volt system) (a) Engine-driven, Lear-Romec Div. RD-7430-2 1 lb. (+39) (Continental Motors 535134 or 626845) (b) Wobble, Beech 35-924230-3 2 lbs. (+74) (c) Weldon 4020-A-1 3 lbs. (+74) (d) Engine-driven, Continental Motors 626062, -1 or -2 or -3 2 lbs. (+39) or 635135-3A1 or 638156-3A1 and (e) Weldon 4020-A-1-A, 4020-A-2-A or 4032-A 3 lbs. (+74) or (f) Thompson 221100-3 3 lbs. (+74) (g) Dukes 4140-00-1 3 lbs. (+74) (h) Dukes 4140-00-7 3 lbs. (+74) (i) Engine driven, Continental Motors 630947-2 or 638154-2A3 2 lbs. (+39) Models 36, A36 2 lbs. (+29) (j) Dukes 4140-00-39 3 lbs. (+74) (k) Engine driven, Continental Motors 626062-9 2 lbs. (+39) (l) Engine driven, Continental Motors 632637-1 2 lbs. (+39) (m) Dukes 4040-00-103 3 lbs. (+80) (n) Dukes 4258-00-15 (Models 36, A36) 3 lbs. (+74) (o) Dukes 4140-00-191 2 lbs. (+79) (p) Engine driven, Continental Motors 643239 (Model V35B) 2 lbs. (+39) (r) Dukes 1236-00-1 or 1372-00-1 2 lbs. (+74) (s) Airborne A/M2B6-54 or Dukes 1371-00-1 (Models V35B, F33A) 3 lbs. (+48) Model A36 3 lbs. (+38) 102. Oil radiator (a) Harrison 8525295 (Continental Motors 625093) 5 lbs. (+11) or (b) Harrison 8528220 (Continental Motors 627392) 5 lbs. (+11) (c) Modine 1E1406D (Continental Motors 632210) 8 lbs. (+36) Models 36, A36 8 lbs. (+26) or (d) Modine 1E1502D (Continental Motors 633277 or 634063) or Modine 1E1774D (Continental Motors 635996) or TCM P/N 655090 8 lbs. (+36) Models 36, G36, A36, A36TC, B36TC 8 lbs. (+26) 103. Induction air cleaner 1 lb. (+10) Models 36, A36, G36, A36TC, B36TC 1 lb. ( 0) 104. Vacuum pump (a) ARO A513-DB, Pesco 3P-194F, Garw in G450 or G455PM 4 lbs. (+41) installed per Beech Dwg. 33-001034, 35-324379-1 or 35-324426 or 35-910004 (b) Airborne 200CW or 200CW-8 or 222CW installed per Beech Dwg. 35-324407 4 lbs. (+41) (c) Airborne 224CW installed per Beech Dwg. 35-324407-7 4 lbs. (+41) Rev. 100 33 3A15 Specifications Pertinent to All Models (cont’d) 105. Starter (14-volt system) (a) Delco-Remy 1109471, 1109678, 1109681, 1109684, 1109694 13 lbs. (+39) (Continental Motors Models O-470-G, O-470-G-CI, IO-470-C, IO-470-J and IO-470-K engines only) (b) Delco-Remy 1108249 17 lbs. (+39) (Continental Motors Models O-470-G, O-470-G-CI, IO-470-C, IO-470-J, IO-470-K, IO-470-N, IO-520-B, and TSIO-520-D engines only) Model 36, A36 17 lbs. (+29) (c) Prestolite MCL6501 (CMC P/N 634592) (Continental Motors 18 lbs. (+39) Models O-470-G, O-470-G-CI, IO-470-C, IO-470-J, IO-470-K, IO-470-N, IO-520-B, and TSIO-520-D) Model 36, A36 18 lbs. (+29) 106. Two 10 gal. auxiliary wing fuel tanks 18 lbs. (+94) See NOTE 1 for data on system fuel. 107. Fuel booster pump installation 35-929020 (eligi ble on H35 when Item 108 fuel 6 lbs. (+57) injection system is not installed). Includes Adel 20653 or Thompson TF-36700 electric fuel pump. 108. Engine (eligible on Model H35) Continental O-470-G-CI installed per Beech Dwg. 35-001032 Negligible weight 109. Starter solenoid Delco-Remy 1114213 or 1118823 or 1464 used with Item 105(a), Negligible weight (b), or (c) (14-volt system) 110. Heated fuel tank vents installed per Beech Dwg. 35-001043 Negligible weight 111. Two 37 gal. fuel tanks in wing re placing two 22 gal. tanks; 11 lbs. (+75) 37 gal. usable in each at (+75). See NOTE 1 for data on system fuel. 112. Engine (eligible on Models 35-33, 35-A33) Continental IO-470-K (same as for IO-470-J engine) Use actual Installation requires revision to induction valve engine controls weight increase IAW Beech engineering data. See Item 11 for optional propeller with this engine. 113. Two 37 gal. fuel tanks in wing re placing the 22 gal. tanks; 11 lbs. (+75) 37 gal. usable in each at (+75). See NOTE 1 for data on system fuel. 114. Optional engine installation (S35, V35, V35A, V35B) (a) Continental TSIO-520-D engine with AiResearch turbocharger. Use actual system installed per Beech Dwg. 35-910028 and AiResearch weight increase Dwg. 100-S35-209 (STC SA1035WE). AiResearch FAA Approved AFMS dated December 2, 1965, or later required. Required equipment: Model V35: Item 101(j), 101(l), 101(m), 104(c) Models V35A, V35B: 115(b) Model S35: 12(a), (b) or 15(a), 11(d) and (e) or 14(a) and (c) and 11(e), 403(p) and (bl) Model V35: 403(r) and (bl) Model V35A: 403(t) or (w) and (bl) Model V35B: 403(y) or (aa) or (af) and (bl) 403(ac) (when two 22 or 37 gal. main fuel cells are installed per Item 616). NOTE: The above items of equipment are to be used when Item 114(a) is installed and in lieu of the corresponding items listed. Items not replaced and still listed are applicable as required. 3A15 34 Rev. 100 Specifications Pertinent to All Models (cont’d) 115. Pressure pump (a) Airborne 200CW or 232CW installed per Beech Dwg. 35-329012-5 or -7 (Models 36, A36) 4 lbs. (+31) (Models 9V35A, V35B, E33A, F33A, E33C, F33C) 4 lbs. (+41) (b) Airborne 224CW or 232CW installed per Beech Dwg. 35-329012-7 4 lbs. (+41) with Item 114 only (c) Airborne 200CW or 232CW installed per Beech Dwg. 33-329010 4 lbs. (+41) (Models E33, F33, G33) (d) Airborne 432CW or 442CW installed per Beech Dwg. 36-324018 (Models V35A, V35B, E33, F33, G33, E33A, F33A, E33C, F33C) 432CW (6 lb.) or 442CW 3 lbs. (+41) (Models 36, A36, A36TC, B36TC) 432C W (6 lb.) or 442CW 3 lbs. (+31) (e) Airborne 242CW (Models E33, E33A, E33C, F33, F33A, F33C, G33, V35A, V35B) 2 lbs. (+41) (Models 36, A36) 2 lbs. (+31) (f) Airborne 212CW or 216CW (F33A, F33C, V35B) 2 lbs. (+41) (Models A36, A36TC, B36TC) 2 lbs. (+31) 116. Optional engine installation (V35B) (a) Continental IO-520-N engine with automatic power control system per Use act. wt. increase applicable Beech Dwgs. Pilot's Operating Handbook and FAA Approved AFMS P/N 35-590118-37 dated August 1979 or later required. Required equipment Item 101(p) and 101(r) and 101(s). NOTE: The above items of equipment are to be used when Item 116(a) is installed and in lieu of the corresponding items listed in applicable sections. Items not replaced and still listed are applicable as required. 117. Fuel pumps (28-volt system) (a) Dukes 1296-00-1 3 lbs. (+74) (b) Dukes 1297-00-1 2 lbs. (+79) (c) Engine driven, CMC 630947-2 or 638154-2A3 2 lbs. (+39) Model A36 2 lbs. (+29) (d) Engine driven, Continental Motors 638154-16A2 (used with IO-520-BB engine) 2 lbs. (+39) Model A36 2 lbs. (+29) (e) Airborne 2B7-34 (used with TSIO-520-U or -UB engine) 5 lbs. (+74) Model A36TC, B36TC (f) Engine driven TCM 639508-9A1 (used with TSIO-520-UB engine) 2 lbs. (+29) Model A36TC (g) Engine driven TCM 639508-5 (used with TSO-520-U engine) 2 lbs. (+29) (h) Engine driven TCM 639508-9A3 (used with TSIO-520-UB engine) 2 lbs. (+29) (Model B36TC, Model A36TC when Kit No. 36-9008-1 is installed) (i) Dukes 4613-00-3 or 4613-00-3NV or 4615-00-5 2 lbs. (+74) (j) Engine driven, Continental Motors 643535-1 or TCM 646212 (used with IO-550-B engine) (Models A36, G36) 2 lbs. (+29) (k) Dukes 4613-00-3NV or 4615-00-5 2 lbs. (+74) (l) Dukes 4613-00-5 (Boost pump) 2 lbs. (+74) 118. Starter (28-volt system) (a) Prestolite MHJ-4003 (CMC P/N 637847) used on Continental Motors engines IO-520-BA, IO-520-BB, TSIO-520-U, and TSIO-520-UB 16 lbs. (+39) (Model A36, A36TC, B36TC) 16 lbs. (+29) (b) Continental Motors P/N 646275 used on Continental Motors engines IO-520-BA, IO-520-BB, TSIO-520-U, TSIO-520-UB, and IO-550-B 14 lbs. (+39) (Model A36, A36TC, B36TC) or Prestolite WHJ-4003 (TCM 655566F) used with IO-550-B engine) 14 lbs. (+29) (Model A36, G36) 119. Starter solenoid (28-volt system) (a) Cutler-Hammer 6041H190 us ed with Item 118(a) Negligible weight Rev. 100 35 3A15 Specifications Pertinent to All Models (cont’d) 120. Optional engine installation (S35 , V35, V35A, V35B, prior to D-10179; 35C33A, E33A, E33C, F33A, prior to CE-816; F33C, prior to CJ-149; 36 and A36, prior to E-1371). (a) Continental IO-520-BB engine insta lled per applicable Beech drawings. Use actual Required equipment Item 117(d). weight increase The above item of equipment is to be used when Item 120(a) is installed and in lieu of the corresponding item listed in applicable section. Landing Gear 201. Two main wheel brake assemblies (a) Goodyear 6.50-8, Type III, Model L6.50 8HBDM or L6.50-8HBM 21 lbs. (+97) Wheel assembly No. 530869M or 9530949 Brake assembly No. 511731M or (b) Goodyear 6.50-8, Type III, No. PD 931 25 lbs. (+97) Wheel assembly No. 9532135 Brake assembly No. 9532167, 9532475, 9532412, or 9532679 or (c) Cleveland 6.00-6 19 lbs. (+97) Wheel assembly 27-100D Brake assembly 35-200A or (d) Cleveland 6.00-6 19 lbs. (+97) Wheel assembly 40-37 Brake assembly 30-24 or (e) Beech 6.00-6, Type III, No. 95-300001 23 lbs. (+97) Wheel assembly 95-300001-1 or 95-300001-67 L.H. brake assembly no. 95-300001-5 R.H. brake assembly no. 95-300001-6 Use only with Item 202(e) or (f). or (f) Beech 6.00-6, Type III, No. 95-300001 23 lbs. (+97) Wheel assembly no. 95-300001-1 or 95-300001-67 modified per Goodyear Dwg. 5R2-430 L.H. Brake assembly No. 95-300001-5 R.H. Brake assembly No. 95-300001-6 Use only with Item 202(e) or (f) or (g) Goodyear 6.50-8, Type III, PD 931 25 lbs. (+97) Wheel assembly No. 9532135 modified per Goodyear Dwg. 5R3-123 Brake assembly No. 9532167, 9532412, 9532475, or 9532679 Use only with Item 202(a). or (h) Beech 6.00-6, Type III, No. 95-30001 23 lbs. (+97) Wheel assembly No. 95-300001-73 L.H. brake assembly No. 95-300001-5 R.H. brake assembly No. 95-300001-6 or (j) Goodyear 6.00-6 or Beech 6.00-6, Type III No. 35-8002 22 lbs. (+97) Wheel assembly No. 9543027 or 35-8002-3 Brake assembly No. 5E4-2869 or 35-8002-5 or 35-8002-25 Use only with Item 202(e) or (f). or (k) Cleveland 6.00-6, No. 20-69 19 lbs. (+97) Wheel assembly No. 40-83 or 40-83A or 40-83B Brake assembly No. 30-54 or 30-54A Use only with Item 202(e) or (f) when modified per Beech Dwg. 35-8004 or (l) Cleveland Wheel assembly 40-98 20 lbs. (+97) Brake assembly 30-66 8 lbs. (+97) 3A15 36 Rev. 100 Specifications Pertinent to All Models (cont’d) 202. Main wheel tires (a) Two 6.50-8, 4 or 6-ply rating tire s with regular tubes 23 lbs. (+97) (b) Two 6.50-8 side inflatable 4 or 6-ply rating tubeless tires used only with Item 201(b) 21 lbs. (+97) or (c) Two 6.00-6 side inflatable 6- ply rating tubeless tires used only with Item 201(c)or (d) or (e) 20 lbs. (+97) or (d) Two 7.00-6 side inflatable 6-ply rating tube less tires used only with Item 201(e) 20 lbs. (+97) or (e) Two 6.00-6, 6-ply rating tires with regular tubes used only with Item 201(f) or (h) or (j) or (k) 18 lbs. (+97) or (f) Two 7.00-6, 6-ply rating tires with regular tubes used only with Item 201(f) or (h) or (j) or (k) 24 lbs. (+97) 205. One nose-wheel 5.00-5 (a) Goodyear Model L5NBD or (L5NBM or Firestone Model DFA531-1 or Goodrich Model 3-897 3 lbs. (+12) or (b) Goodyear 9532102 or 9532669 4 lbs. (+12) (c) Cleveland 21-100 4 lbs. (+12) or (d) Goodyear 9532102 or 9532669 modified per Goodyear Dwg. 5R2-365 and -366. Use only with Item 206(a). 4 lbs. (+12) or (e) Goodyear 9532926. Use only with Item 206(a). 4 lbs. (+12) or (f) Wheel assembly, Cleveland No. 40-77E. 3 lbs. (+12) Use only with Item 206(a). Models 36, A36, G36, A36TC, B36TC 3 lbs. (+ 2) 206. Nose wheel tire (a) One 4-ply rating tire 5.00-5 with regular tube. Use only with Item 205(a) or (d) or (e) or (f) 7 lbs. (+12) Models 36, A36, G36, A36TC, B36TC 7 lbs. (+ 2) or (b) 4-ply rating, side inflatab le, 5.00-5 tubeless tire used only with Item 205(b) or (c). 5 lbs. (+12) 210. Co-pilot brakes (H35 through M35) 2 lbs. (+54) 211. Co-pilot brakes (N35 and subsequent , 35-A33 and subsequent) 4 lbs. (+54) Model 36, A36, G36, A36TC, B36TC 4 lbs. (+44) Electrical Equipment 301. Generator (14-volt system) (a) 50 a. CMC P/N 535896 or Delco-Remy 1101895 16 lbs. (+37) or (b) 50 a. CMC P/N 626380 or Delco-Remy 1101909 16 lbs. (+37) or (c) 50 a. CMC P/N 627272 or Delco-Remy 1101912 16 lbs. (+37) (d) 35 a. CMC P/N 627273 or Delco-Remy 1101913 16 lbs. (+37) (e) 70 a. Delco-Remy P/N 1100667 11 lbs. (+11) or (f) 70 a. Delco-Remy P/N 1100715 11 lbs. (+11) Models 36, A36 11 lbs. (+ 1) (g) 60 a. Beech P/N 33-380009 or 380009-1 installed per Beech Dwg. 33-3001 (H35 thru P35 and 35-33 thru 35-C33) or Beech Dwg. 33-369110 (35-C33, E33, F33) or Beech Dwg. 33-369113 (G33). Item 304(e) required. (h) 70 a. CMC P/N 634785 or Prestolite ALX-9424 11 lbs. (+11) or CMC P/N 641670 or Prestolite ALX-9424 11 lbs. (+ 1) 302. Battery (14-volt system) (a) 12 v. 33 a. hr. (mounted aft of firewa ll in cabin compartment) 28 lbs. (+54) or (b) 12 v. 24 a. hr. Sonotone 22500 nickel -cadmium, installed per Beech 28 lbs. (+54) Dwg. 35-001040. Item 403(h) required. (c) 12 v. 33 a. hr. (mounted forward of firewa ll in engine compartment) 28 lbs. (+45) Models 36, A36 28 lbs. (+35) (d) 12 v. 33 a. hr. (mounted fwd. of firewall in engine compartment per Beech Dwg. 35-3001). 28 lbs. (+45) Rev. 100 37 3A15 Specifications Pertinent to All Models (cont’d) 303. Landing lights (14-volt system) (a) Two General Electric 4522 1 lb. ea (+72) (b) One General Electric 4522 1 lb. (+11) or (c) One General Electric 4522 and one General Electric 4509/4313 2 lbs. (+ 9) (d) One General Electric 4313 1 lb. (+ 7) Model 36, A36 1 lb. ( -3) (e) Two General Electric 4313 2 lbs. (+ 9) Model 36, A36 2 lbs. (- 1) 304. Voltage regulator (14-volt system) (a) Delco-Remy 1118713 2 lbs. (+48) or (b) Delco-Remy 1119224C 2 lbs. (+48) (c) Delco-Remy 1119220C 2 lbs. (+48) (d) Delco-Remy 9000590 used with 301(e) or (f) only 1 lb. (+46) (e) Beech P/N 33-380010 used with Item 301(g) only 1 lb. (+48) or (f) Beech P/N 35-380093 used with Item 301(e) or (f) or (h) 1 lb. (+50) or (g) Beech P/N 35-380093-1 used with Item 301(e) or (f) or (h) 1 lb. (+50) Models 36, A36 1 lb. (+40) or (h) Beech P/N 35-380093-2 used with Item 302(e) or (f) or (h) 1 lb. (+50) Models 36, A36 1 lb. (+40) 305. Anti-collision light, upper, installed per Beech Dwg. 35-364123, 33-001024 or 35-364161 (14-volt system) 2 lbs. (+182) (a) Grimes D7080-1-12 or (b) Beech 33-380003-1 (Whelen WRM-12) 306. Anti-collision light, lower, installed per Beech Dwg. 95-364027 2 lbs. (+102) 35-001031, 33-001024, or 35-364161 (14-volt system) (a) Grimes D7080-1-12 or (b) Beech 33-380003-3 (Whelen WRM B-12) To be installed only when Item 305 is installed. 307. Anti-collision light (Mode ls 36, A36) (14-volt system) (a) Dual - installed per Dwg. 36-360011 (G rimes D7080A-1-12 top, 4 lbs. (+178) D7080A-6-12 bottom) or (Beech 33-380003-1 top, 33-380003-3 bottom) (b) Single top mounted installed per Dwg. 36-360011 (Grimes D7080A-1-12 or Beech 33-380003-1) 2 lbs. (+246) 308. Alternate re-exciter, P/N 60-369017 (Model 36 only) 14-volt system) Negligible weight 309. Alternator (28-volt system) (a) 50 a. 24 v. CMC P/N 641668 or Prestolite ALT-9422 12 lbs. (+11) Model 36, A36TC 12 lbs. (+ 1) (b) 100 a. 24 v. CMC P/N 640789 or Prestolite ALV-9407 23 lbs. (+11) Model A36 22 lbs. (+ 1) (c) 100 a. 24 v. CMC P/N 642056 or CMC P/N 646491 or TCM 18 lbs. (+11) P/N 646844 or TCM P/N 649305 Model A36, A36TC, B36TC 18 lbs. (+ 1) (d) 60 a. 24 v. CMC P/N 642055 or CMC P/N 646490 12.5 lbs. (+11) Model A36, A36TC, B36TC 12.5 lbs. (+ 1) (e) 100 a. 24 v. CMC P/N 646491 or TCM P/N 646844 or TCM P/N 18 lbs. (+ 1) 649305 or CMI P/N 658567 used with IO-550-B engine or CMI P/N 658567 used with IO-550-B engine 13.6 lbs. (+ 1) (f) 60 a. 24 v. CMC P/N 646490 used with IO-550-B engine 12.5 lbs. (+ 1) (g) 20 a. 24 v P/N BC410-1 used with IO-550-B engine (See NOTE 7). Model G36 6 lbs. (+31) 3A15 38 Rev. 100 Specifications Pertinent to All Models (cont’d) 310. Battery (28-volt system) (a) 24 v. 10 a. hr. 25 lbs. (+45) Models A36, G36, A36TC, B36TC 25 lbs. (+38) (b) 24 v. 3.5 a hr. (See NOTE 7) Model G36 12 lbs. (+45) 311. Landing lights (28-volt system) (a) Two General Electric 4596 2 lbs. (+ 9) Models A36, A36TC, B36TC 2 lbs. (- 1) 312. Voltage regulator (28-volt system) (a) Beech P/N 60-389017-3 used with Items 309(a) or (b) or (c) 1 lb. (+50) Models A36, A36TC, B36TC 1 lb. (+40) (b) Beech P/N 36-380056-1 used with Items 309(a) or (b) or (c) 1 lb. (+50) Models A36, A36TC, B36TC 1 lb. (+40) (c) Beech P/N 36-380096-1 used with 309(e) Model A36, G36 1 lb. (+45) (d) B & G BC203-2E used with 309(g) (See NOTE 7) Model G36 1 lb. (+40) 313. Anti-collision light, upper, installed per Beech Dwg. 36-364030 (28-volt system, Models F33A, F33C, V35B) (a) Grimes D-7080A-1-24 2 lbs. (+182) or (b) Whelen WRML-28 2 lbs. (+182) or (c) Whelen 01-0790081-01 1 lb. (+182) 314. Lower beacon light installed per Beech Dwg. 36-364030 or 96-364078 (28 volt system, Models F33A, F33C, V35B) (a) Grimes D-7080A-5-24 to be installed only when Item 313(a) is installed. 2 lbs. (+102) or (b) Whelen WRML-28CCW 2 lbs. (+102) or (c) Grimes 40-0100-3C 2 lbs. (+102) or (d) Whelen 01-0790081-02 1 lb. (+102) 315. Anti-collision light (Model A36, A36TC, G36, B36TC, 28-volt system) (a) Single, top mounted, installed per Beech Dwg. 36-364030 (Grimes D7080A-3-24) 2 lbs. (+246) or (b) Single, top mounted, installed per Be ech Dwg. 36-364030 (Whelen WRML-28) 2 lbs. (+246) or (c) Single, top mounted, installed per Beech Dwg. 36-364030 (Whelen 01-079081-00) 1 lb. (+246) or (d) Dual - installed per Beech Dwg. 36-364030 1 lb. (+246) (Grimes D7080A-3-24 top, Grimes D7080A-5-24 bottom) 4 lbs. (+178) or (e) Dual - installed per Beech Dwg. 36-364030 (Whelen WRML-28 top, WhelenWRML-28CCW bottom) 4 lbs. (+178) or (f) Dual - installed per Beech Dwg. 36-364030 (Whelen WRML-28 top) and Dwg. 96-364070 (Grimes 40-0100-3C bottom) 4 lbs. (+178) or (g) Dual - installed per Beech Dwg. 36-364030 (Whelen 01-0790081-00 top) and Dwg. 96-364078 (Grimes 40-0100-3C bottom) 3 lbs. (+150) or (h) Dual - installed per Beech Dwg. 36-364030 (Whelen 01-0790081-00 top, Whelen 01-0790081-02 bottom) 2 lbs. (+178) Interior Equipment 401. Parachute flares (a) Three 1-1/2 minute, International 15 lbs. (+164) 402. Dual control column (T-type). All serials except E-1946, E-2104, E-2111 and On; EA-320, EA-389 and On. (a) Beech 35-524575 (Models H35 thru N35, 35-33 thru 35-A33) 3 lbs. (+72) (b) Beech 35-524656 (Models P35, S 35, V35, V35A, V35B, 35-B33, 35-C33, E33, F33, G33, 35-C33A, E33A, F33A, E33C) 3 lbs. (+72) Models 36, A36 3 lbs. (+62) (c) Beech 36-524021 (Models V35B, F33A, F33C) 4 lbs. (+73) Models 36, A36, A36TC, B36TC 4 lbs. (+63) Rev. 100 39 3A15 Specifications Pertinent to All Models (cont’d) 403. Airplane Flight Ma nuals (AFM) - DOA approved (a) Deleted (b) Deleted (c) Deleted (d) Deleted (e) Deleted (f) Model H35 AFMS No. 1 dated February 2, 1959, usable H35 and required with Item 108(a) engine installation. (g) Deleted (h) Models H35, J35, K35, M 35, AFMS dated November 20, 1959, required with Item 302(b). (i) AFMS dated December 3, 1959, required with Item 302(b) for Model 35-33. (j) Model 35-33 dated November 5, 1959, 1962, or A ugust 30, 1962, with Item 5, or August 30, 1962, with Item 10; or Item 403(au). (k) Model 35-A33 dated September 15, 1960, revised Dece mber 29, 1960, or August 30, 1962, with Item 10; or Item 403(av). (l) Deleted (m) Model 35-B33 dated September 29, 1961, or A ugust 30, 1962, with Item 10; or Item 403(av). (n) Deleted (o) Model 35-33 dated January 15, 1962, with Item 7; or Item 403(au). (p) Model S35 dated March 31, 1964, or July 8, 1964, or August 18, 1965 (used with Item 114). (q) Model 35-C33 dated November 20, 1964; or Item 403(aw). (r) Model V35 dated October 13, 1965 (used with Item 114). (s) Model 35-C33 dated April 23, 1965 (CD-945 and On , CD-814 thru CD-944 eligible upon re-marking existing airspeed indicator) (t) Model V35A dated September 22, 1967, or September 20, 1968, or October 16, 1970 (used with Item 114). (u) Model E33 dated September 29, 1967, or September 20, 1968, or July 31, 1970; or Item 403(aw). (v) Model E33 dated September 20, 1968, or July 31, 1970 (CD-1200 thru CD-1234); or Item 493(aw). (w) Model V35A dated September 20, 1968, or October 16, 1970 (CD-8872 and On) (used with Item 114). (x) Model F33 dated July 15, 1969. (y) Model V35B dated August 31, 1970, or May 7, 1971 (used with Item 114). (z) Model F33 dated September 12, 1969; or Item 403(aw). (aa) Model V35B dated Sept ember 12, 1969; or June 30, 1970 (used with Item 114). (ab) Model G33 dated January 29, 1971. (ac) AFMS dated February 11, 1972 (used with Item 114). (ad) Model G33 dated February 11, 1972. (ae) Deleted (af) Model V35B dated August 18, 1972 (used with Item 114). (ag) Model A36 dated August 25, 19 72; superseded by Item 403(be). (ah) Deleted (ai) AFMS dated Novemb er 3, 1972, or later. (aj) AFMS dated May 2, 1975, or later with Item 619. (ak) Model K35, M35 POH and FAA Approve d AFM as revised March 1987 or later. (al) Model S35 POH and FAA Approved AFM as revised Ma rch 1987 or later (used when Item 114 is not installed). (am) Model H35 POH and FAA Approved AF M as revised March 1987 or later. (an) Model J35 POH and FAA Approved AFM as revised March 1987 or later. (ao) Models N35, P35 POH and FAA Appr oved AFM as revised March 1987 or later. (ap) Deleted (aq) Model A36 (E-927 thru E2110, except E-1946 & E-2104) POH and FAA Approved AFM 36-590002-17 dated October 1976 or later. (ar) Model F33A (CE-674 and On) and Model F 33C (CJ-129 and On) POH and FAA Approved AFMS dated October 1976 or later (P/N 33-590009-13). (as) Acrobatic Bonanza F33C (CJ-129 thru CJ- 155) POH and FAA Approved AFMS, dated December 1982 or later. (at) Models V35, V35A, V35B POH and FAA Approved AF M as revised March 1987 or later (used when Item 114 is not installed). 3A15 40 Rev. 100 Specifications Pertinent to All Models (cont’d) 403 (cont’d) (au) Model 35-33 POH and FAA Approve d AFM dated June 1977 or later. (av) Models 35-A33 and 35-B33 POH and F AA Approved AFM dated July 1977 or later. (aw) Model 35-C33, E33, and F33 POH and F AA Approved AFM dated September 1977 or later. (ax) Model 35-C33A, E33A, and E33C POH and FAA Approved AFM dated October 1977 or later. (ay) POH and FAA Approved AFMS for the Acrobatic Bona nza E33C (S/N CJ-1 thru CJ-35) dated December 1982 or later. (az) Model F33A (CE-290 thru CE-673) and Model F 33C (CJ-26 thru CJ-128) POH and FAA Approved AFM dated November 1977 or later (P/N 33-59000-15). (ba) POH and FAA Approved AFMS for the Acrobatic B onanza F33 C (CJ-26 thru CJ-128) dated December 1982 or later. (bb) Model V35B POH and FAA Approved AF M as revised March 1987 or later (used when Item 114 is not installed). (bc) Model A36 POH and FAA Appr oved AFM superseded by 403(be). (bd) Deleted (be) Model 36 (E-1 and On) and Model A36 (E-185 thru E-926) POH and FAA Approved AFM 36-590002-19, reissued August 1982. (bf) Model A36TC POH and FAA Approved AFM dated November 1978 or later. (bg) Model A36TC POH and FAA Approved AFMS, dated April 1980 or later, required with Item 16(a). (bh) Models V35B, F33A, A36 POH and FAA Approved AFMS, dated April 1980 or later, required with Item 17(a). (bi) Model B36TC POH and FAA Approve d AFM dated January 1982 or later. (bj) Model A36 (E-1946, E2104, E2111 thru E-3629 and E-3631 thru E-3635) POH and FAA Approved AFM 36-590002-37, reissued November 2002. (bk) Model B36TC POH and FAA Approve d AFM dated October 1983 or later. (bl) FAA Approved AFMS dated March 1987 or later required with Item 114. (bm) POH and FAA Approved AFMS, dated April 1991 or later, required with Item 624. (bn) Model G36 POH and FAA Approved AFM P/N 36-590002-71 (bo) Model G36 Bonanza (E-4021, E-4147 and On) POH and FAA Approved AFM P/N 36-590002-0101 404. Air conditioner installation (i ncluding water) 18 lbs. (+148) 405. (a) Tactair T-3 automatic pilot pe r Beech Dwg. Mod. C.O. B44277 or Beech Dwg. 33-500000 or Tactair Kit No. A1575 including Maintenance and Trouble Shooting T-3 Automatic Pilot (Models 35-33, 35-A33, 35-B33). AFMS dated December 10, 1959, revised December 23, 1960, or dated June 1977 or later, required. (b) AH-1 Altitude Hold per Beech Dwg. Mod. C. O. 57557 or Tactair Kit No. 2 lbs. (+ 58) A1521 (Models 35-A33, 35-B33). Used only with Item 405(a). 406. Tactair T-2 Automatic Pilot per Beech Dwg. Mod. C., B46005 or Tactair Kit 13 lbs. (+79) No. A1915 including Installation Instructions Form BL-1 and Operating Weight includes two Instructions Form BL-2 (Models 35-33, 35-A33, 35-B33). AFMS gyro instruments dated December 16, 1959, or dated June 1977 or later, required. 407. (a) Tactair T-3 Automatic Pilot per Beech Dwg. 35-500001 or Tactair 19 lbs. (+ 95) Kit D451 (Models N35, P35). AFMS dated November 1, 1960, revised December 23, 1960, or AFMS dated November 3, 1961, required for Model N35; and AFMS dated November 3, 1961, required on Model P35; or AFMS 35-590110-17 dated May 1976 or later required for N35, P35. (b) Tactair AH-1 Altitude Hold pr Beech Dwg. 35-500013 or 2 lbs. (+58) Tactair Kit A1521 (Models N35, P35, S35, V35), or Mod. C.O. B83160 (Model S35 only). Usable with Item 407(a) or (c) only. (c) Tactair T-3 automatic pilot per Beech Dwg. 35-500001 or Tactair 19 lbs. (+101) Kit D451 (Models S35, V35), or Mod. C.O. B83160 Tactair Kit D4541 Weight includes two (Model S35 only). AFMS 35-500001-1, dated November 3, 1961, gyro instruments or 35-590110-17 dated October 1975 or later, required for S35. Rev. 100 41 3A15 Specifications Pertinent to All Models (cont’d) 408. Beech Power Flite Control single axis autopilot (a) Basic autopilot system per Beech Dwg. 33-500013-1 or 33-500013-51 6 lbs. (+87) (Models P35, 35-B33 only) or 35-001062, AFMS dated September 29, 1961, required. (b) Autopilot system with course selector directional gyro per Beech Dwg. 10 lbs. (+79) 33-500013-5 or 33-500013-55 (Models P35, 35-B33 only) or 35-001062-1 and -3 AFMS dated September 29, 1961, required. 409. Tactair T-3AL Automatic Pilot 23 lbs. (+93) (a) Installed per Beech Dwg. 33-500002 or Tactair Kit B-2586 23 lbs. (+93) (Models 35-B33, 35-C33 only) AFMS 33-500002-1, dated Weight includes two August 5, 1964, or May 25, 1966, or later, required. gyro instruments (b) Installed per Beech Dwg. 35-500003 or Tactair Kit B-2587 23 lbs. (+93) (Models S35, V35). AFMS 35-500003-1, dated September 1, 1964 or 35-590110-19, dated October 1975 or later, required on S35. (c) Installed per Beech Dwg. 33-500004 or Tactair Kit A3103 (Model 23 lbs. (+93) 35-C33 only). AFMS 33-500002-1 dated May 25, 1966, or later, required. Weight includes two gyro instruments 410. Pilot's check lists: DOA Approved (a) Model F33A (CE-290 thru CE-349) dated November 4, 1969, January 30, 1970, or August 23, 1971: (CE-350 and On) dated August 23, 1971. (b) Model A36 (E-185 thru E-282) dated November 7, 1969, January 30, 1970, or August 23, 1971: (E-283 thru E-3635, except E-3630) dated August 23, 1971. (c) Model F33A reissued February 11, 1972. (d) Model A36 reissued February 11, 1972. 411. Airplane Flight Manuals: DOA Approved (a) Superseded by Item 403(bb) (b) Superseded by Item 403(bc) (c) Superseded by Item 403(az) Deicing Equipment (Propeller) 501. (14-volt system) (a) B.F. Goodrich Electro Thermal Propeller Deicer System on Models 33, 9 lbs. (+22) 35, 36, used in conjunction with McCauley's 2A36C82 or 2A36C23 (36 & A36) (+12) two-bladed propeller installed per Beech Dwg. 35-960076 or Beech Kit Dwg. 35-9001. AFMS P/N 130554 dated February 6, 1967 or later, or AFMS 35-590118-25 dated January 30, 1973, or later, required as applicable, on Models S35, V35, V35A, V35B, E33, F33. AFM P/N 130694 dated March 1, 1967, or later, required on Model 35-C33A. Current FAA Approved checklist or AFMS P/N 35-590118-25 dated January 30, 1973, or later, or P/N 130694 dated October 1977 or later. required as applicable on Models E33, E33A, F33, F33A, F33C, 36, A36. (b) B.F. Goodrich Electro Thermal Propeller Deicing System on Models 33, 35, 9 lbs. (+22) 36, used in conjunction with McCauley's 3A32C76 three-bladed propeller (36 & A36) (+12) installed per Beech Dwg. 35-960077 or Beech Kit Dwg. 35-9005. AFMS P/N 130555 dated February 6, 1967, or later, or AFMS P/N 35-590118-25 dated January 30, 1973, or later, or P/N 130694 dated October 1977 or later, required as applicable on Models S35, V35, V35A, V35B, F33A, A36. AFM P/N 130687, dated February 21, 1967, or later, or AFM P/N 130694, dated October 1977 or later, required on Model 35-C33A, current FAA Approved Checklist or AFMS P/N 35-590118-25, dated January 30, 1973, or later or AFM P/N 130694 dated October 1977 or later, required as applicable on Models F33A, A36. AFM P/N 131332 dated March 14, 1975, or later, or AFM P/N 130694 dated October 1977 or later, applicable on Model 36. (c) B.F. Goodrich electro thermal propeller de icing system used in conjunction 9 lbs. (+24) with Hartzell's PHC-A3VF-4 three-bladed propellers on Models S35, V35, installed per Beech Kit Dwg. 35-9003. AFMS P/N 130555, dated February 6, 1967, is required. 3A15 42 Rev. 100 Specifications Pertinent to All Models (cont’d) 502. (28-volt system) B.F. Goodrich Electro Thermal Propeller Deicing System used in conjunction 7 lbs. (+22) with McCauley 2A36C23 two-blade propeller on Models F33A, F33C, (A36, A36TC (+12) V35B, A36, and McCauley 3A32C76 or Hartzell PHC-C3YF-1RF or & B36TC) McCauley 3A32C406 three-blade propeller on Models F33A, F33C, V35B, A36, A36TC, B36TC, per Beech Drawing 35-960080 or 36-960011. AFMS P/N 36-590002-29 dated April 1978 or later, is required for Models F33A, F33C, V35B, A36, A36TC. AFMS P/N 36-590006-9 dated January 1982 or later, is required for Model B36TC. 503. (28-volt system) McCauley Electro Thermal Propeller Deicing System in conjunction with 7 lbs. (+22) McCauley 3A32C406 three-blade propeller on Models F33A, V35B, (A36, B36TC) (+12) A36, B36TC, and McCauley D3A32C409 three-blade propeller on Model A36 and per Beech Drawing 36-960012. AFMS P/N 36-590002-29 dated April 1978 or later, is required for Models F33A, V35B, A36, prior to E-2111 except E-1946 and E-2104. POH and FAA Approved AFMS P/N 36-590006-9, dated January 1982 or later, is required for Model B36TC prior to EA-389 except EA-320; dated October 1983 or later, required for Model A36, E-1946, E-2104, E-2111 thru E-3635, except E-3630 and Model B36TC, EA-320, EA-389 and On. Miscellaneous (not listed above) 601. Stall warning indicator installation (a) Safe-Flight, Beech Dwg. 35-361025 or 58-361013 Negligible (b) Safe-Flight, Beech Dwg. 58-361013 Negligible 602. Heated pitot head installation (a) Beech Dwg. 35-361100 (H35 thru N35) 1 lb. (+74) (b) Beech Dwg. 33-361010 or 33-001022 (35-33, 35-A33) 1 lb. (+74) (c) Beech Dwg. 35-361159 (P35 thru V35A, V35B, 35-B33 thru E33, 1 lb. (+74) F33, G33, 35-C33A, E33A, F33A, E33C, 36, A36, G36, A36TC, B36TC) **603. Aileron trimmer control installati on per Aircraftsmen, Inc., 1 lb. (+73) Oklahoma City, OK, Dwg. ATC-35. Models 36 and A36 1 lb. (+63) 604. Optional seating per Beech Dwg. 95-534014, 95-534015, and 95-534016 17 lbs. (+135) (K35, M35). 605. Optional seating per Beech Dwg. 35-534401 (N35, P35) 17 lbs. (+135) 606. Zep Oxygen System per Beech Dwg. 35-001055-1 or -3 Use actual and (a) Beech Dwg. 414-001058-1 weight increase or (b) Beech Dwg. 414-001059-1 (H35, J 35, K35, M35, N35, P35, 35-33, 35-A33, 35-B33). 607. Optional seating per Beech Dwg.: (a) 35-534432 or 96-534051-5 or 35-001120 13 lbs. (+155) (5th seat, S35, V35, V35A, V35B (S/N D-9069 thru D-9861, F33A S/N CE-316 thru CE-633) (b) 96-534051-57 or 35-001120 13 lbs. ea. (+155) (5th and 6th seats, S35, V35, V35A, V35B S/N D-9069 thru Stowed D-9861, F33A S/N CE-316 thru CE-633) AFMS, P/N 35-590110-7 dated June 29, l964, or 35-390110-15 dated October 1975 or later required (S35 only) (c) 33-534033 18 lbs. (+144) (5th seat 35-C33, E33, E33C, F33, G33, F33A (S/N CE-290 thru CE-315), F33C, 35-C33A, E33A only) AFMS P/N 33-534033-9 dated March 9, 1965, or September 1977, or later, required for F33. Rev. 100 43 3A15 Specifications Pertinent to All Models (cont’d) Item 607 (cont’d) (d) 96-534051 14 lbs. (+155) 5th seat V35B S/N D-9862 and On F33A CE-634 and On 5th and 6th seats V35B S/N D-9862 and On F33A CE-634 and On 14 lbs. ea. (+155) 608. Oxygen system installation (a) 38 cu. ft. per Beech Dwg. Mod. C.O. B82616 (4 outlets, S35) or 27 lbs. (+78) 35-560000 (4, 5, or 6 outlets, S35, V35) (4 outlets 35-B33, 35-C33, 35-C33A) (b) 48 cu. ft. per Beech Dwg. Mod. C.O. B89386 (4 outlets, S35) or 33 lbs. (+77) 35-560000 (4, 5, or 6 outlets, S35, V 35, V35A, V35B, E33A, F33A, F33C), (4 outlets 35-B33, 35-C33, 35-C33A) (c) 49 cu. ft. per Beech Dwg. 35-560001 and 35-560010-39 25 lbs. (+77) (4, 5, or 6 outlets, V35, V35A, V 35B) (4 outlets), 35-C33, E33, F33, G33, 35-C33A, E33A , F33A, E33C, F33C) (d) 114 cu. ft. per Beech Dwg. 35-560001 and 35-560011-1 52 lbs. (+77) (4, 5, or 6 outlets, V35, V35A, V 35B) (4 outlets, 35-C33, E33, E33C, F33, G33, F33C, 35-C33A, E33A, F33A) (e) 38 cu. ft. per Beech Dwg. 35-560001 and 35-560010-1 27 lbs. (+78) (4, 5, or 6 outlets, V35, V35A, V 35B) (4 outlets, 35-C33, E33, F33, 35-C33A, E33A, F33A, E33C, F33C) (f) 49 cu. ft. per Beech Dwg. 36-560000 and 35-560010 25 lbs. (+77) 7 outlets and 4 or 5 masks (V35B, F33A) 609. Emergency static source installation Negligible weight (a) Beech Dwg. 35-324428. Eligible on Mode ls S35, V35, V35A, V35B, 35-C33, 35-C33A, E33, F33, G33, E33A, E33C, F33A, F33C, 36, A36, G36, A36TC, B36TC. AFMS 35-324428-13 dated January 4, 1965, or later, required (V35, 35-C33). AFMS 35-324428-13 dated January 4, 1965, or later, or POH and FAA Approved AFM dated October 1975, or later, required (S35). AFM 130709 dated March 17, 1967, or POH and FAA Approved AFM dated October 1977 or later, required (35-C33A). AFMS 35-324428-13 dated September 22, 1967, or POH and FAA Approved AFM dated September 1977 or later, required (Models E33, F33, V35A, and V35B, S/N D-9069 thru D-9390). (b) Beech Dwg. 35-5013, eligible on M odels 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, E33, E33A, E33C, F33, F33A, F33C, G33, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, and A36 aircraft. AFMS 35-324428-13 dated January 4, 1965, or later, required on all these models except F33A, G33, V35B, 36, and A36. 610. Landing gear safety system installation: 3 lbs. (+104) (a) Beech Dwg. 35-364170, AFMS 35-364170-5 dated January 29, 1965, or POH and FAA Approved AFMS 35-590110-13 dated September 1977, or later, required (Model S35 prior to D7882 and Model 35-C33 prior to CD-925). (b) Beech Dwg. 35-364170, eligible on Models S35 (D-7882 thru D-7976), V35, V35A, V35B, 35-C33 (CD-925 thru CD-1118), E33, E33A, F33, G33, 35-C33A, E33C, F33A, F33C, 36, A36, A36TC, and B36TC. AFMS 35-364170-5 dated June 8, 1965, or 35-590110-13 dated October 1975 or later, required for Model S35 (D-7882 thru D-7976). AFMS 35-364170-5 dated June 8, 1965, or POH and FAA Approved AFMS 35-590110-13 dated September 1977, or later, required for Models V35, V35A, 35-C33 (CD-925 thru CD-1118), E33 and F33. AFM 130710 dated March 17, 1967, required for 35-C33A. 3A15 44 Rev. 100 Specifications Pertinent to All Models (cont’d) Item 610 (cont’d) (b) AFMS 35-590027-9 dated January 29, 1971, or March 19, 1973, or 35-590110-13 dated October 1976 or later, required for Model G33. AFMS 35-364170-5 dated June 8, 1965, or 33-590027-9 dated March 19, 1973, or 35-590110-13 dated October 1976 or later, required for Model V35B S/N D-9069 and on. Current applicable FAA Approved Checklist or AFMS 33-590027-9 dated March 19, 1973, or 35-590110-13 dated November 1977, or later, required for Model F33A (S/N CE-290 and on), Model 36 (E-1 thru E-184), Model A36 (E-185 thru E-3635, except E-3630), Model A36TC (EA-1 and On), and Model F33C (CJ-26 and On). POH and FAA Approved AFMS 36-590006-7 dated January 1982 or later, required for Model B36TC. (c) Beech Dwg. 35-8001, AFMS 35-364170-5 dated June 8, 1965, required (Models H35 thru S35, 35-C33, and E33). (d) Beech Dwg. 35-8001, AFMS 130471 dated June 7, 1965, required (Models 35-33 thru 35-B33). (e) Beech Dwg. 35-8001, AFMS 130710 dated Marc h 17, 1967, required for Model 35-C33A. (f) Beech Dwg. 35-8001 (Model E33A). (g) Beech Dwg. 35-8001 (Model 36). 611. 24 v. Electrical system (eligible for Model 35-C33, CD-911 and On). Beech Dwg. Mod. C.O. B97393 and B98454A. 101. (h) Replaced by Dukes 4140-00-105 3 lbs. (+74) 301. (c) Replaced by 50 a. Delcotron 1100718 11 lbs. (+37) or (d) Replaced by Continental 631111 11 lbs. +37) 302. (d) Replaced by two 12 v. 24 a. hr. (Beech 118658) 46 lbs. (+45) 304. (b) Replaced by Delco Remy 9000591 1 lb. (+48) Vacuum pump - Beech 50-380090 5 lbs. (+41) Starter - Delco Remy 1108234 (Continental 627841) 16 lbs. (+39) Landing light - One General Electric 4596 1 lb. (+ 7) Heated pitot head - Beech Mod.C.O. B97393-13 1 lb. (+74) Anti-collision light, upper - Grimes D7080-3-24 2 lbs. (+182) 612. Electrically actuate d elevator trim system Negligible weight (a) Installed per Beech Dwg. 35-524669 or 35-3011 (Models V35A, V35B) 3 lbs. (+200) (b) Installed per Beech Dwg. 33-524022 (Models E33, E33A, E33C, F33, 3 lbs. (+164) G33, F33A prior to CE-316, F33C) (c) Installed per Beech Dwg. 36-524013 or 96-524031 (Model F33A, 3 lbs. (+200) CE-316 and On)s 613. Cabin seating (Model 36 series) (a) 5 th and 6th seats per Dwg. 36-530011-1 32 lbs. (+151) (b) 5 th seat (L.H.) per Dwg. 36-530011-3 16 lbs. (+151) (c) 6 th seat (R.H.) per Dwg. 36-530011-4 16 lbs. (+151) (d) Club seating per Dwg. 58-530061 3rd and 4th aft facing seats 40 lbs. (+106) 5th and 6th forward facing seats 32 lbs. (+155) (e) 5 th and 6th seats per Dwg. 58-530204 or 106-530025 30 lbs. (+151) (f) 5 th seat (L.H.) per Dwg. 58-530204 or 106-530025 15 lbs. (+151) (g) 6 th seat (R.H.) per Dwg. 58-530204 or 106-530025 15 lbs. (+151) (h) Club seating per Dwg. 58-530183 or 102-530100 3rd and 4th aft facing seats 50 lbs. (+106) 5th and 6th forward facing seats 30 lbs. (+155) E-1371 thru E-1593 except E-1422, E-1551, E-1569, and E-1581. EA-1 thru EA-32 except EA-21 and EA-28. (i) 5 th and 6th seats per Dwg. 58-530204 or 106-530025 32 lbs. (+155) (j) 5 th seat (L.H.) per Dwg. 58-530204 or 106-530025 16 lbs. (+155) (k) 6 th seat (R.H.) per Dwg. 58-530204 or 106-530025 16 lbs. (+155) E-1422, E-1551, E-1569, E-1581, E-1594 thru E-3635, except E-3630; EA-21, EA-28, and EA-33 and On Rev. 100 45 3A15 Specifications Pertinent to All Models (cont’d) Item 613 (cont’d) (l) 5 th seat (L.H.) per Dwg. 106-530057 16 lbs. (+155) (m) 6 th seat (R.H.) per Dwg. 106-530057 16 lbs. (+155) (n) 5 th and 6th seats per Dwg. 106-530057 32 lbs. (+155) (o) Club seating - per Dwg. 106-530061 3rd and 4th aft facing seats 53 lbs. (+106) 5th and 6th forward facing seats 34 lbs. (+155) (p) Vertical adjusting (co-pilot's seat ) per Dwg. 106-530060-15 (A36, 25 lbs. (+80) E-1946, E-2104, E-2111 thru E-3635, except E-3630. B36TC, EA-320, EA-389 and on, G36. 614. Oxygen system installation (M odels 36, A36, A36TC, B36TC) (a) 38 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 32 lbs. (+151) 36-560012-1 (Models 36 and A36) (b) 49 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 31 lbs. (+73) 36-560012-3 (Models 36 and A36) (c) 114 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 56 lbs. (+71) 36-560011-1 (Models 36 and A36) (d) 49 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 32 lbs. (+81) 36-560013 (Models A36 and A36TC) (e) 76.5 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 41 lbs. (+ 79) 36-560013 (Models A36 and A36TC) (f) 49 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 36-560000 and 31 lbs. (+79) 36-560013 (Models A36, A36TC, B36TC) (g) 76.5 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 36-560000 and 40 lbs. (+77) 36-560013 (Models A36, A36TC, B36TC) (h) 49 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560002 31 lbs. (+79) and 36-560016 (Models A36, B36TC) (i) 76.5 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560002 40 lbs. (+77) and 36-560016 (Models A36, B36TC) (j) 49 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560003 37 lbs. (+90) (Model B36TC) (k) 98 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560001 63 lbs. (+90) (Model B36TC) 615. Utility door installation per Beech Dwg. 36-400011 (Models 36, A36, G36, A36TC, B36TC). Models 36, A36, G36, A36TC, and B36TC approved for flight with both utility doors removed and cabin entrance door installed. Beech placard 36-530062 or 36-530109 required prior to E-1594 except E-1422, E-1551, E-1559, and E-1581 (Models 36, A36). Beech placard 36-530131 required E-1422, E-1551, E-1569, E-1581, E-1594, through E-3635, except E-3630 (Models A36, G36). Beech placard 36-530061 required prior to E-927 (Models 36, A36). Beech placard 36-324035 required E-927 thru E-3635, except E-3630 (Models A36, G36). POH and FAA Approved AFMS for Flight with Utility Doors Removed dated November 1979, or later, required for Model A36TC. POH and FAA Approved AFMS for Flight with Utility Doors Removed 36-590006-5 dated January 1982, or later, required for Model B36TC. Beech placard 36-324069 required for Models A36TC and B36TC. 616. L.H. and/or R.H. fuel cells (22 or 37 gal. each): Negligible weight installed per Beech Dwg. 35-9009. 3A15 46 Rev. 100 Specifications Pertinent to All Models (cont’d) 617. Area navigation equipment inst alled per applicable Beech Dwgs. (a) AFM for King KN-74 area navigation system dated August 23, 1971, or August 11, 1972, or October 1976 or later, required for Models V35B and G33. (b) AFM for King KN-74 area navigation system dated August 23, 1971, or AFMS dated August 11, 1972, or Oc tober 1976 or later, required for Models F33A, A36, and A36TC. (c) POH and FAA Approved AFMS for the Collins ANS-351 Area Navigation System dated November 23, 1977, or later, required for Model F33A, A36, V35B, and A36TC; dated January 1982, or later, required for Model B36TC. (d) POH and FAA Approved AFMS for the King KNS-80 Area Navigation System dated August 1978, or later, required for Models F33A, F33C, V35B, A36, and A36TC; dated January 1982, or later, required for Models B36TC. (e) POH and FAA Approved AFMS for the Bendix MCP-2040 Area Navigation System dated September 1979 or later, required for Models A36, A36TC, and F33A. (f) POH and FAA Approved AFMS for the Foster Air Data AD-511G Area Navigation System dated Marc h 1980 or later required for the Models A36, A36TC, and F33A. (g) POH and FAA Approved AFMS for the King KNS-81 Area Navigation System dated June 1980 or later required for Models A36, A36TC, and F33A; dated October 1980 or later, required for Model V35B; dated January 1982, or later, required for Model B36TC. 618. Standby generator power system per applicable Beech Dwg. (14-volt system) (a) AFMS for standby generator dated Apri l 4, 1972, or August 11, 1972, or March 19, 1973, or later, required for Models V35B and G33. (b) AFMS for standby generator dated Apri l 4, 1972, or August 11, 1972, or March 19, 1973, or later, required for Models F33A and A36. (c) Beech Dwg. 35-3012, AFMS P/N 35-590118-19, dated March 19, 1973, or later, required for all Model 35-33 and 33 series, H35 thru V35B inclusive, 36 and A36 airplanes. 619. Air conditioner (refrigeration type) 70 lbs. (+66) Model A36 70 lbs. (+58) (a) AFMS dated May 2, 1975, or later required for Models V35B, F33A, and A36 prior to E-2111 except E-1946 and E-2104. AFMS dated October 1983 or later required for Model A36, E-1946, E-2104, E-2111 thru E-3635, except E-3630. AFMS, dated April 1984 or later, required for Model B36TC, EA-440 and On. (b) See item 403 (bn) 70 lbs. (+58) 620. 28-volt standby generator power system installed per applicable Beech drawings (a) POH and FAA Approved AFMS dated Oc tober 1978, or later, required for Models F33A, F33C, V35B, and A36 prior to S/N E-2111 except E-1946 and E-2104; dated October 1983, or later, required for Model A36, S/N E-1946, E-2104, E-2111 thru E-3635, except E-3630. (b) POH and FAA Approved AFMS dated August 1979 or later, required for Model A36TC. POH and FAA Approved AFMS dated January 1982, or later, required for B36TC, EA-273 thru EA-388 except EA-320; dated October 1983 or later required for S/N EA-320, EA-389 and on. 621. Standby instrument air pressure sy stem per applicable Beech drawings. POH and FAA Approved AFMS dated April 1984, or later, required for Model A36 S/N E-2180 thru E-3635, except E-3630 and for Model B36TC S/N EA-435 and on; dated November 1984, or later, required for Model F33A S/N CE-1056 and on. 622. Structural modification per Beech Drawing 35-4016. 1 lb. (+245) Rev. 100 47 3A15 Specifications Pertinent to All Models (cont’d) 623. Loran Navigation Equipment installe d per applicable Beech drawings: FAA Approved AFMS for the Bendix/King KLN 88 Loran Navigation System dated October 1990, or later, required for the Models F33A, F33C, A36, and B36TC. 624. Reduced External Noise Option, fact ory installed per Beech Drawing 36-005003. The following items from Section XIII are changed for the reduced external noise option: Engine Limits For all operations 2550 rpm (290 hp) C.G. Range (landing (+80.4) to (+87.7) at 3600 lbs. gear extended) (+74.0) to (+87.7) at 3100 lbs. or less Straight line variation between points given. Maximum Weight 3600 lbs. Serial Nos. Eligible E-2581 thru E-3635, except E-3630 when properly equipped. Required Equipment Items 21(a), (b) and (c), 117(i) and (j), 201(k), 202(f), 205(f), 206(a), 309(e), or (f), 310(a), 312(a) or (b), 403(bj) and (bm), 601(a). NOTE 1. Current weight and bala nce report including list of equipment included in certificated basic empty weight and loading instructions, when necessary, must be provided for each aircraft at the time of original certification. The certificated basic empty weight and corresponding center of gravity locations must include system (undrainable) oil (not included in oil capacity) and unusable fuel (not included in usable fuel) as follows: System oil of 3 lbs. at +21; except Models 36, A36, G36, A36TC, and B36TC, 3 lb. at +11, with two standard wing fuel tanks unusable fuel of 36 lbs. at +79. With two optional wing fuel tanks (Item 111 or 113) unusable fuel of 36 lbs. at +79. Installation of auxiliary wing fuel tanks (Item 106) require inclusion of additional fuel of 5 lbs. at +94. NOTE 2. (a) The following placards must be displayed as indicated on all models except Models 35-C33A, E33A, E33C (Section XII aircraft), F33A and F33C (Section XIV aircraft), G33 (Section XV aircraft), A36 (Section XIII aircraft), V35B (Section XI aircraft), A36TC (Section XVI aircraft), B36TC (Section XVII aircraft). Placards required in FAA Approved AFM for Models G33 and F33A, CE-409 and On, Model A36, E-364 thru E-3635, except E-3630, Model V35B, D-9391 and On, A36TC, B36TC S/N EA-1 and On, G36 S/N E-3630, E-3636 and On, and in FAA Approved AFM and AFMS for Model F33C, S/N CJ-31 and On, must be displayed as noted therein. In full view of pilot: "Utility category airplane. Operate in accordance with FAA Approved AFM. Intentional spins prohibited. No acrobatic maneuvers approved except those listed in the AFM." D-4866 thru D-9068 and CD-1 thru CD-1234: The following placard not required on the above aircraft when both LH and RH fuel cells are installed per Item 616. "Turning type take-offs and take-off immediately following fast taxi turn prohibited. Avoid prolonged slips (20 seconds or more) with fuel tanks less than half full." To the pilot's left, at knee level, adjacent to the emergency static air valve control (when Item 609(a) is installed): In full view of the pilot: Prior to D-8612 and CD-1121: "WARNING - Emergency Airspeed Static Source. See Flight Manual Emergency Procedure for Airspeed Altimeter Calibration Error." 3A15 48 Rev. 100 NOTE 2. (cont’d) D-8612 and On, CD-1121 and On: "WARNING - Emergency Airspeed Static Source. See Pilot's Checklist or Flight Manual Emergency Procedures for airspeed and altimeter calibration error." On fuel selector valve cover or instrument panel in full view of pilot: (Except H35 and J35) "Do not take off if fuel quantity gages indicate in yellow band or with less than 13 gallons in each main tank." (b) The following placards must be displayed as indicated below or as indicated in optional POH and FAA Approved AFM or AFMS: Item 403(ax) or Item 403(ay), on Models 35-C33A, E33A, E33C (Section XII aircraft) or Item 403(az) or Item 403(ba) on Model F33A prior to CE-409, and Model F33C prior to CJ-31 (Section XIV aircraft). To the pilot's left at knee level, adjacent to the emergency static air valve control when Item 609(a) is installed: Prior to S/N CE-183: "WARNING - Emergency Airspeed Static Source. See Flight Manual Emergency Procedures for airspeed altimeter calibration error." CE-183 and On, and CJ-1 and On: "WARNING - Emergency Airspeed Static Source. See Pilot's Checklist or Flight Manual Emergency Procedures for airspeed and altimeter calibration error." On fuel selector valve: "Left hand tank 22 gal." "OFF" "Right hand tank 22 gal." (Standard System) "Left hand tank 37 gal." "OFF" "Right hand tank 37 gal." (Optional System) Above landing gear mechanical position indicator when winter baffles are installed: "NOTICE - Remove winter baffles when OAT exceeds 70  F." On top of front spar carry-through structure between front seats: "EMERGENCY LANDING GEAR INSTRUCTIONS TO EXTEND: Engage handle in rear of front seat and turn counterclockwise as far as possible (50 turns)." On left-hand subpanel: "Vent shutoff, pull to close" (Models 35-C33A, E33A, E33C) "Firewall air pull off" (Models F33A, F33C) On inner side of baggage compartment door: "Baggage Compartment LOAD IN ACCORDANCE WITH WEIGHT AND BALANCE DATA. Maximum structural capacity - 270 lbs." On inner side of baggage compartment door (when Item 607(c) is installed): "No smoking in fifth seat. Maximum fifth seat structural capacity: 170 lbs." On storm window: (Models 35-C33A, E33A, E33C only) "CAUTION - Do not open above 145 mph." Rev. 100 49 3A15 NOTE 2. (cont’d) In full view of pilot: Model 35-C33A, CE-1 thru CE-179 Model E33A, CE-180 thru CE-289 The following placard not required on the above aircraft when both LH and RH fuel cells are installed per Item 616: "Turning type takeoffs, and takeoff immediately following fast taxi turn prohibited. Avoid prolonged slips (20 seconds or more) with fuel tanks less than half full." Model E33C, CJ-1 thru CJ-25 Model F33C, CJ-26 thru CJ-30 "Turning type takeoffs, and takeoff immediately following fast taxi turn prohibited. Avoid prolonged slips (20 seconds or more) with fuel tanks less than half full." In full view of pilot: (Models 35-C33A, E33A, F33A) "UTILITY CATEGORY AIRPLANE. This airplane must be operated in compliance with the operating limitations stated in the form of placards, markings, and manuals. Maximum weight 3300 lbs. (Models 35-C33A, E33A) or 3400 lbs. (Model F33A). Refer to weight and balance data for loading instructions. Occupied seats must be in upright position during takeoff and landing. Altitude lost in stall recovery: 300 ft. Flight maneuver load factor: Flaps up 4.4g, flaps down 2.0g. No acrobatic maneuvers approved except those listed below: Maneuver Maximum Entry Speed Chandelles 152 mph (132 knots) Lazy eights 152 mph (132 knots) Steep turns 152 mph (132 knots) Stalls (except whip stalls) Slow deceleration NOTE: Intentional spins are prohibited. Airspeed Limitation Maximum landing gear extended speed 165 mph (143 knots) (Models 35-C33A, E33A prior to CE-249) Maximum landing gear extended speed 175 mph (152 knots) (Models E33A, CE-249 thru CE-289, and F33A) Maximum design maneuvering speed 152 mph (132 knots)" In full view of pilot: Model E33C, CJ-1 thru CJ-22. "This airplane must be operated in compliance with the operating limitations stated in the form of placards, markings and manuals. Refer to weight and balance data for loading instructions. Occupied seats must be in upright positions during takeoff and landing. Altitude lost during stall recovery: 300 ft. No acrobatic maneuvers approved except those listed below. (UTILITY AND ACROBATIC CATEGORY) UTILITY CATEGORY AIRPLANE Maximum weight 3300 lbs. flight maneuver load factor: Flaps up 4.4g; Flaps down 2.0g. Maneuver Maximum Entry Speed (CAS) Chandelles 152 mph (132 knots) Lazy eights 152 mph (132 knots) Steep turns 152 mph (132 knots) Stalls (except whip stalls) Slow deceleration NOTE: Intentional spins prohibited Airspeed Limitations (CAS) Maximum landing gear extended speed 175 mph (152 knots) Maximum design maneuver speed 152 mph (132 knots) 3A15 50 Rev. 100 NOTE 2. (cont’d) (ACROBATIC CATEGORY ONLY) ACROBATIC CATEGORY AIRPLANE Maximum Weight 2800 lbs. Flight Maneuver Load Factor: Flaps Up +6.0g, -3.0g Center of gravity between Sta. 78.5 and 81.0 Caution: INVERTED FLIGHT IS PROHIBITED. Negative G flight is limited to five seconds or less as required to perform approved maneuvers. See acrobatic supplement to owners' manual. ACROBATIC MANEUVERS WITH LANDING GEAR OR FLAPS EXTENDED ARE PROHIBITED. Acrobatic boost pump must be on to perform the following: Maneuver Maximum Entry Speed (CAS) Chandelles, lazy eights, Steep turns 165 mph (143 knots) Stalls and spins Slow deceleration Maneuver Recommended Entry Speed (CAS) Loop 190 mph (165 knots) Cuban 8 190 mph (165 knots) Immelmann 200 mph (174 knots) Barrel roll 150 mph (130 knots) Single snap roll 110 mph ( 95 knots) Vertical reversement 110 mph ( 95 knots) Split "S" 90 mph ( 78 knots) Airspeed Limitation (CAS) Maximum landing gear extension speed 175 mph (152 knots) Maximum design maneuver speed 165 mph (143 knots) SPIN ENTRY: Stall with power off, flaps up, nose 15 above horizon. With full up elevator, apply full rudder in the direction of desired spin immediately prior to stall. IF AIRPLANE SPIRALS OR AIRSPEED EXCEEDS 130 MPH IAS, INITIATE RECOVERY IMMEDIATELY. NOTE: Keep ailerons neutral in entry and during spin. SPIN RECOVERY: Simultaneously reverse rudder and elevator with ailerons neutral. Neutralize all controls as rotation stops." In full view of pilot: Model E33C, CJ-23 thru CJ-25; Model F33C, CJ-26 thru CJ-30. NOTE: CJ-1 thru CJ-22 eligible for slow roll upon rework to install Kit 35-9012 or 33-921014 connector, 33-921015-1 reservoir assembly, and 33-534088-1 placard which reads as follows: “This airplane must be operated in compliance with the operating limitations stated in the form of placards, markings, and manuals. Refer to weight and balance data for loading instructions. Occupied seats must be in upright position during takeoff and landing. Altitude lost during stall recovery: 300 ft. No acrobatic maneuvers approved except those listed below.” Rev. 100 51 3A15 NOTE 2. (cont’d) (UTILITY AND ACROBATIC CATEGORY) UTILITY CATEGORY AIRPLANE Maximum weight 3300 lbs. (Model E33C); 3400 lbs. (Model F33C) Flight maneuver load factor: Flaps up 4.4g; Flaps down 2.0g. Maneuver Maximum Entry Speed (CAS) Chandelles 152 mph (132 knots) Lazy eights 152 mph (132 knots) Steep turns 152 mph (132 knots) Stalls (except whip stalls) Slow deceleration NOTE: Intentional spins are prohibited. AIRSPEED LIMITATIONS (CAS) Maximum landing gear extended speed 175 mph (152 knots) Maximum design maneuver speed 152 mph (132 knots) (ACROBATIC CATEGORY ONLY) ACROBATIC CATEGORY AIRPLANE Maximum weight 2800 lbs. flight maneuver load factor: Flaps up +6.0g; -3.0g Center of gravity between Sta. 78.5 and 81.0 Caution: INVERTED FLIGHT IS PROHIBITED. Negative G flight is limited to five seconds or less as required to perform approved maneuvers. See acrobatic supplement to owner's manual. ACROBATIC MANEUVERS WITH LANDING GEAR OR FLAPS EXTENDED ARE PROHIBITED. Acrobatic boost pump must be on to perform the following: Maneuver Maximum Entry Speed (CAS) Chandelles, lazy eights, steep turns 165 mph (143 knots) Stalls and spins Slow deceleration Maneuver Recommended Entry Speed (CAS) Loop 190 mph (165 knots) Cuban 8 190 mph (165 knots) Immelmann 200 mph (174 knots) Slow roll 160 mph (139 knots) Barrel roll 150 mph (130 knots) Single snap roll 110 mph ( 95 knots) Vertical reversement 110 mph ( 95 knots) Split "S" 90 mph ( 78 knots) AIRSPEED LIMITATIONS (CAS) Maximum landing gear extension speed 175 mph (152 knots) Maximum design maneuver speed 165 mph (143 knots) SPIN ENTRY: Stall with power off, flaps up, nose 15 above horizon. With full up elevator, apply full rudder in the direction of desired spin immediately prior to stall. IF AIRPLANE SPIRALS OR AIRSPEED EXCEEDS 130 MPH IAS, INITIATE RECOVERY IMMEDIATELY. NOTE: Keep ailerons neutral in entry and during spin. SPIN RECOVERY: Simultaneously reverse rudder and elevator with ailerons neutral. Neutralize all controls as rotation stops." 3A15 52 Rev. 100 NOTE 2. (cont’d) In full view of pilot: Models E33C, F33C: "During acrobatic category operation, occupancy limited to pilot's or pilot's and co-pilot's seats" (Acrobatic Category). Below auxiliary fuel pump switch (Models 35-C33A, E33A, F33A): "Auxiliary fuel pump operation: Use high boost in case of loss of fuel pressure" (Utility and Acrobatic Category). "Use acrobatic boost during acrobatic maneuvers" (Acrobatic Category). "Alternate air - pull and release" (Utility and Acrobatic Category). Above inside cabin door handle: "Rotate handle to full locked position." On left-hand side panel near vent shutoff control (Models 35-C33A, E33A, E33C): "In case of engine fire pull vent shutoff control to close." On left-hand side panel near vent shutoff control (Models F33A, F33C): "In case of engine fire, pull fi rewall air control to close." On cabin door side panel (Models E33C, F33C): "Remove door hold open rod prior to operation in acrobatic category" (Acrobatic Category). "Emergency exit - Pull handle push out on door” (Acrobatic Category). On left-hand side of nose wheel well bulkhead below generator circuit breaker: "Generator circuit breaker, push to reset." On upholstery panel below left-hand middle window near emergency release handle when the folding fifth and sixth seats are installed: "Emergency exit - Pull pin - Push window out." On inner side of baggage compartment door: "Baggage, cargo or family seats, load in accordance with weight and balance data. Maximum structural capacity - 270 lb." (Model F33A, CE-316 and On) On fuel selector valve cover or instrument panel in full view of pilot: "Do not take off if fuel quantity gages indicate in yellow band or with less than 13 gallon in each main tank." (c) The following placards must be displayed as indicated on Models 36 and A36, prior to E-364: On fuel selector valve: "Left hand tank 25 gal." "OFF" "Right hand tank 25 gal." (Standard) "Left-hand tank 40 gal." "OFF" "Right hand tank 40 gal." (Optional) Above landing gear mechanical position indicator when winter baffles are installed: "NOTICE: Remove winter baffles when OAT exceeds 70F." On top of front spar carry-through structure between front seats: "EMERGENCY LANDING GEAR INSTRUCTIONS TO EXTEND: Engage handle in rear of front seat and turn counterclockwise as far as possible (50 turns)." On left-hand subpanel: "Vent shutoff, pull to close." (Model 36) "Firewall Air, pull-off" (Model A36) Rev. 100 53 3A15 NOTE 2. (cont’d) On inner side of forward cargo door: (This placard not required when placard noted ** is installed) "Baggage and Cargo Compartment." "LOAD IN ACCORDANCE WITH WEIGHT AND BALANCE DATA.: "Maximum structural capacity - 400 lbs." On storm window: (Model 36 only) "CAUTION - Do not open above 145 mph." In full view of pilot: Model 36, E-1 thru E-184 The following placard is not required on the above aircraft when both LH and RH fuel cells are installed, per Item 616. "Turning type takeoffs and take off immediately following fast taxi turns prohibited. Avoid prolonged slips (20 seconds or more) with fuel tanks less than half full." "Utility Category Airplane. This airplane must be operated in compliance with the operating limitations stated in the form of placards, markings and manuals. Maximum Weight: 3600 lbs. Refer to weight and balance data for loading instructions. Occupied seats must be in upright position during takeoff and landing. Altitude lost in stall recovery: 300 ft. Flight maneuver load factor: Flaps up 4.4g, Flaps down 3.0g. No acrobatic maneuvers approved except those listed below. Maneuver Maximum Entry Speed Chandelles 160 mph (139 knots) Lazy eights 160 mph (139 knots) Steep turns 160 mph (139 knots) Stalls (except whip stalls) Slow deceleration NOTE: Intentional spins prohibited. AIRSPEED LIMITATIONS Maximum landing gear extended speed 175 mph (152 knots) Maximum design maneuvering speed 160 mph (139 knots) Below auxiliary fuel pump switch: "AUXILIARY FUEL PUMP OPERATION - Takeoff and land with auxiliary fuel pump off except in case of loss of fuel pressure." "Alternate air - pull and release." Above inside cabin door and cargo door handles: "Rotate handle to full locked position." On left hand side panel near vent shut off control: (Model 36) "In case of engine fire, pull vent shut off control to close." On left hand side of nose wheel well bulkhead below generator circuit breaker: "Generator circuit breaker - Push to reset." On left hand side panel near firewall air control: (Model A36) "In case of engine fire, pull firewall air control to close." On baggage straps, aft side of front seat backs: "Baggage stowage - Maximum loading 50 lbs." To the pilot's left at knee level, adjacent to the emergency static air valve control (when emergency static source is installed): "WARNING - Emergency airspeed static source - See Pilot's Checklist or Flight Manual Emergency Procedures for airspeed and altimeter calibration error." 3A15 54 Rev. 100 NOTE 2. (cont’d) On instrument panel: "When utility doors are removed - Airspeed is not to exceed 190 mph (165 knots) CAS." On inner left-hand side of cabin: ** "Baggage and Cargo Compartment" "Load in accordance with weight and balance data" "Maximum structural capacity: 400 lbs." "When utility doors are removed, the following restrictions apply to cabin area: 1. No smoking 2. All loose objects must be secured. 3. Personnel not secured in seats by sa fety belts must wear parachutes." On fuel selector valve cover or instrument panel in full view of pilot: "Do not take off if fuel quantity gages indicate in yellow band or with less than 13 gal. in each main tank." Model G36, E3700, E3755 and On In full view of the pilot: “NO SMOKING” NOTE 3. Reserved. NOTE 4. Fuel filler opening may be ma rked in accordance with FAR 23.1557(c) with the word "fuel" and minimum grade, or CAR 3.757 with word "fuel," minimum octane rating, and usable quantity. NOTE 5. Models E33C, F33C, CJ-1 thru CJ-155, may be operated as 2 PCLM in the Acrobatic Category for those maneuvers listed in Item 403(ay), Item 403(ba), Item 403(as), and NOTE 2(b), when reworked per Beech kit drawing 33-4002. NOTE 6. Company name change effect ive 4/15/1996. The following serial numbers are manufactured under the name of Raytheon Aircraft Company: Model A36: E-3010 thru E-3635, except E-3630. Model B36TC: EA-587 and On. Model G36: E-3630, E-3636 thru E3768 (RAC). NOTE 7. Certified as part of Garmin STC SA01595SE and incorporated into the type design for Model G36. NOTE 8. Company name change effective 3/26/2007. The following serial numbers are manufactured under the name Hawker Beechcraft Corporation. Model G36: E-3769 thru E-3953, E-3955 thru E-3995. NOTE 9. Company name change effective 4/12/2013. The following serial numbers are manufactured under the name Beechcraft Corporation. Model G36, E-3996 thru E-4070. NOTE 10. Company name change effective 10/12/2016. The following serial numbers are manufactured under the name Textron Aviation Inc. Model G36, E-3954, E-4082, E-4089, E-4092, E-4093, E-4099 and On. Contact Textron Aviation as necessary to obtain availability information concerning the drawings and kits which are referenced by this publication. In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Sections I through XVII of this specification must also be displayed by permanent markings. --------- END -------- ``` ## ADs (84, first 50, in force first) - [AD 2024-14-03](https://openairdocs.org/ad/2024-14-03): Autopilot System · Garmin GFC 500 Autopilot (STC SA01866WI). Effective Aug 20, 2024 - [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023 - [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 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2019-23-10](https://openairdocs.org/ad/2019-23-10): Aileron Control System · Textron 35-C33, 35-C33A, 36 and 12 more. Effective Nov 22, 2019 - [AD 2018-06-11](https://openairdocs.org/ad/2018-06-11): Turbocharging · Continental TSIO-520-D engine (Standard Aero STC SA1035WE). Effective May 3, 2018 - [AD 2010-13-10](https://openairdocs.org/ad/2010-13-10): Propeller governors · American Champion 7GCAA, DA 40, A36 and 1 more. Effective Aug 5, 2010 - [AD 2009-25-01](https://openairdocs.org/ad/2009-25-01): Shoulder harnessess · Textron 58, 58A, 58P and 12 more. Effective Jan 8, 2010 - [AD 2009-15-01](https://openairdocs.org/ad/2009-15-01): Wire harness/connector(s) · Textron G36. Effective Jul 27, 2009 - [AD 2008-13-17](https://openairdocs.org/ad/2008-13-17): Circuit breaker toggle switches · Textron 58, 58P, 58TC and 14 more. Effective Aug 6, 2008 - [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008 - [AD 2008-02-06](https://openairdocs.org/ad/2008-02-06): GSM 85 servo gearbox units · Cessna 182T, 206H, LC40-550FG and 11 more. Effective Feb 26, 2008 - [AD 2007-08-08](https://openairdocs.org/ad/2007-08-08): Uplock roller · Textron 35, 35-33, 35-A33 and 49 more. Effective May 25, 2007 - [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006 - [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 94-20-04 R2](https://openairdocs.org/ad/94-20-04-R2): Empennage aft fuselage · Remove V tail and install a Beech Model F33A straight tail (D'Shannon Products STC SA2149CE). Effective Jun 27, 2003 - [AD 2003-01-01](https://openairdocs.org/ad/2003-01-01): Right hand fuselage panel assembly · Textron 36, 58, 58A and 3 more. Effective Feb 27, 2003 - [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001 - [AD 2001-23-10](https://openairdocs.org/ad/2001-23-10): Flap Flex Shaft Assemblies · Textron 35, 35-33, 35-A33 and 60 more. Effective Dec 13, 2001 - [AD 2001-11-03](https://openairdocs.org/ad/2001-11-03): Blower Motor Circuit · Textron 1900D, 58, 58A and 5 more. Effective Jul 20, 2001 - [AD 2001-10-09](https://openairdocs.org/ad/2001-10-09): Automatic Flight Control Systems · Aerostar PA-60-700P (Aerostar 700P), 208, 208B and 15 more. Effective Jun 15, 2001 - [AD 2001-08-08](https://openairdocs.org/ad/2001-08-08): V-band Exhaust Clamp · Modified Teledyne Continental engine equipped (STC SA5223NM or 2 others). Effective Jun 7, 2001 - [AD 2000-24-04](https://openairdocs.org/ad/2000-24-04): Rudder Control Cables · Textron 58, A36 and B36TC. Effective Jan 5, 2001 - [AD 2000-20-14](https://openairdocs.org/ad/2000-20-14): Firewall Sealant · Textron A36 and B36TC. Effective Nov 28, 2000 - [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 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000 - [AD 99-09-15](https://openairdocs.org/ad/99-09-15): Flight Control Mechanism · Textron 1900D, 58, 58A and 5 more. Effective May 18, 1999 - [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998 - [AD 97-16-10](https://openairdocs.org/ad/97-16-10): Filters · Cessna 310R, T310R, 36 and 17 more. Effective Sep 18, 1997 - [AD 97-14-15](https://openairdocs.org/ad/97-14-15): Cabin Side Door And Utility Door Handle · Textron 36, 50, 56TC and 41 more. Effective Sep 2, 1997 - [AD 97-06-11](https://openairdocs.org/ad/97-06-11): Ruddervator Differential Tail Control Rod Assy · Textron 35, 35R, A35 and 16 more. Effective May 16, 1997 - [AD 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996 - [AD 95-04-03](https://openairdocs.org/ad/95-04-03): Wing Spar · Textron 35-33, 35-A33, 35-B33 and 23 more. Effective Apr 7, 1995 - [AD 93-24-03](https://openairdocs.org/ad/93-24-03): Rudder Forward Spar · Textron 35-33, 35-A33, 35-B33 and 13 more. Effective Jan 21, 1994 - [AD 93-03-02](https://openairdocs.org/ad/93-03-02): Loran Receiver System · Textron 58, A36, B36TC and 1 more. Effective Mar 12, 1993 - [AD 92-18-11](https://openairdocs.org/ad/92-18-11): Landing Gear Circuit · Textron A36 and B36TC. Effective Oct 18, 1992 - [AD 92-17-01](https://openairdocs.org/ad/92-17-01): Fuel Metering Unit · Textron A36TC, S35, V35 and 2 more. Effective Sep 11, 1992 - [AD 91-17-01](https://openairdocs.org/ad/91-17-01): Elevator Trim Tab Actuators · Textron 35-33, 35-A33, 35-B33 and 40 more. Effective Nov 25, 1991 - [AD 91-20-08](https://openairdocs.org/ad/91-20-08): Fresh Air Blower Housing · Textron A36, A36TC, B36TC and 3 more. Effective Oct 31, 1991 - [AD 89-05-02](https://openairdocs.org/ad/89-05-02): Elevator Control Fittings · Textron 35, 35-33, 35-A33 and 42 more. Effective Mar 24, 1989 - [AD 88-21-02](https://openairdocs.org/ad/88-21-02): Seat Tracks · Textron 58, 58A, 58P and 13 more. Effective Oct 31, 1988 - [AD 88-20-01](https://openairdocs.org/ad/88-20-01): Firewall Material · Textron A36, B36TC and F33A. Effective Oct 19, 1988 - [AD 87-18-06 R1](https://openairdocs.org/ad/87-18-06-R1): Seat Recline Actuator Handle · Textron 58, 58A, 58P and 9 more. Effective Feb 5, 1988 - [AD 87-08-05](https://openairdocs.org/ad/87-08-05): Modify Fuel System · Textron A36TC. Effective May 14, 1987 - [AD 85-23-07](https://openairdocs.org/ad/85-23-07): Autopilot Systems · Aerostar PA-60-700P (Aerostar 700P), 172L, 172P and 37 more. Effective Jan 27, 1986 - [AD 84-08-04](https://openairdocs.org/ad/84-08-04): Oil Return Line Check Valve · Textron A36TC and B36TC. Effective Oct 15, 1984 - [AD 84-09-01](https://openairdocs.org/ad/84-09-01): Window Emergency Egress Provision · Textron 35, 36, 50 and 60 more. Effective May 25, 1984 - [AD 83-17-05](https://openairdocs.org/ad/83-17-05): Changes To AFM Maneuvers · Textron E33C and F33C. Effective Oct 1, 1983 - [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981 All 84: https://openairdocs.org/tcds/3A15/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Beech A36](https://openairdocs.org/model/beech-a36): 1,907 aircraft (registry code 1151604) - [Beech F33A](https://openairdocs.org/model/beech-f33a): 978 aircraft (registry code 1151425) - [Beech V35B](https://openairdocs.org/model/beech-v35b): 913 aircraft (registry code 1151548) - [Beech S35](https://openairdocs.org/model/beech-s35): 459 aircraft (registry code 1151532) - [Raytheon A36](https://openairdocs.org/model/raytheon-a36): 448 aircraft (registry codes 7150001, 7150000) - [Beech V35](https://openairdocs.org/model/beech-v35): 425 aircraft (registry code 1151538) - [Beech V35A](https://openairdocs.org/model/beech-v35a): 321 aircraft (registry codes 1151544, 1151542) - [Beech P35](https://openairdocs.org/model/beech-p35): 319 aircraft (registry code 1151530) - [Beech 35-B33](https://openairdocs.org/model/beech-35-b33): 291 aircraft (registry code 1151406) - [Beech K35](https://openairdocs.org/model/beech-k35): 237 aircraft (registry code 1151524) - [Beech B36TC](https://openairdocs.org/model/beech-b36tc): 225 aircraft (registry code 1151609) - [Beech M35](https://openairdocs.org/model/beech-m35): 225 aircraft (registry code 1151526) - [Beech H35](https://openairdocs.org/model/beech-h35): 224 aircraft (registry code 1151520) - [Beech J35](https://openairdocs.org/model/beech-j35): 221 aircraft (registry code 1151522) - [Beech 35-C33](https://openairdocs.org/model/beech-35-c33): 185 aircraft (registry code 1151408) - [Beech A36TC](https://openairdocs.org/model/beech-a36tc): 174 aircraft (registry codes 1151603, 1151613) - [Beech N35](https://openairdocs.org/model/beech-n35): 167 aircraft (registry code 1151528) - [Hawker Beechcraft G36](https://openairdocs.org/model/hawker-beechcraft-g36): 146 aircraft (registry code 4220009) - [Beech 35-33](https://openairdocs.org/model/beech-35-33): 130 aircraft (registry code 1151402) - [Beech 35-C33A](https://openairdocs.org/model/beech-35-c33a): 113 aircraft (registry code 1151410) - [Beech 36](https://openairdocs.org/model/beech-36): 111 aircraft (registry code 1151602) - [Raytheon G36](https://openairdocs.org/model/raytheon-g36): 97 aircraft (registry code 7150061) - [Beech 35-A33](https://openairdocs.org/model/beech-35-a33): 85 aircraft (registry code 1151404) - [Textron G36](https://openairdocs.org/model/textron-g36): 84 aircraft (registry code 4223554) - [Raytheon B36TC](https://openairdocs.org/model/raytheon-b36tc): 82 aircraft (registry codes 7150008, 7150065) - [Beech E33](https://openairdocs.org/model/beech-e33): 63 aircraft (registry code 1151422) - [Beechcraft G36](https://openairdocs.org/model/beechcraft-g36): 53 aircraft (registry code 4220034) - [Beech E33A](https://openairdocs.org/model/beech-e33a): 51 aircraft (registry code 1151424) - [Beech G33](https://openairdocs.org/model/beech-g33): 41 aircraft (registry code 1151435) - [Beech E33C](https://openairdocs.org/model/beech-e33c): 22 aircraft (registry code 1151432) - [Beech F33C](https://openairdocs.org/model/beech-f33c): 17 aircraft (registry code 1151434) - [Beech F33](https://openairdocs.org/model/beech-f33): 14 aircraft (registry code 1151423) - [Beech/Goedkerj L A36](https://openairdocs.org/model/beech-goedkerj-l-a36): 1 aircraft (registry code 1151612) - [Beechcraft BONANZA A36](https://openairdocs.org/model/beechcraft-bonanza-a36): 0 aircraft (registry code 4210110) - [Textron F33C](https://openairdocs.org/model/textron-f33c): 0 aircraft (registry code 1151440) ## STCs approved under this data sheet (999, 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 SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc. - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA01134DE](https://openairdocs.org/stc/SA01134DE): Installation of EarthX ETX680-24-TSO Lithium Battery. EarthX Inc. - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA04505CH](https://openairdocs.org/stc/SA04505CH): Installation of Hartzell Propeller model HC-C3YF-1N/NM8410-4 or HC-C3YF-1N/NM8410K-4. Hartzell Propeller Inc. - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [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 SA12416IB](https://openairdocs.org/stc/SA12416IB): Installation of Main wheel, Nose wheel, brake assembly, axle, master cylinder and brake lines. BERINGER AERO - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA01121DE](https://openairdocs.org/stc/SA01121DE): Installation of the Trig Avionics TT23 Transponder as a replacement for the existing Transponder.. Peregrine - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA02363CH](https://openairdocs.org/stc/SA02363CH): Installation of Chuck Ney Enterprises, Inc. CNE IO-470-C/N-MOD Model Engine (STC SE02261CH). Cygnet Aerospace Corp. - [STC SA4103WE](https://openairdocs.org/stc/SA4103WE): Installation of a replacement flexible fuel cell in the wing of the Beech 33, 35, 36. aircraft. Aerosport Fuel Cells, LLC - [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc. - [STC SA01091WI](https://openairdocs.org/stc/SA01091WI): Increase of gross weight by 100 lbs. D'Shannon Products, Ltd - [STC SA01152CH](https://openairdocs.org/stc/SA01152CH): Installation of stainless steel passenger step, P/N 002-430076-23, with South Seas Ventures, Inc. drawing as listed on AML No. SA01152CH, or later FAA approved revision.. McFarlane Aviation LLC - [STC SA12182IB](https://openairdocs.org/stc/SA12182IB): Installation of the MT-Propeller Entwicklung GmbH model MTV-9-D/200-52() propeller. MT-Propeller Entwicklung GmbH - [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [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 SA228CH](https://openairdocs.org/stc/SA228CH): Installation of Model TCAS 791 TCAS I.. Acron Aviation Inc. - [STC SA306CH](https://openairdocs.org/stc/SA306CH): Installation of a Sextant VSI TCAS display.. Acron Aviation Inc. - [STC SA00037WI](https://openairdocs.org/stc/SA00037WI): Installation of B & C Specialty Products BC100-1 battery.. B & C Specialty Products Inc - [STC SA01240SE](https://openairdocs.org/stc/SA01240SE): Installation of secondary voltage indication system. Visual Instruments LLC - [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA01120SE](https://openairdocs.org/stc/SA01120SE): Installation of Door Steward.. Mountain View Aviation LLC - [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation - [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 SA01708WI](https://openairdocs.org/stc/SA01708WI): Installation of third lap belt restraint in the center of the main cabin rear bench seat. MN Engineering LLC - [STC SA00423SE](https://openairdocs.org/stc/SA00423SE): Installation of stainless steel battery box.. CheckSix AeroSolutions, LLC - [STC SA384WE](https://openairdocs.org/stc/SA384WE): Installation of adjustable pilot and co-pilot seat. CheckSix AeroSolutions LLC - [STC SA507WE](https://openairdocs.org/stc/SA507WE): Installed adjustable back rest. CheckSix AeroSolutions, LLC - [STC SA5902NM](https://openairdocs.org/stc/SA5902NM): Installation of locking fuel cap assembly. CheckSix AeroSolutions, LLC - [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [STC SA2754CE](https://openairdocs.org/stc/SA2754CE): Installation of a flap actuated landing gear warning system.. Walter Timothy Miller - [STC SA02024WI](https://openairdocs.org/stc/SA02024WI): Installation of the Aft Auxiliary Heating System (AAHS). Peregrine - [STC SA1252WE](https://openairdocs.org/stc/SA1252WE): Installation of Rajay turbocharged Continental - Teledyne O-470-G-C1 and/or IO-470C, -J, -K, -N engines.. TALCO Aviation - [STC SA2556WE](https://openairdocs.org/stc/SA2556WE): Installation of Rajay turbosupercharged Continental TSIO-520-D engine.. TALCO Aviation - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA00245SE](https://openairdocs.org/stc/SA00245SE): Installation of the Aviation Research Systems, Inc., Locking Fuel Caps. CheckSix AeroSolutions, LLC - [STC SA1722WE](https://openairdocs.org/stc/SA1722WE): Installation of Fiberglass tail fairing.. CheckSix AeroSolutions, LLC All 999: https://openairdocs.org/tcds/3A15/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.