FEDERAL AVIATION ADMINISTRATION
U.S. DEPARTMENT OF TRANSPORTATION
						3A15  
			Beech Aircraft Corporation
					Revision 85

	Models: 35-33, 35-A33, 35-B33, 35-C33, 
	E33, and F33, 35-C33A, E33A and E33C, 
	F33A and F33C, G33, H35, J35, K35 and 
	M35, N35, P35, S35, V35, V35A and 
	V35B, 36 and A36, A36TC, B36TC
										January 15, 1994

AIRCRAFT SPECIFICATION NO. 3A15

Manufacturer:			Beech Aircraft Corporation
				Wichita, Kansas 67201

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)

*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 Extended)
(+82.1) to (+84.7) at 2900 lb.
(+77.6) to (+85.7) at 2525 lb.
(+77.0) to (+85.7) at 2475 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
2900 lb.

No. Seats
4 (2 at +85, 2 at +118)

Maximum Baggage
270 lb. (+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 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 deg.
Aileron tab					Fixed
Aileron  						Up 20 deg.	Down 20 deg.
Elevator tab  					Up 4.5 deg.   	Down 23 deg.
"V" tail elevator action  				Up 22.5 deg.	Down 17.5 deg.
"V" tail rudder action  				Up 21 deg.   	Down 21 deg.
"V" tail max. combination rudder elevator action 	Up 35 deg.	Down 30 deg. 

Serial Nos. Eligible
D-4866 through 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.

II.   Model J35, Bonanza, 4 PCLM (Utility 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 (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 Extended)
(+82.1) to (+84.7) at 2900 lb.
(+77.6) to (+85.7) at 2525 lb.
(+77.0) to (+85.7) at 2475 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
2900 lb.

No. Seats
4 (2 at +85, 2 at +118)

Maximum Baggage
270 lb. (+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 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 deg.
Aileron tab 						Fixed
Aileron  							Up 20 deg.	Down 20 deg.
Elevator tab  						Up 4.5 deg.	Down 23 deg.
"V" tail elevator action  					Up 22.5 deg.	Down 17.5 deg.
"V" tail rudder action  					Up 21 deg.	Down 21 deg.
"V" tail max. combination rudder elevator action		Up 35 deg.	Down 30 deg.

Serial Nos. Eligible
D-5062, D-5331 through 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. 

III.   	Model K35, Bonanza, 4 or 5 PCLM (Utility Category), Approved October 29, 1958.
	Model M35, Bonanza, 4 or 5 PCLM (Utility 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 (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 Extended)
(+82.1) to (+84.7) at 2950 lb.
(+77.5) to (+85.7) at 2525 lb.
(+77.0) to (+85.7) at 2475 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
2950 lb.

No. 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 lb. (+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 lb. (+135)
  On and forward of spar cover  		200 lb. (+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 oil

Control Surface Movements
Wing flaps  					Down 30 deg.
Aileron tab  					Fixed
Aileron  						Up 20 deg.	Down 20 deg.
Elevator tab  					Up 4.5 deg.	Down 23 deg.
"V" tail elevator action 				Up 22.5 deg.	Down 19 deg.
"V" tail rudder action				L.H. Up 23 deg.	L.H. Down 26 deg.
						R.H. Up 26 deg.	R.H. Down 23 deg.
"V" tail max. combination rudder elevator action	L.H. Up 44 deg.	L.H. Down 37 deg. 
						R.H. Up 42 deg.	R.H. Down 40 deg.

Serial Nos. Eligible
Model K35:   D-5726 through D-6161
Model M35:   D-6162 through 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.

IV.   Model 35-33, Debonair, 4 PCLM (Utility 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 Extended)
(+82.1) to (+85.7) at 2900 lb.
(+78.0) to (+86.6) at 2550 lb.
(+78.0) to (+86.7) at 2525 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
2900 lb.

No. Seats
4 (2 at +85, 2 at +118)

Maximum Weight
270 lb. (+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 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 deg.
Aileron tab				Fixed
Aileron  					Up 20 deg.	Down 20 deg.
Rudder tab  				Fixed
Rudder  					Left 25 deg.	Right 25 deg.
Elevator tab  				Up 10 deg.	Down 21 deg.
Elevator  				Up 25 deg.	Down 15 deg.

Serial Nos. Eligible
CD-1 through CD-224, CD-233, CD-234, CD-236, CD-241, CD-246 through 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).

V.   Model N35, Bonanza, 4 or 5 PCLM (Utility 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 Gear Extended)
(+82.1) to (+85.7) at 3125 lb.
(+77.0) to (+85.7) at 2800 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3125 lb.

No. 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 lb. (+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 lb. (+135)
  On and forward of spar cover	200 lb. (+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 deg. 
Aileron tab  						Fixed
Aileron  							Up 20 deg.	Down 20 deg. 
Elevator tab  						Up 5.5 deg.	Down 23 deg.
"V" tail elevator action 	 				Up 22.5 deg.	Down 19 deg.
"V" tail rudder action					L.H. Up 23 deg.	L.H. Down 26 deg.
							R.H. Up 26 deg.	R.H. Down 23 deg.
"V" tail maximum combination rudder elevator action	L.H.	Up 44 deg.	L.H. Down 37 deg.
							R.H. Up 42 deg.	R.H. Down 40 deg.

Serial Nos. Eligible
D-6562 through D-6841

Required Equipment
Items 6(a) and (b) or 9(a) and (b) and (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.

VI.   Model 35-A33, 4 PCLM (Utility Category), Approved November 3, 1960

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				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 Gear Extended)
(+82.1) to (+86.7) at 3000 lb.
(+77.0) to (+86.7) at 2500 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3000 lb.

No. Seats
4 (2 at +85, 2 at +118)

Maximum Baggage
270 lb. (+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 106)

Wing aux. System   20                	719               + 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 deg.
Aileron tab 				Fixed
Aileron  					Up 20 deg.	Down 20 deg.
Rudder tab  				Fixed
Rudder  					Left 25 deg.	Right 25 deg.
Elevator tab  				Up 10 deg.	Down 21 deg.
Elevator  				Up 25 deg.	Down 15 deg.

Serial Nos. Eligible
CD-225 through CD-232, CD-235, CD-237 through CD-240, CD-242 through CD-245, CD-251 through 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 two 22 gal. main fuel cells are installed per Item 616), 601(a).

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 Gear Extended)
(+82.1) to (+86.7) at 3000 lb.
(+77.0) to (+86.7) at 2500 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3000 lb.

No. Seats
4 (2 at +85, 2 at +118)

Maximum Baggage
270 lb. (+140)
For weight and balance information, 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 deg.
Aileron tab 					Fixed
Aileron  						Up 20 deg.	Down 20 deg.
Rudder tab  					Fixed
Rudder  						Left 25 deg.	Right 25 deg.
Elevator tab  					Up 10 deg.	Down 21 deg.
Elevator  					Up 25 deg.	Down 15 deg.

Serial Nos. Eligible
CD-388 through 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 616), 601(a).

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 (TIAS)
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 Gear Extended)
(+82.1) to (+85.7) at 3125 lb.
(+77.0) to (+85.7) at 2800 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3125 lb.

No. 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 lb. (+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 lb. (+135)
  On and forward of spar cover  		200 lb. (+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                	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 deg.
Aileron tab  						Fixed
Aileron  							Up 20 deg.	Down 20 deg.
Elevator tab 						Up 5.5 deg.	Down 23 deg.
"V" tail elevator action  					Up 22.5 deg.	Down 19 deg.
"V" tail rudder action					L.H. Up 23 deg.	L.H. Down 26 deg.
							R.H. Up 26 deg.	R.H. Down 23 deg.
"V" tail maximum combination rudder elevator action	L.H.	Up 44 deg.	L.H. Down 37 deg.
							R.H. Up 42 deg.	R.H. Down 40 deg.

Serial Nos. Eligible
D-6842 through D-7309, except D-7140

Required Equipment
Items 6(a) and (b) or 9(a) and (b) and (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. 

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 Gear Extended)
(+82.1) to (+84.7) at 3300 lb.
(+79.0) to (+85.7) at 3000 lb.
(+77.0) to (+85.7) at 2800 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3300 lb.

No. 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 lb. (+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 lb. (+145)
  On and forward of spar cover		200 lb. (+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 deg.
Aileron tab  						Fixed
Aileron  							Up 20 deg.	Down 20 deg.
Elevator tab  						Up 5.5 deg.	Down 23 deg.
"V" tail elevator action  					Up 22.5 deg.	Down 19 deg.
"V" tail rudder action					L.H. Up 23 deg.	L.H. Down 26 deg.
							R.H. Up 26 deg.	R.H. Down 23 deg.
"V" tail maximum combination rudder elevator action	L.H.	Up 44 deg.	L.H. Down 37 deg.
							R.H. Up 35 deg.	R.H. Down 40 deg.

Serial Nos. Eligible
D-7140, D-7310 through 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. 

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 (Utility 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 mph (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) through 
   S/N CD-1118 and CD-1119 
   through CD-1199)  			130 mph (113 knots)
  S/N CD-1200 and up  			140 mph (122 knots)
Landing gear extended (normal)  		165 mph (143 knots)
  S/N CD-1200 and up  			175 mph (152 knots)

*C.G. Range (Landing Gear Extended)
(+81.5) to (+86.7) at 3050 lb.
(+77.0) to (+86.7) at 2700 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3050 lb.

No. Seats
4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +121, 1 at +142)

Maximum Baggage
270 lb. (+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 deg.
Aileron tab  				Fixed
Aileron  					Up 20 deg.	Down 20 deg.
Rudder tab  				Fixed
Rudder  					Left 25 deg.	Right 25 deg.
Elevator tab  				Up 10 deg.	Down 21 deg.
Elevator  				Up 25 deg.	Down 15 deg.

Serial Nos. Eligible
Model 35-C55:   CD-814 through CD-1118 (except CD-982)
Model E33:   CD-1119 through CD-1234
Model F33:   CD-1235 through CD-1254

Required Equipment
(See Item 611 for replacements & additions with operational 24 v. system)

Model 35-C33:
	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) or 13(a) and (b) and (c) or 14(a) and (b) and 11(b), 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) 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 (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 installed per item 616), 601(a).

Model E33:
	Items 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 through CD-1199), (v) (S/N CD-1200 through CD-1234), 403(ac) (when two 22 or 37 gal. main fuel cells are installed per Item 616), 601(a). 

Model F33:
	Items 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 (Utility 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-520-B or IO-520-BA; IO-520-BB (D-10179 and up) See Item 114, 116, or 120 for optional engine

*Fuel
Aviation gasoline Grade 100LL or 100 minimum

*Engine Limits
(For all airplanes prior to D-10313 and airplanes D-10313 and after equipped with Item 14(a) or 18(a))
  For all operations 			2700 rpm (285 hp)

(For airplanes D-10313 and after 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)
(S/N D-10179 and up)
Flaps extended (normal)          		130 mph   	(113 knots)
(S/N D-8872 and up)              		140 mph   	(122 knots)   	(123 knots)
Landing gear extended (normal)   		165 mph   	(143 knots)
(S/N D-8872 and up)              		175 mph   	(152 knots)   	(154 knots)

*C.G. Range (Landing Gear Extended)
(+82.1) to (+84.4) at 3400 lb.
(+78.0) to (+85.7) at 3000 lb.
(+77.0) to (+85.7) at 2900 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3400 lb.

No. 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 lb (+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 lb. (+145)
  On and forward of spar cover  		200 lb. (+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 after)

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 deg.		Down 30 deg.
Aileron tab  						Fixed
Aileron 	 						Up 20 deg.	Down 20 deg.
Elevator tab  						Up 5.5 deg.	Down 23 deg.
"V" tail elevator action  					Up 22.5 deg.	Down 19 deg.
"V" tail rudder action					L.H. Up 23 deg.	L.H. Down 26 deg.
  							R.H. Up 26 deg.	R.H. Down 23 deg.
"V" tail maximum combination rudder elevator action	L.H.	Up 44 deg.	L.H. Down 37 deg.
							R.H. Up 35 deg.  	R.H. Down 40 deg.

Serial Nos. Eligible
Model V35:   D-7977 through D-8598
Model V35A:   D-8599 through D-9068
Model V35B:   D-9069 and up

Required Equipment

D-7977 through 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 through D-9947), 403(bb), (S/N D-9948 through D-10119 except D-10097), 601(a), 622.

D-10097, D-10120 and after (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.

XII.   	Model 35-C33A, Debonair, 4 or 5 PCLM (Utility Category), Approved January 20, 1966
  	Model E33A, Bonanza, 4 or 5 PCLM (Utility Category), Approved October 10, 1967
  	Model E33C, Bonanza, 4 or 5 PCLM (Utility Category), Approved September 9, 1968
  	Model E33C, Bonanza, 2 PCLM (Acrobatic 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 (CAS)
Utility Category (35-C33A, E33A, E33C)
  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)
    (S/N CE-249 and up & CJ-14 & up)	140 mph (122 knots)
  Landing gear extended (normal)
    (35-C33, E33A)  			165 mph (143 knots)
    (E33A S/N CE-249 & up, E33C)		175 mph (152 knots)

Acrobatic Category 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 & up)  			140 mph (122 knots)
  Landing gear extended (normal)  		175 mph (152 knots)

*C.G. Range (Landing Gear Extended)
Utility Category
  (+82.1) to (+86.7) at 3300 lb.
  (+77.0) to (+86.8) at 2800 lb.
  Straight line variation between points given

Acrobatic Category
  (+78.5) to (+81.0) at 2800 lb.

Empty Weight C.G. Range
None

*Maximum Weight
Utility Category:   		3300 lb.
Acrobatic Category:   		2800 lb.

No. 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 lb. (+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
12 qt. (+25)
See NOTE 1 for data on system oil

Control Surface Movements
Wing flaps  					Down 30 deg.
Aileron tab  					Fixed
Aileron  						Up 20 deg.	Down 20 deg.
Rudder tab  					Fixed
Rudder  						Left 25 deg.	Right 25 deg.
Rudder (E33C in acrobatic category)  		Left 25 deg.	Right 20 deg.
Elevator tab  					Up 10 deg.	Down 27 deg.
Elevator  					Up 25 deg.	Down 15 deg.

Serial Nos. Eligible
Model 35-C33A:   CE-1 through CE-179
Model E33A:   CE-180 through CE-289
Model E33C:   CJ-1 through 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:
	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(e) or (f) or (h), 304(d) or (f) or (g) or (h), 601(a).

Model E33C:
	Items 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 (Utility Category), Approved May 1, 1968 Model A36, Bonanza, 4 to 6 PCLM (Utility Category), Approved October 24, 1969 (See Item 624 for reduced exterior noise configuration)

Engine
S/N E-1 through E-1370 
	Continental IO-520-B or IO-520-BA. See Item 120 for optional engine
S/N E-1371 through E-2110 except E-1946 and E-2104
	Continental IO-520-BB
S/N E-1946, E-2104, E-2111 and after
	Continental IO-550-B

*Fuel
Aviation gasoline Grade 100LL or 100 minimum

*Engine Limits
(For S/N E-1 through E-1608 and E-1609 through 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 S/N E-1609 through 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 S/N E-1946, E-2104, E-2111 and after)
	For all operations  		2700 rpm (300 hp)

*Airspeed Limits
S/N E-1 through 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)

(S/N E-1371 through E-2110 except E-1946 and E-2104)
Flaps extended (15 deg.)             		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)

S/N E-1946, E-2104, E-2111 and after
Maneuvering                      		160 mph   	(139 knots)   	(140 knots)
Maximum structural cruising      		190 mph   	(165 knots)   	(166 knots)
Never exceed                     			234 mph   	(203 knots)   	(205 knots)
Flaps extended (12 deg.)             		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 Gear Extended)
(+81.0) to (+87.7) at 3600 lb. S/N E-1 through E-2110 except E-1946 and E-2104
(+81.0) to (+87.7) at 3650 lb. S/N E-1946, E-2104, E-2111 and after
(+74.0) to (+87.7) at 3100 lb. or less
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
3600 lb. S/N E-1 through E-2110 except E-1946 and E-2104
3650 lb. S/N E-1946, E-2104, E-2111 and after

No. Seats
S/N E-1 through 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)

S/N E-1371 and after
	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 (Structural Limits)
S/N E-1 through E-1370				400 lb. (+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 lb. (+145)
	On and forward of spar cover 		200 lb. (+108)

S/N E-1371 and after
	Rear compartment (aft to Sta. 170)		400 lb. (+145)
	On and forward of rear spar cover with 
	 center seats removed  			200 lb. (+108)
	Aft of rear spar cover to Sta. 170 with 
	 third, fourth, fifth and sixth seats removed 	400 lb. (+145)
	Aft baggage compartment 
	 (Sta. 170 to Sta. 190)  			70 lb. (+180)

Fuel Capacity

Tank         Capacity Gal.     Usable Gal.      Arm

(S/N  E-1  through  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

(S/N E-1594 and after)

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 (S/N E-1 through E-1370)				Down 30.
Wing flaps (S/N E-1371 through E-2110, 
  except E-1946 and E-2104)				Approach15 deg.		Down 30.
Wing flaps (S/N E-1946, E-2104, 
  E-2111 and after					Approach 12 deg.   	Down 30.
Right aileron tab  						Fixed
Left aileron tab (S/N E-1 through E-2110, 
  except E-1946 and E-2104)  					Fixed
Left aileron tab (S/N E-1946, E-2104, 
  E-2111 and after) 						Up 9 deg.	Down 9 deg.
Aileron  								Up 20 deg.	Down 20 deg.
Rudder tab  							Fixed
Rudder (E-1 through E-2110 except E-1946 and E-2104)  		Left 25 deg.	Right 25 deg.
Rudder (S/N E-1946, E-2104, E-2111 and after)			Left 23 deg.	Right 23 deg.
Elevator tab (S/N E-1 through E-2110 except E-1946 and E-2104)  	Up 10 deg.	Down 27 deg.
Right elevator tab (S/N E-1946, E-2104, E-2111 and after)  		Up 10 deg.	Down 25 deg.
Left elevator tab (S/N E-1946, E-2104, E-2111 and after)  		Up 8 deg.	Down 27 deg.
Elevator (S/N E-1 through E-2110 except E-1946 and E-2104)  	Up 23 deg.	Down 20 deg.
Elevator (S/N E-1946, E-2104, E-2111 and after)  			Up 25 deg.	Down 20 deg.

Serial Nos. Eligible
Model 36:   E-1 through E-184
Model A36:   E-185 and after

Required Equipment
S/N E-1 through 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 through E-363 except E-357, E-358, and E-361), 403(ag) (A36 S/N E-357, E-358, E-361 and E-364 through E-926), 403(aq) or 403(bc) (A36 S/N E-927 through E-1240 except E-1111) and 601(a).

S/N E-1111, E-1241 and after (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), S/N E-1111, E-1241 through E-2110 except E-1946 and E-2104, or 20(a) and (b) and 11(e) or (g) S/N E-1946, E-2104, E-2111 and after, 102(c) or (d), 103, 117(a) and (c) prior to S/N E-1371, 117(a) and (d) S/N E-1371 through E-2110 except E-1946 and E-2104, 117(i) and (j) S/N E-1946, E-2104, E-2111 through E-2419, 117(k) and (j) S/N E-2420 through E-2749, 117(l) and (j) S/N E-2750, and after, 201(k), 202(f), 205(f), 206(a), 309(a) or (b) or (c) or (d) prior to S/N E-2111 except E-1946 and E-2104, 309(e) or (f) S/N E-1946, E-2104, E-2111 and after, 310(a), 312(a) or (b), 403(bc) prior to S/N E-2111 except E-1946 and E-2104, 403(bj) S/N E-1946, E-2104, E-2111 and after, 601(a).

XIV.   Model F33A, Bonanza, 4 or 5 PCLM (Utility Category), approved October 24, 1969
	Model F33C, Bonanza, 4 or 5 PCLM (Utility Category), approved October 24, 1969
	Model F33C, Bonanza, 2 PCLM (Acrobatic Category), approved October 24, 1969 See NOTE 5 for eligibility in Acrobatic Category

Engine
Continental IO-520-B or IO-520-BA; IO-520-BB (CE-816 and up, CJ-149 and up)
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 after and CJ-156 and after equipped with Item 14(a) or 18(a))
  For all operations  			2700 rpm (285 hp)

(For airplanes CE-891 and after and CJ-156 and after equipped with Item 11(a))
Takeoff and continuous power  		2700 rpm (285 hp)
Normal operating power  			2550 rpm (275 hp)

*Airspeed Limits
Utility Category (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)
(S/N's CE-816 and after)
(S/N's CJ-150 and after)
Flaps extended (normal)          		140 mph   	(122 knots)   	(123 knots)
Landing gear extended (normal)   		175 mph   	(152 knots)   	(154 knots)

Acrobatic Category (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)
(S/N's CJ-150 and after)
Flaps extended (normal)          		140 mph   	(122 knots)   	(123 knots)
Landing gear extended (normal)   		175 mph   	(152 knots)   	(154 knots)

*C.G. Range (Landing Gear Extended)
Utility Category:
  (+82.1) to (+86.7) at 3400 lb.
  (+77.0) to (+87.7) at 2800 lb.
  Straight line variation between points given

Acrobatic Category:
  (+78.5) to (+81.0) at 2800 lb.

Empty Weight C.G. Range
None

*Maximum Weight
Utility Category:   		3400 lb. (F33A, F33C)
Acrobatic Category:   		2800 lb. (F33C)

No. Seats
S/N CE-290 through CE-315, CJ-26 and up:
	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).

S/N 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(a) is installed or 6 (2 at +85, 2 at +121, 2 at +154) when Item 607(b) is installed

Maximum Baggage
270 lb. (+140)
270 lb. (+150) (S/N CE-316 and up)
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 after and CJ-156 and after)

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 deg.	Down 30 deg.
Aileron tab					Fixed
Aileron  						Up 20 deg.	Down 20 deg.
Rudder tab  					Fixed
Rudder  						Left 25 deg.	Right 25 deg.
Rudder (F33C in acrobatic category) 		Left 25 deg.	Right 20 deg.
Elevator tab  					Up 10 deg.	Down 27 deg.
Elevator  					Up 25 deg.	Down 15 deg.

Serial Nos. Eligible
Model F33A:   CE-290 and up
Model F33C:   CJ-26 and up

Required Equipment
Model F33A:   CE-290 through 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) or 403(ah) or 403(az) S/N CE-290 through CE-400 except CE-394 and CE-395, 403(ah) or 403(az) S/N CE-394, CE-395, CE-401 and CE-673, 403(ar) or 403(bd) (S/N CE-674 through CE-771 except CE-748), and 601(a).

Model F33A:   CE-748, CE-772 and after (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 up, 201(k), 202(f), 205(f), 206(a), 309(a) or (b) or (c) or (d), 310(a), 312(a) or (b), 403(bd), and 601(a). 

Model F33C:   CJ-26 through 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) or 403(ah) or 403(az) S/N CJ-26 through CJ-30, 403(ah) or 403(az) S/N CJ-31 through CJ-128, 403(ar) S/N CJ-129 through CJ-148 and 601(a).

	ACROBATIC CATEGORY:   410(c) and 403(ba) or 403(ah) and 403(ba) or 403(az) and 403(ba) S/N CJ-26 through CJ-30, 403(ah) and 403(ba) or 403(az) and 403(ba) S/N CJ-31 through CJ-128, 403(ar) and 403(as) S/N CJ-129 through CJ-148 and 601(a).

Model F33C:   CJ-149 and after (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 403(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 (TIAS)
Maneuvering 				152 mph (132 knots)
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 Gear Extended)
(+81.3) to (+86.7) at 3300 lb.
(+77.0) to (+86.7) at 2800 lb.
Straight line variation between points given

Empty Weight C.G. Range
None

Maximum Weight
3300 lb.

No. Seats
4  --  (2 at +85, 2 at +117) or 5 (2 at +85, 2 at +117, 1 at +144)

Maximum Baggage
270 lb. (+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

Oil Capacity
10 qt. (+26)
See NOTE 1 for data on system oil

Control Surface Movements
Wing flaps 				Down 30 deg.
Aileron tab 				Fixed
Aileron  					Up 20 deg.	Down 20 deg.
Rudder tab  				Fixed
Rudder  					Left 25 deg.	Right 25 deg.
Elevator tab  				Up 10 deg.	Down 27 deg.
Elevator  				Up 25 deg.	Down 15 deg.

Serial Nos. Eligible
CD-1255 through 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 403(ad), and 601(a).

XVI.   Model A36TC, Bonanza, 4 to 6 PCLM (Utility 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 (IAS)
Maneuvering  				139 knots (160 mph)
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 deg.)		152 knots (175 mph)
  (Above 20,000 feet)  			137 knots (158 mph)
Maximum flaps extended (30 deg.)		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 Gear Extended)
(+81.0) to (+87.7) at 3650 lb.
(+74.0) to (+87.7) at 3100 lb.
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
Takeoff and landing:			3650 lb.

No. 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 (Structural Limits
Rear Compartment (Aft to Sta. 170)		400 lb. (+150)
On and forward of rear spar cover with 
  center seats removed 				200 lb. (+108)
Aft of rear spar cover to Sta. 170 with 
  third, fourth, fifth, and sixth seats removed		400 lb. (+145)
Aft baggage compartment (Sta. 170 to Sta. 190)  	70 lb. (+180)

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 after)
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 deg.	Down 30 deg.
Aileron tab  					Fixed
Aileron  						Up 20 deg. 	Down 20 deg.
Rudder tab  					Fixed
Rudder  						Left 25 deg.	Right 25 deg.
Elevator tab  					Up 10 deg.   	Down 27 deg.
Elevator  					Up 23 deg.   	Down 20 deg.

Serial Nos. Eligible
EA-1 through EA-241, EA-243 through 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 up, 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 Limits
Continental TSIO-520-UB

*Fuel
Aviation gasoline grade 100LL or 100 minimum

*Engine
Takeoff and maximum continuous power 	2700 rpm (36 in. Hg.NAP) (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 deg.)		154 knots (177 mph)
  (Above 20,000 feet)  			139 knots (160 mph)
Maximum flaps extended (30 deg.)		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 Gear Extended)
(+80.0) to (+87.7) at 3850 lb.
(+74.0) to (+87.7) at 3200 lb.
Straight line variation between points given

Empty Weight C.G. Range
None

*Maximum Weight
Takeoff and landing:   			3850 lbs.

No. 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 (Structural Limits)
Rear Compartment (Aft to Sta. 170)		400 lb. (+150)
On and forward of rear spar cover with 
  center seats removed  				200 lb. (+108)
Aft of rear spar cover to Sta. 170 with third,
  fourth, fifth, and sixth seats removed 		400 lb. (+145)
Aft baggage compartment (Sta. 170 to Sta. 190)  	70 lb. (+180)

Fuel Capacity

Tank         Capacity Gal.     	Usable Gal.      	Arm

L & R Main   54 ea.            	51 ea.           	+ 75
  (two interconnected 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 deg.	Down 30 deg.
Right aileron tab  				Fixed
Left aileron tab 
  (S/N EA-242, EA-273 
  through EA-388 except EA-320) 			Fixed
Left aileron tab (S/N EA-320, EA-389 and after) 	Up 9 deg.	Down 9 deg.
Aileron  						Up 20 deg.	Down 20 deg.
Rudder tab  					Fixed
Rudder  						Left 20 deg.	Right 20 deg.
Elevator tab (S/N EA-242, EA-273 through 
  EA-388 except EA-320)  				Up 10 deg.	Down 27 deg.
Right elevator tab (S/N EA-320, EA-389 and after)	Up 10 deg.	Down 25 deg.
Left elevator tab (S/N EA-320, EA-389 and after)  	Up 8 deg.	Down 27 deg.
Elevator  					Up 23 deg.	Down 25 deg.

Serial Nos. Eligible
EA-242, EA-273 and after

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 after, 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 Regulations as amended to May 15, 1956, and Amendment 3-8. For the 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. For the 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, F33A (S/N CE-891 and after), V35B (S/N D-10313 and after), F33C (S/N CJ-156 and after), A36 (S/N E-1609 and after except E-2581 and after equipped with Item 624), A36TC (S/N EA-1 through EA-241 and EA-243 through EA-272), B36TC (S/N EA-242, EA-273 and after). Part 36 through Amendment 36-18 of the Federal Aviation Regulations, A36 (S/N E-2581 and after equipped with Item 624).

Equivalent Safety Findings:   CAR 3.663 and CAR 3.757 for Model V35B (S/N D-9948 and after), A36 (S/N E-927 and after), F33A (S/N CE-674 and after), F33C (S/N CJ-129 and after), A36TC (all serials); CAR 3.387 for Model V35B (all serials), A36 (all serials), F33A (all serials), F33C (all serials), A36TC, (all serials), 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.

Production Basis
Production Certificate No. 8. Delegation option Manufacturer No. CE-2 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations.

Equipment
A plus (+) or minus (-) sign preceding the weight of an item of equipment indicates net weight change when that item is installed. Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by 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 lb. (+ 1)
    Diameter:   not over 84 in., not under 83 in.
    Pitch settings at 33 in. sta.:   Low 13 deg., high not under 30 deg.
  and (b) Woodward hydraulic governor (210175)  					3 lb. (+ 10)
  or (c) Woodward hydraulic governor (210235A) or any later rev. letter			3 lb. (+ 10)

2.   Beech constant speed propeller installation
  (a) Beech 278-100-7 hub with 278-209-84 blades  					73 lb. (+ 1)
    Diameter:   not over 84 in., not under 83 in.
    Pitch settings at 33 in. sta.:   Low 13 deg., high not under 30 deg.
  and (b) Woodward hydraulic governor (210172H)  					3 lb. (+ 10)

3.   Beech constant speed propeller installation
  (a) Beech 278-100-7 hub with 278-214-82 blades  					69 lb. (+ 1)
    Diameter:   not over 82 in., not under 81.5 in.
    Pitch settings at 33 in. sta.:   Low 13.5 deg., high not under 30 deg.
  and (b) Woodward hydraulic governor (210235) all revisions 			3 lb. (+ 10)

4.   Beech constant speed propeller installation
  (a) Beech 278-100-7 hub with 278-213-82 blades  					73 lb. (+ 1)
    Diameter:   not over 82 in., not under 81.5 in.
    Pitch settings at 33 in. sta.:   Low 13.5 deg., high not under 30 deg.
  and (b) Woodward hydraulic governor (210235A) or any later rev. letter  		3 lb. (+ 10)

5.   Hartzell constant speed propeller installation
  (a) Hartzell BHC-92ZF-1D1 hub with 8447 blades  					68 lb. (+ 1)
    Diameter:   not over 84 in., not under 82 in.
    Pitch settings at 33 in. sta.:   Low 11 deg., high not under 26 deg.
  (b) Hartzell hydraulic governor (B4-3)  						4 lb. (+ 10)
  or (c) Woodward hydraulic governor (210335)  					3 lb. (+ 10)
  (d) Hartzell propeller spinner (837-3)  						2 lb. (+ 1)

6.   Beech constant speed propeller installation
  (a) Beech 273-100-11 or 278-100-13 hub with 278-214-82 blades  			69 lb. (+ 1)
    Diameter:   82 in., no cutoff permitted
    Pitch settings at 33 in. sta.:   Low 13.5 deg., high not under 30 deg.
  and (b) Woodward hydraulic governor (210235 or 210350)  --			3 lb. (+ 10)

7.   Flottorp constant speed propeller installation
  (a) Flottorp F12A-4 with 8400-0 blades  --  65 lb. (+ 1)
    Diameter:   not over 84 in., not under 82 in.
    Pitch settings at 33 in. sta.:   Low 11.7 deg. +/-.2 deg. each blade within 
    .2 deg. of each other, high 30 deg. minimum
  (b) Flottorp IF-1 (34-825 Garwin) governor  					5 lb. (+ 10)
  (c) Flottorp FS 200 spinner  							5 lb. (+ 1)
  (d) Woodward governor (210452) (maximum rpm set at 2600) 			3 lb. (+ 10)

8.   Flottorp constant speed propeller installation (H35 only)
  (a) Flottorp F12A-4 with 8400-0 blades  						65 lb. (+ 1)
    Diameter:   not over 84 in., not under 83 in.
    Pitch settings at 33 in. sta.:   Low 13 deg., high 30 deg. minimum
    Airplane Flight Manual Supplement dated May 16, 1962, or August 30, 1962, 
    P/N 35-590106, required.
  (b) Woodward governor (210452) (maximum rpm set at 2600) 			3 lb. (+ 10)
  (c) Flottorp FS 200 spinner assembly  						5 lb. (+ 1)

9.   Flottorp constant speed propeller installation (J35, K35, M35, N35, P35)
  (a) Flottorp F12A-3 with 8400-2 blades  						65 lb. (+ 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 deg., high 30 deg. minimum
    Airplane Flight Manual Supplement 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 lb. (+ 10)
    (Maximum rpm at 2600 for J35, K35, M35)
    (Maximum rpm at 2625 for N35, P35)
  (c) Flottorp FS 200-1 spinner assembly 						5 lb. (+ 1)

10.   Flottorp constant speed propeller installation (H35, 35-33, 35-A33, 35-B33)
  (a) Flottorp F12A-5 with 8400-0 blades  						65 lb. (+ 1)
    Diameter:   (H35 only), not over 84 in., not under 83 in.
    (35-33, 35-A33, 35-B33 only), not over 84 in., not under 82 in.
    Pitch settings at 33 in. sta.:  
      low:   (H35 only) 13 deg.
      (35-33, 35-A33, 35-B33 only) 11.7 deg. +/- .2 deg. each blade within .2 deg. of each other
      high:   (H35, 35-33, 35-A33, 35-B33 only) 30 deg. minimum
    Airplane Flight Manual Supplement dated August 30, 1962, P/N 35-590106, 
    required when this propeller used on Model H35
  (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)

11.   McCauley constant speed propeller installation (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 lb. (+ 1)
      (Model 36)  									62 lb. (- 9)
    Diameter:   not over 84 in., not under 82 in.
    Pitch settings at 30 in. sta.:   low:   (S35, V35, V35A, V35B, 35-C33A, E33A, 
     F33A, E33C, F33C, G33, N35, P35, 36, A36 only) 13.3 deg.
      (35-33, 35-A33, 35-B33, 35-C33, E33, F33 only) 12.0. deg 
      (J35, K35, M35 only) 13.0 deg. 
      (H35 only) 12.7 deg.
      high:   29.2 deg. minimum
    Airplane Flight Manual Supplement, P/N 35-001111 required as follows:
      Supplement dated June 21, 1963, or later, N35, P35, 35-B33; or 
      P/N 35-590101-9 dated May 1976 or later, N35, P35.
      Supplement 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, 35-33, 35-A33, 35-B33.
      Supplement dated May 14, 1968, H35 (with O-470-G engine only), J35, K35, M35 (IO-470-C engine only)
  (b) Woodward governor (210452 or A210680)  					3 lb. (+ 10)
  (c) McCauley D3290A spinner assembly						4 lb. (+ 1)
  (d) McCauley D2822 or D3396 spinner assembly)  					5 lb. (+ 1)
    (Model 36, A36)  								5 lb. (- 9)
  (e) Woodward governor (C210452 or D210680)  					3 lb. (+ 10)
    (Model 36, A36, A36TC, B36TC)  						3 lb. (0)
  (f) Flottorp 1F1 (34-825 Garwin) governor  					5 lb. (+ 10)
  (g) McCauley governor C290D3-X/T23  						3 lb. (+ 10)
    (Model A36, A36TC, B36TC)  							3 lb. (0)

12.   Hartzell constant speed 3-blade propeller installation (S35, V35, V35A, 
        V35B, 35-C33A, E33A, F33A)
  (a) Hartzell PHC-A3VF-4 hub with V8433-2R or V8433-4R blades  			88 lb. (+ 1)
    (S35, V35, 35-C33A, E33A, F33A), V8433-4R blades (V35A, V35B)
    Diameter:   not over 82 in., not under 78-1/4 in.
    Pitch settings at 30 in. sta.:
      low:
        10.5 deg. for V8433-2R
        11.2 deg. for V8433-4R
      high:   30.8 deg. for V8433-2R and V8433-4R
  (b) Hartzell 837-8 spinner assembly  						6 lb. (+ 1)
  (c) Woodward governor (C210452 or D210680)  					3 lb. (+ 10)

13.   Hartzell constant speed 3-blade propeller installation (35-C33)
  (a) Hartzell PHC-A3VF-4 hub with V8433-4R (D) blades  				88 lb. (+ 1)
     Diameter:   not over 80 in., not under 78-1/4 in.
    Pitch settings at 30 in. sta.:
      low:   10.8 deg. +/- .2+
      high:   32 deg. minimum
  (b) Hartzell 837-9 spinner assembly  						6 lb. (+ 1)
  (c) Woodward governor (210452)  						3 lb. (+ 10)

14.   McCauley constant speed 3-blade propeller (S35, V35, V35A, V35B, 
       35-C33, 35-C33A, E33A, F33A, F33C, 36, A36, A36TC) 
  (a) McCauley 3A32C76 hub with 82NB-2 blades  					66 lb. (+ 1)
    (Model 36, A36)  								66 lb. (- 9)
    Diameter:   not over 80 in., not under 78-1/2 in.
    Pitch settings at 30 in. sta.:   low:   
     (S35, V35, V35A, V35B, 35-C33A, E33A, F33A, F33C, 36, A36)  13.3 deg. +.- .2 deg.
    (35-C33)  12.5 deg. +/- .2 deg.
      high:   (S35, V35, V35A, V35B, 35-C33, 35-C33A, E33A, F33A, F33C, 36, A36)  29.0 deg. +/- .5 deg.
    Pitch settings at 30 in. sta. when used with Item 114 (S35, V35, V35A, V35B):
      low:   14.2 deg. +/- .2 deg.
      high:   34.0 deg. +/- .5 deg.
  (b) McCauley D3600 spinner assembly  						4 lb. (+ 1)
  (c) McCauley D3584 spinner assembly  						4 lb. (+ 1)
    (Model 36, A36, A36TC)  							4 lb. (- 9)
  (d) McCauley 3A32C76U hub with 82NB-2 blades (Model A36TC)  			66 lb. (- 9)
    Diameter:   Not over 80 in., not under 78-1/2 in.
    Pitch settings at 30 in. Sta.:
      low:   15.0 deg. +/-.2 deg
      high:   34.5 deg. +/- 1.0 deg.

	Airplane Flight Manual Supplement 130532 dated February 17, 1966, required for 35-C33. Airplane Flight Manual Supplement 130533 dated February 18, 1966, required for S35 and V35 or 35-590110-21 dated October 1975 or later required for S35. Airplane Flight Manual Supplement 130605 dated June 17, 1966, required for S35 and V35 when used with the optional Item 114 engine installation. 

15.   McCauley constant speed 2-blade propeller
  (a) McCauley 2A36C82 hub with 84B-2 blades  					62 lb. (+ 1)
    Diameter:   82 in.
    Pitch settings at 30 in. sta.:
      low:   14.3 deg. +/- .2 deg.
      high:   34.5 deg. +/- .5 deg.

16.   Hartzell constant speed 3-blade propeller installation
  (a) Hartzell PHC-C3YF-1RF hub with F8468A-6R or F8468AK-6R blades (A36TC) 	75 lb. (- 9)
    Diameter:   Not over 80 inches, not under 78 inches
    Pitch settings at 30 in. sta.:
      low:   13.0 deg. +/- 2.0 deg.
      high:   36.0 deg. +/- 1.0 deg.
  (b) Hartzell A2295-1P spinner assembly  						5 lb. (+ 1)
    (Model A36, A36TC)  								5 lb. (- 9)

17.   Hartzell constant speed 3-blade propeller installation (V35B, F33A, A36)
  (a) Hartzell PHC-CJYF-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)
      (Model V35B, F33A,)  							75 lb. (+1)
      (Model A36)  								75 lb. (9)

18.   McCauley constant speed 3-blade propeller (V35B, F33A, A36)
  (a) McCauley 3A32C406- {X} hub with {X} -82NDB-2 blades (Models V35B, F33A)  63 lb. (+ 1)
      (Model A36)  								63 lb. (- 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 deg. +/- .2 deg.
      high:   29.0 deg. +/- .5 deg.
  (b) McCauley D5259 or D5541 or D7168 spinner assembly
      (Models V35B, F33A)  							5 lb. (+ 1)
      (Model A36)  								5 lb. (- 9)

19.   McCauley constant speed 3-blade propeller
  (a) McCauley 3A32C406- {X} hub with {X} -82NDB-4 blades  			63 lb. (- 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 deg. +/- .2 deg.
      high:   34.9 deg. +/- .5 deg.
  (b) McCauley D5259 or D5541 or D7168 spinner assembly  				5 lb. (- 9)

20.   McCauley constant speed 3-blade propeller
  (a) McCauley D3A32C409- {X} hub with {X} -82NDB-2 blades 			63 lb. (- 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:   13.7 deg. +/- .2 deg.
      high:   28.8 deg. +/- .5 deg.
  (b) McCauley D5259 or D5541 or D7168 spinner assembly  				5 lb. (- 9)

21.   Hartzell constant speed 3-blade propeller used with Item 624
  (a) Hartzell PHC-C3YF-1RF hub with F7663-2R blades  				70 lb. (- 9)
    Diameter:   Not over 76 in., not under 75.5 in.
    Pitch settings at 30 in. sta.:
      low:   17.5 deg. +/- .l deg.
      high:   33.0 deg. +/- 1.0 deg.
  (b) Hartzell A-2295-1P spinner assembly 						5 lb. (- 9)
  (c) McCauley C290D3 {X} /T37 governor  					3 lb. (0)
    The letters appearing in the place of the {X} represent minor variations in the governor. They do not affect eligibility or interchangeability. 

Engine and Engine Accessories - Fuel and Oil Systems

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 lb. (+ 74)
  (c) Weldon 4020-A-1  								3 lb. (+ 74)
  (d) Engine-driven, Continental Motors 626062, -1 or -2 or -3 or 635135-3A1
        or 638156-3A1 								2 lb. (+ 39)
       and (e) Weldon 4020-A-1-A, 4020-A-2-A or 4032-A  				3 lb. (+ 74)
       or (f) Thompson 221100-3  							3 lb. (+ 74)
  (g) Dukes 4140-00-1 								3 lb. (+ 74)
  (h) Dukes 4140-00-7  								3 lb. (+ 74)
  (i) Engine-driven, Continental Motors 630947-2 or 638154-2A3			2 lb. (+ 39)
    (Model 36, A36)  								2 lb. (+ 29)
  (j) Dukes 4140-00-39  								3 lb. (+ 74)
  (k) Engine-driven, Continental Motors 626062-9  					2 lb. (+ 39)
  (l) Engine-driven, Continental Motors 632637-1  					2 lb. (+ 39)
  (m) Dukes 4040-00-103  								3 lb. (+ 80)
  (n) Dukes 4258-00-15 Model 36, A36)  						3 lb. (+ 74)
  (o) Dukes 4140-00-191  								2 lb. (+ 79)
  (p) Engine-driven, Continental Motors 643239 (Model V35B) 			2 lb. (+ 39)
  (r) Dukes 1236-00-1 or 1372-00-1  						2 lb. (+ 74)
  (s) Airborne A/M2B6-54 or Dukes 1371-00-1
    (Model V35B, F33A)  								3 lb. (+ 48)
    (Model A36)  									3 lb. (+ 38)

102.   Oil radiator
  (a) Harrison 8525295 (Continental Motors 625093)  				5 lb. (+ 11)
  or (b) Harrison 8528220 (Continental Motors 627392) 				5 lb. (+ 11)
  (c) Modine 1E1406D (Continental Motors 632210)  					8 lb. (+ 36)
    (Model 36, A36)  								8 lb. (+ 26)
    or (d) Modine 1E1502D (Continental Motors 633277 or 634063) or 
    Modine 1E1774D (Continental Motors 635996)  					8 lb. (+ 36)
    (Model 36, A36, A36TC, B36TC)  						8 lb. (+ 26)

103.   Carburetor air cleaner  							1 lb. (+ 10)
  (Model 36, A36, A36TC, B36TC)  --  1 lb. (0)

104.   Vacuum pump
  (a) ARO A513-DB, Pesco 3P-194F, Garwin G450 or G455PM installed per 
       Beech Dwg. 33-001034, 35-324379-1 or 35-324426 or 35-910004 			4 lb. (+ 41)
  (b) Airborne 200CW or 200CW-8 or 222CW installed per Beech Dwg. 35-324407 	4 lb. (+ 41)
  (c) Airborne 224CW installed per Beech Dwg. 35-324407-7  				4 lb. (+ 41)

105.   Starter (14-volt system
  (a) Delco-Remy 1109471, 1109678, 1109681, 1109684, 1109694 
	(Continental Motors Models O-470-G, O-470-G-CI, IO-470-C, 
	IO-470-J and IO-470-K engines only)  					13 lb. (+ 39)
  (b) Delco-Remy 1108249 (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)  						17 lb. (+ 39)
    (Model 36, A36)  								17 lb. (+ 29)
  (c) Prestolite MCL6501 (CMC P/N 634592) 
	(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)  			18 lb. (+ 39)
    (Model 36, A36)  								18 lb. (+ 29)

106.   Two 10 gal. auxiliary wing fuel tanks See NOTE 1 for data on system fuel		18 lb. (+ 94)

107.   Fuel booster pump installation 35-929020 (eligible on H35 when item 108 
	fuel injection system is not installed). Includes Adel 20653 or Thompson 
	TF-36700 electric fuel pump.  						6 lb. (+ 57)

108.   Engine (eligible on Model H35)
  (a) 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), (b), or (c) (14-volt system)  					Negligible weight

110.   Heated fuel tank vents installed per Beech Dwg. 35-001043  			Negligible weight

111.   Two 37 gal. fuel tanks in wing replacing two 22 gal. tanks; 37 gal. usable 
	in each at (+75). See NOTE 1 for data on system fuel  			11 lb. (+ 75)

112.   Engine (eligible on Models 35-33, 35-A33)
  (a) Continental IO-470-K (same as for IO-470-J engine) Installation requires 
	revision to induction valve engine controls in accordance with 
	Beech engineering data. 							Use act. Wt. increase
  (b) See Item 11 for optional propeller with this engine  				Use act. Wt. increase

113.   Two 37 gal. fuel tanks in wing replacing two 22 gal. tanks; 37 gal. usable 
	in each at (+ 75). See NOTE 1 for data on system fuel  			11 lb. (+ 75)

114.   Optional engine installation (S35, V35, V35A, V35B)
  (a) Continental TSIO-520-D engine with AiResearch turbocharger system installed 
	per Beech Dwg. 35-910028 and AiResearch Dwg. 100-S35-209 
	(STC SA1035WE) AiResearch FAA Approved Airplane Flight Manual 
	Supplement dated December 2, 1965, or later required.

    Required equipment:   Item 101(j), 101(l), 101(m), 104(c) (V35), 115(b) (V35A, V35B), 
	12(a), (b) or 15(a), 11(d) and (e) or 14(a) and (c) and 11(e), 403(p) and (bl) (S35),
	403(r) and (bl) (V35), 403(t) or (w) and (bl) (V35A), 403(y) or (aa) or (af) and (bl) 
	(V35B), 403(ac) (when two 22 or 37 gal. main fuel cells are installed per 
	Item 616).  								Use act. Wt. increase

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.

115.   Pressure Pump
  (a) Airborne 200CW or 232CW installed per Beech Dwg. 35-329012-5 or -7 
    (Model 36, A36)								4 lb. (+ 31)
    (V35A, V35B, E33A, F33A, E33C, F33C)  					4 lb. (+ 41)
  (b) Airborne 224CW or 232CW installed per Beech Dwg. 35-329012-7 with 
	item 114 only 								4 lb. (+ 41)
  (c) Airborne 200CW or 232CW installed per Beech Dwg. 33-329010 (E33, F33, G33)  	4 lb. (+ 41)
  (d) Airborne 432CW or 442CW installed per Beech Dwg. 36-324018 (V35A, V35B, 
	E33, F33, G33, E33A, F33A, E33C, F33C)  --  432CW (6 lb.) or 442CW 	(3 lb.) (+ 41)
    (36, A36, A36TC, B36TC)  --  432CW (6 lb.) or 442CW 				(3 lb.) (+ 31)
  (e) Airborne 242CW (E33, E33A, E33C, F33, F33A, F33C, G33, V35A, V35B)  	2 lb. (+ 41)
    (36, A36)  									2 lb. (+ 31)
  (f) Airborne 212CW (F33A, F33C, V35B)  					2 lb. (+ 41)
    (A36, A36TC, B36TC)  							2 lb. (+ 31)

116.   Optional engine installation (V35B)
  (a) Continental IO-520-N engine with automatic power control system per applicable Beech Dwgs. Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement P/N 35-590118-37 dated August 1979 or later required.
    Required equipment:   Item 101(p) and 101(r) and 101(s). 				Use act. Wt. increase

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 lb. (+ 74)
  (b) Dukes 1297-00-1  								2 lb. (+ 79)
  (c) Engine-driven, CMC 630947-2 or 						2 lb. (+ 39)
    638154-2A3 (Model A36)  							2 lb. (+ 29)
  (d) Engine-driven, Continental Motors 638154-16A2 (used with IO-520-BB engine)  	2 lb. (+ 39)
    (Model A36)  									2 lb. (+ 29)
  (e) Airborne 2B7-34 (used with TSIO-520-U or -UB engine) (Model A36TC, B36TC)	5 lb. (+ 74)
  (f) Engine-driven TCM 639508-9A1 (used with TSIO-520-UB engine)  		2 lb. (+ 29)
    (Model A36TC)
  (g) Engine-driven TCM 639508-5 (used with TSO-520-U engine)  			2 lb. (+ 29)
  (h) Engine-driven TCM 639508-9A3 (used with TSIO-520-UB engine) 		2 lb. (+ 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 lb. (+ 74)
  (j) Engine-driven, Continental Motors 643535-1 
	(used with IO-550-B engine Model A36)  					3 lb. (+ 29)
  (k) Dukes 4613-00-3NW or 4615-00-5  						2 lb. (+74)
  (l) Dues 4613-00-5  								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 lb. (+ 39)
    (Model A36, A36TC, B36TC)  							16 lb. (+ 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 lb. (+ 39)
    (Model A36, A36TC, B36TC)  --  14 lb. (+ 29)

119.   Starter solenoid (28-volt system)
  (a) Cutler-Hammer 6041H190 used with item 118(a) 				Negligible weight

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 installed per applicable Beech drawings.  		Use act. Wt. increase
    Required equipment:   Item 117(d).
    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 lb. (+ 97)
    Wheel assembly No. 530869M or 9530949
    Brake assembly No. 511731M
  or (b) Goodyear 6.50-8, Type III, No. PD 931  					25 lb. (+ 97)
    Wheel assembly No. 9532135
    Brake assembly No. 9532167, 9532475, 9532412, or 9532679
  or (c) Cleveland 6.00-6  								19 lb. (+ 97)
    Wheel assembly 27-100D
    Brake assembly 35-200A
  or (d) Cleveland 6.00-6  								19 lb. (+ 97)
    Wheel assembly 40-37
    Brake assembly 30-24
  or (e) Beech 6.00-6, Type III, No. 95-300001  					23 lb. (+ 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 lb. (+ 97)
    Wheel assembly No. 95-30001-1 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 lb. (+ 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 lb. (+ 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 lb. (+ 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 lb. (+ 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 lb. (+ 97)
    Brake assembly 30-66  								8 lb. (+ 97)

202.   Main wheel tires
  (a) Two 6.50-8, 4 or 6-ply rating tires with regular tubes 				23 lb. (+ 97)
  (b) Two 6.50-8 side inflatable 4 or 6-ply rating tubeless tires used only 
	with Item 201(b) 								21 lb. (+ 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 lb. (+ 97)
  or (d) Two 7.00-6 side inflatable 6-ply rating tubeless tires used only 
	with Item 201(e) 								20 lb. (+ 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 lb. (+ 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 lb. (+ 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 lb. (+ 12)
  or (b) Goodyear 9532102 or 9532669  						4 lb. (+ 12)
  (c) Cleveland 21-100  								4 lb. (+ 12)
  or (d) Goodyear 9532102 or 9532669 modified per Goodyear Dwg. 
	5R2-365 and -366. Use only with Item 206(a)				4 lb. (+ 12)
  or (e) Goodyear 9532926. Use only with Item 206(a)  				4 lb. (+ 12)
  or (f) Wheel assembly, Cleveland No. 40-87 or 40-77D. Use only with Item 206(a)  	3 lb. (+ 12)
    (Model 36, A36, A36TC, B36TC)  						3 lb. (+ 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 lb. (+ 12)
    (Model 36, A36, A36TC, B36TC)  						7 lb. (+ 2)
  or (b) 4-ply rating, side inflatable, 5.00-5 tubeless tire used only 
	with item 205(b) or (c)  							5 lb. (+ 12)

210.   Co-pilot brakes (H35 through M35)  						2 lb. (+ 54)

211.   Co-pilot brakes (N35 and subsequent, 35-A33 and subsequent) 			4 lb. (+ 54)
    (Model 36, A36, A36TC, B36TC)  						4 lb. (+ 44)

Electrical Equipment

301.   Generator (14-volt system)
  (a) 50 a. CMC P/N 535896 or Delco-Remy 1101895  				16 lb. (+ 37)
  or (b) 50 a. CMC P/N 626380 or Delco-Remy 1101909  				16 lb. (+ 37)
  or (c) 50 a. CMC P/N 627272 or Delco-Remy 1101912  				16 lb. (+ 37)
  (d) 35 a. CMC P/N 627273 or Delco-Remy 1101913  				16 lb. (+ 37)
  (e) 70 a. Delco-Remy P/N 1100667  						11 lb. (+ 11)
  or (f) 70 a. Delco-Remy P/N 1100715  						11 lb. (+ 11)
    (Model 36, A36)  								11 lb. (+ 1)
  (g) 60 a. Beech P/N 33-380009 or 380009-1 installed per Beech Dwg. 
	33-3001 (H35 through P35 and 35-33 through 35-C33) or Beech 
	Dwg. 33-369110 (35-C33, E33, F33) or Beech Dwg. 33-369113 
	(G33). Item 304(e) required						12 lb. (+ 39)
  (h) 70 a. CMC P/N 634785 or Prestolite ALX-9424  				11 lb. (+ 11)
    or CMC P/N 641670 or Prestolite ALX-9424 					11 lb. (+ 1)

302.   Battery (14-volt system)
  (a) 12 v. 33 a. hr. (mounted aft of firewall in cabin comp.)  				28 lb. (+ 54)
  or (b) 12 v. 24 a. hr. Sonotone 22500 nickel-cadmium, installed per Beech 
	Dwg. 35-001040. Item 403(h) required. 					28 lb. (+ 54)
  (c) 12 v. 33 a. hr. (mounted forward of firewall in engine comp)  			28 lb. (+ 45)
    (Model 36, A36) 								28 lb. (+ 35)
  (d) 12 v. 33 a. hr. (mounted fwd. of firewall in engine compartment per 
	Beech Dwg. 35-3001).							28 lb. (+ 45)

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 lb. (+ 9)
  (d) One General Electric 4313  							1 lb. (+ 7)
    (Model 36, A36)  								1 lb. (- 3)
  (e) Two General Electric 4313 							2 lb. (+ 9)
    (Model 36, A36)  								2 lb. (- 1)

304.   Voltage regulator (14-volt system)
  (a) Delco-Remy 1118713  							2 lb. (+ 48)
  or (b) Delco-Remy 1119224C  							2 lb. (+ 48)
  (c) Delco-Remy 1119220C  							2 lb. (+ 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)
    (Model 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)
    (Model 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 lb. (+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
35-001031, 33-001024, or 35-364161 (14-volt system)  				2 lb. (+102)
  (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 (Models 36, A36) (14-volt system)
  (a) Dual - installed per Dwg. 36-360011 (Grimes D7080A-1-12 top, 
	D7080A-6-12 bottom) or (Beech 33-380003-1 top, 33-380003-3 bottom)  	4 lb. (+178)
  (b) Single top mounted installed per Dwg. 36-360011 (Grimes D7080A-1-12 or 
	Beech 33-380003-1)  							2 lb. (+246)

308.   Alternate Re-Exciter, P/N 60-369017 (Model 36 only) (14-volt system)  		Negligible weight

309.   Generator (28-volt system)
  (a) 50 a. 24 v. CMC P/N 641668 or Prestolite ALT-9422  				12 lb. (+ 11)
    (Model 36, A36TC) 								12 lb. (+ 1)
  (b) 100 a. 24 v. CMC P/N 640789 or Prestolite ALV-9407  				23 lb. (+ 11)
    (Model A36)  									22 lb. (+ 1)
  (c) 100 a. 24 v. CMC P/N 642056 or CMC P/N 646491 or TCM  			18 lb. (+ 11)
    P/N 646844 or TCM P/N 649305
    (Model A36, A36TC, B36TC)  							18 lb. (+ 1)
  (d) 60 a. 24 v. CMC P/N 642055 or CMC P/N 646490  				12.5 lb. (+ 11)
    (Model A36, A36TC, B36TC)  							12.5 lb. (+ 1)
  (e) 100 a. 24 v. CMC P/N 646491 or TCM P/N 646844 or TCM P/N 649305 
	used with IO-550-B engine 						18 lb. (+ 1)
  (f) 60 a. 24 v. CMC P/N 646490 used with IO-550-B engine 				12.5 lb. (+ 1)

310.   Battery (28-volt system)
  (a) 24 v. 15.5 a. hr.  								25 lb. (+ 45)
    (Model A36, A36TC, B36TC)  							25 lb. (+ 38)

311.   Landing lights (28-volt system)
  (a) Two General Electric 4596  							2 lb. (+ 9)
    (Model A36, A36TC, B36TC)  							2 lb. (- 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)

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 lb. (+182)
  or (b) Whelen WRML-28  							2 lb. (+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 D7080A-5-24 to be installed only when Item 313(a) is installed  		2 lb. (+102)
  or (b) Whelen WRML-28CCW  							2 lb. (+102)
  or (c) Grimes 40-0100-3C  							2 lb. (+102)
  or (d) Whelen 01-0790081-02  							1 lb. (+102)

315.   Anti-collision light (Model A36, A36TC, B36TC, 28-volt system)
  (a) Single, top mounted, installed per Beech Dwg. 36-364030 (Grimes D7080A-3-24)	2 lb. (+246)
  or (b) Single, top mounted, installed per Beech Dwg. 36-364030 (Whelen WRML-28)	2 lb. (+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 (Grimes D7080A-3-24 top, 
	Grimes D7080A-5-24 bottom) 						4 lb. (+178)
  or (e) Dual - installed per Beech Dwg. 36-364030 (Whelen WRML-28 top, 
	Whelen WRML-28CCW bottom)  						4 lb. (+178)
  or (f) Dual - installed per Beech Dwg. 36-364030 (Whelen WRML-28 top) and 
	Dwg. 96-364070 Grimes 40-0100-3C bottom)  				4 lb. (+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 lb. (+150)
  or (h) Dual - installed per Beech Dwg. 36-364030 (Whelen 01-0790081-00 top, 
	Whelen 01-0790081-02 bottom)  						2 lb. (+178)

Interior Equipment

401.   Parachute flares
  (a) Three 1-1/2 minute, International  						15 lb. (+164)

402.   Dual control column (T-type) All serials except S/N E-1946, E-2104, E-2111 
	and after; EA-320, EA-389 and after.
  (a) Beech 35-524575 (H35 through N35, 35-33 through 35-A33)  			3 lb. (+ 72)
  (b) Beech 35-524656 (P35, S35, V35, V35A, V35B, 35-B33, 35-C33, E33, F33, 
	G33, 35-C33A, E33A, F33A, E33C)  					3 lb. (+ 72)
  (Model 36, A36)  --  3 lb. (+ 62)
  (c) Beech 36-524021 (V35B, F33A, F33C) 					4 lb. (+ 73)
  (Model 36, A36, A36TC, B36TC)  						4 lb. (+ 63)

403.   Airplane Flight Manuals  							DOA approved
	(a) Deleted	
	(b) Deleted
	(c) Deleted
	(d) Deleted
	(e) Deleted
	(f) Model H35 Airplane Flight Manual Supplement No. 1 dated February 2, 1959, usable H35 and required with Item 108(a) engine installation.
	(g) Deleted
	(h) Airplane Flight Manual Supplement dated November 20, 1959, required with Item 302(b) for Models H35, J35, K35, M35.
	(i) Airplane Flight Manual Supplement dated December 3, 1959, required with Item 302(b) for Model 35-33.
	(j) Model 35-33 dated November 5, 1959, 1962 or August 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 December 29, 1960, or August 30, 1962, with Item 10; or Item 403(av).
	(l) Deleted.
	(m) Model 35-B33 dated September 29, 1961, or August 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 (S/N CD-945 and up. S/N CD-814 through 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 (S/N CD-1200 through CD-1234); or Item 403(aw).
	(w) Model V35A dated September 20, 1968, or October 16, 1970 (S/N CD-8872 and up) (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 September 12, 1969, or June 30, 1970 (used with Item 114).
	(ab) Model G33 dated January 29, 1971.
	(ac) Airplane Flight Manual Supplement 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, 1972; or Item 403(be).
	(ah) Model F33A dated August 11, 1972.
	(ai) Airplane Flight Manual Supplement dated November 3, 1972, or later.
	(aj) Airplane Flight Manual Supplement dated May 2, 1975, or later with Item 619.
	(ak) Model K35 and M35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised March 1987 or later.
	(al) Model S35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised March 1987 or later (used when Item 114 is not installed).
	(am) Model H35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised March 1987 or later.
	(an) Model J35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised March 1987 or later.
	(ao) Model N35 and P35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised March 1987 or later.
	(ap) Deleted
	(aq) Model A36 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated October 1976 or later.
	(ar) Model F33A Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated October 1976 or later.
	(as) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Acrobatic Bonanza F33C (S/N CJ-129 through CJ-155) dated December 1982 or later.
	(at) Model V35, V35A, and V35B Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised March 1987 or later (used when Item 114 is not installed).
	(au) Model 35-33 Pilot's operating Handbook and FAA Approved Airplane Flight Manual dated June 1977 or later.
	(av) Model 35-A33 and 35-B33 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated July 1977 or later.
	(aw) Model 35-C33, E33, and F33 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated September 1977 or later.
	(ax) Model 35-C33A, E33A, and E33C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated October 1977 or later.
	(ay) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Acrobatic Bonanza E33C (S/N CJ-1 through CJ-35) dated December 1982 or later.
	(az) Model F33A (S/N CE-290 through CE-673) and Model F33C (S/N CJ-26 through CJ-128) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated November 1977 or later.
	(ba) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for the Acrobatic Bonanza F33C (S/N CJ-26 through CJ-128) dated December 1982 or later.
	(bb) Model V35B Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised March 1987 or later (used when Item 114 is not installed).
	(bc) Model A36 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated October 1977 or later.
	(bd) Model F33A Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated November 1977 or later.
	(be) Model 36 (S/N E-1 and after) and Model A36 (S/N E-185 through E-926) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated February 1978.
	(bf) Model A36TC Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated November 1978 or later.
	(bg) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement dated April 1980 or later (Model A36TC) required with Item 16(a).
	(bh) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement dated April 1980 or later (Models V35B, F33A, A36) required with Item 17(a).
	(bi) Model B36TC Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated January 1982 or later.
	(bj) Model A36 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated October 1983 or later.
	(bk) Model B36TC Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated October 1983 or later.
	(bl) FAA Approved Airplane Flight Manual Supplement dated March 1987 or later required with Item 114.
	(bm) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement dated April 1991 or later required with Item 624.

404.   Air conditioner installation (including water)  						18 lb. (+148)

405.   
	(a) Tactair T-3 automatic pilot per 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). 
	Airplane Flight Manual Supplement 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.
	A1521 (Models 35-A33, 35-B33). Used only with Item 405(a). 			2 lb. (+ 58)

406.   Tactair T-2 Automatic Pilot per Beech Dwg. Mod. C.O. B46005 or Tactair Kit No. 
	A1915 including Installation Instructions Form BL-1 and Operating Instructions 
	Form BL-2 (Models 35-33, 35-A33, 35-B33). Airplane Flight Manual Supplement 
	dated December 16, 1959, or dated June 1977 or later, required. Weight includes 
	two gyro instruments. 								13 lb. (+ 79)

407.   (a) Tactair T-3 Automatic Pilot per Beech Dwg. 35-500001 or Tactair Kit D451 
	(Models N35, P35). Airplane Flight Manual Supplement dated November 1, 1960, 
	revised December 23, 1960, or Airplane Flight Manual Supplement dated 
	November 3, 1961, required for Model N35; and Airplane Flight Manual 
	Supplement dated November 3, 1961, required on Model P35; or Airplane Flight 
	Manual Supplement 35-590110-17 dated May 1976 or later required for N35, 
	P35. Weight includes two gyro instruments. 						19 lb. (+ 95)
  (b) Tactair AH-1 Altitude Hold per Beech Dwg. 35-500013 or Tactair Kit A1521 (Models 
	N35, P35, S35, V35), or Mod. C.O. B83160 (Model S35 only). Usable with 
	Item 407(a) or (c) only) 								2 lb. (+ 58)
  (c) Tactair T-3 automatic pilot per Beech Dwg. 35-500001 or Tactair Kit D451 (Models 
	S35, V35), or Mod. C.O. B83160 Tactair Kit D4541 (Model S35 only). 
	Airplane Flight Manual Supplement 35-500001-1 dated November 3, 1961, 
	or 35-590110-17 dated October 1975 or later required for S35.  			19 lb. (+101) 
	-	Weight includes two gyro instruments.

408.   Beech Power Flite Control single axis autopilot
  (a) Basic autopilot system per Beech Dwg. 33-500013-1 or 33-500013-51 
	(P35, 35-B33 only) or 35-001062, Airplane Flight Manual Supplement dated 
	September 29, 1961, required.  							6 lb. (+ 87)
  (b) Autopilot system with course selector directional gyro per Beech Dwg. 33-500013-5 or 
	33-500013-55 (P35, 35-B33 only) or 35-001062-1 and -3 Airplane Flight Manual 
	Supplements dated September 29, 1961, required.					10 lb. (+ 79)

409.   Tactair T-3AL Automatic Pilot
  (a) Installed per Beech Dwg. 33-500002 or Tactair Kit B-2586 (35-B33, 35-C33 only) 
	Airplane Flight Manual Supplement 33-500002-1 dated August 5, 1964, or
	May 25, 1966, or later, required. Weight includes two gyro instruments.  		23 lb. (+ 93)
  (b) Installed per Beech Dwg. 35-500003 or Tactair Kit B-2587 (S35, V35). Airplane Flight 
	Manual Supplement 35-500003-1 dated September 1, 1964, or 35-590110-19 
	dated October 1975 or later required on S35.  					23 lb. (+ 93)
  (c) Installed per Beech Dwg. 33-500004 or Tactair Kit A3103 (35-C33 only). Airplane Flight 
	Manual Supplement 33-500002-1 dated May 25, 1966, or later, required. Weight 
	includes two gyro instruments. 							23 lb. (+ 93)

410.   Pilot's check lists:   DOA Approved
  (a) Model F33A (S/N CE-290 through CE-349) dated November 4, 1969, January 30, 1970, 
	or August 23, 1971:   (S/N CE-350 and after) dated August 23, 1971.
  (b) Model A36 (S/N E-185 through E-282) dated November 7, 1969, January 30, 1970, or 
	August 23, 1971:   (S/N E-283 and after) 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(bd)

Deicing Equipment (Propeller)

501.   (14-volt system)
  (a) B. F. Goodrich Electro Thermal Propeller Deicer System on Models 33, 35, and 36 
	series aircraft, used in conjunction with McCauley's 2A36C82 or 2A36C23 two-blade 
	propeller installed per Beech Dwg. 35-960076 or Beech Kit Dwg. 35-9001. Airplane 
	Flight Manual Supplement P/N 130554 dated February 6, 1967, or later, or Airplane 
	Flight Manual Supplement 35-590118-25 dated January 30, 1973, or later, required as 
	applicable on Models S35, V35, V35A, V35B, E33, and F33. Airplane Flight Manual 
	P/N 130694 dated March 1, 1967, or later, required on Model 35-C33A. Current FAA 
	Approved Check List or Airplane Flight Manual Supplement 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, E33C, F33, F33A, F33C, 36, and A36.  		9 lb. (+ 22)
     36 and A36 										        (+ 12)
  (b) B. F. Goodrich Electro Thermal Propeller Deicing System on Models 33, 35, and 36 
	series aircraft, used in conjunction with McCauley's 3A32C76 three-blade propeller 
	installed per Beech Dwg. 35-960077 or Beech Kit Dwg. 35-9005. Airplane Flight 
	Manual Supplement P/N 130555 dated February 6, 1967, or later, or Airplane Flight 
	Manual Supplement 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, and A36. Airplane Flight Manual P/N 130687 dated 
	February 21, 1967, or later, or P/N 130694 dated October 1977 or later, required 
	on Model 35-C33A. Current FAA Approved Check List or Airplane Flight Manual 
	Supplement 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 F33A and A36. Airplane 
	Flight Manual P/N 131332 dated March 14, 1975, or later, or P/N 130694 dated 
	October 1977 or later, applicable on Model 36.  					9 lb. (+ 22)
    36 and A36 										        (+ 12)
  (c) B. F. Goodrich Electro Thermal Propeller Deicing System used in conjunction with 
	Hartzell's PHC-A3VF-4 (Models S35 & V35) three-blade propellers, installed 
	per Beech Kit Dwg. 35-9003. Flight Manual Supplement P/N 130555 dated 
	February 6, 1967, is required.  							9 lb. (+ 24)

502.   (28-volt system)
  B. F. Goodrich Electro Thermal Propeller Deicing System used in conjunction with 
	McCauley 2A36C23 two-blade propeller on the Models F33A, F33C, V35B, and 
	A36, and McCauley 3A32C76 or Hartzell PHC-C3YF-1RF or McCauley 3A32C406 
	three-blade propeller on the Models F33A, F33C, V35B, A36, A36TC, and B36TC 
	per Beech Drawing 35-960080 or 36-960011. Airplane Flight Manual Supplement 
	P/N 36-590002-29 dated April 1978 or later is required for F33A, F33C, V35B, 
	A36, and A36TC. Airplane Flight Manual Supplement P/N 36-590006-9 dated 
	January 1982 or later is required for B36TC.  					7 lb. (+ 22) 
    (A36, A36TC and B36TC)  								        (+ 12)

503.   (28-volt system)
  McCauley Electro Thermal Propeller Deicing System in conjunction with McCauley 
	3A32C406 three-blade propeller on the Models F33A, V35B, A36, and B36TC 
	and the McCauley D3A32C409 three-blade propeller on the Model A36 and per 
	Beech Drawing 36-960012. Airplane Flight Manual Supplement P/N 36-590002-29 
	dated April 1978 or later is required for F33A, V35B, and A36 prior to E-2111 
	except E-1946 and E-2104. Pilot's Handbook and FAA Approved Airplane Flight 
	Manual Supplement P/N 36-590006-9 dated January 1982 or later is required for 
	B36TC prior to S/N EA-389 except EA-320; dated October 1983 or later required 
	for Model A36 S/N E-1946, E-2104, E-2111 and after and Model B36TC S/N 
	EA-320, EA-389 and after.  							7 lb. (+ 22) 
    A36, B36TC)  										        (+ 12)

Miscellaneous (not listed above)

601.   Stall warning indicator installation
   (a) Safe-Flight, Beech Dwg. 35-361025 or 58-361013
   (b) Safe-Flight, Beech Dwg. 58-361013

602.   Heated pitot head installation
  (a) Beech Dwg. 35-361100 (H35 through 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 through V35A, V35B, 35-B33 through E33, F33,
	G33, 35-C33A, E33A, F33A, E33C, 36, A36, A36TC, and B36TC) 			1 lb. (+ 74)

**603.   Aileron trimmer control installation per Aircraftsmen, Inc. Oklahoma City, 
	Oklahoma, Dwg. ATC-35.  							1 lb. (+ 73)
  (Model 36 and A36)  									1 lb. (+ 63)

604.   Optional seating per Beech Dwg. 95-534014, 95-534015, and 95-534016 (K35, M35).  	17 lb. (+135)

605.   Optional seating per Beech Dwg. 35-534401 (N35, P35)  				17 lb. (+135)

606.   Zep Oxygen System per Beech Dwg. 35-001055-1 or -3  			Use actual Wt. increase
	and (a) Beech Dwg. 414-001058-1
	or (b) Beech Dwg. 414-001059-1 (H35, J35, 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 (Fifth seat, S35, V35, V35A, V35B S/N 
	D-9069 through D-9861, F33A S/N CE-316 through CE-633)  				13 lb. (+155)
  (b) 96-534051-57 or 35-001120  								13 lb. ea. (+155)
    (Fifth and sixth seats, S35, V35, V35A, V35B S/N D-9069 through D-9861, 
	F33A S/N CE-316 through CE-633). Airplane Flight Manual Supplement, 
	P/N 35-590110-7 dated June 29, 1964, or 35-390110-15 dated October 1975 
	or later required (S35 only)  							Stowed 
  (c) 33-534033  										18 lb. (+144)
    (Fifth seat 35-C33, E33, E33C, F33, G33, F33A (S/N CE-290 through CE-315), F33C, 
	35-C33A, E33A only). Airplane Flight Manual Supplement P/N 33-534033-9 
	dated March 9, 1965, or September 1977 or later, required for F33.
  (d) 96-534051  										14 lb. (+155)
    Fifth seat V35B S/N D-9862 and on F33A S/N CE-634 and on Fifth and sixth seats 
	V35B S/N D-9862 and on F33A S/N CE-634 and on

608.   Oxygen system installation
  (a) 38 cu. ft. per Beech Dwg. Mod. C.O. B82616 (4 outlets, S35) or 35-560000 (4, 5, or 
	6 outlets, S35, V35) (4 outlets 35-B33, 35-C33, 35-C33A)  				27 lb. (+ 78)
  (b) 48 cu. ft. per Beech Dwg. Mod. C.O. B89386 (4 outlets, S35) or 35-560000 (4, 5, or 
	6 outlets, S35, V35, V35A, V35B, E33A, F33A, F33C), (4 outlets 35-B33, 
	35-C33, 35-C33A)  								33 lb. (+ 77)
  (c) 49 cu. ft. per Beech Dwg. 35-560001 and 35-560010-39 (4, 5, or 6 outlets, V35, 
	V35A, V35B) (4 outlets, 35-C33, E33, F33, G33, 35-C33A, E33A, F33A, 
	E33C, F33C) 									25 lb. (+77)
  (d) 114 cu. ft. per Beech Dwg. 35-560001 and 35-560011-1 (4, 5, or 6 outlets, V35, 
	V35A, V35B) (4 outlets, 35-C33, E33, E33C, F33, G33, F33C, 35-C33A, 
	E33A, F33A)  									52 lb. (+ 77)
  (e) 38 cu. ft. per Beech Dwg. 35-560001 and 35-560010-1 (4, 5, or 6 outlets, V35, 
	V35A, V35B)(4 outlets, 35-C33, E33, F33, 35-C33A, E33A, F33A, 
	E33C, F33C) 									27 lb. (+ 78)
  (f) 49 cu. ft. per Beech Dwg. 36-560000 and 35-560010 7 outlets and 4 or 5 masks 
	(V35B, F33A)  									25 lb. (+ 77)

609.   Emergency static source installation  							Negligible weight
  (a) Beech Dwg. 35-324428. Eligible on (S35, V35, V35A, V35B, 35-C33, 35-C33A, 
	E33, F33, G33, E33A, E33C, F33A, F33C, 36, A36, A36TC, B36TC). 
	Airplane Flight Manual Supplement 35-324428-13 dated January 4, 1965, 
	or later, required (V35, 35-C33). Airplane Flight Manual Supplement 
	35-324428-13 dated January 4, 1965, or later or Pilot's Operating Handbook 
	and FAA Approved Airplane Flight Manual dated October 1975 or later 
	required (S35). Airplane Flight Manual 130709 dated March 17, 1967, or 
	Pilot's Operating Handbook and FAA Approved Airplane Flight Manual 
	dated October 1977 or later, required (35-C33A). Airplane Flight Manual 
	Supplement 35-324428-13 dated September 22, 1967, or Pilot's Operating 
	Handbook and FAA Approved Airplane Flight Manual dated September 1977 
	or later, required (E33, F33, V35A, and V35B, S/N D-9069 through D-9390).
  (b) Beech Dwg. 35-5013, eligible on Model 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. Airplane Manual Supplement 
	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 lb. (+104)
  (a) Beech Dwg. 35-364170, Airplane Flight Manual Supplement 35-364170-5 dated 
	January 29, 1965, or Pilot's Operating Handbook and FAA Approved Airplane 
	Flight Manual Supplement 35-590110-13 dated September 1977 or later, 
	required (S35 prior to D-7882 and 35-C33 prior to CD-925).
  (b) Beech Dwg. 35-364170, eligible on S35 (D-7882 through D-7976), V35, V35A, 
	V35B, 35-C33 (CD-925 through CD-1118), E33, E33A, F33, G33, 35-C33A, 
	E33C, F33A, F33C, 36, A36, A36TC, and B36TC. Airplane Flight Manual 
	Supplement 35-364170-5 dated June 8, 1965, or 35-590110-13 dated October 
	1975 or later required for S35 (D-7882 through D-7976). Airplane Flight 
	Manual Supplement 35-364170-5 dated June 8, 1965, or Pilot's Operating 
	Handbook and FAA Approved Airplane Flight Manual Supplement 35-590110-13 
	dated September 1977 or later, required for V35, V35A, 35-C33 (CD-925 through
	CD-1118), E33 and F33. Airplane Flight Manual 130710 dated March 17, 1967, 
	required for 35-C33A. Airplane Flight Manual Supplement 35-590027-9 dated 
	January 29, 1971, or March 19, 1973, or 35-590110-13 dated October 1976 or 
	later, required for G33. Airplane Flight Manual Supplement 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 after. Current 
	applicable FAA Approved Check List or Airplane Flight Manual Supplement 
	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 after, Model 36 S/N E-1 through 
	E-184, Model A36 S/N E-185 and after, Model A36TC S/N EA-1 and after, and 
	Model F33C S/N CJ-26 and after. Pilot's Operating Handbook and FAA Approved 
	Airplane Flight Manual Supplement 36-590006-7 dated January 1982 or later 
	required for Model B36TC.
  (c) Beech Dwg. 35-8001, Airplane Flight Manual Supplement 35-364170-5 dated 
	June 8, 1965, required (H35 through S35, 35-C33, and E33).
  (d) Beech Dwg. 35-8001, Airplane Flight Manual Supplement 130471 dated 
	June 7, 1965, required (35-33 through 35-B33).
  (e) Beech Dwg. 35-8001, Airplane Flight Manual 130710 dated March 17, 1967, 
	required for 35-C33A. 
  (f) Beech Dwg. 35-8001 (E33A).
  (g) Beech Dwg. 35-8001 (36).

611.   24 v. Electrical system (eligible Model 35-C33, S/N CD-911 and up). Beech Dwg. Mod. C.O. B97393 and B98454A.
  101.   (h) Replaced by Dukes 4140-00-105  						3 lb. (+ 74)
  301.   (c) Replaced by 50 a. Delcotron 1100718  						11 lb. (+ 37)
    or (d) Replaced by Continental 631111  							11 lb. (+ 37)
  302.   (d) Replaced by two 12 v. 24 a. hr. (Beech 118658)  					46 lb. (+ 45)
  304.   (b) Replaced by Delco Remy 9000591  						1 lb. (+ 48)
  Vacuum pump - Beech 50-380090  							5 lb. (+ 41)
  Starter - Delco Remy 1108234 (Continental 627841)  					16 lb. (+ 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 lb. (+182)

612.   Electrically actuated elevator trim system  						Negligible weight
  (a) Installed per Beech Dwg. 35-524669 or 35-3011 (V35A, V35B)  				3 lb. (+200)
  (b) Installed per Beech Dwg. 33-524022 (E33, E33A, E33C, F33, G33, F33A prior to 
	CE-316, F33C) 									3 lb. (+164)
  (c) Installed per Beech Dwg. 36-524013 or 96-524031 (F33A, S/N CE-316 and up) 		3 lb. (+200)

613.   Optional seating (Model 36 Series)
  (a) Fifth and sixth seats per Dwg. 36-530011-1  						32 lb. (+151)
  (b) Fifth seat (L.H.) per Dwg. 36-530011-3  						16 lb. (+151)
  (c) Sixth seat (R.H.) per Dwg. 36-530011-4  						16 lb. (+151)
  (d) Club seating per Dwg. 58-530061
    Third and fourth aft facing seats  								40 lb. (+106)
    Fifth and sixth forward facing seats 							32 lb. (+155)
  (e) Fifth and sixth seats per Dwg. 58-530204 or 106-530025 					30 lb. (+151)
  (f) Fifth seat (L.H.) per Dwg. 58-530204 or 106-530025  					15 lb. (+151)
  (g) Sixth seat (R.H.) per Dwg. 58-530204 or 106-530025 					15 lb. (+151)
  (h) Club seating per Dwg. 58-530183 or 102-530100
    Third and fourth aft facing seats  								50 lb. (+106)
    Fifth and sixth forward facing seats 							30 lb. (+155)

      	E-1371 through E-1593 except E-1422, E-1551, E-1569, and E-1581. EA-1 
	through EA-32 except EA-21 and EA-28.

  (i) Fifth and sixth seats per Dwg. 58-530204 or 106-530025 					32 lb. (+155)
  (j) Fifth seat (L.H.) per Dwg. 58-530204 or 106-530025 					16 lb. (+155)
  (k) Sixth seat (R.H.) per Dwg. 58-530204 or 106-530025  					16 lb. (+155)

	 E-1422, E-1551, E-1569, E-1581, E-1594 and after; EA-21, EA-28, and EA-33 and after

  (l) Fifth seat (L.H.) per Dwg. 106-530057  							16 lb. (+155)
  (m) Sixth seat (R.H.) per Dwg. 106-530057  						16 lb. (+155)
  (n) Fifth and sixth seats per Dwg. 106-530057  						32 lb. (+155)
  (o) Club seating - per Dwg. 106-530061
    Third and fourth aft facing seats  								50 lb. (+106)
    Fifth and sixth forward facing seats  							32 lb. (+155)
  (p) Vertical adjusting (co-pilot's seat) per Dwg. 106-530060-15 (A36, S/N E-1946, 
	E-2104, E-2111 and after. B36TC, S/N EA-320, EA-389 and after)  			23 lb. (+ 80)
614.   Oxygen system installation (Model 36, A36, A36TC, B36TC)
  (a) 38 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 36-560012-1 
	(Models 36 and A36)  								32 lb. (+151)
  (b) 49 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 36-560012-3 
	(Models 36 and A36)  								31 lb. (+ 73)
  (c) 114 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 36-560011-1 
	(Models 36 and A36)								56 lb. (+ 71)
  (d) 49 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 36-560013 
	(Models A36 and A36TC) 							32 lb. (+ 81)
  (e) 76.5 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 35-560001 and 36-560013 
	(Models A36 and A36TC)  							41 lb. (+ 79)
  (f) 49 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 36-560000 and 36-560013 
	(Models A36, A36TC, B36TC) 							31 lb. (+ 79)
  (g) 76.5 cu. ft. with 4, 5, or 6 outlets per Beech Dwg. 36-560000 with 36-560013 
	(Models A36, A36TC, B36TC) 							40 lb. (+ 77)
  (h) 49 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560002 and 36-560016 
	(Models A36, B36TC) 								31 lb. (+ 79)
  (i) 76.5 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560002 and 36-560016 
	(Models A36, B36TC) 								40 lb. (+ 77)
  (j) 49 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560003 (Model B36TC)  	37 lb. (+ 90)
  (k) 98 cu. ft. with 7 outlets and 4, 5, or 6 masks per Beech Dwg. 36-560001 (Model B36TC)  	63 lb. (+ 90)
615.   Utility door installation per Beech Dwg. 36-400011 (Models 36, A36, A36TC, B36TC) 
	Models 36, A36, A36TC, and B36TC are 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. (36, A36)
  Beech placard 36-530131 required E-1422, E-1551, E-1569, E-1581, E-1594, and after. 
	(A36) Beech placard 36-530061 required prior to E-927. (36, A36)
  Beech placard 36-324035 required E-927 and after. (A36)
	Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Flight with Utility Doors Removed dated November 1979, or later, required for A36TC.
	  Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Flight with Utility Doors Removed 36-590006-5 dated January 1982, or later, required for B36TC.
  Beech placard 36-324069 required for 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.

617.   Area navigation equipment installed per applicable Beech Dwgs.
  (a) Airplane Flight Manual Supplement for King KN-74 area navigation system dated 
	August 23, 1971, or August 11, 1972, or October 1976 or later, required for V35B and G33.
  (b) Airplane Flight Manual for King KN-74 area navigation system dated August 23, 1971, or 
	Airplane Flight Manual Supplement dated August 11, 1972, or October 1976 or 
	later, required for F33A, A36, and A36TC.
  (c) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for 
	the Collins ANS-351 Area Navigation System dated November 23, 1977, or later, 
	required for F33A, A36, V35B, and A36TC; dated January 1982, or later, required 
	for B36TC.
  (d) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for 
	the King KNS-80 Area Navigation System dated August 1978, or later, required for 
	F33A, F33C, V35B, A36, and A36TC; dated January 1982, or later, required for B36TC.
  (e) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for 
	the Bendix MCP-2040 Area Navigation System dated September 1979 or later, 
	required for A36, A36TC, and F33A.
  (f) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement for 
	the Foster Air Data AD-511G Area Navigation System dated March 1980 or later 
	required for the Models A36, A36TC, and F33A.
  (g) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement 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 B36TC.

618.   Standby generator power system per applicable Beech Dwg. (14-volt system)
  (a) Airplane Flight Manual Supplement for standby generator dated April 4, 1972, or 
	August 11, 1972, or March 19, 1973, or later, required for V35B and G33.
  (b) Airplane Flight Manual Supplement for standby generator dated April 4, 1972, or 
	August 11, 1972, or March 19, 1973, or later, required for F33A and A36.
  (c) Beech Dwg. 35-3012, Airplane Flight Manual Supplement P/N 35-590118-19, 
	dated March 19, 1973, or later, required for all 35-33 and 33 series, H35 
	through V35B inclusive, 36 and A36 airplanes.

619.   Air conditioner (refrigeration type)  								70 lb. (+ 66)
  (Model A36)  											70 lb. (+ 58)
  Airplane Flight Manual Supplement dated May 2, 1975, or later required for V35B, F33A, and A36 prior to E-2111 except E-1946 and E-2104. Airplane Flight Manual Supplement dated October 1983 or later required for Model A36, S/N E-1946, E-2104, E-2111 and after. Airplane Flight Manual Supplement dated April 1984 or later required for Model B36TC, S/N EA-440 and after.

620.   28-volt standby generator power system installed per applicable Beech drawings
  (a) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement dated October 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 and after.
  (b) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement dated August 1979 or later, required for Model A36TC. Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement dated January 1982, or later, required for B36TC S/N EA-273 through EA-388 except EA-320; dated October 1983 or later required for S/N EA-320, EA-389 and after.

621.   Standby instrument air pressure system per applicable Beech drawings.
  Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement dated April 1984, or later, required for Model A36 S/N E-2180 and after and for Model B36TC S/N EA-435 and after; dated November 1984 or later required for Model F33A S/N CE-1056 and after.

622.   Structural modification per Beech Drawing 35-4016.  						1 lb. (+245)

623.   Loran Navigation Equipment installed per applicable Beech drawings.
  (a) FAA Approved Airplane Flight Manual Supplement for the Bendix/King KLN 88 Loran Navigation System dated October 1990 or later required for the F33A, F33C, A36, and B36TC.

624.   Reduced External Noise Option, factory 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 Gear Extended)
    (+80.4) to (+87.7) at 3600 lb.
    (+74.0) to (+87.7) at 3100 lb. or less
    Straight line variation between points given

Maximum Weight 			3600 lb.

Serial Nos. Eligible			E-2581 and after when properly equipped.

Required Equipment  --  Items 21, (a) and (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 balance report including list of equipment included in certificated empty weight and loading instructions when necessary must be provided for each aircraft at the time of original certification.
  	The certificated empty weight and corresponding center of gravity 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 lb. at +21; except Model 36, A36, A36TC, and B36TC, 3 lb. at +11, with two standard wing fuel tanks unusable fuel of 36 lb. at +79. With two optional wing fuel tanks (Item 111 or 113) unusable fuel of 36 lb. at +79. Installation of auxiliary wing fuel tanks (Item 106) requires inclusion of additional fuel of 5 lb. at +94. 

NOTE 2.   (a) The following placards must be displayed as indicated on all models except 35-C33A, E33A, and E33C (Section XII aircraft) and F33A and F33C (Section XIV aircraft) and G33 (Section XV aircraft) and A36 (Section XIII aircraft) and V35B (Section XI aircraft) and A36TC (Section XVI aircraft) and B36TC (Section XVII aircraft). Placards required in Approved Airplane Flight Manual for G33, F33A S/N CE-409 and after, A36 S/N E-364 and after, V35B S/N D-9391 and after, A36TC, B36TC S/N EA-1 and after, and in Approved Airplane Flight Manual and Airplane Flight Manual Supplement for F33C, S/N CJ-31 and after must be displayed as noted therein. 
  	In full view of pilot:

     "Utility category airplane. Operate in accordance with FAA Approved Airplane Flight Manual. Intentional spins prohibited. No acrobatic maneuvers approved except those listed in the Airplane Flight Manual."   

For S/N D-4866 through D-9068 and S/N CD-1 through 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 S/N D-8612 and CD-1121:

	"WARNING  --  Emergency Airspeed Static Source. See Flight Manual Emergency Procedures for Airspeed Altimeter Calibration Error."

For S/N D-8612 and up, and S/N CD-1121 and up:

	"WARNING  --  Emergency Airspeed Static Source. See Pilot's Check List 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 gallon in each main tank."

(b) The following placards must be displayed as indicated below or as indicated in optional Pilot's Operating Handbook and FAA Approved Airplane Flight Manual or Flight Manual Supplement, Item 403(ax) or Item 403(ay), on Model 35-C33A, E33A, and 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."

  For S/N CE-183 and up:

  For CJ-1 and up:

	"WARNING  --  Emergency Airspeed Static Source- See Pilot's Check List 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 degrees. 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 counter-clockwise as far as possible (50 turns)"

On left hand subpanel:

	"Vent shutoff, pull to close" (35-C33A, E33A, E33C)

	"Firewall air pull off" (F33A, F33C)

  On inner side of baggage compartment door:

	"Baggage Compartment LOAD IN ACCORDANCE WITH WEIGHT 
	AND BALANCE DATA. Maximum structural capacity  	270 lb."

	On inner side of baggage compartment door (when Item 607(c) is installed):

	"No smoking in fifth seat. Maximum fifth seat structural capacity:   170 lb."

On storm window: (35-C33A, E33A, and E33C only)

	"CAUTION  --  Do not open above 145 mph"

In full view of pilot:

    Model 35-C33A (S/N CE-1 through CE-179)
    Model E33A (S/N CE-180 through 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 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."

    Model E33C (S/N CJ-1 through CJ-25)
    Model F33C (S/N CJ-26 through CJ-30)

	"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."

In full view of pilot: (35-C33A, E33A, and 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. (35-C33A, E33A) or 3400 lbs. (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 prohibited.

Airspeed Limitation
  Maximum landing gear extended speed	165 mph (143 knots) (35-C33A, E33A prior to S/N CE-249)
  Maximum landing gear extended speed	175 mph (152 knots) (E33A S/N CE-249 through CE-289 and F33A)
  Maximum design maneuvering speed 	152 mph (132 knots)"
    In full view of pilot:   (E33C) (CJ-1 through 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 lb. 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)

(ACROBATIC CATEGORY ONLY)
ACROBATIC CATEGORY AIRPLANE

  Maximum weight 2800 lb. 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 5 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 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."

    In full view of pilot:   Model E33C (CJ-23 through CJ-25); Model F33C (CJ-26 through CJ-30)

    Note:   CJ-1 through 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.

(UTILITY AND ACROBATIC CATEGORY)

UTILITY CATEGORY AIRPLANE
  Maximum weight 3300 lb. (E33C); 3400 lb. (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 prohibited.

AIRSPEED LIMITATIONS (CAS)
  Maximum landing gear extended speed	175 mph (152 knots)
  Maximum design maneuver speed  	152 mph (132 knots)

(ACROBATIC CATEGORY)
ACROBATIC CATEGORY AIRPLANE

  Maximum weight 2800 lb. 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 5 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)
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."

    In full view of pilot:   Models E33C and 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:   (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 shut-off control:   (35-C33A, E33A, E33C):
      "In case of engine fire pull vent shut-off control to close."

On left-hand side panel near vent shut-off control:   (F33A, F33C):
      "In case of engine fire, pull firewall air control to close."

On cabin door side panel:   (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." (F33A, S/N CE-316 and up)

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 the Models 36 and A36 prior to S/N 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 counter-clockwise as far as possible (50 turns)."

    On left-hand subpanel:

      "Vent shutoff, pull to close." (36) "Firewall Air, pull - off" (A36)
    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:   (36 only)

      "CAUTION  --  Do not open above 145 mph"

 In full view of pilot:
    Model 36 (S/N E-1 through E-184)
    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 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:   (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:   (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 Check List or Flight Manual Emergency Procedures for airspeed and altimeter calibration error."

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 safety belts must wear para   chutes."