# TCDS A-777: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 62
- Revised: November 27, 2017
- Product: Aircraft, Small Airplane
- Certification basis: Part 3, Part 21, CAR 3
- Registered aircraft: 1,537, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/8b/c5/8bc5ca24a7dc93c92ac4abef07661e35699063ded5978780caf0ea389dbc5793
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/71C5912C90480869862581EF0060D024.0001
- Page: https://openairdocs.org/tcds/A-777

## Models (9)

As the data sheet lists them.

- G35
- A35
- D35
- 35R
- B35
- C35
- F35
- 35
- E35

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 
Rev. No. 62 55 55 55 56 55 56 55 56 56 56 54 
Page No. 13 14 15 16 17 18 19 20 21 22 23 24 
Rev. No. 54 54 54 54 54 56 56 54 56 54 55 61 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 A-777  
 Revision 62  
 Textron Aviation   
 35   
A35 E35  
B35 F35   
C35 G35   
D35 35R   
 November 27, 2017  
 
TYPE CERTIFICATION DATA SHEET NO. A-777 
 
This data sheet which is a part of Type Certificate No. A-777 prescribes conditions and limitations under which the product for which 
the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder Textron Aviation Inc. 
 One Cessna Boulevard 
 Wichita, Kansas 67215 
 
Type Certificate Holder Record Beech Aircraft Corporation transferred to 
 Raytheon Aircraft Company on April 15, 1996 
 
 Raytheon Aircraft Company transferred to 
 Hawker Beechcraft Corporation on March 26, 2007 
 
 Hawker Beechcraft Corporation transferred to  
 Beechcraft Corporation on April 12, 2013 
 
 Beechcraft Corporation transferred to  
 Textron Aviation Inc. on October 12, 2016 
 
 
I. Model 35, Bonanza, 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved March 25, 1947 
 
 Engine Continental E-185-1  (See Item 111 for optional engine.) 
 
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff (one minute) 2300 rpm (185 hp) 
  For all other operations 2050 rpm (165 hp) 
 
 Airspeed Limits Maneuvering   130 mph (113 knots)  True Ind. 
  Maximum structural cruising   160 mph (139 knots)  True Ind. 
  Never exceed   202 mph (176 knots)  True Ind. 
  Flaps extended   100 mph (  87 knots)  True Ind. 
  Landing gear extended   100 mph (  87 knots)  True Ind.

A-777 2 Rev. 62 
 
I. Model 35  (cont'd) 
 
 C.G. Range (landing Normal Category: (+82.4) to (+84.8) at 2550 lb. 
   gear extended)  (+80.2) to (+85.4) at 2405 lb. 
   (+76.2) to (+85.4) at 2140 lb. or less 
  Utility Category: (+76.8) to (+78.6) at 2100 lb. 
   (+76.3) to (+78.8) at 1971 lb. 
   (+76.3) to (+78.9) at 1938 lb. or less 
  Straight line variation between points given. 
 
  
76 78 80 82 84 86
1900
2000
2100
2200
2300
2400
2500
2600
NORMAL
CATEGORY
UTILITY
CATEGORY
INCHES
POUNDS  
 Empty Weight C.G. Range None 
 
 Maximum Weight Normal Category: 2550 lbs. 
  Utility Category: 2100 lbs. 
 
 No. of Seats 4 (2 at +86, 2 at +116) 
 
 Maximum Baggage Normal Category: 120 lb. at +139.  When Item 107 installed, baggage 
   arm is +145 and total weight of fuel and baggage must 
   not exceed 120 lb. 
  Utility Category: None 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R main 20 ea. 17 ea. (+75) 
 
   Optional Fuel System (Item 107) 
  Fuselage Aux. Systems 20 19.5 (+132) 
     or (+133) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt. (+45).  See Items 106 and 108 for optional oil tanks and NOTE 1 for 
  data on unusable oil. 
 
 Control Surface Movements Wing flaps   Down 20 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up 10 Down 30 
  "V" tail elevator action Up 20 Down 30 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maxim combination Up 35 Down 35 
    rudder elevator action

Rev. 62 3 A-777 
 
I. Model 35   (cont'd) 
 
 Serial Nos Eligible D1 through 1500 
 
 Required Equipment Items 1, 101, 102, 103, 201, 202, 301, 302, 404(a) and (n) or 404(x), 601(a).  
  Airplanes are eligible for certification with either fabric covered or magnesium 
  flaps and ailerons provided they are installed in pairs, i.e., 2 fabric covered 
  ailerons or 2 magnesium ailerons, etc. 
 
 
II. Model A35, Bonanza, 4 PCLM (Utility Category), Approved July 15, 1948 
 
 Engine Continental E-185-1 (see Item 111 for optional engine) 
 
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff (one minute) 2300 rpm (185 hp) 
  For all other operations 2050 rpm (165 hp) 
 
 Airspeed Limits Maneuvering   130 mph  (113 knots)  True Ind. 
  Maximum structural cruising   160 mph  (139 knots)  True Ind. 
  Never exceed   202 mph  (176 knots)  True Ind. 
  Flaps extended   105 mph  (  91 knots)  True Ind. 
  Landing gear extended   125 mph  (109 knots)  True Ind. 
 
 C.G. Range (landing gear (+83.7) to (+84.4) at 2650 lb. 
   extended) (+80.0) to (+85.4) at 2405 lb. 
  (+75.9) to (+85.4) at 2140 lb. or less 
  Straight line variation between points given. 
  The aft C.G. limit for all weights must be limited to (+84.4) unless 
  the elevator cambered tabs, P/N 35-660040-52 and -53 are installed. 
  (Refer to AD-50-42-1. 
 
76 78 80 82 84 86
1900
2000
2100
2200
2300
2400
2500
2600
POUNDS
AFT
LIMIT
FRONT
LIMIT
 
  INCHES 
 Empty Weight C.G. Range None 
 
 Maximum Weight 2650 lbs. 
 
 No. of Seats 4 (2 at +86, 2 at +116)

A-777 4 Rev. 62 
 
II. Model A35   (cont'd)  
 
 Maximum Baggage 270 lb.  (+139).  For Model A35 refer to Loading Chart (included in the  
  Airplane Flight Manual) for loading instructions.  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) 
  Item 107, if installed, must also be removed. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R Main 20 ea. 17 ea. (+ 75) 
   Optional Fuel System (Item 107 
  Fuselage Aux. Sys. 20 19.5 (+132) 
      or (+133) 
  See NOTE 1 for data on unusable fuel. 
  
 Oil Capacity 10 qt.  (+45).  See Items 106 and 108 for optional oil tanks and 
  NOTE 1 for data on unusable oil. 
 
 Control Surface Movements Wing flaps   Down 20 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up 10 Down 30 
  "V" tail elevator action Up 20 Down 20 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 35 
    rudder elevator action 
 
 Serial Nos. Eligible D-1501 through D-2200 and D-15001 
 
 Required Equipment Items 1, 101, 102, 103, 201, 202, 301, 302, 404(b) and (n) or 404(v), 601(a)  
 
 
III. Model B35, Bonanza, 4 PCLM (Utility Category), Approved December 28, 1949 
 
 Engine Continental E-185-8 with S/N 5122D and On (see Engine Spec. E-246) 
  (See also Item 111 for optional engine.) 
 
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff (one minute) 2450 rpm. (196 hp) 
  For all other operations 2050 rpm. (165 hp) 
 
 Airspeed Limits Maneuvering   130 mph. (113 knots)  True Ind. 
  Maximum structural cruising   160 mph. (139 knots)  True Ind. 
  Never exceed   202 mph. (176 knots)  True Ind. 
  Flaps extended   105 mph. (  91 knots)  True Ind. 
  Landing gear extended   125 mph. (109 knots)  True Ind. 
 
 C.G. Range (landing (+83.7) to (+84.4)  at  2650 lb. 
   gear extended) (+80.0) to (+85.4)  at  2405 lb. 
  (+75.9) to (+85.4)  at  2140 lb. or less 
  For diagram see Section II. 
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 2650 lb. 
 
 No. of Seats 4 (2 at +86, 2 at +116)

Rev. 62 5 A-777 
 
III. Model B35  (cont'd) 
 
 Maximum Baggage 270 lb. (+139).  For Model B35 refer to Loading Chart (included in the  
  Airplane Flight Manual) for loading instructions.  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) 
  Item 107, if installed, must also be removed. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R Main 20 ea. 17 ea. (+ 75) 
 
    Optional Fuel System (Item 107) 
  Fuselage Aux. Sys. 20 19.5 (+132) 
      or (+133) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt.  (+36) 
  See NOTE 1 for data on unusable oil. 
 
 Control Surface Movements Wing flaps   Down 30 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up 10 Down 31 
  "V" tail elevator action Up 20 Down 20 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 35 
    rudder elevator action 
 
 Serial Nos. Eligible D-2201 through D-2680 
 
 Required Equipment Items 1, 101, 103, 113, 201, 202, 301, 302, 404(c) and (n) or 404(v).  
 
 
IV. Model C35, Bonanza, 4 PCLM (Utility Category), Approved January 16, 1951 
 
 Engine Continental E-185-11 with S/N 5122D and On (see Engine Spec. E-246) 
  See also Item 111 for optional engine. 
  
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff (one minute) 2600 rpm  (205 hp) 
  For all other operations 2300 rpm (185 hp) 
 
 Airspeed Limits Maneuvering 130 mph (113 knots)  True Ind. 
  Maximum structural cruising 160 mph (139 knots)  True Ind. 
  Never exceed 202 mph (176 knots)  True Ind. 
  Flaps extended 105 mph (  91 knots)  True Ind. 
  Landing gear extended 125 mph (109 knots)  True Ind.

A-777 6 Rev. 62 
 
IV. Model C35   (cont'd) 
 
 C.G. Range (landing (+82.9) to (+84.4) at 2700 lb. 
   gear extended) (+80.1) to (+85.4) at 2500 lb. 
  (+76.5) to (+85.4) at 2240 lb. or less 
 
76 78 80 82 84 86
2100
2200
2300
2400
2500
2600
2700
2800
POUNDS AFTLIMIT
FRONT
LIMIT
 
    INCHES 
 Empty Weight C.G. Range None 
 Maximum Weight 2700 lb. 
 
 No. of Seats 4 (2 at +86, 2 at +116) 
 
 Maximum Baggage 270 lb. (+139).  For Model C35 refer to Loading Chart (included in the Airplane  
  Flight Manual) for loading instructions.  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) 
   Item 107, if installed, must also be removed. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R main 20 ea. 17 ea. (+75) 
    Optional Fuel System  (Item 107) 
  Fuselage Aux. System 20  19.5  (+132) 
       or (+133) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt.  (+36) 
  See NOTE 1 for data on unusable oil. 
 
 Control Surface Movements Wing flaps   Down 30 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up   8 Down 31 
  "V" tail elevator action Up 22.5 Down 17.5 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 30 
    rudder elevator action 
 
 Serial Nos. Eligible D-2681 through D-3400 (except D-3293) 
 
 Required Equipment Items 1, 101, 103, 113, 201, 202, 301, 302, 404(u), 601(b), 608.

Rev. 62 7 A-777 
 
V. Model 35R, Bonanza, 4 PCLM  (Utility Category), Approved June 6, 1951 
 
 Engine Continental E-185-8 with S/N 5122D and On (see Engine Spec. E-246). 
  (See also Item 111 for optional engine.) 
 
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff (one minute)  2450 rpm (196 hp) 
  For all other operations  2050 rpm (165 hp) 
 
 Airspeed Limits Maneuvering  130 mph  (113 knots) True Ind. 
  Maximum structural cruising 160 mph  (139 knots) True Ind. 
  Never exceed  202 mph  (176 knots) True Ind. 
  Flaps extended  105 mph  (  91 knots) True Ind. 
  Landing gear extended  125 mph   (109 knots) True Ind. 
 
 C.G. Range (landing (+83.7)  to  (+84.4)  at  2650 lb. 
   gear extended) (+80.0)  to  (+85.4)  at  2405 lb. 
  (+75.9)  to  (+85.4)  at  2140 lb. or less 
  For diagram see Section II. 
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 2650 lb. 
 
 No. of Seats 4 (2 at +86,  2  at  +116) 
 
 Maximum Baggage 270 lb. (+139).  Load in accordance with loading chart in Airplane Flight Manual. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R main 20 ea. 17 ea. (+75) 
    Optional Fuel System  (Item 107) 
  Fuselage Aux. System 20  19.5  (+132) 
       or (+133) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt.  (+36) 
  See NOTE 1 for data on unusable oil. 
 
 Control Surface Movements Wing flaps   Down 30 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up 10 Down 31 
  "V" tail elevator action Up 20 Down 20 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 35 
    rudder elevator action 
 
 Serial Nos Eligible D-25R1 and on (note that the "D-25" is the retained original Model 35 
  S/N and the number following the "R" designation is the numerical order of 
  modification.  All Model 35 (Section I) S/N's are eligible for modification by 
  Beech Aircraft Corporation in accordance with Beech Dwg. 35-000009. 
 
 Required Equipment Items 1, 101, 103, 113, 201, 202, 301, 404(e)  and (n) or 404(v) and (w), 601(b). 
 
 
VI. Model D35, Bonanza, 4 PCLM (Utility Category), Approved January 5, 1953 
 
 Engine Continental E-185-11 with S/N 5122D and above (see Engine Spec. E-246) 
  (See also Item 111 for optional engine.) 
 
 Fuel 80 min. grade aviation gasoline

A-777 8 Rev. 62 
 
VI. Model D35   (cont'd) 
 
 Engine Limits Takeoff (one minute)  2600 rpm  (205 hp) 
  For all other operations  2300 rpm  (185 hp) 
 
 Airspeed Limits Maneuvering    130 mph  (113 knots)  True Ind. 
  Maximum structural cruising   160 mph  (139 knots)  True Ind. 
  Never exceed    202 mph  (176 knots)  True Ind. 
  Flaps extended    105 mph  (  91 knots)  True Ind. 
  Landing gear extended    125 mph  (109 knots)  True Ind. 
 
 C.G. Range (landing (+83.2)  to  (+84.3)  at 2725 lb. 
   gear extended) (+80.1)  to  (+85.4)  at 2500 lb. 
  (+76.5)  to  (+85.4)  at 2240 lbs. or less 
 
76 78 80 82 84 86
2100
2200
2300
2400
2500
2600
2700
2800
INCHES
POUNDS AFT
LIMIT
FRONT
LIMIT
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 2725 lbs. 
 
 No. of Seats 4 (2 at +86, 2 at +116) 
 
 Maximum Baggage 270 lb. (+139).  For Model D35 refer to the Loading Chart  (included in Airplane 
  Flight Manual) for loading instructions.  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) 
  Item 107, if installed, must also be removed. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R main 20 ea. 17 ea. (+75) 
    Optional Fuel System (Item 107) 
  Fuselage Aux. System 20  19.5  (+132) 
       or (+133) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt.  (+36) 
  See NOTE 1 for data on unusable oil.

Rev. 62 9 A-777 
 
VI. Model D35   (cont'd) 
 
 Control Surface Movements Wing flaps   Down 30 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up   8 Down 31 
  "V" tail elevator action Up 22.5 Down 17.5 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 30 
    rudder elevator action 
 
 Serial Nos Eligible D3401 through D3698 
 
 Required Equipment Items 1, 101, 103, 113, 201, 202, 301, 302, 404(t), 601(b), 608.  
 
 
VII. Model E35, Bonanza, 4 PCLM (Utility Category), Approved January 15, 1954 
 
 Engine Continental E-185-11 with S/N 5122D and On (see Engine Spec. E-246) 
  (See also Item 111 for optional engine.) 
 
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff (one minute)  2600 rpm  (205 hp) 
  For all other operations  2300 rpm  (185 hp) 
 
 Airspeed Limits Maneuvering    130 mph  (113 knots)  True Ind. 
  Maximum structural cruising   175 mph  (152 knots)  True Ind. 
  Never exceed    202 mph  (176 knots)  True Ind. 
  Flaps extended    105 mph  (  91 knots)  True Ind. 
  Landing gear extended    125 mph  (109 knots)  True Ind. 
 
 C.G. Range (landing (+83.2)  to  (+84.9)  at 2725 lb. 
   gear extended) (+80.1)  to  (+85.7)  at  2500 lb. 
  (+76.5)  to  (+85.7)  at  2240 lb. or less 
 
76 78 80 82 84 86
2100
2200
2300
2400
2500
2600
2700
2800
INCHES
POUNDS AFT
LIMIT
FRONT
LIMIT
 
 Empty Weight C.G. Range None

A-777 10 Rev. 62 
 
VII. Model E35   (cont'd) 
 
 Maximum Weight 2725 lb. 
 
 Number of Seats 4  (2 at +86, 2 at +118) 
 
 Maximum Baggage 270 lb.  (+140).  For Model E35 refer to the Loading Chart (included in the  
  Airplane Flight Manual) for loading instructions.  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) 
   Item 107, if installed, must also be removed. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R main 20 ea. 17 ea. (+75) 
    Optional Fuel System  (Item 107) 
  Fuselage Aux. System 20  19.5  (+132) 
       or (+133) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt.  (+36) 
  See NOTE 1 for data on unusable oil. 
 
 Control Surface Movements Wing flaps   Down 30 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up   8 Down 31 
  "V" tail elevator action Up 22.5 Down 17.5 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 30 
    rudder elevator action 
 
 Serial Nos Eligible D-3293 and D-3699 through D-3998 
 
 Required Equipment Items 1, 101, 103, 113, 201, 202, 301, 302, 404(r), 601(b), 608.  
 
 
VIII. Model F35, Bonanza, 4 PCLM (Utility Category), Approved January 5, 1955 
 
 Engine Continental E-185-11 with S/N 5122D and On  (see Engine Spec. E-246) 
   (See also Item 111 for optional engine.) 
 
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff  (one minute)  2600 rpm  (205 hp) 
   For all other operations  2300 rpm  (185 hp) 
 
 Airspeed Limits Maneuvering    130 mph  (113 knots)  True Ind. 
   Maximum structural cruising   175 mph  (152 knots)  True Ind. 
   Never exceed    202 mph  (176 knots)  True Ind. 
   Flaps extended (normal)   105 mph  (  91 knots)  True Ind. 
   Landing gear extended (normal)   125 mph  (109 knots)  True Ind.

Rev. 62 11 A-777 
 
VIII. Model F35   (cont'd) 
 
 C.G. Range (landing gear (+83.2)  to  (+85.1)  at 2750 lbs. 
   extended) (+80.1)  to  (+85.7)  at 2525 lbs. 
   (+76.5)  to  (+85.7)  at 2265 lbs. or less 
 
76 78 80 82 84 86
2100
2200
2300
2400
2500
2600
2700
2800
INCHES
POUNDS AFT
LIMIT
FRONT
LIMIT
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 2750 lb. 
 
 No. of Seats 4 (2 at +86, 2 at +118) 
 
 Maximum Baggage 270 lb.  (+140).  For weight and balance information refer to FAA Approved 
   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) 
    Item 107, if installed, must also be removed. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
  L & R main 20 ea. 17 ea. (+75) 
    Optional Fuel System (Item 107 and 122) 
  Fuselage Aux. System 20  19.5  (+132) 
       or (+133) 
  Win Aux. System. 20  19  (+  94) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt.  (+36) 
  See NOTE 1 for data on unusable oil. 
 
 Control Surface Movements Wing flaps   Down 30 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up   8 Down 31 
  "V" tail elevator action Up 22.5 Down 17.5 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 30 
    rudder elevator action 
 
 Serial Nos Eligible D-3999 through D-4391 (except D-4376) 
 
 Required Equipment Items 1, 101, 103, 113, 201, 202, 301, 302, 404(s), 601(b), 608.

A-777 12 Rev. 62 
 
IX. Model G35, Bonanza, 4 PCLM (Utility Category), Approved December 1, 1955 
 
 Engine Continental E-225-8 with S/N 30087 and On (see Engine Spec. E-246) 
 
 Fuel 80 min. grade aviation gasoline 
 
 Engine Limits Takeoff (one minute)  2650 rpm  (225 hp) 
   For all other operations  2300 rpm  (185 hp) 
 
 Airspeed Limits Maneuvering    130 mph  (113 knots)  True Ind. 
   Maximum structural cruising   175 mph  (152 knots)  True Ind. 
   Never exceed    202 mph  (176 knots)  True Ind. 
   Flaps extended (normal)   120 mph  (104 knots)  True Ind. 
   Landing gear extended (normal)   140 mph  (122 knots)  True Ind. 
 
 C.G. Range (landing gear (+83.2)  to  (+85.1)  at  2775 lb. 
   extended) (+79.9)  to  (+85.7)  at  2525 lb. 
   (+76.5)  to  (+85.7)  at  2265 lb. or less 
 
76 78 80 82 84 86
2100
2200
2300
2400
2500
2600
2700
2800
INCHES
POUNDS AFT
LIMIT
FRONT
LIMIT
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 2775 lb. 
 
 No. of Seats 4 (2 at +86, 2 at +118) 
 
 Maximum Baggage 270 lb.  (+140).  For weight and balance information refer to FAA Approved 
   Flight Manual.  With rear seat removed for cargo, maximum baggage is as 
   follows: 
 
    Aft of spar cover   270 lb.  (+125) 
    On and forward of spar cover  200 lb.  (+108) 
    Item 107, if installed, must also be removed. 
 
 Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
   L & R Main 20 ea. 17 ea. (+  75) 
     Optional Fuel System (Item 107 and 122) 
   Fuselage Aux. System 20 19.5 (+132) 
       or (+133) 
   Wing. Aux. System 20 19  (+  94) 
   See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 10 qt.  (+36) 
   See NOTE 1 for data on unusable oil.

Rev. 62 13 A-777 
 
IX. Model G35   (cont'd) 
 
 Control Surface Movements Wing flaps   Down 30 
  Aileron tab   Fixed 
  Aileron Up 20 Down 20 
  Elevator tab Up   8 Down 31 
  "V" tail elevator action Up 22.5 Down 17.5 
  "V" tail rudder action Up 21 Down 21 
  "V" tail maximum combination Up 35 Down 30 
    rudder elevator action 
 
 Serial Nos Eligible D-15002, D-4376 and D-4392 through D-4865 
 
 Required Equipment Items 1, 101, 103, 113, 201, 202, 301, 302, 404(q), 601(b), 608.  
 
 
Specifications Pertinent to All Models 
 
Datum  83.1 inches forward of the jack pads on the front spars. 
 
Leveling Means (Models 35, A35, B35, C35, 35R) Leveling plates inside baggage door. 
   (Models D35, E35, F35, G35) Two external screws in bulkhead aft of 
   baggage compartment on left side.  (Use plumb bob). 
 
Certification Basis Part 03 of the Civil Air Regulations effective November 13, 1945. Type Certificate No. 777 
issued March 25, 1947.  Application for Type Certificate dated June 20, 1945.  Repair and 
alteration data may be approved under delegation option procedures of Federal Aviation 
Regulations 21. 
 
Production Basis (all models) Production Certificate No. 8.  Original airworthiness certificates for airplanes with S/N's  
   D-3551 through D-4865 and D-15002 were issued under delegation option provisions of  
   FAR 21. 
 
Required Equipment A plus (+) or minus (-) sign preceding the weight of an item of equipment indicates net weight 
change when that item is installed. Approval for the installation of all items of equipment 
listed herein has been obtained by the aircraft manufacturer except those items preceded by an 
asterisk (*).  This symbol denotes that approval has been obtained by someone other than the 
aircraft manufacturer.  An item so marked may not have been manufactured under an FAA 
monitored or approved quality control system.  Conformity must be determined if the item is 
not identified by a Form FAA-186, PMA or other evidence of FAA production approval.  An 
item preceded by two asterisks (**) indicates approval under delegation option provisions of 
Part 21 of the Federal Aviation Regulations. 
 
Propeller and Propeller Accessories (excepting Deicing Equipment) 
 1. Beech controllable propeller 
  (a) Hub R203-100, blades R201-217-88 (eligible on Models 35, A35) 67 lb. (+  2) 
   For interchangeable blade models, see Propeller Spec. P-807.  (Note 6) 
   Diameter:  not over 88 in., not under 86-1/4 in. 
   Static rpm at maximum permissible throttle setting (no additional tolerance permitted): 
    Not over 1925, not under 1825 
   Pitch settings at 33 in. sta.: 
    Low 13 high - not under 26 
 or (d) Hub B200-100, blades B200-88 (eligible on Models 35, A35, B35, 35R) 56 lb. (+  2) 
   For interchangeable blade models, see Propeller Spec. P-867  (Note 6) 
   Diameter:  not over 88 in., not under 86-1/4 in. 
   Static rpm at maximum permissible throttle setting (no additional tolerance permitted): 
    Not over 1950, not under 1850, or not over 2020, not under 1920  
   Pitch settings at 33 in. sta.: 
    Low 13, high - not under 26, or low 12, high not under 26 
   Only airplanes with engines having S/N 5122D and above are eligible to use 12 low 
    pitch and 2020-1920 static rpm range  (see Engine Spec. E-246)

A-777 14 Rev. 62 
 
Specifications Pertinent to All Models (cont’d) 
 
Propeller and Propeller Accessories (excepting Deicing Equipment) (cont’d) 
 or (e) Hub 215-109, blades 215-207-88 (eligible on Models 35, A35, B35, C35, D35,  67 lb. (+  2) 
     E35, F35, 35R).  Also see Item 111(d) for E-225-8 engine eligibility). 
   Diameter:  (All models eligible except C35) not over 88 in., not under 86-1/4 in. 
     (Model C35) not over 88 in., not under 86 in. with E185 engines having S/N below  
     22183 or not under 84 in. with E185 engines having S/N 22183 and above.  
   Static rpm at max. permissible throttle setting (no additional tolerance permitted): 
     Models 35, A35, B35, 35R) not over 2040, not under 1940 or not over 2165, not  
     under 2065.  (Models D35, E35, F35) not over 2230,not under 2130.  (Model C35  
     with 88 in. prop.) not over 2230, not under 2130.  (Model C35 with 84 in. prop.)  
     not over 2250, not under 2150. 
   Pitch settings at 33 in. sta.:  (Models 35, A35, B35, 35R) low 16, high - not under 
     30 or low 15, high - not under 30 
     (Models D35, E35, F35) low 13, high - not under 30 
     (Model C35 with 88 in. diam. prop.) low 13 , high - not under 30 
     (Model C35 with 84 in. diam. prop.) low 13-3/4, high - not under 30 
   Only Models 35, A35, B35 and 35R airplanes with engines having S/N 5122D and above  
     are eligible to use 15 low pitch and 2165-2065 rpm range (see Engine Spec. E-246). 
 
 or (f) Hub 215-109, blades 215-213-84 (eligible on Models A35, B35, C35, D35, E35, 67 lb. (+  2) 
   F35 and G35 with E-225-8 engines having S/N 30087 and above)  (See Items 111(b) 
   and (d). 
   For interchangeable blade models, see Propeller Spec. P-873 (Note 6) 
   Diameter: not over 84 in., not under 84 in. (Models C35, D35) 
     not over 84 in., not under 82 in.  (Models A35, B35, E35, F35, G35)  
   Static rpm at max. permissible throttle setting (no additional tolerance permitted): 
    not over 2380, not under 2280 
   Pitch settings at 33 in. sta.:  low 12-1/2, high - not under 29-1/2 
 
 and (b) Pitch control motor installation 5 lb. (+23) 
      or  (+  8) 
 
 and (c) Propeller spinner 3 lb. (+  0) 
 
 or (g) Hub 215-109, blades 215-213-84 (eligible on Models C35, D35, and 67 lb. (+  2) 
   F35 with E-185-11 engines having S/N 22183 and above).  For interchangeable 
   blade models, see Propeller Spec. P-873 (Note 6) 
   Diameter: not over 84 in., not under 82 in.  (Model F35)  
     not over 84 in., not under 84 in.  (Models C35, D35)  
   Static rpm at maximum permissible throttle setting:  not over 2250, not under 2150.  
    No additional tolerance permitted. 
   Pitch settings at 33 in. sta.: 
    Low 13-3/4, high - not under 30 
 
 2. Beech constant speed propeller (eligible on Models 35, A35, B35, C35, D35, E5, 35R)  58 lb. (+  2) 
  (a) Hub B200-105, blades B200-220-88 (includes Beech B200-236 hydraulic motor). 58 lb.  (+  2) 
   For interchangeable blade models, see Propeller Spec. P-867  (Note 6). 
   Diameter:  not over 88 in., not under 86-1/4 in. 
   Pitch settings at 33 in. sta.: 
     Low 8.5, high - not under 25 
 or (e) Hub 215-112, blades 215-207-88 (includes Beech B200-236 (hydraulic motor) 69 lb. (+  2) 
   Diameter:  not over 88 in., not under 86 in. with E-185 engines having S/N below 22183 
   or not under 84 in. with E-185 engines having S/N 22183 and above. 
   Pitch settings at 33 in. sta.: 
     Low 12, high - not under 30 
 and (b) Propeller governor installation (includes Beech B200-237 governor and B200-238  7 lb. (+39) 
   adapter or B200-239 governor  (required with (e)). 
 and (c) Propeller spinner (Beech 35-960026)    3 lb. (+  0)

Rev. 62 15 A-777 
 
Specifications Pertinent to All Models (cont’d) 
 
Propeller and Propeller Accessories (excepting Deicing Equipment) (cont’d) 
 3. Constant speed propeller 
  *(a) Hub B200-100, blades B200-220-88 (eligible on Models 35, A35, B35, 35R).  56 lb. (+  2) 
   For interchangeable blade models, see Propeller Spec. P-867 (Note 6). 
   Diameter:  not over 88 in., not under 86-1/4 in. 
   Pitch settings at 33 in. sta.: 
     Low 9.5, high - not under 26  (Models 35, A35) 
     Low 8-1/2, high - not under 25  (Model B35) 
 or *(e) Hub R203-100, blades R201-217-88 (eligible on Models 35 and A35);  67 lb.(+  2) 
   For interchangeable blade models, see Propeller Spec. P-807   (Note 6). 
   Diameter: not over 88 in., not under 86-1/4 in. 
   Pitch settings at 33 in. sta.: 
    Low 9.5, high - not under 22.5 
 or (f) Hub 215-107, blades 215-207-88 (eligible on Models 35, A35, B35, C35, D35,   67 lb. (+  2) 
   E35, F35, 35R and G35.  (See also Item 111(d) for E-225-8 engine eligibility). 
   Diameter: not over 88 in., not under 86 in. with E -225 engines with S/N 30087 
   and above. 
   Pitch settings at 33 in. sta.: 
    Low 11, high - not under 30 
 or (g) Hub 215-107, blades 215-213-84 (eligible on Models A35, B35, C35, D35, E35,  67 lb. (+  2) 
   F35, G35 with E-225-8 engines having S/N 30087 and above - see Items 111(b) and 
   (d), and on Models C35, D35, F35 with E-185-11 engines having S/N 22183 and above). 
   For interchangeable blade models, see Propeller Spec. P-873  (Note 6) 
   Diameter:  not over 84 in., not under 82 in.  (Models A35, B35, E35, F35, G35)  
    Not over or under 84 in.  (Models C35, D35)  
   Pitch settings at 33 in. sta.: 
    Low 11-1/2, high not under 30 
 and (b) Propeller governor (including Flight Research Engineering Corp. automatic propeller  7 lb. (+59) 
   control Model 31A) installation to be accomplished per Flight Research Dwg. 31-175. 
 and (c) Propeller spinner      3 lb. (+  0) 
 and (d) Pitch control motor installation     5 lb. (+23) 
   Approved Airplane Flight Manual, Item 404 dated October 11, 1950, required   or (+  8) 
   when Item 3(f) installed.  Flight Research Airplane Flight Manual Supplement dated 
   July 20, 1950, must be appended to Approved Airplane Flight Manual, Item 404 or 
   Approved Airplane Flight Manual, Item 404 dated October 11, 1950, required when  
   Items 3(a) or (e) installed. 
 
 *4. Hartzell controllable propeller (eligible on Models 35, A35)   69 lb. (+  2) 
  (installation per Hartzell Dwg. B-1121) 
  Hub HC-12x20-7B blades, 8433-0 (includes propeller control valve and installation components). 
  Diameter:  not over 84 in., not under 82-1/2 in. 
  Static rpm at maximum permissible throttle setting:  (no additional tolerance permitted): 
    not over 2050, not under 2000 
  Pitch settings at 30 in. sta.:  Low 16-1/2, high 27 
  Counterweight length, 4-1/8 in. 
  Only airplanes with engines having silver main thrust bearings, CMC P/N 40644, eligible for 
    this propeller installation.  Hartzell Airplane Flight Manual Supplement dated July 1, 1949, 
    must be appended to Approved Airplane Flight Manual , Item 404, when this propeller 
    is installed. 
 
 *5. Hartzell constant speed propeller (eligible on Models 35, A35, B35) (installation per Hartzell  
  Installation Instruction No. 1 dated October 25, 1950, revised August 22, 1951, and Hartzell  
  Dwg. B-161 and B-145) 
  (a) Hub HC-12x20-7C, blades 8433-0    69 lb. (+  2) 
   Diameter:  not over 84 in., not under 82-1/2 in. 
   Pitch settings at 30 in. sta.: 
    Low 11, high 25 
   Counterweight length 4-1/8 in. 
   Only airplanes with engines having silver main thrust bearings, CMC P/N 40644 
   eligible for this propeller installation.

A-777 16 Rev. 62 
 
Specifications Pertinent to All Models (cont’d) 
 
Propeller and Propeller Accessories (excepting Deicing Equipment) (cont’d) 
 and (b) Governor installation includes Hartzell Model A-1 governor and C-137-1 Tee drive.  7 lb. (+  42) 
   Hartzell Airplane Flight Manual Supplement dated August 22, 1951, must be appended 
   to Approved Flight Manual, Item 404, when this propeller installed. 
 
 *6. Hartzell constant speed propeller (eligible with Item 111(c) only) 
  (a) Hub HC-12x20-1, blades 9333C-3    64 lb. (+  0) 
   Diameter: not over 90 in., not under 88-1/8 in. 
   Pitch settings at 34 in. sta.: 
    Low 15, high 35 
  (b) Propeller spinner, Hartzell      6 lb. (+  9) 
 and (c) Hamilton Standard 1Q12-G1 propeller governor    5 lb. (+  9) 
 
Engines and Engine Accessories - Fuel and Oil Systems 
 101. Fuel pumps 
  (a) Deleted May 20, 1948 
  (b) Engine-driven, Romec RD-7750, RD-7750-1, RD-7790, RD-7420, RD-7420B or RD-7420C 1 lb. (+40) 
 or (e) Engine-driven, Thompson TF-1100-M2, TF-1100-2 or TF-1900   1 lb. (+40) 
 and (c) Wobble-Saval No. 5262      2 lb. (+74) 
 or (d) Wobble-Beech 35-921171 or 35-924065 or 35-924230, 35-924065   2 lb. (+74) 
   or 35-924230 required in Models A35, B35 and C35.  35 -942430 required in Models D35, 
   E35, F35, G35 and 35R.  When 35-924230 installed, Beech Airplane Flight Manual 
   Supplement No.1 dated July 28, 1951, must be appended to Approved Airplane Flight 
   Manual, Item 404, if manual is dated earlier than May 2, 1951.   
 
 102. Oil radiator - Harrison 8513295     10 lb.(+37) 
 
 103. Carburetor air cleaner      1 lb. (+11) 
 
 104. Vacuum pump - ARO A51DA or A-513DB or Pesco 3P-194-F   4 lb. (+37) 
 
 105. Starter 
  (a) Delco-Remy 1190658 (with CMC E-185-1 engine only)   15 lb. (+41) 
  (b) Delco-Remy 1109660 (with CMC E-185-1 engine only)   21 lb. (+42) 
  (c) Beech 35-369005 (with CMC E-185-8 or -11 engine only)   18 lb. (+42) 
  *(d) Precision Machine Works E-80-1001 (with CMC-E-185-8 engine only)  18 lb. (+42) 
  (e) Eclipse type 36E14 or 36E14-1-C (with CMC E-185-8 or -11 or E-225-8 engines only)  19 lb. (+42) 
  *(f) Eclipse type E80-13B (with Item 111(c) only)    19 lb. (+43) 
  (g) Eclipse E80 Type 397 Model 13 with mounting pad modified per Beech 
   Dwg. 35-369005 and clutch setting 200 ft.-lb. (with CMC E-225-8 engine 
   only) equivalent to CMC P/N 530983.  Models 35, 35R, A35, B35, C35, D35  
   (S/N's D-3401 through D-3550) 
 
 106. Oil cooler tank (Beech 35-929013) replacing Item 102 and standard oil tank.  -9 lb. (+35) 
  Arm of oil is +43.  See Note 1 for data on unusable oil. 
 
 107. 20 gal. auxiliary fuel tank.  When this item is installed in Model 35, baggage arm is +145  17 lb. (+132) 
  and weight of baggage and fuel must not exceed 120 lb.  See Note 1 for data on unusable fuel.  or (+133) 
 
 108. Oil cooler tank (Beech 35-929144, 35-939160, 35-939164 or 35-939172) replacing Item 102  -10 lb. (+32) 
  and standard oil tank.  Arm of oil is +36.  See Note 1 for data on unusable oil. 
   
 109. Fuel booster pump installation - includes Adel 20653 (with suffix "H" or later revision  6 lb. (+57) 
  letter in serial number or 1/8 red band around pump body) or Thompson TF-36700 electric 
  fuel pump.  (Thompson TF-1900 or Romec R-7420B engine-driven fuel pump required 
  with this item.) 
 
 110. Winterization equipment 
  (a) Engine cooling air inlet baffle, Beech 35-910277 (for airplanes with Item 108)  1 lb. (+10) 
  (b) Oil cooler tank valve, Beech 35-090076 (for airplanes with Item 106)   2 lb. (+45)

Rev. 62 17 A-777 
 
Specifications Pertinent to All Models (cont’d) 
 
Engines and Engine Accessories - Fuel and Oil Systems  (cont’d) 
 111. Engine 
  (a) VMV R-185-8 or -11 (same limits as for E-185-1 or -8 in specific airplane model). Use actual weight 
   Installation E-185-11 in Models 35 and A35 will require rework of engine mounts 
   in accordance with Beech instructions. 
  (b) Continental E-225-8 with S/N 30087 and up (see Engine Spec. E-267 replacing 
   E-185-11 in Model E35 or F35 only. 
   Engine limits: Takeoff (one minute), 2650 rpm  (225 hp) 
      For all other operations, 2300 rpm  (185 hp)  
   Fuel:  80 min. grade aviation gasoline 
   One of the following propellers must be installed: 
    Beech controllable propeller 
      As listed under Item 1(e) or (f) whichever is applicable  
    Beech constant speed propeller 
      As listed under Item 3(f) or (g) whichever is applicable 
 or *(c) Lycoming GO-435-D1 in Models C35 and D35 only.  See Note 4 for limitations. 
 or *(d) Continental E-225-8 replacing E-185 engine in Models 35, A35, B35, C35 and D35  
   with S/N's D-3698 and below, and 35R with S/N D-25R1 and up. 
   Engine limits:  (Model 35) 
   Takeoff (one minute) 185 hp., 2300 rpm 26.5 in. Hg MP 
   For all other operations 165 hp, 2050 rpm, 27.5 in. Hg MP  
    (Models A35, B35, C35, D35, F35, 35R) 
   Takeoff (one minute) 225 hp, 2650 rpm, full throttle or 205 hp, 2600 rm, 26.5 in. Hg. MP.  For all  
     other operations, 185 hp, 2300 rpm, 26.5 in. Hg MP  
   Fuel:  80 min. grade aviation gasoline 
   Propeller:  Item 1(e) with 13 low pitch for Models A35, B35, C35, D35, and 15  low pitch for Model 35; 
    or Item 1(f), 3(f), or 3(g) 
   Continental E-225-8 engine is mechanically interchangeable with the E-185 engine without major 
    installation alterations.  Use of E-185-11 engine mounts and revised airplane supporting brackets 
    may be necessary to adapt the E-225 engine (see Item 111(a)).  Beech 35-924230 hand fuel pump 
    is required for 225 hp takeoff rating (see Item 101(d)).  Engine tachometer and manifold pressure 
    guage markings are to agree with pertinent E-225 engine limits.  Airplane Flight Manual Supplement 
    covering revised engine operating limitations should be submitted to Regional Chief, Engineering 
    and Manufacturing Branch, for approval before attachment to Airplane Flight Manual, Item 404. 
 
*112. Engine fire extinguisher system (Van's Air Service Dwg. 5-4 dated July 15, 1949, with operation 
  instructions 5-4).        22 lb. (+75) 
 
 113. Oil cooler tank (Beech 35-939172).  See Note 1 for data on unusable oil.   6 lb. (+39) 
 
*114. 10 gal. auxiliary fuel tank installed per Aircraftsmen, Inc. (Oklahoma City, Oklahoma)   12 lb. (+127) 
  installation instructions and Dwg. AT-A35 for Models A35, B35, C35, D35, E35, F35, G35 
  or AT-35 for Model 35.  Approved Airplane Flight Manual (Item 404) Model 35 dated  
  May 22, 1950, or later; Model A35 dated May 22, 1950, or later; Model B35 dated  
  December 16, 1949, or later; Model C35 dated July 27, 1951, or later; Model D35 dated 
  January 5, 1953, or later; Model E35 dated December 15, 1953, or later; Model F35 dated  
  January 1, 1955, or later; or Model G35 dated November 18, 1955, or later is required  
  with this installation. 
 
*115. Oil cooler shutter.  Installed in acordance with Aircraftsmen, Inc., Oklahoma City,   1 lb. (+45) 
  Oklahoma, installation instructions and Dwg. AOS 35-1 and -2.  (For airplanes with oil 
  cooler tank mounted to engine, see Items 108 and 113). 
 
*116. Engine breather oil separator installed in accordance with Roscoe Turner Aeronautical No weight change 
  Corporation, Indianapolis, Indiana, installation instructions dated July 20, 1951.  (Eligible  
  on airplanes having S/N 1885 and up and prior airplanes equipped w ith proper engine 
  breather system).

A-777 18 Rev. 62 
 
Specifications Pertinent to All Models (cont’d) 
 
Engines and Engine Accessories - Fuel and Oil Systems  (cont’d) 
*117. 18 gal. auxiliary fuel tank installed in accordance with Remmert-Werner, Inc., St. Louis,  35 lb. (+133) 
  Mo., Dwg. 35-01002, sheets 1 and 2, Models 35, A35, B35, C35, 35R.  Remmert -Werner 
  Airplane Flight Manual Supplement dated August 27, 1952, is required with this  
  installation.  Fuel arm at +135. 
 
*118. Fuel pumps  (with Item 111(c) only) 
  (a) Engine-driven - Thompson AN-4100TF    2 lb. (+41) 
 and (b) Wobble-Beech 35-924230      2 lb. (+74) 
   With 35-924230 pump installed, Beech Airplane Flight Manual Supplement No. 1  
   dated July 28, 1951, must be appended to Approved Airplane Flight Manual, Item 404, 
   if manual is dated earlier than May 2, 1951. 
 
*119. Oil radiator, Heat Exchangers, Inc., Model 102-G (with Item 111(c) only)   8 lb. (+13) 
 
*120. Vacuum pump, Pesco B-11, 194-F (with Item 111(c) only)   4 lb. (+43) 
 
+121. 20 gal. auxiliary fuel tank installed in accordance with Santa Monica Aviation, Municipal  17 lb. (+132) 
  Airport, Santa Monica, CA., Dwg 19543 and 19544 (Models D35 and E35)  
 
 122. Two 10 gal. auxiliary wing fuel tanks.  See NOTE 1 for data on unusable fuel.  18 lb. (+  94) 
 
 123. Heated fuel tank vents installed per Dwg. 35-001043, Models 35, A35, B35, C35, D35   Neglect weight 
  (S/N D-3401 through D-3550) 
 
Landing Gear 
 201. Main wheel-brake assemblies 
  (a) Two 6.50-8, Type III with 6.50-8 4- or 6-ply rating tires and regular tubes 
   (1) Goodyear Model L6.50-8HBM    44 lb. (+97) 
    Wheel assembly 530869M or 9530949 
    Brake assembly 517731M 
 
 or (b) Two 7.00-8, Type III with 6.50-8 4-ply rating tires and regular tubes   48 lb. (+97) 
   (1) Firestone Model DFA-234 
    Wheel assembly DFA-233 
    Brake assembly CFA-299 
 
 or (c) Two 6.50-8, Type III with side inflatable 6.50-8 4- or 6-ply rating tubeless tires 
   (1) Goodyear PD-931      49 lb. (+97) 
    Wheel assembly 9532135 
    Brake assembly 9532167 
 
  (d) Goodyear 6.50-8, Type III, PD-931    25 lb. (+97) 
    Wheel Assembly 9532135 
    Brake assembly 9532412 
    (Use on aircraft S/N D15002 only) 
 
 or (e) Two Cleveland 6.00-6, No. 20-69, Type III with 7.00-6 6-ply rated tires and 
   regular tubes.       43 lb. (+97) 
    Wheel assembly 40-83 
    Brake assembly 30-54 
    (Use on aircraft modified per Beech Dwg. 35-8004) 
 
 202. Nose wheels 
  (a) Goodyear L5NBM or L5NBD or Firstone DFA 531-1 with 5.00-5 4-ply tire and tube  10 lb. (+12) 
  (b) Goodyear 9532102 with 5.00-5 side inflatable 4-ply rating tubeless tire  9 lb. (+12) 
 
 203. Co-pilot brakes        2 lb. (+54)

Rev. 62 19 A-777 
 
Specifications Pertinent to All Models (cont’d) 
 
Electrical Equipment 
 301. Generator 
  (a) 25 a. Delco-Remy P/N 1101879 or 1101886    14 lb. (+42) 
 or (b) 35 a. CMC P/N 533730 (includes CMC generator 532701 equivalent to Delco -Remy  16 lb. (+42) 
   1101887) 
 or (c) 50 a. CMC assy. P/N 539829 (includes CMC generator 539538 equivalent to  
   Delco-Remy 1101888) or Delco-Remy P/N 1101908    16 lb. (+42) 
   Models 35 (S/N D-3351 through D-3698), E35, F35, G35 
 
 302. Battery 
  (a) 12 v. 33 a. hr.       28 lb. (+44) 
            or (+54) 
 or (b) 12 v. 24 a. hr. Sonotone 22500 installed per Beech Dwg.  35 -001040.  Item 404(1) or (m) 
   required with this installation.     28 lb. (+54) 
  (c) 12 v. 33 a. hr. (mounted forward of firewall in engine compartment)   28 lb. (+45) 
   per Beech Dwg. 35-3001. 
 
 303. Landing lights, General Electric 4522    1 lb. ea. +72) 
 
*304. Generator, 5 a. Lear Dwg. A43977     15 lb. (+42) 
*305. Voltage regulator, Delco-Remy 1118340 (with Item 301(a) only)  Negligible weight 
*306. Generator, 35 a. Leece-Neville E7A (with Item 111(c) only)   22 lb. (+41) 
 307. Anti-collision light, lower, installed per Beech Dwg. 35-001031   2 lb. (+102) 
  (a) Grimes D7080-1-12 
 or (b) Beech 33-3800001-3 (Whelen) 
 
Interior Equipment 
 401. Three 1-1/2 min. parachute flares, International    15 lb. (+164) 
 
 402. Dual control column (T-Type) Beech 35-524575    3 lb. (+  72) 
 
 403. Ballast 
  (a) Beech 35-410236 (9 lb. max)   Use actual weight change 
             (+270) 
            or (+271) 
  (b) Beech 35-410374  (15 lb. max.)   Use actual weight change 
             (+  11) 
 
 404. FAA Approved Airplane Flight Manual (Models 35, A35 and B35.  Approved AFM's 
  of previous dates also acceptable provided latest manual not required by optional 
  equipment item). 
  (a) Model 35 dated October 11, 1950, S/N D-1 through D-1500; or Item 404(x). 
  (b) Model A35 dated October 11, 1950, S/N D-1501 through D-2200 and D-15001; 
   or Item 404(v). 
  (c) Model B35 dated October 11, 1950, S/N D-2201 through D-2680; or Item 404(v). 
  (d) Deleted. 
  (e) Model 35R dated May 2, 1951, S/N D-25R1 and up; or Item 404(v) and (w). 
  (f) Deleted. 
  (g) Deleted. 
  *(h) Rawdon Bros. FAA Approved Airplane Flight Manual Supplement dated September 24, 
   1954 (required with Item 111(c)). 
  (i) Deleted. 
  (j) Deleted. 
  (k) Deleted. 
  (l) FAA Approved Airplane Flight Manual Supplement dated November 20, 1959, required 
   with Item 302(b), (35, A35, B35, C35, D35, S/N D-3401 through D-3550). 
  (m) DMCR Approved Airplane Flight Manual Supplement dated November 20, 1959, 
   required with Item 302(b) (D35, S/N 3551 and up, E35, F35, G35).  
  (n) Airplane Flight Manual Supplement dated May 12, 1972.

A-777 20 Rev. 62 
 
Specifications Pertinent to All Models (cont’d) 
 
Interior Equipment (cont’d) 
  (o) FAA Approved Airplane Flight Manual Supplement dated June 14, 1972, required with 
   Item 111(b) engine in Model F35 airplane with Item 3(f) propeller. 
  (p) FAA Approved Airplane Flight Manual Supplement dated January 9, 1973, required for 
   Model G35 with Item 3(f) propeller. 
  (q) Model G35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised 
   March 1987 or later. 
  (r) Mode E35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised 
   March 1987 or later. 
  (s) Model F35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised 
   March 1987 or later. 
  (t) Model D35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised 
   March 1987 or later. 
  (u) Model C35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual as revised 
   March 1987 or later. 
  (v) Models A35 and B35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual 
   dated January 1977 or later. 
  (w) Model 35R Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement  
   dated January 1977 or later, S/N D-25R1 and On. 
  (x) Model 35 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual dated 
   March 1977 or later. 
 
 405. Ambulance conversion installation (litter and attendant chair replace rear seat and copilot's seat back) 
  (a) Model 35, A35 and B35      12 lb. (+102) 
  (b) Model C35, D35, E35, F35 and G35   No weight change 
  (c) Model 35, A35, B35 and 35R with shoulder harness installed    5 lb. (+85) 
 
 406. Air conditioner installation (including water)    16 lb. (+144) 
 
*407. Lear Model L-2B automatic pilot and     44 lb. (+119) 
  Model 1404A altitude controller (optional equipment installed per Lear Dwg. 82861.   2 lb. (+176) 
  Either Item 301(b) or 304 and 305 required with this installation.  
  The following placard (required for aircraft having Manuals (a), (b) and (c) only) should 
  be installed in a conspicuous place near the autopilot controller in full view of the pilot: 
   "1. Do not use autopilot below 300 ft. above terrain except during approach or  
    landing when autopilot not to be used below 100 ft. above terrain.  Minimum 
    altitudes do not override any higher minimum oprational altitudes. 
   2. Do not override autopilot to increase angle of  bank." 
  Servo slip clutch stall torque settings in in.-lb.  10%; rudder 40; aileron 25; elevator 9. 
  Servo drum pitch diametrs for all three axes are 1.375 in. 
  Lear Model 1350-A2 approach coupler    8 lb. (+144) 
 and Lear Model 2203A altitude controller installed per Lear Dwg. 83861AB   3 lb. (+175) 
  (a) FAA Approved Airplane Flight Manual Supplement dated April 6, 1951, required 
   with Models 35, A35 and B35.   
  (b) FAA Approved Airplane Flight Manual Supplement dated March 29, 1951, required 
   with Model C35 installation. 
  (c) FAA Approved Airplane Flight Manual Supplement (Lear Dwg. 96120) may be 
   used in lieu of above supplements on all models. Revision dated September 3, 1952, 
   required when altitude controller installed. 
  (d) FAA Approved Airplane Flight Manual Supplement dated November 24, 1954, 
   required with 1350A-2 approach coupler and 2203A altitude controller. 
  (e) FAA Approved Airplane Flight Manual Supplement dated May 20, 1955, required 
   with only autopilot.  (Models 35 through F35) 
  (f) FAA Approved Airplane Flight Manual Supplement dated May 23, 1955, required 
   with autopilot with approach coupler.  (Models 35 through F35)  
  (g) FAA Approved Flight Manual Supplement dated September 24, 1956, required 
   with autopilot with approach coupler (Models 35 through G35)  
  (h) FAA Approved Flight Manual Supplement dated September 25, 1956, required with 
   autopilot only (Models 35 through G35)

Rev. 62 21 A-777 
 
Specifications Pertinent to All Models (cont’d) 
 
Interior Equipment (cont’d) 
*408. Mitchell Co-pilot model AK-044 per Mitchell Bulletin 102 (1-655)   23 lb. (+67) 
  (Weight includes horizon and directional gyros, 8 lb. at +66) 
  Aileron slip clutch stall torque 20  in.-lb. 
  Pilot overpower force at wheel rim 8 lb. 
  FAA Approved Airplane Flight Manual Supplement dated January 13, 1955, required. 
 
*409. Lear ARCON automatic rudder control per Lear Dw. 703088 including one servo   15 lb. (+152) 
  Model 3000A with capstan pulley (dia. 2.688 in.) and clutch slip torque 76  in.-lb.  FAA 
  Approved Lear Airplane Flight Manual Supplement dated February 15, 1955, or 
  March 31, 1955, required. 
 
*410. Tactair T-1 autopilot installed per Tactair instruction dated December 6, 1954.  Maximum   10 lb. (+129) 
  servo cable forces:  aileron 30 lb., elevator 30 lb.  Item 104 (Pesco 3P-194F) vacuum pump 
  required.  FAA Approved Tactair Airplane Flight Manual Supplement for the Model T-1 
  autopilot dated December 6, 1954, required. 
 
*411. Fedeal Telephone and Radio Co. Model F-200 autopilot installed per Manual of   19 lb. (+151) 
  Installation Instructions No. 105 dated December 15, 1955, applicable to autopilot S/N 1882,  
  1945, 1946, 1000 and 1001 (Mode l D35 only) 
 
*412. Federal Telephone and Radio Co. Model F-200 autopilot installed per Section 2 manual   19 lb. (+151) 
  110 dated July 27, 1956, applicable to autopilot S/N 2001 and up (Model C35, D35, E35,  
  F35, G35 only).  Servo slip clutch torque aileron and elevator 35 in-lb.  10%.  FAA  
  Approved Flight Manual Supplement dated March 21, 1956, required.  
 
 413. Beech Power Flite Control single axis autopilot. 
  (a) Basic autopilot system per Beech Dwg. 35-001062-1 (D35, S/N D-3551 through   6 lb. (+87) 
   D-3698, E35, F35, G35 only). Airplane Flight Manual Supplement P/N 33 -500013-65 
   dated September 29, 1961, required. 
  (b) Autopilot system with course selector directional gyro per Beech Dwg. 35-001062-1, 
   -3, (D35, S/N D-3551 through D-3698, E35, F35, G35 only).  Airplane Flight Manual   10 lb. (+ 79) 
   Supplement P/N 33-500013-65 dated September 29, 1961, required. 
 
 414. FAA Approved Flight Manual 
  (a) FAA Approved Airplane Flight Manual Supplement P/N 130472 dated June 4, 1965,  
   required with Item 606 (35, A35, B35, C35, D35 (S/N D-3401 through D-3550), and 35R. 
  (b) DOA Approved Airplane Flight Manual Supplement P/N 130471 dated June 7, 1965,  
   required with Item 606 (D35 (S/N D-3551 and up), E35, F35, and G35) 
 
Miscellaneous (Not listed above) 
 601. Stall warning indicator installation 
  (a) Beech Dwg. 35-361005 
  (b) Safe Flight, Beech Dwg. 35-361025 
 
 602. Heated pitot head installation, Beech Dwgs. 35-361100    1 lb. (+74) 
 
*603. Aileron trimmer control installation per Aircraftsmen, Inc., Oklahoma City, Oklahoma, 
  Dwg. ATC-35. 
 
 604. Landing gear door modification installed per installation instructions and drawings as Use actual weight change 
  listed in Beech Installation Bulletins. 
  (a) 35-604  (Model 35) 
  (b) 35-603  (Models A35, B35, C35, D35 and E35) 
 
 605. Zep oxygen system per Beech Dwg. 35-001-55-1 or -3 
 and (1) Beech Dwg. 414-001058 
 or (2) Beech Dwg. 414-001059

A-777 22 Rev. 62 
 
Specifications Pertinent to All Models (cont’d) 
 
Miscellaneous (Not listed above) (cont’d) 
 606. Landing Gear Safety System per Beech Dwg. 35-8001 
  (Models 35R, 35, A35, B35, C35, D35 (S/N D-3401 through D-3550), E35, F35 and G35). 
  Item 414(a) or (b) required with this item. 
 
 607. Emergency Static Source Installation   Negligible Weight 
  (a) Beech Drawing 35-5013 eligible on 35 through G35 and 35R.  
   Airplane Flight Manual Supplement 35-324428-13 dated January 4, 1965, or later 
   required D35 (D3551 and after), E35, F35 and G35.  Airplane Flight Manual  
   35-324428-19 dated March 5, 1965, required 35R, 35 through D35 (through D3550). 
 
 608. Structural modification per Beech Drawing 35-4016.    3 lb. (+225) 
 
NOTE 1. Current weight and balance report together with list of equipment included in certificated empty weight and 
loading instructions when necessary must be in 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: 
 
  With Item 102, unusable oil of 7 lb. at (+39). 
 OR With Item 106, 108, or 113, unusable oil of 3 lb. at (+37).  
 OR With Item 111(c) and 119, unusable oil of 2 lb. at (+20). 
  With standard wing fuel tanks, unusable fuel of 36 lb. at (79). 
  Installation of auxiliary fuel tank, Item 107, requires inclusion of additional unusable fuel of 3 lb. at (+132 or 
+133). 
 
  Installation of auxiliary fuel tank, Item 122, requires inclusion of additional unusable fuel of 5 lb. at (+94). 
 
NOTE 2. The following placards must be displayed in front of and in clear view of pilots: 
 
  Model 35: 
  "This airplane must be operated as a Normal or Utility Category airplane in compliance with the approved 
operating limitations applicable in each case.  All markings and placards on this airplane apply to its operation as 
a Normal Category Airplane.  For Utility Category operations, refer to the Airplane Flight Manual (or Approved 
Operating Limitations) document for airspeed, weight and maneuvering limitations.  No acrobatic maneuvers 
(including spins) approved for Normal Category Operations." 
 
  Model A35, B35, C35, E35, F35, G35 or 35R : 
  "Utility Category Airplane.  Operate in accordance with FAA Airplane Flight Manual. Intentional spins 
prohibited.  No acrobatic maneuvers approved except those listed in the Airplane Flight Manual." 
 
NOTE 3. Deleted January 12, 1950. 
 
NOTE 4. Lycoming GO-435-D1 engine eligible for installation in Models C35 and D35 (Normal Category) as 
accomplished by Rawdon Bros. Aircraft, Inc., Wichita, Kansas, per approved technical data and the following 
limitations: 
 
  Engine    Lycoming GO-435-D1 
 
  Fuel     80/87 minimum grade aviation gasoline 
 
  Engine Limits  Takeoff (one minute) 3400 rpm  (260 b. hp) 
       Maximum continuous 3000 rpm  (24p b. hp)

Rev. 62 23 A-777 
 
Specifications Pertinent to All Models (cont’d) 
 
  Airspeed Limits  Maneuvering  130 mph  (113 knots)  True Ind. 
       Max. structural cruising 160 mph  (139 knots)  True Ind. 
       Never exceed  202 mph  (176 knots)  True Ind. 
       Flaps extended  105 mph  (  91 knots)  True Ind. 
       Landing gear extended 125 mph  (109 knots)  True Ind. 
 
  C.G. Range (landing (+82.8) to (+84.4) at 2850 lb. 
    gear extended)  (+78.6) to (+85.4) at 2500 lb. 
       (+76.5) to (+85.4) at 2325 lb. 
 
76 78 80 82 84 86
2100
2200
2300
2400
2500
2600
2700
2800
INCHES
POUNDS AFT
LIMIT
FRONT
LIMIT
2900
 
  Maximum Weight  2850 lb. 
 
  No. of Seats   4 (2 at +85, 2 at +116) 
 
  Maximum Baggage 270 lb. (+139).  Refer to loading chart revised September 10, 1954 (included  
       in Rawdon Bros. Flight Manual Supplement) for loading instructions. 
 
     Fuel Capacity Tank Capacity Gal. Usable Gal. Arm 
      L & R Main 20 ea.  17 ea. (+75) 
        Optional Fuel System (Item 107) 
      Fuselage Aux. Sys. 20 19.5 (+132) 
           or (+133) 
      See NOTE 1 for data on unusable fuel. 
 
   Oil Capacity  4 gal.  (+57) 
 
   Control Surface Wing flaps   Down 30 
     Movements Aileron tab Fixed 
      Aileron Up 20 Down 20 
      Elevator tab Up 10 Down 31 
      "V" tail elevator action Up 22.5 Down 17.5 
      "V" tail rudder action Up 21 Down 21 
      "V" tail maximum Up 35 Down 30 
       combination rudder elevator action 
 
   Serial No. Eligible D-2681 through D-3550 
 
   Required Equipment  4, 103, 118, 119, 201, 202, 302(a), 306, 307, 404(h), 601(b)  
     Items 
 
   Certification Basis  CAR 3 effective November 1, 1949, and 3.112C of Amendment 3-4 effective  
     January 15, 1951.

A-777 24 Rev. 62 
 
Specifications Pertinent to All Models (cont’d) 
 
NOTE 5. When Item 604 installed, landing gear may be lowered at following airspeeds under emergency conditions: 
 
 Model Item Airspeed 
   35 604(a) 160 mph  (139 knots)  True Ind. 
 A35 604(b) 175 mph  (152 knots)  True Ind. 
 B35 604(b) 175 mph  (152 knots)  True Ind. 
 C35 604(b) 175 mph  (152 knots)  True Ind. 
 D35 604(b) 175 mph  (152 knots)  True Ind. 
 E35 604(b) 175 mph  (152 knots)  True Ind. 
 
 
 
---- END ----
```

## ADs (47, in force first)

- [AD 2024-14-03](https://openairdocs.org/ad/2024-14-03): Autopilot System · Garmin GFC 500 Autopilot (STC SA01866WI). Effective Aug 20, 2024
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022
- [AD 2007-08-08](https://openairdocs.org/ad/2007-08-08): Uplock roller · Textron 35, 35-33, 35-A33 and 49 more. Effective May 25, 2007
- [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 94-20-04 R2](https://openairdocs.org/ad/94-20-04-R2): Empennage aft fuselage · Remove V tail and install a Beech Model F33A straight tail (D'Shannon Products STC SA2149CE). Effective Jun 27, 2003
- [AD 2002-21-13](https://openairdocs.org/ad/2002-21-13): V-tail · Textron 35, 35R, A35 and 1 more. Effective Dec 10, 2002
- [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001
- [AD 2001-23-10](https://openairdocs.org/ad/2001-23-10): Flap Flex Shaft Assemblies · Textron 35, 35-33, 35-A33 and 60 more. Effective Dec 13, 2001
- [AD 99-05-13 R1 WD](https://openairdocs.org/ad/99-05-13-R1-WD): Withdrawal of AD 99-05-13 · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Jul 5, 2000
- [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000
- [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998
- [AD 97-14-15](https://openairdocs.org/ad/97-14-15): Cabin Side Door And Utility Door Handle · Textron 36, 50, 56TC and 41 more. Effective Sep 2, 1997
- [AD 97-06-11](https://openairdocs.org/ad/97-06-11): Ruddervator Differential Tail Control Rod Assy · Textron 35, 35R, A35 and 16 more. Effective May 16, 1997
- [AD 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996
- [AD 89-05-02](https://openairdocs.org/ad/89-05-02): Elevator Control Fittings · Textron 35, 35-33, 35-A33 and 42 more. Effective Mar 24, 1989
- [AD 84-09-01](https://openairdocs.org/ad/84-09-01): Window Emergency Egress Provision · Textron 35, 36, 50 and 60 more. Effective May 25, 1984
- [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981
- [AD 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981
- [AD 75-15-08](https://openairdocs.org/ad/75-15-08): Engine Lubrication · Filtrator Company Engine Crankcase Breather and Vacuum Pump… (D'Shannon Products STC SA2219WE). Effective Sep 10, 1975
- [AD 75-05-02](https://openairdocs.org/ad/75-05-02): Engine Oil · Beryl D Shannon Aviation Specialties Engine Crankcase… (D'Shannon Products STC SA2653WE). Effective Feb 21, 1975
- [AD 72-18-01](https://openairdocs.org/ad/72-18-01): Fuel Selector Valve Warning Light · Textron 35, A35, B35 and 1 more. Effective Aug 29, 1972
- [AD 72-11-02](https://openairdocs.org/ad/72-11-02): Engine Fuel Interruption · Textron 35, 35-33, 35-A33 and 48 more. Effective May 20, 1972
- [AD 62-08-03](https://openairdocs.org/ad/62-08-03): Control Wheels · Textron 35, 35-33, 35-A33 and 33 more. Effective Jul 9, 1970
- [AD 69-18-01](https://openairdocs.org/ad/69-18-01): Fuel System Modification · Textron 35, A35, B35 and 1 more. Effective Aug 30, 1969
- [AD 63-25-01](https://openairdocs.org/ad/63-25-01): Fuselage Modification · Textron 35, 35-33, 35-A33 and 7 more
- [AD 47-47-07](https://openairdocs.org/ad/47-47-07): Engine Identification Plate · Textron 35, 35-33, 35-A33 and 4 more
- [AD 47-47-08](https://openairdocs.org/ad/47-47-08): Fuel Line Chafing · Textron 35, 35-33, 35-A33 and 4 more
- [AD 48-08-01](https://openairdocs.org/ad/48-08-01): Starter Rework · Textron 35, 35-33, 35-A33 and 4 more
- [AD 49-04-01](https://openairdocs.org/ad/49-04-01): Aileron Chain · Textron 35, 35-33, 35-A33 and 4 more
- [AD 49-26-01](https://openairdocs.org/ad/49-26-01): Trailing Antenna Rework · Textron 35 and A35
- [AD 49-31-01](https://openairdocs.org/ad/49-31-01): Emergency Fuel Pump 'O' Rings · Textron 35 and A35
- [AD 49-48-01](https://openairdocs.org/ad/49-48-01): Thompson Fuel Pump · Textron 35 and A35
- [AD 50-05-02](https://openairdocs.org/ad/50-05-02): Push-Pull Controls · Textron 35, A35, Push-Pull Controls and 1 more
- [AD 50-42-01](https://openairdocs.org/ad/50-42-01): Elevator Tab Replacement · Textron A35
- [AD 51-14-01](https://openairdocs.org/ad/51-14-01): Fuel Booster Pump Removal · Textron 35 and A35
- [AD 53-01-02](https://openairdocs.org/ad/53-01-02): Fuel Selector Valve Rework · Textron 35, A35, B35 and 1 more
- [AD 55-22-01](https://openairdocs.org/ad/55-22-01): Oil Outlet Check Valve · Textron 35, 35-33, 35-A33 and 4 more
- [AD 59-08-01](https://openairdocs.org/ad/59-08-01): Landing Gear Limit Switches · Textron A35, B35 and C35
- [AD 76-05-04](https://openairdocs.org/ad/76-05-04): Stabilizer Attach Fitting · Textron 35, 35-33, 35-A33 and 7 more
- [AD 2019-21-08](https://openairdocs.org/ad/2019-21-08) (historical): Aileron Control System · Textron 35-C33, 35-C33A, 36 and 16 more. Effective Nov 22, 2019
- [AD 94-20-04 R1](https://openairdocs.org/ad/94-20-04-R1) (historical): V-tail · Remove V tail and install a Beech Model F33A straight tail (D'Shannon Products STC SA2149CE). Effective Dec 10, 2002
- [AD 99-05-13](https://openairdocs.org/ad/99-05-13) (historical): Fuel Tank Selector · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Apr 19, 1999
- [AD 98-13-02](https://openairdocs.org/ad/98-13-02) (historical): Placard - Speed · Raytheon 35 Model or Series (all), 35R, A35 and 1 more. Effective Jul 7, 1998
- [AD 94-20-04](https://openairdocs.org/ad/94-20-04) (historical): V-Tail Structure · Remove V tail and install a Beech Model F33A straight tail (D'Shannon Products STC SA2149CE). Effective Nov 28, 1994
- [AD 72-22-01](https://openairdocs.org/ad/72-22-01) (historical): Landing Gear Uplock Rollers · Raytheon 35-33, 35-A33, 35-B33 and 49 more. Effective Oct 25, 1972

## Registered aircraft by registry model (OpenAirDocs)

- [Beech 35](https://openairdocs.org/model/beech-35): 266 aircraft (registry code 1151502)
- [Beech C35](https://openairdocs.org/model/beech-c35): 258 aircraft (registry code 1151508)
- [Beech G35](https://openairdocs.org/model/beech-g35): 224 aircraft (registry code 1151516)
- [Beech F35](https://openairdocs.org/model/beech-f35): 192 aircraft (registry code 1151514)
- [Beech A35](https://openairdocs.org/model/beech-a35): 159 aircraft (registry code 1151504)
- [Beech B35](https://openairdocs.org/model/beech-b35): 148 aircraft (registry code 1151506)
- [Beech D35](https://openairdocs.org/model/beech-d35): 142 aircraft (registry code 1151510)
- [Beech E35](https://openairdocs.org/model/beech-e35): 141 aircraft (registry code 1151512)
- [Beech 35R](https://openairdocs.org/model/beech-35r): 7 aircraft (registry code 1151518)
- [Beechcraft 35 BONANZA](https://openairdocs.org/model/beechcraft-35-bonanza): 0 aircraft (registry code 4210121)

## STCs approved under this data sheet (470, first 50)

- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc.
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA01120SE](https://openairdocs.org/stc/SA01120SE): Installation of Door Steward.. Mountain View Aviation LLC
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc.
- [STC SA01708WI](https://openairdocs.org/stc/SA01708WI): Installation of third lap belt restraint in the center of the main cabin rear bench seat. MN Engineering LLC
- [STC SA3584NM](https://openairdocs.org/stc/SA3584NM): Installation of aileron and flap gap seals.. CheckSix AeroSolutions, LLC
- [STC SA01168SE](https://openairdocs.org/stc/SA01168SE): Installation of Teledyne Continental E225-8 engine modified.. CheckSix AeroSolutions, LLC
- [STC SA384WE](https://openairdocs.org/stc/SA384WE): Installation of adjustable pilot and co-pilot seat. CheckSix AeroSolutions LLC
- [STC SA4381WP](https://openairdocs.org/stc/SA4381WP): Replacing the instrument panel.. CheckSix AeroSolutions, LLC
- [STC SA507WE](https://openairdocs.org/stc/SA507WE): Installed adjustable back rest. CheckSix AeroSolutions, LLC
- [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA2753CE](https://openairdocs.org/stc/SA2753CE): Installation of flap actuated landing gear warning system.. Walter Timothy Miller
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA00245SE](https://openairdocs.org/stc/SA00245SE): Installation of the Aviation Research Systems, Inc., Locking Fuel Caps. CheckSix AeroSolutions, LLC
- [STC SA00246SE](https://openairdocs.org/stc/SA00246SE): Installation of the Aviation Research Systems, Inc., Locking Fuel Caps. CheckSix AeroSolutions, LLC
- [STC SA00460SE](https://openairdocs.org/stc/SA00460SE): Installation of stainless steel battery box.. CheckSix AeroSolutions, LLC
- [STC SA1722WE](https://openairdocs.org/stc/SA1722WE): Installation of Fiberglass tail fairing.. CheckSix AeroSolutions, LLC
- [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC
- [STC SA04537CH](https://openairdocs.org/stc/SA04537CH): Installation of wingtip position/anti-collision light support bracket. Gallagher Aviation LLC
- [STC SA01561CH](https://openairdocs.org/stc/SA01561CH): Installation of Hartzell Model PHC-(C, L)3YF-1RF/F8068(-2) three bladed propeller on Raytheon Aircraft Company (Beech) aircraft equipped with Teledyne Continental Motors six-cylinder engines. D'Shannon Products Ltd.
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [STC SA02771LA](https://openairdocs.org/stc/SA02771LA): Installation of openable window. Ellis and Associates CADD/Technical Illustration
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA00638WI](https://openairdocs.org/stc/SA00638WI): Installation of Concorde Battery Corporation (vrsla) Valve Regulated Sealed Acid Battery.. Aero-Mach Wilco LLC
- [STC SA11GL](https://openairdocs.org/stc/SA11GL): Installation of Cleveland 6.00-6wheels and brakes conversion kit 199-49.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA19GL](https://openairdocs.org/stc/SA19GL): Install Cleveland 7.00-8 wheels and brakes.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA00469NY](https://openairdocs.org/stc/SA00469NY): Installation of Main Landing Gear Auxiliary Landing Lights.. Gallagher Aviation LLC
- [STC SA00901NY](https://openairdocs.org/stc/SA00901NY): Installation of a wing tip recognition lights.. Gallagher Aviation LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)

All 470: https://openairdocs.org/tcds/A-777/stcs.md

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