TCDS A-777

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