BONANZA G36 Specifi cation and Description E-4063 THRU E-4080 Contents THIS DOCUMENT IS PUBLISHED FOR THE PURPOSE 1. GENERAL DESCRIPTION ....................................2 OF PROVIDING GENERAL INFORMATION FOR THE 2. GENERAL ARRANGEMENT .................................3 EVALUATION OF THE DESIGN, PERFORMANCE AND EQUIPMENT OF THE BONANZA G36. IT IS NOT A 3. DESIGN WEIGHTS AND CAPACITIES ................4 CONTRACTUAL AGREEMENT UNLESS APPENDED 4. PERFORMANCE ..................................................4 TO AN AIRCRAFT PURCHASE AGREEMENT. 5. STRUCTURAL DESIGN CRITERIA ......................4 6. FUSELAGE ...........................................................4 7. WING .....................................................................5 8. EMPENNAGE .......................................................5 9. LANDING GEAR ...................................................5 10. POWERPLANT .....................................................5 11. PROPELLER .........................................................6 12. SYSTEMS .............................................................6 13. FLIGHT COMPARTMENT AND AVIONICS ...........7 14. INTERIOR ...........................................................12 15. EXTERIOR ..........................................................12 16. ADDITIONAL EQUIPMENT .................................12 17. EMERGENCY EQUIPMENT ...............................12 18. DOCUMENTATION & TECH PUBLICATIONS ....13 19. MAINTENANCE TRACKING PROGRAM ...........13 20. NEW AIRCRAFT LIMITED WARRANTY .............13 21. CREW TRAINING AGREEMENT ........................15 1 BONANZA G36 (E-4063 THRU E-4080) / BEECHCRAFT CORPORATION INTRODUCTION 1. GENERAL DESCRIPTION This document is published for the purpose of The Bonanza G36 is a single engine aircraft utilizing general information for the evaluation of the design, an all metal airframe. The aircraft has provisions for performance and equipment of the Beechcraft Bonanza up to six occupants and their baggage. The aircraft is G36 aircraft. Should more detailed data be required, it certifi ed for single pilot operation. can be obtained by contacting: The Bonanza G36 is powered by a Continental Motors Beechcraft Corporation IO-550-B engine with a Hartzell constant-speed three P.O Box 85 bladed propeller mounted on the nose of the aircraft. Wichita, Kansas 67201-0085 The Bonanza G36 is certifi ed in accordance with CAR Attention: Contracts Administration, Dept. 191 Part 3 Utility Category. Telephone: 316.676.7111 Fax: 316.676.1910 Dimensions This document describes only the Bonanza G36 Overall Height ...................................8 ft 7 in. (2.62 m) aircraft, serial numbers E-4063 thru E-4080, its Overall Length ................................27 ft 6 in. (8.38 m) powerplant and standard equipment. Also included are Wing the warranties applicable to the Bonanza G36 aircraft, Continental Motors engine, Garmin Avionics, Hartzell Span (overall) ...............................33 ft 6 in. (10.21 m) propeller as well as the Bonanza G36 crew training Area .........................................181 sq. ft (16.81sq. m) agreement. In the event of any discrepancy between Sweep (at 25% chord) .....................................0.0 deg this document and the Aircraft Purchase Agreement Dihedral ........................................................... 6.0 deg to which it may be appended, terms specifi ed in the Horizontal Tail Aircraft Purchase Agreement shall govern. Span (overall) .................................12 ft 2 in. (3.71 m) Engine and Avionics warranties are subject to change Dihedral ........................................................... 0.0 deg at the discretion of the manufacturer. Beechcraft Corporation does not warrant engines or avionics. Cabin Should the engine or avionics warranty refl ected in this Length (including cockpit) ...............12 ft 7 in. (3.84 m) document not be the current warranty provided by the Height (max) .....................................4 ft 2 in. (1.27 m) manufacturer, Beechcraft Corporation disclaims any Width (max) ......................................3 ft 6 in. (1.07 m) liability to Buyer for any such error. Entry Doors The term “Aircraft” as used in this document and in Fwd Cabin Door..................... 37 in. wide x 36 in. high the Aircraft Purchase Agreement into which it may ...................................... (0.94 m. wide x 0.91 m. high) be incorporated by reference shall unless otherwise designated include the entire Bonanza G36 aircraft and Aft Utility Door........................ 45 in. wide x 35 in. high all of its parts, components and related publications, ...................................... (1.14 m. wide x 0.89 m. high) including manuals, as more fully described in this Specifi cation and Description. Throughout this document, Beechcraft Corporation reserves the right to revise the ‘Specifi cation and Description’ whenever occasioned by product improvements, government regulations or other good cause as long as such revisions do not result in a signifi cant reduction in performance standards. Copyright © 2015 Beechcraft Corporation. All rights reserved. 2 2. GENERAL ARRANGEMENT 3 BONANZA G36 (E-4063 THRU E-4080) / BEECHCRAFT CORPORATION 3. DESIGN WEIGHTS AND CAPACITIES Limit Speeds Never Exceed V ..................... 205 KIAS (380 km/hr) Maximum Ramp Weight ................3,663 lb (1,665 kg) NE Max Structural Cruising VNO ...... 165 KIAS (306 km/hr) Maximum Take-off Weight .............3,650 lb (1,659 kg) Maneuvering V ........................ 141 KIAS (261 km/hr) Maximum Landing Weight .............3,650 lb (1,659 kg) A Basic Empty Weight * ....................2,630 lb (1,193 kg) Flap Extension Speeds Fuel Capacity (Useable ) .....................444 lb (202 kg) VFE (Approach) .........................154 KIAS (285 km/hr) (@ 6.0 lb per U.S gallon) VFE (Full Down) ......................... 124 KIAS (230 km/hr) * Estimated Basic Operating Weight includes standard Landing Gear Operating and Extension Speeds interior, prop de-ice, air conditioning, avionics, VLO/VLE (retraction/extension) .... 154 KIAS (285 km/hr) unusable fuel and oil. CG Range 4. PERFORMANCE Forward Limit to 3,100 lb (1,409 kg) ....................74 in Forward Limit to 3,650 lb (1,659 kg) ....................81 in All performance data is based on a standard aircraft and Aft Limit (at all weights) .................................... 87.7 in International Standard Atmospheric (ISA) conditions. Take-off and landing lengths are based on level, hard 6. FUSELAGE surface, dry runways with zero wind. The fuselage is fabricated of high strength aluminum Range (-3%) .................................910 nm (1,685 km) alloy, with appropriate use of steel and other materials. (1 pilot + 2 passengers, VFR. Range allows for taxi, The aircraft structure uses traditional methods of take-off, climb, cruise, descent and VFR fuel reserve aircraft design and validated through full scale fatigue of 45 minutes at Max. Range Power) testing with no published life limits. The fuselage is shaped to provide optimized cabin room Stall Speed (Flaps Down) ..........58 kt (107 km/hr) IAS and passenger comfort. A maximum internal cabin width (at 3,650 lb/1,659 kg) of 3 ft 6 in. (1.07 m) and maximum cabin height of 4 ft Service Ceiling...............................18,500 ft (5,639 m) 2 in. (1.27 m) is provided. Take-off Field Length ..........................1,913 ft (583 m) Cabin (Sea Level, ISA, 3,650 lb. / 1,659 kg.) The cockpit seating area, passenger seating area and rear baggage area comprise the cabin portion of Landing Distance ...................................950 ft (290 m) the fuselage. The pilot’s entry door is located on the (Sea Level, ISA, 3,650 lb. / 1,659 kg.) forward right side of the fuselage while the passengers enter the cabin through the aft utility door on the right High Speed Cruise Speed (-3%) ....176 kt (326 km/hr) rear side of the fuselage. (ISA, 6,000 ft (1,829 m) altitude, Max. Cruise Power 25 In. Hg (or full throttle) @ 2,500 rpm) The standard seating confi guration consists of club seating in the cabin, with the 3rd and 4th seats facing 5. STRUCTURAL DESIGN CRITERIA aft and the 5th and 6th seats facing forward. The Bonanza G36 wing and fuselage are of conventional Utility Doors semi-monocoque construction. It has fully cantilevered The utility doors, located on the aft right side of the wings and empennage. Most of the structures are cabin, provide for loading and unloading of passengers fabricated of high strength aluminum alloy. Steel and and baggage. The aft door must be closed fi rst. The other materials are used as needed. The robustness forward door cannot be closed until the latch of the aft of the design philosophy has been validated over door is latched and fl ush with the edge of the door. thousands of hours operation of airplanes in the fl eet. After the forward door is closed it can be latched from Continuing structural integrity is ensured through an the outside by rotating a half-moon shaped handle to inspection program and appropriate maintenance the closed position. A conventional handle of the inside action. The aircraft structure is divided into three major of this door provides for opening or closing from the components, the fuselage, wing and empennage. inside. 4 Baggage Compartment 9. LANDING GEAR The baggage compartment is accessible through The Bonanza G36 is equipped with retractable tricycle the utility doors on the right side of the fuselage. The landing gear. The main landing gear uses conventional