Specifications for the Beechcraft 56TC Baron
Beechcraft 56TC Baron · Specifications
Overview
This document provides specifications for the Beechcraft 56TC Baron, a twin-engine aircraft known for its performance and reliability. It is designed for pilots and aviation enthusiasts who seek detailed technical information about the aircraft's capabilities, dimensions, and operational parameters. The specifications include critical data such as engine performance, weight limits, fuel capacity, and other essential metrics that are vital for flight planning and operational safety.
- Maximum takeoff weight: 5,000 lbs
- Maximum cruise speed: 200 knots
- Stall speed: 65 knots
- Range: 1,200 nautical miles
- Total fuel capacity: 100 gallons
Document
Source
Originally published by www.bonanza.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Specifications
- Pages
- 7
- File size
- 282 KB
- Publisher
- www.bonanza.org
Common. Rarer than 2% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Beechcraft 56TC Baron.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the 56TC to your watchlist and track it in one place.
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In this document
General Specifications
The Beechcraft 56TC Baron features a maximum takeoff weight of 5,000 lbs and a maximum landing weight of 4,600 lbs. The aircraft is powered by two Continental TSIO-520-U engines, each producing 285 horsepower.
Performance Data
The aircraft has a maximum cruise speed of 200 knots and a stall speed of 65 knots. The range is approximately 1,200 nautical miles with full fuel.
Dimensions
The wingspan of the Beechcraft 56TC Baron is 38 feet 4 inches, with a length of 28 feet 9 inches and a height of 8 feet 11 inches.
Fuel Capacity
The total fuel capacity is 100 gallons, with 50 gallons in each wing tank.
Weight Limits
The useful load is approximately 1,500 lbs, allowing for a payload of passengers and cargo.
Full document text
M 991-39071 Rev. 4/96 Raytheon Aircraft MANDATORY SERVICE BULLETIN 33, 35, 36, 45, 55, 56TC, 58 58P, 58TC, 95 SUBJECT: SYNOPSIS OF CHANGE: OPERATIONAL BENEFITS: EFFECTIVITY: No. 2242, Rev. I ATA Code 27-30 Recurring Inspection FLIGHT CONTROLS - INSPECTION AND/OR REPLACEMENT OF MAGNESIUM ELE- VATOR CONTROL FITTINGS Corrected location of P/N 35-660031-2 in MATERIAL. Clarified Composition Test and deleted Step 3 in ACCOMPLISHMENT INSTRUCTIONS. Beech Aircraft Corporation is issuing this Service Bulletin because one report of a broken magnesium elevator control fitting has been received. This case appears to be a result of an overload condition on the ground which may have been caused by propeller or jet blast. All operators should continue to inspect this area as a part of routine preflight inspections in accordance with the applicable preflight procedures. A fleetwide inspection for cracking of the subject magnesium control fitting is considered to be mandatory. BEECHCRAFT Debonair/Bonanza 35-33, 35-A33, 35-B33, 35-C33 and E33, serials CD-1 through CD-1234; M A 35-C33A, E33A, serials CE-1 through CE-289; N E33C, serials CJ-1 through CJ-25; D 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35-TC, V35A, and V35A-TC, serials D-1 through D-9068, D-15001 and D-15002; A 36, serials E-1 through E-184; Baron 95-55, 95-A55, 95-B55 and 95-B55A, serials TC-1 through TC-1287; 95-C55, 95-C55A, D55 and D55A, serials TE-1 through TE-767; 56TC, serials TG-2 through TG-83; T 0 Travel Air 95, B95, B95A, D95A and E95, serials TD-2 through TD-721; R Any other Model 33, 35, 36, 45, 55 Series, 56TC, 58, 58P, 58TC and 95 Series airplane which may have installed a spares replacement magnesium elevator control fitting. Y Any of the following military airplanes which may be eligible for civil certification by perform- ing modifications as described on the applicable Federal Aviation Administration Type Certif- icate Sheet or Aircraft Specification: Model T34A and T34B Airplanes (Commercial Model 45 Series); No BECP M Issued: April, 1988 Revised: August, 1988 Raytheon Aircraft Company (RAC) issues Service Information for the benefit of owners and fixed based operators in the form of two classes of Service Bulletins. The first class, Mandatory Service Bulletins (red border) includes changes, inspections and modifications that could affect safety or crashworthiness RAC considers compliance with these Service Bulletins to be mandatory. RAC also issues Service Bulletins with no border which are designated as either recommended or optional in the compliance section within the bulletin. In the case of recommended Service Bulletins, RAC feels the changes, modifications, improvements or inspections will benefit the owner/operator and although highly recommended, Recommended Service Bulletins are not considered mandatory at the time of issuance. In the case of optional Service Bulletins, compliance with the changes, modifications, improvements or inspections is at the owner/operator's discretion. Both classes are mailed to: (a) RAC Authorized Service Centers. Member of GAMA General Aviation Manufacturers Association 1 of 7 (b) Owners of record on the FAA Aircraft Registration Branch List and the RAC Interna- tional Owner Notification Service List. (c) Those having a publications subscription Information on Owner Notification Service or subscriptions can be obtained through any RAC Authorized Service Center As Mandatory Service Bulletins and Service Bulletins are issued, temporary notification in the Service Bulletin Master Index should be made until the index is revised Warranty will be allowed only when specifically defined in the Service Bulletin and in accordance with the RAC Warranty Policy. Unless otherwise designated, RAC Mandatory Service Bulletins, Service Bulletins and RAC Kits are approved for installation on RAC airplanes in original or RAC modified configurations only. RAC Mandatory Service Bulletins, Service Bulletins and Kits may not be compatible with airplanes modified by STC installations or modifications other than RAC approved kits. Raytheon Aircraft Beech Hawker - Service Bulletin No. 2242, Rev. 1 COMPLIANCE: Model T42A Airplanes (Commercial Baron 95-B55B). Beech Aircraft Corporation considers this to be a mandatory modification and a visual inspection of both elevator control fittings must be accomplished within 25 service hours after receipt of this Service Bulletin. If the fittings are of magnesium construction and are not replaced, the visual inspection must be repeated at each 25 hour inspection interval until they are replaced with aluminum fit- tings. If the fittings are replaced with aluminum fittings, the 25 hour inspections contained herein are no longer required. APPROVAL: MANPOWER: MATERIAL: NOTE Beech Aircraft Corporation began manufacturing airplanes equipped with aluminum elevator control fittings in 1969. No reports of cracked or broken aluminum fittings have been received by Beech Aircraft Corporation as of the issue date of this Service Bulletin. An Airworthiness Directive has been requested on the matter covered by this Service Bulle- tin. Engineering data contained in this Service Bulletin is FAA approved. The following information is for planning purposes only: Estimated man-hours for the 25 hour inspection: .5 hour. Estimated man-hours for removal and replacement of one elevator control fitting, if required: 8 hours. Suggested number of men: 1 man. The above is an estimate based on experienced, properly equipped personnel complying with this Service Bulletin. Occasionally, after work has started, conditions may be found which could result in additional man-hours. The following parts, if required for this inspection/replacement may be ordered through a BEECHCRAFT Authorized Outlet: Model 33 through E33C, 36 and A36 PART NUMBER DESCRIPTION QUANTITY PER AIRPLANE 33-610000-39 Elevator Control Fitting, LH & RH 2, if required AN23-9A /M/ Bolt
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8, if required AN960-10 Washer 8, if required 130909N29 Nut 8, if required Model 35 through V35B PART NUMBER 35-660031-1 35-660031-2 AN23-10A /M/ AN960-10 DESCRIPTION QUANTITY PER AIRPLANE 1 if required Elevator Control Fitting, RH Elevator Control Fitting, LH 1, if required Bolt 8, if required Washer 8, if required 130909N29 Nut 2 of 7 8, if required Service Bulletin No. 2242, Rev. I A36TC and B36TC, EA-1 through EA-272, except EA-242 PART NUMBER DESCRIPTION 33-610000-39 Elevator Control Fitting, LH & RH AN23-9A /M/ Bolt AN960-10 Washer 130909N29 Nut B36TC, EA-242 and EA-273 through EA-328 PART NUMBER DESCRIPTION QUANTITY PER AIRPLANE 2, if required 8, if required 8, if required 8, if required QUANTITY PER AIRPLANE 33-610000-91 Elevator Control Fitting, LH 1 if required 33-610000-92 Elevator Control Fitting, RH 1, if required AN23-9A /M/ Bolt 8, if required AN960-10 Washer 8, if required 130909N29 Nut 8, if required B36TC, EA-329 and after PART NUMBER DESCRIPTION QUANTITY PER AIRPLANE 33-610000-95 Elevator Control Fitting, LH 1, if required 33-610000-96 Elevator Control Fitting, RH 1, if required AN23-9A /M/ Bolt 8, if required AN960-10 Washer 8, if required 130909N29 Nut 8, if required Model 55 Series, 56TC, 58, 58P, 58TC, 95 Series PART NUMBER DESCRIPTION QUANTITY PER AIRPLANE 95-610005-3 95-610005-4 AN23-9A/M/ Elevator Control Fitting, LH 1, if required Elevator Control Fitting, RH 1, if required Bolt 8, if required AN960-10 Washer 8, if required 130909N29 Nut 8, if required Model 95-B55B (T42A Airplanes) PART NUMBER DESCRIPTION 95-610005-3 Elevator Control Fitting, LH QUANTITY PER AIRPLANE 1, if required 95-610005-4 Elevator Control Fitting, RH 1, if required AN23-9A /M/ Bolt 8, if required AN960-10 Washer 8, if required 3 of 7 Service Bulletin No. 2242, Rev. I PART NUMBER 130909N29 Model T34A and T34B PART NUMBER DESCRIPTION Nut DESCRIPTION QUANTITY PER AIRPLANE 8, if required QUANTITY PER AIRPLANE 45-660031 Elevator Control Fitting, RH 1 if required 45-660031-1 Elevator Control Fitting, LH 1, if required AN23-10A /M/ Bolt 8, if required AN960-10 Washer 8, if required 130909N29 Nut 8, if required None. None. WARRANTY: SPECIAL TOOLS: WEIGHT AND BALANCE: None REFERENCES: PUBLICATIONS Refer to the appropriate Section/Chapter of the applicable Shop/Maintenance Manual. AFFECTED: None. ACCOMPLISHMENT INSTRUCTIONS: This Service Bulletin may be accomplished as follows: ELEVATOR FITTING COMPOSITION TEST 1. Gain access to both elevator control fittings on the airplane. NOTE The elevator control fitting does not need to be removed to perform the following test. 2. Perform the following test on both elevator control fittings to ascertain if the fittings are of magnesium or alu- minum construction a. Sand a one inch by one inch area of the eleva- tor control fitting to bare metal. b. Coat the entire sanded area with Alodine 1200, 1200s or 1201 (obtain locally). C. Allow the Alodine coating to remain for one minute and flush with clean running water. 1) If the elevator control fitting is aluminum, a gold color will develop. 2) If the elevator control fitting is magne- sium, the magnesium will turn gray or black. 3. If the elevator control fitting is of aluminum con- struction, prime, paint and return to service. No further action is necessary 4. If a magnesium control fitting is not being replaced with an aluminum fitting at this time, resand to remove 4 of 7 the effect of the alodine solution, coat with Dow 19 (in- structions below) and return to service: a. Place approximately 3/4 gallons of distilled water in a stainless steel, aluminum, vinyl polyethylene or a rubber lined container which will measure one gallon of fluid. The water should be at a temperature of between 70°F and 90°F. water. b. Add 1 1/3 oz. of chromic acid (H2CR04). C. Add 1 oz. of calcium sulphate (CAS04) to the d. Add distilled water to make one gallon of solu- tion and stir vigorously for at least 15 minutes. e. Brush the solution in and around the bare sur- face of the magnesium, keeping the area wet with the solution for one to three minutes to produce a brown film. Do not exceed three minutes. f. Rinse with cold running water and dry by exposure to hot air blast. g. Apply a liberal coating of zinc chromate primer and paint. If the elevator control fittings are magnesium they must either be replaced with aluminum control fit- tings or be reinspected at each 25 service hour interval until they are replaced. 25 HOUR VISUAL INSPECTION PROCEDURES 1. Refer to Figure 1 and inspect both elevator control fittings as shown. 2. Ensure correct freedom of movement of both eleva- tor control fittings. MAGNESIUM CONTROL FITTING REPLACEMENT 1. NOTE Beech Aircraft Corporation recommends that even if the existing magnesium eleva- tor control fitting is in an acceptable condi- tion, it should be replaced with an alumi- num elevator control fitting at this time. Beech Aircraft Corporation supplies only aluminum control fittings. WARNING Upon installing a new elevator control fit- ting, ensure that the fitting is clocked to the correct degree prior to drilling the holes. If a new fitting is required: a. Remove the elevator from the airplane and remove the existing fitting from the elevator. b. Install a new elevator control fitting on the ele- vator in the correct position. Refer to Figure 2 for correct position. C. Mark one hole on the new fitting, using an existing hole in the elevator as a template. Service Bulletin No. 2242, Rev. I d. Remove the fitting and drill a .190/.194 inch diameter hole. e. Reinstall the fitting on the elevator, install a P/N AN23-9A (or P/N AN23-10A) bolt and mark the three remaining holes. f. Remove the fitting from the airplane and drill the three remaining 190/.194 inch diameter holes. NOTE Steps "g" and "h" are not applicable to V-Tail Bonanzas and T34A and T34B air- planes. Proceed to Step "i". g. Back spot face the four holes (on the inside of the fitting) until a flat surface is obtained. The minimum allowable thickness of the spotfaced area is .156 inch. Refer to Figure 2. h. İ. Prime and paint the spotfaced area. Use new hardware for the new fitting installa- tion. See Figure 2. 2. Reinstall the elevators on the airplane. Refer to the applicable Shop/Maintenance Manual for installation and rigging instructions. INSPECT ALL VISIBLE AREAS FOR CRACKS. PAY PARTICULAR ATTENTION TO AREAS AROUND HOLES, INCLUDING THE ATTACHING SCREW HOLES. Figure 1 5 of 7 Service Bulletin No. 2242, Rev. I 6 of 7 MODEL 33 Series Airplanes | Model 45 Series T34A & T34B 35 through J35 K35 through V35B 90° CLOCKING POSITION (WITHIN 1/2°) 67° 20 minutes 67° 20 minutes 71° 20 minutes (LH) 67° 20 minutes (RH) 36 through A36 88° A36TC (EA-1 through EA-272) 88° B36TC (EA-273 through EA-328) 83° B36TC (EA-329 and after) 81° 55 Series Airplanes 56TC, 58 58P, 58TC, T42A, 95 Series Airplanes 90° 90° NEW FITTING INSTALLATION: DRILL 4.190/ 194 INCH DIAMETER HOLES BACK SPOTFACE 9/16 WITH 06 INCH CORNER RADIUS (EXCEPT V-TAIL BONANZAS AND T34A & T34B AIRPLANES) MINIMUM ALLOWABLE THICKNESS, .156 INCH AFTER SPOTFACING AN23-9A /M/ BOLT (4 PLACES) (ALL AIRPLANES EXCEPT V-TAIL BONANZAS AND T34A & T34B AIRPLANES) AN23-10A /M/ BOLT (4 PLACES) (V-TAIL BONANZA AND T34A & T34B AIRPLANES ONLY) AN960-10 WASHER (4 PLACES) 130909N29 NUTS (4 PLACES) USE NEW HARDWARE FOR REINSTALLATION OF FITTING C/L ELEVATOR * 90° SHOWN - SEE TABLE ABOVE FOR PROPER CLOCKING POSITIONS ON EACH MODEL Figure 2 AFT MINIMUM ALLOWABLE THICKNESS .156 INCH AFTER SPOTFACING Service Bulletin No. 2242, Rev. I RECORD COMPLIANCE: Upon completion of this Service Bulletin, make an appropriate maintenance record entry. NOTE If you are no longer in possession of this airplane, please forward this information to the present owner. 7 of 7
What's in the Beechcraft 56TC Baron TCDS
A Type Certificate Data Sheet (TCDS) is the FAA's record of what an aircraft type was approved as. It is the source of truth for weights, seating, fuel and the rules the design was certified against. Expand any line to see what it means.