Beechcraft Travel Air Systems
Beechcraft 95 Travel Air · Specifications
Overview
This document provides detailed specifications and operational guidelines for the Beechcraft 95 Travel Air. It is intended for pilots and aviation enthusiasts who require in-depth knowledge of the aircraft's systems, performance metrics, and operational procedures. Key areas covered include engine specifications, fuel system details, weight and balance procedures, and critical flight parameters. The document also outlines safety considerations and operational limitations essential for safe flight operations.
- Service ceiling: Dual engine 19,300 ft, Single engine 6,800 ft.
- Total fuel capacity: 112 gallons (106 usable).
- Maximum weight: 4200 lbs, Aft baggage limit: 400 lbs, Nose baggage limit: 270 lbs.
- Vmc (minimum controllable airspeed): 84/80 MPH.
- Engine specifications: 2 x Lycoming O-360, 180 hp each.
Document
Source
Originally published by prayaviation.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Specifications
- Pages
- 11
- File size
- 1.3 MB
- Publisher
- prayaviation.com
Most owners only have the POH. Here's the essential set for the Beechcraft 95 Travel Air.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the 95 Travel Air to your watchlist and track it in one place.
More Beechcraft 95 Travel Airmanuals & documents
See all 28 →- SHORT TERM RENTAL COMPLIANCE CHECKLISTChecklist
- Airworthiness Directive AD/BEECH 95/26 Amdt 4Other Documents
- Pray Aviation Beech 95 Travelair FTMPilot's Operating Handbook
- Mandatory Service Bulletin SB 28–4127Other Documents
- SERVICE BULLETIN SB 32-4125Parts Catalog
- Maneuvers ProfilesChecklist
- Airworthiness Directive Schedule Aeroplanes Beechcraft 58 and 95 Series (Baron)Airworthiness Directives
- SERVICE BULLETIN MANDATORY SB 28-4131Service Bulletins
- BPPP Instructor Standards ManualPerformance Data
- SCHEDULE OF AIRWORTHINESS DIRECTIVESOther Documents
- Landing Gear Inspection Checklist and Repair GuideChecklist
- AIRWORTHINESS DIRECTIVE AD/BEECH 95/21Other Documents
If you fly the Beechcraft 95 Travel Air, you may also be researching these.
In this document
Engines
The Beechcraft 95 Travel Air is equipped with two Lycoming O-360 engines, each producing 180 horsepower, totaling 360 horsepower. The engines are 4-cylinder, horizontally opposed, naturally aspirated, carbureted, and air-cooled. The oil capacity is between 6 to 8 quarts per engine, with an emergency minimum of 2 quarts.
Fuel System
The aircraft has a total fuel capacity of 112 gallons, with 106 gallons usable. It features four fuel tanks: two main tanks of 25 gallons each (22 usable) and two auxiliary tanks of 31 gallons each (all usable). The fuel burn rate is approximately 10 gallons per hour. Fuel grade required is 100LL.
Weight and Balance
The maximum weight limit for the Beechcraft 95 Travel Air is 4200 lbs, with specific baggage limits of 400 lbs for aft baggage and 270 lbs for nose baggage. The center of gravity limits are defined as a forward limit of 75 inches aft of datum at a gross weight of 3600 lbs, extending to 80.5 inches at 4200 lbs.
V-Speeds
Key V-speeds for the Beechcraft 95 Travel Air include Vso at 70 MPH, Vs at 80 MPH, Vmc at 84/80 MPH, Vr at 90 MPH, and Vy at 100 MPH. These speeds are critical for safe operation during various phases of flight.
Landing Gear and Flaps System
The landing gear system is fully electrical, utilizing a torque motor for operation. The gear can be manually cranked in case of an emergency. The flaps system operates with an electric motor and can be set to a maximum of 30 degrees.
Safety notes
- Always take off and land on mains.
- Never take off with less than 13 gallons of fuel in the mains.
- Wait 30 seconds before takeoff after high-speed taxi.
Full document text
Service Ceiling Dual engine: 19,300’ Single engine: 6,800’ Engines Specs: 2 x Lycoming O-360 4-cyl horizontally opposed, naturally aspirated, carbureted, air cooled 2 x 180 hp each = Total 360 hp Oil capacity: 6-8 qts per engine (emerg: 2 qts) Fuel burn: 10 gals/hr aside (Except for N948T: IO-360, fuel injected) Propellers Specs: Two-bladed Hartzell constant speed, full feathering props. Maximum 2700 RPM Maintains constant RPM: With oil pressure through the prop governor (speeder springs/flyweights/pilot valve) Nitrogen unfeathering accumulator: Brings prop out of feather (Training purposes only) Locking pins: Prevents props from feathering when engine is 600 RPM. Saves wear and tear on starters. Fuel System Fuel Capacity: 112 total (106 useable) Four Tanks: Two MAIN: 25 gal each (22 usable) Two AUX: 31 gal each (all usable) 4 fuel pumps: 2 engine driven & 2 electric boost 9 fuel sumps: 4 each wing and 1 under nose Fuel grade: 100LL (blue dyed & 6 lbs/gal) Switching tanks: “LOOK BEFORE YOU LEAP” X-Feed: Only from fuel tank to engine Fuel Limitations: 1. ALWAYS T/O & L on MAINS. 2. NEVER T/O with less than 13 gals (yellow arc). 3. WAIT 30 secs before T/O after high speed taxi. Heater Janitrol combustion heater: Located in the nose compartment. Self-contained system. Draws 5 lbs/hr of 100LL from left main tank and ignites in the nose. Blower then circulates hot air throughout the cabin. Switch is activated by the "CABIN VENT" knob on the panel. Electrical 28V system: 1 x 24V battery 2 x 28V alternators – 25 amps (Except for N948T: 70 amps) Circuit breakers: Protects the system Voltage regulator: Balances loads between two alternators. One alt can run the whole system. Gear and Flaps System are: 100% electrical Gear System Sungear system: Uses a torque motor to rotate a circular disk which is connected to push pull rods attached to the landing gear. The push pull rods push the gear and doors out and pulls them in. ‘WOW’ or Squat switch: On Left Main Gear. Prevents the gear from retracting on ground. Other safety systems: Gear warning horn, nose gear indicator and nose gear mirror Gear hand crank: For emergency use (roughly 50 turns counterclockwise) Landing checks: “GREEN, RED, BLUE, ONE IN THE MIRROR” Flaps System Micro switch: Up, Neutral, or Down position Full flaps: 30 “VERIFY FLAPS” Flaps: Uses electric motor connected to flexible torsion cables which drive flaps down with jackscrews Beechcraft Travel Air Systems IACRA: BE-95-95/BE-95-D95A Circle the one you are in: N2VC N2021C N2728Y N948T P T M What is Vmc? Vmc is the minimum controllable airspeed with the critical engine INOP and wind milling. This is determined by FAR 23 under aircraft certification. The FAA developed this list for all twin engine aircraft under 12,500 lbs and are looking for the WORST case scenario. Performance is not accountable in this test, merely aircraft CONTROL or heading. We use the acronym COMBATS. (For more information, reference to YouTube: PrettyFlyForACFI) Vmc Factors (COMBATS): Critical Engine INOP and Wind Milling Operating Engine Takeoff Power (FULL) Max Gross Weight Bank 5 into Good Engine with Zero Sideslip Aft CG Takeoff Configuration ▪ Trimmed for takeoff ▪ Flaps set for takeoff (UP) ▪ Cowl Flaps open ▪ Out of ground effect ▪ Gear UP Sea Level Density Altitude What determines a critical engine? Critical Engine Factors (PAST): P-Factor Accelerated Slipstream Spiraling Slipstream Torque These can be seen in the Vmc Demo How does each of these factors affect Vmc? Does it increase or decrease Vmc? Traffic Pattern: Before Landing Check – Approaches Approach Speed: 120 MPH Base leg to FA course Throttles 17” then: Boost Pumps – ON Cowl Flaps – OPEN Gas – MAINS Precision: ½ dot GS or Non-precision: ½ mile from FAF Throttles 15” then: Undercarriage – DOWN (150 MPH) Mixture – SET (RICH 3000’ DA) Props – HIGH RPM Seatbelts & Switches – LDG/RW LIGHTS Maintain 120 MPH Generally with no flaps V-Speeds (MPH) Vso 70 Vs 80 Vmc – Red Line 84/80 Vr 90 Vx 90 Vxse 90 Glide 100 Vy 100 Vyse – Blue Line 100/108 Normal Climb 120 Vfe 130 Vle 150 Va 160 Vno 185 Vne 240 Weight and Balance Procedure Take the basic empty weight, moment and arm from the weight and balance report in your airplane’s POH. The empty weight is for zero fuel. To the above data add the weight and moment for all pilots, passengers, baggage and fuel. Enter this information on the Weight and Balance form. A sample is provided below: Item Weight Arm Moment Aircraft (reg. GSAK) 2939 234020 Fuel – main tanks 200 75 15000 Fuel – aux tanks 300 93 27900 Pilots 400 85 34000 Passengers 140 136 5040 Cargo – area 1 (Nose compartment) 50 31 1550 Cargo – area 2 (Baggage compartment) 50 150 7500 Ramp Weight 4079 79.7 325,010 Taxi fuel allowance -15 84 -1260 Takeoff Weight 4064 79.7 323750 Fuel Consumed – mains -100 75 -7500 Fuel consumed – aux -75 93 -6975 Landing Weight 3889 79.5 309275 The moment for fuel, pilots, passengers, and cargo is calculated by multiplying the weight for each item by the arm. The arms can be found in the table below. The moments for all items including the empty airplane are then added. In the sample the total is 325,010. This gives the ramp weight and moment. Item Weight Arm Moment Aircraft Fuel – main tanks 75 Fuel – aux tanks 93 Pilots 85 Passengers 136 Cargo – area 1 (Nose compartment) 31 Cargo – area 2 (Baggage compartment) 150 Ramp Weight Taxi fuel allowance -15 84 -1260 Takeoff Weight Fuel Consumed – mains - 75 - Fuel consumed – aux - 93 - Landing Weight Checkride Weight and Balance Procedure Weight Limits Maximum weight: 4200 lbs Aft baggage limit: 400 lbs Nose baggage limit: 270 lbs Center of Gravity Limits Center of gravity limits (gear extended): Forward limit 75 inches aft of datum to gross weight of 3600 lbs, then straight-line variation to 80.5 inches aft of datum at gross weight 4200 lbs. Aft limit – 86 inches aft of datum at all weights Maneuver Limits
Show full textShow less
This is a normal category airplane. Acrobatic maneuvers, including spins, prohibited. Flight Load Factor Limits At design gross weight: Positive 4.4g; negative 3.0g (flaps up) Positive 2.0g); negative 0.0g (flaps down) Gust limits: positive 4.32g; negative 2.32g (flaps up) Item Weight Arm Moment Aircraft Fuel – main tanks 75 Fuel – aux tanks 93 Pilots 85 Passengers 136 Cargo – area 1 (Nose compartment) 31 Cargo – area 2 (Baggage compartment) 150 Ramp Weight Taxi fuel allowance -15 84 -1260 Takeoff Weight Fuel Consumed – mains - 75 - Fuel consumed – aux - 93 - Landing Weight Single Engine Rate of Climb Single Engine Climb Gradient Conditions: Climb on single engine Airspeed at Vyse Propeller on failed engine feathered Approximately 5 degrees bank toward operating engine Note: This chart is based on page 6-9 of the Beechcraft Travelair D95A Owners Manual. All IFR departure procedures require a minimum of 200 ft/Nm climb gradient. Some procedures require more than 200 ft/Nm. Transport Canada regulations do NOT require single engine climb gradients for legal IFR departures but the lack of such climb gradients should cause pilots to prepare alternate plans of action in the event of an engine failure below MEA. Single Engine Ceiling Conditions: All altitudes are ISA Density Altitudes Altitude for 200 ft/Nm climb is with zero wind. Practical Test Checklist (Applicant) Appointment with Evaluator Evaluator’s Name: _______________________________________________ Location: ______________________________________________________ Date/Time: ____________________________________________________ FTN: _________________________________________________________ Acceptable Aircraft □ Aircraft Documents: □ Airworthiness Certificate □ Registration Certificate □ Operating Limitations □ Aircraft Maintenance Records: □ Logbook Record of Airworthiness Inspections and AD Compliance □ Pilot’s Operating Handbook, FAA-Approved Aircraft Flight Manual □ Completed Weight and Balance □ Complete Performance Charts Personal Equipment □ View-Limiting Device □ Current Aeronautical Charts (printed or electronic) □ Computer and Plotter □ Flight Plan Form (Completed XC flight planning if applicable) □ Chart Supplements U.S., Airport Diagrams and appropriate Publications □ Current AIM Personal Records □ Passport or Birth Certificate □ Identification – Photo/Signature ID (government issued) □ Pilot Certificate □ Current Medical Certificate □ Completed FAA Form 8710-1, Airman Certificate and/or Rating Application with Instructor’s Signature (IACRA) □ Original Knowledge Test Report □ Pilot Logbook with appropriate Instructor Endorsements □ FAA Form 8060-5, Notice of Disapproval (if applicable) □ Letter of Discontinuance (if applicable) □ Approved School Graduation Certificate (if applicable) □ Evaluator’s Fee (if applicable) US Military □ College Diploma or Military Pilot School Graduate and Proof of Active Duty □ ARMS Logbook Flight Hours Have your IACRA filled out, logbook endorsements, cross country flight planning, weight and balance and performance charts completed prior to your check ride. (Bold approaches are more frequently used for check rides although the evaluator can use any available airport/approach within the area.) AIRPORTS TO KNOW: NORTH FLOW SOUTH FLOW WICHITA (KICT) ILS 01L, ILS 01R ILS 19L, ILS 19R NEWTON (KEWK) RNAV 35, VOR/DME-A ILS 17, RNAV 17, VOR/DME-A JABARA (KAAO) RNAV 36, VOR-A, GPS-E ILS 18, RNAV 18, VOR-A, GPS-E STEARMAN (1K1) RNAV 17 AUGUSTA (3AU) RNAV 36, VOR/DME-A VOR/DME-A ELDORADO (KEQA) ALL ALL SALINA (KSLN) (PVT, INST, COMM) ALL ALL