T-34 Limitations
Beechcraft T-34C Turbo Mentor · Other Documents
Overview
This document provides critical limitations and operational parameters for the Beechcraft T-34C Turbo Mentor. It is intended for pilots and maintenance personnel to ensure safe and effective operation of the aircraft. The manual covers various aspects including engine performance, airspeed limitations, weight limitations, and other operational limits necessary for flight planning and execution. Pilots will find essential data regarding engine temperatures, torque, fuel flow, and G limits, which are crucial for maintaining the aircraft within its operational envelope.
- Normal operating ITT range: 400-695°C
- Max takeoff weight: 4,400 lbs
- Max clean airspeed: 280 KIAS up to 20,000 feet
- Oil system capacity: 4.4 gallons
- G limits: +4.5/-1.0 G's up to 280 KIAS
Document
Source
Originally published by www.cnatra.navy.mil. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Other Documents
- Pages
- 1
- File size
- 14 KB
- Publisher
- www.cnatra.navy.mil
Common. Rarer than 17% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Beechcraft T-34C Turbo Mentor.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the T-34C Turbo Mentor to your watchlist and track it in one place.
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In this document
Engine Performance
The T-34C Turbo Mentor is powered by a Pratt & Whitney PT6A-25 engine. Key performance metrics include a normal operating ITT range of 400-695°C, with a maximum continuous temperature of 695°C and a maximum acceleration temperature of 825°C. The engine tachometer indicates a normal operating range of 89-93% N1, with maximum values reaching 101.5%.
Airspeed Limitations
The aircraft has specific airspeed limitations that must be adhered to for safe operation. Maximum clean airspeed at surface level up to 20,000 feet is 280 KIAS, reducing to 245 KIAS between 20,000 and 25,000 feet. Other critical speeds include a maximum gear extension speed of 150 KIAS and a full flap landing speed of 85 KIAS.
Weight Limitations
The T-34C has several weight limitations that are crucial for flight safety. The maximum ramp weight is 4,425 lbs, with takeoff and landing weights limited to 4,400 lbs. The maximum aerobatic weight is 4,300 lbs, and the maximum zero fuel weight is 3,650 lbs.
Oil and Fuel Specifications
The oil system capacity is 4.4 gallons, with a usable oil amount of 1.4 gallons when upright. The engine operates with a fuel flow of approximately 335 lbs/hr during normal operation and around 125 lbs/hr at idle.
G Limits
The aircraft is designed to withstand specific G forces, with limits of +4.5/-1.0 G's up to 280 KIAS and +4.5/-2.3 G's up to 220 KIAS. With flaps down, the G limits are reduced to +2.0/-1.0.
Safety notes
- Max time inverted: 15 seconds
- Max operating altitude: 25,000 feet
- Max crosswind component: 22 knots (no flaps), 15 knots (full flaps)
Full document text
T-34 Limitations Operating limits: ITT Normal idle range 400-660°C Normal operating range 400-695°C Max @ shutdown w/cond.lever 610°C Max continuous 695°C Max acceleration 825°C Hot start 925°C (2 sec) Max during starts 1090°C Prop RPM (N 2) Idle operating range <1800RPM Normal operating range 2200 RPM ±25 Over speed governor 2332 RPM ±40 Fuel topping governor 2398 RPM Engine Tachometer (N1) Introduce fuel @ 12% Flameout 10-12% FCU stuck @min.flow(rollback) 40-60% Minimum for flight (griped) 60% Idle operating range 62-65% Normal operating range 89-93% Maximum 101.5% Max acceleration 102.6% Airspeed Limitations Max clean (surface-20,000’) 280 KIAS (20,000- 25,000’) 245 KIAS Max canopy emergency open 250 KIAS Max canopy open 240 KIAS Max turbulent air penetration 195 KIAS Max gear extension 150 KIAS Max flap extension 120 KIAS Max gear retraction 120 KIAS Min flap retraction 90 KIAS Downwind airspeed 100 KIAS VFR/overhead break airspeed 170 KIAS Full flap landing airspeed 85 KIAS No flap landing airspeed 95 KIAS Best angle of climb (Vx) 75 KIAS Best rate ot climb (Vy) 100 KIAS Recommended bailout airspeed 90-120 KIAS Max range airspeed 580 ft-lbs Max endurance airspeed 420 ft-lbs Torque Idle operating range 150 ft-lbs Auto ignition range 300-180… Descent 300… Prop over speed test range 400-500… Normal operating range 400-l015… Climb 1015 (695°C) Max allowable 1015… Maximum torque 1315… Max torque (oil malfunction) 850… Fuel Flow Idle ~125 lbs/hr Normal operation ~335 lbs/hr Oil Temperature Min starting temperature -40°C Normal Operating range 10-99°C Maximum 100°C Oil pressure Idle operating range 40 PSI min Normal operating range 65-85 PSI Maximum fluctuation +5 (within limits) Max oil pressure 100 PSI G Limits Up to 280 KIAS +4.5/-1.0 G's Up to 220 KIAS +4.5/-2.3 G's Flaps down +2.0/-1.0 Time limits Max time inverted 15 sec Max time vertical (nose up) 15 sec Max time vertical (nose down) 3 sec Max time wings vertical (knife edge):3 sec “Zero G” condition transient Starter 40s/60s/40s/60s/40s/30min Dimensions: Wing span 33’ 5” Length 28’8” Height (at rest) 9’11” Tread 9’6” Prop arc clearance 11” Weight limitations Maximum ramp weight 4,425 lbs Takeoff and landing 4,400 lbs Max aerobatic weight 4,300 lbs Max zero fuel weight 3,650 lbs Approximate basic weight ~2,970 lbs Miscellaneous limits Max sink rate @ touch down 600 FPM Max crosswind component 22(NF),15(FF) Max operating altitude 25,000’ Air start envelope, SL-20k’ 80-280 KIAS Engine: Pratt & Whitney PT6A-25 Flat rated 550 SHP(1315) Normal operation 425 SHP(1015) Landing Gear Nose gear turn limits ±30° Main tire pressure 90 PSI ± 2 Nose wheel tire pressure 70 PSI ± 2 Oxygen system capacity 1850 PSI@70°F Oxygen system volume 76 cubic feet Oil system capacity 4.4 gal Oil tank capacity 2.8 gal Usable oil (upright) 1.4 gal (inverted) .25