Limitations Flashcards
Max Gross Weight Internal Load
3200 lbs @ 75 psf
Max Gross Weight External Load
3350 lbs
Max Gross Weight – Fixed Floats
3000 lbs
Max Gross External Load – Fixed Floats
3350 lbs
Max Cargo Hook Load
1500 lbs
Max Fixed Cargo Hook Load
1200 lbs
Minimum Cockpit Weight
170 lbs
Maximum Cockpit Weight
550 lbs
Maximum Baggage Compartment Weight
250 lbs @ 86 psf
Min Approved Empty Wt (C of G Calc required)
1500 lbs
Minimum Cockpit Weight with Range Extender
200 lbs
Maximum Cockpit Weight with Range Extender
400 lbs
Maximum Aft Passenger Weight with Range Extender
510 lbs
Max Bag Compartment Wt With 3 Rear Pax and Range Extender
110 lbs
Max Alt GW < 3000 Lbs
20,000’ PA
Max Alt GW > 3000 Lbs
13,500’ DA
Max Alt Fixed Floats
15,000’ PA
Pressure Altitude
Alt shown with alt set to 29.92
Density Altitude (Pa corrected for Temp)
Pa + (100x(actual T° - standard T°))
ICAO Standard Day
15°C at SL (-2°/1000’)
Vne Power On < 3000 lbs
150 mph < 3000 lbs (-4 mph /1000’ > 3000’)
Vne Power On > 3000 lbs
140 mph > 3000 lbs (-8 mph/1000’ > 3000’)
VNE Auto
115 mph a/s >=high rate of descent/low Nr
VNE Aft doors off
100 mph (-1 mph/1000’ > 3000’)
VNE Front doors off
80 mph (-1 mph/1000’ > 3000’)
VNE Takeoff torque 85%-100%
92 mph (upper mast bearing wear/mast bending)
VNE – Fixed Floats
120 mph (-5 mph/1000’ > 3000’)
VNE – Fixed Floats – Autorotation
100 mph
VNE – Fixed Floats – left FWD door removed
90 mph
VNE - Cargo Hook & Gross Weight > 3000 lbs
91 mph
Best Rate of Climb
60 mph
Min Rate of Descent
60 mph
Maximum Glide Configuration
80 mph / 90% Rotor RPM
Max Sideways/X-wind
20 mph
Max Rearwards
20 mph
Take Off Power Limits Tq, TOT, N1
Tq 100% TOT 810°C N1 105% for 5 minutes
N2 – Power Turbine Power On
97 – 100%
N2 – Power Turbine Transient
105% for 15 sec
N2 – Power Turbine Avoid continuous ops between
75-88% N2 above 30% Tq Max 60 sec
N2 – Power Turbine Flight Idle Autorotation
98% N2
N2 – Power Turbine drives
N2 tach gen, gearbox, accessories
Nr - Rotor Power On
97 – 100%
Nr - Rotor Power Off (autorotation)
90 – 107% (high Nr=max rotor energy for landing but will increase rate of descent)
Nr - Rotor Autorotation touchdown min
Prior to 70% Nr
Nr - Rotor Transient RPM Droop
95% for max 5 sec
Nr - Rotor Acceleration Range (aqap with cyclic neutral)
50-60% Nr to avoid t/r resonance
Rotor Brake Actuation Speed
38%-30% Nr
Rotor brake limit prevents
Excessive brake wear/overheating
Stress on gear boxes
Uncontrolled rotation on slippery surfaces
Main Blade Tip Tie-down load
Max 100 lbs
Main Blade Tip Tie-down deflection
Max 24”
Main rotor
Semi-rigid system (flaps & feathers)
Main rotor mast tilt longitudinal
Fwd 5° for level fuselage when disc tilted fwd
Main rotor mast tilt lateral
Left 1.5° to allow for t/r drift
Main rotor diameter
33’ 4”
Main rotor rpm at 100% N2
394 rpm
N1 - Gas Producer Max
105%
N1 - Gas Producer Transient
106% for 15 seconds
N1 - Gas Producer Drives
Eng fuel pump, N1 tach gen, oil pumps, starter/gen, Air/oil separator, gear train in the accessory gate
Tq - Torque Take Off
100% for 5 minutes
Tq - Torque Transient
110% for 5 seconds
Tq - Torque Max Continuous
85%
TOT Continuous
100-738°C
TOT Take Off
738-810°C for 5 minutes
TOT Power Transient
810-843°C for 6 seconds
TOT Start
810-927°C for 10 sec/927 for 1 sec
TOT Residual TOT max prior to start
<150°C
TOT Exceeding 810°C or Tq 100% may cause
N1 topping and rotor droop
Engine Anti-Ice/Pitot Heat
OAT > 4.4°C
Engine Anti-Ice/Pitot Heat
Visible Moisture AND OAT < 4.4°C
Engine Anti-Ice Test
Rise of 10-20°C
Engine Anti-Ice
inlet guide vanes/front bearing support hub
Tail Rotor Feather bearing free play
¼” at Blade tip
Tail Rotor Pitch Change Link Radial & Axial Free play
10/1000”
Tail Rotor Clearance between blade tip and tail boom skin
1”
Tail Rotor Design
Delta hinge
Snow Baffles (Engine Air Induction System Deflector Kit) Additional Mandatory Equipment
Particle Separator Engine Relight (not above 12,000`)
Snow Baffles (Engine Air Induction System Deflector Kit) Hover/Flight/Ground Ops in blowing/falling snow
20 minutes with vis > ½ mile
Snow Baffles (Engine Air Induction System Deflector Kit) Ground Idle Operation
5 minutes (shutdown and inspection required)
Snow Baffles (Engine Air Induction System Deflector Kit) Snow Baffle Removal
26.7°c
Starter Limitation - battery start
40s/60s ; 40s/60s ; 40s/30 min
Starter Limitation - external Power
25s/30s ; 25s/30s ; 25s/30 min
Load Meter Maximum
70%
External Power Supply required
28v 400a
Generator Output
30v 100/150a derated to 105a
Generator driven from
engine reduction gearbox Compressor access drive
Battery – max temp
60°C
Battery
24v 13 amp-hour or 17 amp-hour
Cargo Hook Max GW
3350 lbs
Cargo Hook Max capacity
1200/1500 lbs
Cargo Hook Vne > 3000 lbs
91 mph
Cargo Hook Cautions
Check slung load clearance and obstacles
Avoid flight over people/vehicles/structures
High hover till cargo touches ground then maintain tension and press cargo release
Power Plant Allison Turbine or Rolls Royce
Model 250-C20B or 250-C20J
Power Plant Shaft Horsepower
420 d/r to 317 (t/o) 270 (max cont)
Power Plant 2 stage compressor
Axial & centrifugal ratio 6:1
Power Plant Compressor on start
Driven by generator
Power Plant Compressor after start
Driven by N1 gas producer
Power Plant N2 drives
Gearbox and accessories
C OF G Forward - Aft
106.0 forward – 114.2 aft
C OF G Left - Right
3.0 left 4.0 right
C OF G Fore/Aft with one or both front doors off or front/rear combo off
106.0 forward – 110.0 aft
C OF G vs Fuel burn
Moves forward with fuel burn
C OF G Datum (Station 0)
screws on pitot tube mount
55.16” fwd of fwd jackpoint centerline
C OF G Calculation
must be calc with fwd doors removed
Wt x arm = moment
total moment ÷ total wt = total arm
C OF G Rate of climb reduction with any door off
-350 fpm
OAT Temp limits min
-40°C
OAT Temp limits max
+52°C at SL - 2°/1000’
Altitude Limits
SL – 20,000 PA
Certified Noise Level
82.6 dBA
Width
6.28 ft
Length
39.21 ft
Height
11.63 ft
Engine Oil Capacity
5.5 qt MIL-PRF23699 >-40°C /MIL-PRF7808
Transmission/Freewheel Oil Capacity
5 qt
Tail Rotor Gear Box Oil Capacity
0.38 Pint
Log Book Entry Required each time
eng/trans/trgb oil added Brand/type/quantity
Engine Oil pressure range
50-130 psi
Engine Oil Pressure Minimums
< 78.5 N1
78.5 - 94.2 N1
> 94.2 N1
50 psi
90 psi
115 psi
Engine Oil temp range
0-107°C
Freewheel oil supply
Main gear box
Hydraulic Capacity
1 Pint
Hydraulic Fluid pressure range
600 +/- 25 psi
Hydraulic pump driven from
Main rotor gear box
Fuel Capacity Standard Tank
77.06 US Gallons
Unusable Fuel Standard Tank
Boost Pumps On
1.06 US Gallons
Fuel Capacity Large Tank
92.06 US Gallons
Unusable Fuel Large Tank
Boost Pumps On
1.03 US Gallons
Fuel Capacity Range Extender
96.70 US Gallons
check gauge each 15 min
Unusable Fuel with Range Extender
Boost Pumps On
1.06 US Gallons
Unusable Fuel – 1 or 2 Boost Pumps Off
10 US Gallons
Average Fuel Consumption
30 Us Gallons / Hour
Jet A (Limited to: OAT > -18°C)
6.8 lbs / US Gallon Jet A, Jet A1, JP5, JP8
Jet B (May be used at all temperatures)
6.4 lbs / US Gallon Jet B, JP4
Min Fuel press cold wx ops -18°C to -32°C
8 psi (Jet A, Jet A1, JP5, JP8) red triangle
Heli with airframe fuel filter
Anti-icing additive not required at any temp
Fuel Pump pressure range
4-30 psi
Trans Oil pressure range continuous
30-50 psi
Trans Oil pressure range max
70 psi
Trans Oil temp range
15-110°C
Transmission reduction ratio
6016 eng output rpm to 394 rotor rpm
Pop Out Floats VNE Inflated Airspeed
80 mph
Pop Out Floats VNE Autorotation Airspeed
70 mph
Pop Out Floats VNE Inflation Airspeed
60 mph
Pop Out Floats Max Inflation Altitude
<2000 ft agl
Pop Out Floats Max Rate of Climb
1000 fpm
Bleed Air Valve Location
5th stage compressor
Bleed Air Valve During start, acceleration, low comp ratio ops
Open to unload compressor & prevent blade stall & surge
Bleed Air Valve Closes at
Closes at 87% N1
Bleed Air Heat Prohibited (8)
Eng fail, insufficient pwr, fcu/gov fail, eng overtemp, OAT>5°C, t/o, ldg, >85% Tq
Bleed Air vs TOT
TOT will rise 20-50°C
Carbon Monoxide Detector
Monitor
ventilate as required
