MAY 2015 Chapter 4 Airworthiness Limitations Page 4.7
Page 3 of 5 R00015LA
Number of Seats 5 (4 for Police Version)
Seat Locations Pilot and forward occupant at STA 49.0 in
Aft outboard occupants at STA 80.0 in
Aft center occupant at STA 78.0 in
Maximum Compartment Main baggage compartment
Weights Maximum weight is 300 lb at STA 107.0 in
Maximum loading density is 50 lb/ft
2
Underseat baggage compartments
Forward seats – Maximum weight is 50 lb at STA 42.0 in
Rear seats – Maximum weight is 50 lb at STA 82.0 in
Note: For any seat location, the maximum combined weight of the
load on the seat (e.g., occupant) plus the weight of stowed items
and any installed equipment in the underseat baggage
compartment is 300 lb.
Fuel Capacity Fuel tank capacity is 74.6 U.S. gallons
Usable fuel quantity is 73.6 U.S. gallons at STA 102.5 in
Note: Aircraft empty weight includes 1.0 U.S. gallon of unusable fuel.
Oil Ca
aci
ies Com
onen
Ca
acit
t
STA
in
En
ine 6 126.0
Main Rotor Transmission 2 100.0
Tail Rotor Transmission 0.11 327.0
H
draulic Reservoi
0.65 110.8
Maximum Operating Altitude
14,000 feet Density Altitude.
ground level is 9,000 ft.
Rotor Blade and
Control Movements
Main Rotor Blades Collective Pitch 13.0° ±0.5° total travel
Cyclic Pitch
Forward 13.50° to 14.25°
Af
13.50° to 14.25°
Lef
7.5° to 8.5°
Ri
h
6.0° to 7.0°
Note: Collective low pitch to
be established in accordance
with the Maintenance Manual and Instructions for
Continued Airworthiness (RTR 660) procedures to
obtain proper autorotation RPM.
Tail Rotor Blades
Collective Pitch
Full right
edal
15.5° to 16.5°
edal
8.5° to 19.0°
All blade angles measured at 75% radius
Manufacturer’s Serial Numbers 0002 and subsequent.
Certification Basis 14 CFR part 27, dated February 1, 1965, as amended by Amendment 27-1 through
Amendment 27-44.
Equivalent Safety Finding:
Number AT14992LA-R-S-1
RHC Note: Tail rotor blades collective pitch full left pedal should be "18.5° to 19.0°".
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