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skin with a nomex honeycomb core and a bendable
trailing edge strip to aid in blade tracking. Each blade
secured to its lead-lag link by two blade attachment
pins. These pins can be removed without the use of
tools and they pass vertically through the lead-lag link
and blade root fittings which are both made of titanium.
Five sets of stainless steel doublers are located
on the upper and lower surfaces of the blade at the
blade root. The blades may be folded by removing the
appropriate blade attachment pin (one for each blade)
and any two adjacent pitch link bolts and pivoting the
blade to the rear position using a hand-held blade support
device.
2.41.2 Tail Rotor. The tail rotor is of semirigid, teetering
design. Two pairs of blades, each pair fastened to its
own delta hinged hub, provide antitorque action and
directional control. A titanium fork houses two elastomeric
teetering bearings and drives the rotating swashplate
through an attached scissors assembly. The tail
rotor assembly is splined to, and driven by, the tail rotor
gearbox drive shaft which passes through a static mast.
Blade pitch changes when directional control inputs
cause the non-rotating swashplate to act upon the rotating
swashplate. One pitch link for each blade, attached
to the rotating swashplate and pitch horn,
causes blade movement about two pitch-change bearings
in the blade root. Centrifugal forces are carried by
stainless steel strap assemblies that attach outboard to
the blade root and inboard at the hub center. An elastomeric
bearing assembly positions the hub and strap
pack in the tail rotor fork. Each blade has one stainless
steel spar and two aluminum spars. Doublers and rivets
attach the blade to the blade root. Brackets on the
root fitting hold chord-wise balance weights. Spanwise
balance weights are installed at the tip of each blade in
an aluminum tip cap.
2-59

TM 1-1520-238-10
AIR DATA DC circuit breaker to the left wing pitot
heater. Both circuit breakers are on the pilot overhead
circuit breaker panel. The AIR DATA DC circuit
breaker also provides 28 vdc to the ADS control relay.
When energized, this relay sends 115 vac from the No.
1 essential ac bus through the AIR DATA AC circuit
breaker to the air data sensor for anti-icing. In addition,
the CPG AUX panel ADSS switch, when set to on,
energizes the ADS control relay to provide the air data
sensor with 115 vac from the No. 3 essential ac bus
through the AIR DATA AC circuit breaker.
2.43.3 PNVS and TADS Anti-Ice/De-Ice. Three position
TADS/PNVS toggle switches on the pilot ANTIICE
panel and the CPG AUX/ANTI-ICE panel control
the operation of the TADS/PNVS window heaters.
These switches receive 28 vdc from the No. 1 essential
dc bus through the CANOPY ANTI-ICE CONTR circuit
breaker. Window heating is automatically controlled
by a thermal control sensor in the respective
heater power return circuits.
a. In Flight TADS/PNVS Anti-Ice/De-Ice. With the
helicopter in flight and the pilot or CPG TADS/PNVS
switch set to ON, the squat switch relay closes to provide
28 vdc from the pilot or CPG TADS/PNVS switch
to the MRTU. This causes the MRTU to send a signal to
energize anti-ice relays in the TADS power supply and
PNVS electronic unit. The TADS and PNVS anti-ice relays
then provide the TADS and PNVS window heaters
with 115 vac from the No. 1 essential ac bus through
the TADS AC on the CPG circuit breaker panel and the
PNVS AC circuit breakers on the pilot overhead circuit
breaker panel.
b. On Ground TADS/PNVS Anti-Ice/De-Ice. When
the helicopter is on the ground, the squat switch opens
removing power from the TADS/PNVS switches and
the TADS and PNVS window heaters. When either
TADS/PNVS switch is set to GND, a signal is sent to
the MRTU which energizes the TADS/PNVS anti-ice
relays. These relays then provide the TADS and PNVS
window heaters with 115 vac from the No. 1 essential
ac bus through the TADS AC and PNVS AC circuit
breakers.
2.43.4 Engine Inlet and Nose Gearbox Anti-Ice. Engine
bleed air is used to heat the engine air inlet, and
heater blankets are used to anti-ice the nose gearbox.
Engine anti-ice protection is controlled by a ENG INLET
ON/OFF toggle switch on the pilot ANTI-ICE
panel. In the ON position, ENG 1 and ENG 2 advisory
lights located above the switch will illuminate when the
system is functioning properly. The engine anti-ice
valves and engine gearbox heater blanket controller receive
28 vdc from the No. 1 essential dc bus through the
ENG ANTI-ICE circuit breaker on the pilot overhead
　
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