曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費(fèi)者

the vertical stabilizer. This air cools both the tail rotor
gearbox and the intermediate gearbox. Four thermistors
monitor temperature and an accelerometer measures
vibration limits. The intermediate gearbox is a
grease-lubricated sealed unit.
a. intermediate Gearbox Caution Light indicators.
The four thermistors and the accelerometer provide
crewmembers with temperature and vibration
caution lights. Both crew stations have TEMP INT and
VIB GRBX light segments.
Prolonged out of ground effect hovering
(20 - 30 min.) with outside air
temperatures above 75 °F (24 °C) may
cause the tail rotor gearbox to overheat.
2.40.6 Tail Rotor Gearbox. The tail rotor gearbox,
mounted on the vertical stabilizer, reduces the output
rpm and changes the angle of drive. The tail rotor output
shaft passes through the gearbox static mast. All
tail rotor loads are transmitted to the static mast. The
output shaft transmits only torque to the tail rotor. Lubrication
of this gearbox is identical to that of the intermediate
gearbox.
a. Tail Rotor Gearbox Caution Light indicators.
The four thermistors and the accelerometer
function in the same way as for the intermediate gearbox.
The associated caution light on the pilot and CPG
caution/warning panels are labeled TEMP TR and
VIB GRBX. (Both the intermediate and tail rotor gearboxes
activate the VIB GRBX light segment).
TM 1-1520-238-10
Section Vlll. ROTORS
2.41 ROTOR SYSTEM.
The rotor system consists of a single, four-bladed, fully
articulated main rotor and a four-bladed tail rotor assembly
with two teetering rotor hubs.
2.41.1 Main Rotor. The main rotor has four blades.
The head is a fully articulated system that allows the
four blades to flap, feather, lead, or lag independent of
one another. The head consists of a hub assembly, pitch
housings, rotor dampers, and lead-lag links. Attached
to the rotor head are four easily removable blades. The
main rotor is controlled by the cyclic and collective
sticks through a swashplate mounted about the static
mast.
a. Hub Assembly. The main rotor hub is a steel
and aluminum assembly that supports the main rotor
blades; it is driven by the main rotor drive shaft. The
hub rotates about a static mast, which supports it. This
arrangement allows the static mast, rather than the
main rotor drive shaft, to assume all flight loads. The
hub is splined to the main rotor drive shaft by means of
a drive plate adapter that is bolted to the hub. The hub
is secured to the static mast by a large locknut secured
by multiple bolts. The hub houses two sets of tapered
roller bearings that are grease-lubricated and sealed.
These bearings transfer hub loads to the static mast.
Mechanical droop stops limit blade droop. When blade
droop occurs, a striker plate on the pitch housing contacts
a roller. The roller presses a plunger against a
droop stop ring on the lower portion of the hub.
b. Pitch Housing. The pitch housing permits
blade pitch changes in response to flight control movements
transmitted through the swashplate. This is
made possible within the four pitch housings by Vshaped
stainless steel strap assemblies that are able to
twist and flap to permit blade feathering and flapping.
Cyclic and collective stick inputs are transmitted to the
pitch housing horns by pitch links attached to the
swashplate. Feather bearings are installed inboard on
the pitch housing to allow vertical and horizontal loads
to be transferred from the pitch housing to the hub.
Centrifugal loads are transmitted by each strap assembly
to the hub.
c. Lead-Lag Links. The lead-lag link for each
blade is connected to the outboard end of each pitch
housing and is secured in place by a pin and two bearings
that allow the link to move horizontally. The pin
goes through the V-portion of each strap within the
pitch housing.
d. Damper Assemblies. Two damper assemblies
control the lead-lag movement of each main rotor blade.
Each damper attaches outboard to a link lug and inboard
to a trunnion at the pitch housing. The damper
contains elastomeric elements that distort to allow the
blade to lead or lag.
e. Main Rotor Blades. Each main rotor blade is a
constant-chord asymmetrical airfoil. The outboard tip
is swept aft 20° and tapers to a thinner symmetrical
section. The blade has a 21-inch chord. Tip weights are
installed within the blade. Chord-wise, the leadingedge
and forward half of the blade is a four-cell structural
box of stainless steel and fiberglass with a stainless
steel spar. The aft half of the blade has fiberglass
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：阿帕奇攻擊直升機(jī)操作手冊1(39)