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Loss of Tail Rotor Effectiveness
LTE
A critical, low-speed aerodynamic flight characteristic which can result in an uncommanded rapid yaw rate which does not subside of it's own accord and, if not corrected, can result in the loss of aircraft control.

(Right Yaw)
Full left pedal; Cyclic forward

Low RPM
Below ETL
High Gross Weight
High DA
Low speed Right Turns
What 9 lights on before start?
ENGINE OUT
GEN FAIL
HYDRAULIC SYSTEM
XMSN OIL PRESS
RPM
R/FUEL BOOST
L/FUEL BOOST
R/FUEL XFR
L/FUEL XFR
When do lights turn off during start
START - 50%
ENGINE OUT - 55%
AUTO RELIGHT - 60%
FADEC
Full Authority Digital Engine Control
FADEC Control
ECU - Engine Control Unit
Airframe mounted

HMU - Hydro Mechanical Unit
Engine mounted

Throttle is the only mechanical link
9 Points of FADEC ECU
Ng
Np
Nr
MGT
Torque
Collective Pitch
PLA - Power Lever Angle
CIT - Combustion Inlet Temp
P1 - Ambient Pressure
BIT
Built In Test
FADEC Fault Categories
CATEGORY 1 — FADEC FAIL/
FADEC MANUAL — DIRECT
REVERSION TO MANUAL
SYSTEM (DRTM)

CATEGORY 2 — FADEC
DEGRADED

CATEGORY 3 — FADEC FAULT

CATEGORY 4 — RESTART
FAULT

CATEGORY 5 — MAINTENANCE
ADVISORY, FADEC SYSTEM
FAULTS — ENGINE SHUTDOWN
Software Version
5.4
Secondary Governor
Rotor type
Four bladed soft-in-plane flex beam type yoke/hub design
w/lead-lag, coning/flapping, and droop stops
Flapping Flexture
Rotor yoke, star shaped
Rotor Diameter
35 feet MR
5.42 feet TR
Max downward force on blade tip
Max distance down
60 lbs
50 In???
Failsafe Systems
Hydraulic
Anti-Ice
Particle Separator
PMA
Permanent Magnetic Alternator
Activates at 85% Np
LRB's
2 CEFA - Combined Engine Filter Assembly
Air Frame Fuel Filter
2 Hydraulics
Transmission Oil
Gerny Strap
Tab on the back of vertical fin to disrupt airflow
407 Engine & HP
250-C47B
813 SHP Derated
674 SHP for 100% TQ
630 SHP for 93.5% TQ
Np Power Turbine gear train components
Torquemeter
Freewheeling Unit
Permanent Magnetic Alternator
Ng Gas Producer gear train components
Starter/Generator
Hydro Mechanical Unit
Oil Pump Assembly
x of y cards