MD Helicopters MD900 with PW206E, Flight Manual

Page: 277 / 450

CSP–900RFM206E–1
ROTORCRAFT FLIGHT MANUAL
MD900 With PW 206E
Systems Description
Original
7–39
F92–077
ROTOR
SYSTEM
HYDRAULIC
SYSTEM
AIRFRAME
SYSTEM
POWERPLANT
SYSTEM
BALANCE
MONITORING
SYSTEM
INTEGRATED INSTRUMENT
DISPLAY SYSTEM (IIDS)
DRIVE
SYSTEM
FUEL
SYSTEM
ELECTRICAL
SYSTEM
NOTAR
SYSTEM
Figure 7–22. IIDS System Monitoring
BIT failures are stored in non−volatile memory to assist in three situa
tions:
First , a transient or intermittent failure;
Second , a situation where the pilot observed a problem with the IIDS
but didn’t notice any failure annunciation;
Third , ease of IIDS maintenance on and off the aircraft. These fault
words are stored in the Fault Log when a BIT failure was detected
in the IIDS, BMS, EEC, or aircraft transducers/sensors, and can be
examined through the IIDS display or ground based maintenance com
puter (GBMC).
When the testing determines that an internal fault exists, the appropri
ate redundant function, if such redundant system exists, will be com
manded to assume the primary role. The redundant functions shall
be sufficiently isolated such that a failure of the function will not cause
BIT
Failures