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log is maintained to track the number of engine starts.
Engine limit data (hereafter referred to as exceedance data) is recorded
when a TGT, HP, LP or EVM limit is exceeded on either engine. Recording
also occurs when a fire indication is detected on either engine or when a
fire test is performed on an operating engine while airborne. The recording
includes pre- and post-exceedance data points so that a detailed timeversus-
parameter plot of the exceedance may be constructed. Certain
CAS messages are associated with engine exceedance detection and, if
the exceedance is not corrected, the subsequent recording of the
exceedance. On SPZ-8000 equipped airplanes, a blue ENGINE
EXCEEDANCE advisory message is displayed when an exceedance is
detected. On SPZ-8000 equipped airplanes having ASC 415 and SPZ-
8400 equipped airplanes, the blue ENGINE EXCEEDANCE advisory
message has been removed and replaced with a red ENGINE
EXCEEDANCE warning message. If the detected exceedance is not
corrected, it is recorded and a blue EXCEEDANCE RECORD advisory
message is displayed (SPZ-8000 equipped airplanes having ASC 415 and
SPZ-8400 equipped airplanes). The exceedance can then be viewed on
the EXCEEDANCES system page.
APU exceedance data is recorded when an EGT or RPM limit is exceeded,
a fire indication is detected or when an APU fire test is performed while
airborne. Like engine limit data recording, APU limit recording includes preand
post-exceedance data points so that a detailed time-versus-parameter
plot of the exceedance may be constructed. CAS messages are also
associated with APU exceedance detection and, if the exceedance is not
corrected, the subsequent recording of the exceedance. A blue APU
EXCEEDANCE advisory message is displayed when an exceedance is
detected. If the detected exceedance is not corrected, it is recorded and a
blue EXCEEDANCE RECORD advisory message is displayed (SPZ-8000
equipped airplanes having ASC 415 and SPZ-8400 equipped airplanes).
The exceedance can then be viewed on the EXCEEDANCES system
page.
Brake temperature exceedance data is recorded when a brake
temperature exceeds 625°C. On SPZ-8000 equipped airplanes having
ASC 415 and SPZ-8400 equipped airplanes, a blue EXCEEDANCE
OPERATING MANUAL
2A-31-00 PRODUCTION AIRCRAFT SYSTEMS
Page 24
January 31/02
Revision 6
RECORD advisory message is displayed. The exceedance can then be
viewed on the EXCEEDANCES system page.
The EXCEEDANCES system page display holds the most recent
exceedance data until airplane power is turned off or another exceedance
is detected. All exceedances are held in the fault warning computer’s
memory, however. If the EXCEEDANCES page is selected before any
exceedances are recorded, a white NO EXCEEDANCES RECORDED
message is displayed on the page.
Although engine trend and limit data recording operates automatically, a
manual request for recording can also be made by the flight crew. On
airplanes SN 1253 and subsequent and SN 1000 through 1252 having
ASC 255, a crew activated recording switch (labeled SNAPSHOT, shown in
Figure 13) allows the flight crew to record maximum values and the time in
exceedance for up to five (5) minutes on the ground or while in flight.
The memory allocated within each fault warning computer for trend and
limit recording is a nonvolatile type of memory known as Electrically
Erasable and Programmable Read Only Memory (EEPROM). On SPZ-
8000 equipped airplanes, 64 kilobytes of memory is allocated, with
provisions for an additional 64 kilobytes of growth memory. On SPZ-8400
equipped airplanes, 128 kilobytes of memory is allocated. When the fault
warning computer is tested, a message indicating EEPROM memory
usage is generated.
On SPZ-8000 equipped airplanes having ASC 415 and SPZ-8400
equipped airplanes, a blue T&L >80% FULL advisory message is displayed
on CAS when 80% of the allocated EEPROM memory has been used. The
flight crew should then notify maintenance personnel to download and
erase the fault warning computer memory at the next convenient
maintenance period. The T&L >80% FULL advisory message is displayed
only when the airplane is on the ground at speeds of less than 50 knots.
The fault warning computer contains a dedicated output for data
downloading. Downloading is performed using the data loader.
3. Controls and Indications:
(See Figure 11 through Figure 13.)
A. Circuit Breakers (CBs):
Circuit Breaker Name: CB Panel: Location: Power Source:
BUS CONT #1 CP K-2 ESS DC Bus
BUS CONT #2 CP L-2 ESS DC Bus (1)
BUS CONT #3 CP M-2 ESS DC Bus (2)
FWC #1 CP A-13 ESS DC Bus
　
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