(4)
<SYSTEM SELF TEST> This will start a self test and will show any LRU failures (not related to class of fault).
(5)
<SHUTDOWNS> This gives the cause of the shutdown and the related class 1 LRUs. A list of the shutdown faults and texts of the possible causes is shown in tables 2, 3 and 5.
(6)
<APU DATA/OIL> This gives the APU serial number, operation hours, cycles and the oil level.
(7)
<CLASS 3 FAULTS> This gives every class 3 fault that has occurred, see table 6. The MCDU display format changes. The change is related to the mode selection that is made. The text of the LRU failures is related to which LRU has failed. A sample of the LRU failures is given in tables 2, 3, 4 and 6. A flight 'LEG' is specified as from initial power up, through flight, to power off after the aircraft has landed.
(8)
<FAULT CONDITIONS> This screen is only accessible by the prompt from the screens that follow:
-<SHUTDOWNS>
-<SYSTEM SELF-TEST>
-<LAST LEG REPORT>
-<PREVIOUS LEGS REPORT>
-<CLASS 3 FAULTS>.
The FAULT CONDITION screen consits of two pages. It gives parametric
APU data from the fault data record of the Non Volatile Memory of the
ECB.
(a)
FAULT CONDITIONS Page 1 Page 1 of the FAULT CONDITION screen gives the data that follows:
-APU serial number (S/N);
-Date the fault occured
-GMT when the fault occured;
-Fault Message
-Selected APU speed (NA) in %;
-EGT1 in deg.C;
-EGT2 in deg.C;
-
Inlet Pressure (PA2) in m.Bar;
-
Inlet Temperature (LCIT) in deg.C;
-A/C Flight Phase (ACFP);
-Fault Code Number (FCN);
-LRU ID Number;
-APU Operating State (OPST).
(b)
FAULT CONDITIONS Page 2 Page 2 of the FAULT CONDITION screen gives the data that follows:
-APU serial number (S/N);
-Date the fault occured
-GMT when the fault occured;
-Fault Message
-Fuel Servo Command (FSC) in mA;
-BCV Position in %;
-IGV Position in deg;
-
LCD Total Pressure (PT) in bar;
-
LCD Detlta Pressure (DPA) in psid;
-ECS Demand (ECSD) in %;
-Gearbox Oil Temperature (OTA) in deg.C;
-Generator Oil Temperature (GOT) in deg.C;
-State of Low Fuel Pressure Switch (LFP) yes/no state.
9. AIDS
____
(Ref. Fig. 009)
The Aircraft Integrated Data System (AIDS) which contains two programmed reports connects with the APU system. The two programmed reports are:
-Main Engine Start (MES) IDLE,
-
SHUTDOWN.
A.
MES/IDLE Report The Main Engine Start (MES)/IDLE report is supplied after every fiftieth MES and it is used to monitor APU performance. The report includes:
-
the data from both Main Engine Starts (MES),
-
the idle mode that follows (until the APU is shutdown),
-
the data from the last APU start, which includes the APU operation hours and the start cycles.
B.
SHUTDOWN Report The SHUTDOWN report is supplied after every APU shutdown occurs and is used for trouble shooting. The printer 4TW of the MCDUs prints out both the reports and ground software analyzes the reports. This information includes the APU operation hours and the start cycles.
APU - MES/IDLE and SHUTDOWN Reports (AIDS)
Figure 009
CES 10. BITE Test
_________
A. Power-up Test The Power-up test is a major test, which is performed every time when the ECB enters the POWER UP state. The test includes the following features:
-
test of the watchdog timer circuit,
-
test of the On-Board Replaceable Module (OBRM) of the ECB,
-
test ECB-Read Only Memory (ROM),
-
test of the ECB-RAM,
-
test of the integrity of the primary and backup overspeed circuirity (speed injection test),
-
test of the discrete and analog outputs,
- oil level test.
(1)
Watchdog timer test The ECB is equipped with a watchdog, ensuring the correct function of the Central Processing Unit (CPU) of the ECB. In case the timer circuit of the watchdog is not reset within 32msec after power-up, a system reset is created and the ECB is disabled. For each occurence of a watchdog time out, the fault output of the ECB is activated. A reactivation and restart is possible by cycling the APU-MASTER switch in the cockpit. Three occurrences of a watchdog time out, results in a hardware latch-up of the ECB and requires a cycling of power to reset the ECB.
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