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It is important to delay starting the APU for five minutes after application of anti-icing fluid near the APU area. This allows any anti-icing fluid inadvertently directed into the APU inlet to drain out. Three consecutive APU start attempts may be made at 1 minute intervals, followed by a 20 minute wait. Two more start attempts may be made. No further attempts may be made for a period of at least 40 minutes. Six consecutive and successful APU starts may be made at 10 minute intervals with a one-hour waiting period prior to additional start attempts. IGNITION SYSTEM The APU ignition system consists of an ignition unit, igniter plug lead and a single igniter plug. The ignition system is energized during the APU start cycle and is de-energized when the APU start sequence is complete. To engage the APU, pull up on the switch, position the switch to RUN for approximately 3 seconds until the APU indications are displayed on the left MFD. Then move the switch to START and hold until the START icon is displayed on the left MFD, the APU will then begin the start sequence. The APU ignition system consists of a single output ignition unit. Should a flameout occur during operation, the ignition unit automatically fires the igniter through the auto relight function of the ECU. An immediate restart (APU starter re en-gagement) can be initiated upon APU rolldown below 10% rpm. SYSTEM OPERATION The ECU uses 28 vdc power from the right aircraft battery bus to energize the ignition system during the ignition/start se-quence. During the start sequence, the R BATT switch is illuminated OFF on the ELECTRICAL panel and the flow line from R BATT to the R ESS BUS on the Electrical synoptic page is depicted in white. The ignition system is energized at 5% APU rpm and stays energized until 95% rpm. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6 05-01-07 PNEUMATIC SUPPLY DESCRIPTION |
