- On the PFD, ND CAPT side and upper ECAM display unit MAINTENANCE MODE comes into view.
- The MASTER CAUT light comes on.
- Ignore the ECAM warnings.
The EIS (DMC3) ENGINE OVER SPD/TEMPshows.
The over limit red indexes are reset.
The CFDS MENU comes into view.
A. Do the EIS stop procedure: (Ref. TASK 31-60-00-860-002). Subtask 77-00-00-862-050
B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
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POWER - DESCRIPTION AND OPERATION
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1. General
_______
This chapter deals with the N1, N2 indications.
2. N1 Indicating System
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A. General
The measurement channel for the low pressure rotor is designed as
follows:
- the speed sensor on the engine sends a signal to the ECU
- the ECU processes the N1 signal and transmits it to the ECAM through the ARINC 429 data bus (Ref. 73-25-00).
B. N1 Speed Sensor
(1) General The N1 speed sensor is installed in the fan frame strut No.6 at the
5:00 o'clock position. It is secured to the fan frame with 2 bolts. When the N1 speed sensor is installed on the engine you can only see these components :
- the three-connector receptacle
- the connector head
- the sensor flange.
(2) Description
(Ref. Fig. 001)
The N1 speed sensor consists of the following :
- a three-connector receptacle (ch A - airframe - ch B).
- a flange for attachment of the sensor to the engine
- a rigid metal tube including two bonded damping rings, a magnetic head (sensor probe) which includes 3 windings, 3 permanent magnets and the pole pieces and three pairs of shielded lead wire providing the electrical signals from the sensing elements to the connectors.
(3) Operation
(a) Function
(Ref. Fig. 002)
The N1 speed sensor :
- detects the LP rotor assembly rotational speed
- transmits the corresponding signals to the Engine Vibration Monitoring Unit, the Electronic Control Unit, Channel 1 and the Electronic Control Unit, Channel 2.
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N1 Speed Sensor
Figure 001
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N1 Sensor Electrical Diagram
Figure 002
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(b) Principle This sensor is an induction type tachometer. It consists of 3 independent sensing elements which are magnetically and electrically insulated from each other. Each sensing element includes a magnet, a winding, and a pole piece. These sensing elements are hermetically enclosed in a stainless steel housing. The sensitive elements transmit signals. The signals are supplied to the connectors through conductors embedded in a metal tube. A sensor ring mounted on the fan shaft is provided with 30 teeth. The passage of each tooth modifies the flux field of the magnets and causes a flux variation in the coils. This generates an alternating electromotive force proportional to the rotational speed of the low pressure rotor assembly.
NOTE : The sensor ring has one tooth thicker than the 29 others.
____ This tooth generates a signal of greater amplitude used as phase reference for trim balance (processed in the EVMU).
C. N1 Indication
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
(Ref. Fig. 003)
R **ON A/C 106-149, 303-399, 401-499,
(Ref. Fig. 003A)
**ON A/C ALL
The N1 indication is displayed on the upper display unit of the ECAM system :
- in the analog form, by a pointer deflecting in front of a dial,
- in the digital form, in the lower section of the dial.
The indication is normally green.
When N1 LIM < N1 < 104 percent :
- the indication becomes amber
When N1 > 104 percent :
- the indication becomes red
- the MASTER CAUT light comes on accompanied by a single chime
- the following messages appear on the ECAM : 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM ENGINE INDICATING 發(fā)動(dòng)機(jī)指示(8)
