R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 34-21-26Page 501 1201-220, 1May 01/05 1 1 1CES 1 1EFF : 001-049, 051-099, 101-105, 151-199, 1 34-21-26Page 502 1201-220, 1May 01/05 1 1 1CES 1 STANDBY DATA : ATTITUDE AND HEADING - DESCRIPTION AND OPERATION
R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220,
R R 5. Close-up________ **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, Post SB 34-1280 For A/C 213-213, Subtask 34-21-26-420-053 A. Install the standby airspeed indicator (Ref. TASK 34-21-26-400-001).
_______________________________________________________________
1. General
_______
A. Standby Heading The standby heading is performed by a magnetic compass that is an independent instrument which provides the flight crew with the A/C magnetic heading. It is installed on the top of the windshield center post and allows a check of the heading provided by the main sources of the heading system. It acts in standby when these systems are inoperative.
B. Standby Attitude The standby attitude is performed by a gyroscopic horizon that is an independent instrument which provides the flight crew, with a constant indication of the aircraft attitude. It is contained in a 3 ATIs case and installed on the center instrument panel. It allows a check of the attitude provided by the main sources of attitude system. It acts in standby when these systems are inoperative.
2. Component Location
__________________
R **ON A/C 001-049, 051-061, 101-105, 201-203,
(Ref. Fig. 001)
R **ON A/C 062-099, 151-199, 204-212, 214-220,
(Ref. Fig. 001A)
R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-212, 214-220,
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
-------------------------------------------------------------------------------2FN COMPASS-STANDBY 211 831 34-22-23 7FN IND-STANDBY HORIZON 4VU 211 831 34-22-24
3. System Description
__________________
R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 34-22-00Page 1 1201-212, 214-220, 1Config-1 May 01/05 1 1 1CES 1
Standby Data - Attitude and Heading - Component Location
Figure 001
R 1EFF : 001-049, 051-061, 101-105, 201-203, 1 34-22-00Page 2 1 1 Config-1 May 01/05 1 1 1CES 1
Standby Data - Attitude and Heading - Component Location
Figure 001A
R 1EFF : 062-099, 151-199, 204-212, 214-220, 1 34-22-00Page 3 1 1 Config-1 May 01/05 1 1 1CES 1
R **ON A/C 001-049, 051-061, 101-105, 201-203,
(Ref. Fig. 002, 003)
A. Standby Compass The standby compass consists of a magnetic element rotating inside a compass bowl, immersed in a damping liquid. The magnetic element (1) is linked to a graduated compass card which moves against a lubber line (2) and gives the magnetic heading. Below the viewing window are two apertures (4) marked N.S and E.W, allowing to achieve compensation by positioning the two small magnetized bars (compensator). Above the viewing window is a non-magnetic lamp (3) assembly which provides illumination of the compass card.
R **ON A/C 062-099, 151-199, 204-212, 214-220,
(Ref. Fig. 002, 003A)
A. Standby Compass The standby compass consists of a magnetic element rotating inside a compass bowl, immersed in a damping liquid. The magnetic element (1) is linked to a graduated compass card which moves against a lubber line (2) and gives the magnetic heading. Above the viewing window are two apertures (4) marked B (E.W) and C (N.S) , allowing to achieve compensation by positioning the two small magnetized bars (compensator). Below the viewing window is a non-magnetic lamp (3) assembly which provides illumination of the compass card.
R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-212, 214-220,
B. Standby Horizon Indicator The standby horizon indicator is supplied with 28VDC from essential bus 401PP. A static inverter in the instrument converts this 28VDC into three phase alternate current to supply the gyroscopic motor. The gyro rotor rotates at high speed (> 23,000 RPM) around its vertical axis and provides the vertical reference. The gimbal assy comprises two orthogonal axes (pitch and roll). The internal gimbal which includes the stator controls the rotation of the drum in the pitch axis by means of gear. The pitch gimbal is restricted to approximately plus or minus 85 degrees around the pitch axis (mechanical stop).
R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 34-22-00Page 4 1201-212, 214-220, 1Config-1 May 01/05 1 1 1CES 1
Standby Data - Attitude and Heading - Electrical Circuit
Figure 002
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM NAVIGATION 导航2(110)
