曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

Power Supply
The number 1 AHRS normally receives power from the left radio bus while the number 2 AHRS always receives power from the right radio bus.  If power is removed from a system, in addition to the flags, the ADI will rotate 90 degrees to the right. When the EMER PWR switch is turned ON, the number 1 AHRS receives its power from the 115 volt AC emergency bus and will align in the normal mode.
AHRS Power Up
When power is first applied, the AHRS goes through an alignment similar to an inertial reference system. It will take 45 seconds to complete the automatic alignment mode. During this period, the attitude and heading fail flags will be in view and the ADI spheres will be rotated.
Caution: During the 45 second automatic alignment mode (if the flags
are in view and the ADI spheres are rotated), the aircraft
MUST NOT BE MOVED. If the aircraft is moved or bumped
(by the jetway, a service truck, or the tow bar connected to a
tug), you MUST power down and restart the 45 second
alignment mode.
Note:  Wind buffet, passenger loading, and cargo loading will not appreciably affect the alignment process.
At the end of the 45 second period, the flags will be removed from view, the ADI spheres will be erected, and the AHRS will align in the normal mode.
Note:  The results of the Autoland Pre-flight test is modified on the AHRS aircraft. See section 4 for more information.
VHF Navigation Systems
There are two independent VHF navigation systems, VOR/LOC 1 and VOR/LOC 2.  VOR/LOC 1 is controlled by the Captain’s VHF NAV control panel, and VOR/LOC 2 is controlled by the F/O’s VHF NAV control panel.
VOR/LOC 1 provides VOR/LOC/GS deviation signals to the Captain’s HSI, LOC/GS deviation signals to the F/O’s ADI, VOR bearing to the #1 pointer on both RMI’s, and input to DFGC’s 1 & 2.
VOR/LOC 2 provides VOR/LOC/GS deviation signals to the F/O’s HSI, and LOC/GS deviation signals to the Captain’s ADI, VOR bearing to the #2 pointer on both RMI’s, and input to DFGC’s 1 & 2.
On some aircraft, a radio navigation selector is provided to select NORM (normal), BOTH ON 1 (VOR/LOC/GS 1), or BOTH ON 2 (VOR/LOC/GS 2). When NORM is selected, function is as described above. When BOTH ON 1 or BOTH ON 2 is selected, the selected system provides VOR/LOC/GS deviation signals to both HSIs and ADIs.  An amber NAV (navigation) light is provided on the Captain’s and F/O’s instrument panels to indicate that the radio navigation selector is out of NORM and switching has occurred.
Audio for VOR/LOC 1 and 2 is selected on the audio control panel.  Refer to the Communications chapter for description of audio control panel.
VHF Navigation radio #1 operates on Emergency Power.
Marker Beacon System
The pre-tuned marker beacon system provides visual and aural signals to the flight crew. Three dimmable lights on the Captain’s and F/O’s instrument panels provide visual position indications when passing over an outer, middle, or an airway marker. An aural tone will sound simultaneously with a light. Volume for the marker beacon is controlled on the audio control panel. The Marker Beacon system does not operate on Emergency Power.
Continental
Rev. 12/01/00 #29 Flight Manual
Distance Measuring Equipment
There are two Distance Measuring Equipment (DME) units, DME 1 and DME 2. DME 1 is tuned with VOR/LOC 1, and DME 2 is tuned with VOR/LOC 2.  MILE NO 1 and MILES NO 2 indicators will digital readouts are provided on each HSI.  Maximum range, at maximum altitude is 200 miles. The DME system does not operate on Emergency Power.
Automatic Direction Finding System
There are two automatic direction finding systems, ADF 1 and ADF 2.  One dual control panel provides separate tuning and mode selection for each ADF system. Each ADF system provides bearing input to the pointers on the Captain’s and F/O’s compass indicator. Two VOR/ADF selector knobs are provided on each compass indicator. When the selector knob on the left is in ADF, bearing is displayed on VOR/ADF 1 pointer.  When the selector knob on the right is in ADF, ADF bearing is displayed on VOR/ADF 2 pointer. Audio for ADF 1 and 2 is selected on the audio control panel.  Neither ADF radio operates on Emergency Power.
Attitude Director Indicator
Two vertical gyros, VG 1 and VG 2, supply attitude information to the
Captain’s and F/O’s respective ADI’s and both DFGC’s. VG 1 operates on
Emergency Power.

On some aircraft, an AUX VG is installed to provide backup in the event of
failure of VG 1 or VG 2.  A VERT GYRO selector with positions NORM, L ON AUX,
and R ON AUX is provided. When in NORM, operation is as described above.
When in L ON AUX, the AUX VG supplies attitude information to the
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：MD-80 Flight Manual 麥道80飛行手冊 2(174)