Verify that the waypoints have not been entered into INS No. 2 and No. 3 by sequencing CDU No. 2 and CDU No. 3 WPT switches to the waypoint numbers.On CDU No. 2 and CDU No. 3 place the AUTO/MAN/RMT switches to RMT.Using the CDU of the transmitter INS enter the following waypoint coordinate data into the INS. When entering the data ensure that the WPT switch on the CDU of the transmitter INS is set to the appropriate number.
NOTE: For waypoint coordinate entry procedures refer to
____ par. (f).
a) Enter the waypoint data shown below, using INS No. 1
as the transmitter INS. Waypoint 1. N48.00.0 W122.16.8 Waypoint 2. N20.00.0 W120.00.0 Waypoint 3. N30.00.0 W130.00.0
b) Enter the waypoint data shown below, using INS No. 2
as the transmitter INS. Waypoint 4. N40.00.0 E40.00.0 Waypoint 5. N50.00.0 E50.00.0 Waypoint 6. N60.00.0 E60.00.0
c) Enter the waypoint data shown below, using INS No. 3
as the transmitter INS. Waypoint 7. S70.00.0 W170.00.0 Waypoint 8. S80.00.0 W180.00.0 Waypoint 9. S90.00.0 W109.00.0
Verify that waypoints 1 thru 9 have been entered into all three inertial navigation system by setting the data selectors on each CDU to WPT and sequencing the WPT switches to the appropriate waypoint number.On each control display unit return to AUTO/MAN/RMT switch to the MAN position.
EFFECTIVITY AIRPLANES WITH LTN-72 INS
CONFIG 01 A Page 513 Aug 25/87
34-41-00
(h) Place data selector to DSR TK/STS and observe that two-digit status number appears in right-hand display (Fig. 501). The number starts high (90) and decrements towards 01 as the alignment progresses. The READY NAV annunciator illuminates when the status reaches 02.
NOTE: If the status number changes from 02 to 10, the READY
____ NAV annunciator goes out and stays out until the status number again changes to 02.
(i)
When READY NAV annunciator on MSU illuminates, advance mode selector switch to NAV and verify that READY NAV annunciator extinguishes and system status indicates 01.
(j)
If INS is no longer required, restore airplane to normal.
(4)
Test Inertial Navigation System/Central Air Data System Interface
(a)
If required, prepare for test as described in paragraph D.
(b)
Provide 200 knots TAS input to INS No. 1 and 3 from the No. 1 Central Air Data Computer (Ref. 34-12-00).
(c)
Set display selector switches on No. 1 and No. 3 CDU's to the HDG/DA positions and note heading readout on left-hand display.
(d)
Set No. 1 and No. 3 CDU display selector switches to WIND position and wait 90 seconds for the wind magnitude to stabilize.
(e)
Verify that No. 1 and No. 3 CDU's indicate: 1) Wind angle (left display) equals CDU heading | 2 degrees. 2) Wind magnitude (right display) equals 200 | 6 knots.
(f)
Press and hold the No. 1 CADC self-test pushbutton. Verify that both the No. 1 and No. 3 CDU numerical displays go blank.
(g)
Release the No. 1 CADC self-test pushbutton.
(h)
Repeat steps (b) through (g) for the No. 2 CADC and the No. 2 INS.
(i)
If INS is no longer required, restore airplane to normal.
(5)
Test Inertial Navigation System/HSI Interface
(a)
If required, prepare for test as described in paragraph D.
(b)
Verify that the AUTO/MAN/RMT switch on each CDU is in MAN.
(c)
Verify that the mode selector switch on each MSU is in NAV and the READY NAV annunciator is extinguished.
(d)
Verify that both Capt's and F/O's VOR-ILS/INS switches are in the INS position.
(e)
Verify that INS transfer switch on the captain's main instrument panel is in the normal powition (Capt 1 and F/O 2).
EFFECTIVITY AIRPLANES WITH LTN-72 INS
CONFIG 01 A Page 514 Aug 25/87
34-41-00
(f) Verify that the following HSI annunciators are displayed thus:
HSI ANNUNCIATOR CAPT's HSI F/O's HSI
MAG/TRUE TRUE TRUE
VOR-ILS/INS INS INS
DATA SOURCE 1 2
(g) INS Self-Test and HSI Display. 1) Place the mode selector switch on each MSU to ALIGN. 2) Ensure CDU No. 1 FROM/TO display is 0 0. 3) Place the CDU No. 1 WPT switch to any position except 0. 4) Place the CDU No. 1 display selector switch to TEST. 5) Verify that the displays of the captain's HSI perform as
follows:
~ê è CDU AUTO-MAN-RMP SWITCH SETTING HORIZONTAL SITUATION èêê. INDICATOR DISPLAYS è AUTO MAN RMT èééé. Azimuth Card (as read 11.25 |1. 11.25 |1. 11.25 |1. against the lubber line) è”””. Drift Angle Marker 22.5 |2. 22.5 |2. 22.5 |2. (read against azimuth card) è”””. Desired Track Arrow 50.1 |2. 59.6 |2. 354.1 |2. (read against azimuth card) è”””. Cross Track Deviation 2 dots L 1 dot L 1 dot R Distance Bar è”””. DIST 888 888 888 è”””' GND SPEED 512 512 512 ééé
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航3(39)
