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commands complemented with ICLS steering in order to more clearly define D/L capability. It does
not show TCN or WYPT steering which may be used in conjunction with, or independent of, D/L
steering during the approach.
Figure 24-26. ACL Mode 2 Steering Display
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VII-24-64 ORIGINAL
Figure 24-27. T/C Guidance to Marshal (Sheet 1 of 3)
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VII-24-65 ORIGINAL
Figure 24-27. T/C Guidance to Marshal (Sheet 2 of 3)
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VII-24-66 ORIGINAL
Figure 24-27. T/C Guidance to Marshal (Sheet 3 of 3)
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VII-24-67 ORIGINAL
Figure 24-28. ACL Control - Marshal to Touchdown (Sheet 1 of 5)
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VII-24-68 ORIGINAL
Figure 24-28. ACL Control - Marshal to Touchdown (Sheet 2 of 5)
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VII-24-69 ORIGINAL
Figure 24-28. ACL Control - Marshal to Touchdown (Sheet 3 of 5)
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VII-24-70 ORIGINAL
Figure 24-28. ACL Control - Marshal to Touchdown (Sheet 4 of 5)
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VII-24-71 ORIGINAL
Figure 24-28. ACL Control - Marshal to Touchdown (Sheet 5 of 5)
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VII-24-72 ORIGINAL
CHAPTER 25
Backup/Degraded Operations
25.1 MISSION COMPUTER NO. 1 FAILURE
If there is a failure of MC 1 (navigation computer) there are certain capabilities which are lost. Some
basic navigation capabilities are provided by the backup functions of MC 2. Functions not available
when MC 1 is failed are the autopilot functions, G limiter and roll limiter, map and navigation
situations display, and GPS and the HUD steering displays (except for data link). In addition, the HSI
functions of position keeping source selection, position updating, target marking, and data entry and
display are not provided when MC 1 is failed. The functions provided by MC 2 are the basic HUD flight
data; backup HSI display with INS, TACAN and ADF information; mode II ACL capability; and
automatic throttle control. The control of CNI equipment by the UFCD is not affected by an MC 1
failure, and ILS steering is available on the standby attitude indicator. No backup position keeping is
provided if the INS fails when MC 1 is failed. In this case the standby attitude reference indicator is
used by MC 2 for attitude information and the velocity vector is not displayed on the HUD.
Failure of MC 1 causes a loss of all DDI caution displays except MC 1,
HYD 1A, HYD 1B, HYD 2A, and HYD 2B.
25.1.1 Backup HUD Display. With MC 1 failed, the backup HUD display is identical with the
primary HUD display except that the bank angle scale is not provided and the heading scale is at the
same position as in the weapon delivery modes. The ghost velocity vector is provided during backup
operation and the velocity vector may be caged/uncaged.
25.1.2 Backup HSI Display. With MC 1 failed, the backup HSI display consists of a magnetic
compass rose oriented heading-up with a TACAN pointer and an ADF pointer. A digital readout of
TACAN bearing and distance and the station identifier are provided in the upper left corner. The INS
present position is displayed inside the compass rose at the top center. Waypoint 0 is displayed. The
ACL mode option pushbutton is displayed for selection.
25.2 BACKUP ATTITUDE AND NAVIGATION SYSTEM
If a failure occurs in the primary attitude and navigation system (INS), output signals of pitch, roll,
magnetic heading, and airspeed are provided to the mission computer system for use in the backup
attitude navigation computations. The backup system consists of standby attitude reference indicator,
static power inverter, and magnetic azimuth detector.
25.2.1 Standby Attitude Reference Indicator. The standby attitude reference indicator (figure 25-1)
is a self-contained pitch and roll instrument which is mounted on the main instrument panel. An
electrically driven gyro maintains vertical orientation by use of an electronic erection system. The
erection system automatically cuts off when lateral accelerations exceed approximately 0.15 g. The
gyro spin speed and erection system provides a minimum of 3 minutes of attitude information with a
total power loss. Pitch and roll servos provide back up pitch and roll attitude for use by other systems.
The attitude presentation is 360° in roll, 92° in climb, and 78° in dive.
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VII-25-1 ORIGINAL
25.2.2 Static Power Inverter. If there is an interruption or loss of aircraft ac power, 28 volt dc power
is applied to the static power inverter to produce the 115 volt ac power needed for standby attitude
reference indicator operation.
25.2.3 Magnetic Azimuth Detector. The magnetic azimuth detector (MAD) consists of three sensing
elements configured in a wye. The sensing elements are mounted so that average positions are
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NATOPS Flight Manual 飞行手册 2(113)
