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A. Heading flag in view on both HSI’s and RDMI’s.
B. FMC position is blank on the POS REF page of the FMC/CDU.
C. Course, distance, and ETA information based on present position are
blank on the PROGRESS and LEGS pages of the FMC/CDU.
D. HSI Nav flags are in view if NAV position is selected on the HSI
switch.
5. If only one IRS is in the ATT mode, the following indications are present:
A. Set IRS HDG prompt is displayed at the bottom of the POS INIT page.
B. IRS display unit/data displays for present position, wind, and
track/ground speed are blank for the IRS in the ATT mode.
(Continued)
737
Flight Manual
Continental
FLT MGMT, NAV
Sec. 2.11 Page 15
Rev. 11/15/02 #41
If an IRS is in ATT mode, perform the following steps to regain the navigation
mode:
Determine which IRS is in the ATT mode by selecting PPOS on the IRS display
unit/display selector and switching between left and right IRS’s to find the blank
data display.
Place the appropriate IRS mode selector OFF. Wait until the ALIGN light
extinguishes (approximately 30 seconds).
Place the IRS mode selector to NAV and insert present position to restart the
ten-minute alignment procedure. Be sure that aircraft is not moved during
alignment.
* * * *
IRS ON DC
The IRS is operating from the switched hot battery bus (power to the right IRS
is removed automatically after 5 minutes).
* * * *
FLT MGMT, NAV
Sec. 2.11 Page 16
Rev. 11/15/02 #41
Continental
737
Flight Manual
LOSS OF ALIGNMENT (INFLIGHT)
Note: Refer to IRS FAILURE (Inflight) procedure, if applicable.
If an IRS loses both AC and DC power, the alignment is lost. Alignment can
also be lost if the mode selector is moved out of the NAV position.
If alignment is lost in flight, the navigation mode (including present position and
ground speed outputs) is inoperative for the remainder of the flight. However,
selecting ATT allows the attitude mode to be used to re-level the system and
provide ADI attitude. The attitude mode requires approximately thirty seconds
of straight and level unaccelerated flight to complete the re-leveling. Some
attitude errors may occur during acceleration, but will be slowly removed after
acceleration.
The attitude mode can also provide heading information. However, to establish
compass synchronization, the crew must manually enter the initial magnetic
heading. Thereafter, drift of the IRS heading will occur (up to 15° per hour).
Therefore, when in the ATT mode, an operating compass system must be
periodically cross-checked and an updated magnetic heading entered in the IRS,
as required.
Manual IRS entry of MAG heading on the IRS display unit:
· Mode selector(s) is ATT.
· Press H (heading) key (located on #5).
· Enter compass heading on numeric keys.
· Press ENTER key.
· Cross-check and verify heading. Heading flags should be retracted from
view.
· The IRS heading will precess (drift) and must be updated periodically.
* * * *
737
Flight Manual
Continental
FLT MGMT, NAV
Sec. 2.11 Page 17
Rev. 11/15/02 #41
BCD SINGLE FMC FAILURE WITH DUAL FMC’S
Failure of a single FMC is indicated by:
· FMC ALERT light.
· Failure of MAP information on the failed side.
· Line selection of FMC on the MCDU is deleted on failed side.
· Scratch pad message SINGLE FMC OPERATION
FMC navigation is still available from the remaining FMC. Select the operable
FMC to return MAP information to the failed side.
FMC Selector ..........................................................................AS REQUIRED
Note: This abnormal can be caused by a software mis-compare between the
FMCs.
IF FMC/CDU Alert Message DUAL FMC OP RESTORED Appears:
FMC Selector.............................................................................NORMAL
* * * *
FLT MGMT, NAV
Sec. 2.11 Page 18
Rev. 11/15/02 #41
Continental
737
Flight Manual
VHF NAV FAILURE
In the event of a failure of the number one or the number two VHF NAV radio
as indicated by the various warnings and flags, select the functioning VHF NAV
radio with the VHF NAV Transfer Switch.
* * * *
VOR/ILS NAVIGATION SYSTEM FAILURE
Certain Non-EFIS VOR/ILS navigation systems can be susceptible to failures
which will not be reflected on the display instrument (HSI, RDMI). This type of
internal fault is in the signal sent by the receiver to the display. Since no
“feedback loop” exists between the instrument and the receiver no failure flag
　
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