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 6)  AIRPLANES WITHOUT CONTROL WHEEL STEERING; in A/P stand-alone (no F/D is on) operation, Lateral Navigation (LNAV) is accomplished through the following modes: heading hold, heading select, localizer only, approach guidance and rollout, and turbulance penetration.
 7)  When coupled with the Flight Management Computers (FMCs), the LNAV mode utilizes VOR (Very high frequency Omnidirectional Range), IRS (Inertial Reference System), and stored flight plan information.
 8)  In A/P stand-alone operation, Vertical Navigation (VNAV) is accomplished with the following modes: a) Pitch altitude hold
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 b) AIRPLANES WITH CONTROL WHEEL STEERING; Pitch CWS c) Autostabilizer trim - through Stabilizer Trim Elevator
 Asymmetry Module (SAM) d) Vertical speed select and hold e) Airspeed/Mach select and hold f) Go-around g) Approach guidance, flare, and landing h) GUN 001-050, 052-999;
 Glideslope with backcourse
 9)  When coupled to the FMCS, the VNAV mode uses the following references: a) Stored flight plan incorporating Standard Terminal
 Arrival Routes (STARs) and Standard Instrument Departures (SIDs). b) Computed flight plan depending on the IAS/MACH mode selected. c) Computed flight plan depending on the FMCs selected mode. d) IRS. 10) The FCC roll modes do not use any functions associated with Stabilizer Trim Elevator Asymmetry Module (SAM).
 11) The FCC pitch modes use functions associated with SAMs in the following systems: a) Horizontal Stabilizer Trim System (Ref 27-41-00). b) Automatic Stabilizer Trim System (Ref 22-22-00)
 (b)  Displays 1) EADI - AFDS Displays (Normal) (Fig. 14) a) The airplane is represented on the EADI as a fixed, white symbol consisting of an inverted V-bar. b) The integrated cue command bar is a magenta inverted vee capable of vertical and horizontal movement.
 c)  If the commanded fly-to point (CFP) is outside the normal deflection range for the command bars, both bars deflect together. They remain intersected at 0.125 inches (minimum) from the bar end to indicate the CFP.
 d)  AIRPLANES WITH CONTROL WHEEL STEERING; up to 8 alphanumeric characters, 0.167 inches high, identify one of the following modes: CMD or FD (left justified) or CWS, TEST (right justified). This readout is green and appears on the third line from the bottom of the Flight Mode Annunciation (FMA) on the right side (area E). The FMA is located in the lower, right and left corners of the ADI display.
 e)  AIRPLANES WITHOUT CONTROL WHEEL STEERING; up to 8 alphanumeric characters, 0.165 inches high, identify one of the following modes: CMD or FD (left aligned) or TEST (right aligned). This readout appears on the top line of the Flight Mode Annunciation (FMA) on the right side. The FMA is located in the lower, right and left corners of the ADI display.
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LOC DEVIATION SCALE
NORMAL
AFDS AND TMC EADI MODE ANNUCIATION 
A  B  C  D  E  F 
IAS LIM TEST IDLE THR-HOLD FLAP LIM MACH LIM MACH IAS EPR  FLARE G/S  FLAP LIM TO GA ALT CAP FLARE G/S MACH LIM MACH IAS LIM IAS VNAV V/S ALT HOLD  CWS TEST FD CMD  ROLLOUT B/CRS LOC  ATT ROLLOUT B/CRS LOC LNAV HDG SEL HDG HOLD TRK HOLD 

AREA 7 ATTITUDE REFERENCE FAILURE FLAG
AREA 2 SELECTED DECISION HEIGHT DISPLAY (REF) AREA 4 RADIO ALTITUDE DISPLAY (REF)
AREA 8 GLIDE SLOPE FAIL FLAG
AREA 13 AFDS STATUS
AREA 14 AFDS ROLL ARM FMA AREA 15 AFDS ROLL
ENGAGED FMA AREA 12 LOCALIZER DEVIATION FLAG FMA
ABNORMAL
EADI - AFDS Displays Figure 14 (Sheet 1)
D01522
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