TM 1-1510-224-10 All pointers and scales are flagged. All heading related markers and pointers are removed. Flight control computer standby mode is activated. (12) EADI  dim  control  Control  of  the  intensity of    the    raster    and    stroke    writing    on    the    EADI    is accomplished   by   a   control   knob   placarded   ADI   DIM, which is an outer concentric which is an outer concentric knob with the   DH  SET/TEST  knob.    Turning  the  knob counterclockwise   to   the    OFF   position   will   cause   the EADI  to  become  blank  and  the  composite  mode  to  be displayed on the EHSI. (13) Single-needle    pointer    bearing    source selector   switch.        The    single-needle    pointer    bearing source  selector  switch,  located  on  the  lower  left  side  of the  display  controller,  is  used  to  select  which  navigation information sources will provide information to the single- needle bearing pointer. (a) TCN. Single-needle pointer receives   bearing   information   from   TACAN   navigation receiver. (b) INS. Single-needle pointer receives  bearing  information  from  the  inertial  navigation system. (c) ADF. Single-needle pointer receives     bearing     information     from     ADF     navigation receiver. (d) VOR1.          Single-needle     pointer receives  bearing  information  from  #  1  VHF  navigation receiver. (e) OFF.          Removes     single-needle pointer from the EHSI. 3-20. ELECTRONIC ATTITUDE DIRECTOR INDICATOR (EADI). a. Description.    The  EADI  (fig.    3-9),  combines  a sphere-type    attitude    display    with    lateral    and    vertical computed steering signals to provide commands required  to  intercept  and  maintain  a  desired  flightpath. The EADI provides the following display information: Attitude display Flight director command cue Flight director mode annunciations Vertical deviation Expanded localizer Radio altitude with rising runway display Decision height setting and annunciations Marker beacon annunciations Air data command Rate of turn Reversionary annunciations Flags Comparison monitors b. EADI  Controls,  Indicators,  and  Functions (fig.  3-9). (1) Attitude source annunciator. The selected attitude source will be displayed on the  EADI if it  is  other  than  the  normal  source  for  that  instrument. Possible   annunciations   are   ATT1   (vertical   gyro   #   1), ATT2  (vertical   gyro   #   2),   or   ATT3   (inertial   navigation system).    As  other  attitude  sources  are  selected,  they will   be   annunciated   in   white.      When   the   pilot's   and copilot's attitude sources are the same, the annunciation will be amber. (2) Lateral mode capture annunciator.  Flight director   mode   capture   is   annunciated   on   the   EADI   in green.    Possible    annunciations    are    approach    (APR), localizer (LOC), long-range navigation   (LNAV),  heading (HDG), and navigation (NAV). (3) Attitude   sphere.        The    attitude    sphere moves  with  respect  to  the  symbolic  aircraft  reference  to display pitch and roll attitude. (4) Roll attitude pointer.    Roll  attitude  pointer indicates   aircraft   roll   attitude   with   respect   to   the   roll attitude scale. (5) Roll attitude scale.  The roll attitude scale indicates aircraft bank angle in degrees with respect to a moving pointer. (6) Vertical   mode   arm   annunciator.        Flight director   vertical   mode   arming   is   annunciated   on   the EADI in white.  Possible annunciations are altitude select (ASEL) and glideslope (GS). (7) Vertical mode  capture  annunciator.  Flight director   vertical   mode   capture   is   annunciated   on   the EADI  in  green.    Possible  annunciations  are  glideslope (GS),   vertical   speed    (VS),   indicated    airspeed    (IAS), altitude (ALT), and go-around (GA). (8) Pitch  attitude  scale.      The   pitch   attitude scale has white reference marks in 5 degree increments. (9) Horizon line.  The horizon line is affixed to the sphere and remains parallel to the earth's surface. 3-25