TM 55-1510-222-10 Table 3-2.  Various Values For UTM Grid Coefficients SPHEROID COEFFICIENT RADIUS International 29700 8388 m Clark 1866 29498 8206 m Clark 1880 29346 8429 m Everest 30080 7276 m Bessel 29915 7397 m Modified Everest 30080 7304 m Australian National 29825 8160 m Airy 29932 7563 m Modified Airy 29932 7340 m Source: Universal Transverse Mercator Grid Technical Manual TM 5-241-8, Headquarters Department of the Army. 30 April 1973, page 4 Flatness Coefficient::  100 (1/f) Relative Radius: a-6,3700.000 (4) Abbreviated INS Interface Test As required. NOTE Assuming    a    level    aircraft,    attitude indicators   will   become   level   during alignment  state  8  and  remain  level  in all   modes   until   INS   is   shut   down. Warning   indicators   for   INS   attitude signals  from  the  INS  are  valid  while attitude sphere display is level. NOTE · The  INS  can  provide  test  signals to the Horizontal Situation Indicator     (HSI)     and     connected displays.    Pressing  TEST  switch during     STBY,     ALIGN,     or     NAV mode causes all digits on connected digital displays to indicate   8's,   and   illuminates   the WYPT  on  the  pilot's  HSI  and  the ALERT   annunciator.      Additional HSI     test     signals     are     provided when   INS   is   in   ALIGN   and   data selector  is  at  any  position  other than   DSRTK/STS.      Under   those conditions,  pressing  TEST  switch causes   HSI   to   indicate   heading, drift  angle,  and  track  angle  error, all at 0°  or 30°.  At the same time, cross  track  deviation  is  indicated at   3.75   nautical   miles   (one   dot) right or left and INS-controlled HSI flags are retracted from view. · Output test signals are supplied to the autopilot when INS steering is selected.        Rotating    AUTO/MAN switch    to    AUTO    and    pressing TEST  during  alignment  furnishes a 15°  left bank steering command. A 15° right bank steering command is furnished when AUTO/MAN switch is set to MAN. · The autopilot will not engage until after     the     CDU     test     switch     is pressed   and   the   NAV   flags   are pulled out of view. · The  quick  test  procedure  may  be performed any time after alignment  state  8  is  reached  and prior to entry into NAV. 1.  Mode selector (MSU) - ALIGN. Observe CDU displays are illuminated. 2.    Data  selector  (CDU)  DSRTK/STS.    Monitor right  data  display  until  state  8  (or  lower)  is reached.  Observe right data display is ---N4, where N is not 9. 3.  AUTO-MAN switch (CDU) - MAN. 4.      Data   selector   Set   to   any   position   except DSRTK/STS. 5.  CDU test switch - Hold depressed. 6.  INS Couple to flight director and autopilot, as applicable. After performing the preceeding step, observe: a.        All    annunciators    in    MSU    Check illuminated. b.  All annunciators in CDU - Check 3-49