Piper Aircraft Corporation Malibu Mirage PA-46-350P, Airplane Maintenance Manual

Page: 978 / 1956

PAGE 32
Feb 28/07
5E12
34-20-00
PIPER AIRCRAFT, INC.
PA-46-350P, MALIBU MIRAGE
MAINTENANCE MANUAL
d Place the ADAHR S test cable calibration switch in the "CAL" (closed) position.
Ensure that the heading system flag comes into view on the EADI, replacing the
heading scale tape and the digital readout.
NOTE: If no calibration has ever been entered into the ADAHR S memory, a
heading flag will be in view at the time of the unit initial power-up.
e Position the aircraft on the NORTH heading of the compass rose and record the
indicated "MAGHDG" as displayed on the ND. Record the heading indication in
Chart 11. (This is the raw data output from the flux detector). Repeat this step
for EA
S T, S OUTH, and WE S T headings.
f After recording the raw heading information, calculate and record the index
heading errors in Chart 11. Refer to Figure 5 to calculate the errors. The
following logic applies to calculating heading errors:
For N, if indication is +, then error is +
For N, if indication is -, then error is -
For E, if indication is more than 90, then error is +
For E, if indication is less than 90, then error is -
For
S , if indication is - and less than 1 8 0, (i.e. -179) then error is +
For S , if indication is + and less than 1 8 0, (i.e. +179) then error is -
For W, if indication is - and less than 90, (i.e. - 8 9) then error is +
For W, if indication is - and greater than 90, (i.e. -91) then error is -
Enter the errors for the four cardinal headings in Chart 11. Add the errors and
enter the sum in the "TOTAL ERROR" block in Chart 11. Divide the Total Error
by 4 and enter the result in the "INDEX ERROR" block in Chart 11. This result is
the "Index Error" of the flux detector.
g If the index error is greater than one (1) degree, loosen the flux detector and
adjust out the index error by rotating the flux detector.
h Repeat steps (e) through (g) until the index error is less than one (1) degree.
NOTE: Upon completion of the flux detector indexing procedure, apply torque
stripe to each of the flux detector mounting screws.
i This completes flux detector indexing, proceed to Heading S ystem Calibration /
Compensation, below.
2 Heading S ystem Calibration / Compensation
a Heading system calibration / compensation should be performed upon
completion of flux detector indexing, above, and using the same aircraft
configuration specified in setup, above.
b Place the Navigation Display (ND) in the "NORMAL" or mission operational
mode (normal power-up).
E
N
W
S
+
-
+
+
+ -
-
-
Calculating Heading Error
Figure 5