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3-3-9.  Controls and Function, Gyromagnetic Com- pass Set (AN/ASN-43)
Figure  3-3-5.  Doppler Navigation Set Control (AN/ASN-128)

TM-1-1520-240-10 Army CH-47D Heilcopter (EIC:RCD) Manual
Page Navigation
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TM  1-1520-240-10            3-3-5 NOTE If synchronizing becomes necessary in flight with   the   AFCS   on,   position   the   SWIVEL switch to UNLOCK. After synchronization is complete,   position   the   SWIVEL   switch   to LOCK. This prevents unwanted yaw axis in- puts. c.  Manual Synchronization.  If power has been ap- plied to the system with the compass slaving switch at FREE  or  if  the  system  has  been  operated  in  the  free directional gyro mode for a period of time, the compass cards will not be aligned with the magnetic heading of the helicopter. The system can be reset to the correct mag- netic heading by pushing and turning the PUSH TO SET knob in the direction of the symbol indicated by the an- nunciator pointer until the pointer is centered. If the slav- ing switch is then set to SLAVED, the compass cards will maintain correct magnetic heading. Figure  3-3-4.  Directional Gyro (CN-998/ASN-43) 3-3-11.  Doppler Navigation Set (AN/ASN-128). NOTE When   the   Airborne   Navigation   Set   AN/ ASN-149 (Global Positioning System GPS) is installed,  the  Doppler  Navigation  Set  AN/ ASN-128 is controlled by the GPS CDU. For a description of the Airborne navigation Set and Doppler Navigation Set. a.  The doppler navigation set (fig. 3-3-5) is a self- contained navigation system that does not require any ground-based aids. The system provides worldwide nav- igation with position readout available in both universal transverse mercator (grid) (UTM) and latitude and longi- tude  (lat/long).  Navigation  and  steering  is  done  using lat/long coordinates, and bilateral UTM-lat/long conver- sion routine is provided for UTM operation. b.  The system in conjunction with heading data from the gyro compass, and pitch and roll data from the copi- lot’s attitude gyro, provides velocity, position, and steer- ing information from ground level to 10,000 feet. c.  The computer-display unit (CDU) is on the canted console, between the pilot and copilot positions. Course deviation, bearing, distance to destination, and NAV GO/ NOGO are also presented to the HSI. Built in test equip- ment (BITE) continuously monitors system operation. If a failure occurs, a malfunction indicator lamp will light and coded data, indicating the failed component, will be displayed on the CDU when the MODE switch is set to TEST. Power to operate the set is supplied by the No. 2 DC bus through the NAV DOPPLER circuit breaker on the No. 2 PDP, and the No. 1 AC instrument bus through the NAV DOPPLER circuit breaker on the No. 1 PDP.







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