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LOCALIZER NO. 3 (747SP; SN ALL)
LOOP NO. 2 ADF SENSE
NO. 1 ANTENNA
NO. 2
IB 401-405; SN ALL EXCEPT 351-360 IB 406-499; SN 351-360
747 Navigation Antenna Location
Figure 1
EFFECTIVITY IB ALL
CONFIG 3 SN ALL
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T33323
747 Navigation Systems Block Diagram Figure 2 (Sheet1)
EFFECTIVITY CONFIG 3799 Page 6
IB ALL
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747 Navigation Systems Block Diagram Figure 2 (Sheet 2)
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SN ALL
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17. Periscopic Sextant Mount (34-49-00) Kollsman A28460-00-002
________________________
A. The periscopic sextant mount provides direct access from the flight deck to the outside atmosphere as a provision for using a periscopic sextant.
18. ATC System (34-53-00) RCA AVQ-65 (IB 401, 402, 405) Collins 621A-3 (SN ALL)
__________
KING KXP 7500 (IB 406 and on)
A. The air traffic control (ATC) system, when interrogated by a ground station, automatically transmits a pulse coded signal to the ground station containing airplane altitude and identity information. This signal is displayed on a PPI used by ground personnel to monitor airplane traffic.
19. DME System (34-55-00) Collins 860E-2 or King KDM-7000 (IB)
__________
KING KDM-7000B or Bendix KDM-7000B (SN)
A. The DME (distance measuring equipment) system is used to determine airplane distance from a VOR/DME ground station. An interrogator unit in the airplane transmits a pulse coded signal to the ground station which triggers a time delayed reply. The time interval between the interrogating signal and ground station reply is measured and displayed as distance on a digital or analog indicator.
20. ADF System (34-57-00) Marconi AA3701-2 or Collins 51Y-7 (IB)
__________
Marconi AA3733-2 or Collins 51Y-7 (SN)
A. The automatic direction finder (ADF) system is used to determine airplane bearing from a conventional broadcast or low range radio station. The radio signal is simultaneously received by an omnidirectional sense antenna and a bidirectional loop antenna and resolved into a single component representing the angular position of the radio station. This station bearing is displayed relative to airplane magnetic heading on the airplane radio magnetic indicator (RMI).
21. Performance Management System (34-62-00) (When Installed)
_____________________________
A. The performance management system (PMS) provides both throttle and pitch control to attain and maintain required altitudes and speeds with the most efficient use of fuel for the selected climb, cruise or descent mode of operation. For example, during cruise the pitch control maintains the airplane altitude at the selected altitude, smooths out temporary speed changes and reduces throttle activity. The throttles are controlled during cruise to compensate for longer term effects on speed.
B. The performance management system (PMS) also provides waypoint control over the inertial naviation system (INS) so that all waypoint data may be entered into the PMS rather than into the INS. The PMS stores distance measuring equipment (DME) station data in the PMS computer unit memory. This data is selected for a desired flight plan and is also used by the PMS to provide DME updated present position to the INS.
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This subject has been relocated to 20-11-31/201.
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XA MEL - MAINTENANCE PROCEDURE NO. 34-1 TRUE AIR SPEED INDICATOR
_____________________________________________________________ XA XA 1. ____________________________________
TRUE AIR SPEED INDICATOR INOPERATIVE XA A. _______
General XA XA The following procedure is applicable when TRUE AIR SPEED INDICATOR XA is inoperative, to permit normal aircraft dispatchability as required XA by the B.747 MEL. XA XA B. _________
Procedure XA XA Placard affected TRUE AIR SPEED INDICATOR "INOP". XA
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