Description and Operation
Antenna
ATC Control Module
ATC Transponder
Trouble Shooting
Adjustment/Test
ATC Antenna............................................................................................................ 34-53-11 Removal/Installation
ATC Transponder .................................................................................................... 34-53-21 Removal/Installation
ATC Control Panel ................................................................................................... 34-53-31 Removal/Installation
DME SYSTEM ......................................................................................................... 34-55-0
Description and Operation
Antennas
Control Panel
Indicators
Interrogator Unit
Trouble Shooting
Adjustment/Test
DME Antenna........................................................................................................... 34-55-11 Removal/Installation
DME Interrogator ..................................................................................................... 34-55-21 Removal/Installation Subject Subject No.
5C5
Contents 34 Page 6 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
AUTOMATIC DIRECTION FINDER SYSTEM............................................................ 34-57-01
Description and Operation
Control Panel
Fixed Loop Antenna
Loop Antenna Transmission Cable
Quadrantal Error Corrector
Receivers
Sense Antenna
Sense Antenna Input Coupler
Trouble Shooting
Adjustment/Test
Automatic Direction Finder Loop Antenna ............................................................... 34-57-11 Removal/Installation
ADF Sense Antenna Couplers................................................................................. 34-57-21 Removal/Installation
ADF Sense Antenna ................................................................................................ 34-57-31 Removal/Installation
OMEGA NAVIGATION SYSTEM................................................................................ 34-59-01
Description and Operation
Antenna Coupler
Basic OMEGA Principles
Control Display Unit
Horizontal Situation Indicator
Receiver Processor Unit
Trouble Shooting
Adjustment/Test
OMEGA/ADF Antenna Coupler .................................................................................. 34-59-11 Removal/Installation
*[1] Airplanes with Collins FD-110 Flight Director System *[2] Airplanes with Sperry SP177 Auto Flight Control System *[3] GJ ALL EXCEPT B-2509 and B-2510 *[4] GJ B-2509 and B-2510 *[5] Airplanes with Sperry Primus 90 Weather Radar System *[6] Airplanes with Collins WXR-700 X Weather Radar System *[7] GJ ALL EXCEPT B-2524 *[8] GJ B-2524 *[9] GJ ALL EXCEPT B-2509, B-2510 AND B-2524 *[10] B-2509, B-2510 AND B-2524
5C8
Feb 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Contents 34 Page 7
PITOT STATIC SYSTEM -DESCRIPTION AND OPERATION
EFFECTIVITY
GJ ALL EXCEPT B-2524
1. General
A. The pitot static system consists of four combined pitot static probes; two alternate static ports; and connecting tubing to air data instruments, air data equipment, and drain trap and test fittings (Fig. 1 and 2) . These instruments measure dynamic (pitot) and ambient (static) air pressures to determine airplane vertical speed, airspeed, mach number, and altitude.
B. Heater circuits are provided for anti-icing of the pitot static probes. Refer to Chapter 30, Pitot Static Tubes and Temperature Probe Anti-Icing System.
2. Pitot System (Fig. 2)
A. Four pitot tubes are used to sense dynamic air pressure. Two probes are mounted on each side of the fuselage below control cabin window No.
B. The captain's pitot source is from the upper left pitot static probe and the first officer's from the upper right pitot static probe. These pitot pressures are applied to the appropriate instruments and equipment as shown in Fig. 2.B. Auxiliary No. 1 and No. 2 pitot pressures from the lower right and lower left pitot static probe feed various indicators and equipment.
3. Static System (Fig. 2)
A. Static or ambient pressures are sensed through two ports on the combined pitot static probe. Each static port is connected to a port on the opposite side of the airplane. The four static pressure systems feed instruments and equipment as shown in Fig. 2.B. Static pressure is also available from alternate static ports at station 406 on both sides of the airplane. These alternate static ports, when selected, feed instruments and equipment normally connected to captain's and first officer's static systems.
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