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B. The pitot-static system consists of four combined pitot-static probes, two alternate flush static ports and connecting tubing. The pitot-static lines are self draining. Where this is impractical, drain traps are provided.
C. Heater circuits are provided for anti-icing of the pitot static probes. Refer to Chapter 30, Pitot Static Tubes, Alpha Vane and Temperature Probe Anti-Icing System.
Pitot System (Fig. 2)
____________
A. The airplane pitot system consists of four separate pitot systems: captain's, first officer's, auxiliary No. 1 and auxiliary No. 2. Four combined pitot-static probes are used to sense pitot pressure. Two probes are mounted on each side of the airplane below control cabin window No. 3.
B. The captain's pitot system, upper-left pitot-static probe, provides pitot pressure to the air data computer (ADC) No. 1. The first officer's pitot system, upper-right pitot-static probe, provides pitot pressure to ADC No. 2. Auxiliary No. 1 pitot system, lower right pitot-static probe, is not used. Auxiliary No. 2 pitot system, lower-left pitot-static probe, provides pitot pressure to the standby airspeed/altimeter indicator.
Static System (Fig. 2)
_____________
A. The airplane static system consists of five separate static systems: captain's, first officer's, auxiliary No. 1, auxiliary No. 2 and alternate. Static pressure is sensed through ports on the combined pitot static probes and the flush static ports at station 406 on both sides of the airplane. Each static port is cross-connected to a port on the opposite side of the airplane.
B. The captain's static system, upper-left and lower-right pitot-static probes, provides static pressure to ADC No. 1. The first officer's static system, upper-right and lower-left pitot-static probes, provides static pressure to ADC No. 2. Auxiliary No. 1 static system, lower-right and upper-left pitot-static probes, provides static pressure to the cabin differential pressure indicator and electronic pressure controller. Auxiliary No. 2 static system, lower-left and upper-right probes, is not used.
C. The alternate static system provides static pressure to the combined standby altimeter/airspeed indicator.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
ALTERNATE STATIC PORT (STA 406)
WINDOW AND PITOT HEATER MODULE (P5) (REF 30-31-00)
737-300/400/500
MAINTENANCE MANUAL
UPPER RIGHT
PROBE
UPPER LEFT(STA 248) PROBE (STA 248)
LOWER LEFT PROBE (STA 248) PROBE (STA 248) ALTERNATE LOWER RIGHT STATIC PORTSEE A SEE B
PITOT STATIC PROBE
PITOT DRAIN S2 STATIC PORT
HOLE
S1 STATIC PORT
PITOT STATIC PROBE TYPICAL (2 RIGHT AND 2 LEFT)
A
ALTERNATE STATIC PORT
(LEFT AND RIGHT)
B
Pitot Static System Component Location Figure 1 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
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ú ú 01 Page 2 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
NOSE WHEEL WELL, FORWARD BULKHEAD
. RIGHT - DRAIN FITTINGS: 6 AND 7
. LEFT - DRAIN
FWD FITTINGS: 11 AND 12 SEE D
E1 RACK FWD
ELECTRICAL AND ELECTRONICCOMPARTMENT
. E1 RACK, RIGHT SIDE DRAIN FITTINGS: 4,5,9 AND 10
. E1 RACK, LEFT SIDE DRAIN FITTINGS: 1 AND 2
SEE D
PITOT STATIC SYSTEM DRAIN LOCATION
IDENTIFICATION PLACARD
RETAINING LANYARD
CAP BAYONET FITTING
PITOT STATIC DRAIN FITTING
D
Pitot Static System - Component Location
Figure 1 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
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ú ú 09 Page 3 ú Mar 15/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
INDICATOR NO. 1 AND NO. 2 - LEFT SIDE OF
CABIN ALTIMETER
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本文链接地址：737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 1(34)
