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 B.  The captain's pitot system, upper-left pitot-static probe, provides pitot pressure to the digital air data computer (DADC) No. 1 and to the combined standby airspeed/altimeter indicator. The first officer's pitot system, upper-right pitot-static probe, provides pitot pressure to DADC No. 2. Auxiliary No. 1 pitot system, lower right pitot-static probe, provides pitot pressure to the flap load limiter airspeed switch No. 1 (S560). Auxiliary No. 2 pitot system, lower-left pitot-static probe, provides pitot pressure to the flap load limiter airspeed switch No. 2 (S562).
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 DADC No. 1 and to the combined standby airspeed/altimeter indicator. The first officer's static system, upper-right and lower-left pitot-static probes, provides static pressure to DADC No. 2. Auxiliary No. 1 static system, lower-right and upper-left pitot-static probes, provides static pressure to the cabin differential pressure indicator, electronic pressure controller and flap load limiter airspeed switch No. 1 (S560). Auxiliary No. 2 static system, lower-left and upper-right probes, provides static pressure to the flap load limiter airspeed switch No. 2 (S562).
 C.  The alternate static system, when selected by the captain's or first officer's static source selector valve, provides static pressure to the equipment and instruments normally connected to the captain's or first officer's static system.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

ALTERNATE STATIC PORT (STA 406)
WINDOW AND PITOT HEATER MODULE (P5) (AMM 30-31-00)
CAPTAIN'S STATIC SOURCE SELECTOR VALVE
SEE C UPPER RIGHT PROBE (STA 248)
LOWER RIGHT PROBE (STA 248)
FIRST OFFICER'S STATIC SOURCE SELECTOR VALVE
SEE C

ALTERNATE STATIC PORT (LEFT AND RIGHT)
B
UPPER LEFT PROBE (STA 248)
LOWER LEFT PROBE (STA 248)
SEE A
PITOT DRAIN HOLE ALTERNATE STATIC PORT
SEE B
PITOT STATIC PROBE
S2 STATIC PORT
S1 STATIC PORT
PITOT STATIC PROBE TYPICAL (2 RIGHT AND 2 LEFT)
A
MOUNTING SCREW (3 LOCATIONS)
LEVER 
STATIC  GUARD 
LINES 
SELECT LEVER 
VALVE  (SHOWN IN
 ALTERNATE 
POSITION) 

STATIC SOURCE SELECTOR VALVE
C

Pitot Static System - Component Location
Figure 1 (Sheet 1)

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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: 6,7 & 8
. LEFT - DRAIN
FWD FITTINGS: 11 & 12
SEE D

E1 RACK FWDELECTRICAL & ELECTRONIC COMPARTMENT
. E1 RACK, RIGHT SIDE DRAIN FITTINGS: 3,4,5,9 & 10
. E1 RACK, LEFT SIDE DRAIN FITTINGS: 1 & 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 WITHOUT EFIS ú
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 ú ú 04 Page 3 ú Feb 25/87

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
　
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