(c)  
Disconnect hoses from pitot and static system drain fittings and alternate static ports.

(d)  
Remove the four pitot static probes (Ref 34-11-11 R/I). Disconnect pitot and static hoses from all four pitot tubes.

5C8
Feb 20/89 34-11-01 Page 201
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Pitot Static System Drain Location  533 
34-11-01  Figure 201  Oct 20/84 
Page 202 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

D.  Flush Pitot Static System
(1)  Flush pitot and static lines with dry filtered air (not exceeding 15 psig) for 3 minutes. Uncap each tube or hose and flush and recap in the order indicated in following steps.
(a)  
Flush captain's pitot system from hose disconnected from upper left pitot static probe to: 1) Pitot hose disconnected from air data computer No. 1. 2) Pitot line disconnected from drain fitting No. 1 located at left side of E1 rack.

(b)  
Flush first officer's pitot system from pitot hose disconnected from upper right pitot static probe to: 1) Pitot hose disconnected from air data computer No. 2. 2) Pitot line disconnected from drain fitting No. 10 located at right side of E1 rack.

(c)  
Flush auxiliary No. 1 pitot system from pitot hose disconnected from lower right pitot static probe to: 1) Pitot hose disconnected from flap load limiter airspeed switch No. 1. 2) Pitot hose disconnected from drain fitting No. 3 located at right side of E1 rack.

(d)  
Flush auxiliary No. 2 pitot system from pitot hose disconnected from lower left pitot static probe to: 1) Pitot hose disconnected from combined standby altimeter/airspeed indicator. 2) Pitot hose disconnected from flap load limiter airspeed switch No. 2. 3) Pitot line disconnected from drain fitting No. 7 located at right forward end of

nose wheel well.

(e)  
Flush captain's static system from captain's static hose disconnected from upper left pitot static probe to: 1) Static hose disconnected from air data computer No. 1. 2) Static line disconnected from drain fitting No. 2 located at left side of E1 rack. 3) Static line disconnected from drain fitting No. 11 located at left forward end of

nose wheel well. 4) Static line disconnected from lower right static probe.

(f)  
Flush first officer's static system from first officer's static hose disconnected from upper right pitot static probe to: 1) Static hose disconnected from air data computer No. 2. 2) Static line disconnected from drain fitting No. 9 located at right side of E1 rack. 3) Static line disconnected from drain fitting No. 6 located at right forward end of

nose wheel well.
4) Static hose disconnected from lower left pitot static probe.

(g)  
Flush auxiliary No. 1 static system from port on manifold located in electronics compartment forward right side to: 1) Static hose disconnected from cabin altimeter and differential pressure indicator. 2) Static hose disconnected from electronic pressure controller. 3) Static hose disconnected from flap load limiter airspeed switch No. 1. 4) Static line disconnected from drain fitting No. 4 located at right side of E1 rack. 5) Static line disconnected from drain fitting No. 12 located at left forward end of

nose wheel well.
6) Static hose disconnected from lower right pitot static probe.

(h)  
Flush auxiliary No. 1 static system from upper left pitot static probe to: 1) Static line disconnected from lower right pitot static probe. 2) Static line disconnected from drain fitting No. 12.

(i)  
Flush auxiliary No. 2 static system from static line disconnected from upper right pitot static probe to: 1) Static hose disconnected from flap limiter airspeed switch No. 2. 2) Static hose disconnected from lower left pitot static probe. 3) Static line disconnected from drain fitting No. 8 located at right forward end of

nose wheel well.

(j)  
Flush alternate static system from static line disconnected from right side static port to: 1) Static line disconnected from left side static port. 2) Static line disconnected from drain fitting No. 5 located on right side of E1 rack. 3) Static hose disconnected from combined standby altimeter/airspeed indicator.

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Feb 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-11-01 Page 203 

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34-11-01 Page 204  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/89 

E.  Restore Pitot Static System to Normal
(1)  
Connect all pitot and static hoses or lines that were disconnected in step 2.C. to their respective components.
　
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