selector valve. Place selector valve in ALTERNATE position. Flush and return selector valve to NORMAL. Do not reconnect tubing at this time. 7) Static line disconnected from drain fitting No. 6 located at right forward end of nose wheel well.
(j)
On GJ B2509-B2510, flush first officer's static system from capped end of static manifold located forward of first officer's instrument panel on inboard side 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) Disconnect alternate static system tubing from first officer's static source
selector valve. Place selector valve in ALTERNATE position. Flush and return selector valve to NORMAL. Do not reconnect tubing at this time. 4) Static line disconnected from drain fitting No. 6 located right forward end of nose wheel well.
(k)
Flush first officer's static system from first officer's static hose disconnected from upper right pitot static probe to: 1) Static line disconnected from drain fitting No. 6. 2) Static line disconnected from lower left pitot static probe.
(l)
Flush No. 1 auxiliary 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
5C8
34-11-0 Page 204 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/85
in panel P5.
2) Static hose disconnected from electronic pressure controller.
3) Static hose disconnected from flap load limiter airspeed switch No. 1.
4) On ALL EXCEPT B2509-B2510,
static hose disconnected from mach airspeed switch. 5) Static line disconnected from drain fitting No. 4 located on right side of E1 rack. 6) Static line disconnected from drain fitting No. 12 located at left forward end of
nose wheel well.
7) Static hose disconnected from lower right pitot static probe.
(m)
Flush No. 1 auxiliary 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.
(n)
Flush No. 2 auxiliary static system from static line disconnected from upper right pitot static probe to: 1) Static hose disconnected from flap load 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.
(o)
Flush alternate static system from line disconnected from captain's static source selector valve to: 1) Static line disconnected from first officer's static source selector valve. Do not
5C8
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-11-0 Page 205
allow any dirt to be blown into selector valve. Reconnect line to the first officer's
static source selector valve. 2) Static line disconnected from drain fitting No. 5 located on right side of El rack. 3) Reconnect line to captain's static source selector valve.
(p) Flush alternate static system from right side static port to: 1) Static line disconnected from left side static port. 2) Static line disconnected from drain fitting No. 5.
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.
(2)
Ensure that no deposit or roughness exists in or about the static ports and pitot probe apertures.
(3)
Perform a leakage test of all systems (Ref 34-11-0, Adjustment/Test).
3. Pitot Static System Draining
A. General
(1) The pitot static system should be drained periodically per 737 Maintenance Planning Procedure Document, or when airplane has sustained ground exposure to very heavy rainfall, such as monsoonal or tropical thundersquall type rains.
B. Drain System
(1)
Locate each drain fitting as shown in Fig. 201. Operate each as described in the following paragraph:
NOTE: If temperature is below freezing, turn on probe heater for 5 minutes, and if necessary, warm drain line and fittings before draining.
(2)
Unlock and remove drain cap on lower body of drain by upward pressure and twisting to release cap from the bayonet pins. Invert drain cap and insert the raised, hexagonal shaped portion of cap into opening now exposed in bottom of drain body. Pressing cap into drain body with hand pressure opens a spring-loaded seal and allows any collected liquid in the sump to exit, by gravity flow, from pitot-static system. Remove cap, invert it, and lock it onto base of the drain as it was originally.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 導(dǎo)航 NAVIGATION 1(9)
