(f)
Flush No. 2 auxiliary pitot system from pitot line disconnected from lower left pitot static probe to: 1) Pitot hose disconnected from flap load limiter airspeed switch No. 2. 2) Pitot line disconnected from drain fitting No. 7 located at right forward end of
nose wheel well.
(g)
On GJ ALL EXCEPT B2509-B2510, flush captain's static system from capped end of static manifold located forward of captain's instrument panel on inboard side to: 1) On GJ ALL EXCEPT B2509-B2510,
5C8
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-11-0 Page 203
static hose disconnected from instantaneous vertical speed indicator.
2) On GJ B2509-B2510,
static hose disconnected from combined standby airspeed/altimeter indicator. 3) Static hose disconnected from air data computer No. 1. 4) Static line disconnected from drain fitting No. 2 located at left side of E1 rack. 5) Disconnect alternate static system tubing from captain'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. 6) Static line disconnected from drain fitting No. 11 located at left forward end of nose wheel well.
(h)
Flush captain's static system from captain's static line disconnected from upper left pitot static probe to: 1) Static line disconnected from drain fitting No. 11. 2) Static line disconnected from lower right pitot static probe.
(i)
On GJ ALL EXCEPT 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 altimeter. 2) Static hose disconnected from instantaneous vertical speed indicator. 3) Static hose disconnected from mach airspeed indicator. 4) Static hose provisions for air data computer No. 2. 5) Static line disconnected from drain fitting No. 9 located at right side of E1 rack. 6) 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. 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
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 通讯描述和操作(77)
