(b)
On GJ B2509-B2510, disconnect hoses to captain's combined standby airspeed/altimeter indicator.
(c)
In electronic compartment, disconnect hoses to air data computers, flap load limiter airspeed switches, mach airspeed switch (if installed) and electronic pressure controller.
(d)
Disconnect hoses from pitot and static system drain fittings and alternate static ports.
(e)
Remove pitot static probes (34-11-11 R/I). Disconnect pitot and static hoses from each.
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Pitot Static System Drain Location 5B8
34-11-0 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 - Unpublished Work - See title page for details.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)
On GJ ALL EXCEPT B2509-B2510, flush captain's pitot system from pitot line 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 end of E1 rack.
(b)
On GJ B2509-B2510, flush captain's pitot system from capped T located behind instrument panel on outboard side to: 1) Pitot hose disconnected from combined standby airspeed/altimeter indicator. 2) Pitot line disconnected from upper left pitot static probe. 3) Pitot hose disconnected from air data computer No. 1. 4) Pitot line disconnected from drain fitting No. 1 located at left side end of E1 rack.
(c)
On GJ ALL EXCEPT B2509-B2510, flush first officer's pitot system from capped T located behind first officer's instrument panel on outboard side to: 1) Pitot hose disconnected from mach airspeed indicator. 2) Pitot hose disconnected from upper right pitot static probe. 3) Pitot hose provisions for air data computer No. 2. 4) Pitot line disconnected from drain fitting No. 10 located at right side of E1 rack.
(d)
On GJ B2509-B2510, flush first officer's pitot system from capped T located behind first officer's instrument panel on outboard side to: 1) Pitot line disconnected from upper right pitot static probe. 2) Pitot hose disconnected from air data computer No. 2. 3) Pitot line disconnected from drain fitting No. 10 located on right side of E1 rack.
(e)
Flush No. 1 auxiliary 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) On GJ ALL EXCEPT B2509-B2510,
pitot hose disconnected from mach airspeed warning switch. 3) Pitot line disconnected from drain fitting No. 3 located on right side of E1 rack.
(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,
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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
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