(d)
Pitot line disconnected from drain fitting 16 (Fig 301, sheet 3).
EFFECTIVITY
ALL 48 Page 308 Oct 25/9734-11-00
(e) Pitot hose disconnected from central air data computer No. 1.
(2)
Flush first officer's pitot system from capped "T" located behind and on centerline of first officer's instrument panel to:
(a)
Pitot hose disconnected from airspeed indicator.
(b)
Pitot hose disconnected from upper right pitot-static probe.
(c)
Pitot line disconnected from drain fitting 8 (Fig 301, sheet 2).
(d)
Pitot line disconnected from drain fitting 14 (Fig 301, sheet 3).
(e)
Pitot hose disconnected from central air data computer No. 2.
(3)
Flush auxiliary pitot system No. 1 from pitot hose disconnected from lower left pitot-static probe to:
(a)
Pitot line disconnected from drain fitting 4 (Fig. 301, sheet 1).
(b)
On LH 082-099; AF 151-199; AZ 231 WITH SB 27-2343, AND AZ 281-299; SN 351-399; IB 415-499; MD ALL; GN ALL; AT ALL; VM ALL, plus airplanes incorporating SB 27-2297; pitot hoses disconnected from three flap positioning airspeed switches.
(c)
On AZ 212-299, pitot hose disconnected from pitot pressure transducer.
(d)
On LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from drain fitting 17 (Fig 301, sheet 3).
(e)
Pitot line disconnected from drain fitting 27 (Fig 301, sheet 4).
(f)
On AZ 201-202, 209-211; IB 405, pitot hose disconnected from flight recorder
(g)
If installed, pitot line disconnected from lower rudder ratio control module at aft equipment center.
(h)
On LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from left elevator feel computer.
(i)
If installed, pitot line disconnected from lower rudder ratio controller module at section 48.
(j)
On LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from left rate controller on stabilizer control module.
(k)
On ALL EXCEPT LH 001-003; AF 101-104; AZ 201-202, unplugged swivel tee in section 48 at station 2450, forward of stabilizer trim control bracket installation.
(l)
On ALL EXCEPT LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from left elevator feel computer to uncapped tee at station 2458, LBL 8; and to line disconnected from left stabilizer control module.
(4)
Flush auxiliary pitot system No. 2 from pitot hose disconnected from lower right pitot-static probe to:
(a) Pitot line disconnected from drain fitting 9 (Fig 301, sheet 2).
EFFECTIVITY
ALL 43 Page 309 Apr 25/9734-11-00
(b)
Pitot line disconnected from drain fitting 13 (Fig 301, sheet 3).
(c)
On LH 001-080; AF 101-150, 191-192; AZ 231 WITHOUT SB 27-2343, AND AZ 201-230, 232-280; SN 301-350; IB 401-414; GN 601, less airplanes incorporating SB 27-2179 and SB 27-2297; pitot hose disconnected from flap positioning airspeed switch.
(d)
Pitot hose disconnected from mach airspeed warning switch.
(e)
Pitot hose disconnected from gear down dispatch airspeed warning switch.
(f)
On airplanes with supplementary fuel tanks, pitot hose disconnected from fuel tank airspeed warning switch.
(g)
On LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from drain fitting 15 (Fig 301, sheet 3).
(h)
Pitot line disconnected from drain fitting 23 (Fig. 301, sheet 4).
(i)
On FREIGHTERS, pitot line disconnected from drain fitting 42 (Fig. 301, sheet 4).
(j)
Pitot line disconnected from drain fitting 26 (Fig 301, sheet 4).
(k)
If installed, pitot line disconnected from upper rudder ratio control module at aft equipment center.
(l)
On LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from right elevator feel computer. pitot line disconnected from upper rudder ratio controller module at section 48.
(m)
On LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from right rate controller on stabilizer control module.
(n)
On ALL EXCEPT LH 001-003; AF 101-104; AZ 201-202, unplugged swivel tee in section 48 at station 2450, forward of stabilizer trim control bracket installation.
(o)
On ALL EXCEPT LH 001-003; AF 101-104; AZ 201-202, pitot line disconnected from right elevator feel computer to uncapped tee at station 2460 RBL 5; and to line disconnected from right stabilizer control module.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航1(34)
