(d)  
On LH 082-099; AF 150-199; AZ 231 WITH SB 27-2343, AND AZ 281-299; SN 351-399; MD ALL; GN ALL; AT ALL; VM ALL, plus airplanes incorp SB 27-2297; static line disconnected from three flap positioning airspeed switches.

 (e)  
Static line disconnected from drain fitting 5 (Fig 301, sheet 1).

 (f)  
On LH 001-003; AF 101-104; AZ 201-202, static line disconnected from drain fitting 18 (Fig 301, sheet 3).

 (g)  
Static line disconnected from drain fitting 24 (Fig 301, sheet 4).

 (h)  
On AZ 201-202, 209-211; IB 405, static hose disconnected from flight recorder.

 (i)  
If installed, static line disconnected from lower rudder ratio control module at aft equipment center.

 (j)  
On LH 001-003; AF 101-103; AZ 201; less airplanes incorporating SB 27-2027, static line disconnected from left elevator feel computer.

 (k)  
If installed, static line disconnected from lower rudder ratio module at section 48.

 (15)
 Flush auxiliary static system number 2 from static hose disconnected from lower left pitot-static probe to:

 (a)  
Static line disconnected from drain fitting 31 (Fig 301, sheet 1).

 (b)  
Static hose disconnected from upper right pitot-static probe.

 (c)  
On FREIGHTERS, static lines disconnected from drain fitting 34. Refer to figure 301, sheet 2.

 EFFECTIVITY
 
 ALL  07 Page 312  Apr 25/9434-11-00
 (d)  On ALL FREIGHTERS EXCEPT LH 082; AF 151-154,
 static line disconnected from nose door latch differential
 pressure switch.
 (e)  Static hose disconnected from differential pressure indicator
 in flight engineer's panel.
 (f)  On LH 011-099; AF 152-199; AZ ALL; SN 351-399; IB 415-499; plus
 airplanes incorporating SB 77-2060,
 static hose disconnected from N1 monitor altitude switch
 behind flight engineer's panel.
 (g)  On airplanes with CF6 series engines,
 static hose disconnected from engine stage cutout altitude
 switch.
 XA  (h)  On AF 101-114; AZ 201, 202, 209-211; SN 301, 302; IB 405,
 XA  in right crawlway, disconnect lavatory and galley ventilation
 XA  differential pressure switch.
 (i)  Static line disconnected from drain fitting 11 (Fig 301,
 sheet 2).
 (j)  If installed,
 static hose disconnected from galley and toilet exhaust
 differential pressure switch in right crawlway (Ref 21-26-05).
 (k)  On LH 001-070; AF 101-150; AZ 231 WITHOUT SB 27-2343, AND AZ
 201-230, 232-280; SN 301-350; IB ALL; less airplanes incorp SB
 27-2297 ;
 static line disconnected from flap positioning airspeed
 switch.
 (l)  Static hose disconnected from mach airspeed warning switch.
 (m)  Static hose disconnected from gear down dispatch airspeed
 warning switch.
 (n)  On airplanes with supplementary fuel tanks,
 static hose disconnected from fuel tank airspeed warning
 switch.
 (o)  Static hose disconnected from cabin pressure controller.
 (p)  Static line disconnected from drain fitting 12 (Fig 301,
 sheet 3).
 (q)  On airplanes with fail-operative A/P-F/D,
 static hose disconnected from altitude rate unit.
 (r)  On airplanes with fail-operative A/P-F/D or provisions,
 static line disconnected from drain fitting 36 (Fig. 301,
 Sheet 3).
 (s)  On LH 001-003, AF 101-104; AZ 201-202,
 static line disconnected from drain fitting 20 (Fig 301,
 sheet 3).
 (t)  Static line disconnected from drain fitting 22 (Fig 301,
 sheet 4).
 (u)  Static line disconnected from drain fitting 25 (Fig 301,
 sheet 4).
 (v)  On FREIGHTERS,
 static line disconnected from drain fitting 41 (Fig. 301,
 sheet 4).
 (w)  If installed,

 EFFECTIVITY

 
 ALL  ATG Page 313  Oct 25/9734-11-00
 static line disconnected from upper rudder ratio control module at aft equipment center.
 (x)  
On LH 001-003; AF 101-103; AZ 201; less airplanes incorporating SB 27-2027, static line disconnected from right elevator feel computer.

 (y)  
If installed, static line disconnected from upper rudder ratio control module at section 48.
　
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航1(36)