flap positioning airspeed switches (six inputs).
(b)
On AZ 212-299, pitot pressure transducer (AIDS) (one input)
EFFECTIVITY
ALL 51 Page 301 Oct 25/9734-11-00
(4)
In right crawlway (section 41), disconnect following instruments from pitot-static system:
(a) If installed (Ref 34-11-00, Description and Operation), galley and toilet exhaust differential pressure switch (one input) (Ref 21-26-05)
(5)
In main equipment center, disconnect from pitot-static system:
(a)
On LH 001-070; AF 101-199; AZ 231 WITHOUT SB 27-2343, AND AZ 201-230, 232-280; SN 301-350; IB 401-414; less airplanes incorporating SB 27-2297; flap positioning airspeed switch (two inputs).
(b)
Mach airspeed warning switch (two inputs)
(c)
Gear down dispatch airspeed warning switch (two inputs)
(d)
On airplanes with supplementary fuel tanks, fuel tank airspeed warning switch (two inputs)
(e)
Cabin pressure controller (one input)
(f)
Central air data computer No. 1 and No. 2 (two inputs each)
(g)
On airplanes with fail-operative A/P-F/D, altitude rate unit (one input)
(6)
In aft equipment center, disconnect following instruments from pitot-static system:
(a) On AZ 201-202, 209-211; IB 405,
flight recorder (two inputs)
NOTE: Access to the pitot-static connectors is through the
____ access panel in the aft closet below the aft equipment center (Fig. 302).
(b) If installed, rudder ratio control modules (four inputs)
NOTE: Access to pitot-static connectors is through ceiling
____ panel at aft equipment center.
(7)
In section 48 of the airplane, disconnect from pitot-static system:
(a)
On LH 001-003; AF 101-103; less airplanes incorporating SB 27-2027, elevator feel computers (two pitot and two static inputs) (Ref 27-31-14). On LH 004-099; AF 104-199; AZ 202-299; SN ALL; IB ALL; MD ALL; GN ALL; AT ALL; VM ALL, plus airplanes incorporating SB 27-2027, elevator feel computers (two pitot inputs)(Ref 27-31-14).
(b)
If installed, rudder ratio controller modules (four inputs)
(c)
Rate controllers on stabilizer control modules (two pitot inputs)
(8)
Remove drain assemblies from pitot-static system as follows:
(a)
In left crawlway (section 41) remove all drain assemblies (Fig. 301, sheet 1)
(b)
In right crawlway (section 41) remove all drain assemblies (Fig. 301, sheet 2).
EFFECTIVITY
ALL 53 Page 302 Oct 25/9734-11-00
AUXILIARY STATIC SEE A1 OR A2
DRAIN NO. 31 SYSTEM NO. 2 SEE B
SEE J
SEE C
JSEE DRAIN NO. 30 STATIC SYSTEM FIRST OFFICER'S
A1
DRAIN NO. 30 JSEE STATIC SYSTEM FIRST OFFICER'S CAPTAIN'S STATIC JSEE SYSTEM DRAIN NO. 32
DRAIN NO. 31 SYSTEM NO.2 AUXILIARY STATIC
SEE J SYSTEM NO. 1 DRAIN NO. 33 JSEE AUXILIARY STATIC
A2
DRAIN NO. 3 JSEE SYSTEM CAPTAIN'S PITOT DRAIN NO. 6 STATIC CAPTAIN'S SYSTEM
STATIC SYSTEM CAPTAIN'S DRAIN NO. 1 DRAIN NO. 5 SYSTEM NO. 1 AUXILIARY STATIC J DRAIN NO. 4 SEE AUXILIARY PITOT SYSTEM NO. 1
B
C DRAIN NO. 7 SYSTEM ALTERNATE STATIC
Figure 301 (Sheet 1) Pitot-Static System - Drain Location
EFFECTIVITY
ALL703 Page 303
34-11-00
Apr 25/79
AUXILIARY STATIC
SYSTEM NO. 1
DRAIN NO. 28
SEE J
FWD
AUXILIARY STATIC SYSTEM NO.2 DRAIN NO.35 SEE J
INBDFWD
E
SEE D1ORD2
SEEE SYSTEM DRAIN NO. 29 SEE J SEE F
CAPTAIN'S STATIC
D1
CAPTAIN'S STATIC SYSTEM
DRAIN NO.29
SEE J
AUXILIARY STATIC
SYSTEM NO.1
DRAIN NO.28
SEE J
FIRST OFFICER'S
STATIC SYSTEM
DRAIN NO.34
FIRST OFFICER'S SEE J
STATIC SYSTEM DRAIN NO. 10
D2
FIRST OFFICER'S PITOT SYSTEM DRAIN NO. 8
SEE J
FIRST OFFICER'S
STATIC SYSTEM
DRAIN NO. 2 AUXILIARY STATIC
SYSTEM NO. 2 DRAIN NO. 11
AUXILIARY PITOT SYSTEM NO. 2 DRAIN NO. 9
F SEE J
Pitot-Static System - Drain Location
Figure 301 (Sheet 2)
EFFECTIVITY
ALL 703 Page 304
34-11-00
Apr 25/79
STANCHION
1 APLS WITH 3-CHANNEL
NO. 3
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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(32)
