Pitot-Static System
Figure 201 (Sheet 14)
EFFECTIVITY
LH 082-099; AF 151-190,193-199;
AZ 231 WITH SB 27-2343, AND
AZ 281-299; SN 351-399; MD ALL;
703 Page 222GN 602-699; AT ALL; VM ALL, PLUS
34-11-00
Apr 25/94APLS INCORP SB 27-2179 OR 27-2297
LEGEND
RSW - RIGHT SIDEWALL CP - CAPTAIN'S PITOT
LSW - LEFT SIDEWALL FP - F/O'S PITOT
LBL - LEFT BUTTOCK LINE CS - CAPTAIN'S STATIC
RBL - RIGHT BUTTOCK LINE FS - F/O'S STATIC
D - DRAIN A - ALTERNATE STATIC
C - CONNECTOR AP1 - AUXILIARY PITOT NO. 1
T - TEE CONNECTOR AS1 - AUXILIARY STATIC NO. 1
P - ALTERNATE STATIC PORT AP2 - AUXILIARY PITOT NO. 2
E - ELBOW AS2 - AUXILIARY STATIC NO. 2
Pitot-Static System
Figure 201 (Sheet 15)
EFFECTIVITY
LH 082-099; AF 151-190, 193-199;
AZ 231 WITH SB 27-2343, AND
AZ 281-299; SN 351-399; MD ALL;
703 Page 223GN 602-699; AT ALL; VM ALL; PLUS
34-11-00
Apr 25/94APLS INCORP SB 27-2179 OR 27-2297
(f) Place vinyl adhesive tape over forward set of static ports (S1) on lower left pitot-static probe.
WARNING:_______ WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT
CONDITION IS VISIBLE FROM THE GROUND. FAILURE TO
OBSERVE AND REMOVE COVERINGS OVER STATIC PORTS BEFORE
FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF
SAFE FLIGHT.
CAUTION:_______ DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. YOU
CAN CAUSE DAMAGE TO THE SURFACE IN THE AREA WHEN YOU
REMOVE THE SEALS.
NOTE: Vacuum may be applied to static system through drain
____ fitting in main electronic equipment center (using suitable adapter). Should option be chosen, all static ports mentioned in (e) and (f) must be sealed.
Test connectors (Ref par. 1.A.) may be used instead of drain fittings to connect pneumatic test set.
(g) On LH 001-070; AF 101-150; AZ 231 WITHOUT SB 27-2343, AND AZ 201-230, 232-280; SN 301-350; IB 401-414; less airplanes incorporating SB 27-2297; open T.E. FLAP LOAD RELIEF circuit breaker on P12 panel.
WARNING: FAILURE TO OPEN T.E. FLAP LOAD RELIEF CIRCUIT
_______ BREAKER MAY RESULT IN INJURY TO PERSONNEL.
NOTE: If trailing edge flaps are positioned at greater than
____ 25 degrees and simulated airspeed of auxiliary pitot-static system No. 2 is raised to 172 (| 3) knots, the flaps will be actuated unless T.E. FLAP LOAD RELIEF circuit breaker is open.
(h) Disconnect and cap pitot line, or connect separate static line from test set to stabilizer control module (Ref 27-41-04).
On AF 104; AZ 202; plus airplanes incorporating Service
Bulletin 27-2027,
disconnect and cap pitot line or connect separate static line
from test set to elevator feel computer (Ref 27-31-14).
On LH 004-099; AF 105-199; AZ 203-299, SN ALL;
IB 405-499; MD ALL; GN ALL; AT ALL; VM ALL,
disconnect pitot line from elevator feel computer and
stabilizer control module by means of quick-disconnect at
station 2450, LBL 10.
EFFECTIVITY
ALL 01 Page 224 Apr 25/9834-11-00
CAUTION: ELEVATOR FEEL COMPUTER AND STABILIZER CONTROL MODULE
_______ MUST HAVE BOTH PITOT AND STATIC CONNECTIONS OR NEITHER PITOT NOR STATIC CONNECTIONS DURING TEST; OTHERWISE DAMAGE COULD RESULT TO FEEL COMPUTER AND CONTROL MODULE.
(2) Pressurize Auxiliary Pitot-Static System No. 2
(a)
Make sure test equipment installation is complete and ready for operation.
(b)
For pressures below ambient, operate pitot vacuum source and control valve such that pressure in pitot system does not start to decrease until after static system has begun to evacuate. Pitot system vacuum should be monitored continuously during pump down.
(c)
For pressure above ambient, operate pitot pressure source and control valve such that pressure in pitot system begins to increase before static system starts to pressurize. Monitor instruments continuously.
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