(3)
Verify application of air by observing that the duct pressure indicator on the flight engineer's panel registers approximately 40 PSI.
EFFECTIVITY
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34-15-00
(4) Verify air flow from left TAT probe. Air should exit probe at a
rate of approximately two cubic feet per minute.
(5) Place a thermometer adjacent to left TAT probe. Shield from
direct sunlight, wind, probe windstreams and contact with probe
or airplane.
(6) Condition the left TAT probe such that the TAT/EPRL indicator TAT
readout is +45.C or less.
NOTE:____ Heat may be applied probe by holding LEFT probe heater
switch on pilots' overhead panel in TAT TEST position.
(7) After thermometer has stabilized, check that TAT indication agrees
with ambient temperature of probe within | 2.0.C. Remove
thermometer.
(8) Select each of the flight modes in any sequence on mode selector
panel. Check that mode selected is displayed by indicator and TAT
indication should not be affected by switching from any one mode to
another.
(9) Simulate a .211 mach input per applicable section of the central
air data computer - adjustment/test, 34-12-00.
(10) Select TOD mode on mode selector panel. Apply heat to left TAT probe to verify that TAT indication increases to 59.C or more. Check that EPRL readout decreases as TAT readout increases over the range +45.C through +55.C. At 59. -0. +4.C, the yellow warning flags should obscure the TAT and EPR limit readouts. Remove heat and verify that TAT flap disappears from view at or before a temperature of 59.C is reached and that EPR limit flag disappears from view at or above a TAT indication of 52.C.
NOTE: Set LEFT probe heater switch to OFF when yellow warning
____ flags appear or at a TAT readout of +63.C maximum.
(11)
Remove mach input.
(12)
Lower nacelle anti-ice module from overhead panel P5.
(13)
Select CON flight mode on mode selector panel and observe EPRL counter readout on TAT/EPRL indicator.
(14)
Apply a jumper cable between terminal 2 of No. 1 nacelle anti-ice valve open light and aircraft ground. Observe that EPRL reading on TAT/EPRL indicator decreases an appreciable amount.
(15)
Place wing anti-ice. Switch on pilots' overhead panel to ON. EPRL reduction should be approximately double of previous test.
(16)
Set wing anti-ice switch to OFF and remove jumper cable from No. 1 nacelle anti-ice valve open light. Observe that EPRL counter readout returns to original value.
(17)
Repeat above procedure for nacelle anti-ice valve lights 2, 3 and
4. In each case, indicator readout reduction should be approximately the same value as above.
(18)
Remove jumper cable, place wing anti-ice switch to OFF and install nacelle anti-ice module.
(19)
Shutdown air supply to aspirated temperature probe.
(20)
Remove electrical power if no longer required (Ref 24-22-00).
EFFECTIVITY
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34-15-00
ALTITUDE ALERT SYSTEM - DESCRIPTION AND OPERATION
_________________________________________________
1. General_______(Fig. 1)
A. The Altitude Alert System (AAS) provides aural and visual signals to the pilots when the airplane approaches or deviates from a selected altitude. Selected altitude is set by the ALT SEL control on the autopilot-flight director mode select panel.
B. The altitude alert system includes an altitude alert computer, an altitude alert test switch, an altitude select panel, and two altitude alert annunciators.
C. The altitude alert computer receives 28-volt dc power from flight instrument bus No. 2, and 26-volt ac power from flight instrument bus No. 2 autotransformer No. 6.
D. The altitude alert computer receives altitude data from central air data computer No. 2, altitude select data from the autopilot-flight director mode select panel, barometric pressure correction from the first officer's altimeter barometric setting, and an inhibit deviation signal from the main landing gear DOWN sensor.
E. The captain's and first officer's altitude alert annunciators illuminate when approaching the selected altitude in either ascent or descent.
F. All XA except AF 121, 122, 157, 161, 183, 184; The altitude alert computer automatically resets to the approach mode whenever the difference between the selected altitude and the actual altitude exceeds 950 feet because of airplane altitude change or new altitude selection on ALT SEL control.
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