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 ~.............................................................................. | TABLE 501 - CONVERSION OF VIBRATION UNITS TO MILS | ................................................................................ | PARAMETER | S332T304-23/-25/ | S360N021-100/-102/ | | | /-26/-27/-30 AVM | /-201 AVM | ................................................................................ | NO. 1 BRG LP VIB | 1 UNIT = 1.75 MILS | 1 UNIT = 1.75 MILS | | | | (BELOW 2.5 UNITS) *[1] | ................................................................................ | NO. 1 BRG HP VIB | 1 UNIT = 0.569 IPS | 1 UNIT = 0.569 IPS | ................................................................................ | TRF LP VIB | 1 UNIT = 2.0 MILS | 1 UNIT = 3.2 MILS | | | | (BELOW 2.5 UNITS) *[2] | ................................................................................ | TRF HP VIB | 1 UNIT = 0.65 IPS | 1 UNIT = 0.65 IPS | ................................................................................ | N1 | 10 - 120 % | 10 - 120 % | ................................................................................ | N2 | 5 - 115 % | 5 - 115 % | ................................................................................ | TIME | TENTHS OF HOURS | TENTHS OF HOURS | 2.......................…........................….............................1 *[1] For units more than 2.5; MILS = 4.375 + (UNITS - 2.5) x 6.25 *[2] For units more than 2.5; MILS = 8.0 + (UNITS - 2.5) x 4.8
 S 485-056-C00
 (2)  Put the AVM indicator overlay on the AVM indicator which is on the pilot's center instrument panel, P2.
 (a)  Use tape to keep the overlay in the correct position.
 S 485-057-C00
 (3)  Install the selector switch and breakout cable.
 (a)  For the applicable engine, open this circuit breaker and attach a DO-NOT-CLOSE tag: 1) Main Power Distribution Panel P6
 a) ENG VIB MON
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 72-31-00
 ALL  ú ú C02 Page 580P ú Nov 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
(b)  
Remove the AVM signal conditioner from the main E/E rack (AMM 77-31-03/401).

 (c)  
Connect the breakout cable to the electronic shelf connector and the signal conditioner connector.

 (d)  
Make the breakout cable and selector switch go into the flight compartment.

 (e)  
For the applicable engine, close this circuit breaker and attach a DO-NOT-CLOSE tag: 1) Main Power Distribution Panel, P6

 a) ENG VIB MON
 S 485-058-C00
 (4)  
If the vibration sensor for the No. 1 bearing does not operate, install the FFCCV vibration sensor (AMM 77-31-00/201).

 S 975-059-C00

 (5)  
Make a record of the initial balance screws as follows.

 CAUTION: MAKE SURE THAT YOU PUT COVERS ON ALL OF THE LOWER HALF OF
_______ THE INLET COWL SURFACE. ALSO MAKE SURE THAT THE EDGES OF THE MATS TOUCH OR ARE ATTACHED WITH SOME TAPE. IF THE EDGES ARE NOT, THEN THE TOOLS OR PARTS CAN FALL AND CAUSE DAMAGE TO THE INLET COWL SURFACE.
 (a)  
Use tape to put the protective mats on the inner lower half of the inlet cowl.

 (b)  
Write the type and location of the balance screws which are installed radially in the spinner rear cone (Fig. 502 and 503).

 (c)  
Remove the protective mats and all other remaining unwanted material from the inlet cowl.

 (d)  
Find and make a record of the conditions that follow.

 CAUTION: DO NOT USE THE AIRPLANE TOTAL TEMPERATURE INDICATION
_______ TO GET THE AMBIENT AIR TEMPERATURE. ALSO, MAKE SURE THAT YOU GET THE LOCAL BAROMETRIC PRESSURE (NOT CORRECTED TO SEA LEVEL) FROM THE CONTROL TOWER. THIS CAN HELP PREVENT AN INCORRECT TRIM TARGET SELECTION.
 DO NOT USE A MERCURY THERMOMETER ON THE AIRPLANE. MERCURY FROM A BROKEN THERMOMETER CAN CAUSE DAMAGE TO THE AIRPLANE COMPONENTS.
 1) Get the ambient air temperature (outside air temperature (OAT)) in the shade of the wheel well of the nose gear. 2) Get the barometric pressure.
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 72-31-00
　
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