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 | Clevis attachments:  | No wear/looseness  |  Replace/Repair before  |
 | Lever to connecting  | permitted  |  250 hours  |
 | rod to VSV unision  |  |  |
 | ring for IGV, 5th  |  |  |
 | 6th, and 7th stages  |  |  |
 | for looseness.  |  |  |
 |  |  |  |
 | Actuator support  | Maximum wear/looseness  |  Replace/Repair before  |
 | bracket upper mounting  | permitted is 0.040 inch  |  250 hours  |
 | attachments for radial  | (1.016 millimeters).  |  |
 | wear/looseness.  |  |  |
 |  |  |  |
 | Actuator support  | Maximum wear/looseness  |  Replace/Repair before  |
 | bracket lower mounting  | permitted is 0.050 inch  |  250 hours  |
 | attachments for radial  | (1.270 millimeters).  |  |
 | wear/looseness.  |  |  |
 |  |  |  |
 | Lever set assembly for  | Maximum wear/looseness  |  Replace/Repair before  |
 | axial wear/looseness  | permitted is 0.040 inch  |  250 hours  |
 |  | (1.016 millimeters).  |  |
 |  |  |  |
 | Lever set assemply for  | Maximum wear/looseness  |  Replace/Repair before  |
 | radial wear/looseness  | permitted is 0.030 inch  |  250 hours  |
 |  | (0.762 millimeters).  |  |
 |  |  |  |

 2.........................…...........................….........................1
 F.  Do an Inspection of the Variable Stator Vane Actuator (SVA) for Position Indication.
 S 866-016-N00
 (1) Supply electrical power when it is necessary (AMM 24-22-00/201).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 75-31-00
 ALL  ú ú N01 Page 609 ú Oct 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 226-017-N00
 (2)  
Do the inspection steps that follow:

 (a)  
Move the Lever Set (bellcrank) to the vane open position (unision rings move up). 1) Use a standard wrench on the wrench flats. 2) Insert the rig pin.

 (b)  
With the Ground Test Power ON, read the Stator Vane Actuator position (percent) on the flight deck display. 1) Both EEC channels must show between 94 percent and 96

 percent for the actuator position.

 (c)  
Remove the lever set (bellcrank) rig pin.

 (d)  
Move the lever set (bellcrank) to the vanes full closed stop (unision rings move down).

 (e)  
With EEC ground test power ON, read the actuator position (percent) on the flight deck display. 1) Both EEC Channels must show between -6 percent and -4

 percent.

 (f)  
If either position gives a faulty reading, or if the system is hard to operate, do the steps that follow: 1) Do Visual Check - Stator Vane Unision Ring/Actuator Linkage

 Check (FIM 71-07-00/101). 2) Do an Engine Check - Variable Stator Vane System Check
 (FIM 71-08-00/101). 3) Rig the stator vane system (AMM 75-31-00/501). 4) Replace the Stator Vane Actuator (AMM 75-31-02/401).
 S 866-021-N00
 (3)
Remove electrical power if it is not necessary (AMM 24-22-00/201).

 G.
Put the Airplane Back to Its Usual Condition.

 S 416-015-N00
 WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00 WHEN YOU CLOSE THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
 (1)  Close the thrust reversers (AMM 78-31-00/201).
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 75-31-00
 ALL  ú ú N01 Page 610 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(2)  S 416-008-N00Close the core cowl panels (AMM 71-11-06/201).
　
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