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 NOTE: TRF sensors with a 50 pC/g sensitivity have an
____ identification (white) bushing installed on the sensor lead approximately 3 inches (76 mm) from the connector mounting bracket. This bracket is found at the 5:30 o'clock position on the high pressure compressor (HPC) forward stator case. TRF sensors with a 20 pC/g sensitivity do not have an identification bushing. Also, TRF sensors with a 50 pC/g sensitivity have this mark, "50 pC/g", engraved on the lead connector housing. TRF sensors with a 20 pC/g sensitivity are not engraved.
 2)  If the AVM is not compatible, applicable corrective action must be taken to get compatibility (Ref SB 77-1011 and CFMI SB 77-008).
 CAUTION: MAKE SURE THAT THE CORRECT CONE BOLTS ARE INSTALLED ON THE
_______ TWO FORWARD ENGINE MOUNTS. THE CONE BOLTS FOR AIRPLANES WITH VIBRATION ISOLATORS ARE DIFFERENT SIZES THAN THE CONE BOLTS FOR AIRPLANES WITHOUT VIBRATION ISOLATORS. INCORRECT CONE BOLT INSTALLATION CAN CAUSE DAMAGE TO THE CONE BOLT AND THE STRUT CROSSBEAM.
 (b) Engine/strut vibration isolation compatibility requirements.
 1)  If the power plant configuration includes vibration isolation, use the table below to get the correct cone bolt for strut crossbeams with or without vibration isolators.
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 71-00-02
 ALL  ú ú C17B Page 470 ú Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
Prepare For the Installation of the Power Plant
_______________________________________________
 ~........................................................................ | ENGINE/STRUT VIBRATION ISOLATION COMPATIBILITY REQUIREMENTS | ..........................................................................
 |  STRUT CROSSBEAM  |  FORWARD ENGINE MOUNT  |
 |  CONFIGURATION  |  CONE BOLT P/N 310A1041( )  |
 |  .................................... .....
 |  |  LEFT  |  RIGHT  |

 .......................................................................... | WITH VIBRATION ISOLATORS | -5 | -5 | | WITHOUT VIBRATION ISOLATORS | -1 | -2 or -7 | 2................................….................….....................1
 2)  If the engine and the strut vibration isolation configurations are not compatible, change the forward engine mount cone bolts (AMM 71-21-01/401).
 (c) Pneumatic control logic and the wire bundle W1508.
 1)  Make sure the configuration of the wire bundle W1508 (WDM 36-11-01) at the bleed air regulator (M1180) agrees with the airplane for the correct operation of the PRSOV during an engine start. a) AIRPLANES WITHOUT SB 36-1016;
 Wire 1508-011 is connected to pin 4 of the connector D3064.
 b)  AIRPLANES WITH SB 36-1016; Wire 1508-011 is connected to pin 5 of the connector D3064.
 c)  AIRPLANES BEFORE LINE POSITION 1628 AND AIRPLANES WITHOUT SB 36-1016; Wire 1508-011 is connected to pin 4 of the connector D3064.
 d)  AIRPLANES AFTER LINE POSITION 1628 AND AIRPLANES WITH SB 36-1016; Wire 1508-011 is connected to pin 5 of the connector D3064.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-00-02
 ALL  ú ú C08B Page 471 ú Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
Prepare For the Installation of the Power Plant
_______________________________________________
 (d) Engine/strut interference compatibility
 CAUTION:_______ BEFORE YOU INSTALL THE POWER PLANT, MAKE SURE THE COUPLING
 ON THE INLET COWL ANTI-ICING DUCT ABOVE THE 12 O'CLOCK
 STRUT IS ALIGNED SUCH THAT THE TENSIONER BOLT IS ON THE
 INBOARD OR OUTBOARD SIDE.  IF THE COUPLING IS NOT
 CORRECTLY ALIGNED, DAMAGE TO THE STRUT AND COUPLING CAN

 OCCUR.
 (e) Fuel control box compatibility
 1)  Make sure the correct fuel control box agrees with the fuel control push-pull cables installed for the airplane model and engine type.
　
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