| CZBJ |
ENGINE SECTION LOCATION |
HIGH PRESSURE COMPRESSOR |
| CZCJ |
STAGE NUMBER |
1 |
| AGAV |
END ITEM IDENTIFICATION |
F118-GE-100 AIRCRAFT GAS TURBINE ENGINE |
| APGF |
DESIGN TYPE |
AXIAL COMPRESSOR |
| MDCL |
MATERIAL DOCUMENT AND CLASSIFICATION |
TI-17 MFR REF SINGLE MATERIAL RESPONSE OVERALL |
| FEAT |
SPECIAL FEATURES |
T.O. 2J-F110-14, FIG 67, IND 5 UNDER P/N 1559M63G02; INCLUDES STAGE 2; ALSO CONSISTS NO. 1 DISK AND NO. 2 DISK AND FORWARD SHAFT THAT MAKES A 1 PIECE CONSTRUCTION THAT HOLDS BOTH STGS; WEIGHTS 40.3 LBS; BASIC P/N CAN BE USED ON ALL ENGINE TYPES, BUT ONCE USED ON THE F118, IT CAN ONLY BE USED ON AN F118 ENGINE; REIDENTIFICATION WILL CONSIST OF ADDING THE ENGINE TYPE AS A DASH NUMBER FOLLOWING THE P/N |
| CXCY |
PART NAME ASSIGNED BY CONTROLLING AGENCY |
ORIGINAL NAME SPOOL,COMPRESSOR ROTOR |
| CRTL |
CRITICALITY CODE JUSTIFICATION |
ABHP AND ABMZ AND FEAT AND CZBJ |
| ABMZ |
DIAMETER |
17.300 INCHES NOMINAL |
| ABHP |
OVERALL LENGTH |
6.143 INCHES MINIMUM AND 6.163 INCHES MAXIMUM |
| MATT |
MATERIAL |
TITANIUM ALLOY OVERALL |