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This Group consists of a two stage high pressure turbine and a manifold for the Active Clearance Control (ACC) air. Fan air is bled onto the turbine case during cruise power operation to cool and shrink the case. This decreases turbine blade tip clearances and improves turbine efficiency. The group also includes 14th-stage bleed air cooling for the 2nd-stage vanes.
LOW PRESSURE COMPRESSOR (LPC) DRIVE SHAFT GROUP:
This Group connects the LPC and low pressure turbines. It also contains both the Number 1 low pressure rotor thrust bearing and the Number 2 roller bearing.
TURBINE NOZZLE GROUP:
This Group is located between the diffuser and high pressure turbine cases. It consists of the 1st-stage turbine nozzle guide vanes and cooling ducts supplying 17th-stage air to the 1st-and 2nd-stage turbine blades.
LOW PRESSURE COMPRESSOR (LPC) GROUP:
This Group is connected to the forward end of the LPC shaft. It contains a single stage fan disk connected to the 4th-stage drum rotor low pressure compressor. A unique feature of this group is that the fan blades are independently replaceable.
Engine components are shown in Figure 2-4 and Figure 2-5; component weights are shown in Figure 2-3.
Figure 2-3 PW2000 SERIES ENGINE COMPONENT WEIGHTS

NO.*[1]  COMPONENT  DRY WEIGHT  WET WEIGHT  SPECIAL GSE REQUIRED
LBS (KGS)  LBS (KGS) 
1  STARTER (HAMILTON STD)  39.5 (17.92)  40.5 (18.37)  NO 
2  INTEGRATED DRIVE GENERATOR  123.0 (55.79)  130.0 (58.97)  YES 
3  FUEL PUMP/FUEL CONTROL  60 (27.22)  --- YES 
4  ELECTRONIC ENGINE CONTROL (HAMILTON STD)  38.5 (17.46)  --- NO 
5  ACCESSORY/ANGLE GEAR BOX  275 (124.74)  280 (127)  YES 
6  FUEL/OIL COOLER  23 (10.43)  --- NO 
7  OIL TANK  21 (9.53)  --- NO 
8  HYDRAULIC PUMP  35.0 (15.88)  38.0 (17.24)  NO 
9  PRECOOLER  64.5 (29.26)  --- YES 

*[1] SEE FIGURES Figure 2-4 AND Figure 2-5 FOR NUMBERED COMPONENT LOCATIONS
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2.3 ENGINE SPECIFICATIONS
2.3.1 Overall Dimensions/Weights
Overall engine dimensions and basic weights are shown in Figure 2–6. These values may change over its development stage, hence, for development of ground handling configurations, the data shown must be verified with the latest available drawings. See also 2–4 Figure 2-5 and Figure 2-9.
　
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