2.  Thrust Reverser (Fig. 1 and 2)
_______________
 A.  The thrust reverser includes two C-shaped fan ducts each which includes:
 (1)  A circumferential array of nine stationary cascade vanes
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
FAIRINGS FORWARD STRUT 
SEE  A 
AFT FAIRING 1. UPPER BIFURCATION 2. SCREW (4 LOCATIONS) 
3. THRUST REVERSER 
SEE  B  THRUST REVERSER HINGES (6 LOCATIONS) 4. UPPER BIFURCATION FORWARD FAIRING A 5. SCREW (24 LOCATIONS)  FWD 
TRACK FAIRINGS 
BIFURCATION UPPER  POINTS FORWARD ATTACHMENT SLING ASSEMBLY 
POINTS AFT ATTACHMENT SLING ASSEMBLY 
SLEEVE TRANSLATING 
FAN DUCT COWL  FORWARD ATTACHMENT SLING ASSEMBLY POINTS 
BIFURCATION LOWER  FWD 
B 
Figure 1 Thrust Reverser 

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
DRAG LINK FIXED STRUCTURE
BLOCKER DOOR
CASCADE VANES
TRANSLATING SLEEVE ACTUATOR ROD END
FAN COWL ACCESS DOORS
DRAG LINK
FIXED STRUCTURE BLOCKER DOOR
CASCADE VANES
TRANSLATING SLEEVE
THRUST REVERSER TRANSLATING SLEEVE
STOWED POSITION

STOWED, THE TR SUPPLIES A SMOOTH AIRFLOW FOR FAN TO PRODUCE THRUST AND AN EXTERNAL AERODYNAMIC NACELLE SHAPE.
FAN FWD THRUST
EXTENDED POSITION
DEPLOYED, THE TR SENDS THE AIRFLOW FROM THE FAN TO SUPPLY REVERSE THRUST.
FIXED CASCADE VANES
REVERSED FAN THRUST
TRANSLATING SLEEVE
TR COWLING IS INSTALLED TO THE REAR OF
THE FAN COWL AND GOES AROUND THE ENGINE.

TRANSLATING SLEEVE
BLOCKER DOOR
Thrust Reverser Deployed/Stowed
Figure 2

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(2)  
A translating cowl that covers the cascade vanes while the thrust reverser is in the forward thrust mode

 (3)  
A circumferential array of 6 blocker doors that stop the exit of the fan duct to divert the fan bypass air radially outward through the cascade vanes when the thrust reverser is in the reverse thrust mode.

 B.  
The two C ducts make the right and left halves of the fan duct, and thrust reverser. Each thrust reverser includes the two inner and outer walls of the fan duct, structurally attached at the ends of the C by the upper and lower bifurcation.

 C.  
The thrust reverser is installed directly to the rear of and is attached to the fan case. It makes a bifurcated duct for fan exhaust when the separate left and right thrust reversers are latched into position.

 D.  
The separate left and right reversers are independently held from the strut by three hinges each.

 E.  
The latching system includes a left and right latch band, which attaches each half to the fan case, three lower tension latches which attach the left and right half together, and deflection limiters and wear pads which give the structural integrity necessary to install the thrust reverser to the airplane and to keep its intended shape.

 F.  
To help with the maintenance, thrust reverser opening actuator systems are given for each half, and hold-open rods hold the thrust reverser safely.

 G.  
It is not necessary to remove the thrust reverser and core cowl panels during an engine change.

 H.  
Duct sidewalls (upper and lower bifurcation) are aluminum honeycomb bulkheads to keep apart the inner and outer flowpath surfaces made by the inner cowl and the translating sleeves. A flow splitter is made by the forward edges. They are to the rear and apart from the fan frame struts.
　
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