HOLD OPEN ROD
T12 TEMPERATURE SENSOR
A
FORWARD LATCH
FAN COWL PANEL
HINGE
GENERATOR COOLING
(4 PLACES) AIR OVERBOARD PORT
T2 TEMPERATURE SENSOR CSD ACCESS DOOR
FAN COWL LATCH (4 PLACES)
B
Fan Cowl LocationFigure 2 (Sheet 1)
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71-11-00
ALL ú ú C01 Page 3 ú Feb 25/86
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
VORTEX CONTROL DEVICE (INBOARD SEE
FAN COWL PANEL ONLY)
Fan Cowl Location
Figure 2 (Sheet 2)
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FWD
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737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
B. Access doors in the fan cowl panels are provided for servicing the engine oil tank and to monitor and replenish the CSD oil supply. The engine oil tank access door incorporates a pressure relief door. An access port, located above the CSD access door, is provided to permit manual actuation of the start valve. On some fan cowl panels, another access port, located on the left fan cowl panel, is provided to permit installation of the part power rig pin for engine trim while the fan cowl panel is closed. Two exhaust fittings are also provided, the starter air discharge duct fitting (located on the right fan cowl panel) and the generator cooling air overboard port (located on the left fan cowl panel). The starter air discharge duct fitting also incorporates a scupper and drain holes for collecting and discharging fluid leakage overboard from the engine vent and drain system.
C. The fan cowl panels are hinged at the fan cowl support beam. The panels are secured by six flush-mounted hook-type tension latches, four along the split line and two at the inlet cowl.
D. Hold-open rods, provided for each panel, allow the cowl to be supported and locked in the open position. The rods are stowed in receivers on the fan cowl when not in use.
E. A vortex control device (VCD) attaches to the inboard fan cowl panel at approximately the 2 o'clock position on the No. 1 engine and the 10 o'clock position on the No. 2 engine.
F. Three vortex generators are attached to the upper aft end of each fan cowl panel. For installation instructions, refer to Boeing 737-300 Component Maintenance Manual (CMM 71-13-26).
4. Forward Fairing (Fig. 3)
_______________
A. The forward fairing is a streamlining cowl, fairing the forward bulkhead to the fan cowl support beam. Removing the forward fairing provides access to the front of the strut forward bulkhead and the forward electrical and fluid disconnects. The forward fairing also incorporates a pressure relief door.
B. The forward fairing is attached at its forward end and along the sides with fasteners. The aft end is secured by clips to allow for strut/fairing motion.
5. Fan Duct Cowl and Thrust Reverser
_________________________________
A. Refer to AMM 78-31-00/001, Fan Thrust Reverser System, for description and operation of fan duct cowl and thrust reverser assembly.
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71-11-00
ALL ú ú C01 Page 5 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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SEE A
FORWARD FAIRING
PRESSURE RELIEF DOOR
STRUT
FWD
A
Forward Fairing Location Figure 3
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