G42838
500 Jan 20/82 Thrust Reverser Push-Pull Quick-Disconnect Connection Figure 406 71-00 Page 419
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
T. Connect the engine start and thrust control push-pull cables (8) at the engine cross-shaft. If adjustment is required (Ref. 76-11-0 A/T). Attach push-pull cables with bolts, bolt retainers (preferred installation), washers, and locknuts. Tighten locknuts to torques given in Fig. 403. Remove rigging pins installed in step R.
U. Connect the pneumatic duct to the flanged coupling on the horizontal firewall (4, Fig. 402).
V. Connect the engine pressure ratio sensing lines (2) at their disconnect bracket. The Pt2 line connects to the left. Connect the high pressure sensing line (9) at the disconnect bracket.
W. Connect the engine bonding lead(s) to the grounding lug (3) near the forward end of the firewall.
X. Connect and lockwire the electrical connectors (1) at the forward end of the firewall. Connect and lockwire the electrical connectors (13) on the forward horizontal firewall (Fig. 402).
Y. Connect fuel supply flex hose (11) at the disconnect bracket on the engine.
Z. On No. 1 engine connect water pressurizing line (10) at disconnect bracket.
CAUTION: CROSS-CONNECTION OF HIGH PRESSURE SENSING LINE (9) AND WATER PRESSURIZING LINE MAY RESULT IN INABILITY OF PACK VALVE TO CLOSE, WITH CONTROL SWITCH OR OVERHEAT SWITCH ACTUATION, WHENEVER THE PNEUMATIC SYSTEM IS PRESSURIZED.
506
71-00 Page 420 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/92
AA. Perform close visual check of all cleaned surfaces of lower aft flange of forward engine mount support fitting, with special attention to edge radii on both sides of each thrust link lug (Ref 54-41-0 I/C).
AB. Connect the hydraulic supply, pressure, and return lines (7) at their quick-disconnect bracket. Tighten hex head couplings to value shown in Fig. 402.
CAUTION: ENSURE TOP SECTIONS OF HYDRAULIC HOSES HAVE CLEARANCE WITH OUTER FAN DUCT TO PREVENT CHAFING DAMAGE.
AC. Install fixed fairing (Ref 71-11-21).
AD. Install thrust reverser deflector door fairing (Ref Chapter 78).
7. Restore Airplane to Normal Configuration
A. On airplanes with intermixed engines or airplanes being restored to basic engines, check 71-09-201, Power Plant (JT8D) - Intermix for special instructions.
B. Check that tools and loose material are removed and strut cavities are free of debris before installing access doors/panels.
CAUTION: TOOLS, LOOSE MATERIAL, AND DEBRIS IN STRUT CAVITIES MAY BLOCK DRAINS RESULTING IN POSSIBLE FUEL ACCUMULATION AND STRUT FIRE.
C. Install forward, mid, and aft access panels on both sides of midfairing. Install cone bolt access door on each side of fixed fairing. Install engine-to-wing forward fairing (Ref Chapter 54).
D. Check engine start and thrust control rigging (Ref Chapter 76).
E. Check adjustment of oil quantity indicating system (Ref Chapter 79). Check servicing of engine oil tank, CSD, starter, and CSD wet pad spline cavity (Ref Chapter 12).
F. Return engine fire switch to down and locked position.
G. If no other maintenance is being performed, remove tag from ground power receptacle and connect external electrical power.
H. Position ground power switch and battery switch to ON. Push (closed) FUEL FLOW circuit breakers.
I. Turn on fuel pumps for applicable engine. Check fuel system for leaks.
Note: If you must use the fuel boost pumps in the center tank, you must have a maintenance person or observer in the flight compartment to continuously monitor the LOW PRESSURE lights. Turn the applicable fuel boost pump to the OFF position if the LOW PRESSURE light for the center tank stays on.
J. Test engine in accordance with Power Plant Repair Reference Table (Ref 71-00 A/T).
K. If no further engine maintenance is necessary, install side removable cowl panels (Ref 71-11-11). Check cowl frames and air duct clearance with modeling clay to ensure approximately 0.125 inch minimum clearance. Readjust air ducts if clearance is not adequate, recheck for air leaks if any relocation of ducts was necessary on next engine run.
CAUTION: DO NOT INSTALL OTHER JT8D ENGINE COWL PANELS ON JT8D-17
ENGINES, DAMAGE TO FUEL CONTROL MAY OCCUR.
Sep 01/02 71-00 Page 421 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
POWER PLANT (JT8D) - ADJUSTMENT/TEST
1. Power Plant Test
A. General
(1)
This section provides the necessary information to accomplish the tests required following repair or replacement of engine and airplane system components. Information is also provided for minimum ground check runs required to functionally test and trouble shoot airplane systems and components.
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 動力裝置 POWER PLANT(10)
