国航机务英语第二册-阅读与理解.doc

Technical English
Reading and Writing
Contents
Unit One: Electrical Power 3
Lesson 1 Removal and Installation 4
Lesson 2 Adjustment/Test 12
Lesson 3 Location 22
Lesson 4 Warning and Caution 25
Lesson 5 Fault Description 28
Lesson 6 Troubling-shooting 33
Unit Two: Mechanic 45
Lesson 1 Removal and Installation 46
Lesson 2 Adjustment/Test 54
Lesson 3 Location 60
Lesson 4 Warning and Caution 62
Lesson 5 Fault Description 65
Lesson 6 Troubling-shooting 68
Unit Three: Avionics 79
Lesson 1 Removal and Installation 80
Lesson 2 Adjustment/Test 85
Lesson 3 Location 90
Lesson 4 Warning and Caution 92
Lesson 5 Fault Description 94
Lesson 6 Troubling-shooting 96
Unit Four: Structure 107
Lesson 1 Processes and Procedures 108
Lesson 2 Repair 114
Unit Five: Cabin 128
Lesson 1 Removal and Installation 129
Lesson 2 Maintenance Practice 132
Lesson 3 Repair 135
Unit One
Electrical Power
Lesson One
Removal and Installation
句型结构
A remove of… … … … 的拆卸
An installation of… … … … 的安装
Remove… … 拆掉… …
Install… … 安装… …
Prepare for the removal/installation… … 准备拆卸/安装… …
Before/ Pirior to removing/installing… … do… …
在拆/安装… …之前，做… …
Set… …to… … 把… …设置到… …位置
Make sure that… … 确保… …
To get access to… … 进到… …

1.
A. This procedure has these tasks:
(1) A removal of the SPCU.
(2) An installation of the SPCU.
2.
(1) Before you touch the SPCU [1], do this task: ESDS Handling for Metal Encased Unit Installation, TASK 20-40-12-400-802.
SUBTASK 24-34-11-420-001
(2) To install the SPCU [1] on the P6 panel, do this task: E/E Box Installation,
TASK 20-10-07-400-801.
SUBTASK 24-34-11-860-006
(3) Remove the safety tag and close this circuit breaker:
3.
Prepare for the Removal
SUBTASK 24-34-21-860-001
(1) Set the STANDBY POWER switch on the P5-5 panel to the OFF position and attach a DO-NOTOPERATE tag to it.
SUBTASK 24-34-21-860-002
(2) Set the BAT switch on the P5-13 panel to the OFF position and attach a DO-NOT-OPERATE tag to it.
SUBTASK 24-34-21-860-003
(3) Open this access panel:
4.
(3) Do these steps to connect the static inverter:
(a) Put the wires on the terminal studs of the static inverter.
(b) Install the nut [2], lockwasher [3] and washer [4] on the terminal stud.
(c) Tighten the nut to 135-145 inch-pounds (15.3-16.4 Newton meters).
(d) Install the nut [5], lockwasher [6] and washer [7] on the terminal stud.
(e) Tighten the nut to 65-75 inch-pounds (7.3-8.5 Newton meters).
(f) Do these steps to install the terminal block covers:
1) Hold the two terminal block covers [11] in place.
2) Install the four screws [8], lockwashers [9] and washers [10] that hold the terminal block covers.
(g) Install the electrical connector on the static inverter.
5.
B. Procedure
SUBTASK 28-22-43-420-001
(1) Move the P5-2 module close to its position in the P5 panel.
SUBTASK 28-22-43-420-002
(2) Connect the connectors D616, D626, and D628 to the rear of the P5-2 module.
SUBTASK 28-22-43-420-003
(3) Install the P5-2 module in its position with the six quick-release fasteners on the baseplate.
SUBTASK 28-22-43-710-001
(4) Do this task: Operational Test of the Fuel System Module, P5-2, TASK 28-22-43-710-801.
6.
D. Procedure
SUBTASK 28-22-43-860-003
(1) Supply external power to the airplane if power is not supplied. To do this, do this task: Supply External Power, TASK 24-22-00-860-813
(2) Remove the safety tags and close these circuit breakers:
F/O Electrical System Panel, P6-3
Row Col Number Name
A 7 C00355 FUEL TEMP IND
B 3 C00360 FUEL SPAR VALVE ENG 2
B 4 C00359 FUEL SPAR VALVE ENG 1
B 5 C00540 FUEL SPAR VALVE IND
B 7 C00361 FUEL CROSS FEED VALVE
E 11 C00313 INDICATOR MASTER DIM SECT 1
F 12 C00318 INDICATOR MASTER DIM SECT 6
Power Distribution Panel Number 1, P91
(3) Remove the safety tags and close these circuit breakers:
7.
(a) To get access to the hydromechanical unit (HMU) found at approximately 8
o’clock, do
this task: Open the Fan Cowl Panels, TASK 71-11-02-010-801-F00.
Open this access panel:
Number Name/Location
413 Left Fan Cowl, Engine 1
(b) Disconnect connector DP1207 at the HMU and jumper pin 1 to pin 2 in DP1207 (SSM 76-21-11).
(c) On the P5-2 panel, make sure that the ENG VALVE CLOSED light for Engine No. 1 is off.
(d) Remove the jumper from connector DP1207 and re-connect DP1207 to the HMU.
(e) On the P5-2 panel, make sure that the ENG VALVE CLOSED light for Engine No. 1 is on bright.
8.
General
A. A removal check valve attaches to each of the six fuel boost pumps. The fuel boost pumps are installed on the front and rear spars. The removal check valve lets you remove the motor impeller without defueling the fuel tank.
B. This procedure contains two tasks. The first task removes the removal check valve. The second tas kinstalls the removal check valve.
9.
D. Prepare for the Installation
SUBTASK 26-18-02-860-002
(1) Make sure that this circuit breaker is open and has safety tag:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 19 C00388 FIRE PROTECTION DETECTION OVHT WW WING BODY
SUBTASK 26-18-02-010-003
(2) Make sure the applicable access doors and panels are open as shown in Table 401, Wheel Well, Wing and Lower Aft Body Overheat Sensor Element Removal , TASK 26-18-02-000-801.
SUBTASK 26-18-02-010-004
(3) Make sure you remove the airplane parts that are in the way as shown in Table 401, Wheel Well, Wing and Lower Aft Body Overheat Sensor Element Removal , TASK 26-18-02-000-801.
10.
A. Aircraft Maintenance Configuration
(1) Make sure that the ground service network is energized
(Ref. TASK 24-42-00-861-801).
(2) Make sure that the access platform is in position on the side of the aircraft below the wiper.
(3) Make sure that the access platform is in position at the access door 811.
(4) Make sure that the access door 811 is open.
(5) On the panels 211VU and 212VU
(a) make sure that the WIPER control switches are in the OFF position
(b) make sure that the warning notices to tell persons not to operate the WIPER control switches are in position.
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
11.
Remove the safety clip(s) and the wiper arm goes slowly. Tag(s) and close this(these) circuit breaker(s):
FOR 5001DG
2DB1
FOR 5002DG
2DB2
FOR 5001DG The wiper is in the park position.
On the panel 211VU, set the CAPT WIPER control switch to OFF.
FOR 5002DG
On the panel 212VU, set the F/O WIPER control switch to OFF.

12.
(3) Pull down on the lever arm for the rinse fitting cap (cap) and let the cap move down to open the cap assembly.
SUBTASK 38-32-16-034-005
(4) Remove the cotter pin from the hinge pin and remove the washer.
SUBTASK 38-32-16-034-006
(5) Remove the hinge pin from the retainers and the cap.

SUBTASK 38-32-16-024-007
(6) Remove the cap.
13.
E. Procedure
SUBTASK 33-43-04-860-004
(1) Open this circuit breaker and install safety tag:
Ground Service/Handling Power Panel, P320
Row Col Number Name
E 1 C33020 TAIL L
(SSM 33-43-11) (WDM 33-43-11) (WDM 33-43-12)
SUBTASK 33-43-04-960-002
(2) Do these steps to replace the light assembly:
(a) Remove the bolts [26].
(b) Pull out the light assembly [22].
(c) Disconnect the electrical connector [21].
(d) Remove the screw [25] and washer [24] on the jumper.
(e) Pull off the jumper [23].
(f) Replace the light assembly [22].
1) Make sure the lamps are installed in the light assembly (TASK 33-43-04-960-801).
(g) Connect the jumper [23].
NOTE: Do not change the 90 degree bend in the jumper terminal lug.
14.
1) Install the washer [24] and screw [25].
2) Use the electrical bonding bonding meter, COM-1550, to make sure the resistance
between the light assembly and the jumper measures no more that 0.0025 ohms.
3) Apply a fillet seal to the connection with sealant, A02315.
(h) Connect the electrical connector [21].
(i) Bond the faying surfaces of the light assembly [22].
1) Use the electrical bonding bonding meter, COM-1550, to make sure the resistance between the lens assembly and the fuselage measures no more that 0.0025 ohms.
2) Apply the sealant, A00247 to the base of the light assembly [22].
NOTE: Do not apply the sealant to the lens assembly.
(j) Put the light assembly [22] in the tailcone.
(k) Install the bolts [26] with the corrosion-preventative compound, C00528.
15.
(1) Remove sealant around the periphery of housing and the anti-collision lens (Prepare For Sealing, TASK 51-31-01-160-801).
SUBTASK 33-44-03-900-001
(2) Remove and discard the damaged lens from housing.
SUBTASK 33-44-03-100-004
(3) Remove the used adhesive sealant from housing and edges of the lens opening (Prepare For Sealing, TASK 51-31-01-160-801).
SUBTASK 33-44-03-400-001
(4) Put the new lens with rubber bands to keep the lens in poisition.
(a) Use 0.005 to 0.020 inch (0.13 to 0.51 mm) thick teflon shims (commercially available) to make sure that the lens does not touch the housing.
(b) Attach the lens with masking tape.
(5) Do a check for a mismatch of the anti-collision lens to the surface of housing:
(a) Make sure the lens is flush to ±0.025 inch (±0.64 mm) at top and bottom of the wing tip, and other areas are no more than 0.030 inch (0.76 mm).
1) If it is necessary, use thicker or thinner shims.
Lesson 2
Adjustment/Test
句型结构
Leave … …in… …mode until… … 将… …保持在… …位，直到… …
a minimum/maximum of 15 minites 最少/最多15分钟
the lights stay on/off 灯保持亮/灭
either…or… 或…或…
do a test of the… … 做…的测试
do/perform/the following steps 做/执行下列步骤

1.
A. General
(1) The capacity check makes sure each battery pack can operate its emergency lights and signs for a minimum of 15 minutes.
(2) Make sure the battery packs are fully charged.
(3) Do the battery pack capacity check:
(a) At the overhead panel, P5, set the pilots emergency light switch to the on mode.
NOTE: You will note the amount of time the emergency lights stay on for each battery pack.
(b) Leave the switch in the on mode untill all emergency lights go off.
(c) Make sure the emergency lights and signs stay on for a minimum of 15 minutes.
1) Identify each battery pack that does not operate its emergency lights and signs for a minimum of 15 minutes.
(d) At the P5 panel, set the pilots emergency light switch to the off mode.
(e) Charge the battery packs.
2.
Procedure
SUBTASK 33-44-00-860-002
(1) Make sure electrical power is supplied to the airplane. If it is necessary, do this task: Supply Electrical Power, TASK 24-22-00-860-805
SUBTASK 33-44-00-860-003
(2) Make sure the anti-collision lights are off.
SUBTASK 33-44-00-710-003
(3) Do a test of the upper and lower anti-collision lights (beacons) with the cabin/utility switch:
(a) At the overhead panel, P5, set the cabin/utility switch to the on mode.
1) Make sure the anti-collision lights on the top and bottom of the fuselage flash 40 to 45 times a minute.
(b) Set the cabin/utility switch to the off mode.
1) Make sure the lights go off.
2.
(5) Do a test of the new lamp assembly.
(a) At the overhead panel, P5, set the switch for the lower anti-collision light (beacon) to the on mode.
1) Make sure the lamp flashes.
(b) Set the switch to the off mode.
1) Make sure the lamp goes off.
3.
1. General
A. This procedure has one task to do an operational test of the ac electrical-load-distribution system.
The operational test includes a test of the utility power ELCUs and the galley power ELCUs.
Reference Title
24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES
SSM 24-51-01 System Schematics Manual
WDM 24-51-11 Wiring Diagram Manual
B. Location Zones
Zone Area
221 CONTROL COMPARTMENT LEFT (STA 220 TO 380)
C. Additional Information
NOTE: Additional information useful for this procedure may be found in these references:
_ WDM 24-51-11, 24-53-21 thru 24-53-62
_ SSM 24-51-01, 24-53-01 thru 24-53-02
2.
SUBTASK 24-50-00-865-002
(1) Supply electrical power (PAGEBLOCK 24-22-00/201).
SUBTASK 24-50-00-715-010
(2) Do a test of the indicator lights for the electrical system:
(a) Set the IND LTS switch, on the P5 panel, to TEST.
(b) Make sure all the indicator lights for the electrical system on the P5 panel and the P461 panel come on.
(c) Set the IND LTS switch to BRT.
SUBTASK 24-50-00-865-006
(3) Make sure the BUS TIE 1, 2, 3, and 4 switches, on the P5 panel, are set to AUTO.
(a) Make sure the ISLN lights on the BUS TIE switches are off.
SUBTASK 24-50-00-865-007
(4) Make sure the OFF lights on the UTILITY switches, on the P5 panel, are off.
(a) If the OFF light(s) are on, push the applicable UTILITY switch.
SUBTASK 24-50-00-715-011
(5) Do a test of the ELCUs:
(a) Push the ELEC switch on the EICAS display panel to get access to the synoptic page for the electrical system.
(b) Make sure the ELCUs 1, 2, 3, and 4 for the utility power indicate that they are closed.
(c) Make sure the ELCUs 1, 2, 3, and 4 for the galley power indicate that they are closed.
4.
Operational Test - Electrical Power Distribution
A. General
(1) This procedure uses indicator lights and EICAS to do an operational test of these units:
(a) The ground service select relay.
(b) The ground service transfer relay
(c) The left and right utility bus relays
(d) The instrument bus voltage sensing units
5.
Do these steps to do a test of the instrument bus voltage sensing units:
(a) Supply electrical power (AMM 24-22-00/201).
(b) Push the STATUS switch on the EICAS DISPLAY select panel.
(c) Make sure the EICAS messages, CAPT INSTR XFER and F/O INSTR XFR, do not show on the bottom display.
(d) Open this circuit breaker on the main power distribution panel, P6:
1) 6J14, CAPT PRIM INST BUS
(e) Make sure the EICAS message, CAPT INSTR XFER, shows on the bottom display.
(f) Close this circuit breaker on the main power distribution panel, P6:
1) 6J14, CAPT PRIM INST BUS
(g) Make sure the EICAS message, CAPT INSTR XFER, does not show on the bottom display.
(h) Open this circuit breaker on the main power distribution panel, P6:
(i) Make sure the EICAS message, F/O INSTR XFER, shows on the bottom display.
(j) Close this circuit breaker on the main power distribution panel, P6:
1) 6L20, F/O PRIM INST BUS
(k) Make sure the EICAS message, F/O INSTR XFER, does not show on the bottom display.
(l) Remove electrical power if it is not required
(AMM 24-22-00/201).
6.
1. General
A. This procedure has this task:
(1) An operational test of the backup electrical power.
B. To do the operational test of the backup electrical power, you must either start an engine or, if the engine is already on, you can request a manually initiated engine start test through the CMC.
7.
2. Backup Electrical Power - Operational Test
A. General
(1) To