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时间:2011-11-02 14:33来源:蓝天飞行翻译 作者:航空
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10  NAS1149C0463R  . WASHER  2 
15  BACN10YR4C  . NUT WARNING: ONLY PERSONNEL INSTRUCTED IN PROPER USAGE SHOULD OPERATE LEVER HOISTS. A LIGHTLY LOADED LEVER HOIST MAY RELEASE ITS LOAD, IF CONTROL IS PUT INTO NEUTRAL (OR FREE) POSITION. IF LEVER HOIST RELEASES, INJURY OR DAMAGE COULD RESULT. POSITION OVERHEAD SLING OVER INLET COWL (20). SECURE FOUR PINS IN INLET COWL HOIST RECEPTACLES AT THE THREE AND NINE O’CLOCK POSITIONS. ADJUST SLING AS REQUIRED TO ASSURE THE INLET COWL WILL REMAIN HORIZONTAL WHEN THE SHIPPING CONTAINER MOUNTING BOLTS ARE REMOVED. ALIGN INLET (20) ON SHEAR PINS (5). SECURE INLET (20) TO ENG FLG -A-WITH ITEMS (25 THRU 40). TIGHTEN NUTS (40) TO 300-500 LB-IN.  2 
20  .
INLET
PREASSEMBLY
(REF
INLET
PREASSEMBLY/Figure
2-1)
 REF  -
25  BACB30US6K27  . BOLT  24 
30  BACW10DS6TU  . WASHER  24 
35  NAS1149C0663R  . WASHER  24 
40  BACN10HR6CS  . NUT  24 
45  330N3011-1  . SPACER  24 

71-00-02
 
PW2000 SERIES ENGINES


757
POWERPLANT BUILDUP MANUAL


Inlet Cowl Installation
Figure 14-1 (Sheet 2)

71-00-02
P/P BUILDUP FIGURE 14-1 Page 4 May 05/2009
 

ITEM NO.  PART NUMBER  NOMENCLATURE  UC  QTY 
14-1  INLET COWL INSTALLATION (FIGURE 14-1, SHEET 2) REMOVE ACCESS PANEL IF INSTALLED. SLIDE ELECTRICAL HARNESS INTO INLET COWL AND ATTACH ELECTRICAL CONNECTORS TO PT2/TT2 PROBE. SLIDE SEAL, PLATE AND BRACKET INTO INLET COWL AND INSTALL BOLTS. POSITION ACCESS PANEL OVER OPENING IN INLET COWL. LUBRICATE ALL SURFACES OF BOLTS WITH GREASE. INSTALL CRES BOLTS AT FORWARD AND AFT POSITIONS. TIGHTEN BOLTS TO 68-82 LB-IN. INSTALL TITANIUM BOLTS. TIGHTEN BOLTS TO 68-82 LB-IN. CONNECT PT2 LINE TO INLET COWL. SEAL ACCESS PANEL GAP FLUSH WITH BMS 5-79 (BMS 5-95 OPT) SEALANT. 

71-00-02
 

QEC SYSTEMS TESTS
1.  General
A.  QEC systems tests provided in this section are optional and duplicate tests normally performed after engine installation on an airplane.
B.  Though these tests are optional, performing these tests can detect problems which could cause delays following engine installation on an airplane.
2.  Engine Fire/Overheat Warning System Test
A.  General
(1)  
This test checks electrical resistance of the fire and overheat detector system.

(2)  
Reference WDM 26-11-11, 26-11-21, 26-11-12, 26-11-22


B.  Equipment
(1)  Multimeter -Fluke 8020 or equivalent
C.  Test the fire detection warning system.
(1)  
Check that the resistance between pin 1 and 9 of connector D1082P is 3.0 K ohms ± 150 ohms.


 
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