(2)
Flexible Fiberscope (Flexiscope) - IF7D3X3-32, Olympus Corp., IFD
B. References
(1) AMM 49-31-42/401, Combustor Unit
C. Access
(1)
Location Zones
101 Control Cabin (Left)
205 Electronic Compartment
703 APU Compartment
(2)
Access Panels
1201 Electronic Equipment Access Door
3804 APU Cowl Door
D. Procedure
S 866-014
(1) Set the switch and the circuit breaker:
(a)
Set the APU master switch on the P5 forward overhead panel to the OFF position and attach a DO-NOT-OPERATE tag.
(b)
Open this circuit breaker and attach a DO-NOT-CLOSE tag: 1) E3-3 Electrical Shelf, APU Control Unit
S 016-015
(2) Open the APU cowl door:
(a)
Open the latches for the APU cowl door.
(b)
Open the APU cowl door.
(c)
Connect the door support rods.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
49-21-00
ALL ú ú 01 Page 601 ú Jul 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / GTCP85-129 SERIES /737-300/400/500/ ENGINES /MAINTENANCE MANUAL ////////////////////////
TURBINE TORUS
ASSEMBLYTURBINE
PLENUM SEE A
GASKET
TURBINE
NOZZLE
SEE B
TURBINE
WHEEL AND
EXDUCER
CRACKS THAT CONNECT ANY TWO
BOLT HOLES OR EXTEND FROMSEE E THE HOLE TO THE FLANGE OF
THE EXHAUST FLANGE ASSEMBLY
DIFFUSER ARE NOT PERMITTED
HOUSING
ASSEMBLY CRACKS IN THE BOLT HOLES OR AFT FLANGE OF THE EXHAUST PIPE ASSEMBLY ARE NOT PERMITTED
TURBINE PLENUM ASSEMBLY SEE I A METAL THICKNESS LESS THAN 0.03 INCH (.7 mm) DUE TO CORROSION OR
EXAMINE THE SPACERS FOR
EROSION IS NOT PERMITTED
WORN AREAS THAT CAN CAUSE THE ASSEMBLY TO INCORRECTLY CRACKS THAT CANALIGN WITH THE TORUS ASSEMBLY CAUSE THE MATERIAL TO BREAK AWAY ARE NOT PERMITTEDBUCKLING MORE THAN
0.125 INCH (3.2 mm)
IS NOT PERMITTED
CRACKS SEPARATED BY LESS THAN 0.25 INCH (6.3 mm) OFCRACKS LONGER THAN MATERIAL ARE NOT PERMITTED
0.25 INCH (6.3 mm)
ARE NOT PERMITTED
CRACKS THAT CONNECT THE
LOUVERS AND THE HOLES ARE
NOT PERMITTED
CRACKS IN THE COOLING
SKIRT ARE NOT PERMITTED
CRACKS IN THE GUIDE
VANES OR THE WELD
ARE NOT PERMITTED
COMBUSTOR UNIT
APU Engine Check Figure 601 (Sheet 1)
E36543
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
49-21-00
ALL ú ú 01 Page 602 ú Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CRACKS IN COVER LESS THAN 1.50 INCH (38.1 mm) ARE PERMITTED. CRACKS THAT CAN CAUSE THE MATERIAL TO BREAK AWAY ARE NOT PERMITTED.
EROSION IN PLUG WITH SUBSEQUENT DEFORMATIONS IN COVER NEAR INLET FLANGE DEEPER THAN
METAL THINNING OR CRACKING 0.25 INCH (6.3 mm) ARE NOT PERMITTED. EROSION WITH
IS NOT PERMITTED.
SUBSEQUENT METAL THINNING OR CRACKING ARE NOT PERMITTED
MINIMUM PERMITTED SPACE BETWEEN CRACKS IS 2.00 INCHES (51 mm).
WEAR IN INLET FLANGE LESS THAN 0.040 INCH (1 mm) DEEP IS PERMITTED UNLESS CRACKS OCCUR WHICH GO THROUGH THE OPPOSITE SURFACE OF THE INLET FLANGE
TURBINE TORUS ASSEMBLY
APU Engine Check
Figure 601 (Sheet 2)
CRACKS AROUND OR IN WELD POINTS OF EXHAUST PIPE WALL ARE PERMITTED.
CRACKS THAT ARE SEPERATED IN THE TUBE OR TUBE WELD AND SHORTER THAN ONE INCH AND DO NOT EXTEND INTO ONE OF THE TWO FLANGES ARE PERMITTED.
E36552
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
49-21-00
ALL ú ú 01 Page 603 ú Mar 12/01
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機(jī)維護(hù)手冊(cè) AIRBORNE AUXILIARY POWER 2(2)
