(1) Temporarily mark each blade (80) from 1 to 36 on their convex side.
R Use a temporary marking (Material No. CP5061). Blade No. 1 will be the blade immediately above the offset hole in the fan disk bolt flange. Numbering is counter-clockwise (CCW), forward locking aft.
(2) Removal of the first and second fan blades circled 1 and 2.
NOTE : The removal of blades (80) is counterclockwise (CCW) after the
____
first blade removed.
NOTE : Put the first blade to be removed at the 12 o'clock position
____
to ease the removal.
(a) Remove spacer (70) from the fan blade circled 2 located immediately at left of the first blade circled 1 you want to remove. Carefully lower blade circled 2 in its dovetail recess (this unlocks it from its engagement on the booster spool), and move it at a slope (inclined) to the left. Do not try to remove it now.
(b) Remove spacer (70) from the first blade circled 1 to be removed.
(c) Lower blade circled 1 in its dovetail recess (this unlocks it), and carrefully pul it forward while you move its left midspan shroud above the right midspan shroud of the (sloped) blade circled 2 at left. Remove blade circled 1.
(d) Remove blade.
(3) Removal of the 3rd to the 36th blades:
(a) The removal of the following blades is easier, done CCW, and as follows for each blade:
1 Remove spacer (70)
_
F 『 EEFF : ALL E Page 41672-21-00
E E Feb 01/00 E E ECES E F 『 E C F M E E E E 56-5B E E E 2 Remove blade (80).
_
(4) Put spacer (70) and fan blades from 1 through 36 in their related compartements on STAND, STORAGE - FAN BLADES (865A2631G01)
F 『 EEFF : ALL E Page 41772-21-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E F 『 E C F M E E E E 56-5B E
Removal of Fan Blades
Figure 403/TASK 72-21-00-991-302- 12 (SHEET 1)
F EEFF : ALL 『E 72-21-00 Page 418
E E Feb 01/98
E E
ECES E
Removal of Fan Blades
Figure 403/TASK 72-21-00-991-302- 22 (SHEET 2)
F EEFF : ALL 『E 72-21-00 Page 419
E E Feb 01/98
E E
ECES E
F 『
E C F M E
E E
E 56-5B E
E E
TASK 72-21-00-400-007
Installation of the Fan Rotor Blades
CAUTION : ALL FAN ROTOR BLADES SHALL BE MATCHMARKED OR NUMBERED FOR ASSEMBLY IN
_______ ORIGINAL ALIGNMENT AND POSITION USING ONLY APPROVED MARKING MATERIAL.
CAUTION : DO NOT DISSOCIATE FAN BLADE PAIRS MATCHED DURING ORIGINAL ASSEMBLY.
_______ BLADES FROM A SAME PAIR MUST ALWAYS BE LOCATED 180 DEGREES APART.
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific warning notice
No specific access platform 1 m (3 ft. 3 in.)
856A2631 1 STAND, STORAGE - FAN BLADES
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R Material No. CP2104 * molykote g rapid (Ref. 70-30-00) Material No. CP5062 * MoS2 dry film lubricant (Ref. 70-30-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
72-21-00-400-005 Installation of the Spinner Front Cone
72-21-00-400-006 Installation of the Spinner Rear Cone
72-21-00-991-303 Fig. 404
72-21-00-991-304 Fig. 405
F 『 EEFF : ALL E Page 42072-21-00
E E May 01/01 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
3. Job Set-up
__________ Subtask 72-21-00-860-056
A. Aircraft Maintenance Configuration
(1) Make sure that the access platform is in position.
(2) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine.
(3) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM ENGINE 发动机 1(86)
