72-31-05
ALL ú ú N01 Page 602 ú Feb 10/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
S 016-008-N00
(2)
Remove the fan blades (AMM 72-31-02/401).
S 016-009-N00
(3)
Remove the 1st-stage stator (AMM 72-31-04/401).
S 236-010-N00
CAUTION: USE CAUTION WHEN YOU USE THIS PROCEDURE TO MAKE A DECISION
_______ ABOUT THE CONDITION OF THE ENGINE. THE INSPECTION LIMITS ARE A RESULT OF STRUCTURAL ANALYSIS. THE PART LIFE AND THE PERFORMANCE OF THE ENGINE CAN DECREASE QUICKLY WHEN THE DAMAGE OF THE PARTS BECOMES NEAR TO THE MAXIMUM CONTINUE-IN-SERVICE LIMITS.
(4)
With ultra high sensitivity penetrant, do a fluorescent penetrant inspection of the blades for cracks (AMM 70-31-01/201).
(a)
No cracks are permitted.
S 216-011-N00
(5) Refer to Table 601 and the limits that follow when you examine the 1.6th-stage blades (Fig. 601).
~............................................................. | TABLE 601 | | MAXIMUM PERMITTED 1.6TH STAGE BLADE BLEND LIMITS | ............................................................... | BLADE AREA | LIMIT | ............................................................... | A | 0.375 inch (9.525 mm) radius | ...............................................................
| B | Not more than 25% of the local |
| | thickness and not more than |
| | 10% of the airfoil surface |
............................................................... | C | 0.125 inch (3.175 mm) in depth | ............................................................... | D | None | ............................................................... | E | 0.032 inch (0.813 mm) in depth | 2......................…......................................1
NOTE: These limits are for damage that was blended, and not for
____ damage that is not blended.
(a) Blended areas must have a length that is not less than four times the depth.
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72-31-05
ALL ú ú N01 Page 603 ú Feb 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(b) The limits that follow are for blended areas that are at the
maximum depth on opposite edges of the blades.
1) One blended area must not be immediately opposite the
other.
2) One blended area must not be less than the average blade
width from the other blended area.
(c) No more than two blended areas at the maximum depth limit are
permitted on each blade edge.
(d) All blended edge damage which is not more than 1/2 the maximum
depth limit are permitted, if 3/4 of each edge is not blended.
(e) The sum of the lengths of blended tip damage must not be more
than 25% of the total tip length.
(f) Blades that have rough dents (blade material compressed and
edges raised) and defects with small radii or ragged edges must
be removed.
(g) Rounded damage at the leading and trailing edges, which you can
see on the opposite surface of the blade, are permitted as
follows:
1) The damage is on the outer half of the blade.
2) The dent is not more than 0.010 inch (0.254 mm) in depth.
(h) Carefully examine defects that are on the inner half of the
blade, before you try to repair them.
NOTE: Nicks in the leading and trailing edges change the____
performance of the engine more as they occur near to the
root.
S 216-017-N00
(6)
Examine the 1.6th stage stator rubstrip for signs of damgage.
(a)
If you find damage, refer to AMM 72-31-08/601 for the damage limits.
S 356-012-N00
(7)
Repair the applicable blades (AMM 72-31-05/801).
S 426-013-N00
(8)
Install the 1st-stage stator (AMM 72-31-04/401).
S 416-014-N00
(9)
Install the fan blades (AMM 72-31-02/401).
S 416-015-N00
(10)
Install the inlet cone (AMM 72-31-01/401).
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本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 1(180)
