(b)
Blocker doors and the attached drag links
1) Cracks are not permitted.
(c)
Rotary flex shaft tubes and coupling nuts
1) Cracks are not permitted.
(d)
The translating sleeves
1) Cracks are not permitted.
(e)
The tracks and sliders
1) Cracks are not permitted.
(f)
The inner and outer ducts
1) Cracks are not permitted.
(g)
If any of the parts above have cracks, replace the parts.
S 216-006-C00
(10) AIRPLANES WITH MAGNESIUM CASCADES; Do a check of the cascade segments for cracks, nicks, gouges, and corrosion.
(a) Examine the magnesium cascades for nicks and gouges.
1) Make sure that damage along the strongback edges is not more than a depth of 0.05 inches (1.3 mm).
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2) Make sure that damage to the vanes is not more than a depth of 0.5 inches (12.7 mm).
(b)
Examine the cascades for loose fasteners or missing fasteners.
(c)
Examine the magnesium cascade segments for cracks using an eddy current inspection.
NOTE: Eddy current inspection is a proven method to find
____ cracks in the cascade segments while the cascade segments are installed on the engine.
Refer to Boeing SL 78-27 or SB 78-1057 for more information on inspection intervals. Use NDT Part 6, 51-00-00, Fig. 4 for the eddy current inspection. For equipment calibration, use aluminium surface crack reference standard number 126 or equivalent. A right angle probe with a one-half inch standoff will allow inspection on the top and bottom edges, and on the outer root radius. The magnesium cascade material is AZ92A-T6 alloy.
~...................................................................... | MAGNESIUM | CATEGORY A *[1] | CATEGORY B *[2] | | CASCADE | LOCATIONS | LOCATIONS | | PART NUMBERS | ENGINE POSITION *[3]| ENGINE POSITION *[3]| ........................................................................ | 315A1212-3 | 1 1 | 1 12 | | | | 2 7 | ........................................................................ | 315A1210-13 | 2 2 | --| ........................................................................ | 315A1213-3 | 2 4 | --| ........................................................................ | 315A1212-4 | 2 5 | 1 10 | | | 2 16 | --| 2..............…...........................…...........................1
*[1] Cascade segments that are Category A have more probability for cracking. Category B have less probability for cracking than category A locations.
*[2] All cascade segments not listed in this table are Category B. These category B locations have part numbers that are common to category A locations.
*[3] See AMM 78.31.05/401 for the cascade positions.
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1) If the crack is more than 0.75 inch long or less than 0.5 inch from a fastener hole, replace the cascade segment (AMM 78-31-05/401).
2) If the crack is less than 0.75 inch long and more than 0.5 inch from a fastener hole, stop drill the crack.
NOTE: Make sure the stop drill procedure removes the crack
____ tip. The crack tip moves more on the inner surface of the mounting flange than on the outer surface.
a) Stop drill with a 0.125 inch diameter drill bit. b) Apply DOW 19, MIL-M-3171 Type 6, or Alodine, and then primer BMS 10-11.
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