Cessna 510 Mustang Structural Repair Manual page 23

(2) Indicate whether damage crosses any structure (e.g., stiffeners, frames, ribs etc.) and whether that structure is
damaged.
(3) Indicate whether cracks were detected from gouges or dents and what method of inspection was used to detect
crack damage. (Preferred methods are eddy current and fluorescent penetrant).
(4) Indicate inspection method(s) used to verify any "crack free" condition(s).
(5) Thoroughly inspect all surrounding and sub-structure in the vicinity of primary damage for secondary or collateral
damage
C. Corrosion
(1) Specify method of inspection used to find damage.
CAUTION: Control the corrosion removal process so you only remove the minimum material.
(2) Locally and completely remove corrosion per Model 510 Structural Repair Manual (do not blend) for purposes of
determining maximum depth of or extent of damage.
(3) Inspect for cracks per Model 510 Nondestructive Testing Manual Part 7, Penetrant Inspection.
(4) After complete corrosion removal, measure length, width, depth, and thickness of the material remaining and, if
possible, the original thickness. Also measure dimensions to nearest adjacent details (e.g. fasteners, holes, radii,
edges etc.). Specify data on detailed sketch.
(5) To aid in quantifying required dimensions, it is recommended that molds (e.g. constructed of either 5-minute epoxy or
plaster) be made. Make sure molds fully encompass damage area(s) and details such as nearest adjacent fasteners,
holes, edges and radii. Obtain required dimensions from molds. Retain molds for possible shipment to Cessna.
(6) If damage encompasses a large area, include dimensions on contour maps.
Copyright © Textron Aviation Inc.
Retain printed data for historical reference only. For future maintenance, use only current data.
FOR TRAINING PURPOSES ONLY
ISSUE 02 , JAN 2018
Model 510 Structural Repair Manual (Rev 2)
51-01-00-0 (Original Issue)
Print Date: Wed Mar 21 05:09:54 CDT 2018
Page 2 of 6