Cessna 510 Mustang Structural Repair Manual page 99

(4) This process is not intended for removing dents from face sheets thicker than 0.080 inch (2.0 mm).
(5) Dent removal on (convex) curved surfaces can be accomplished if a specific area on the face of the flux concentrator
coil, approximately 0.625 inch (16 mm) in length by 0.375 inch (8 mm) in width, is in contact with the dented area.
(6) Electrical equipment panels located over the dent that meet the following criteria must be disconnected when using
the EDR:
(a) Electrical equipment panels that include the airplane skin as one of its walls.
(b) Electrical equipment panels closer than 1.4 times their height.
(7) Process is not intended for removing dents on a concave surface.
(8) Process must not be used for removing dents over a fuel cell, unless it is empty and closed.
(9) Process must not be used in a flammable environment.
(10) Process must not be used in a wet environment
B. Skin Material Limitations:
(1) Dent removal can be performed only on aluminum sheet if it meets the following:
(a) Material must not have been previously cold or hand formed to alter/remove dent(s).
(b) Single layer skin panels only, i.e., process not recommended for skin panel (bonded) assemblies with multiple
layers. Use of the EDR process on multiple layer (bonded) skin panels may result in failure to remove the dent
and/or debonding the skin panels. For dents in multiple layer (bonded) skin panels, contact Cessna Citation
Customer Support for disposition.
NOTE:
(2) Skin Thickness Limitations:
(a) Maximum skin panel or face sheet thickness: 0.080 inch (2.0 mm)
(b) Minimum skin panel or face sheet thickness: 0.032 inch (0.81 mm).
NOTE:
C. Dent Dimensions (Refer to Figure 201).
NOTE: If individual dents do not meet specified depth, diameter and D/x criteria, contact Cessna Citation
Customer Support for disposition.
(1) Measure the depth of the dent by using a centered depth gage capable of measuring with an accuracy of 0.001 inch
(0.025 mm).
(2) The geometry of each dent must meet the following criteria:
(a) Maximum dent depth (x) less than or equal to 0.100 inch (2.5 mm).
(b) Dent diameter: (D) greater than 0.25 inch (6.3 mm), but less than or equal to 3.0 inches (76 mm).
(c) If D is less than or equal to 0.25 inch (6.3 mm), it is acceptable to repair by application of aerodynamic filler.
(d) Dent diameter to depth ratio: D/x must be greater than 15.
1 Diameter of dent is to be measured across the minor axis at multiple locations.
2 Minimum measured D (smallest D/x ratio) determines acceptability.
D. Dent Location
NOTE: If all location criteria cannot be met, contact Cessna Citation Customer Support for disposition.
(1) For dents in vicinity of static ports, the repaired skin must meet aerodynamic smoothness requirements. Refer to
Maintenance Manual, Chapter 34.
(2) Periphery of dent must be greater than 10 inches (254 mm) from a skin splice, cutout, penetration, or edge of skin
panel.
(3) Periphery of dent must be greater than 2 inches (51 mm) from protruding structure (e.g., antennae), stiffening
element(s) (e.g. stringer, rib, frame, spar, doubler, etc.) or fasteners.
(4) There must be no damage (deformation, cracking, etc.) to substructure in immediate vicinity of dent.
(5) There must be no sheared or loose/working fasteners in immediate vicinity of dent.
Copyright © Textron Aviation Inc.
Retain printed data for historical reference only. For future maintenance, use only current data.
This limitation applies only to solid sheet bonded materials, not to metal honeycomb
under structure.
Use of EDR on thinner material may result in over-pulling the skin/face sheet past the
original plane, resulting in a convex surface.
FOR TRAINING PURPOSES ONLY
ISSUE 02 , JAN 2018
Model 510 Structural Repair Manual (Rev 2)
51-72-00-2 (Original Issue)
Print Date: Wed Mar 21 05:12:26 CDT 2018
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