It is usually the result of faulty design or improper maintenance practices.
A51. Stress induced by press-and-shrink fits and those in rivets and bolts.
Fatigue corrosion is caused by the combined effect of corrosion and stress
applied in cycles to a component.
A slight vibration, friction, or slippage between two contacting surfaces that
are under stress or heavy load.
Steel, aluminum, and magnesium.
Applicable periodic maintenance information cards (PMICs).
A cathode, an anode, and an electrolyte.
Black paint to prevent glare.
Clad, anodized, and exfoliated.
Hand polish the corroded areas with MIL-P-6888 metal polish.
Nonclad aluminum alloys.
Aluminum wool or fiber bristle brushes.
A65. An aeronautical engineer.
A66. Structural repair manuals for the specific aircraft model.
A67. Contacts, springs, connectors, printed circuit board runs, and wires.
A68. In the engine exhaust areas.
Conduct an inspection and evaluation of the suspected area,
Extensive hand sanding or light mechanical sanding.
VACU-Blast dry honing portable machine.
Abrasive or grit blasting.
Sodium Nitrite MIL-S-24521.
The applicable aircraft Structural Repair Manual (SRM) or the "Corrosion"
section of the Maintenance Instruction Manual (MIM)
Chemical conversion coatings increase a surfaces resistance to corrosion
and improve paint bonding to the surface.
The protection of the exposed surfaces against decay.
You should wear eye protection, gloves, and a rubber apron.
Ensure the aircraft is properly grounded.
Use a NO LOAD 3200 rpm pneumatic drill motor.