AE 417 · Aerospace Structures and Instrumentation Laboratory · Fall 2025 · ERAU
Every aircraft in service is inspected continuously using nondestructive evaluation (NDE) methods — techniques that find damage without harming the part being inspected. NDE is what allows airlines to operate aging aircraft safely and enables manufacturers to certify composite primary structures. This lab provided hands-on exposure to five complementary NDE techniques applied to real aerospace hardware: visual inspection (borescope), thermography, radiography, liquid penetrant, and ultrasonics.
A Ridgid Micro CA-150 borescope was inserted into the interior of a metallic aircraft wing airfoil section and navigated along the inner skin surface. Under the enhanced lighting of the borescope, visible scratches and cracks near the rivet holes were identified — the type of stress-concentration-driven fatigue damage that motivates maintenance inspection intervals for riveted structures. The borescope proved effective for hard-to-access interior surfaces that no standard optical tool could reach.
The FLIR T440 camera imaged a paper subject before and after applying cold water droplets and a hand imprint. The camera resolved temperature differentials at the ±0.1°C level, with cold water appearing as cool blue zones (22.2°C) against the warm amber background (26.1°C), and the hand imprint glowing red at 26.6°C. This demonstrated how thermal gradients reveal material non-uniformities, disbonds, and coolant leaks in aerospace hardware.
X-ray images of a welded aluminum plate revealed the weld bead geometry and internal profile useful for quality assurance. An Apple Watch image illustrated how overlapping components complicate defect discrimination in complex assemblies — a known limitation of 2D projection radiography. The X-ray system required a dedicated computer and shielded enclosure for operator safety.
A fluorescent dye was applied to an aluminum pressure vessel and allowed to dwell for ~10 minutes before being wiped and developed. Under UV illumination, at least eight discrete damage indications appeared as bright zones against the green developer background — scratches and cracks completely invisible under normal white light. This demonstrated the technique’s superior sensitivity to shallow, tight surface discontinuities.
A 5 MHz piezoelectric transducer was coupled with ultrasonic couplant to stepped aluminum calibration blocks (SCB). As the probe moved from the thickest section (~24.96 mm) to the thinnest (~3.32 mm), echo spacing in the A-scan decreased proportionally, tracking known thickness steps with clear step-wise echo patterns. Ledge edges produced slight amplitude reduction from scattering, validating the technique’s sensitivity to internal geometry changes — the same principle airlines use to monitor skin corrosion on aging aircraft from the outer surface.