Uma-5588 | Method

A Boeing 787 repair facility recently integrated the UMA-5588 method into its post-repair protocol. After a lightning strike repair, technicians scanned the patch area. The method flagged a UI score of 0.72 where visual inspection showed a smooth surface. Upon peel testing, the area revealed a 60% lack of adhesion. The method saved the airline from a potential in-flight panel separation.

The method supports two modes:

The method was originally developed by a consortium of aerospace engineers in 2018 (Project Code: 5588) to solve a specific problem: the high rate of false negatives in carbon-fiber-reinforced polymer (CFRP) inspections. Older methods failed to detect "kissing bonds"—interfaces where two surfaces touch without adequate molecular adhesion. The UMA-5588 method resolved this by analyzing the phase shift of reflected acoustic waves across the 55–88 kHz spectrum. uma-5588 method

Per UMA-5588, each analytical batch (max 20 samples) must include:

Acceptance Criteria:

Because the sweep occurs in milliseconds, scanning a large 10-square-meter aircraft panel takes roughly 15 minutes using the UMA-5588 method, compared to 2 hours using a spot-check manual method.

The UMA-5588 method defines the procedure for determining the stability of fine-grained aggregates when subjected to cyclic moisture exposure. Unlike standard compression tests, this method focuses specifically on the material’s resistance to slaking and structural degradation during rapid wetting-drying cycles. A Boeing 787 repair facility recently integrated the

The stability of the material is calculated using the following formula:

$$USI = \left( \fracM_retainedM_initial \right) \times 100$$ uma-5588 method

Where: