Sure, we specialize is rapid prototyping CMM inspection where we check principal dimensions and GD&T seamlessly including position, perpendicularity, concentricity, and profile tolerances, and bearing bore where we use accurate measurement bore gauges, air gauging, and coordinate measuring machines to inspect with ±0.001mm resolution, verifying ±0.015mm tolerance with an astonishing finish of Ra 0.4-0.8μm. For pinholes, we employ gauges and optical comparators where we check an impressive ±0.002mm resolution which verifies ±0.025mm positional accuracy and ±0.013mm diameter tolerance. For straightness measurement, we laser alignment systems to verify 0.40mm/m linear meters across 300-2,000mm link lengths which is a remarkable outcome. As for material confirms using optical emission spectroscopy (OES), and X-ray fluorescence (XRF) which validates alloy composition per AMS specifications (7075, Ti-6Al-4V, 4340, 15-5PH). We also conduct extensive non-destructive testing (NDT) with particle inspection (MPI) per ASTM E1444/AMS 3041 for iron detecting surface and subsurface defects of 0.1-2mm depth, fluorescent penetrant inspection (FPI) per AMS 2644 for aluminum and titanium so we do not miss surface discontinuity inclusions of 0.05-1mm, and even perform ultrasonic inspection to assess internal void defects and porosity with eddy current testing for bearing surfaces and heat-affected surfaces. Rest assured, we also perform structural testing to ultimate loads a range of about 3.75-6.0g simulating 50-300 kN combined loads, with strain gauge monitoring and hydraulic actuator simulation. We even fatigue test forks simulating over 100,000 extension/retraction cycles with spectrum loading per ASTM E466/E647 and MIL-STD-1530D generating S-N.
The report explains that starting with data collection, data that shows the curves and the fatigue crack growth, specifically regarding the kinematic tests measuring the flap synchronization accuracy ($\pm$1$^{\circ}$) and the articulation binding forces over an angular range of 30$^{\circ}$. Orientation of the bearing, data that shows wear patterns over an extended number of cycles, and contact pressure and friction are characteristics of bearing interface testing that should be analyzed. Regarding finite element analysis (FEA), the values of stress, deflection, buckling, and overall structure will be theoretically analyzed, and the values should be within 10\% of the values collected in the experimental data. Validation of the heat treatment should be completed first, with documentation that fulfills the requirements of ASTM E18 (HRC 28-35 for steel, HRC 42-46 for 15-5PH) microstructure analysis and the stabilization of parameters that might change in training, should be examined and documented. Validation of surface treatment will include anodization as per MIL-A-8625 (thickness 50-75 encouraged) or specific citations, as well as plating thickness, and documentation of certification of FAR 21 and EASA Part 21G.
As far as supporting business jets, regional jets, military transport, and their upgrades, we provide low volume production (20-500 sets annually) as well as high volume production (in the thousands) for commercial transport jets. We can provide complete traceability of materials including certificates for metals and alloys used (7075, Ti-6Al-4V, 4340, 15-5PH) along with certificates for their heat treatments including certificates for time, temperature profiles and the hardness verification of necessary alloys. We can provide first article inspections (FAIR) according to aerospace standard 9102 along with complete volume measurements, geometric dimensional tolerancing (GD&T). We can also provide the documents required for the testing of materials of the metals, alloys, and structures to validate complete traceability for tensile, yield, and fracture strengths per standards (E8, E399) of the alloys used. We can provide the aerospace standards for non-destructive tests and traceable structural analysis of the metals to validate the ultimate load and fatigue performance were tested. We also validate the high performance of the microstructures to inhibit crack growth. Kinematic performance of the flap controls can also be documented. Finally, we can validate compliance with the aerospace standards for military and commercial jets.