Aircraft Wing Fairing Brackets CNC Machining for Aerospace

6061-T6 aluminum provides 310 MPa tensile strength and achieves ±0.075mm machinability accuracy for fairing brackets and supports 500-5,000 N loads. Fairing brackets are lightweight, thus reducing design weight by 60% when substitution steel, and also provides good corrosion protection in moisture and de-icing fluid environments. It provides reasonable stiffness to minimize fairing misalignment, has good weldability for complicated assemblies, and low cost. With 20-100 brackets produced per plane, it lowers cost for high-volume metal fabrication. 2024-T3 aluminum provides 470 MPa tensile strength and offers exceptional damage tolerance and crack growth resistance, vital for cycled flap tracks. It provides a good design life of 60,000-90,000 hours of safe flight, good formability for cast bracket design, and has topped the aeronautical industry in wing constructions. Ti-6Al-4V brings 300 kN·m/kg specific strength. It offers 900 MPa tensile strength and provides superior corrosion resistance. It does, however, expand at 8.6 µm/m K. Not only does it have high fatigue resistance, it also stays dimensionally stable in extreme temperatures (-55 to 85 degrees Celsius) and is compatible with composite fairing structures.

Milling operations with a precision of ±0.075 mm of the dimension are performed to manufacture flap track fairing brackets and pylon fairing supports. Of the composite fairing interfaces, some are manufactured with precision machining having a flatness tolerance of ±0.075 mm, and some are created with precision drilling that produces a series of bolts with a positional tolerance of ±0.060 mm per MS/AN standard. Countersinking of fastener access to a ≤ ±0.050 mm depth are placed to maintain conformity of the fairing to an aerodynamic smoothness of ±0.3 mm of the fairing surface. Some machining produces provisions to accommodate the insertion of elastomeric vibration damping cushioning materials. Edge preparation includes AS8049 deburring. Heat treatment performed includes solution treatment of 2024, T3 (tempers) (providing the best damage tolerance), solution treatment and aging of 6061,7075 to T6 (tempers), and titanium to the same treatment of solution and aging. For surface treatment, chromate conversion per MIL-DTL-5541, hard anodizing per MIL-A-8625 Type II (10-25 μm), and protective primers per MIL-PRF-23377, system TC (topcoat) to some specified standards of corrosion resistance and lastly, systems with aerodynamic requirements are included.

Our fairing bracket structures (100-800mm) dimensions and tolerances have an accuracy of ±0.075mm and we continue to make sure that fairings are aligned and contours are aerodynamic to eliminate gaps of drag >3mm or steps >2mm. Composite fairing interfaces are adjusted to a contour of flatness ±0.075mm to guarantee that we eliminate gaps of drag >3mm or steps >2mm and maintain a smooth surface for fairings to be loaded or bonded. The mounting hole positional accuracy of ±0.060mm per MS/AN standards for 4-30 fasteners is ensured to avoid load spanning that leads to an improper redistribution of load and counter sink depth tolerance of 0.050mm is maintained for a sub-flush installation of ±0.3mm with the fairing to ensure that the surface of the fairing is smooth and aerodynamic. All of these tolerances are what supports a bracket of 100-800mm with a load of 500-15, 000 N, fairing weight of 5-150 kg, fatigue life of 60,000-90,000 flight hours, and also the certification of aerodynamic fairing from the FAA and EASA compliance.

Yes. We offer full prototyping capability with CMM inspection of critical dimensions, verifying if these volume measurements are within specification, measuring dimensional accuracy to within ±0.075mm, measuring fairing interface flatness to within ±0.075mm using precision dial indicators, measuring mounting hole positional accuracy to within ±0.060mm across 4-30 locations, measuring countersink depth to within ±0.050mm, measuring perpendicularity within ±0.075mm, verifying material traceability enough to meet AMS standards (6061 per AMS 4027, 2024 per AMS 4037, 7075 per AMS 4123, Ti-6Al-4V per AMS 4928)., verifying fairing fit-check with composite or aluminum fairing components to measure contact gap closure with alignment and uniformity tolerances <3mm, for structural integrity of fully monitored and controlled structures (e.g., <0.2% un-locked and permanent deformations). For fatigue testing, we simulate flight scenarios including flap extended and retracted positioning, controlled to measure approximately 50-200 cycles per flight or 6-18 million total cycles. We measure and report fatigue growth and critical flight hour simulating 60-90K total flight hours. We document thermal GBRDS and BIS for structural components to validate incorporated thermal cycling with bracket testing for vibrations, measured after 100+ cycles down to -55C up to +85C. The flight hour cycles replicate external (average atmospheric) cyclic pressurization. Dimensional control in thermal and over 100+ cycles. Economic cycle control to measure blockage. Flight certification gaps and steps are <3mm and hold <2mm steps. The structural bracket was tested for intactness and to measure its damping capability in controlled external vibrations. The complete composite and structural testing was conducted as per RTCA DO-160. Environmental testing was performed for integrity of the complete assembly. The assembly passed material and coating flamability testing per FAR 25.853. Also measured of external vibrations up to ASTM B117 for 1000+ hours testing salt spray. Also successfully measured to pass UV exposure, and de-icing fluid for moisture and fluids are compatible.
We assist in low-volume production (50-1,000 brackets per year) for business jets and aircraft modifications, while also catering to high-volume production (thousands to tens of thousands) for commercial airplanes with full traceability of materials and compliance with AS9100D quality standards supporting FAA, EASA, and aerodynamic Performance certifications for applications in flap track fairings (covering inboard/outboard flap tracks during cruise on 737, A320, 777, 787, A350), engine pylon fairings (wing-to-nacelle fairings on twin-engine aircraft), landing gear door brackets (main gear and nose gear wheel well doors), and wing-to-body fairings (fuselage blend fairing), slat track fairings, aileron hinge fairings, spoiler hinge fairings, and commercial transpor inspection panel support brackets (A220, A320 family with 8-20 flap track fairing brackets, A350, 737 with drag reduction 2-5% from fairing coverage, 777, 787) Regional jets, business jets (G650, Global 7500, Falcon), and military transports have a service life of 60,000-90,000 flight hours with common aircraft installations of 20-100 fairing brackets. This provides fuel savings through drag reduction of 2-5% during cruise flight, which represents 70-80% of flight time.