Aerospace structures contain fastener holes, rivet holes, bolt holes, locating holes, pin holes, threaded-hole preparation, attachment holes, countersink-preparation holes, stepped holes, and repeated assembly-hole patterns.
These features are commonly found in aircraft skins, wing ribs, spars, fuselage frames, bulkheads, stringers, structural brackets, attachment fittings, support beams, seat-track components, access panels, and other assembled aerospace structures.
Workpiece materials may include aerospace aluminum alloys, titanium alloys, stainless steel, high-strength alloy steel, and metallic stack structures. Large quantities of repeated holes, thin walls, curved surfaces, overlapping components, close hole spacing, and strict assembly requirements increase the risk of drill walking, exit burrs, trapped chips, hole-size variation, tool wear, and inconsistent fastener fit.
Landun CNC Tool supports drill selection and custom carbide drill development based on the component drawing, material combination, hole diameter and depth, stack thickness, entry and exit conditions, tolerance, coolant method, burr requirement, and current machining problem.
Aircraft skins, ribs, frames, stringers, brackets, and structural panels may contain large numbers of fastener, rivet, and assembly holes that must maintain consistent diameter, spacing, and position.
Large workpiece dimensions, fixture movement, uneven entry surfaces, spindle runout, accumulated tool wear, machine-positioning variation, and thermal changes can affect repeated-hole consistency.
Stable drill-point geometry, low-runout toolholding, rigid component support, consistent edge preparation, and controlled tool-life management help improve hole-position and diameter repeatability. Spotting may be used where the entry surface does not provide reliable centering.
Aircraft skins, thin panels, ribs, brackets, and lightweight structural parts may develop exit burrs, edge tearing, local vibration, or deformation when the drill breaks through the material.
Thin sections provide limited support at the hole exit. Excessive feed, weak clamping, long tool overhang, unsuitable point geometry, or uneven remaining wall thickness can increase breakthrough force and reduce edge quality.
Sharp cutting geometry, stable workholding, low runout, and controlled feed near breakthrough help reduce cutting force and exit burr formation. Application-specific drill points can also be developed for thin-wall and unsupported exit conditions.
Fastener and assembly holes may pass through overlapping skins, brackets, reinforcement plates, or metallic stack sections. Chips can become trapped between layers or remain inside enclosed structural areas.
Changes in material thickness, small gaps between assembled sections, interrupted cutting, unsuitable flute geometry, and insufficient coolant or air delivery can prevent chips from leaving the hole efficiently.
Suitable flute geometry, controlled feed, stable chip formation, short tool overhang, and appropriate coolant or air delivery help improve chip evacuation. Custom geometry may be developed according to the material sequence, total stack thickness, and breakthrough conditions.
Titanium attachment fittings, stainless brackets, high-strength structural joints, and reinforced assembly areas may cause rapid flank wear, edge chipping, rising cutting load, or unstable hole diameter.
Titanium and high-strength aerospace materials generate high cutting loads and concentrated heat. Low thermal conductivity, work hardening, material adhesion, and insufficient coolant delivery can accelerate coating wear and cutting-edge damage.
Material-specific geometry, suitable carbide grades, controlled edge preparation, wear-resistant coatings, and stable coolant delivery help improve cutting-edge strength and tool-life consistency. Cutting parameters should be matched to the material, hole depth, and production volume.
Close-tolerance fastener holes, bolt-hole preparation, pin holes, countersink-preparation holes, stepped holes, and assembly features may require stable diameter, depth, concentricity, and finishing allowance.
Repeated tool changes, drill-point allowance, tool wear, unstable entry, chips remaining inside the hole, and accumulated positioning errors can affect the final relationship between the drilled hole and later reaming, countersinking, or fastening operations.
Stable drill geometry, controlled working length, consistent diameter control, and suitable preparation allowance help improve downstream assembly. Step, chamfer, and combination carbide drills can reduce tool changes and maintain the relationship between connected features.
RECOMMENDED DRILL SERIES
Common drilling applications include rivet holes, panel-attachment holes, locating holes, inspection-panel holes, repeated edge-hole patterns, and preparation holes in aluminum aircraft skins and structural panels.
Typical features include fastener-hole patterns, bolt holes, locating holes, attachment holes, threaded-hole preparation, and repeated connection features in ribs, spars, stringers, and wing structural members.
Common applications include assembly holes, rivet holes, bolt holes, locating holes, bracket-attachment holes, pin-hole preparation, and repeated connection patterns across frames, bulkheads, and structural joints.
Typical drilling applications include mounting holes, pin holes, bolt-hole preparation, stepped holes, threaded-hole preparation, combined drilling and chamfering, and close-tolerance attachment features.
For fastener holes, rivet holes, bolt holes, locating holes, threaded-hole preparation, and general assembly drilling in aircraft skins, ribs, spars, frames, brackets, and structural fittings.
For small rivet holes, inspection holes, locating features, compact bracket holes, small pin holes, and other small-diameter assembly applications.
For deep attachment holes, long structural connection features, thick fittings, support blocks, and other high depth-to-diameter assembly-hole applications.
For metallic stack structures, angled entry, stepped holes, combined drilling and chamfering, countersink preparation, special diameters, thin-wall breakthrough, and drawing-based assembly features.
| INFORMATION | WHY IT MATTERS |
|---|---|
| Component or assembly drawing | Confirms hole positions, repeated patterns, joint structure, entry angles, feature relationships, tolerances, and special requirements. |
| Workpiece material or material combination | Helps determine carbide grade, drill geometry, flute design, edge preparation, coating, and cutting parameters. |
| Individual and total stack thickness | Helps evaluate drilling depth, material transitions, chip evacuation, breakthrough conditions, and required working length. |
| Hole diameter, depth, and type | Defines drill size and blind-, through-, fastener-, rivet-, pin-, step-, or preparation-hole requirements. |
| Position, diameter, and finishing allowance | Helps determine entry control, runout limits, drill size, later reaming or countersinking allowance, and inspection requirements. |
| Entry and exit conditions | Helps assess curved entry, thin-wall breakthrough, unsupported exits, interrupted cutting, and burr risk. |
| Burr, surface, and assembly requirements | Helps evaluate cutting-edge geometry, breakthrough control, hole-edge quality, and fastener-fit requirements. |
| Machine, holder, fixture, and coolant conditions | Helps assess machine rigidity, spindle runout, component support, tool access, coolant or air delivery, and chip evacuation. |
| Current machining problem and production target | Clarifies burrs, chip retention, drill walking, tool wear, hole variation, breakage, tool life, or cycle-time targets. |
Review the component drawing, workpiece material, hole structure, machine conditions, and current drilling problem.
Select a suitable standard drill series or develop a custom drill based on hole depth, tolerance, entry conditions, and machining requirements.
Produce the drill with controlled geometry, edge preparation, coating selection, and multi-stage inspection to support consistent quality.
Support sample testing, specification confirmation, and stable repeat production after the drill solution is approved.
Walter 5-axis grinding supports stable drill-point geometry, flute consistency, diameter accuracy, and shank concentricity.
Controlled edge preparation helps improve cutting-edge consistency, coating adhesion, wear resistance, and tool-life stability.
Coating selection is matched to the workpiece material and drilling conditions to improve wear resistance, heat control, and cutting stability.
HELICHECK PLUS and 150× / 300× visual inspection help verify dimensions, cutting edges, coating appearance, and overall tool condition.
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