AME-S STRUCTURES #1

How do you find ‘’K’’ Value?. Tangent x (Bending Degrees/2). Sine × (Bending Degrees/2). Radius ÷ (Material Thickness × 2). Cosine × (Neutral Axis Factor).

What type of Chisel is typically used to remove the collar from a mechanical lock fastener?. Cape Chisel. Flat Chisel. Round-Nose Chisel. Diamond-Point Chisel.

Which tool should you not use to cut Kevlar?. WATER JET CUT. ROTARY FILE. DIAMOND WHEEL. SCISSOR SHEAR.

When repairing a Wing Panel, the cutout should have a radius of?. 0.500’’. 0.250’’. 0.750’’. 1.000’’.

What method is used to conduct static electricity in Fiberglass and Kevlar?. Braid aluminum wire embedded in the fiber. Carbon powder brushed on the surface. Copper foil taped externally. Static wicks bonded only to the paint layer.

What are the determining qualities when examining wood?. The cut of the wood Slope of the grain Number of Growth Rings. The color variation across the surface The weight difference between end and edge grain The hardness changes when tapping the wood. The moisture stain pattern on the surface The color variation caused by sunlight exposure The hardness difference between earlywood and latewood.

What is the minimum grain count (growth rings) per inch in softwoods?. 6 rings per inch. 4 rings per inch. 10 rings per inch. 2 rings per inch.

What is the difference between Laminated Wood and Plywood?. Laminated Wood: two or more layers of wood bonded with the grain running Parallel Plywood: Wood layers bonded with the grain direction at a 90° angle. Laminated Wood: layers bonded with alternating 45° grain, Plywood: layers bonded with parallel grain only. Laminated Wood: uses cross-laminated softwood strips, Plywood: uses single-direction hardwood veneers. Laminated Wood: grain runs diagonally for added torsion strength, Plywood: grain runs longitudinally in all plies.

What is the most water-resistant glue used in wood structure repairs?. Resorcinol Glue. Polyvinyl acetate adhesive. Casein glue. Animal hide glue.

What are the 3 important steps to form a durable structural bond?. Preparation of the wood surface prior to applying the adhesive Utilization of a good quality aircraft-standard adhesive Performing a good bonding technique. Using a low-grade adhesive without surface cleaning Applying excessive heat during clamping to speed up curing Sanding the joint after bonding instead of before applying adhesive. Relying solely on the natural resin content of the wood Applying excessive heat to force the adhesive into the grain Using exterior household glues without preparing the bonding area.

What are the 4 time-periods of adhesives. Pot Life,Open-Assembly Time, Closed-Assembly Time, Pressing Time. Mixing cycle, curing delay, resin soak period, clamp release time. Activation phase, bonding window, surface flash time, cooling interval. Adhesive warm-up time, pre-pressure stage, gel formation time, unload period.

What factor affects the cure rate of the glue?. Temperature. Humidity. Wood color variation. Surface roughness.

Most wood damage is caused by conditions such as …. Moisture Temperature Sunlight. Humidity Vibration Air pressure. Vibration Surface dust accumulation Improperly mixed adhesives.

What is important before inspecting wooden structures?. Check the moisture content of the wood, if too high, dry the wood structure. Verify the varnish color of the wood, if too dark, lighten the coating. Inspect the paint adhesion on the wood, if peeling, repaint the structure. Check the surface polish of the wood, if dull, apply a finishing coat.

What is a Compression Failure?. Damaged by compression of the main Load-carrying members, usually appears as fine line across the grain, replacement of the part. Internal separation of wood fibers caused by excessive twisting forces, usually showing diagonal marks along the grain, sanding of the area. Defect produced by prolonged moisture absorption, presenting as dark streaks parallel to the grain, ventilation of the structure. Damage created by surface abrasion on non-load-carrying sections, typically visible as shallow scratches, polishing of the surface.

What are the basic criterions of wood structure repair?. The repaired structure be as strong as the original structure and keep the original rigidity and aerodynamic shape. The repair must focus only on cosmetic appearance without considering load paths. The structure should be restored using any adhesive regardless of certification. The main goal is to minimize material use even if strength is reduced.

What are the most common wood spars?. Solid spar Laminated Spars Externally routed I-Beam Spar. Split spar Boxed spar Parallel flange spar. Webbed spar Built-up spar Hollow core spar. Scarfed spar Channel spar Stepped laminate spar.

What is the maximum number of repairs allowed on a single spar?. No more than two. No more than one. No more than three. No more than four.

How do you splice Routed I-Beam spars?. Much the same as solid rectangular spars and contoured to fit into the routed portion. Joined using standard butt joints without the need for reinforcement plates. Spliced by overlapping the flanges only while leaving the web unreinforced. Connected with simple metal brackets that attach directly to the outer spar caps.

What is a splayed patch?. For repairs of small holes in thin plywood skin. For covering large openings in thick composite panels. Used to reinforce internal structural joints in wing ribs. Applied to restore damaged load-bearing areas in laminated wood.

What is a surface patch?. Repair of hole in plywood skin by using the same material, grain in same direction. Used to reinforce internal rib joints without altering the main structure. Applied only to strengthen solid spars by adding parallel grain layers. Repair of fabric covering using doped cloth over the affected section.

What is a plug patch?. Flush patch in plywood skin, trim the damage to a round shape, put a doubler inside then glue the plug patch to the doubler. Used to reinforce large plywood sections by adding external plates over the damaged area. Method for repairing plywood by inserting a square replacement panel secured with perimeter fasteners. Technique that covers surface defects using overlapping veneer layers bonded across the damaged zone.

What is a scarfed patch?. Makes the least change in thickness or rigidity. Provides a thicker joint with increased stiffness. Adds multiple layers to reinforce the damaged area. Creates a raised surface that alters the aerodynamic contour.

Which type of Kevlar is most used in aviation?. Kevlar 49. Kevlar 21. Kevlar 38. Kevlar 65.

Where is Kevlar ideal in aviation?. On parts that are subject to high stress and vibration ex: Main rotor blades, hub assemblies. On components exposed mainly to low thermal loads such as cabin side panels and interior fairings. On areas requiring high electrical insulation like avionics access covers and instrument bay panels. On structures subjected mostly to aerodynamic drag only, for example wing-tip decorative housings.

Fiber composites is used primarily on?. Primary structural components. Secondary decorative panels. Nonload-bearing interior trim. Minor cabin insulation supports.

What is the main quality of Fiber Composites?. Compressive strength. Tensile strength. Impact resistance. Thermal stability.

What materials are the most used as Core in composite sandwich construction?. Honeycomb and Foam cores, Wood cores occasionally. Honeycomb and paper cores, cork cores occasionally. Foam and cardboard cores, fabric cores occasionally. Wood and plastic cores, rubber cores occasionally.

What material are foam cores made from?. Styrofoam. Polyurethane. Vinyl chloride. Polyethylene.

What material are wood cores made from?. Balsa Wood. Cedar wood. Pine wood. Spruce wood.

Ribbon Direction?. The direction in which a Honeycomb can be pulled apart, Pulling one side of the honeycomb that is perpendicular to the ribbon separates it, revealing the ribbon direction. The direction in which the cell walls naturally fold inward, pressing along the surface of the honeycomb causes the panels to collapse evenly, giving the appearance of uniform compression lines. The direction in which the honeycomb bends most easily, applying pressure along the face of the core forces the cells to distort sideways, indicating the primary flexing orientation. The direction in which the honeycomb twists under a rotational load, rotating the panel around its center highlights the axis where the internal structure offers the least torsional resistance.

How is Electrical Bonding done on Carbon composite?. A fine aluminum screen laminated under the top layer, may be used with carbon composites if sandwiched between two layers of fiberglass to prevent Galvanic corrosion. A thin copper mesh bonded over the outer laminate, typically applied without any fiberglass barrier to allow direct electrical flow across the composite surface. A stainless steel foil layer embedded near the mid-laminate, intended to spread current uniformly but not protected against galvanic interaction. A woven bronze screen placed directly beneath the finish ply, designed to dissipate static charges but not isolated from the carbon fibers.

How do you describe a Semi-monocoque structure?. Substructure of former and stringers. Substructure of spars and ribs. Substructure of beams and webs. Substructure of frames and panels.

Which method of NDT should not be used on composite?. Liquid penetrant inspection (Dye penetrant). Magnetic particle inspection (Magnaflux testing). Radiographic inspection using standard x-ray film. Ultrasonic inspection with conventional pulse-echo systems.

What are the advantages of a Double Flair connection?. Stronger connection, smoother and more concentric and provides a better seal than a single flare. Easier installation, simpler tube alignment and allows basic sealing with minimal preparation. Faster assembly, reduced tooling requirements and offers a standard fit for most basic flare joints. Lower manufacturing cost, decreased material usage and delivers an adequate seal for low-pressure lines.

Engine mounts can be made from?. Welded alloy steel tubing Formed sheet metal Forged alloy fittings. Cast aluminum brackets Pressed titanium panels Machined bronze joints. Extruded magnesium channels Rolled stainless strips Heat-treated copper mounts. Composite laminate frames Bonded fiberglass plates Layered kevlar supports.

What is the maximum depth accepted for a damaged wood spar?. No more than 1/4 of the spar thickness. No more than 1/2 of the spar thickness. No more than 3/8 of the spar thickness. No more than 2/3 of the spar thickness.

What to do when the aircraft is flying left wing heavy?. Wash-in of the left wing or Wash-Out of the right wing, or both. Increase the trim tab on the right wing or reduce the trim on the left wing, or both. Adjust the aileron balance on the left side or modify the hinge tension on the right, or both. Add additional weight to the right wing or remove weight from the left wing, or both.

What media blasting can be used in aviation?. Plastic, Glass Bead, Nut Shells, Cornhusk, Wheat Starch, Sodium Bicarbonate, Fruit Seeds. Steel grit, aluminum oxide, silicon carbide, iron shot, ceramic pellets. Sand Blast, copper slag, emery powder, steel beads, mineral grit. Carbon shot, metal abrasives, pumice grit, abrasive stones, powdered quartz.

Relief hole size for a box made from 2024 T3 0.050in thick sheet of aluminum with a 5/32 radius?. The relief hole should be 2 times the Bend radius: 5/16. The relief hole should be equal to the bend radius: 5/32. The relief hole should be 3 times the bend radius: 15/32. The relief hole should be 4 times the bend radius: 5/8.

A rivet snap should be?. Slightly larger than the rivet head. Just a bit smaller than the rivet head. Exactly the same size as the rivet head. Much wider than the rivet head surface.

How do you control the RPM of a Helicopter?. Twist grip arm. Collective lever grip. Foot pedal lever. Pilot-controlled twist knob.

What speed should you use when drilling Stainless Steel?. 300 to 1000 RPM. 3000 to 5000 rpm. 1200 to 1500 rpm. 1500 to 2000 rpm.

How to weld an Anchor that supports heavy loads on a tube?. Slot the tube, insert the anchor, weld on both sides of the tube. Drill a small pilot hole, insert the anchor, and braze lightly around the tube. Clamp the anchor externally to the tube and apply a single continuous weld bead. Place the anchor over the tube end, heat the joint, and fuse with a surface fillet weld.

What is the AC 43.13-1B for?. Gives specifics data for repairs approved by Transport Canada. Provides only general cleaning procedures for aircraft surfaces. Gives information exclusively about turbine engine troubleshooting. Contains guidelines only for aircraft upholstery installation.

What happens when you rework a dent on a non-thermic treated tube?. The reworked area will be stronger (Cold Work). The reworked area will become brittle and prone to cracking. The reworked area will weaken significantly after smoothing. The reworked area will lose alignment and require full replacement.

On a tube rivet layout, what is the distance between the rivets?. 45°. 30°. 60°. 75°.

What is the pitch for rivets on a tube repair?. 3D. 2D. 4D. 5D.

What is applied on fiber to increase its resistance?. Matrix (Resin). Hardener (catalyst). Protective coating. Surface primer.

Woods mostly used for aircraft Plywood?. African mahogany and American Birch. Philippine mahogany and canadian spruce. Okoume hardwood and northern poplar. Douglas fir and western hemlock.

What is Chrome Molybdenum?. 4130 steel. A low-carbon steel. A nickel-chromium alloy. 1045 steel.

What material is used for tubular structure?. 4130. 2024. 5056. 1000.

How do you verify the Anodization of a part?. Ohmmeter to check for electrical conductivity, Anodize= Zero conductivity. Use a magnifying glass to observe the surface color change of the oxide layer. Scrape a small area to see if the base metal becomes shiny under light. Check for slight magnetic attraction which indicates the coating has worn off.

How is electrical conductivity done in composite?. Aluminum screen bounded under the first layer. Copper mesh bonded beneath the surface layer. Bronze foil laminated under the initial ply. Steel gauze installed below the top laminate.

What is the ratio of Resin/Fiber?. 60% Fiber 40% Resin. 55% Fiber 45% Resin. 65% Fiber 35% Resin. 50% Fiber 50% Resin.

How do you detect water in composite?. X-Rays Laser Holography Acoustic emission testing. Ultrasonic inspection Infrared thermography Visual borescope inspection. Infrared thermography Microwave interferometry Ultrasound backscatter analysis.

How do you remove water from composite?. With a Vacuum bag setup, the combination of negative pressure, bleeder, and Heat blanket. By using compressed air only, directing airflow across the surface without applying heat. By leaving the composite exposed to sunlight until evaporation occurs naturally. By applying a cold air blower around the structure allowing moisture to dissipate slowly.

Which system pressurize the fuselage?. Compressor bleed air. Hydraulic pump air. Cabin circulation fan. Fuel boost pump air.

What makes the air go trough the pneumatic system?. Compressor bleed air. Engine cooling air. Environmental control flow. Turbine discharge flow.

Which methods are used to detect ice on an aircraft?. Visual Detection Optical Detection Electronic Detection. Thermal detection Infrared sensing Wing vibration monitoring. Pressure switches Cabin airflow sensors Fuel temperature probes. Ultrasonic scanning Hydraulic flow indicators Magnetic field detectors.

What is a Stressed-Skin Structure?. Formed without a truss frame, more streamlined shape, weight reduction because the skin carries the structural loads. Built around an internal truss frame, designed for heavy reinforcement, reliant on ribs for load support. Uses thick external panels, shaped with minimal contouring, depends primarily on bulkheads for strength. Constructed with rigid internal beams, focuses on maximizing stiffness, transfers loads mainly through the substructure.

What is a Monocoque Structure?. Stressed-Skin structure, lightweight, can fail if subjected to relatively minor dents or crease. Reinforced-panel layout, moderate weight, relies on numerous internal fittings for load support. Load-sharing shell design, heavier build, maintains shape only through closely spaced bulkheads. External-frame construction, increased rigidity, depends primarily on ribs and spars for strength.

What is a Semi-Monocoque Structure?. Skin fastened to a sub-structure or skeletal framework, which allows the loads to be distributed between the structural components and the skin. Skin formed as a single load-bearing shell, providing rigidity with minimal internal structure, resulting in low resistance to localized impacts. Frame constructed entirely of longitudinal members, which carry the primary stresses of the aircraft and support non-structural exterior coverings. Structure relying on external bracing and tension wires, allowing the internal members to handle compression loads while the fabric covering adds no strength.

What are the main components of a Semi-Monocoque’s substructure?. -Longerons -Stringers (Smaller Longerons) -Formers (Frame) -Bulkheads (Formers that also serve as compartment walls). -Longerons -Stringers positioned diagonally -Intermediate ribs for airflow control -Bonded panels acting as temporary bulkheads. -Primary spars running along the skin -Secondary stiffeners arranged crosswise -Circular frames supporting localized loads -Removable bulkhead inserts for inspection access. -Main longitudinal beams -Light auxiliary stringers for minor support -Curved formers shaping the outer contour -Pressure bulkheads separating nonstructural zones.

What is Maneuverability?. Characteristic of an airplane in flight that causes it to return to a condition of Equilibrium or steady flight after it is disturbed. Ability of an aircraft to maintain altitude without requiring continuous control input. Quality of an airplane that allows it to resist any change in direction or attitude. Property of an aircraft that reduces its sensitivity to pilot commands and external forces.

What is Controllability?. The capacity of an airplane to respond to the pilot’s control inputs. The ability of an aircraft to maintain stable flight without pilot input. The capability of an airplane to resist any change in direction. The tendency of an aircraft to remain level regardless of control movement.

What are Trim Tabs?. Small movable portions of the trailing edge of a control surface controlled from the cockpit to alter the camber of the surface and create an aerodynamic force that will hold the surface deflected. Normally used on the elevator to permit adjustment of the tail load so the airplane can be flown hands-off at any given airspeed. Small hinged sections attached near the leading edge of the control surface that automatically adjust to reduce aerodynamic drag and stabilize the aircraft during cruise flight. Minor adjustable panels located on the underside of the control surface designed to relieve structural loads and improve smooth airflow over the airplane at high speeds. Short auxiliary surfaces mounted ahead of the main control surface used to increase lift, modify airflow distribution, and maintain directional stability during takeoff and landing.

What are balance tabs?. Used to decrease the control forces, same tab as the trim tab, Control rod for the balance tab is connected to the fixed surface of the same side as the horn on the tab, if the control surf ace is deflected upward, the connecting linkage will pull the tab down. Used primarily to add rigidity to the control surface, the tab moves in the same direction as the surface to increase its stiffness and prevent flutter during high-speed flight, and it is normally connected directly to the main spar for additional support. Installed to modify the aerodynamic balance only at low speeds, the tab deflects simultaneously with the control surface to create extra drag, and its linkage is attached to an auxiliary hinge located behind the trailing edge. Designed to provide damping during rapid control movements, the tab operates independently from the pilot’s inputs to reduce vibration, and it is usually mounted on a separate bracket positioned near the outboard section of the control surface.

What are Anti-Servo Tabs?. Used on all-movable horizontal tail surfaces (Elevators) the tabs attempts to streamline the control surface to decrease sensitivity, moves same direction as the surface. Used to limit the movement of the control surface by creating resistance that centers the surface after deflection, operating opposite to the applied input to increase overall stability of the aircraft. Installed on the trailing edge of the surface to provide additional damping, the tab moves opposite to the surface to reduce oscillations and prevent overcontrolling during high-speed flight. Designed to increase control pressure by forcing the control surface toward neutral, the tab moves opposite to the pilot’s input to avoid excessive sensitivity of fully movable tail units.