General Assessment Cont 2 - Section I. Aircraft Structure Damage Assessment Prodecures Aircraft Sections Small cracks will enlarge under con- a detail assessment can be made tinued loading, particularly when and the damage can be repaired by BDAR located at the edge of a hole. DA Form Mark the flattened cross section. The length of damaged structure using grease pencil or the remaining effective cross section paint.
Use the labeling scheme shown in is still capable of supporting a load. Damaged Cross Section Figure Measuring Skin Panel Damage Measuring Damage in Webs and Panels Measuring Damage in Honeycomb Sandwich Panels Page 59 TM BD AIRFRAME The type, extent, and variation of b Repairs on damaged struc- damage under condition 3 does not per- tural elements that are better than mit categorization of the many com- condition 1 may be deferred except for binations of damage.
The aircraft consists of three accomplished by the use of intercoastals main sections. The forward cabin sec- and two aluminum redistribution bulkheads. The horizontal stabilizer tion extends from the cockpit nose at is a standard spar-rib-skin riveted FS1 to the bulkhead aft of the passenger OH Helicopter Cockpit Fuselage Pylon Support Structure Sheet 1 of 5 Fuselage Pylon Support Structure Sheet 2 of 5 Fuselage Pylon Support Structure Sheet 3 of 5 Fuselage Pylon Support Structure Sheet 5 of 5 Aft Fuselage Structure Tail Boom Cowling and Firewalls Page 73 TM BD AIRFRAME 4 Three or more fasteners next Determine the priority of the to each other, which join a cap, various required repairs based on repair longeron, and stringer to the web, are time, difficulty of repair, resources sheared, pulled-through or missing.
Web Panels. Classify a skin or web panel as failed if any of the following 4 The panel is secured by mecha- conditions exist: nical fasteners.
Page 76 Table Page 77 Table Page 78 Table Page 80 Table Page 81 Table Page 85 Table Page 86 Table Page 87 Table Page 88 Table Page 90 Table Controls and drive- of a component. One NOTE method to create a complex curve in a Steel and aluminum are incom- normally straight angle or T - Profile patible materials and normally member is to place appropriate cuts and stop drill holes to allow bends, as require special precautions.
Typical Former Repair Sheet 1 of 2 Cutout in Damaged Skin Cut a piece of substitute stringer NOTE or stiffener to extend a minimum of six fasteners beyond the damage on each end. Stiffener can be placed on out- Use an angle, channel, or z-angle extru- side; Use several Cherry Rivets item 38, Appx C layers as necessary, and overlap onto skin well beyond damaged area. Typical Patch Plate Repair Remove sections of the aircraft skin Remove existing rivets and back drill containing the damage.
Do not cut cap holes in the patch plate if the area is or longeron, but cut off ragged ends, Repair of Damaged Bulkhead Flange Typical Combination Repair Sheet 2 of 2 If not, install rivets between existing rivets if space permits. Drill with No. Clean area with solvent. Landing Gear and Support Installation Figure Skid Tube Damage Zones Assessment Procedure Logic Clamp Repair Figure Fabricated Clamp The dures which have been developed.
O and FS T63 Series Engine Monitor TOT and N1 gauges for possible stall readings. Blocking of the air bleed valve will render the engine highly susceptible to surge which could NOTE Flex Line Tubing ID 0. Tape, Fiberglass or Duct Obtain a small piece of hose or item 51, Appx C tubing and insert the piece into the. Solvent, Naptha item 7, Appx C hole on the oil tank, Figure Record BDAR action taken.
Assemble reinstall. Apply sealant to all After sealant has dried, replenish edges. Put sealant or gasket material over. Section 1. Blade Latch 1. Pitch Link Blade Assy 2. Lever Retaining Bolt 3. Idler Link 4. Swashplate Assy Grip Mast Nut 5. Link 6. Collective Lever Hub Assy Oil Lubricated shown 7. Inner Ring Hub 2.
Pitch Horn 3. Blade 4. Assessment Procedures Smooth damage; remove all rough. Army Green Tape, Maximum Width edges. Fiberglass or Aluminum Wafers completely around blade where tape is. When entire blade and over the repaired area. Wrap exact number of tape wraps on opposite side at approximately same span location. TB Installation and removal instructions for the trimble trimpack global positioning system gps Special mission kits on OHc round glass Kiowa helicopters.
TB Installation and removal instructions for the trimble trimpack global positioning system gps Special mission kits on OHa Kiowa helicopters.
TB Announcement of approval and release of nondestructive test equipment inspection procedure manual tm , technical manual aviation unit maintenance avum and aviation intermediate maintenance avim manual nondestructive inspection procedures for OH Kiowa helicopter series.
TB Announcement of approval and release of nondestructive test equment inspection procedure Manual for. TM Technicalman aviation unit maintenance avum and aviation intermediate maintenance avim Manual nondestructive inspection procedures for OH Kiowa helicopter series. Government works are covered by 17 USC paragraph You must be logged in to post a comment. Skip to navigation Skip to content.
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