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  1. Payyan1234

    LARGE CUTOUT ON FUSELAGE SKIN

    Thanks Guys, I could get hold of the Niu Third edition, which is a fantastic reference.
  2. Payyan1234

    LARGE CUTOUT ON FUSELAGE SKIN

    Thanks for all replies. I had no access to the SRM, But now access to Bhrun and Niu and referring it. The repair will be endorsed by a Part 21J EASA design approval.
  3. Payyan1234

    Aluminium Machining and Properties

    Sorry about the late reply, Fiberglass/hydro-forming option is on my back pocket. Still waiting from the CNC machining supplier about the possibility and cost. The case is protruding out from the fuselage skin and has good amount of contours to make it aerodynamic . It is a restricted part ...
  4. Payyan1234

    LARGE CUTOUT ON FUSELAGE SKIN

    The cut out need to be remain same. It is a flare dispenser equipment exerts a out of plane loading ( equivalent Blast/statc load) of 8kN (1800 lbf) and that is the main driver. The load should pass from equipment casing 4 steel bolt ( 2 each shorter side of the cutout) to the skin /...
  5. Payyan1234

    LARGE CUTOUT ON FUSELAGE SKIN

    I have to create a Large cutout on FAR 23 Airplane Fuselage (Unpressurised ) see attached figure. Since it is a large out of plane loading, decided to frame it up. (design load) * A Doubler, wedge between the skin ,frame and stringers * A STIFFENING ANGLE between the frame to Transfer the...
  6. Payyan1234

    Aluminium Machining and Properties

    Thanks all..It sounds like a wrong decision to machine it..
  7. Payyan1234

    FAR/EASA 25 Compliance Matrix

    I used compliance matrix check list AC 23-24 for small aircraft
  8. Payyan1234

    Aluminium Machining and Properties

    Sorry , It is not duplicating a part . It is an avionics modification , where the casing is little complicated to form in sheet metal, so decided to do CNC machining.
  9. Payyan1234

    Aluminium Machining and Properties

    Our team is thinking of machining a 0.063" thick casing/fairing from an aluminium bar ( 6.5" thick bar) due to complex shape. Similar location mod on Aircraft all used 0.063 2024-T3 sheet metal. * Is it possible to Machining this to such a small thickness ? * Which Aluminium grade and what...
  10. Payyan1234

    STRESS ANALYSIS

    Thanks for all suggestions Vmo is 170 kts. The drag force calculated for the profile is less.But how do we calculate the Total drag for comparison?. We are communicating with the people who making findings of compliance. No immediate responses.. Following this assumption.. "Unpressurised...
  11. Payyan1234

    STRESS ANALYSIS

    Excited to read everyone replies, Yes I am including the gust inertia for analysis. Need to speak the supporting company for finding of Compliance Presently Convenient Locations have choosed for Installation ( to Avoid existing avionics and structures) Decided to put playcard to avoid Abuse...
  12. Payyan1234

    STRESS ANALYSIS

    RB, Thanks for the reply, The equipment is a sensor weigh 2kgs and mounting on fwd skin near to door ( centre of frames and stringer) and another at aft skin near empennage (close to stringer) . Our company is creating all the Technical data package and endorsed by a Part 21J approved agency...
  13. Payyan1234

    STRESS ANALYSIS

    Hi, I am new to the Aircraft Modification world. I have given a task to attach some Avionics equipment (only 2Kgs) to a small airplane (Twin Otter) fuselage, using appropriate mounting brackets. The process I am following is * Using Type certificate Found the Inertia requirements. ( Do I...
  14. Payyan1234

    Configuration management Plan in Design

    Hi, Anybody knows or have template on "Design Configuration management" . I have been asked to create a template for it for an Aircraft modification project. Thanks
  15. Payyan1234

    Thermal stress in Dissimilar joint

    RPstress, I have attached picture for more clarification. The equipment (Aluminium alloy (0.125" thick base plate) attached to the sandwich mounting plate via 4 steel screws (#10) and an aluminium doubler plate and sealed/bonded at the edges. To assess the strength due to high temperature...
  16. Payyan1234

    Thermal stress in Dissimilar joint

    RPStress, Thanks for the reply. I assuming the sandwich has zero TEC, therefore top and bottom doubler plates expands and restricted by the sandwich panel in bearing.
  17. Payyan1234

    Thermal stress in Dissimilar joint

    Hi, I have a question regarding joint strength of an equipment , which is placed on a honeycomb core and backed by a doubler plate. Please see the attached picture. The equipment sees high temperature around 102 degrees. I have analysed the joint by calculating the delta displacement from...

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