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Thread: Module 6 - Delamination in composites

  1. #41
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    Default Re: Module 6 - Delamination in composites

    What do you mean?
    Dip me in chocolate and throw me to the lesbians....



  2. #42
    Join Date
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    Default Re: Module 6 - Delamination in composites

    Quote Originally Posted by Dunny View Post
    talking of the CAA, have you seen their latest piss take, a failed licence application now costs you 170....

    robbing barstewards.
    Good. Will stop no-hopers who don't meet the minimum requirements trying their luck just in case and clogging up the system.
    I'm a very persuasive person. I can convince myself of anything.

  3. #43
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    Default Re: Module 6 - Delamination in composites

    Quote Originally Posted by Doc View Post
    Good. Will stop no-hopers who don't meet the minimum requirements trying their luck just in case and clogging up the system.
    That's Billy's renewal screwed then.........




    The voices in my head may not be real, but they have some good ideas!

  4. #44
    Join Date
    Sep 2001
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    Default Re: Module 6 - Delamination in composites

    "Refunds – rejected or withdrawn applications
    There have been a number of applications for the issue of an AML or for additional privileges to be added to an existing AML which have
    been rejected by the CAA due to, for example, lack of experience criteria. This has resulted in the CAA refunding 100% of the application
    charge even though time has been incurred to review the application in order to reach the rejection decision.
    The CAA is required to recover its costs from those that have caused those costs to be incurred. Therefore, for applications received from 15
    September 2016 the CAA will be deducting 170 to recover the average costs of its application review in respect of those applications that the
    CAA has rejected or where the applicant has withdrawn his/her application before the CAA has completed its review.
    This deduction will be associated with applications in respect of AML activities under the UK Official Record Series 5 No. 310 Personnel
    Licensing Scheme of Charges para 13.1 Table 58 Refs a), c) i), d) and/or e). This action is in line with the CAA Charges Waiver and Refund
    Policy dated 1 September 2016."
    Eat more pies....M0NCL


  5. #45
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    Default Re: Module 6 - Delamination in composites

    Reading through ORS5 No 310 it would appear they charge a man-hour rate of 170.

    Not sure what planet they are on, but its certainly not this one....
    Eat more pies....M0NCL


  6. #46
    Join Date
    Apr 2005
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    NZ
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    314

    Default Re: Module 6 - Delamination in composites

    Quote Originally Posted by Engineer View Post
    ......On the certificate pass or fail it has a section called 'knowledge deficiency report' which will list subsections of that module you got wrong.
    This is true of NZCAA.
    Helps people review the cheat sheets they pass on to their colleagues.
    Romania has much to learn.

  7. #47
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    Default Re: Module 6 - Delamination in composites

    Quote Originally Posted by kinger View Post
    This is true of NZCAA.
    Helps people review the cheat sheets they pass on to their colleagues.
    Romania has much to learn.
    I will need help to make the connection.

    Haven't heard of Romania in aviation since the Rom-BAC thingy ended.
    I love this job

  8. #48

    Default Re: Module 6 - Delamination in composites

    This question is worded very badly..... However looking at the 3 possible answers I'd say:

    The thicker the composite laminate the stronger it is - I'd expect to see the smallest delamination due to impact damage to a thick panel with the 3 answers available.

    Because a composite panel is curved does not necessarily mean it has reduced damage tolerance in comparison to a flat panel, fuselage, wing leading edges etc - all just as strong as a flat composite laminate.

    A thin panel however is the weakest of the 3 options, and an impact to the thin panel would cause the largest delamination.

    Hope this helps.

    Ian

  9. #49
    Join Date
    Jul 2004
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    Europe
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    Default Re: Module 6 - Delamination in composites

    Quote Originally Posted by oorian18 View Post
    This question is worded very badly..... However looking at the 3 possible answers I'd say:

    The thicker the composite laminate the stronger it is - I'd expect to see the smallest delamination due to impact damage to a thick panel with the 3 answers available.

    Because a composite panel is curved does not necessarily mean it has reduced damage tolerance in comparison to a flat panel, fuselage, wing leading edges etc - all just as strong as a flat composite laminate.

    A thin panel however is the weakest of the 3 options, and an impact to the thin panel would cause the largest delamination.

    Hope this helps.

    Ian
    No, Ian, it doesn't help. Because the original poster came back with the update from his exam in which option a) Curved was deemed correct.

    I enjoyed reading through the thread, though.
    Eez kut, yez..

  10. #50

    Default Re: Module 6 - Delamination in composites

    The lesson learned here today was read all the posts before you comment!

    Assuming it must be a large surface area impact that’s only making contact with a small area of the curved part then eh, not a very well worded question.

    On the plus side if I now get asked this on module 6 exam I’ll get it correct, every cloud and all that!

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