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  1. 737eng

    Adding 1.15 to margin of safety for repairs.

    Per my view and what I require for a repair that I review and approve as a Static Strength DER- Per 25.625 if you are using tested allowables to design your joint than you don't need to utilize the 1.15 factor. If you are using computed allowables (i.e. Fbru*d*t) then you have to include the...
  2. 737eng

    Structural repair question?

    If the repair is statically acceptable and the durability is adequate, then it is OK. I usually try to get a minimum of three rows for fastener load distribution. However, compliance to the FARs is what you are after, as long as you check the durability of the two rows and implement...
  3. 737eng

    FCBS for DC10-30

    As an operator you need to know what structure is FCBS. Yes, the DAHs will provide you with a mtc program that will cover the damage tolerance requirements of the original OEM and/or STC structure. However, you also have to determine if existing/future repairs/mods require further supplemental...
  4. 737eng

    FCBS for DC10-30

    Not only is there a cost associated with the FCBS list but there is also going to be a cost associated with the Compliance Document/Repair Evaluation Guideline. I am not saying that you need this data to put your OIP together, but it would sure make it easier. If your fleet is small enough...
  5. 737eng

    From Airline Structure Eng. to Stress Eng.

    I made the jump (at an older age) and beware the grass is not always greener. I thoroughly enjoy doing the analysis and I have learned a lot, especially about Fatigue and DT, however, an analyst sits behind a computer in a cubicle all day, the whole job is done in a cubicle. I miss going down...
  6. 737eng

    oversize bolt for 5/16-24 bolt repair

    Going with a Hi-Lok would provide for a nice assortment of oversize fastener options available and a very good solution, just check your hole tolerances to ensure you are maintaining the fit that you desire. Another option would be to change to another material bolt, perhaps a Ti NAS6805 or...
  7. 737eng

    Pitch Distance

    If it is a "fitting" and the fitting has an offset load the actual shear stress could go up per fastener due to the eccentric load acting on the closer spaced fasteners.
  8. 737eng

    Inter-rivet buckling

    40818, Was the answer too conservative or did testing show that the panel buckled between fasteners prior to what was calculated?
  9. 737eng

    Hole edge distance

    For a joint you have to check: Shear strength of fastener Bearing of material Tear-out of material due to short edge margin Tear-out between fasteners Tension failure Transitional failure (head popping or bending, pull through, everything that can only be tested) If you have an edge margin...
  10. 737eng

    Question on the definition of Limit Load and service life

    Well, I finally was able to pull quotes directly out of AC 120-77 and think that I at least got someone's attention on the documentation and substantiation requirements for a repair. In lieu of trying to "dumb" down my presentation, I just stuck with the Regs and stated that all repairs, minor...
  11. 737eng

    Question on the definition of Limit Load and service life

    Thanks again for your responses. I think we are all in agreement that the structure has to be shown to meet limit and ultimate loads when either repaired or damage is reworked and let go. Compliance has to be shown by some sort of engineering substantiation, what that engineering...
  12. 737eng

    Question on the definition of Limit Load and service life

    I am trying to prove that you have to accomplish an analysis to show that it can carry the limit and ultimate loads, even for Minor repairs or damage. To me stating that the repair or damage is minor and just stating that the "aircraft flew in that way" or "we see that damage all the time and...
  13. 737eng

    Question on the definition of Limit Load and service life

    rb, thanks for your response. My interest is to disprove the old mentality of "it flew in that way, it will fly out that way" by proving that the aircraft most likely did not experience or more critically will not be able to sustain the limit load (and thus is not in compliance). I want to...
  14. 737eng

    Question on the definition of Limit Load and service life

    I know that Limit Load is the maximum load anticipated on the aircraft or component during its service life. My question is what is the definition of service life and how it relates to limit load. I was taught that a limit load is only to occur once in the life of a fleet (i.e. 1 aircraft out...
  15. 737eng

    'Enthusiasm' or 'Knowledge' ?

    I think that personality (which could include enthusiasm) and smarts (which may not be actual knowledge of actual job) are the key to hiring. If you hire a smart person who fits in with your current culture, you can easily teach them the job. However, you can hire the person with the most...
  16. 737eng

    Johnson-Euler Buckling

    I believe that Johnson-Euler is in Flabel or at least mentioned.
  17. 737eng

    Antenna stress and DTA example

    I took the class, it's worth the trip, don't plan on trying to keep up with work back at the office when you are there. Method taught to determine the stresses is a bit conservative in my opinion, but it is valid method that will provide a very conservative inspection threshold and interval...
  18. 737eng

    Antenna stress and DTA example

    U of W is offering a 1 week course which focuses on just this, DTA for antenna installs. Contact the SEA ACO or the U of W extension to get details and go. It is a great class and believe me you won't have any time to do any sight seeing while you're there!! Also recommend utilizing Kamy...
  19. 737eng

    How big a pay cut would you take?

    Just took a 5% paycut. What ticks me off the most is that I heard it on the news before I heard it from the company. 2nd thing that ticks me off is that all the press releases and memos state that all salaried employees are taking a 5% pay-cut, which in my opinion makes it sound like we are...
  20. 737eng

    A310 Fuselage Cross Section to find Inertia and Centroid Values

    I remember coming across something by Broek that detailed how to accomplish what you are doing. Good read if you can find it. I would recommend picking up Broek's "Practical Use of Fracture Mechanics" and "Fatigue of Structures and Materials" by scijve (sp?)

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