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MNLiaison Thanks for the valuable feedback. Do you have any idea how I can get a PDF copy of the AFGS-87221A document? Thank you.

Thanks rb1957, I have a copy of MIL-A-8865B but not MIL-A-008865. The reason for this verification is because the load factors for the litter installation for the MIL-A-008865 is supposedly greater than those specified in MIL-A-8865B. I currently do not have documentation to prove this because...

Does anyone knows if MIL-A-8865B is the superseding document for MIL-A-008865? There are no history for MIL-A-008865 except that it is cancelled with no replacement. Anyone out there have a copy of MIL-A-008865? Thank you Regards aeu

Crackkilz, 100G seems a lot to be applied for a load factor. Do you have a reference for the 100G load factor or is that a guideline that you have been using? rb1957, the FAR crash loads were exactly what I had in mind. But I was thinking of other load factors which might be more critical. I...

To all who have analysed or certified antenna installations in the Radome area, what are the typical crash load factors that were used? Is there also any references that defines those crash load factors? Regards AEU

Sparweb, you might want to try NACA 733. Most probably you will find what you are looking for. That reference was called out from NACA TN 3781 and Bruhn C5 reference page references TN 3781. Good luck.

Thanks Sparweb and BATman2 for your comments. I think the real argument here is; that if the imperfection (non-visible) is actually acceptable. I agree wholeheartedly with Sparweb's statement of restoring equivalent strength and no degradation of service life. The problem I posed initially was...

TO answer Batman 2, at times, it is not economical to get a new sheet due to time constraint unless numbers can be shown to substantiate the damage. As indicated by Sparweb, there are no conclusive method or 100% information to come to a perfect "engineering" decision. In item (b) of Batman 2...

Consider this, a skin panel is sitting around waiting to be loaded on the assembly jig. However, it is found that approximately 1" x 5" of the edge has wrinkled due to mishandling of the skin panel. After cold working, and the wrinkling has been straighten, a conductivity test on the damaged...

For all liaison stress engineers and DERs out there, here is a detail which I never got any answer to, 1) Does a freeze plug install in a parent material has to be concentric to the blueprint rivet hole (i.e. equal wall thickness on all sides), if not, then is there a reference that tells or...

Is the crack in the direction of the longeron or perpendicular to the longeron direction? Is the crack at the top or the horizontal flanges of the hat section? By your description above, I would recommend nesting a blueprint splice hat section long enough to distribute the load back into the...

Recently, I have been asked of the maximum allowable of material to be removed from a fastener head for a countersink rivet to be considered structural. As an example, A NAS1097AD7 rivet in a 0.040 inch thick 2024-T3 materia, the maximum depth of countersink using Boeing guideline is 66% of...

Sheet metal or extrusions of parts may be cold-formed in any temper but preferabably in -W condition or -O condition. This is covered under SRM 51-30-01 which refers you back to BAC 5300 (forming and straightening of mettalic alloys). If formed in -W or -O condition, the part has to go thru a...

Hi Baja, if you are referring to minor/major modification in terms of incorporating new design, I believe you are referring to an alteration to the original type certificate. Thus, it is required per FAR 23 to obtain approval from the OEM. The only reason to obtain approval from the OEM is that...

Can anyone out there help me with the following fastener allowables (i.e shear strength, tensile strength) a) NAS 623 b) NAS 603 c) MS 35206 d) NAS 514 e) NAS 602 f) NASM 27039 If at all possible, does anyone know where I can download the spec sheet. Thanks in advance