1. Sounds like You need a Boeing, Lockheed, Cessna, etc… liaison handbook, and/or design manual(s)… which have all the info You are looking for… and MUCH MORE about aero fastening. Good luck.
2. If this (1) is NOT feasible, then I recommend the following basic documents for starters… most easily procurable thru the web at say IHS or the FAA AC website. Some may have to be purchased at nominal cost (of doing business).
MIL-HDBK-5 (old) or MMPDS (current) metals and fastener data and [any version].
AN3—20 (old) or NASM3—20 (current) base spec for AN3-X to AN20-X Bolts
Note: I recommend using newer generation hardware such as NAS6203—6220 for a number of reasons, but most importantly higher strength, tighter tolerances and OVERSIZES are available [for “aw-sh*ts].
AN960 or NAS1149 for washers
AN310, AN315, AN316, AN320 [Or equiv NASMxxx], NAS679, etc Nuts
FF-N-836 or MIL-N-25027 [NASM25027] procurement specs for Nuts
AS567 Safetying Hardware, General Practices
MIL-B-6812 (old) or NASM6812 (current) procurement spec for AN bolts.
NAS618 standard fastener dimensions and hole tolerances
MIL-STD-403C Rivet and Screw [and low-grade bolt] Installation spec
AC43.13 for acceptable maintenance and repair techniques. [FAA website]
ACs for general maintenance practices [specifically need procedures for Nut/Bolt Installation]
3. How does this all work to insure a fully analyzed Bolted joint Installation??? As follows..
3.1 MIL-HDBK-5 Para 8.1.5 discusses how to analyze for “standard bolts” [not shear head, because reduced fasteners may fail the head in pin bending when shear-loaded... think-about-it].
3.2 MIL-HDBK-5 Table 8.1.5(a) defines absolute shear strength of generic “bolts”, based on known [heat treat] shear-stress capability. ANXX bolts are roughly 75-KSI and NAS62XX Bolts are 95-KSI [approx values ONLY]. NOTE: the NASM3—20 spec actually provides max rated strength for each bolt size. Example form this table for a 0.250-In diameter 75-KSI shear bolt:
P (shear-ult) = 3680-lbs
3.3 MIL-HDBK-5 Table 184.108.40.206. Unit Bearing Strength of Sheet and Plate in Joints With Threaded Fasteners or Pins; Fbru = 100 KSI. This defines bearing-tear-out for “generic 100-KSI material [try finding it]. The intent is to match fastener [hole] diameter and sheet thickness to determine a “shear ultimate”… based on 100-KSI material. This number is then factored up/down based on the FBru of the “real-world” alloy being analyzed. Example [MIL-HDBK-5J, Table 220.127.116.11]:
0.250-In Dia Hole thru 0.10-thick material (at 100-KSI Fbru) = 2500-lbs bearing force.
For 7075-T6 sheet, 0.10-thick, 2-D edge distance, from table 18.104.22.168(b1), Fbru (A) = 156-KSI.
Therefore max allowable bearing load for this sheet metal is 156/100 x 2500-lbs = 1.56 x 2500 = 3900-lbs
3.3 Comparing shear ultimate VS material Bearing ultimate determines MAX allowed P (shear) at this location. Example [for the 0.250-dia bolt in 0.100-thick sheet]:
Bolt Shear Ult = 3680-lbs
Hole Bearing Ult = 3900-lbs
Therefore, Ult allowable load at this hole is the lesser of these loads = 3680-lbs [bolt fails slightly before the hole fully-tears-out, not a bad joint if I do say-so].
Note: this analysis presumes a "standard head bolt" with a shear-rated nut [W/WO a washer].
Regards, Wil Taylor