Updated Attachment 1 - Composite panel Specification Sheet-2.pdf
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- Solicitation number
- FA302026Q0081
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This document is a specification sheet for the manufacture of composite training panels used in the ASM Supplemental Advanced Composite Repair course, identified by part number/NSN 9390-CO-MPO-SITE.
The panel specifications require a sandwich composite construction measuring 18" x 18" with a 1" thick core and +/- .125 inch tolerances on overall dimensions. The exterior skin (Side 1) consists of 8 plies of quasi-isotropic, balanced ply unidirectional graphite epoxy tape in a layup of [(+45/-45/0/90)][(90/0/-45/+45)], using Hexcel number T2C190-12-F263-2 or equivalent to Boeing Material Specification BMS8-212 TY3 CL1 GR190. The core material is fiberglass/phenolic honeycomb (HRP-3/16-4.0) with 1" continuous height containing no splices or butts, featuring uniform transition angles with 1/4" radius edges. The interior skin (Side 2) comprises 4 plies of Kevlar 49 Aramid prepreg in crowfoot cross ply layup, using Cytec number MXM-7880-/285 or equivalent to Boeing specification BMS8-218 ST285. Internal and external skins must be bonded to the core using film adhesive equivalent to BMS5-154 TY2 CL1 GR5, with METLBOND 1515-4M noted as an acceptable substitute adhesive. All surfaces must be wrinkle-free with no seams or butted joints.
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SPECIFICATIONS FOR MANUFACTURE OF COMPOSITE TRAINING PANELS, Panel Composite, Panel part number/NSN: 9390-CO-MPO-SITE
(Panels are used by ASM, Supplemental Advanced Composite Repair course)
See Notes I - 4 for materials requirements. Panel overall width and length dimensions +/- .125 tolerances.
I. Exterior skin 8 Plies, quasi-isotropic lay-up unidirectional graphite epoxy tape, Hexcel number T2C- 190-12-F263-2, or equal to (Boeing Material Specification) BMSS-212 TY3 CL! GR190. Balanced ply orientation [(+45 / -45 / 0 / 90)] [(90 / 0 / -45 / +45)]
2. Fiberglass/ Phenolic honeycomb core, 3/16-4.0, 1" thick HRP, (height I" continuous, with no splices or butts) HRP-3/16-4.0. Transition angles to be uniform.
3. Interior skin Kevlar 49 Aramid prepreg. Cytec number MXM-7880-/285, or equal to BMSS-218 ST285, 4 plies ( crowfoot) cross ply lay-up.
4. Internal and external skins to core, bond with film adhesive equivalent to BMS5-154 TY2 CL! GR5.
NOTE: All surfaces must be wrinkle free with no seams or butted joints.
18"
2 1/211 ....._ 1 11----Jiitr
1,4" Radius
Interior Skin Side Kevlar 49 Aramid Prepreg
14 1/2" 18"
Note 3
Note2 u.--- Note 1
:I Specification sheet/drawing for all specific design requirements.
Advanced composite training panel, composite FFP-Panel, Composite l" thick core XIS" XI 8".
Side 1 (exterior Skin), 8 plies BMS8-212 TY3 CL! GR 190 equivalent, balanced ply lay-up, {[(+45, -45, 0, 90)][(90, 0, -45, +45)]} Fiberglass/Phenolic Honeycomb Core 3/16-4.0, 1.0" Thick HRP.
Side 2, (Interior Skin) is Kevlar 49 aramid prepreg. Equal to Boemg spec BMSS-218 ST285, 4 plies ( crowfoot weave) cross ply lay-up. 2 sides with transition edges as per specification sheet with W' radiuses;
core height continuous, with no splices or butts. Skin to core bond with film adhesive equivalent to BMSS-
154 TY2 CL! GR5
1057727264C Highlight
Text1: ** NOTE-- METLBOND 1515-4M is an acceptable sub adhesive for item 4.
File details come from the government source that posted it. Updated .