Attachment 1 - Composite panel Specification Sheet.pdf

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Amendment 2 - FA302026Q0081 357TRS Composite Course Panels - Extend Quote Due Date Until Tuesday, 18 August at 2pm, CDT, and Post Updated Amendment 1 -SOW.
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FA302026Q0081
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This is a specification sheet for the manufacture of composite training panels used in the ASM Supplemental Advanced Composite Repair course (Panel part number/NSN: 9390-CO-MPO-SITE).

The panel specifications require a sandwich construction composite measuring 18" × 18" with 1" thick core and +/- 0.125" dimensional tolerances. The exterior skin consists of 8 plies of quasi-isotropic unidirectional graphite epoxy tape (Hexcel T2C190-12-F263-2 or equivalent to Boeing Material Specification BMS8-212 TY3 CL1 GR190) with balanced ply orientation [(+45/-45/0/90)][(90/0/-45/+45)]. The core material is fiberglass/phenolic honeycomb (3/16-4.0, 1" thick HRP) with continuous height and no splices or butts, featuring uniform transition angles with 1/4" radius edges. The interior skin comprises 4 plies of Kevlar 49 Aramid prepreg in crowfoot cross-ply lay-up (Cytec MXM-7880-/285 or equivalent to BMS8-218 ST285). Internal and external skins must be bonded to the core using film adhesive equivalent to BMS5-154 TY2 CL1 GR5. All surfaces must be wrinkle-free with no seams or butted joints. The panel dimensions are specified as 18" width by 14½" to 15½" length on the interior skin side.

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File Type Posted
Updated Attachment 1 - Composite panel Specification Sheet-2.pdf PDF
Attachment 2 Provisions and Clauses.pdf PDF
Attachment 3 RFO Combo - Working.pdf PDF

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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

File details come from the government source that posted it. Updated .