Amendment 2 for Aircraft Panels.docx
DOCX document 222 KB Posted
- Attached to
- FY21 Aircraft Composite Panels Federal contract opportunity
- Solicitation number
- FA302021Q0016
View the file
Other files for this federal contract opportunity
| File | Type | Posted |
|---|---|---|
| Amendment 2 for Aircraft Panels.pdf | ||
| Amendment 1 Aircraft Composite Panels.pdf | ||
| New Combo - FY21 Aircraft Composite Panels.pdf | ||
| Attachment 1 Composite Panels Specifications.pdf | ||
| CLSExport_FA302027Q0016.pdf |
On GovTribe
Work with this file on GovTribe
- Download the original file
- Contacts named in this file
- Similar government files
- Ask GovTribe AI about this file
Text version
department of the air force air education and training command
June 23, 2021
82 CONS/PKAB
206 J Ave, Bldg. 1662 Sheppard AFB TX 76311-2746
SUBJECT: Amendment 2, Request for Quote: FY21 Aircraft Composite Panels
1. The Government response for received vendor questions are as follows. Please incorporate the following clarifications into the above referenced Request for Quote:
Q1) Why is splicing on the unidirectional prepreg not allowed?
A1) The composite panels are built 18" to allow multiple classes to accomplish repairs on the same panel. All of the prepreg graphite currently used for the schoolhouse, comes in 36" rolls. If 12" wide material has to be used by the manufacture, butt-splicing the material would be fine, as long there is NO OVERLAPPING of the material and the direction of the carbon fiber does not change for that specific area.
Q2) What are the specification limits on thickness of the prefabricated skins (either overall or CPT) or for the thickness of the honeycomb core?
1. On the Carbon Graphite side, each layer needs to be .005 of an inch, for a total of 8 layers; layered in a quasi-isotropic orientation. The total length/width of 18"x18" panel, must be +/- .125"
1. On the Armid (Kevlar) side, each layer needs to be .010 of an inch, for a total of 4 layers; layered in a cross-ply orientation. There is a transition on two sides of the panel at the 14.5" mark roughly.
1. The honeycomb core needs to be 1" thick with a cell size no bigger than 1/4".
1. The film adhesive bonding honeycomb core to Armid and Graphite sides have no specification.
Q3) Is there any NDE to verify the quality of the fabricated skins before bonding or any NDE to verify a quality bond (no delamination areas) have been achieved between the skins and the honeycomb core before delivery?
A3) NDE (NDI) does not verify the quality of bond on these panels upon arrival to our schoolhouse.
Q4) Is this a best effort contract?
A4) No.
2. If you have any questions please contact Sydney Hocker at (940) 676-4308 or sydney.hocker@us.af.mil.
CARRI DULANEY
Contracting Officer image1.png
File details come from the government source that posted it. Updated .