P/N: 150-021-8c1-1
Category: Doors & Access Panels
This product requires a custom quote. Please contact our sales team for pricing information or submit an RFQ (Request for Quote).
| Condition | Stock |
|---|---|
| New Surplus | 1 Available |
Part 150-021-8c1-1 is a prebond panel repair bonded material for aircraft door and access panel restoration. This material restores panel stiffness and bondline integrity before patch bonding operations during MRO structural repairs. Apply and cure per the aircraft Structural Repair Manual and approved repair data.
The prebond material prepares bonded surfaces for secondary adhesive application, ensuring proper load transfer and repair durability. Verify compatibility with your aircraft's Illustrated Parts Catalog before installation.
Please note: Product descriptions are provided for informational purposes. Always refer to your aircraft's Illustrated Parts Catalog (IPC) to verify part compatibility and specifications.
Part 150-021-8c1-1 is a prebond panel repair bonded material for aircraft door and access panel restoration. This material restores panel stiffness and bondline integrity before patch bonding operations during MRO structural repairs.
The PREBOND PANEL REPAIR BONDED MATERI may be available as an OEM (Original Equipment Manufacturer) or PMA (Parts Manufacturer Approval) part depending on condition and source. Both carry FAA certification for airworthiness. Currently available in: New Surplus. Contact us for sourcing details.
Installation hardware requirements vary by application. Check your aircraft's Structural Repair Manual (SRM) or Illustrated Parts Catalog (IPC) for the complete installation kit requirements for the PREBOND PANEL REPAIR BONDED MATERI. We stock related hardware and can help identify companion parts.
Yes, we ship airframe components worldwide. International orders typically arrive within 3-14 business days depending on destination. Export documentation and customs forms are included. Contact us for international shipping quotes on the 150-021-8c1-1.