MODIFICATION
56 -- Heat Resistant Light Weight Matting
- Notice Date
- 11/6/2017
- Notice Type
- Modification/Amendment
- NAICS
- 332312
— Fabricated Structural Metal Manufacturing
- Contracting Office
- Department of the Navy, Naval Air Systems Command, Naval Air Warfare Center Aircraft Division Lakehurst, Contracts Department, Hwy. 547 Attn:B562-3C, Lakehurst, New Jersey, 08733-5083
- ZIP Code
- 08733-5083
- Solicitation Number
- N6833518R0045-RFI
- Archive Date
- 12/5/2017
- Point of Contact
- Rene Brown, Phone: 732-323-2780
- E-Mail Address
-
rene.brown@navy.mil
(rene.brown@navy.mil)
- Small Business Set-Aside
- N/A
- Description
- The Purpose of this amendment is to answer the below questions submitted by industry. 1.Q-Is there a target weight per square foot of the matting? A-There is no targeted weight for this system at this time but should be as light as possible while maintaining the structural requirements identified in the RFI 2.Q-With respect to the matting material, are there requirements for corrosion and / or durability, such as stress corrosion cracking of the mat? A-There are no requirements relating to corrosion or durability at this time. 3.Q-Regarding the thermal load requirements, is the 250 hours of exposure a cumulative total of multiple exposures or will the panel be exposed for a continuous 250 hour period prior to load testing? A-Section 2.1 describes a single duration load. The mat solution shall be capable of withstanding the thermal exposure during stand-alone Vertical Takeoff and Landing ( VTOL) operations of all USMC Rotary and Tilt-Rotor aircraft. 4.Q-How will the thermal load be applied to the mat panels? A- The mat solution shall be capable of withstanding the thermal exposure during stand-alone VTOL operations of all USMC Rotary and Tilt-Rotor aircraft. 5.Q-Is this requirement for support of the V22 Osprey? If so is the 400°F heat exposure the requested maximum temperature? This temperature seems to be less than what we were working with previously. Has something changed to reduce the heat exposure? A-This mat system shall support all USMC Rotary and Tilt-Rotor Aircraft for stand-alone VTOL operations. 6.Q- What is the duration of the supported loads? (No indication except in section1.3) A-The duration for dynamic loading of aircraft, as described in section 1.1 of the RFI, will be approximately 2-5 seconds. Static loading requirements are defined in section 1.2. The duration of dynamic loading for ground vehicles is described in section 1.3. 7.Q-What is the Outdoor Temperature Range? Ambient temperature for use? (For example from -40 to + 80 ° C). A-The Environmental requirements for this mat solution have not been officially defined. The USMC operates in all regions of the world consisting of Hot Dry, High Humidity and Extreme Cold Climatic Conditions that are detailed in MIL-HDBK-310 and MIL-STD-810G. 8.Q-What type of anchoring is required? Does the matting have to be fixed to the ground? A-The mat system shall accept perimeter anchors. There shall be no internal anchoring within the VTOL expanse. Yes, the mat system shall be fixed to the ground. 9.Q-There is no indication about the desired dimensions of a panel. Is there a specific size being sought? A-There is no specific size being sought, at this time. 10.Q- Does matting need to be installed on an aircraft carrier potoon? How will it be transported? A- There are no plans on installing this mat system on any maritime vessel. There are currently no defined transportation methods for this system. 11.Q-Is Material Handling Equipment (MHE) allowed? If yes what kind? A-Material Handling Equipment requirements have not been defined at this time. 12.Q-Can the material be porous or not? A-There are no restrictions to the type of material at this time, as long as the system can support stand-alone VTOL operations. 13.Q-In cases 1.1 and 1.2, we've noticed that the weight specified corresponds with current Navy VTOL aircraft, however the areas specified is singular suggesting a single tyre loading. Is this assumption correct? What is the maximum single tyre load? A-Sections 1.1 and 1.2 specify maximum singular loading, at this time. 14.Q-In cases 1.1 and 1.2, we assume load is applied vertically whereby 1.3 is rolling as described? A-Sections 1.1 and 1.2 are vertically applied loads and in Section 1.3 the load is applied rolling. 15.Q-Do you have any dimensional constraints on the panels? Length x Width x Thickness? A-There is no specific size being sought, at this time. 16.Q-Do you have any mass constraints for the panels? Lb/ft2 and per single panel? A-There is no targeted weight for this system at this time but should be as light as possible while maintaining the structural requirements identified in the RFI 17.Q-2.1 ‘250 hours of exposure' - will the panels be exposed to this continuously or is this an intermittent requirement with total exposure time of 250 hours? A-Section 2.1 describes a single duration load. The mat solution shall be capable of withstanding the thermal exposure during stand-alone Vertical Takeoff and Landing (VTOL) operations of all USMC Rotary and Tilt-Rotor aircraft. THIS IS A REQUEST FOR INFORMATION ONLY. It is not a Request for Proposal, a Request for Quotation, an Invitation for Bids, a solicitation, or an indication that the PMA251 Program Office or NAVAIR will contract for the items contained in the RFI. NAVAIR will not pay respondents for any information generated for or provided in response to this RFI. The Government will not reimburse the respondent for any costs associated with the information submitted in response to this request, nor will the Government compensate any respondent for any costs incurred in developing the information provided to the Government. The Government will not release any information marked with a Proprietary legend, received in response to this RFI, to any firms, agencies, or individuals outside of the Government without written permission in accordance with the legend.
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