Pre-Award Qualification Notice for Nut Drive Manifold, C-5 Galaxy Aircraft, NSN 1650-01-327-1355

12/19/2022 EXTENSION OF RESPONSE DATE TO 06 JAN 2023 THIS NOTICE IS HEREBY AMENDED TO ATTACH THE MOST RECENT VERSION OF THE SQS FOR THIS NSN. RESPONSE DATE IS EXTENDED TO NOVEMBER 2, 2022. PLEASE SEE SQS ATTACHMENT DATED 2022_09_02 Pre-Award Qualification Notice for NUT DRIVE MANIFOLD, C-5 GALAXY AIRCRAFT, NSN 1650-01-327-1355 This notice identifies a pre-award qualification opportunity established in accordance with FAR 9.2, as supplemented, in anticipation of a forthcoming competitive acquisition opportunity. The current forecast procurement requirements for NSN 1650-01-327-1355, Nut Drive Manifold, over the next five government fiscal years (October - September) is: 2023: 12 Each 2024: 01 Each 2025: 01 Each 2026: 01 Each 2027: 01 Each DESCRIPTION: The - Nut Drive Manifold (NDM) is the hydraulic manifold assembly that controls the C-5 Pitch Trim Actuator's Nut Drive Motor. Primary pilot control of the Pitch Trim Actuator (PTA) is through the NDM. The PTA positions the entire horizontal stabilizer assembly for pitch trim of the C-5 aircraft and is a Critical Safety Item. The NDM provides the only manual override for control of the PTA in the event of a PTA control malfunction. Manufacture of parts for C-5 NDM requires strict control of processes to ensure adherence to extremely close tolerances during machining of specified material. Special machining equipment is required to produce the precisely manufactured part surfaces. Consistent manufacturing processes are necessary to ensure that the manifold components are manufactured such that the Pitch Trim Actuator assembly provides precise control of the horizontal stabilizer pitch during flight. Failure of the Nut Drive Manifold to position the horizontal stabilizer could place the aircraft and crew in an extremely hazardous situation due to the pilots being unable to properly trim the aircraft for its flight condition and requiring use of backup controls. Although there is a screw drive manifold that can also run the PTA, flight safety histories indicate that aircrew task saturation as a result of component failures dramatically increases the risk of an aircraft mishap if they occur in critical phases of flight. If the failure occurs under these conditions, there is a risk of loss of life and/or aircraft. Approximate dimensions assembled for shipping: Length 13.5 inches, Width 13.5 inches, Height 7.0 inches; Maximum Dry Weight: 36.375 pounds. Manifold body primary material: 7050-T7451 Aluminum allow, IAW SAE AMS 4050 Hydraulic valve primary material: 440C Stainless Steel IAW SAE AMS 5630 OR ASTM A 276. Some Subassemblies require cryogenic soak between tempers during heat treatment. Tolerances controlled to the +0.001 inches, machining component diametric clearances of 0.00020+0.00005 inches, cylindricity controlled to +0.00005 inches, surface roughness of up to 4 RMS. Component and Assembly level hydraulic testing and verification required. REQUIREMENT The qualification requirements specified herein are necessary to verify the structural and functional integrity of this NSN. Failure to procure these items from a fully qualified source can result in structural or functional deficiencies that will compromise the mission capability of the respective weapon system. These parts require engineering source approval by the design control activity to assure the integrity of the part. Potential sources are encouraged to demonstrate their ability to meet the standards specified in this announcement for qualification by the design control activity with respect to NSN 1650-01-327-1355. The information provided in this notice is designed to advise potential sources of the documentation, requirements, and procedures to obtain pre-award qualification approval for the item identified in this notice. The Government will not reimburse any potential offeror for their submission of a pre-award qualification package, and the submission does not guarantee either approval as a source or an opportunity for any future contract. This notice does not constitute a solicitation and does not ensure that a competitive solicitation will follow. Failure to submit a complete and timely pre-award qualification package could result in an interested offeror not being considered for future awards for the item identified in this notice. The technical data package associated with this item may be requested from the Government Point of Contact identified below. The technical data package is subject to export control restrictions; therefore, an interested vendor must be registered in the Joint Certification Program (JCP). To request access to data/drawings, or other releasable technical data, interested vendors may provide their CAGE number to the contracting officer listed below for verification of JCP standing. Alternatively, a current, approved DD2345 may be submitted. Upon verification, data access will be granted. To become registered in the JCP, vendors can do so at https://www.dla.mil/HQ/LogisticsOperations/Services/JCP/ The Government Point of Contact for the technical requirements specified for qualification is: Engineer Name Engineer E-mail Andrew Hyatt Andrew.Hyatt.9@us.af.mil Responses must be received no later than close of business 19OCT2022. Due to USAF networking, prior to sending attachments in response to this announcement, contact the undersigned Engineering and Contracting POCs below for submission instructions. Andrew Hyatt/Engineer Andrew.Hyatt.9@us.af.mil Christine Tomlinson/Contract Specialist Christine.Tomlinson@us.af.mil Franklin Holland/Competition Advocate Franklin.holland@dla.mil See attached Source Qualification Statement for additional information.