SOURCES SOUGHT
67 -- B-52 BOMB BAY CAMERA
- Notice Date
- 7/2/2009
- Notice Type
- Sources Sought
- NAICS
- 443130
— Camera and Photographic Supplies Stores
- Contracting Office
- Department of the Air Force, Air Force Materiel Command, Tinker OC-ALC - (Central Contracting), 3001 Staff Drive, Ste 1AG76A, Tinker AFB, Oklahoma, 73145-3015
- ZIP Code
- 73145-3015
- Solicitation Number
- FA8122-09-R-0004
- Archive Date
- 12/31/2009
- Point of Contact
- Janet M Kuruvilla, Phone: (405)734-4634
- E-Mail Address
-
janet.kuruvilla@tinker.af.mil
(janet.kuruvilla@tinker.af.mil)
- Small Business Set-Aside
- N/A
- Description
- The purpose of this sources sought synopsis is to seek out sources for the purchase of 20 B-52 Bomb Bay Cameras. 2 ea first articles will be required. Commercial FAR Part 12 procedures will be used. The following is a description of the camera requirements: Bomb Bay Camera Requirements 1.This document details specific requirements for the B-52H Bomb Bay Camera operational environment. Specifics applicable to the B-52 environment are contained in the B-52 Modification Planning Guide. 2.The current camera utilized in the B-52 has become unsupportable due to component obsolescence. The replacement camera shall consist of Commercial-Off-The-Shelf (COTS) components that meet the Form, Fit, and Functional requirements of the existing camera. 3.The B-52 Bomb Bay Camera System utilizes 2 cameras that are mounted on sheet metal brackets, attached to the aft bomb bay bulkhead. The cameras obtain power from the aircraft 28 VDC bus. Both cameras are controlled from the Navigation Crew station via the Bomb Bay Camera System Control Panel. The camera video signal is carried to the control panel via 75 ohm RG-179 coaxial cable. The video will be displayed on a standard laptop computer with the aid of a USB 2.0 video capture device. The video signal is fed to the capture device composite video input from the control panel Video Output receptacle. Both cameras have an internal thermostatically controlled heating system to preclude fogging of the camera lens and outer protective enclosure glass window. 4.The camera shall be equipped with a service port for introduction of dry gaseous nitrogen. A nitrogen purge and charge is necessary to displace air within the camera housing, thus reducing the potential of internal condensation occurring during times of rapid temperature change. After purging operations are performed, the camera shall have the capability to maintain a dry gaseous nitrogen charge. The camera purge and service process will be performed by Air Force maintenance personnel and shall not require tools or equipment that are not readily available in the field. 5.Applicable Documents: B-52H Modification Planning Guide D675-60000-14 - B-52 Electrical Power Requirements B-52H Modification Planning Guide D675-60000-15 - Random Vibration Test Requirements for Equipment installed in B-52 Airplanes B-52H Modification Planning Guide D675-60000-16 - Thermal Environments and Equipment Requirements MIL-STD-810G - Environmental Engineering Considerations and Laboratory Tests MIL-STD-461F - Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment MIL-E-5400T - Electronic Equipment, Airborne, General Specification For Applicable Documents Cont. MIL-STD-704E - Aircraft Electric Power Characteristics D2-1049 - Design Criteria B-52 Advanced Configurations 6. Reliability: The expected Mean Time Between Failure (MTBF) shall exceed 17,500 operational hours. 7.Power: The camera shall be capable of operating on DC power ranging from 22 to 31 VDC as required by MIL-STD-704 and in accordance with exceptions defined in B-52 Modification Planning Guide D675-60000-14, which details exceptions to MIL-STD-704 as applicable to the B-52H aircraft. Power consumption shall not exceed 5 watts. 8.Electromagnetic Interference and Compatibility: The camera shall meet the requirements of MIL-STD-461F for emission and susceptibility to electromagnetic interference. 9.Altitude: The camera shall be capable of operating, without degradation from 0 to 50,000 feet pressure altitude as prescribed by MIL-E-5400T for Class 2 equipment. Although the requirement for Class 2 equipment dictates a maximum altitude of 70,000 feet, the B-52 maximum operating altitude is 50,000 ft. 10.Temperature: The camera is required to be fully operational at temperatures between -54 degrees centigrade and +71 degrees centigrade as required by MIL-E-5400T, for Class 2 equipment. The camera shall withstand temperatures of -55 degrees centigrade to +90 degrees centigrade during periods of storage and shipping. 11.Temperature - Altitude Combination: The camera shall be capable of operation, without degradation within the combined temperature - altitude combination required by MIL-E-5400T, for Class 2 equipment with altitude limitation of paragraph 9 above. 12.Temperature Shock: The camera shall be able to withstand temperature rates of change of 1.8°F per second over the temperature range of -65°F to +203°F for MIL-E-5400T for Class 2 equipment. The camera shall be capable of withstanding temperature shock without degradation of components, operation, or performance. Lens frost and inside fogging of the cover glass shall be prevented by a thermostatically controlled internal heating system or other means. 13.Humidity: The camera shall be capable of operation, without degradation when subjected to the requirements of MIL-STD-810F, Method 507.4. Fogging of the inside of the cover glass or camera lens shall not occur. 14.Salt Fog/Spray: The camera shall be capable of operation, when subjected to the requirements of MIL-STD-810G, Method 509.4 in salt fog and spray as found in a salt-sea environment without degradation of operation or performance. 15.Rain: The camera shall be capable of operating, when subjected to the requirements of MIL-STD-810G, Method 506.4, procedure 1 in an environment equivalent to rain, due to atmospheric exposure while bomb bay doors are open. 16.Sand and Dust: The camera shall withstand, in both an operating and non-operating condition, when subjected to the requirements of MIL-STD-810G, Method 510.4, Procedure 1, exposure to sand and dust particles as encountered in operational areas around the world. 17.Acceleration: The camera shall not experience damage with the following load factors applied separately as defined by D2-1049. Load Direction Load Factor Fore & Aft 2.0 Down 5.5 Up 3.66 Side 2.0 18. Fungus: The camera shall withstand, during operating and non-operating conditions, when subjected to the requirements of MIL-STD-810G, Method 508.5, where indefinite exposure to fungus growth as encountered in tropical climates. Fungus inert materials, as defined by MIL-T-5400T paragraph 3.1.11, shall be used in fabrication of the camera. In no case shall overall spraying of the camera or components be necessary to meet this requirement. 19.Vibration: Camera operation or performance shall not be affected by the B-52 vibration environment. The camera shall meet all requirements associated with the vibration environment for the B-52 bomb bay as defined in B-52 Modification Planning Guide D675-60000-15, equipment designation 5A. The camera shall be able to withstand vibration encountered in the B-52 airplane without degradation of components, operation, or performance of the equipment. Reference Figure 1. Figure 1 20.Mechanical Shock: The camera shall be subjected to Mechanical Shock testing as prescribed by MIL-STD-810F. The camera shall be capable of enduring 30 g, 11 ms shock in each of three orthogonal axes without degradation of components, operation, or performance of the equipment. 21.Explosive Atmosphere: The camera shall not cause ignition or shall be demonstrated to be explosion proof in an environment of any mixture of air and jet fuel. Operation of the camera shall not result in the temperature of any surface exposed to the ambient air to exceed the safe limit detailed in MIL- STD-810F Method 511.4 Procedure I. 22.Physical Characteristics: The camera housing is cylindrical and shall meet the dimensional requirements detailed in Figure 2. The electrical receptacle and service port shall be located approximately as shown. The longitudinal surface of the camera shall be free of items that would interfere with mounting to the existing aircraft mounting bracket. Reference Figure 3. Camera weight shall not exceed 2.5 pounds. 23.Electrical Interface: The camera electrical interface shall be compatible with the current B-52 aircraft electrical interface circular connector part number MS3116F12-10S. The electrical discretes will conform to the following; Pin A - RS-170 Video Out Pin B - RS-170 Video Shield Pin C - Gen-Lock Sync In Pin D - RS-170Video #2 Out Pin E - +28 VDC Heater Power Pin F - Over Temperature Warning (Provide DC Power Ground Potential For Over Temperature Discrete) Pin G - Not Used Pin H - Heater On (Provide DC Power Ground Potential For Heater On Discrete) Pin J - +28 VDC Camera Power Pin K - 28 VDC Camera and Heater Return 24.Lens Requirement: The camera lens shall be an ASA "C" mount 8 mm with automatic iris capability. 25.Camera Performance: Camera performance as applicable to imaging and video format shall meet or exceed requirements and specifications detailed in Table 1. The camera video output shall be RS170 compliant and compatible with industry standard RS-170 and NTSC composite video display equipment and systems. TABLE 1 Sensor........................................................................................... Frame Transfer CCD Image Format.............................................................................. ½", 4:3 Aspect Ratio Pixel Count................................................................................... 786 H x 488 V Sensitivity (minimum usable)................................................... 0.05 FC Face Plate Spectral Response....................................................................... 400 - 1100 Nm Signal to Noise Ratio................................................................... 50 db Automatic Gain Control.............................................................. 10 db Gamma Correction...................................................................... 1.05 - 0.5, selectable Geometric Distortion.................................................................. 0% Resolution (Horizontal)................................................................................ 580 TVL (Vertical)..................................................................................... 360 TVL Sync Standard............................................................................... 525 line, 30 Frames/sec Gen-Lock Sync Input.................................................................... Composite Sync or Video More details are to follow in the solicitation. This sources sought synopsis will be posted out until 9 July 2009. The estimated date for posting the synopsis is 10 July 2009. The estimated date for posting the solicitation is 20 July 2009. The estimated response date on the solicitation is 19 August. Please respond to Janet Kuruvilla- 448 SCMG/PKBC, janet.kuruvilla@tinker.af.mil, and let me know if you are interested in responding to this solicitation- please let me know before Thursday, July 9th.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/USAF/AFMC/OCALCCC/FA8122-09-R-0004/listing.html)
- Place of Performance
- Address: 3001 STAFF DRIVE, TINKER AFB, OK 73145, TINKER AFB, Oklahoma, 73145, United States
- Zip Code: 73145
- Zip Code: 73145
- Record
- SN01864633-W 20090704/090703001029-1d99ca809f93a190a8fc57c8da93c61b (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
(may not be valid after Archive Date)
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