RFI_ACES II Ejection Seat - F-15S - NSN: 1680-645-8077 and 1680-01-645-8078

Request for Information ACES II Ejection Seat (F-15SA) Survey NSNs 1680-01-645-8077 and 1680-01-645-8078 PNs A119050-573 and A119050-575) This market survey is being conducted to identify potential sources that may possess the expertise, capabilities, and experience to meet the qualifications for procurement of the ACES II Ejection Seat use by Royal Saudi Air Force (RSAF) on the F-15SA aircraft. The level of security clearance and amount of foreign participation in this requirement has not been determined. Contractors/Institutions responding to this market research are placed on notice that participation in this survey may not ensure participation in future solicitations or contract awards. The government will not reimburse participants for any expenses associated with their participation in this survey. The only known source is AMI Industries, Inc., Colorado Springs, CO. No samples, drawings or specifications are available for potential vendors to evaluate. Please note this ejection seat is unique to the F-15SA aircraft. PURPOSE/DESCRIPTION The government is conducting market research to identify potential sources that may possess the expertise, capabilities, and experience to meet the requirements for qualification to deliver the ACEII Ejection Seat (front and rear cockpit), National Stock Number (NSN): 1680-01-645-8077, PN 119050-573 and NSN: 1680-01-645-8078, PN 119050-575. The Government does not own or have access to the engineering data for these items. FUNCTION: The Advanced Concept Ejection Seat (ACES) was designed to be rugged and lightweight compared to earlier systems. It also was designed to be easy to maintain and updatable. It includes the following features: Electronic Sequencing and timing, Mortar-deployed main chute, Auto sensing of egress conditions, Parachute reefing to control opening at all speed ranges, and Multi-Mode operation for optimum recovery of the crewman. The ACES II is a third-generation seat, capable of ejecting a pilot from zero-zero conditions up to maximum altitude and airspeeds in the 600 KEAS range. The peak catapult acceleration is about 12gz. The ACES II has three main operating modes, one each for the low speed/low altitude, medium speed, and high speed/high altitude. In Mode 1, which includes 0-0 up to 250kts, the parachute is inflating in less than two seconds. In Mode 2 the chute is inflating in less than 6 seconds. Mode 2 is effective up to the maximum rated speed of the seat. Mode 3 deployment is delayed by the sequencer until the seat-man package reaches either Mode 2, or Mode 1 conditions, whichever comes first. Primarily, Mode 3 refers to operation above 15000 feet where separation from the seat would result in disconnection from the emergency oxygen, and also possible lead to more severe opening shock of the parachute due to differing atmospheric conditions. Seat modes are selected by the sequencer based on atmospheric conditions, and the modes vary depending on differences in the conditions such as apparent airspeed and apparent altitude. A light-weight crewman would reach an apogee of close to 200 feet if they ejected at ground level with zero airspeed. Typical performance is as follows: The seat structure is primarily aluminum alloy stamp formed with ridges for structural strength. The box-like structure is referred to as a monologue construction. The back section which is nominally 16 inches wide has a set of three rollers on each side which interface with the extruded aluminum rails in the cockpit. The seat itself weighs approximately 127 pounds, with the rocket-catapult weighing 21LBs. The propulsion is a CKU-5/A/A rocket-catapult which uses a conventional solid propellant catapult charge to start seat movement, and a solid-propellant rocket motor to sustain the movement. The rocket motor is ignited at the end of the catapult stroke as the seat leaves the aircraft. The rocket-catapult is attached to the seat at the headrest end and to the cockpit at the base via a twin-barrel linear actuator which provides for seat height adjustment. The nominal adjustment range is +2.5-inch vertical adjustment. The actuator is attached at the fixed base to the cockpit structure and at the upper end via twin screw barrels to the base of the rocket-catapult. Seat functions are normally activated by the Recovery Sequencing Subsystem which consists of the environmental sensing unit, and the recovery sequencing unit, an electronic box located inside the seat rear on the right hand side. The environmental sensing unit consists of two altitude compensated dynamic pressure transducers, and two static pressure transducers. The dynamic pressure sensors (pitot tubes) are located on or near the headrest and read the air pressure as the seat exits the aircraft. The pressure differential between them and the ambient (static) sensors behind the seat is compared by the recovery sequencing unit to determine what operating mode the sequencer should select. The sequencer is fully redundant with two thermal batteries, two electrical systems, and an individual bridge wire from each in each of the electro-explosive squibs. The thermal batteries are activated by hot gas bled off from the catapult firing. There is a small window on the right side of the seat back to check the batteries for signs that they have been fired. Firing of the seat is normally by pulling one of the ejection control handles mounted on the seat bucket sides. See attached RFI with Contractor Capability Survey for additional details.