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A1.2.4.8.3.6. Complete grounding and bonding methodology.
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A1.2.4.8.3.7. A bent pin analysis for all connectors for safety critical or hazardous systems that have spare pins.
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A1.2.4.9. Flight Hardware Ordnance Subsystems
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A1.2.4.9.1. General Data. A detailed description of the ordnance subsystems of the launch vehicle or space craft shall be provided. The description shall include the information identified in A1.2.4.1.
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A1.2.4.9.2. Flight Hardware Ordnance Hazard Classifications and Categories. The following ordnance hazard classification data shall be submitted:
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A1.2.4.9.2.1. UNO classifications and DOD hazard classifications, including class, division, and compatibility group, in accordance with DOD-STD-6055.9 and NASA-STD 8719.12 respectively.
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A1.2.4.9.2.2. DOT classification.
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A1.2.4.9.2.3. The ordnance device and system hazard category for each ordnance item and system in accordance with 13.1.2; test results and/or analysis used to classify the ordnance devices and systems as Category A or B.
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A1.2.4.9.3. Flight Hardware Ordnance System Data. The following ordnance system data shall be submitted:
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A1.2.4.9.3.1. A block diagram of the entire ordnance system.
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A1.2.4.9.3.2. A complete line schematic of the entire ordnance system from the power source to the receptor ordnance, including telemetry pick-off points and ground (umbilical) interfaces.
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A1.2.4.9.3.3. Diagrams showing the location of all ordnance components on the vehicle.
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A1.2.4.9.3.4. A description of wiring, ETS, and FOC routing.
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A1.2.4.9.3.5. A description of electrical, ETS, and optical connections and connectors.
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A1.2.4.9.3.6. Detailed, complete schematics of the entire ordnance system showing component values such as resistance and capacitance, tolerances, shields, grounds, connectors, and pin outs.
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A1.2.4.9.3.6.1. The schematics shall include all other vehicle components and elements that interface or share common usage with the ordnance system.
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A1.2.4.9.3.6.2. All pin assignments shall be accounted for.
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A1.2.4.9.3.7. Detailed narrative description and functional schematic of the operation of the ordnance system. The narrative description and functional schematic shall be capable of being used to determine the configuration and resulting failure tolerance of the vehicle and ground ordnance systems at any time during prelaunch processing, launch countdown, or launch, including all credible failure scenarios.
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A1.2.4.9.3.8. The FMECA for each ordnance system.
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A1.2.4.9.3.9. An operational flow of the ordnance system processing and checkout, including timelines and summaries of each procedure to be used.
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A1.2.4.9.3.10. A sketch showing the accessibility of manual arming and safing devices.
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A1.2.4.9.3.11. Specification drawings and documents for all airborne and ground ordnance systems.
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A1.2.4.9.4. Flight Hardware Ordnance Component Design Data. The following ordnance component design data shall be submitted:
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A1.2.4.9.4.1. A complete and detailed description of each ordnance system component and how it functions.
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A1.2.4.9.4.2. Specification drawings and documents for all airborne and ground ordnance components.
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A1.2.4.9.4.3. Illustrated breakdown of all mechanically operated ordnance components.
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A1.2.4.9.4.4. Part number, manufacturer, and net explosive weight for each ordnance item.
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A1.2.4.9.4.5. Temperature and humidity requirements for each ordnance item.
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A1.2.4.9.4.6. Bridgewire resistance, maximum safe no-fire current, and minimum all-fire current for each low voltage EED.
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A1.2.4.9.4.7. Maximum no-fire voltage and minimum all-fire voltage for each EBW.
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A1.2.4.9.4.8. Maximum no-fire energy and minimum all-fire energy for each LID and PAD.
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A1.2.4.9.4.9. A list and summary of test plans procedures, and results, as required.
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A1.2.4.9.4.10. 8 x 10 inch color photographs or electronic copies of all ordnance items.
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The photographs or electronic copies should be of sufficient detail to identify individual ordnance items as well as to show the ordnance item(s) in installed configuration on the payload. These photographs are intended to ensure the safety of Explosive Ordnance Disposal personnel who may be directed to render the ordnance safe.
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A1.2.4.9.5. Flight Hardware Ordnance Component Handling and Storage Data. Specific requirements for handling and storing the flight ordnance shall be submitted.
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A1.2.4.9.6. Solid Rocket Motors, Rocket Motor Segments, and Associated Components. In addition to the requirements listed for ordnance, the following data shall be provided for solid rocket motors, rocket motor segments, and associated components:
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A1.2.4.9.6.1. Propellant Properties.
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A1.2.4.9.6.1.1. Propellant explosive hazard classification (DoD, UNO, DOT, including test results), if not previously addressed by A1.2.4.9.2.1.
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A1.2.4.9.6.1.2. Propellant formulation (composition).
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A1.2.4.9.6.1.3. Propellant autoignition température.
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A1.2.4.9.6.1.4. Propellant static sensitivity (energy in Joules required to ignite the propellant).
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A1.2.4.9.6.1.5. Propellant conductivity.
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A1.2.4.9.6.2. Propellant Reactions to Impact on Hard Surface.
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A1.2.4.9.6.2.1. Ignition threshold drop height.
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A1.2.4.9.6.2.2. Low order detonation threshold drop height.
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A1.2.4.9.6.2.3. Critical impact velocity (threshold velocity required to break up propellant sufficiently so that it will transit from deflagration to detonation in a 1 inch diameter schedule 40 steel pipe).
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A1.2.4.9.6.3. Igniter data
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A1.2.4.9.6.3.1. Type of propellant and propellant properties data as specified in A1.2.4.9.6.1 and A1.2.4.9.6.2 above.
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A1.2.4.9.6.3.2. Data on each igniter initiator, such as a through bulkhead initiator (TBI).
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A1.2.4.9.6.3.3. Igniter weight.
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A1.2.4.9.6.3.4. Igniter grounding provisions.
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A1.2.4.9.6.3.5. Igniter storage requirements.
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A1.2.4.9.6.3.6. Igniter handling requirements.
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A1.2.4.9.6.3.7. Igniter testing and inspection requirements.
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A1.2.4.9.6.3.8. Igniter packaging requirements (if shipped separately).
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A1.2.4.9.6.3.9. Igniter case description, including design safety factors.
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A1.2.4.9.6.4. Rocket Motor/Segment Data.
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A1.2.4.9.6.4.1. Motor/segment case description, including design safety factors.
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A1.2.4.9.6.4.2. Method of proof testing the rocket motor/segment case before propellant loading.
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A1.2.4.9.6.4.3. Weight of propellant.
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A1.2.4.9.6.4.4. Cross-section drawings showing propellant grain design details, case insulation, including physical dimensions, and joint details for segmented rocket motors.
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A1.2.4.9.6.4.5. Motor/segment nondestructive testing requirements.
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A1.2.4.9.6.4.6. Motor/segment storage requirements.
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A1.2.4.9.6.4.7. Motor/segment handling requirements.
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A1.2.4.9.6.4.8. Motor/segment grounding requirements.
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A1.2.4.9.6.4.9. Description of structural, mechanical, and electrical subsystems.
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A1.2.4.9.6.4.10. Description of materials and properties of seals and O-rings.
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A1.2.4.9.6.5. Data submission and analysis, as described in Chapter 18. If these data and analysis are submitted as part of another section of the SDP (MSPSP), shall cross-reference that analysis here.
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A1.2.4.10. Flight Hardware Non-Ionizing Radiation Sources
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A1.2.4.10.1. General Data. A detailed description of the non-ionizing radiation sources shall be provided. The description shall include the information identified in A1.2.4.1.
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