BA-X PSPEC Bailout_signed.pdf

AFLCMC/WNU-BAX/

15 May 2024

PERFORMANCE SPECIFICATION

Back Automatic Parachute (BA-X) – Bailout

Prepared by

AFLCMC/WNU

1981 Monahan Way Wright-Patterson AFB, OH 45433-7017

APPROVED BY: ____________________________________

Date: 15 May 2024 Ms. Nichole Taylor

Chief Engineer, Human Systems Division 1981 Monahan Way, Bldg 12

APPROVED BY: ____________________________________

Date: 15 May 2024 Ms. Angela Babian

Chief Engineer, Egress & Survival Branch

PREPARED BY: ____________________________________

Date: 15 May 2024 1st Lt Nathan Dablain

Engineer, Egress & Survival Branch

Contents

1. Scope

1.1. Introduction

1.2. Document Overview

2. Applicable Documents

2.1. General

2.2. Government Documentation

2.2.1. Government Specifications, Standards and Handbooks

2.2.2. Other Government documents, drawings, and publications

2.3. Non-Government Publications

2.4. Order of Precedence

3. System Requirements

3.1. Workmanship

3.1.1. Material Age

3.1.2. Defects

3.1.3. Cleanliness

3.1.4. Edges

3.2. FAA Certification

3.3. Recycled, Recovered, or Environmentally Preferable Materials

3.4. Integration

3.4.1. Aircrew

3.4.2. Aircrew Flight Equipment (AFE) Compatibility

3.4.3. Aircraft Compatibility

3.5. Physical Characteristics

3.5.1. System Donning

3.5.2. System Doffing

3.5.3. Inadvertent Function

3.5.4. Physical Constraints

3.5.5. Ripcord Pin Protection

3.5.6. Sizing Reference

3.5.7. Parachute Automatic Release

3.5.8. Personnel Lowering Device (PLD)

3.5.9. Accessory Components

3.5.10. Fitting

3.6. Egress Conditions

3.6.1. Speed

3.6.2. Altitude

3.6.3. Rate of Descent

3.6.4. Canopy Collapse Prevention

3.6.5. Deceleration Magnitude

3.6.6. Oscillation

3.6.7. Parachute Maneuverability

3.6.8. Parachute Landing

3.7. Environmental Requirements

3.7.1. Storage Temperatures

3.7.2. Operating Temperatures

3.7.3. Humidity

3.7.4. Rain

3.7.5. Solar Radiation

3.7.6. Blowing Dust

3.7.7. Blowing Sand

3.7.8. Fungus

3.7.9. Vibration

3.7.10. Shock

3.7.11. Salt Fog

3.7.12. Contamination by Fluids

3.7.13. Explosive Decompression

3.7.14. Electromagnetic Interference and Compatibility

3.8. Human Systems Integration

3.9. Logistics

3.9.1. Reliability

3.9.2. Service Life

3.9.3. Maintainability

3.9.4. Training

3.10. Nameplates and Product Markings

3.11. Packaging, Handling, and Transportation

3.11.1. Transportation

3.11.2. Package Marking

3.12. Environment, Safety, and Occupational Health (ESOH)

3.12.1. Safety

3.12.2. Safety and Health Hazard Management

3.12.3. Allergic Reaction

4. VERIFICATION (Qualification Provisions)

4.1. Workmanship

4.2. FAA Certifications

4.3. Recycled, Recovered, or Environmentally Preferable Materials

4.4. Integration

4.4.1. Aircrew

4.4.2. AFE Compatibility

4.4.3. Aircraft Compatibility

4.5. Physical Characteristics

4.5.1. System Donning

4.5.2. System Doffing

4.5.3. Inadvertent Function

4.5.4. Physical Constraints

4.5.5. Ripcord Pin Protection

4.5.6. Sizing Reference

4.5.7. Parachute Automatic Release

4.5.8. Personnel Lowering Device (PLD)

4.5.9. Accessory Components

4.5.10. Fitting

4.6. Egress Conditions

4.7. Environmental Conditions

4.7.1. Storage Temperatures

4.7.2. Operating Temperatures

4.7.3. Humidity

4.7.4. Rain

4.7.5. Solar Radiation

4.7.6. Blowing Dust

4.7.7. Blowing Sand

4.7.8. Fungus

4.7.9. Vibration

4.7.10. Shock

4.7.11. Salt Fog

4.7.12. Contamination by Fluids

4.7.13. Explosive Decompression

4.7.14. Electromagnetic Interference and Compatibility

4.8. Human Systems Integration

4.9. Logistics

4.9.1. Reliability

4.9.2. Service Life

4.9.3. Maintainability

4.9.4. Training

4.10. Nameplates and Product Markings

4.11. Packaging, Handling, and Transportation

4.11.1. Transportation

4.11.2. Package Marking

4.12. Environment, Safety, and Occupational Health (ESOH)

4.12.1. Safety

4.12.2. Safety and Health Hazard Management

4.12.3. Allergic Reaction

5. PACKING, HANDLING, STORAGE AND TRANSPORATION

5.1. Packing

5.2. Labeling

5.3. Shipment Marking

6. Notes

6.1. Special Definitions

1. Scope

1.1. Introduction

This specification establishes the performance and test requirements for a back-automatic parachute (BA-X) for use in bailout applications. The BA-X will replace current emergency back style parachutes which cause muscular and skeletal issues in both seated and standing aircrew because of excessive bulk and weight. The BA-X will be worn by aircrew during walk around applications on the B-52. The BA-X shall be a complete emergency bailout parachute system to include the features and accessories identified in Section 3 of this document.

The BA-X will be utilized in bailout, constant wear, and static line parachute applications for B-52 aircrew during flight in war and peace time. When not in storage, the BA-X will remain inside the aircraft until due for inspection or utilized as defined in Section 3.

1.2. Document Overview

The BA-X requirements are defined in section 3 of this document and the verification methods are specified in section 4. Within the system requirements section, “shall” denotes a mandatory level of performance to be met by the contractor. “Should” indicates a desired level of performance, but one that is not contractually binding. “Will” indicates a fact that is relevant to the system and does not need to be verified.

Performance specification requirements are defined in this document within the context of their threshold and/or objective values. Thresholds and objectives, as designated within brackets in the individual requirements ([T] and [O] respectively), are upper and/or lower values that define a criterion’s acceptable performance range and provide the designer with allowable trade space that can be used during the development process. If not specified otherwise, requirements are thresholds. This trade space (i.e., the capability range between the threshold and objective) allows the systems engineering activities to flow without interruption. A performance threshold identifies the minimum acceptable value that, in the government’s judgment, is required to satisfy a need of the program. If performance threshold values are not achievable, program performance may be seriously degraded, and the utility of the system may become questionable. A performance objective is identified as the value desired by the user. It represents an incremental, operationally meaningful, time-critical, and cost-effective improvement to the threshold value to be viewed by government evaluators as a significantly value-added achievement to ultimate system performance, cost savings, and risk reduction. An objective value may be the same as the threshold when the achievable performance increase above the threshold is not quantitatively significant, operationally important, or useful.

2. Applicable Documents

2.1. General

The documents listed in this section are specified in sections 3, 4, or 5 of this specification This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements of documents cited in sections 3, 4, or 5 of this specification, whether or not they are listed.

2.2. Government Documentation

2.2.1. Government Specifications, Standards and Handbooks.

The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract.

DEPARTMENT OF DEFENSE STANDARDS

MIL-STD-129R Military Marking for Shipment and Storage MIL-STD-130N Identification Marking of US Military Property MIL-STD-461F Requirements for the Control of Electromagnetic Interference

Characteristics of Subsystems and Equipment MIL-STD-464C Electromagnetic Environmental Effects Requirements for Systems MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests MIL-STD-882E DoD Standard Practice: System Safety MIL-STD-2073E Standard Practice for Military Packaging MIL-DTL-7567C Parachutes, personnel, detail manufacturing instructions for

(Copies of these documents are available online at http://quicksearch.dla.mil or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.)

2.2.2. Other Government documents, drawings, and publications The following other Government documents, drawings, and publications form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract.

T.O. 14-1-1 (Reference) USAF Aircrew Flight Equipment and Clothing and Equipment T.O. 1B-52H-1 Flight Manual, USAF Series B-52H Aircraft FAR 25-853, Appendix F Federal Aviation Regulation – Airworthiness Standards DOD Instruction 5000.02 Operation of the Defense Acquisition System TSO-C23f Technical standard Order for Personal Parachute Assemblies

(TSO-C23f available from http://rgl.faa.gov/Regulatory_and_Guidance_Library/)

2.3. Non-Government Publications

Parachute Industry Association PIA TS 135 Performance Standards for Personnel Parachute Assemblies and Components

(Copies of these documents are available for purchase from http://www.pia.com/)

SAE International AMS-STD-595A Colors Used in Government Procurement

(Copies of these documents are available for purchase from https://www.sae.org)

2.4. Order of Precedence

In the event of a conflict between the text of this document and the applicable documents cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

http://www.pia.com/

3. System Requirements

3.1. Workmanship

The workmanship employed in the manufacture of all parts and assemblies shall be of the highest quality and shall conform with MIL-DTL-7567C.

3.1.1. Material Age

The contractor shall select new materials not more than 3.5 years old (based on date of manufacture) of good quality that can meet all the operational and environmental requirements specified herein.

3.1.2. Defects

There shall be no defects which might affect function or appearance.

3.1.3. Cleanliness

The finished assemblies and all integral parts shall be clean and free of oils and any other materials that might adversely affect their operations.

3.1.4. Edges

All excess flash shall be properly trimmed with all metal and plastic parts smooth and free of sharp edges.

3.2. FAA Certification

The parachute system shall be TSO certified to the latest FAA standards stated in TSO-C23f.

3.3. Recycled, Recovered, or Environmentally Preferable Materials Recycled, recovered, or environmentally preferable materials may be used wherever possible provided that the material meets or exceeds new material specifications, meets or exceeds the operational and maintenance requirements, and promotes economically advantageous life cycle costs.

3.4. Integration

The BA-X shall properly integrate with Aircrew, Aircrew Flight Equipment and Aircraft.

3.4.1. Aircrew

3.4.1.1. Aircrew Weight

The BA-X shall accommodate aircrew and gear with a gross weight (total exit weight including all gear and the parachute) range of 120 to 300 pounds [T]; 107 to 350 pounds [O].

3.4.1.2. Anthropometric Characteristics

The BA-X shall accommodate Multivariate Population Cases 1-9 identified in Table 1 [T].

Shall accommodate 100% of aircrew members [O]. Case dimensions drawn from Table 5 of ENFC-CSB-08-01 (Change 1).

Table 1. Multivariate Cases for COTS (dimensions in inches) Case 1 Case 2 Case 3 Case 4 Case 5 Case 6 Case 7 Case 9

Small Medium build Short

Medium build Long

Tall Sitting Height Short

Overall Large

Longest Limbs

Overall Small

Smallest Pilot

Thumb tip reach 27 27.6 33.9 29.7 35.6 36 26.1 30 Buttock-knee length 21.3 21.3 26.5 22.7 27.4 27.9 20.8 22.5 Knee-height sitting 18.7 19.1 23.3 20.6 24.7 24.8 18.1 20 Eye height sitting 32.8 35.5 34.9 38.5 40 38 31 34 Shoulder height sitting 20.6 22.7 22.6 25.2 26.9 25 19.5 21.8

Shoulder breadth range 14.7- 18.1

16.4- 20.6

16.2- 21.2

16.8- 21.7

16.9- 22.6

16.8-

22.5 14.2-18 16.4-20.6

Chest depth range 7.4-10.9 6.9-10.6 7.2-11.3 7.1-11 7.3-12.1 7.4-12.2 7.2-10.2 6.9-10.6 Thigh circumference range 18.5-25 17.1-25

20.2- 27.6

17.6- 26.3

18.6- 29.2

19.1- 29.7

17.8-

25.2 17.1-25

Standing height 61.2 64.1 71.5 69 77 76.4 59.2 64 Nude Weight range 103 lbs to 245 lbs

3.4.2. Aircrew Flight Equipment (AFE) Compatibility

The BA-X shall be compatible with and not degrade the performance of aircrew or standard AFE configurations IAW T.O. 14-1-1.

3.4.2.1. Hanging Harness

Shall not interfere with the aircrew member’s performance of all necessary hanging harness procedures as specified in T.O. 14D1-2-1 with full equipment loads IAW T.O. 14-1-1.

3.4.2.2. Survival/Rescue Compatibility

The BA-X shall not interfere with or degrade the performance of any survival/rescue equipment or procedures.

3.4.2.3. Emergency Over the Horizon Beacon Accessibility

The URT-46 Beacon shall be accessible by AFE technicians to where they do not affect the integrity of the pack to allow for battery and mode setting changes.

3.4.2.4. LPU-38/P Compatibility

The BA-X shall allow for installation of the LPU-38/P life preserver without interference with the user’s helmet, head, and neck. Method of attachment shall be IAW 3.5.9 of this specification. The BA-X shall allow for positive inflation of the LPU when in the water and must be positioned in such a way that it keeps the crew member’s head above water.

3.4.3. Aircraft Compatibility

The BA-X shall not degrade the safety, effectiveness, and performance of aircrew members in all non-ejection crew duty stations in the B-52H, nor interfere with ingress/egress (including emergency ground) requirements.

3.4.3.1. Snagging Hazards

The BA-X shall minimize snagging hazards while worn by the crewmember in the aircraft.

3.4.3.2. Inadvertent Actuation

Inadvertent actuation of the BA-X shall not cause an unsafe condition on the aircraft and shall not damage the aircraft.

3.4.3.3. Aircraft Modifications

The BA-X shall not require any aircraft modifications.

3.4.3.4. Universal Water Activated Release System (UWARS) Integration The BA-X shall integrate with the UWARS during operation, when being installed or removed from the aircraft, and while left on the aircraft ready for use (prepositioned).

3.4.3.5. Static Line Integration

The BA-X shall allow for static line deployment of incapacitated aircrew members via direct attachment of the static line to the AAD arming mechanism.

3.5. Physical Characteristics

3.5.1. System Donning

All aircrew shall perform BA-X donning unassisted in 20 seconds or less.

3.5.2. System Doffing

The BA-X shall be removed without assistance, separating the entire system from the crewmember in 10 seconds or less.

3.5.3. Inadvertent Function

The BA-X and the AAD (Automatic Activation Device) shall not inadvertently function nor shall secured points become unsecured during use within the conditions defined in this specification.

3.5.3.1. Windblast

The BA-X, including the AAD, shall not inadvertently function at bailout windblast speeds up to 250 KEAS.

3.5.4. Physical Constraints

3.5.4.1. Dimensions

The base BA-X configuration with AAD and all accessories shall not exceed 24” high by 14.5” wide by 4.4” thick [T], 22” high by 14” wide by 4” thick [O].

3.5.4.2. BA-X Weight

Weight of basic parachute equipped with AAD and excluding Oxygen bottle and PLD shall not exceed 22 lb [T], 17 lb [O].

3.5.4.3. Pack Color

The BA-X shall use common colors IAW AMS-STD-595.

3.5.4.4. Canopy Color

The BA-X canopy shall be color-coded in the sequence as follows:

• Approximately 36 percent international orange IAW AMS-STD-595, Color Number

12197; then

• Approximately 36 percent white IAW AMS-STD-595, Color Number 37875; then

• Approximately 14 percent sand shade IAW AMS-STD-595, Color Number 33303; then

• Approximately 14 percent olive green IAW AMS-STD-595, Color Number 34256.

3.5.4.5. Ripcord Pull Force

The ripcord pull force causing activation shall be a minimum of 15 lbf and a maximum of 22 lbf.

3.5.4.6. Ripcord Compatibility

The ripcords shall be compatible with freefall applications.

3.5.4.7. Ripcord Travel

The parachute activation sequence shall be initiated by a ripcord travel of 0.5 to 1.5 in.

3.5.4.8. Ripcord Handle Free Pull Distance

The Pull Distance the Ripcord Handle shall be able to be moved without causing Ripcord Travel is 1.5 to 3.0 in.

3.5.5. Ripcord Pin Protection

Ripcord pins shall be protected from bending.

3.5.6. Sizing Reference

The BA-X shall include sizing reference numbers, based on manufacturer sizing scheme, on adjustment webbing to aid in user fitting.

3.5.7. Parachute Automatic Release

3.5.7.1. Time Delay

The BA-X AAD shall have a 5 second time delay that begins after the AAD activation handle is pulled and the AAD Activation Altitude condition is met.

3.5.7.2. AAD Activation Altitude

Automatic activation shall be initiated after the Time Delay if altitude is less than or equal to 14,000 ± 1,000 ft MSL.

3.5.7.3. Working Temperature

The AAD shall operate correctly after being exposed to the following temperature range -65°F to 145°F.

3.5.7.4. AAD Service Life

The AAD shall have a service life of 15 years [T]; 20 years [O].

3.5.8. Personnel Lowering Device (PLD)

The BA-X shall have attachment points for the personnel lowering device PCU-10/P.

3.5.9. Accessory Components

The BA-X shall include D-rings for the attachment of LPU D-Rings, LPU attachment zipper(2” below seam tape), an external pocket for optional use of MD-1 & 2 Bail Out Oxygen Bottles, stows or method of routing and securing oxygen hose from MD-1 & 2 Oxygen Bottles, and an external inspection data pocket to hold AFTO Form 391 (approximately 5” x 3” x 1/8”, or folded in half will fit MS70094 pocket).

3.5.10. Fitting

The BA-X shall require less than 5 minutes to adjust fitment to the user.

3.6. Egress Conditions

The BA-X canopy shall deploy correctly when initiated from all combinations of speed, altitude, aircrew weight and all other parameters provided in this specification.

3.6.1. Speed

The BA-X canopy shall deploy and inflate safely IAW this specification, after bailouts that begin in the speed range of 85 to 250 knots equivalent airspeed (KEAS). “Begin” here refers to the speed at which the aircrew exits the aircraft, not the speed at which the parachute deploys.

3.6.2. Altitude

The BA-X canopy shall deploy and inflate safely when initiated from between 500 ft to 14000 ft mean sea level (MSL).

3.6.3. Rate of Descent

3.6.3.1. Vertical Velocity

The velocity component of the BA-X normal to the ground shall be less than 23 ft/s [T], 21 ft/s [O], at 350 lb gross weight and standard sea level conditions.

3.6.3.2. Horizontal Velocity

The magnitude of the velocity components of the BA-X parallel to the ground shall be less than 15 ft/s at 350 lb gross weight and standard sea level conditions.

3.6.4. Canopy Collapse Prevention

After deployment, the parachute canopy shall not have a propensity to collapse.

3.6.5. Deceleration Magnitude

The peak chest acceleration magnitude during parachute deployment and inflation shall be less than 15 g.

3.6.6. Oscillation

The BA-X steady state descent oscillation shall not exceed ±10° from vertical for all weights in surface winds up to 15 mph.

3.6.7. Parachute Maneuverability

The system shall provide the crew member control over steering the parachute during descent equal to 10 degrees/sec [T], 20 degrees/sec [O].

3.6.8. Parachute Landing

Upon landing, the aircrew member must be able to disengage from the parachute risers using the quick release fittings.

3.7. Environmental Requirements

The context of “operate” as used in this section means to meet all the requirements of this specification without performance degradation.

3.7.1. Storage Temperatures

The BA-X shall remain structurally intact and meet the performance requirements of this document after exposure to storage temperatures from -65°F to 160°F (-54°C to 71°C) IAW MIL-

STD-810G.

3.7.2. Operating Temperatures

The BA-X shall remain structurally intact and meet the performance requirements of this document during exposure to operating temperatures from -65°F to 145°F (-54°C to 63°C) IAW

MIL-STD-810G.

3.7.3. Humidity

The BA-X shall remain structurally intact and meet the performance requirements of this document when exposed to a humidity levels up to 100% relative humidity IAW MIL-STD- 810G.

3.7.4. Rain

document when exposed to a rainfall rate of 4 inches per hour in a 40 mph wind.

3.7.5. Solar Radiation

document when exposed to solar radiation at a rate of 1120 W/m2 at 49°C (120°F).

3.7.6. Blowing Dust

The BA-X in storage configuration shall remain structurally intact and meet the performance requirements of this document after exposure to blowing dust.

3.7.7. Blowing Sand

The BA-X in storage configuration shall remain structurally intact and meet the performance requirements of this document after exposure to blowing sand.

3.7.8. Fungus

The BA-X shall be made of materials resistant to fungal growth.

3.7.9. Vibration

The BA-X shall operate after being exposed to the vibration environment of all MDSs listed in section 1.1.

3.7.10. Shock

The BA-X shall remain structurally intact and meet the performance requirements of this document after exposure to functional and transit shock.

3.7.11. Salt Fog

The BA-X shall withstand the effects of salt fog exposure, remain structurally intact and meet the performance requirements of this document after exposure.

3.7.12. Contamination by Fluids

The BA-X shall meet the performance of this specification with incidental contact with substances common to the military aviation environment and not be degraded.

3.7.13. Explosive Decompression

The BA-X shall withstand exposure to explosive decompression without damage or inadvertently activating.

3.7.14. Electromagnetic Interference and Compatibility

3.7.14.1. Susceptibility and Emissions

The BA-X, including the AAD, shall not be susceptible to damage or inadvertent actuation, nor emit electromagnetic radiation which will cause interference or malfunction of any aircraft component, instrument or control or any item stowed in the aircraft.

3.7.14.2. Electrostatic Discharge

The BA-X, including the AAD, shall withstand exposure to Electrostatic Discharge (ESD) without damage or inadvertently activating and continue to meet performance requirements after exposure.

3.8. Human Systems Integration

The BA-X shall be developed and designed with the human considered a primary system component.

Operators, maintainers, sustainers, trainers, and other support personnel shall be considered in hardware selection and system construction to maximize performance in all settings. The BA-X shall allow for maximum flexibility, comfort, and protection for all aircrew members during all missions.

The BA-X will conform with human factors engineering practices IAW MIL-STD-1472H.

3.9. Logistics

3.9.1. Reliability

The probability that the system shall meet its specified requirements over its service life shall be at least 0.98 at the 90 percent confidence level. This reliability is required in deployment and in opening, whether the parachute canopy is deployed automatically or manually.

3.9.2. Service Life

The BA-X, except for the AAD, shall be designed to have a service life (to include storage and operation) of 20 years [T], 25 years [O].

3.9.3. Maintainability

3.9.3.1. Time between Scheduled Repacks

The system shall meet reliability requirements with inspection or repack periods of 365 days [T], 730 days [O].

3.9.3.2. Mean Preventative Maintenance Time

The maintainer shall be able to complete preventative maintenance actions (to include unpack, inspection, and repack) within 2 hours.

3.9.3.3. AFE Maintenance

The BA-X shall be designed to be fitted, repaired, and maintained by a maintenance concept (Organizational) by three and five level AFE specialists (AFSC 1P0X1) using a Technical Order derived from a vendor supplied commercial manual.

3.9.4. Training

The BA-X shall employ the “Train the Trainer” concept and shall not require additional time be added to AFE and Aircrew training pipelines to implement maintenance and use training.

3.10. Nameplates and Product Markings

The BA-X shall be appropriately identified with a unique identification (UID) that is globally unique and unambiguous IAW MIL-STD-130. Each separable component shall be marked per contract requirements with at least the following information: Part number, US Government contract number, Serial number, Date of manufacture, Manufacturer’s CAGE code, and Date placed in service area left blank.

3.11. Packaging, Handling, and Transportation

3.11.1. Transportation

Packaging of BA-X shall be suitable for transportation by air, land, and sea and shall also be capable of movement by theater distribution systems.

3.11.2. Package Marking

System and all component marking and bar codes shall be IAW MIL-STD-129.

3.12. Environment, Safety, and Occupational Health (ESOH)

3.12.1. Safety

The BA-X shall be safe to operate, store, and maintain in its intended environment throughout its shelf and service life.

3.12.2. Safety and Health Hazard Management

The BA-X shall present no uncontrolled safety or health hazards during its shelf and service life.

3.12.3. Allergic Reaction

Materials shall be hypoallergenic and not cause allergic reaction or irritation of the user's skin.

4. VERIFICATION (Qualification Provisions) This section specifies the verification requirements to qualify the BA-X in meeting all the requirements in Section 3. Procurement activity may consider leveraging existing data for verification. Methods of verification are defined below.

Table 2. Verification Methods I Inspection Verification without the use of special laboratory appliances or procedures.

May include visual examination, simple physical manipulation, and/or mechanical and electrical gauging and measurement.

A Analysis Verification that utilizes established technical or mathematical models or simulations, algorithms, charts, graphs, or other scientific principles and procedures.

D Demonstration Verification that involves actual operation, adjustment, or reconfiguration of an item under specific scenarios. Items may be instrumented and quantitative limits of performance measured.

T Test Verification that involves thorough exercising of an item under specified conditions with instrumentation and data analysis accomplished IAW a set of applicable test procedures.

Table 3. Requirements Verification Traceability Matrix Performance Requirement Description Verification Verification Paragraph Method Paragraph

3.1 Workmanship I 4.1

3.1.1 Material Age I, A 4.1

3.1.2 Defects I 4.1

3.1.3 Cleanliness I 4.1

3.1.4 Edges I 4.1

3.2 FAA Certification I 4.2

3.3 Recycled, Recovered, or Environmentally

Preferable Materials A 4.3

3.4 Integration - 4.4

3.4.1 Aircrew - 4.4.1

3.4.1.1 Aircrew Weight A, T 4.4.1.1

3.4.1.2 Anthropometric Characteristics I, A, D 4.4.1.2

3.4.2 AFE Compatibility I, D 4.4.2

3.4.2.1 Hanging Harness I, D 4.4.2.1

3.4.2.2 Survival/Rescue Compatibility D 4.4.2.2

3.4.2.3 Emergency OTH BCN Accessibility D 4.4.2.3

3.4.2.4 LPU-38/P Compatibility D 4.4.2.4

3.4.3 Aircraft Compatibility I, D 4.4.3

3.4.3.1 Snagging Hazards I, D 4.4.3

3.4.3.2 Inadvertent Actuation I, D 4.4.3

3.4.3.3 Universal Water Activated Release

System (UWARS) integration I, D 4.4.3

3.4.3.4 Static Line Integration I, D 4.4.3

3.4.3.5 Aircraft Modifications I, D 4.4.3

3.5 Physical Characteristics 4.5

3.5.1 System Donning D 4.5.1

3.5.2 System Doffing D 4.5.2

3.5.3 Inadvertent Function I, A 4.5.3

3.5.3.1 Windblast D, T 4.5.3.1

3.5.4 Physical Constraints - 4.5.4

3.5.4.1 Dimensions I 4.5.4.1

3.5.4.2 BA-X Weight I 4.5.4.2

3.5.4.3 Pack Color I 4.5.4.3

3.5.4.4 Canopy Color I 4.5.4.4

3.5.4.5 Ripcord Pull Force D 4.5.4.5

Paragraph Method Paragraph

3.5.4.6 Ripcord Compatibility D 4.5.4.6

3.5.4.7 Ripcord Travel D 4.5.4.7

3.5.4.8 Ripcord Handle Free Pull Distance D 4.5.4.8

3.5.5 Ripcord Pin Protection A 4.5.5

3.5.6 Sizing Reference I 4.5.6

3.5.7 Parachute Automatic Release A, D, T 4.5.7

3.5.7.1 Time Delay A, D, T 4.5.7

3.5.7.2 AAD Activation Altitude A, D, T 4.5.7

3.5.7.3 Working Temperature A, D, T 4.5.7

3.5.7.4 AAD Service Life A, D, T 4.5.7

3.5.8 Personnel Lowering Device A, D 4.5.8

3.5.9 Accessory Components I, D 4.5.9

3.5.10 Fitting I, D 4.5.10

3.6 Egress Conditions - 4.6

3.6.1 Speed T 4.6

3.6.2 Altitude T 4.6

3.6.3 Rate of Descent T 4.6

3.6.3.1 Vertical Velocity T 4.6

3.6.3.2 Horizontal Velocity T 4.6

3.6.4 Canopy Collapse Prevention D, T 4.6

3.6.5 Deceleration Magnitude T 4.6

3.6.6 Oscillation A, T 4.6

3.6.7 Parachute Maneuverability A, T 4.6

3.6.8 Parachute Landing T 4.6

3.7 Environmental Requirements T 4.7

3.7.1 Storage Temperatures T 4.7, 4.7.1

3.7.2 Operating Temperatures T 4.7, 4.7.2

3.7.3 Humidity T 4.7, 4.7.3

3.7.4 Rain T 4.7, 4.7.3

3.7.5 Solar Radiation T 4.7, 4.7.5

3.7.6 Blowing Dust T 4.7, 4.7.6

3.7.7 Blowing Sand T 4.7, 4.7.7

3.7.8 Fungus T 4.7, 4.7.8

3.7.9 Vibration T 4.7, 4.7.9

3.7.10 Shock T 4.7, 4.7.10

3.7.11 Salt Fog T 4.7, 4.7.11

3.7.12 Contamination by Fluids T 4.7, 4.7.12

3.7.13 Explosive Decompression T 4.7, 4.7.13

3.7.14 Electromagnetic Interference and

Compatibility T 4.7, 4.7.14

3.7.14.1 Susceptibility and Emissions A, T 4.7, 4.7.14.1

Paragraph Method Paragraph

3.7.14.1 Electrostatic Discharge A, T 4.7, 4.7.14.1

3.8 Human Systems Integration A, D 4.8

3.9 Logistics - 4.9

3.9.1 Reliability A, T 4.9.1

3.9.2 Service Life A, T 4.9.2

3.9.3 Maintainability - 4.9.3

3.9.3.1 Time Between Scheduled Repacks A, D 4.9.3.1

3.9.3.2 Mean Preventative Maintenance Time A, D 4.9.3.2

3.9.3.3 AFE Maintenance A, D 4.9.3.3

3.9.4 Training D 4.9.4

3.10 Nameplates and Product Markings I 4.10

3.11 Packaging, Handling, and Transportation - 4.11

3.11.1 Transportation I, A 4.11.1

3.11.2 Package Marking I, A 4.11.2

3.12 Environmental, Safety, and Occupational

Health (ESOH)

- 4.12

3.12.1 Safety I, A 4.12.1

3.12.2 Safety and Health Hazard Management I, A 4.12.2

3.12.3 Allergic Reaction I, A 4.12.3

4.1. Workmanship

Sections 3.1.1 through 3.1.4 shall be verified by analysis of vendor drawings, data, material certifications, and by inspection.

4.2. FAA Certifications

The vendor shall supply proof of FAA certification and test data.

4.3. Recycled, Recovered, or Environmentally Preferable Materials Shall be verified by analysis of vendor design and/or material list(s) and certifications provided to the government.

4.4. Integration

4.4.1. Aircrew

4.4.1.1. Aircrew Weight

Shall be verified by analysis and in conjunction with section 4.6 Egress Conditions.

4.4.1.2. Anthropometric Characteristics

Shall utilize fit mapping with human subjects and BA-X. The contractor shall use a representative population sample to determine compliance with Paragraph 3.4.1.

4.4.2. AFE Compatibility

Requirement shall be verified through inspection and demonstration with all listed MDSs in section 1.1 with standard AFE configurations IAW T.O. 14-1-1.

4.4.2.1. Hanging Harness

The hanging harness test shall be conducted using three subjects (minimum). The anthropometric body size range of the individuals shall be IAW (In Accordance With) section

4.5.1 System Donning. Test subjects shall be configured with the BA-X and AFE configurations identified in T.O. 14-1-1 and be suspended in a hanging harness. Each test subject shall demonstrate each configuration.

4.4.2.2. Survival/Rescue Compatibility

A demonstration with SERE personnel shall verify that the BA-X can successfully integrate with survival/rescue CONOPs and TTPs.

4.4.2.3. Emergency OTH BCN Accessibility

A demonstration shall be performed with AFE personnel to verify that they can access the URT-46 beacon to make battery and mode selection changes without affecting BA-X integrity.

4.4.2.4. LPU-38/P Compatibility

A demonstration shall be performed with aircrew to verify that the BA-X with LPU-38/P installed does not obstruct the user’s helmet, head, and neck. A water demonstration shall verify that the LPU-38/P when installed on the BA-X is capable of fully inflating and keeping the user’s head above water.

4.4.3. Aircraft Compatibility

Shall be verified through inspection and demonstration at all crew duty stations. Safety, effectiveness, and performance assessments shall be made during performance of mission duties such as preflight, ingress, normal in-flight duties, emergency procedures, egress, and post-flight procedures utilizing aircraft qualified test subjects to validate compatibility and non-interference.

4.5. Physical Characteristics

4.5.1. System Donning

Donning shall be demonstrated using at least three subjects. Test subjects shall target Table 1 JPATS cases 2, 5, and 7. At least one subject shall be female. Test subjects shall don, without assistance, while wearing each AFE configuration in Table 3. Testing shall be accomplished in conjunction with section 4.6 Egress Conditions.

4.5.2. System Doffing

Doffing shall be demonstrated utilizing the same test subjects in the same ensemble types as specified in 4.5.1. Testing shall be accomplished in conjunction with section 4.6 Egress conditions.

4.5.3. Inadvertent Function

Shall be verified by analysis of design and inspection of final system. Data shall be collected during all other tests and from test subject survey.

4.5.3.1. Windblast

Shall be verified by demonstration and tests.

4.5.4. Physical Constraints

4.5.4.1. Dimensions

Shall be verified by inspection.

4.5.4.2. BA-X Weight

4.5.4.3. Pack Color

4.5.4.4. Canopy Color

4.5.4.5. Ripcord Pull Force

Shall be verified by demonstration.

4.5.4.6. Ripcord Compatibility

4.5.4.7. Ripcord Travel

4.5.4.8. Ripcord Handle Free Travel Pull Distance

4.5.5. Ripcord Pin Protection

Shall be verified by analysis of design.

4.5.6. Sizing Reference

4.5.7. Parachute Automatic Release

Shall be verified by analysis and during parachute drop tests.

4.5.8. Personnel Lowering Device (PLD)

Shall be verified by analysis and demonstration.

4.5.9. Accessory Components

Shall be verified by inspection and demonstration.

4.5.10. Fitting

Shall be verified by inspection and demonstration.

4.6. Egress Conditions

Parachute drop and jump tests shall be performed using torso manikins and live jumpers to cover the weight, speed, and altitude range of 3.6. They will be augmented with AFE such that the maximum weight tested shall be 350lbs and the minimum weight tested shall be 120lbs. 114 tests shall be conducted in total. Data on BA-X oscillation in wind shall be verified by test data collected during Parachute drop/live jump testing. Maneuverability and landing shall be verified using live jumps.

4.7. Environmental Conditions

The BA-X shall be subjected to the environmental tests described in the following sections. Testing shall use the same articles for multiple Environmental Conditions tests to demonstrate BA-X environmental resistance. Individual tests, as well as combinations of some environmental tests, could influence subsequent testing. Therefore, guidance for test sequence identified in Paragraph

2.1.2 of each Test Method in MIL-STD-810G shall be strictly adhered to.

The BA-X shall be visually inspected for any damage and degradation immediately prior to and immediately following each test. The BA-X shall not inadvertently function during any environmental test. BA-X systems shall be subjected to jump tests of 4.6 at the conclusion of Environmental Conditions testing. The BA-X shall function within performance specification requirements following Environmental Conditions testing. Results from testing on Environmental Conditions test articles shall be compared to test articles not subjected to Environmental Conditions testing to document any resulting physical damage and/or functional degradation.

Environmental test requirements for the BA-X may be met by similarity to the existing Air Force back style parachute.

4.7.1. Storage Temperatures

The BA-X in its packed configuration for storage shall be tested IAW MIL-STD-810G, Method 501.6, High Temperature, Procedure I. The BA-X shall be subjected to a non-operating (storage) high temperature cycle exposure of 91°F to 160°F using the temperature and relative humidity conditions per Table 501.6-III, High temperature cycles, climatic category A1 – Hot Dry (Induced Conditions), for seven 24 hour cycles.

The system shall be subjected to low temperature IAW MIL-STD-810G, Method 502.6 Low Temperature, Procedure I. Exposure duration shall be 72 hours minimum at -65°F (-54°C).

4.7.2. Operating Temperatures

The BA-X in its operational configuration shall be tested IAW MIL-STD-810G, Method 501.6, High Temperature, Procedure II. The temperature profile shall be constant at 145°F (63°C).

The BA-X in its operational configuration shall be tested IAW MIL-STD-810G, Method 502.6, Low Temperature, Procedure II. The temperature profile shall be constant at -65°F (-54°C).

4.7.3. Humidity

The system shall be subjected to humidity IAW MIL-STD-810G, Method 507.6, Procedure II.

The BA-X shall be exposed to ten 24-hour cycles IAW, Figure 507.6-7, Aggravated temperature-humidity cycle.

4.7.4. Rain

The system shall be subjected to rain IAW MIL-STD-810G, Method 506.6, Procedure I or equivalent. Rain exposure shall be 4 inches per hour with a 40 mph wind.

4.7.5. Solar Radiation

The system shall be subjected to solar radiation IAW MIL-STD-810G, Method 505.6, Procedure II. Test duration shall be ten 24 hour cycles with an irradiance intensity of 1120 ± 47 W/m2 at 120°F (49°C) with 4% relative humidity.

4.7.6. Blowing Dust

The system shall be subjected to blowing dust IAW MIL-STD-810G, Method 510.6, Procedure I.

Air velocities shall be 8.9 m/s (1750 ft/min). Test article shall be set-up on a test manikin and worn as if in an operational environment. Red china clay shall be the dust composition. Particle concentration shall be maintained at 10.6 ± 7 g/m3 (0.3 ± 0.2 g/ft3) for the duration of the test.

Particle size distribution shall be 100% by weight less than 150 μm. In order to simulate the effects of multidirectional winds, the test item shall be rotated at 90 minute intervals to expose all faces (top, bottom, and all four sides) to the test environment. Test duration shall be nine hours at 23°C and an additional nine hours at 71°C. Humidity shall be kept at or below 30% relative humidity for the duration of the test.

4.7.7. Blowing Sand

The system shall be subjected to blowing sand IAW MIL-STD-810G, Method 510.6, Procedure II. Air velocities shall be 18 to 29 m/s (3540 to 5700 ft/min). Test article shall be set-up on a test manikin and worn as if in an operational environment. Silica sand (at least 95% by weight SiO2) shall be used for the test. The particle size distribution shall be from 150 μm to 850 μm, with a mean of 90 ± 5% by weight smaller than 600 μm and larger than 149 μm, and at least 5% by weight 600 μm and larger. In order to simulate the effects of multidirectional winds, the test item shall be rotated at 90 minute intervals to expose all faces (top, bottom, and all four sides) to the test environment. Test duration shall be nine hours at 71°C. Humidity shall be kept at or below 30% RH for the duration of the test.

4.7.8. Fungus

The system shall be subjected to fungus IAW MIL-STD-810G, Method 508.7. Test duration shall be 84 days. Either the U.S. fungus group (Table 508.7-I) or European fungus group (Table XXIII), as identified in MIL-STD-810G, shall be utilized for the test. If the U.S. fungus group is used, one type fungus from the European fungus group, Scopulariopsis brevicaulis, shall be added to the test group. Following visual inspection for damage, the BA-X shall be cleaned after testing to demonstrate the reversal effects of fungus removal. The BA-X shall be resistant to fungal growth, withstand the effects of fungus, remain structurally intact and meet the performance requirements of this document during and after exposure. Signs of fungal growth shall be evaluated and reported using Table 508.7-II from MIL-STD-810G.

4.7.9. Vibration

The system shall be subjected to operating vibration IAW MIL-STD-810G, Method 514.7.

Conduct vibration testing after and on the same test article used for high and low temperature testing to evaluate cumulative effects. All BA-X configurations shall undergo Test Category 4 - Test Procedure I, Test Category 7 - Test Procedure I, Test Category 8 - Test Procedure I, Test Category 12 - Test Procedure I, Test Category 13 - Test Procedure I, and Test Category 14 - Test Procedure I. The BA-X shall also undergo gunfire vibration testing IAW MIL-STD- 810G, Method 519.7. The BA-X shall undergo a B-52H platform specific vibration test using a spectrum the BA-X is likely to encounter in operational use. Materiel is deemed to have failed if it suffers permanent deformation or fracture; if any fixed part or assembly loosens; if any moving or movable part of an assembly becomes free or sluggish in operation; if any movable part or control shifts in setting, position or adjustment, and if test item performance does not meet specification requirements while exposed to functional levels and following endurance tests.

4.7.10. Shock

The BA-X shall be tested IAW MIL-STD-810G Method 516.7, Procedure I (Functional Shock), IV (Transit Drop), Procedure V (Crash Hazard), and Procedure VI (Bench Handling). For

Procedure IV, the BA-X shall be dropped different ways at height of six feet. Shock testing shall be done after and on the same test item used for vibration testing.

4.7.11. Salt Fog

The BA-X shall be subjected to salt fog IAW MIL-STD-810G, Method 509.6 . The test shall consist of a minimum of four alternating 24-hour periods of salt fog exposure and drying conditions (two wet and two dry). Test chamber temperature shall be maintained at 35 ± 2°C. A 5% -±1% salt solution concentration shall be used with a fall-out rate such that each receptacle collects 2±1 ml of solution per hour for each 80cm2 of horizontal collection area (10cm diameter).

4.7.12. Contamination by Fluids

The BA-X shall be subjected to chemical testing IAW MIL-STD-810G, Method 504.2, Procedure I, intermittent contamination option. In addition to the fluids listed in Table 504.2-I of MIL-STD- 810G, the following contaminants shall be tested: MIL-H-82382 hydraulic fluid, and MIL-L- 7808 aircraft engine lubricant. Test lubricant temperatures shall be as listed in Table 504.2-I.

Test item temperature shall be 52°C ± 2°C (125°F ± 3.6°F). The BA-X shall be visually and functionally checked immediately after the chemical profile and results shall be compared with pretest data. Following testing, the test item shall be stored for a period of 30 days and then visually and functionally tested to evaluate the long term effects of exposure to chemicals.

4.7.13. Explosive Decompression

Explosive decompression testing shall be IAW MIL-STD-810G, Method 500.6, Procedure IV.

The BA-X shall not inadvertently function during decompression. The BA-X shall be visually inspected for damage following testing.

4.7.14. Electromagnetic Interference and Compatibility

4.7.14.1. Susceptibility, Emissions, and Electrostatic Discharge The system shall be tested IAW MIL-STD-461 Paragraphs 5.16 to 5.21.

4.8. Human Systems Integration

Shall be verified by demonstration and analysis.

4.9. Logistics

4.9.1. Reliability

Verification of mission reliability shall be calculated through analysis using USAF jump tests and FAA certification.

4.9.2. Service Life

The service life shall be verified through accelerated service life testing and environmental test data. The accelerated service life test shall simulate the forces acted on the parachute during unpacking/repacking for the equivalent of 25 years and will be performed by unpacking/repacking the parachute 25 times. Analysis shall be performed on the results of environmental test data to further verify service life requirements. After the service life testing, the BA-X and all its components shall show no signs of cracking, corrosion, thermal degradation, delamination, or wear and shall remain structurally intact and meet the performance requirements of this specification.

4.9.3. Maintainability

4.9.3.1. Time between Scheduled Repacks

Shall be verified through reliability analysis and maintenance demonstrations.

4.9.3.2. Mean Preventative Maintenance Time

Shall be verified through reliability analysis and maintenance demonstrations.

4.9.3.3. AFE Maintenance

Shall be verified by demonstration and analysis of technical data.

4.9.4. Training

Shall be verified through demonstration using the “Train the Trainer” concept to ensure AFE technicians as well as aircrew members can be taught how to maintain and use the BA-X without having to increase current training pipeline durations.

4.10. Nameplates and Product Markings

Shall be verified by inspection of drawings and hardware.

4.11. Packaging, Handling, and Transportation

4.11.1. Transportation

Shall be verified by analysis and inspection of drawings.

4.11.2. Package Marking

Shall be verified by analysis and inspection of drawings.

4.12. Environment, Safety, and Occupational Health (ESOH)

4.12.1. Safety

Shall be verified through inspection and analysis.

4.12.2. Safety and Health Hazard Management

Shall be verified by inspection and analysis.

4.12.3. Allergic Reaction

Shall be verified by inspection and analysis.

5. PACKING, HANDLING, STORAGE AND TRANSPORATION

5.1. Packing

Unless otherwise specified in the contract, systems, components, and parts to be delivered shall be preserved and packaged in a manner that will afford adequate protection against corrosion, deterioration, and physical damage during shipment from the supply source to the first receiving activity. The level of preservation and packaging in general shall conform to the uniform freight classified rules or other applicable carrier rules, and may be the supplier’s commercial practice when such meets the requirements of this level.

5.2. Labeling

All containers shall be tagged or labeled to identify and quantify the items and indicate dates of acquisition. The internal sealed bag shall be marked as a unit pack in accordance with MIL-STD- 129, MIL-STD-130, and the DoD Guide to Uniquely Identifiable Items, and the outer fiberboard shipping container shall also be marked in accordance with MIL-STD-129. Minimum information to be included on both the internal sealed bag and the outer shipping container shall be: National Stock Number, Noun, Serial Number, Part Number, Unit of Issue, Unique Identification Code, and Quantity, Manufacturer CAGE Code, Contract Number, Date Packed, and “Warranted Item.”

5.3. Shipment Marking

All shipping containers shall be tagged or stamped with all the marking necessary for delivery and storage, all markings required by regulations, statutes and common carriers, and all markings necessary for safety and safe delivery.

6. Notes

6.1. Special Definitions

The following provides definitions for terms unique to this specification:

AGL Above Ground Level AAD Automatic Activation Device BA-X Back-Automatic Parachute CBRN Chemical, Biological, Radiological, Nuclear EMP Electromagnetic Pulse ESD Electrostatic Discharge IAW In Accordance With KEAS Knots Equivalent Airspeed NBC Nuclear, Biological, and Chemical NVG Night Vision Goggle PLD Personnel Lowering Device UID Unique Identification GSA Government Services Administration DLA Defense Logistics Agency SBSS Standard Base Supply System AFEMS Air Force Equipment Management System

3.9.4. Training