Attachment_1_-_E-MMPS-PRF-0001V3.0.pdf

UNCLASSIFIED

E-MMPS-PRF-0001V3.0

Performance Specification for the Enhanced-Multi Mission Parachute System

(E-MMPS)

Prepared for:

Product Manager

Marine Corps Systems Command Reconnaissance and Amphibious Raids

2200 Lester Street Quantico, VA 22134-6050

APPROVED FOR USE AS

FUNCTIONAL BASELINE BY: _________________________________ DATE: ____________

LtCol Christopher Madeline Product Manager Marine Corps Systems Command Reconnaissance and Amphibious Raids

DISTRIBUTION STATEMENT A: Approved for public release. Distribution is unlimited.

INCH-POUND

Comments, suggestions, or questions on this document should be addressed to Product Manager Reconnaissance and Amphibious Raids (PdM RAR), 2200 Lester Street, Quantico, VA 22134-6050.

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Record of Changes Date Revision Reason for Change Approved By

Jan 2017 2.0 Original Document Acting PdM May 2017 3.0 SRR/SFR Revisions PM iii

Table of Contents

1. SCOPE

1.1. SCOPE

1.2. BACKGROUND

2. APPLICABLE DOCUMENTS

2.0. GENERAL

2.1. GOVERNMENT DOCUMENTS

2.1.1. Specifications, Standards, and Handbooks

2.1.2. Other Government Documents, Drawings, and Publications

2.2. NON-GOVERNMENT PUBLICATIONS

2.3. ORDER OF PRECEDENCE

3. REQUIREMENTS

3.1. DELETED

3.2. MAJOR COMPONENTS

3.2.1. Harness Container

3.2.2. Main Canopy Assembly. This functional main canopy assembly shall include a minimum of the

3.2.3. Reserve Canopy Assembly

3.2.4. Deleted

3.2.5. Soft Canopy Stuff Sack

3.2.6. Soft E-MMPS Storage Bag

3.3. FUNCTIONAL IDENTIFICATION AND MARKINGS

3.3.1. System Marking

3.3.2. Harness Container Data Card Pocket

3.3.3. Harness Container Color and Size Marking

3.3.4. Main Canopy Marking

3.3.5. Reserve Canopy Marking

3.3.6. Suspension Line Attachment Point Marking

3.3.7. Main Canopy Color

3.3.8. Reserve Canopy Color

3.3.9. Item Unique Identification Marking

3.3.10. Reserve Flap Marking

3.4. SYSTEM AND HARNESS CONTAINER FUNCTIONS AND FEATURES

3.4.1. Rapid Reserve Deployment Feature

3.4.2. Riser Release Safety Feature

3.4.3. Container Closure

3.4.4. Deployment Configurations

3.4.5. Operational and Emergency Procedures

3.4.6. Equipment Attachment Points

3.4.7. Deleted

3.4.8. Soft Canopy Stuff Sack

3.4.9. Soft E-MMPS Storage Bag

3.4.10. Interfaces

3.4.11. Aircraft Compatibility

3.4.12. Fitment

3.4.13. Service Life and Environmental Factors

3.4.14. Reliability

3.4.15. Preventative Maintenance Checks and Services

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3.5. MAIN CANOPY FUNCTIONS

3.5.1. Weight Requirement

3.5.2. Deployment Altitude Range

3.5.3. Horizontal Travel

3.5.4. Glide Modulation

3.6. RESERVE CANOPY FUNCTIONS

3.6.1. Weight Requirement

3.6.2. Emergency Deployment Altitude Range

3.6.3. Horizontal Travel

3.6.4. Glide Modulation

3.7. E-MMPS DETECTION MITIGATION

3.7.1. Audible Detection

3.7.2. Visual Detection

4. VERIFICATION

4.1. GENERAL

4.1.1. Methods of Verification

4.1.2. Test Equipment Accuracy

4.1.3. Types of Inspection/Test

4.2. MAJOR COMPONENTS

4.2.1. Harness Container

4.2.2. Main Canopy Assembly

4.2.3. Reserve Canopy Assembly

4.2.4. Deleted

4.2.5. Soft Canopy Stuff Sack

4.2.6. Soft E-MMPS Storage Bag

4.3. FUNCTIONAL IDENTIFICATION AND MARKINGS

4.3.1. System Marking

4.3.2. Harness Container Data Card Pocket

4.3.3. Harness Container Color and Size Marking

4.3.4. Main Canopy Marking

4.3.5. Reserve Canopy Marking

4.3.6. Suspension Line Attachment Point Marking

4.3.7. Main Canopy Color

4.3.8. Reserve Canopy Color

4.3.9. Item Unique Identification Marking

4.3.10. Reserve Flap Marking

4.4. SYSTEM AND HARNESS CONTAINER FUNCTIONS AND FEATURES

4.4.1. Rapid Reserve Deployment Feature

4.4.2. Riser Release Safety Feature

4.4.3. Container Closure

4.4.4. Deployment Configurations

4.4.5. Operational and Emergency Procedures

4.4.6. Equipment Attachment Points

4.4.7. Deleted

4.4.8. Soft Canopy Stuff Sack

4.4.9. Soft E-MMPS Storage Bag

4.4.10. Interfaces

4.4.11. Aircraft Compatibility

4.4.12. Fitment

4.4.13. Service Life and Environmental Factors

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4.4.14. Reliability

4.4.15. Preventative Maintenance Checks and Services

4.5. MAIN CANOPY FUNCTIONS

4.5.1. Weight Requirement

4.5.2. Deployment Altitude Range

4.5.3. Horizontal Travel

4.5.4. Glide Modulation

4.6. RESERVE CANOPY FUNCTIONS

4.6.1. Weight Requirement

4.6.2. Emergency Deployment Altitude Range

4.6.3. Horizontal Travel

4.6.4. Glide Modulation

4.7. E-MMPS DETECTION MITIGATION

4.7.1. Audible Detection

4.7.2. Visual Detection

4.8. RESPONSIBILITY AND CERTIFICATION

4.8.1. Responsibility for Inspection

4.8.2. Responsibility for Compliance

4.8.3. Certification

5. PACKAGING

6. NOTES

6.1. ACQUISITION REQUIREMENTS

6.2. DEFINITIONS

1. SCOPE.

1.1. Scope. This specification describes the performance requirements for the Enhanced-Multi Mission Parachute System (E-MMPS).

1.2. Background. The United States Marine Corps (USMC) currently uses the Multi Mission Parachute System (MMPS), which is an Advanced Ram Air Parachute System (ARAPS). The E- MMPS, therefore, is derived from the Advanced Ram Air Parachute System ARAPS Statement of Need (SON) requirement, and will be a lifecycle replacement for the MMPS parachute system.

The E-MMPS will be configured to meet specific mission requirements for various methods of free-fall and static-line parachute insertions. The glide capability of the E-MMPS will provide commanders the means to conduct increased standoff infiltrations into designated areas. E-MMPS will also allow proper fitment for the full range of Marines (5th percentile female to 95th percentile male).

2. APPLICABLE DOCUMENTS.

2.0. General. The documents listed in this section are specified in sections 3 and 4 of this performance specification. This section does not include documents 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 and 4 of this performance specification, whether or not they are listed here.

2.1. Government Documents.

2.1.1. Specifications, Standards, and Handbooks. The following specifications, standards, and handbooks of the exact revision listed below 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-A-70625 Automated Acceptance Inspection Equipment Design, Testing and Approval, of

MIL-STD-882 Standard Practice for System Safety

MIL-STD-130 Identification Marking of U.S. Military Property

MIL-STD-1472 Human Engineering

MIL-DTL-6645J Parachutes, Personnel, General Specification for

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

2.1.2. Other Government Documents, Drawings, and Publications. The following other Government documents, drawings, and publications of the exact revision level below 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.

UNITED STATES MARINE CORPS TECHNICAL MANUALS

TM 70244A-OI U.S. Marine Corps Technical Manual for Military Freefall Operations

TM 11168A-OI U.S. Marine Corps Technical Manual for Multi Mission Parachute System (MMPS)

(Copies of these documents are available for download from https://mceits.usmc.mil/sites/pubs/default.aspx)

TECHNICAL REPORTS

NATICK/TR-11/017 Measurer’s Handbook: US Army and Marine Corps Anthropometric Surveys, 2010-2011

(Copies of this document are available for download from http://www.dtic.mil/get-tr-doc/pdf?AD=ADA548497)

NATICK/TR-13/018 2010 Anthropometric Survey of U.S. Marine Corps

Personnel: Methods and Summary Statistics

(Copies of this document are available for download from http://www.dtic.mil/get-tr-doc/pdf?AD=ADA581918)

2.2. Non-Government Publications. The following other documents, drawings, and publications of the exact revision level below 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.

AMERICAN SOCIETY FOR TESTING AND MATERIALS

ASTM D737-96 Standard Test Method for Air Permeability of Textile Fabrics

(Copies of this document are available for download at http://www.usapa.army.mil/)

PARACHUTE INDUSTRY ASSOCIATION

PIA TS 135 v1.4 Performance Standards for Personnel Parachute Assemblies and Components

(Copies of this document are available for download at http://www.pia.com/)

2.3. Order of Precedence. In the event of a conflict between the text of this document and the references 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.

3. REQUIREMENTS.

3.1. Deleted.

3.2. Major Components. All components shall be included as part of the E-MMPS, intact and undamaged. The E-MMPS shall include the following major components:

3.2.1. Harness Container. Including harness, detachable radio pocket, detachable parachute oxygen system pocket, and technical manual.

3.2.2. Main Canopy Assembly. This functional main canopy assembly shall include a minimum of the main parachute, slider, risers, suspension lines and control lines.

3.2.3. Reserve Canopy Assembly. This functional reserve canopy assembly shall include a minimum of the reserve static line, reserve parachute, slider, suspension lines and control lines.

3.2.4. Deleted.

3.2.5. Soft Canopy Stuff Sack.

3.2.6. Soft E-MMPS Storage Bag.

3.3. Functional Identification and Markings.

3.3.1. System Marking. The E-MMPS operating limits as defined both in section 4.2 and in Table 1 of PIA TS 135 shall be marked or placarded in a pocket on the parachute harness container (pack). Intent is to clearly label system and components with minimum and maximum operating limits and to include altitude parameters. The lowest maximum operating weight of any component in the assembly (canopy, harness, etc.) and the lowest maximum pack opening speed of any component (canopy, harness, etc.) shall be included. Allowable omission exceptions to the Table 1 list will be: the TSO authorization statement, average peak force measurements and maximum drogue deployment speed.

3.3.2. Harness Container Data Card Pocket. The harness container for the E-MMPS shall be provided with a parachute data card pocket constructed such that the data card will not be lost, damaged or interfere with the parachutist operation of the system. The pocket shall be readily accessible when the parachute is packed in the container and when the user is donning the parachute assembly.

3.3.3. Harness Container Color and Size Marking. The harness container shall be Coyote, Code 476/498 (FED-STD-595), in color and marked to easily differentiate between harness sizes (if two harness sizes are used).

3.3.4. Main Canopy Marking. The E-MMPS main canopy and components shall include the following markings:

• Manufacturers Name, Code or Symbol (main)

• Part Number (main and all components)

• Serial or Lot Control Number (main, drogue, and pilot chutes)

• Date of Manufacture (main)

• Date Placed in Service - Blank (main)

• Maximum AUW (main)

• Minimum AUW (main)

3.3.5. Reserve Canopy Marking. Each reserve canopy shall be marked to show its approved use as follows:

• Single Harness Reserve Parachute Canopy

• Manufacturers Name, Code or Symbol (reserve)

• Part Number (reserve and all components)

• Serial or Lot Control Number (reserve and pilot chute)

• Date of Manufacture (reserve)

• Date Placed in Service - Blank (reserve)

• Maximum AUW (reserve)

• Minimum AUW (reserve)

3.3.6. Suspension Line Attachment Point Marking. Each group of suspension line attachment points (main and reserve) shall be identifiable and distinguishable from adjacent groupings.

3.3.7. Main Canopy Color. The main canopy shall be silver in color. The associated deployment initiation devices and deployment control devices shall be of a color that is distinguishable between sizes (if two harness or canopy sizes are used).

3.3.8. Reserve Canopy Color. The reserve canopy shall be silver in color. The associated deployment initiation devices and deployment control devices shall be of a color that is distinguishable between sizes (if two harness or canopy sizes are used).

3.3.9. Item Unique Identification Marking. Any component or assembly valued at or above $5,000.00 shall be marked with Item Unique Identification (IUID) in accordance with MIL-STD- 130.

3.3.10. Reserve Flap Marking. The reserve flap shall be marked to indicate the production sequence number (for instance with two sizes: 0001-1999 for small & 2001-#### for large)

3.4. System and Harness Container Functions and Features.

3.4.1. Rapid Reserve Deployment Feature.

3.4.1.1. Reserve Static Line. The E-MMPS container shall incorporate a Reserve Static Line (RSL).

3.4.1.2. Main-Assisted Reserve Deployment System. The E-MMPS container should incorporate a Main-Assisted Reserve Deployment (MARD) system.

3.4.1.3. Reserve Static Line Loads. The Reserve Static Line (RSL), including all joints and the reserve pin shall withstand the loads described in PIA TS 135 section 4.3.2 without failure.

3.4.1.4. Rapid Reserve Deployment Direct Drop. The Rapid Reserve Deployment (RRD) feature shall meet the functional requirements throughout the deployment altitude range.

Performance at the lower end of the range shall be as described in PIA TS 135 section 4.3.8.1 for altitudes up to 5,000 ft Mean Sea Level (MSL). System performance throughout the rest of the altitude range shall also be without functional material failures.

3.4.1.5. Rapid Reserve Deployment Breakaway Drop. The RRD feature shall meet the functional requirements throughout the deployment range. Performance at the lower end of the range shall be as described in PIA TS 135 section 4.3.8.2 for altitudes up to 5,000 ft MSL. System performance throughout the rest of the altitude range shall also be without functional material failures.

3.4.2. Riser Release Safety Feature. The E-MMPS container shall incorporate a safety feature to release the main canopy in the event of a riser breakage. The system shall release from either one or both risers.

3.4.3. Container Closure.

3.4.3.1. One-Pin Closure. The E-MMPS reserve container shall have a one-pin reserve closure.

3.4.3.2. Pin Checks. The reserve and main container pin protector flaps shall provide a clear window/cover to view the closing loop and pin, allowing the parachutist to conduct pin checks without lifting the pin protector flaps.

3.4.4. Deployment Configurations.

3.4.4.1. Self-Set Drogue and Hand-Deployed Pilot Chute. The E-MMPS container shall be able to be rigged for self-set drogue and hand-deployed pilot chute.

3.4.4.2. Primary Actuation Device or Ripcord. Each primary actuation device (main and reserve), including all joints, shall withstand the loads it encounters as described in PIA TS 135 section 4.3.2 (a) - (d) without failure.

3.4.4.3. Drogue Release Force. For main parachute assemblies rigged for a drogue, the drogue release force shall not be less than 5 lbf (22.2N) and shall not exceed 27 lbf (120.1N) [NOTE: PIA requires max of 22lbf but USMC will allow up to 27lbf].

3.4.4.4. Human Factors. The E-MMPS shall meet the human factors requirements described in PIA TS 135 section 4.3.3 (a) - (e) in all configurations (main & reserve), as excepted in 3.4.4.3 above substituting 27 lbf vice the 22lbf stated.

3.4.4.5. Deleted.

3.4.5. Operational and Emergency Procedures. The E-MMPS container shall employ operational and emergency procedures similar to those of the Tandem Offset Re-supply Delivery System (TORDS). Similar infers that the E-MMPS shall:

• Not use a 3-ring drogue release

• Include a left drogue release at back of left hip

• Include a right drogue release at front of right hip,

• Include reserve and cut-away releases facing outboard on the main lift web

• Include a cutaway handle of a green pillow type

• Include a reserve release handle of a red pillow type

3.4.6. Equipment Attachment Points.

3.4.6.1. Equipment Attachment Point Location and Quantity. The E-MMPS container shall incorporate eight equipment attaching points located in the high, middle, low, and side positions.

3.4.6.2. Construction and Load Capability. All equipment attachment points shall be of a forged construction. The upper equipment attachment points shall have a minimum proof load strength of 5,000 lbs.

3.4.7. Deleted.

3.4.8. Soft Canopy Stuff Sack. The E-MMPS shall include a soft canopy stuff sack to store the canopy after landing to prevent damage. The stuff sack color shall match the harness container.

3.4.9. Soft E-MMPS Storage Bag. The E-MMPS shall include a soft storage bag to store the system and prevent damage. The storage bag color shall match the harness container.

3.4.10. Interfaces.

3.4.10.1. Parachutist Oxygen System.

3.4.10.1.1. Compatibility with Parachutist Oxygen System and Parachutist High

Altitude Oxygen System. The E-MMPS container shall be compatible with the current USMC Parachutist Oxygen System (POS) and Parachutist High Altitude Oxygen System (PHAOS).

3.4.10.1.2. Removable Parachutist Oxygen System Pocket. The E-MMPS container shall have a removable pocket compatible with the current USMC POS.

3.4.10.2. Military Cybernetic Parachute Release System Compatibility. The E-MMPS container shall include a processing unit pouch, a control unit pocket compatible with the 1500 35A model Cybernetic Parachute Release System (CYPRES) 2 Automatic Activation Device (AAD) control unit and channels for the CYPRES cabling. The pocket shall include a transparent window that allows viewing and operating the CYPRES control unit.

3.4.10.3. Parachutist Equipment Compatibility.

3.4.10.3.1. Equipment Compatibility. The E-MMPS shall function properly with the current helmets [Reconnaissance Modular Helmet Kit (RMHK)], Parachutist Individual Equipment Kit (PIEK), Parachute Drop Bag (PDB), weapons, and body armor.

3.4.10.3.2. Radio Pocket. The E-MMPS harness shall provide a removable and replaceable accessory pocket able to fit a PRC-148 or PRC-150 series radio.

3.4.11. Aircraft Compatibility.

3.4.11.1. Limited Compatibility. In the following configurations (see Table 1 below) with attached equipment, the E-MMPS shall be deployable without causing safety issues to the airframe, aircrew, or parachutist for parachuting operations.

Table 1. E-MMPS Deployment Configurations by Aircraft.

Deployment Configuration by Aircraft C-130 MV-22 CH-53

D ep lo ym en t

M et ho d

Hand Deployed Pilot Chute X X X

Self-Set Drogue X X X

3.4.11.2. Full Compatibility. In all configurations with attached equipment, the E- MMPS container should be deployable without causing safety issues to the airframe (all DoD and USSOCOM approved aircraft), aircrew and parachutist for parachuting operations.

3.4.12. Fitment. The referenced reports (NATICK/TR-11/017) Measurer’s Handbook and (NATICK/TR-13/018) 2010 Anthropometric Survey of U.S. Marine Corps Personnel: Methods And Summary Statistics provide excellent information to aid in establishing critical engineering harness dimensions. A suggested table of sizing dimensions is provided in the definitions section.

3.4.12.1. Two Harness Sizes. The E-MMPS harness assembly shall fit the 5th percentile female to 95th percentile male parachutist as defined by Table B-1 of MIL-STD-1472 (stature and weight) with up to two different sized adjustable harnesses.

3.4.12.2. One Harness Size. The E-MMPS harness assembly should fit the 5th percentile female to 95th percentile male parachutist as defined by Table B-1 of MIL-STD-1472 (stature and weight) in one adjustable harness.

3.4.12.3. Harness Release. The harness(es) shall be constructed such that, after landing, the parachutist can separate from the harness assembly unaided.

3.4.13. Service Life and Environmental Factors.

3.4.13.1. Fifteen Year Service Life. The E-MMPS shall have a service life of 15 years.

3.4.13.2. Twenty Year Service Life. The E-MMPS should have a service life of 20 years.

3.4.13.3. Materials and Workmanship. Material quality and workmanship quality shall be demonstrated to be suitable for the manufacture of, and appropriate for the intended use in, personnel parachute assemblies. All materials shall remain functional for storage from -40 to +200 deg F, and from 0 to 100% relative humidity. All plated ferrous parts shall be treated to minimize hydrogen embrittlement.

3.4.13.4. Proof Loads. All materials and components shall meet or exceed the proof loads specified in the applicable specification, drawing, or standard, without failure. In the absence of an applicable specification, drawing, or standard for a particular material, successful completion of the qualification [First Article Testing] tests shall be considered adequate evidence of suitability.

3.4.13.5. Stitching.

3.4.13.5.1. Stitching Type. Stitching shall be of a type that will not ravel when broken [NOTE: This is not required for consumable or frangible parts].

3.4.13.5.2. Stitching Contrast. All E-MMPS stitching colors shall be of a color to contrast and differentiate between stitching and joined materials.

3.4.13.6. Environmental Performance. The E-MMPS shall meet all environmental requirements for both the main and the reserve as described in section 4.3.5 and Table 3 of PIA TS 135.

3.4.13.7. Component Qualification. The E-MMPS components shall meet all requirements listed in Table 4 of PIA TS 135.

3.4.14. Reliability.

3.4.14.1. Threshold Reliability. The E-MMPS shall possess a reliability of no less than 95% with a confidence level of no less than 90, including use of the reserve as required. Failure of a parachute assembly or component is defined in section 6. Notes.

3.4.14.2. Objective Reliability. The E-MMPS should possess a reliability of no less than

99.5% with a confidence level of no less than 90, including use of the reserve as required. Failure of a parachute assembly or component is defined in section 6. Notes.

3.4.14.3. Structural Overload Strength. The E-MMPS (in main canopy configuration) shall satisfy the strength requirements described in PIA TS 135, Section 4.3.6 (4.3.6.1 - 4.3.6.4).

The overload condition specified in 4.3.6(a) = 1.2 MOW x C130 traveling at a 25,000 ft MSL equivalent speed. The functionally open time requirement applies to the reserve only.

3.4.14.4. Stability. The E-MMPS (main configuration) at the minimum operating weight shall not have oscillations that exceed 15 degrees from the vertical, in an unaltered post-deployment configuration per section 4.3.10 of PIA TS 135.

3.4.14.5. Freefall and Opening Shock. The E-MMPS (main configuration) with an individual (with or without equipment) weighing not more than the maximum operating weight, shall successfully complete freefalls IAW PIA TS 135 section 4.3.11 without the user(s) suffering significant discomfort from the opening shock and shall be able to disengage themselves, unaided, from the harness after landing.

3.4.15. Preventative Maintenance Checks and Services. The E-MMPS shall have a Preventive

Maintenance Checks and Services (PMCS) cycle of no less than 365 days.

3.5. Main Canopy Functions.

3.5.1. Weight Requirement. The E-MMPS main canopy [use of 2 different sized canopies due to 2 different size harnesses is acceptable] shall be capable of deploying in all configurations with a parachutist weighing 165 lbs. to 425 lbs. All Up Weight (AUW).

3.5.2. Deployment Altitude Range.

3.5.2.1. Threshold Altitude Deployment Range. The E-MMPS main canopy shall have an altitude deployment range between 4,500 ft Above Ground Level (AGL) and 24,999 ft MSL.

3.5.2.2. Objective Altitude Deployment Range. The E-MMPS main canopy should have an altitude deployment range between 4,000 ft AGL and 29,000 ft MSL.

3.5.3. Horizontal Travel.

3.5.3.1. Threshold Horizontal Travel. The E-MMPS main canopy shall allow a parachutist at 85% of maximum AUW to travel 23.5 km horizontal distance from an altitude of 19,999 ft MSL after exiting from an aircraft and freefalling for 1,000 ft and arriving 1,500 ft above the drop zone in all wind conditions [NOTE: Unless otherwise specified, assume all drop zones mentioned in this specification for horizontal travel are at 0 ft MSL].

3.5.3.2. Objective Horizontal Travel. The E-MMPS main canopy should allow a parachutist at 85% of maximum AUW to travel 26 km horizontal distance exiting from an aircraft at an altitude of 19,999 ft MSL after exiting from an aircraft and freefalling for 1,000 ft and arriving 1,500 ft above the drop zone in all wind conditions.

3.5.4. Glide Modulation. The E-MMPS main canopy should have a mechanism (not a technique, trim tabs, or brakes) that reduces the glide ratio (glide modulation) to allow for small target landing zones (70 m x 100 m).

3.6. Reserve Canopy Functions.

3.6.1. Weight Requirement.

3.6.1.1. Deployment Weight Range. The E-MMPS reserve canopy shall be able to deploy with a parachutist within the minimum and maximum AUW of the main canopy.

3.6.1.2. Twisted Line Function. IAW PIA TS 135 section 4.3.7 for twisted lines, the E- MMPS reserve shall successfully function with a weight of no more than the maximum operating weight and airspeed at the time of pack opening of 60 KEAS (111.1 km/h).

3.6.1.3. Stability. IAW PIA TS 135 sections 4.3.10 and Table 3, the E-MMPS reserve shall successfully function and oscillations shall not exceed 15 degrees from the vertical, in an unaltered post-deployment configuration.

3.6.1.4. Freefall and Opening Shock. IAW PIA TS 135 section 4.3.11, per Table 3, the

E-MMPS reserve with an individual (with or without equipment) weighing not more than the maximum operating weight, shall successfully complete freefalls IAW PIA TS 135 section 4.3.11 without the user(s) suffering significant discomfort from the opening shock and shall be able to disengage themselves, unaided, from the harness after landing.

3.6.1.5. Main Parachute Interference. When installed but not deployed, the main parachute assembly shall not interfere with the proper function of the reserve parachute assembly.

3.6.2. Emergency Deployment Altitude Range.

3.6.2.1. Threshold Emergency Deployment Altitude Range. The reserve canopy shall be able to deploy in an emergency between altitudes of 2,000 ft AGL and maximum MSL altitude of the main canopy.

3.6.2.2. Objective Emergency Deployment Altitude Range. The reserve canopy should be able to deploy in an emergency between altitudes of 1,500 ft AGL and maximum MSL altitude of the main canopy.

3.6.3. Horizontal Travel.

3.6.3.1. Threshold Horizontal Travel. The E-MMPS reserve canopy shall allow a parachutist at 85% of maximum AUW to travel 20 km horizontal distance from an altitude of 19,999 ft MSL after exiting from an aircraft and freefalling for 1,000 ft and arriving 1,500 ft above the drop zone in all wind conditions.

3.6.3.2. Objective Horizontal Travel. The E-MMPS reserve canopy should allow a parachutist at 85% of maximum AUW to travel 22 km horizontal distance exiting from an aircraft at an altitude of 19,999 ft MSL after exiting from an aircraft and freefalling for 1,000 ft and arriving 1,500 ft above the drop zone in all wind conditions.

3.6.4. Glide Modulation. The E-MMPS reserve canopy should have a mechanism (not a technique, trim tabs, or brakes) that reduces the glide ratio (glide modulation) to allow for small target landing zones (70 m x 100 m).

3.7. E-MMPS Detection Mitigation.

3.7.1. Audible Detection. The E-MMPS slider (for the main canopy) should provide the functionality to collapse in order to mitigate audible detection.

3.7.2. Visual Detection. All E-MMPS system components should provide detection mitigation across the visible and electromagnetic spectrums.

4. VERIFICATION.

4.1. General. This section establishes the requirements for verification that the E-MMPS system design meets the requirements of Section 3 of this specification [NOTE: Vendor provided data, upon verification, will be used to the greatest extent possible to minimize resources and costs].

4.1.1. Methods of Verification. Verification that the system and its associated components and assemblies meet the requirements of Section 3 shall be determined by one of the following methods as designated in Table 2 and described in Section 4:

Inspection (I) - Physical examination of documentation, hardware, or software to verify conformance to specified requirements. Inspection is used to check adequacy of design documentation to applicable specifications and conformance of hardware and software to design documentation and applicable standards. Inspection includes verification by design reviews and evaluation of the engineering design.

Analysis (A) - The use of recognized techniques, including computer models, to interpret or explain equipment performance or test data. Analysis is used in lieu of, or to supplement, test data.

Demonstration (D) - Performance of the actual function of the design requirement.

Demonstration is used on subsystem and components or when quantitative measurement is not required for verification. It does not have to take place in an operational environment.

Test (T) - To provide data in an operational environment. The data are subsequently used to evaluate quantitative product performance and effectiveness characteristics. Evaluation includes comparison of demonstrated characteristics with requirements.

4.1.2. Test Equipment Accuracy.

4.1.2.1. Environmental. Unless otherwise specified herein, the accuracy of instruments and test equipment used to control and monitor the environment shall be as specified in accordance with industry standards.

4.1.2.2. Functional. Unless otherwise specified herein, the total error in any measurement process used to measure performance characteristics shall not exceed 10% of the tolerance of each characteristic being measured. Gauge and instrument settings shall be specific with no operator variations allowed. Any automated acceptance inspection equipment (AAIE) prove-out shall be performed in accordance with MIL-A-70625.

4.1.3. Types of Inspection/Test.

4.1.3.1. First Article Test. The First Article Test (FAT) will consist of visual inspection, analysis, demonstration, and testing in the E-MMPS operational configuration. Each E- MMPS to be used during the dummy drops or live jump flight tests will undergo a thorough in-service inspection (i.e., equipment check) and assembly by qualified USMC Riggers, with participation by the Offeror. The in-service inspection and assembly will be conducted in accordance with all applicable manufacturer instructions for the system being configured and all applicable USMC standard operating procedures for the in-service inspection of ram air parachute systems. Results of the in-service inspection will be documented along with the pull test results of

4.4.4.4. Each E-MMPS will have a unique number assigned for tracking during the ground evaluation and flight tests. Any system failing the in-service inspection will not be used for dummy drops or live jumps. The FAT will allow actual verification (See Table 2 below), serve as the qualification inspection, and shall be performed on the E-MMPS system in the operational configuration.

Table 2. Requirement Matrix and Verification Methods.

Spec.

Para 3 Requirement Title

Harness Container, Main, Reserve, Component

Spec Para 4

Verification

FAT

Method

I A D T

Conf. Insp. % Sample

(not FAT)

3.2. MAJOR COMPONENTS 4.2

3.2.1 Harness Container HC 4.2.1 I 10%

3.2.2 Main Canopy Assembly M C 4.2.2 I 10%

3.2.3 Reserve Canopy Assembly R C 4.2.3 I 10%

3.2.4 Deleted 4.2.4

3.2.5 Soft Canopy Stuff Sack C 4.2.5 I 10%

3.2.6 Soft E-MMPS Storage Bag C 4.2.6 I 10%

3.3. FUNCTIONAL IDENTIFICATION AND MARKINGS 4.3

3.3.1 Parachute Harness Container Marking HC M R 4.3.1 I 10%

3.3.2 Harness Container Data Card Pocket HC 4.3.2 I 10%

3.3.3 Harness Container Color and Size Marking HC 4.3.3 I 10%

3.3.4 Main Canopy Marking M C 4.3.4 I 10%

3.3.5 Reserve Canopy Marking R 4.3.5 I 10%

3.3.6 Suspension Line Attachment Point Marking M R 4.3.6 I 10%

3.3.7 Main Canopy Color M C 4.3.7 I 10%

3.3.8 Reserve Canopy Color R C 4.3.8 I 10%

3.3.9 IUID Marking 4.3.9 I 10%

3.3.10 Reserve Flap Marking HC 4.3.10 I 10%

3.4. SYSTEM AND HARNESS CONTAINER

FUNCTIONS/FEATURES 4.4

3.4.1 Rapid Reserve Deployment Feature 4.4.1

3.4.1.1 Reserve Static Line HC R C 4.4.1.1 I 10%

3.4.1.2 Main-Assisted Reserve Deployment System HC R C 4.4.1.2.1 I 10%

4.4.1.2.2 A

4.4.1.2.3 D

3.4.1.3 Reserve Static Line Loads HC R C 4.4.1.3 D

3.4.1.4 RRD Direct Drop HC R C 4.4.1.4.1 A

4.4.1.4.2 T

3.4.1.5 RRD Breakaway Drop HC R C 4.4.1.5.1 A

4.4.1.5.2 T

3.4.2 Riser Release Safety Feature HC M C 4.4.2 I 10%

3.4.3 Container Closure 4.4.3

3.4.3.1 One-Pin Closure HC C 4.4.3.1 I 10%

3.4.3.2 Pin Checks HC C 4.4.3.2.1 I 10%

Spec.

Para 3 Requirement Title

Harness Container, Main, Reserve, Component

Spec Para 4

Verification

FAT

Method

I A D T

Conf. Insp. % Sample

(not FAT)

3.4.3.2 Pin Checks HC C 4.4.3.2.2 D

3.4.4 Deployment Configurations 4.4.4

3.4.4.1 Self-Set Drogue and Hand-Deployed Pilot Chute HC M C 4.4.4.1 I 10%

3.4.4.2 Primary Actuation Device/Ripcord HC M R C 4.4.4.2 A

3.4.4.3 Drogue Release Force HC C 4.4.4.3.1 A

4.4.4.3.2 T

3.4.4.4 Human Factors HC M R C 4.4.4.4.1 A

4.4.4.4.2 T

3.4.4.5 Deleted 4.4.4.5

3.4.5 Operational and Emergency Procedures HC C 4.4.5.1 I

4.4.5.2 A

3.4.6 Equipment Attachment Points 4.4.6

3.4.6.1 Equipment Attachment Point Location and Quantity HC 4.4.6.1 I 10%

3.4.6.2 Construction and Load Capability HC 4.4.6.2 A

3.4.7 Deleted 4.4.7

3.4.8 Soft Canopy Stuff Sack C 4.4.8 I

3.4.9 Soft E-MMPS Storage Bag C 4.4.9 I

3.4.10 Interfaces 4.4.10

3.4.10.1 Parachutist Oxygen System 4.4.10.1

3.4.10.1.1 Compatibility with Parachutist Oxygen System and

Parachutist High altitude Oxygen System HC M C 4.4.10.1.1 D

3.4.10.1.2 Removable Parachutist Oxygen System Pocket HC C 4.4.10.1.2 D

3.4.10.2 Military Cybernetic Parachute Release System HC R 4.4.10.2 D

3.4.10.3 Parachutist Equipment Compatibility 4.4.10.3

3.4.10.3.1 Equipment Compatibility HC M R C 4.4.10.3.1 D

3.4.10.3.2 Pocket for Radios HC C 4.4.10.3.2 D

3.4.11 Aircraft Compatibility 4.4.11

3.4.11.1 Limited Compatibility HC M C 4.4.11.1.1 I

4.4.11.1.2 A

3.4.11.2 Full Compatibility HC M C 4.4.11.2 A

3.4.12 Fitment 4.4.12

3.4.12.1 Two Harness Sizes HC M R C 4.4.12.1 D

3.4.12.2 One Harness Size HC M R C 4.4.12.2 D

3.4.12.3 Harness Release HC 4.4.12.3.1 A

4.4.12.3.2 D

Para 3 Requirement Title

Harness Container, Main, Reserve, Component

Spec Para 4

Verification

FAT

Method

I A D T

Conf. Insp. % Sample

(not FAT)

3.4.13 Service Life and Environmental Factors 4.4.13

3.4.13.1 Fifteen Year Service Life HC M R C 4.4.13.1 A

3.4.13.2 Twenty Year Service Life HC M R C 4.4.13.2 A

3.4.13.3 Materials and Workmanship HC M R C 4.4.13.3.1 I 100%

4.4.13.3.2 A

3.4.13.4 Proof Loads HC M R C 4.4.13.4 A

3.4.13.5 Stitching 4.4.13.5

3.4.13.5.1 Stitching Type HC M R C 4.4.13.5.1 I 100%

3.4.13.5.2 Stitching Contrast HC M R C 4.4.13.5.2 I 10%

3.4.13.6 Environmental HC M R C 4.4.13.6 A

3.4.13.7 Component Qualification C 4.4.13.7 A

3.4.14 Reliability 4.4.14

3.4.14.1 Threshold Reliability HC M R C 4.4.14.1.1 A

4.4.14.1.2 T

3.4.14.2 Objective Reliability HC M R C 4.4.14.2.1 A

4.4.14.2.2 D

3.4.14.3 Structural Overload Strength HC M C 4.4.14.3.1 A

4.4.14.3.2 D

3.4.14.4 Stability HC M C 4.4.14.4 A

3.4.14.5 Freefall and Opening Shock HC M C 4.4.14.5.1 A

4.4.14.5.2 D

3.4.15 Preventative Maintenance Checks and Services HC M R C 4.4.15 A

3.5. MAIN CANOPY FUNCTIONS 4.5

3.5.1 Weight Requirement HC M C 4.5.1.1 A

4.5.1.2 T

3.5.2 Deployment Altitude Range 4.5.2

3.5.2.1 Threshold Altitude Deployment Range HC M C 4.5.2.1.1 A

4.5.2.1.2 T

3.5.2.2 Objective Altitude Deployment Range HC M C 4.5.2.2.1 A

4.5.2.2.2 T

3.5.3 Horizontal Travel 4.5.3

3.5.3.1 Threshold Horizontal Travel M 4.5.3.1.1 A

4.5.3.1.2 T

Para 3 Requirement Title

Harness Container, Main, Reserve, Component

Spec Para 4

Verification

FAT

Method

I A D T

Conf. Insp. % Sample

(not FAT)

3.5.3.2 Objective Horizontal Travel M 4.5.3.2.1 A

4.5.3.2.2 T

3.5.4 Glide Modulation M C 4.5.4.1 I

4.5.4.2 A

4.5.4.3 D

3.6. RESERVE CANOPY FUNCTIONS 4.6

3.6.1 Weight Requirement 4.6.1

3.6.1.1 Deployment Weight Range HC R C 4.6.1.1.1 A

4.6.1.1.2 T

3.6.1.2 Twisted Line Function HC R C 4.6.1.2.1 A

4.6.1.2.2 D

3.6.1.3 Stability HC R C 4.6.1.3.1 A

4.6.1.3.2 T

3.6.1.4 Freefall and Opening Shock HC R C 4.6.1.4.1 A

4.6.1.4.2 T

3.6.1.5 Main Parachute Interference HC M R C 4.6.1.5.1 A

4.6.1.5.2 D

3.6.2 Emergency Deployment Altitude Range 4.6.2

3.6.2.1 Threshold Emergency Deployment Altitude Range R 4.6.2.1.1 A

4.6.2.1.2 D

3.6.2.2 Objective Emergency Deployment Altitude Range R 4.6.2.2.1 A

4.6.2.2.2 D

3.6.3 Horizontal Travel 4.6.3

3.6.3.1 Threshold Horizontal Travel R 4.6.3.1.1 A

4.6.3.1.2 T

3.6.3.2 Objective Horizontal Travel R 4.6.3.2.1 A

4.6.3.2.2 T

3.6.4 Glide Modulation R C 4.6.4.1 I

4.6.4.2 A

4.6.4.3 D

3.7. E-MMPS DETECTION MITIGATION 4.7

3.7.1 Audible Detection M C 4.7.1.1 I

4.7.1.2 A

3.7.2 Visual Detection HC M R C 4.7.2.1 I

4.7.2.2 A

4.1.3.2. Conformance Inspection. Conformance inspection shall be completed on the E-

MMPS production systems as a prerequisite for acceptance by the Government. Specific paragraphs that make up the Conformance Inspection are identified in Table 2 including the lot sampling percentages.

4.2. Major Components.

4.2.1. Harness Container. Inspection of the E-MMPS will be used to ensure the presence of the harness container, detachable radio pocket, detachable parachute oxygen system pocket, and technical manual.

4.2.2. Main Canopy Assembly. Inspection of the E-MMPS will be used to ensure the presence of the main canopy assembly.

4.2.3. Reserve Canopy Assembly. Inspection of the E-MMPS will be used to ensure the presence of the reserve canopy assembly.

4.2.4. Deleted.

4.2.5. Soft Canopy Stuff Sack. Inspection of the E-MMPS will be used to ensure the presence of the soft canopy stuff sack.

4.2.6. Soft E-MMPS Storage Bag. Inspection of the E-MMPS will be used to ensure the presence of the soft E-MMPS storage bag.

4.3. Functional Identification and Markings.

4.3.1. System Marking. Inspection of the E-MMPS will be used to ensure that the minimum and maximum operating limits in section 4.2 and in Table 1 of PIA TS 135 are marked or placarded on or attached to the outside of the parachute harness container (pack). The marking/placard may refer to the technical manual for the minimum operating weight.

4.3.2. Harness Container Data Card Pocket. Inspection of the E-MMPS will be used to ensure that the harness container has been provided with a parachute data card pocket constructed such that the card will not be lost, damaged or interfere with the parachutist operation of the system. Inspection will also be used to verify that the data card pocket will be readily accessible when the parachute is packed in the container and when the user is donning the parachute assembly.

4.3.3. Harness Container Color and Size Marking. Inspection will be used to ensure harnesses are Coyote, Code 476/498 (FED-STD-595) in color and marked to differentiate between harness sizes (if two harness sizes are used).

4.3.4. Main Canopy Marking. Inspection will be used to ensure that the marking requirements of 3.3.4 for the E-MMPS main canopy and components have been satisfied.

4.3.5. Reserve Canopy Marking. Inspection will be used to ensure that the marking requirements of 3.3.5 for the E-MMPS reserve canopy and components have been satisfied.

4.3.6. Suspension Line Attachment Point Marking. Inspection will be used to ensure that each grouping of suspension line attachment points (main and reserve) are identified and distinguishable from adjacent groupings.

4.3.7. Main Canopy Color. Inspection will be used to ensure that each main canopy is silver in color and the associated deployment initiation devices and deployment control devices are of a color that is distinguishable between sizes (if two harness or canopy sizes are used).

4.3.8. Reserve Canopy Color. Inspection will be used to ensure that each reserve canopy is silver in color and the associated deployment initiation devices and deployment control devices are of a color that is distinguishable between sizes (if two harness or canopy sizes are used).

4.3.9. Item Unique Identification Marking. Inspection will be used to ensure that each E-

MMPS is marked with an IUID in accordance with MIL-STD-130.

4.3.10. Reserve Flap Marking. Inspection will be used to ensure the outer flap of each reserve container is marked with the production sequence number.

4.4. System and Harness Container Functions and Features.

4.4.1. Rapid Reserve Deployment Feature.

4.4.1.1. Reserve Static Line. The E-MMPS will be visually inspected to verify the presence of a RSL.

4.4.1.2. Main-Assisted Reserve Deployment System.

4.4.1.2.1. Inspection. The Government will inspect the E-MMPS to verify the existence of a MARD system.

4.4.1.2.2. Analysis. The vendor will provide a video for the Government to analyze, showing the proper initiation and operation of a MARD system inflating the reserve canopy.

4.4.1.2.3. Demonstration. The Government will conduct a demonstration using the MARD system during FAT.

4.4.1.3. Reserve Static Line Loads. The Government will demonstrate that the RSL, including all joints and the reserve pin, withstand the test loads of PIA TS 135 section 4.3.2 without failure.

4.4.1.4. Rapid Reserve Deployment Direct Drop.

4.4.1.4.1. Analysis. The vendor shall provide evidence and data for the

Government to analyze showing the RRD feature has completed direct drop testing satisfying the functional requirements of PIA TS 135 section 4.3.8.1.

4.4.1.4.2. Test. The Government will conduct 4 dummy air drop tests at 25,000 ft MSL with a four second delay. Each test system will be weighted to 1.2 times the maximum opening weight for each harness size. Each test system shall perform as designed without material failure exiting from a C-130 aircraft.

4.4.1.5. Rapid Reserve Deployment Breakaway Drop.

4.4.1.5.1. Analysis. The vendor shall provide evidence and data for the

Government to analyze, showing that the RRD feature has completed breakaway testing satisfying the functional requirements of PIA TS 135 section 4.3.8.2 for altitudes up to 5,000 ft MSL.

4.4.1.5.2. Test. The Government will conduct 2 dummy breakaway tests for each harness size, where the RSL actuates the reserve pack, to ensure that the RRD and MARD, if applicable, successfully functions after breakaway from an open and normally functioning main canopy, as described in section 4.3.8.2 of PIA TS 135.

4.4.2. Riser Release Safety Feature. The E-MMPS container will be inspected to verify the existence of a safety feature to release the main canopy in the event of a riser breakage (system may release from either one or both risers).

4.4.3. Container Closure.

4.4.3.1. One-Pin Closure. The E-MMPS container will be inspected to verify the presence of a one-pin reserve closure.

4.4.3.2. Pin Checks.

4.4.3.2.1. Inspection. Inspection will be used to verify that the reserve and main container pin protector flaps provide a clear window/cover to view the closing loops and pins, allowing the parachutist to conduct pin checks without lifting the pin protector flaps.

4.4.3.2.2. Demonstration. The Government will demonstrate a pin check, IAW the USMC Freefall Technical Manual.

4.4.4. Deployment Configurations.

4.4.4.1. Self-Set Drogue and Hand-Deployed Pilot Chute. The E-MMPS will be inspected to verify the capability to rig the parachute system in both self-set drogue and hand-deployed pilot chute deployment methods.

4.4.4.2. Primary Actuation Device or Ripcord. The vendor shall provide evidence and data for the Government to analyze, showing that each primary actuation device has completed straight tension load testing that satisfies the functional requirements of PIA TS 135 section 4.3.2 (a)-(d).

4.4.4.3. Drogue Release Force.

4.4.4.3.1. Analysis. The vendor shall provide evidence and data for the Government to analyze, showing the drogue release force satisfies the functional requirements of PIA TS 135 section 4.3.3 [NOTE: PIA requires max of 22lbf but USMC will allow up to 27lbf].

4.4.4.3.2. Test. The main drogue parachute assembly and release will be tested on the ground and also evaluated based on user feedback during other test events to ensure a human release force shall not be less than 5 lbf (22.2N) and shall not exceed 27 lbf (120.1N) [NOTE: PIA TS 135 requires max of 22 lbf but USMC will allow up to 27 lbf].

4.4.4.4. Human Factors.

4.4.4.4.1. Analysis. The vendor shall provide evidence and data for the

Government to analyze, showing that the release force for all pulls and releases satisfy the functional requirements of PIA TS 135 Table 2 and section 4.3.3.

4.4.4.4.2. Test. The E-MMPS will be tested IAW Table 2 of PIA TS 135, as described in section 4.3.3 subsections (a) through (e). There shall be no failure to meet any of the requirements during the qualification tests of this section.

4.4.4.5. Deleted.

4.4.5. Operational and Emergency Procedures.

4.4.5.1. Inspection. The vendor provided E-MMPS container samples will be inspected by the government to verify they are similar in accordance with section 3.4.5.

4.4.5.2. Analysis. The Government will conduct analysis to verify the vendor provided data (i.e. operational and emergency operating procedures) are similar to those of the TORDS.

4.4.6. Equipment Attachment Points.

4.4.6.1. Equipment Attachment Point Location and Quantity. The E-MMPS container will be inspected to ensure there are eight equipment attaching points located in the high, middle, low, and side positions.

4.4.6.2. Construction and Load Capability. The vendor data (i.e. material capacity ratings and vendor provided test data) will be analyzed by the Government to ensure equipment attachment points are forged material capable of supporting the typical paratrooper equipment without failure and proof strengths are provided certifying strength. The minimum proof load strength for the upper equipment attachment points shall be 5,000 lbs.

4.4.7. Deleted.

4.4.8. Soft Canopy Stuff Sack. The soft canopy stuff sack will be inspected to ensure it can store the canopy to prevent damage and the color is matched to the harness container.

4.4.9. Soft E-MMPS Storage Bag. The soft storage bag will be inspected to ensure it can store the E-MMPS to prevent damage and the color is matched to the harness container.

4.4.10. Interfaces.

4.4.10.1. Parachutist Oxygen System.

4.4.10.1.1. Compatibility with Parachutist Oxygen System and Parachutist High Altitude Oxygen System. The E-MMPS will be used, along with one USMC provided POS (currently PHAOS), to demonstrate proper compatibility and fitment.

4.4.10.1.2. Removable Parachutist Oxygen System Pocket. The E-MMPS will be used, along with one USMC provided POS (currently PHAOS), to demonstrate proper compatibility and fitment and that the pocket can be removed and reattached.

4.4.10.2. Military Cybernetic Parachute Release System Compatibility. The E-MMPS container will use demonstration to verify: the presence of a transparent pocket, the compatibility with viewing the 1500 35A model CYPRES 2 AAD control unit with the pocket closed, and the ability to operate the CYPRES control unit through the transparent pocket window with the pocket closed.

4.4.10.3. Parachutist Equipment Compatibility.

4.4.10.3.1. Equipment Compatibility. Demonstration will be used to show that the E-MMPS is compatible with the current helmets [Reconnaissance Modular Helmet Kit (RMHK)], Parachutist Individual Equipment Kit (PIEK), Parachute Drop Bag (PDB), weapons, and body armor (all of which will be provided by the Government).

4.4.10.3.2. Radio Pocket. Demonstration will be used to verify the E-MMPS harness provides a removable and replaceable radio pocket for a PRC-148 or PRC-150 series radio.

4.4.11. Aircraft Compatibility.

4.4.11.1. Limited Compatibility.

4.4.11.1.1. Inspection. Inspection of the E-MMPS will be used to ensure that the E-MMPS is compatible in the deployment configurations for the aircraft listed in Table 1.

4.4.11.1.2. Analysis. Analysis of vendor provided data will be used to show that, with attached equipment, the E-MMPS configurations in Table 1 are deployable without causing safety issues to the airframe, aircrew, or parachutist.

4.4.11.2. Full Compatibility. Analysis of vendor provided data will be used to show the

E-MMPS will be deployable without causing safety issues to the airframe (all DoD and USSOCOM approved aircraft), aircrew, and parachutist with attached equipment.

4.4.12. Fitment.

4.4.12.1. Two Harness Sizes. Through demonstration, at least one Marine representing a 5th percentile female and at least one Marine representing a 95th percentile male will physically put on each of their respective size harnesses to demonstrate that a harness fits IAW MIL-STD- 1472 Appendix B, Table B-1 Stature and Weight.

4.4.12.2. One Harness Size. Through demonstration, at least one Marine representing a

5th percentile female and at least one Marine representing a 95th percentile male will physically put on the harness to demonstrate that a harness fits the full range of Marines IAW MIL-STD-1472 Appendix B, Table B-1 Stature and Weight.

4.4.12.3. Harness Release.

4.4.12.3.1. Analysis. The Government will conduct analysis of vendor provided video and photographic data showing that the harnesses are constructed so that, after landing, the parachutist can separate from the harness assembly unaided.

4.4.12.3.2. Demonstration. Demonstration will be used by releasing the harness, to ensure the harness is constructed so that, after landing, the parachutist can separate from the harness assembly unaided.

4.4.13. Service Life and Environmental Factors.

4.4.13.1. Fifteen Year Service Life. Analysis of vendor provided data will determine if the E-MMPS meets a service life of 15 years.

4.4.13.2. Twenty Year Service Life. Analysis of vendor provided data will determine if the E-MMPS meets a service life of 20 years.

4.4.13.3. Materials and Workmanship.

4.4.13.3.1. Inspection. Inspection of the E-MMPS materials and workmanship will be used to ensure that materials are intact and no flaws, cracks, rips, or other impairments are noticed.

4.4.13.3.2. Analysis. The E-MMPS materials will be evaluated through analysis of vendor provided data to show the quality that documented experience and/or tests have conclusively demonstrated to be suitable for…