LPU Performance Specification 3.19.25.docx

DEPARTMENT OF THE NAVY

PROGRAM EXECUTIVE OFFICE PMA202

NAVAL AIR SYSTEMS COMMAND

PATUXENT RIVER, MD. 20670

DRAFT PERFORMANCE SPECIFICATION

USN Rotary Wing and Tilt Rotor Life Preserver Document Number: PMA202-PRF-XXX

Controlled by: U.S. Navy/NAVAIRSYSCOM

Controlled by: PEO(U&W)/PMA-202

CUI Category: Defense

Distribution: DISTRIBUTION STATEMENT D: DISTRIBUTION AUTHORIZED TO THE DEPARTMENT OF DEFENSE AND U. S. DOD CONTRACTORS ONLY; ADMINISTRATIVE OR OPERATIONAL USE; 07 FEBRUARY 2019. OTHER REQUESTS FOR THIS DOCUMENT SHALL BE REFERRED TO COMMANDER, NAVAL AIR SYSTEMS COMMAND (PMA-202), RADM WILLIAM MOFFETT BLDG, 47123 BUSE RD, BLDG 2272 PATUXENT RIVER, MD 20670-1547

POC: Captain Castelein, carey.f.castelein.mil@us.navy.mil

1. SCOPE

1.1. Scope. This performance specification covers the life preserver unit (LPU) for United States Navy Rotary Wing and Tiltrotor cockpit and mobile aircrew.

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 documents cited in sections 3, 4, or 5 of this specification, whether or not they are listed.

2.2. Government documents.

2.2.1. 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. Copies of these documents are available online at https://assist.dla.mil/.

DEPARTMENT OF DEFENSE STANDARDS

2.3. 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 are those cited in the solicitation.

FEDERAL REGULATIONS

GOVERNMENT REPORT

2.4. Non-government publications. The following documents 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 ASSOCIATION OF TEXTILE CHEMISTS AND COLORISTS

AMERICAN SOCIETY FOR TESTING MATERIALS (ASTM)

ELECTROSTATIC DISCHARGE ASSOCIATION

2.5. Order of precedence. Unless otherwise noted, 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. Reserved

3.2. Reserved

3.3. Flotation.

3.3.1. Self-Righting. The LPU shall have the following capabilities in righting the aircrew, including those who have become incapacitated or unconscious after egress wearing armor, with cell/s inflated and while dressed in Survival and mission equipment as stated in Table 1, during a Beaufort Sea State of “5”.

3.3.1.1. Maximum righting time of 5 seconds.

3.3.1.2. Inability of the wearer to float face downwards.

3.3.2. Flotation Angle. The LPU shall achieve and maintain the following flotation angles for aircrew, including those who have become unconscious, dressed in the Survival and Mission Equipment contained in Table 1 during a Beaufort Sea State of “5”.

3.3.2.1. Torso angle between 20° and 65°

3.3.2.2. Average torso angle between 30° and 50° (back of vertical)

3.3.2.3. Face-plane angle between 15° and 60° (back of vertical)

3.3.2.4. Average face-plane angle between 20° and 50° (back of vertical)

Table 1. Survival Equipment

SOF-T Tourniquet

Strobe, SDU-39N

Greatland Laser Light

Whistle, Fox 40

Sea Dye Marker

CRU-103 regulator

Miscellaneous, Optional Capability

Strike Force Firestarter

M18 Pistol (incl. 1 mag in weapon)

M18 Pistol Holster

Magazine Pocket (x1 per 2 mags)

PC GEN III Soft Armor (front/back) (size: medium)

ESAPI Hard Armor (size: medium)

Misc. 5 lbs of gear including pocket

3.3.3. Freeboard. When the flotation device is activated, the LPU shall achieve and maintain the following freeboard for aircrew, including those who have become incapacitated or unconscious, dressed in the Survival and Mission Equipment contained in Table 1 during a Beaufort Sea State of “5”.

3.3.3.1. At least 4” for any individual

3.3.3.2. Average of at least 4.75” across all individuals

3.3.4. Surfacing. When the flotation device is activated, the LPU shall ascend aircrew wearing armor, survival, and mission equipment identified in Table 1 from a depth of 33 feet [T]. The LPU may ascend aircrew from a depth of 45 feet [O].

3.3.5. Buoyancy at surface. The LPU flotation component shall provide no less than 65 pounds of net buoyancy upon inflation at the surface for a period of 24 hours (threshold) and for 48 hours. (objective).

3.3.6. Actuation manual operation. As a primary method of inflation, the LPU shall provide a manually initiated mechanism to full inflation of both buoyancy bladders within 5 seconds activated by either hand and not limited in direction of motion [T]; activated by single motion by either hand and not limited in direction of motion [O].

3.3.7. Oral inflation. As a secondary method of inflation, the LPU shall provide a means for oral inflation of each cell with the following capabilities

3.3.7.1. Easily accessible to the mouth and either hand when donned while in water

3.3.7.2. Positive shut-off

3.3.7.3. A check valve with a means of deflating the life preserver

3.3.7.4. Prevents inadvertent deflation.

3.3.7.5. Float each subject with respiration unimpeded within 30 seconds.

3.3.8. Multi cells. The LPU shall include a primary cell and at least one contingency cell that functions as an emergency backup in case the primary cell fails during use. The primary cell and contingency cell shall individually meet the requirements paragraph 3.3

3.3.9. Flotation support. The LPU shall remain in-place on aircrew, including those who have become incapacitated or unconscious after egress, when submerged in water, with flotation deployed [T] and without the aid of leg straps [O].

3.4. Physical characteristics, design, and construction.

3.4.1. Corrosion resistant finish. The LPU connectors and any metal/metallic surfaces shall have a corrosion-resistant finish.

3.4.2. Smoothing. All LPU surfaces shall be smooth to prevent damage to the aircrew and to interfacing parts of the system.

3.4.3. Electro-static discharge. The LPU shall avoid/preclude the propensity to suddenly discharge any static electricity accumulated at levels that can ignite volatile vapors or aerosolized fuels in the aviation pre-flight, operational, or post-flight environment.

3.4.4. Over pressurized condition. When pressurized with air to 70 kPa (10 psig) and held for 5 minutes, LPU must not show sign of permanent deformation, damage, or pressure loss of more than 3.5 kPa (0.5 psig)

3.4.5. Fatigue (pressurized condition after cycling). When inflated, the LPU pressure shall remain within 20% of the manufacturer’s stated operating pressure without evidence of material, seams, or constructional failure.

3.4.6. Puncture resistance. The LPU shall withstand a puncture force of up to 7 lbs. when exposed to a rounded point no less than 1 mm in diameter, in accordance with 46 CFR 160.176-13(s).

3.4.7. Flammability. The LPU flotation component shall be protected against flash fire in the uninflated condition after exposure to a flash fire as simulated by a 4-sec duration 84kW/hr. flame engulfment in accordance with ASTM F1930-18.

3.4.8. Finish/color.

3.4.8.1. Visual signature protection. The LPU's visible and flotation components (inflated) shall be a currently approved U.S. Armed Forces camouflage pattern or any non-black shade of an approved pattern.

3.4.8.2. Infrared signature protection. The LPU's visible components, in both the stowed and deployed configuration, shall be controlled in the near-infrared range, IAW the spectral reflectance table (Table 2) for the specific color or pattern. Spectral reflectance values shall not be outside the range limits at more than three of the wavelength ranges specified.

3.4.8.3. Low luster surfaces. Any LPU hardware that is exposed during use and wear shall have a matte or flat surface finish as defined in ASTM E284-17.

Table 2. Spectral Reflectance Requirement Values (percent) Solid Shades

Wave- length (nan-ometers)

Camouflage Green 483

Foliage Green 504

Urban Gray 505

Coyote 498 Coyote Brown 3758

Tan 380

Tan 499

3.4.9. Connection with Vest. The LPU shall remain attached to the survival vest, not compromise vest functionality and meet the requirements of this specification after exposure to an impact resulting from a survivable crash.

3.5. Human Systems Integration.

3.5.1. Aircrew sizing. The LPU shall properly fit, without any degradations in mission performance or safety, a population covering the central 90% of male and female aircrew [T]; the central 98% of male and female aircrew [O].

3.5.2. Water survival. The LPU shall not prevent aircrew in performance of water survival actions including:

3.5.2.1. swimming 75 yards using survival breaststroke or side stroke without hard armor with uninflated flotation

3.5.2.2. ingress into the deployed multi-place life raft (allowable to reduce air pressure in the flotation device)

3.5.2.3. self-donning of rescue strop

3.5.2.4. ingress into the rescue basket

3.5.2.5. deployment of Survival Egress Air (SEA)-LV2;

3.5.2.6. underwater egress from an inverted multi-place aircraft through doors and through windows, in dark condition;

3.5.2.7. ejection of the ballistic plates;

3.5.3. Human strength capability. The LPU shall not require arm, hand, and thumb-finger forces to operate actuation, release, and other mechanisms in excess of those required for females as specified in MIL-STD-1472, "Arm, hand, and thumb/finger controls."

3.5.4. Inadvertent actuation. The LPU's life critical arm, hand, and thumb-finger operated mechanisms shall comply with MIL-STD-1472 section 5.1.1.7 to withstand typical movements of the aircrew (such as running, crawling, and climbing) to prevent accidental activation.

3.5.5. Dressed envelope, head neck mobility. The LPU shall have a Cooper-Harper rating of no greater than 4 to execute head mobility tasks for both the cockpit and mobile aircrew wearing the Survival and Mission equipment as specified in Table 1 with flotation not activated and while wearing the helmet.

3.5.6. Emergency ground egress. The LPU shall not cause snagging or interference preventing emergency egress of the aircraft on land within 30 seconds while wearing equipment specified in Table 1.

3.5.7. Emergency water egress. The LPU shall not cause snagging or interference preventing underwater egress through a 22 x 18-inch opening with 2-inch rounded corners while wearing equipment specified in survival equipment and mission equipment columns of Table 1.

3.5.8. In-flight ops. The LPU shall not cause snagging or interference with any required mission maneuver, equipment, or aircraft component during nominal operations within an aircraft.

3.5.9. Gloves. The LPU shall allow aircrew to perform the required functions of the system with and without the following gloves: GS-FRP/2, HAU-15/P, JB1GU.

3.5.10. Flotation Removal. If externally mounted, the LPU shall be removable from the vest system.

3.5.11. Vest surface area: If externally mounted, LPU surface area on front and side panels of survival vest shall be minimized to the greatest extent possible (e.g., for LPU-21 type design: < 102 sq inch covered from Apex of Shoulder forward and from side of body forward. For LPU-37 type design: less than 88 sq inch covered from Apex of Shoulder forward.)

3.5.12. LPU Weight: LPU shall weigh less than 3.2 lbs. in installed states (including all connecting hardware).

3.5.13. LPU Uninflated Buoyancy. LPU uninflated buoyancy shall be greater than (–0.74) lbs. (threshold) or neutrally buoyant (objective).

3.6. Operating and storage environment.

3.6.1. General. After exposure to the below environmental conditions, the LPU shall perform as specified herein and materials shall not be subject to cracking, shrinking, crazing, delamination, corrosion, or significant degradation of physical properties that affect function.

3.6.2. High temperature. The LPU shall perform as specified following exposure to storage temperatures as defined in Procedure I of MIL-STD-810 Method 501.7 with high temperature limit as 71 C.

3.6.3. Low-temperature storage. The LPU shall perform as specified following exposure to storage temperatures as defined in Procedure I of MIL-STD-810 Method 502.7 with low temperature limit as -51 C.

3.6.4. Humid conditions. . The LPU shall perform as specified following exposure to humidity conditions as defined in Procedure II of MIL-STD-810 Method 507.6.

3.6.5. Fungus. The LPU materials shall not support fungal growth when exposed to fungus in accordance with MIL-STD-810, Method 508.5, Fungus.

3.6.6. Salt fog. The LPU shall perform as specified following exposure to the salt fog condition as defined in MIL-STD-810 Method 509.7.

3.6.7. Blowing dust. The LPU shall perform as specified following exposure to blowing dust conditions as defined in Procedure I of MIL-STD-810 Method 510.7.

3.6.8. Blowing sand. The LPU shall perform as specified following exposure to blowing sand conditions as defined in Procedure II of MIL-STD-810 Method 510.7.

3.6.9. Solar radiation. The LPU shall perform as specified following exposure to solar load of 1120± 47 W/m2 at a temperature of 125°F for 10 cycles (200 hours) as defined in Procedure II of MIL-STD-810 Method 505.7.

3.6.10. Fluid contamination. The LPU shall perform as specified following exposure to the military aviation contaminants identified in Table 3.

Table 3. Fluid Contaminants

3.7. Maintainability.

3.7.1. Scheduled maintenance interval. The LPU shall not require preventive maintenance actions, including inspections, less than 360-day period.

3.7.2. Mean time to repair (MTTR). The MTTR shall not exceed 1.0 hours for any unscheduled (e.g., corrective) maintenance action.

3.7.3. Level of repair. The organizational level (O-level) maintenance functions shall be limited to rigging and derigging the life preserver onto the survival vest. Cleaning, inspection, assembly, adjustment, fitting, reconfiguration, functional checkout, and minor repair shall be done at Intermediate level (I-level).

3.7.4. Support equipment. The LPU shall require no new and unique special tools or support equipment over the current tools and support equipment identified in the Aircraft Maintenance Material Requirements List (AMMRL) outlined in NAVAIRINST 13650.1.

3.8. Reliability.

3.8.1. Cyclic inflation test. LPU shall meet the requirements of this specification after 20 cycles of inflation, deflation, and repacking.

3.8.2. Mission Reliability RM. Mission reliability is the probability of completing a specified mission without a failure. The LPU shall be designed for a Mission Reliability (RM) of 84.1% based on a preventive maintenance schedule of 360 days (8640 hours) thus achieving a Mean Time Between Failure (MTBF) of 50,000 hours. A failure is any system degradation, indication of failure or actual failure that prevents the system from performing its mission. Mission reliability is calculated using a reliability function, R(t) = e^(-λt), where λ is the failure rate and t is time.

[note: this is not accurate but best possible option as of now. We can remove this if needed. Contractor should provide reliability estimate/analysis.]

4. VERIFICATION

4.1. Design verification. The section 3 requirements will be verified by one or more of the methods described in Table 4. In all cases, the method of verification will successfully verify the requirement has been met. This matrix identifies the verification methods (I, A, D, T are inspection, analysis, demonstration, test, respectively) to be used in verifying each requirement paragraph in section 3.

4.1.1. Verification of requirements may allow presentation of existing qualification and verification data, as described in qualification by similarity below, to ensure items are suitable for safe operation worldwide.

4.1.2. Qualification by similarity will be used to the maximum extent possible to qualify requirements in place of what has been captured in Table 4.

4.2. Verification conditions. Unless otherwise specified, all verifications shall be performed in accordance with the test conditions specified below.

4.2.1. Verification requiring aircraft will be performed on one or more of the following platforms: MH-60R/S, CMV-22 and MH-53.

4.2.2. Verification requiring in water demonstration or test will be performed in Navy facility providing the required conditions for evaluation.

Table 4. Verification Matrix

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

4.3. Flotation.

4.3.1. Self-righting. Verification shall be done by demonstration in accordance with 46 CFR §160.176-13(d)(2) in the Aviation Survival Training Center Facility water survival training environment.

4.3.2. Freeboard. Verification shall be done by test in accordance with 46 CFR §160.176-13(d)(3)(i) and 46 CFR §160.176-13(d)(4).

4.3.3. Surfacing. Verification shall be by demonstration in a deep-water environment with a human surrogate of negative 14 lbs. net buoyancy, and gear surrogates of negative 15 lbs. net buoyancy representing the dressed aircrew employing a diver as follows:

4.3.3.1. the diver submerges the surrogate human /gear package to specified water depth (correcting for density of the water composition).

4.3.3.2. Next, the diver shall actuate the flotation IAW manufacturer's procedures, and will release the surrogate. Time to break surface of water is measured and recorded to nearest half-second.

4.3.3.3. A minimum of 22 tests shall be conducted on a minimum of 6 Survival Vest samples of associated sizes. Samples can be reused from other testing. If a reused sample constitutes a failure, a retest is allowed on a new sample.

4.3.4. Buoyancy at surface. Verification shall be by demonstration in accordance with 46 CFR §160.176-13(j)(2) while achieving and sustaining not less than a 65 lb. net buoyant force. A minimum of 22 tests shall be conducted on a minimum of five test assets.

4.3.5. Actuation manual operation. Verification shall be by demonstration as per 46 CFR 160.176-13(c) in the Aviation Survival Training Center Facility water survival training environment.

4.3.6. Oral inflation. Verification shall be by demonstration as per 46 CFR 160.176-13(c) in the Aviation Survival Training Center Facility water survival training environment.

4.3.7. Dual cells. Verification shall be by examination in accordance with 46 CFR §160.176-9(a).

4.3.8. Flotation support. Verification shall be by demonstration in the Aviation Survival Training Center Facility water survival training environment.

4.4. Physical characteristics, design, and construction.

4.4.1. Corrosion resistant finish. LPU shall be verified through inspection of test articles subjected to environmental testing per section 4.6.

4.4.2. Smoothing. The LPU shall be visually and physically examined in both the inflated and non-inflated state for sharp edges or burrs. The examination shall include the donning of a pair of clean cotton gloves, and running fingertips or the palm along all the surfaces of the LPU.

4.4.3. Electro-static discharge. Verification shall be by test IAW the requirements and procedures delineated in drawing 1005938.

4.4.4. Over pressurized condition. One lifejacket is used in this test. Before pressurizing the lifejacket, each over-pressure valve, if any, must be blocked. One inflation chamber is then pressurized with air to 70 kPa (10 psig) and held for 5 minutes. After the 5 minute period, there must be no sign of permanent deformation, damage, or pressure loss of more than 3.5 kPa (0.5 psig). This test is then repeated as many times as necessary to test a different chamber until each chamber has been tested in this manner. The pressure within the LPU shall be measured and recorded and then visually inspected for evidence of material, seam or constructional failures.

4.4.5. Fatigue (pressurized condition after cycling). A completely deflated LPU assembly shall be placed in a horizontal position on the floor or table of the inspection area. The pressure readings shall be taken with the LPU in this position. The LPU shall be inflated with air to the manufacturer’s specified operating pressure. Hold at this pressure for no more than 15 seconds and then deflate. Repeat this sequence a total of 20 times, except that on the final sequence, the pressure in the bladder shall be recorded 30 ± 10 seconds after inflation. After recording the pressure, the LPU shall be visually inspected for evidence of material, seam or constructional failures. Upon completion of this test and visual examination, the LPU shall be completely deflated and then subjected to the leakage test in 4.4.6.

4.4.6. Puncture resistance. A fully inflated LPA shall be placed on a flat, level surface. A test point 4 mm (5⁄32 in.) in diameter tapering to a rounded point, 1 mm (3⁄64 in.) in diameter, shall be pressed against an inflation chamber of the LPU perpendicular to the surface of the chamber at a rate of 300 mm/minute (12 in./minute). The test point shall be applied until the inflation chamber is punctured or the chamber walls are touching each other. The force required to puncture the inflation chamber or make the chamber walls touch each other shall be recorded.

4.4.7. Flammability. Verification shall be by test in accordance with ASTM-F-1930, Standard Test Method for Evaluation of Flame-Resistant Clothing for Protection against Flash Fire Simulations Using an Instrumented Manikin.

4.4.8. Finish/Color.

4.4.8.1. Visual Signature Protection. Verification shall be by inspection. The color and appearance of the finished materials shall match the standard sample when viewed using AATCC Evaluation Procedure 9, Option A, under filtered tungsten lamps that approximate artificial daylight D75 illuminant with a color temperature of 7500° ± 200° K with illumination of 100 ± 20 foot candles, and shall be a good match to the standard sample under horizon lamplight at 2300° ± 200° K.

4.4.8.2. Infrared signature protection. Verification shall be by test. Spectral reflectance data shall be determined on the face side of materials and shall be obtained from 600 to 860 nanometers (nm) at 20 nm intervals on a spectrophotometer relative to the barium sulfate standard, the preferred white standard. Other white reference materials may be used, e.g. magnesium oxide or vitrolite tiles, provided they are calibrated to absolute white. The spectral bandwidth shall be less than 26 nm at 860 nm. Reflectance measurements may be made by either the monochromatic or polychromatic mode of operation. When the polychromatic mode is used, the spectrophotometer shall operate with the specimen diffusely illuminated with the full emission of a source that simulates either CIE source A or CIE source D65. The specimen shall be measured as a single layer, backed with six layers of the same fabric and shade. Measurements shall be taken on a minimum of two different areas and the data averaged. The measured areas should be taken at least 6 inches away from the selvage. The specimen shall be viewed at an angle no greater than 10 degrees from the normal, with the specular component included. Photometric accuracy of the spectrophotometer shall be within 1 percent and the wavelength accuracy within 2 nm. The standard aperture size used in the color measurement device shall be 0.3725 inches in diameter. Any color having spectral reflectance values outside the limits at four or more of the wavelengths specified shall be considered a test failure.

4.4.8.3. Low Luster Surfaces. Verification shall be by inspection.

4.4.9. Connection with Vest: Verification shall be by test.

4.5. Human systems integration.

4.5.1. Aircrew sizing. Verification shall be by demonstration. The relevant population shall be assessed through a lab demonstration of relevant individuals representing appropriate use cases.

4.5.2. Water survival. Verification shall be by demonstration in a water survival training environment, such as in the Aviation Survival Training Center Facility. Verification shall include test subjects representing the boundaries of the aircrew anthropometric range.

4.5.3. Human strength capability. Verification shall be by demonstration and test.

4.5.4. Inadvertent actuation. Verification shall be by demonstration in mission representative environment.

4.5.5. Dressed envelope, head neck mobility. Verification shall be by demonstration in mission representative environment. Verification shall include test subjects representing the boundaries of the aircrew anthropometric range.

4.5.6. Emergency ground egress. Verification shall be by demonstration in a mission representative environment. Verification shall include test subjects representing the boundaries of the aircrew anthropometric range.

4.5.7. Emergency water egress. Verification shall be by demonstration in the Aviation Survival Training Center Facility water survival training environment. Verification shall include test subjects representing the boundaries of the aircrew anthropometric range.

4.5.8. In-flight ops. Verification shall be by demonstration in a mission representative environment. Verification shall include test subjects representing the boundaries of the aircrew anthropometric range.

4.5.9. Gloves. Verification shall be by demonstration in a lab environment.

4.5.10. Flotation removal. Verification shall be by demonstration in a lab environment. The LPU shall be removable from the vest system without any loss of function or damage.

4.5.11. Vest Surface Area. Verification shall be done by inspection.

4.5.12. LPU Weight. Verification shall be done by inspection.

4.5.13. LPU Uninflated Buoyancy. Verification shall be done by demonstration.

4.6. Operating and storage environment.

4.6.1. Reserved.

4.6.2. High temperature. Verification shall be by inspection, demonstration, and test prior to and after conditioning in accordance MIL-STD-810, Method 501.7, Procedure I. Both complete end items and component materials shall be included. Prior to each conditioning procedure, a complete visual examination and functional checkout of the end item shall be performed. End items shall be packaged as described in section 5. After conditioning, a complete visual examination and functional checkout of the end item shall be repeated and the results recorded. Any differences between pre-and post-conditioning visual examination and functional check-out shall be documented. Inability of LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.3. Low-temperature storage. Verification shall be by inspection, demonstration, and test prior to and after conditioning in accordance MIL-STD-810, Method 502.7, Procedure I. Both complete end items and component materials shall be included. Prior to each conditioning procedure, a complete visual examination and functional checkout of the end item shall be performed. End items shall be packaged as described in section 5. After conditioning, a complete visual examination and functional checkout of the end item shall be repeated and the results recorded. Any differences between pre-and post-conditioning visual examination and functional check-out shall be documented. Inability of LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.4. Humid conditions. Verification shall be by inspection, demonstration and test prior to and after conditioning in accordance with MIL-STD-810, Method 507.6. Test items shall be conditioned at 95% relative humidity and 140°F for 10 days. Both complete end items and component materials shall be included. Prior to the procedure, a complete visual examination and functional checkout of the end item shall be performed. After conditioning, a complete visual examination and functional checkout of the test item shall be repeated and the results recorded. Any differences between pre-and post-conditioning visual examination and functional check-out shall be documented. Inability of LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.5. Fungus. Verification shall be by inspection prior to and after conditioning in accordance with MIL-STD-810, Method 508.5, Fungus. The verification shall be performed on LPU system component materials. Prior to conditioning, a complete visual examination of the component materials shall be performed. After conditioning, a complete visual examination of the component materials shall be repeated. Any evidence of fungal growth shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.6. Salt fog. Verification shall be by inspection and demonstration prior to and after conditioning in accordance with MIL-STD-810, Method 509.4, Salt Fog. A minimum of two conditioning cycles shall be conducted, with each cycle consisting of a 24-hr exposure to the salt fog environment followed by a 24-hr dry time. Prior to the conditioning procedure, a complete visual examination and functional checkout of the test item shall be performed. After conditioning, a complete visual examination and functional checkout of the test item shall be repeated, and the results recorded. Any differences between pre-and post-conditioning visual examination and functional checkout shall be documented. Inability LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.7. Blowing dust. Verification shall be by inspection and demonstration prior to and after conditioning in accordance with MIL-STD-810, Method 510.7 Procedure I. The air velocity to be used for Procedure I is 8.9 m/sec (1750 ft/min), and for Procedure II, 18 - 29 m/sec (3540 - 5700 ft/min). In order to simulate multidirectional winds, the test item shall be rotated at 90-minute intervals to expose all faces to the test environment. Prior to the procedure, a complete visual examination and functional checkout of the test item shall be performed. After conditioning, a complete visual examination and functional checkout of the test item shall be repeated, and the results recorded. Any differences between pre-and post-conditioning visual examination and functional check-out shall be documented. Inability of LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.8. Blowing sand. Verification shall be by inspection and demonstration prior to and after conditioning in accordance with MIL-STD-810, Method 510.7 Procedure II. The air velocity to be used for Procedure I is 8.9 m/sec (1750 ft/min), and for Procedure II, 18 - 29 m/sec (3540 - 5700 ft/min). In order to simulate multidirectional winds, the test item shall be rotated at 90-minute intervals to expose all faces to the test environment. Prior to the procedure, a complete visual examination and functional checkout of the test item shall be performed. After conditioning, a complete visual examination and functional checkout of the test item shall be repeated, and the results recorded. Any differences between pre-and post-conditioning visual examination and functional check-out shall be documented. Inability of LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.9. Solar radiation. Verification shall be by inspection, demonstration, and test prior to and after conditioning in accordance with Procedure II of MIL-STD-810 Method 505.7. A minimum of ten, twenty-four-hour conditioning cycles shall be conducted. Both complete end items and component materials shall be included. Prior to the procedure, a complete visual examination and functional checkout of the end item shall be performed. After conditioning, a complete visual examination and functional checkout of the end item shall be repeated and the results recorded. Any differences between pre- and post-conditioning visual examination and functional check-out results shall be documented. Inability of LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.6.10. Fluid contamination. Verification shall be by inspection, demonstration and test prior to and after conditioning in accordance with MIL-STD-810, Method 504, Contamination by Fluids. End items and component materials shall be conditioned with the contaminants identified in Table 3 in accordance with the “occasional contamination” procedure for ten, twenty-four-hour cycles. Both complete end items and component materials shall be included. Prior to the procedure, a complete visual examination and functional checkout of the end item shall be performed. After conditioning, a complete visual examination and functional checkout of the end item shall be repeated and the results recorded. Any differences between pre-and post-conditioning visual examination and functional check-out shall be documented. Inability of LPU to meet the requirements of this specification, after conditioning, shall constitute failure. A manufacturer-supplied Certification of Compliance to applicable requirements that includes a report from an independent testing laboratory containing sufficient data to demonstrate compliance with requirements may be accepted in lieu of testing.

4.7. Maintainability.

4.7.1. Scheduled maintenance interval. Verification shall be by analysis.

4.7.2. Mean time to repair (MTTR). LPU maintainability shall be verified through Maintainability Demonstration (M-Demo) to ensure compliance with the MTTR requirements in Section 3.7.2. The M-Demo shall be performed either in the usage environment, or in an environment that simulates the usage environment. MTTR elements subject to tracking during maintenance actions include failure isolation, disassembly, removal and replacement, reassembly, and checkout times. Personnel representative of the level of maintainer servicing a fielded system shall be utilized as maintainers during the demonstration.

4.7.3. Level of repair. Verification shall be through completion of a maintenance demonstration.

4.7.4. Support equipment. Verification shall be by inspection. Applicable tools and support equipment lists shall be compared with current tools and support equipment identified in the AMMRL outlined in NAVAIRINST 13650.1.

4.8. Reliability.

4.8.1. Cyclic inflation test. Verification should be done by test. A completely deflated LPU assembly shall be placed in a horizontal position on the floor or table of the inspection area. The temperature and pressure readings shall be taken with the LPU in this position. The LPU shall be inflated with air to the manufacturer’s specified operating pressure. Cycle shall be repeated 20 times. At the end of 20th iteration, LPU shall be subjected to leakage verification and then section 4.3 (Flotation) of this document.

4.8.2. Mission Reliability RM.: Verification shall be done by analysis/ Production reliability acceptance test (PRAT).

5. PACKAGING

5.1. For acquisition purposes, the packaging requirements shall be as specified in the contract or order. When packaging of materiel is to be performed by Department of Defense (DoD) or in-house contractor personnel, these personnel need to contact the responsible packaging activity to ascertain packaging requirements. Packaging requirements are maintained by the Inventory Control Point's packaging activities within the Military Service or Defense Agency, or within the military service's system commands. Packaging data retrieval is available from the managing Military Department's or Defense Agency's automated packaging files, CD-ROM products, or by contacting the responsible packaging activity.

6. NOTES

This section contains information of a general or explanatory nature that may be helpful, but is not mandatory.

6.1. Intended use.

6.2. Definitions.

6.2.1. Analysis. Analysis is a technical evaluation of design information such as equations, charts, graphs, drawings, schematics, and other data. If actual tests were conducted for a related or unrelated purpose, and utilization of these data will prove that requirement has been met, it should be considered “analysis”. Analysis methods include the use of modeling and simulation with a government-accredited model.

6.2.2. Demonstration. Demonstration is an observable functional operation, under controlled conditions not requiring subsequent analysis of data, is used to verify that a given requirement is met.

6.2.3. Face-Plane Angle. Face-Plane angle is the angle between a vertical line and a line passing through the most forward part of the forehead and chin.

6.2.4. Freeboard. Freeboard is the vertical distance from the water surface to the bottom of the mouth.

6.2.5. Inspection. Inspection is a method of verification to determine compliance with specification requirements and consists primarily of visual observations, mechanical measurements of the equipment, physical locations, and technical examination of engineering-support documentation. Inspection is used to determine system characteristics by examination of the item and comparing the item with descriptive documentation, and engineering drawings, to determine conformance with specified requirements.

6.2.6. Torso Angle. Torso angle is the angle between a vertical line and a line passing through the shoulder and hip.

6.2.7. Test. Test is a method of verification that will measure equipment performance under specific configuration-load conditions and after the controlled application of known stimuli. Quantitative values are measured, compared with previously determined success criteria, and evaluated to determine the degree of compliance. Analysis or review is subsequently performed on the data derived from the testing. Analysis as described here is an integral part of this method and should not be confused with the "analysis" described above.

6.2.8. Threshold. Threshold is the minimum requirement for the LPU. Threshold requirements either have no indication or are denoted with [T] when associated with an objective capability or performance.

6.2.9. Objective. Objective capabilities exceed the threshold requirement, denoted with [O], to indicate an additional capability may be obtained if a cost-effective implementation is achievable as approved by the PMA.

6.2.10. Qualification. Qualification by similarity consists of the review of certified/approved test data in conjunction with design evaluation data to substantiate the following: a) A similar item of equipment has been previously qualified to the requirements of this specification. b) The new item does not incorporate differences that would invalidate this criterion. A qualification by similarity is a prediction based on existing data with detailed examination of the differences and similarities between the previously qualified item and the item under consideration. The contractor may propose this method to the Government on a case-by-case basis.