WNUK-14-007 _Performance_Specification_-_13_Feb_14.pdf

PRF-TA-PLB-001-06G

Draft as of 13 February 2014

SUPERSEDING

PRF-TA-PLB-001-06F

24 December 2013

PERFORMANCE SPECIFICATION

PERSONNEL LOCATOR BEACON

Prepared by:

AFLCMC/WNUV

Aircrew Performance Branch

1981 Monahan Way, Building 12

Wright-Patterson AFB, OH 45433-7217

APPROVED FOR USE BY: _____________________________ DATE: _______________

WILLIAM A. MCGUFFEY, Colonel, USAF

Chief, Human Systems Division

1981 Monahan Way, Building 12

Wright-Patterson AFB, OH 45433

DISTRIBUTION STATEMENT E. Distribution authorized to DoD Components only

(Propriety Information) 02 December 2013. Other requests shall be referred to

AFLCMC/WNUV, 1981 MONAHAN WAY, WRIGHT-PATTERSON AFB, OHIO 45433

INCH-POUND

TABLE OF CONTENTS

1. SCOPE

1.1. Scope

2. APPLICABLE DOCUMENTS

2.1. General

2.2. Government documents

2.2.1. Specifications, standards, and handbooks

2.2.2. Other Government documents, drawings, and publications

2.3. Non-Government publications

2.4. Order of precedence

3. SYSTEM REQUIREMENTS

3.1. General

3.1.1. Configuration Requirements

3.1.1.1. Configuration A

3.1.1.1.1. Modifications

3.1.1.1.2. Activation mode selection

3.1.1.2. Configuration B

3.1.1.3 Configuration C

3.1.1.3.1. Modifications

3.2. PLB Transceiver functions and performance characteristics

3.2.1. COSPAS - SARSAT compatible

3.2.2. Modes of operation

3.2.2.1. Shut-down commands

3.2.3. Transmission Types

3.2.3.1. 406 MHz Transmissions

3.2.3.1.1. COSPAS - SARSAT compatibility

3.2.3.1.2. Integral Global Positioning System (GPS)

3.2.3.1.2.1. GPS timing and priority

3.2.3.1.2.2. GPS accuracy

3.2.3.1.2.3. GPS almanac update

3.2.3.2. 121.5 and 243.0 MHz transmissions

3.2.3.2.1. 121.5 and 243.0 MHz peak effective output

3.2.3.2.1.1. Compatibility with ADF

3.2.3.2.2. Inadvertent transmission prevention

3.2.3.2.3. Triple-band Transmission mode (Mode 1)

3.2.3.2.3.1. VHF/UHF transmitter output filter

3.2.3.3. Transmitter external light

3.2.3.4. Transmitter output impedance

3.2.3.4.1. Antenna matching frequency

3.2.4. Test functions

3.2.4.1. BIT Go/No-Go indicators

3.2.5. Electromagnetic interference

3.2.6. Multi-PLB interoperability

3.2.7. Computer Interface

3.2.4. PLB Go/No-Go indicator

3.3. PLB Transceiver Physical Characteristics

3.3.1. Size

3.3.1.1. PLB in Stowage Pocket

3.3.1.2. PLB in Parachute Pack

3.3.2. Weight

3.3.2.1. Configurations A

3.3.2.2. Configuration B/C

3.3.3. Color

3.3.4. Controls

3.3.4.1. Tactile Detent

3.3.4.2. External Mode Selector Switch

3.3.5. Markings

3.3.5.1. Switch and Control Function

3.3.5.2. Battery Inspection Sticker

3.3.6. Connectors

3.3.6.1. Connectors pull force

3.3.6.2. Connection and disconnection

3.3.7. Battery(s)

3.3.7.1. Power

3.3.7.1.1. Operation in C/S T.001 Class 2 Temp Range

3.3.7.1.2. Service Storage (shelf life)

3.3.7.1.3. In-Service, Non-Operating usage

3.3.7.2. Battery Sealed Compartment

3.3.7.2.1. Battery Safety Requirements

3.3.7.2.2. Battery Replacement

3.3.8. Antenna(s)

3.3.8.1. Integral or Attached Transmitting Antenna

3.3.8.1.1. Characteristics

3.3.8.2. Trailing wire transmitting antenna

3.3.8.2.1. Characteristics

3.3.8.2.2. Non-Interference

3.3.8.3. Receiving antennas

3.3.8.3.1. Operation

3.3.8.3.2. Characteristics

3.3.8.4. Trailing wire receiving antenna

3.3.8.4.1. Characteristics

3.3.8.4.2. Non-Interference

3.3.8.5. Antenna switching priority

3.3.9. Activation and control cable assembly

3.3.9.1. Cable assembly functions and performance

3.3.9.2. Plunger switch assembly operation

3.3.9.2.1. Characteristics

3.3.9.2.2. Fit

3.3.9.3. Rocker Switch Assembly

3.3.9.3.1. Fit

3.3.9.3.2. Switch Selection

3.3.9.3.2.1. Switch selection view

3.3.9.3.3. Switch Safety Pin

3.3.9.3.4. Go/No-Go Indicator

3.3.9.4. Cable assembly connector and wire bundle

3.3.9.4.1. Characteristics

3.3.9.4.2. Non-Interference

3.3.9.4.3. Color-coding

3.3.9.4.4. Sizing

3.3.9.4.5. Electromagnetic Interference

3.3.10. Automatic mechanical activation device

3.3.10.1. Operation with the C/S T.001 Class 2 Temp range

3.3.10.2. Installation

3.3.11. Lanyard

3.3.11.1. Characteristics

3.3.11.2. Type and Length

3.4. Environmental requirements

3.4.1. Storage temperature

3.4.2. Temperature shock

3.4.3. Operating temperature

3.4.4. Transit shock pulse

3.4.5. Vibration curves

3.4.6. Functional shock

3.4.7. Temperature, altitude, and humidity

3.4.8. Acceleration

3.4.9. Explosive atmosphere

3.4.10. Rapid decompression

3.4.11. Explosive decompression

3.4.12. Solar radiation

3.4.13. Sand and dust

3.4.14. Water resistance

3.4.15. Humidity

3.4.16. Moisture with salt

3.4.17. Fungus

3.4.18. Electrostatic buildup and discharge

3.5. Reliability and maintainability

3.5.1. Service life

3.5.1.1. Configuration A

3.5.1.2. Configuration B

3.5.1.3. Configuration C

3.5.2. Maintainability

3.5.2.1. Technical Orders

3.5.2.2. Mean time to Repair (MTTR)

3.6.3. Reliability

3.6. Integration

3.6.1. Human Systems Integration (HSI)

3.6.1.1. Manpower, personnel, and training

3.6.1.2. Human factors

3.6.1.3. Environment

3.6.1.4. Safety and occupational health

3.6.1.5. Survivability and habitability

3.6.2. Life Support Equipment (LSE) interface

3.6.2.1. Modification restrictions

3.6.2.2. PLB decontamination

4. VERIFICATION

4.1. Scope

4.1.1. Verification Testing (VT)

4.1.2. Qualification Testing (QT)

4.1.3. First Article Testing (FAT)

4.1.4. Production Lot Testing (PLT)

4.1.5. Functionality Check (FC)

4.2. Methods

4.3. PLB configurations

4.3.1. Configuration Requirements

4.3.1.1. Transceiver configurations

4.3.1.2. Automatic emergency activation

4.3.2. PLB Transceiver functions and performance

4.3.2.1. COSPAS - SARSAT compliance

4.3.2.2. Modes of Operation

4.3.2.3. Transmissions

4.3.2.3.1. 406 MHz Transmissions

4.3.2.3.1.1. GPS functions

4.3.2.3.1.2. GPS almanac update

4.3.2.3.2. Homing PLB transmission

4.3.2.3.3. Transmission light

4.3.2.3.4. Power Output

4.3.2.4. Test Functions

4.3.2.5. Electromagnetic interference

4.3.2.6. Multi-PLB interoperability

4.3.2.7. Computer Interface

4.3.3. Transceiver physical characteristics

4.3.3.1. Size

4.3.3.2. Weight

4.3.3.3. Color

4.3.3.4. Manual controls

4.3.3.5. Markings

4.3.3.6. Connectors

4.3.3.7. Battery(s)

4.3.3.7.1. Performance characteristics

4.3.3.7.2. Physical characteristics

4.3.3.8. Antennas

4.3.3.8.1. Integral transmitting antenna

4.3.3.8.1.1. Performance characteristics

4.3.3.8.2. Trailing wire transmitting antenna

4.3.3.8.2.1. Performance characteristics

4.3.3.8.2.2. Physical characteristics

4.3.3.8.3. Receiving antennas

4.3.3.8.3.1. Integral receiving antenna

4.3.3.8.3.2. Physical characteristics

4.3.3.8.4. Trailing wire receiving antenna

4.3.3.8.4.1. Performance characteristics

4.3.3.8.4.2. Physical characteristics

4.3.3.8.5. Antenna switching priority

4.3.3.9. Activation and control cable assembly

4.3.3.9.1. Cable assembly functions and performance

4.3.3.9.2. Plunger switch operation

4.3.3.9.2.1. Plunger switch physical characteristics

4.3.3.9.3. Rocker switch assembly

4.3.3.9.3.1. Rocker switch physical characteristics

4.3.3.9.4. Wire bundle physical characteristics device

4.3.3.10. Automatic mechanical activation device…

4.3.3.10.1. Performance characteristics

4.3.3.10.2. Physical characteristics

4.3.3.11. Lanyard

4.3.3.11.1. Performance characteristics

4.3.3.11.2. Physical characteristics

4.3.4. Environmental requirements

4.3.4.1. Storage temperature

4.3.4.2. Temperature shock

4.3.4.3. Operating temperature

4.3.4.4. Transit shock

4.3.4.5. Vibration curves

4.3.4.6. Functional shock

4.3.4.7. Temperature, altitude, and humidity

4.3.4.8. Acceleration

4.3.4.9. Explosive atmosphere

4.3.4.10. Rapid decompression

4.3.4.11. Explosive decompression

4.3.4.12. Solar radiation

4.3.4.13. Sand and Dust

4.3.4.13.1. Blowing dust

4.3.4.13.2. Blowing sand

4.3.4.14. Water resistance

4.3.4.15. Humidity

4.3.4.16. Moisture with salt

4.3.4.17. Fungus

4.3.4.18. Electrostatic buildup and discharge

4.4. Reliability and Maintainability

4.4.1. Service life

4.4.2. Maintainability

4.4.3. Mechanical Durability

4.5. Integration

4.5.1. Human Systems Integration (HSI)

4.5.1.1. Manpower, personnel, and training

4.5.1.2. Human factors

4.5.1.3. Environment

4.5.1.4. Safety and occupational health

4.5.1.5. Survivability and habitability

4.5.2. Life Support Equipment (LSE) interface

5. PACKAGING, HANDLING, AND TRANSPORTATION

5.1. Packing

5.2. Labeling

5.3. Shipment marking

6. NOTES

6.1. Intended use

6.2. Acquisition requirements

6.3. Qualification testing

CONCLUDING MATERIAL

LIST OF TABLES

Table 3-1. PLB Transmission Status

Table 4-1. Verification Matrix

1. SCOPE

1.1. Scope. This specification prescribes the performance requirements and identifies verification procedures for the Personnel Locator Beacon, hereafter referred to as the PLB, which includes all necessary components to meet the performance requirements described in Section 3, below. The beacon allows for automatic position/location in aircraft post-emergency egress conditions. The critical period of operation for the PLB is the initial period immediately after ejection or bailout during aircrew parachute descent prior to water or land contact. During this initial period the

PLB shall provide an alert signal to uniquely identify the active PLB and supply a precision GPS location. Once on the ground or in the water, the PLB shall provide approaching search and rescue (SAR) forces with a homing signal for their direction finding equipment during search and rescue operations.

2. APPLICABLE DOCUMENTS

2.1. General. The documents listed in this section are specified in this standard. While every effort has been made to ensure the completeness of this list, document users are cautioned that they shall meet all specified requirements of documents cited in this specification, whether or not they are listed here.

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.

DEPARTMENT OF DEFENSE STANDARDS

MIL-STD-129 Military Marking for Shipment and Storage

MIL-STD-130 Identification Marking of US Military Property MIL-STD-461 Requirements for the Control of Electromagnetic Interference

Characteristics of Subsystems and Equipment

MIL-STD-516 Airworthiness Certification Criteria

MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests

MIL-STD-882 DoD Standard Practice System Safety MIL-STD-1472 Human Engineering

MIL-STD-2073 Standard Practice for Military Packaging

(Copies of these documents are available online at http://quicksearch.dla.mil , or from the

Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA

19111-5094.)

2.2.2. Other Government documents, drawings, and publications. The following other

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

NATO STANAG 7007 Search and Rescue Electronic Systems http://quicksearch.dla.mil/

T.O. 14-1-1 (Reference) USAF Aircrew Life Support Equipment and Ensemble Configurations

T.O. 14D3-11-1 (Reference) Personnel Recovery Parachute Technical Manual

FAR 25-853, Appendix F FEDERAL AVIATION REGULATION - Airworthiness Standards: Transport Category Airplanes

FAA TSO-C142a Non-Rechargeable Lithium Cells and Batteries

DOD Instruction 5000.02 Operation of the Defense Acquisition System

2.3. Non-Government publications. The following documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues with these documents are cited in the solicitation or contract.

COSMICHESKAYA SISTYEMA POISKA AVARIYNICH SUDOV-SEARCH AND RESCUE

SATELLITE-AIDED TRACKING (COSPAS - SARSAT)

C/S G.005 COSPAS - SARSAT Guidelines on 406 MHz PLB Coding, Registration and Type Approval

C/S T.001 Specification for COSPAS - SARSAT 406 MHz Distress Beacons

C/S T.007 COSPAS - SARSAT 406 MHz Distress PLB Type Approval Standard

(Copies of these documents are available from http://www.COSPAS-SARSAT.org/ , or contact the COSPAS - SARSAT Secretariat, at: COSPAS - SARSAT, 700 de la Gauchetière West, Suite

2450, Montreal (Quebec) H3B 5M2, Canada

RADIO TECHNICAL COMMISSION FOR AERONAUTICS (RTCA)

RTCA/DO-160 Environmental Conditions and Test Procedures for Airborne Equipment

RTCA/DO-204 Minimum Operational Performance Standards 406 MHz Emergency Locator Transmitters (ELT)

(Copies of these documents are available for purchase from http://www.rtca.org/ , RTCA, Inc.,1828 L Street NW, Suite 805, Washington, DC 20036, or fax to 202-833-9434.)

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

3. SYSTEM REQUIREMENTS

3.1. General

3.1.1. Configuration Requirements. The Air Force requires a single Personnel Locator Beacon

(PLB) that satisfies both peacetime and wartime beacon needs across ejection seat and parachute applications to provide the rescue of downed aircrew. The PLB is a small emergency locator device that will automatically activate in aircraft emergency situations to include ejection, or bailout. It is a form, fit, function replacement for the legacy URT-33/URT-44 beacons and will be used in three (3) configurations (A/B/C). The PLB itself shall be identical in all configurations http://www.cospas-sarsat.org/ http://www.rtca.org/

EXCEPT the method of automatic activation which will be dependent on the interface with the ejection seat or parachute.

A Advanced Concept Ejection Seat II

(ACES II)

Typically in A-10, B-1, B-2, F-15, F-16, and F-

22 aircraft

B Back Automatic (BA) parachute and

Low Profile Parachute (LPP)

Typically in B-52, C-5, C-17, C-130, KC-10, and KC-135 aircraft

C Martin Baker (MB) ejection seat Typically in F-4, T-6, and T-38 aircraft

3.1.1.1. Configuration A. Configuration A shall include the capability to interface with the seat in such a way as for the PLB to activate in an emergency situation upon man-seat separation in the ejection sequence of the ejection seat.

3.1.1.1.1. The interface shall not require any modifications to the current seat configuration.

3.1.1.1.2. The PLB shall provide the aircrew the inflight capability to manually select between an automatic activation mode, in the event of an ejection, and a manual activation mode, while seated in the ejection seat.

3.1.1.2. Configuration B. Configuration B shall include an automatic PLB activation device to activate upon parachute canopy deployment after bailout.

3.1.1.3. Configuration C. Configuration C shall include the capability to interface with the seat in such a way as for the PLB to activate in an emergency situation upon man-seat separation in the ejection sequence of the ejection seat.

3.1.1.3.1. The interface shall not require any modifications to the current seat configuration in T-

6, and T-38 aircraft. If necessary, the F-4 mounting bracket may require minor modification.

3.2. PLB Transceiver functions and performance characteristics.

3.2.1. COSPAS - SARSAT compatible. The PLB shall be compatible with COSPAS - SARSAT technical requirement document C/S T.001, with the exception the applicable portions that are superseded by the military specific operational performance deviations specified herein, and shall be COSPAS - SARSAT compliant. The PLB may have a Type Approved Certificate (TAC) by COSPAS-SARSAT.

3.2.2. Modes of operation. The PLB shall have the ability to transmit per the following modes, which shall be selectable by the user:

Mode 1 Continuous transmission at 121.5, 243.0, and 406 MHz after activation and until battery exhaustion or manual shutdown

Mode 2 Continuous transmission at 121.5 and 243.0 MHz only after activation and until battery exhaustion or manual shutdown.

Mode 3 Continuous transmission at 406 MHz only after activation and until battery exhaustion or manual shutdown.

3.2.2.1. After the initial activation, the PLB shall ignore any subsequent shut-down command not originating with the PLB On/Off switch, including any extraneous signals caused by environmental factors as defined in paragraph 3.4.

3.2.3. Transmission Types.

3.2.3.1. 406 MHz Transmissions. The transceiver shall, provided a 406 MHz transmission mode has been selected (Modes 1/3, para. 3.2.2.) activate automatically in an emergency situation and will transmit a digital emergency message transmission on 406.0 to 406.1 MHz containing a unique identification and programmable number/code IAW C/S T.001.

3.2.3.1.1. The 406 MHz transmissions shall be in compliance with COSPAS - SARSAT technical requirements document C/S T.001, with the exception of the military specific operational performance deviations specified herein.

3.2.3.1.2. The transceiver shall include an integral Global Positioning System (GPS) receiver/microprocessor capable of acquiring and processing GPS satellite transponder signals to generate reliable GPS location data to be coded into the 406 MHz digital emergency message

IAW C/S T.001, and C/S G.005.

3.2.3.1.2.1. While attempting to acquire or update position data, the GPS function shall be full time and have priority over homing signals.

3.2.3.1.2.2. The GPS location data coded into the 406 MHZ emergency message shall be accurate to within 328 feet of actual location.

3.2.3.1.2.3. In addition to accepting almanac updates from GPS satellite transponders, the PLB shall have the capability to manually update the GPS almanac. A visual indication of almanac update in progress and of successful GPS almanac update shall be provided to the user.

3.2.3.2. 121.5 and 243.0 MHz Transmissions. Homing signal transmission on 121.5 and 243.0

MHz transmissions shall be a pulsed carrier tone, modulated IAW NATO STANAG 7007, Annex B.

3.2.3.2.1. The 121.5 and 243.0 MHz transmissions radio frequency (RF) peak effective output power of the PLB transmitter shall be not less than 100 milliwatts.

3.2.3.2.1.1. The 121.5 and 243.0 MHz transmissions shall be compatible with common automatic direction finding (ADF) equipment employed by an aircraft flying at 10,000 ft. AGL, 60 nautical miles away.

3.2.3.2.2. If the homing signal only transmission mode has been selected (Mode 2, para. 3.2.2.), upon initial activation, the PLB shall be designed to limit any inadvertent transmission to a minimum of 15 seconds and a maximum of 45 seconds.

3.2.3.2.3. If the triple-band transmission mode has been selected (Mode 1, para. 3.2.2.), homing signal transmission shall be initiated immediately following the first 406 MHz burst. The homing signal shall not interfere with the subsequent 406 MHz transmission burst.

3.2.3.2.3.1. The VHF/UHF transmitter output shall be filtered to avoid performance degradation in GPS reception initial acquisition time.

3.2.3.3. The PLB will be equipped with an external light (i.e., LED) to indicate to the user the device is transmitting.

3.2.3.4. The PLB shall have an output impedance of the transmitter such as to provide maximum power output and optimum matching at 121.5, 243.0, and 406.0 to 406.1 MHz when connected to the integral antenna. The PLB output impedance shall also fall within the limits required by the manufacturer of any power cells selected for use.

3.2.3.4.1. The antenna matching frequency maximum power output priority shall focus on 406

MHz signals first, followed by 243.0 MHz and 121.5 MHz transmissions.

3.2.4. Test functions. The PLB shall include capabilities for Built-In-Test (BIT) or self-test functions. The BIT check shall be a complete and accurate representation of PLB serviceability, and shall meet the self-test requirements of RTCA/DO-204.

3.2.4.1. The BIT check indicators shall display to display operational status Go/No-Go information. The results of the BIT shall be viewable (a) as a Go/No-Go indicator on the exterior of the PLB, and (b) as a Go/No-Go indicator on the cable assembly rocker switch and shall be viewable by the user in configuration A.

3.2.5. Electromagnetic interference. The PLB, while installed in configurations A/B/C, shall not cause electromagnetic interference with other equipment items located on the aircraft in compliance with Electromagnetic Interference Test Procedures (EMITP) IAW MIL-STD-461, Section 5, for Radiated Susceptibility (RS103), Radiated Harmonic and Spurious Emissions

(CE106), and Radiated Emissions (RE102), and spurious emission specifications in C/S T.001.

The PLB shall not exhibit any malfunctions, degradation of performance, or deviation from the specifications as a result of the tests and shall meet the performance limits specified in the applicable portions of MIL-STD-461 and C/S T.001.

3.2.6. Multi-PLB interoperability. At a minimum, four (4) PLBs shall be able to function concurrently within a 100 square ft. area at a minimum distance of 1 ft. apart, to ensure proper signaling, GPS, homing functions, and aircrew identification following bailout from a multi-place aircraft under both static and dynamic conditions.

3.2.7. Computer interface (If used). Computer interface device for data exchange shall provide the capability to manually execute a GPS almanac update, to initiate a BIT check, to read out detailed beacon diagnostic data following a BIT check, reset battery information, and to upload new or revised software or settings into the beacon.

3.3. PLB Transceiver physical characteristics.

3.3.1. Size. The transceiver case shall be a small, rugged, and lightweight enclosure measuring no more than 1.32 by 2.70 by 5.00 inches in size, including paint thickness, any attached plates or decals, and any raised surface features.

3.3.1.1. The PLB shall be capable of being installed in all configurations without any modification to any survival kits; to include closure of any retaining strap snaps.

3.3.1.2. The parachute pack may have minor modifications as long as the intent of activation procedures (T.O. 14D3-11-1, Chapter 5) is not compromised. A minor modification is defined as a one-time task that can be accomplished at the organizational maintenance level within 15 minutes and without the use of special tools, equipment, or materials.

3.3.2. Weight.

3.3.2.1. The weight of configurations A shall not exceed 1.8 lbs. This includes 0.5 lbs. for the automatic activation functionality interfacing with the ejection seat, cabling, and external antenna(s), if used.

3.3.2.2. The weight of configuration B/C shall not exceed 1.3 lbs. This includes the weight of all antennas, mechanical activation devices, and lanyards.

3.3.3. Color. The PLB case shall have a dull/low IR reflective surface of any subdued color that facilitates concealment in combat situations.

3.3.4. Control functions. All controls shall have a positive tactile detent (by touch) for each selectable position, and shall be operable while wearing standard USAF flight gloves (GS/FRP-

2) and without the use of any tools.

3.3.4.1. On the exterior of the case, the PLB shall have a manual on/off switch which includes a means to reduce the likelihood of inadvertent operation, such as a cover, detents, and/or high operating force. This inadvertent operation safeguard shall prevent possible erroneous switching due to the forces associated with ejection, parachute opening, landing and ground contact, and/or hard aircraft landings.

3.3.4.2. The PLB case shall incorporate manual functional controls on its exterior to enable automatic or manual selection of transmission mode and on/off function. The mode selected shall be clearly marked and accessible/visible to the user. In configuration B, the external mode selector capability shall be readily accessible and visible to the user during flight or on the ground.

3.3.5. Markings. The PLB operating instructions, part number, serial number, contract number, COSPAS - SARSAT hexadecimal identification number, Unique Identification (UID) code, and external display legends (if applicable) shall be permanently affixed to the case.

3.3.5.1. All switches and control identification shall be similarly provided on the case, or on the switch or control itself.

3.3.5.2. A 1.00 by 1.25 inch space with a smooth uniform surface shall be made available on the exterior of the case for affixing a USAF NL555, Battery Inspection Label to record battery replacement date and periodic inspections. The design of the PLB shall be such that operation or functionality of the PLB shall not be adversely effected by attachment of the USAF NL555, Battery Inspection Label.

3.3.6. Connectors. If connectors are required, the connector interfaces shall be waterproof, and their design shall preclude cross connection of the incorrect connector into any port.

3.3.6.1. All connectors shall withstand a pull force of at least 5 lbs. in at least 8 cardinal directions (0°/360°, 45°, 90°, 135°, 180°, 225°, 270° 315°) in relation to the connector along with a straight pull at 0 degrees without any damage that would alter the electrical characteristics of the connectors or the attached wire bundle.

3.3.6.2. All connectors shall permit connection and disconnection by an aircrew wearing standard USAF flight gloves.

3.3.7. Battery(s). The PLB shall be powered by one (1), or more, non-rechargeable, commercially available battery(s). A commercially available battery shall be available for purchase from a catalog or ordering equivalent.

3.3.7.1. The battery(s) shall provide power to meet the required output power levels specified in section 3.2.3.

3.3.7.1.1. The battery(s) shall be capable of sustaining C/S T.001 specified PLB operation while transmitting in the following modes in the C/S T.001 Class 2 operating temperature range:

Mode 1 A minimum of 24 hours Continuous transmission at 121.5, 243.0, and 406

Mode 2 A minimum of 36 hours Continuous transmission at 121.5 and 243.0 MHz

Mode 3 A minimum of 48 hours Continuous transmission at 406 MHz

3.3.7.1.2. The battery(s) shall be capable of providing the minimum amount of power necessary to meet this performance specification after 2 years of out of service storage (shelf life) at temperatures up to +68° F.

3.3.7.1.3. The battery(s) shall be capable of providing the minimum amount of power necessary to meet this performance specification after an additional 3 years of in-service, non-operating usage (to include periodic self-test or other maintenance processes) at temperatures up to +131

°F.

3.3.7.2. The battery(s) shall be contained in a sealed compartment that is an integral part of the

PLB.

3.3.7.2.1. The battery(s) shall comply with the battery safety requirements outlined in

RTCA/DO-204 and shall hold an FAA Technical Standard Order TSO-C142a certification (or equivalent) for flight safety/airworthiness approval.

3.3.7.2.2. The PLB shall be designed to allow battery replacement in 5 minutes or less by

Aircrew Flight Equipment (AFE) maintenance personnel with standard shop tools. No water intrusion shall be allowed as a result of the battery(s) replacement actions.

3.3.8. Antenna(s) If external antennas are used in the design, circuit switching associated with antenna removals or failures shall be automatic and shall not have the potential to make the transceiver or its GPS functions inoperable. The PLB shall not be damaged when operating with either a short or an open circuit on any antenna circuit. The antenna shall not interfere with stowage in any configuration’s stowage pocket.

3.3.8.1. Integral or Attached Transmitting Antenna. The integral and/or attached transmitting antenna shall be compatible with C/S T.001.

3.3.8.1.1. Any integral and/or permanently attached transmitting antenna shall withstand the operational environments for all configurations and be built-in or deployable and collapsible by the user while wearing standard USAF flight gloves and without the use of any tools.

3.3.8.2. Trailing Wire Transmitting Antenna. Trailing wire transmitting antenna (if used) shall be C/S T.001 compatible.

3.3.8.2.1. Only as much length as is necessary for optimal transmitting performance shall be required, provided integration with configurations A/B/C is maintained. A minimum of the first

14 inches of the trailing antenna shall be a coaxial cable extension.

3.3.8.2.2. The trailing wire assembly shall be constructed to not snag other equipment during emergency ejection egress (man-seat separation). The trailing wire assembly shall be constructed and integrated to not interfere with parachute canopy deployment or canopy release upon landing in configuration B.

3.3.8.3. Receiving Antennas (If used). If different antennas are used in the design, circuit switching associated with antenna removals or failures shall be automatic.

3.3.8.3.1. Operation of the antennas in any normally operational position, combination, or sequence shall not result in a failure of the PLB to successfully fulfill all performance specifications. The PLB shall not be damaged when operating with either a short or an open circuit on any antenna circuit. The integral GPS receiving antenna shall be compatible with the

GPS receiver/microprocessor, and shall be designed to enable the required GPS functional performance.

3.3.8.3.2. The integral receiving antenna shall be built-in and shall withstand the operational environment to include packing/integration with configurations A/B/C.

3.3.8.4. Trailing wire receiving antenna (If used). The integral GPS receiving antenna shall be compatible with the GPS receiver/microprocessor, and shall be designed to enable the required

GPS functional performance.

3.3.8.4.1. Only as much length as is necessary for optimal GPS performance shall be required, provided integration with configurations A/B/C is maintained. A minimum of the first 14 inches of the trailing antenna shall be a coaxial cable extension.

3.3.8.4.2. The trailing wire assembly shall be constructed to not snag other equipment during emergency ejection egress (man-seat separation) and shall be capable of being stowed in the configurations A/C survival kit. The trailing wire assembly shall be constructed and integrated to not interfere with canopy deployment or canopy release upon landing.

3.3.8.5. Antenna switching priority. If the design warrants external antennas, the PLB shall sense the removal, loss, or complete failure of external trailing wire antenna, transmitting or GPS, and automatically switch to the corresponding integral antenna as needed to maintain transmissions or GPS system operation. The external antennas shall have priority over the integral antennas until an external wire antenna is removed or switched over based on the preceding automatic switching conditions.

3.3.9. Activation and control cable assembly. The activation and control cable assembly shall provide a functional interface between the PLB and configuration A ejection seats as described in the following subsections. The cable assembly shall be employed only in configurations A and shall be a form, fit, and function replacement for the existing control/activation cable assembly(s).

3.3.9.1. The primary function of the cable assembly shall be to provide automatic electrical activation of the PLB upon man-seat separation in an emergency ejection situation. Secondary functions shall include providing (a) the capability for selection of manual or automatic PLB activation, (b) Go/No-Go indicator which shall present the functional status of the PLB functions. The rocker switch of the cable assembly shall provide the capability to select manual or automatic PLB activation as presented in the following Table 3-1, PLB Transmission Status.

C o n fi g u ra ti o n s A

Cable assembly

Rocker Switch

Setting

Plunger Position PLB On/Off Switch Setting

ON OFF

AUTO

Depressed Transmit Silent

Extended Transmit Transmit

MANUAL

Depressed Transmit Silent

Extended Transmit Silent

C o n fi g u ra ti o n

B /C

Mechanical PLB On/Off Switch Setting

Activation Plug

ON OFF

IN PLACE NA Silent Silent

PULLED NA Transmit Silent

Table 3-1. PLB Transmission Status

Note: The PLB is normally packed with the manual ON/OFF control switch OFF in the configurations A, and the switch ON in the configuration B/C.

3.3.9.2. Plunger Switch. The plunger switch shall provide the signal to activate the PLB on man-seat separation. With the plunger depressed (seat pan lid closed), the plunger switch contacts are in the open circuit position (PLB deactivated). The plunger switch shall be stored in its compressed (plunger depressed/open circuit) state, indicating to the PLB that the assembly has not left the seat kit enclosure. Upon man-seat separation, when the seat pan lid opens, it releases the plunger switch to the extended or closed circuit position, which shall then activate the PLB if automatic activation has been selected on the rocker switch.

3.3.9.2.1. The plunger switch shall be a single pole, two-position, normally closed momentary switch. The plunger switch shall have a spring force of 5 lbs. ± 1 lb. holding the switch open.

3.3.9.2.2. The plunger switch assembly total height, diameter, distance of travel shall fit the plunger switch holder.

3.3.9.3. Rocker Switch assembly. The rocker switch assembly shall serve as the mounting point for a Go/No-Go indicator. The position of the Go/No-Go indicator shall be such that it may be seen from above by the seated aircrew when the rocker switch assembly is mounted to the ejection seat assembly.

3.3.9.3.1. The rocker switch assembly shall fit the rocker switch holder.

3.3.9.3.2. Rocker switch motion shall move the switch from open (manual operation selection) to closed (automatic operation selection) and stay in either selected position.

3.3.9.3.2.1. When viewed by the aircrew sitting in the ejection seat, manual shall be to the left and automatic shall be to the right. To the seated aircrew, a red dot shall be visible on the left when the automatic setting is selected, and a green dot shall be visible on the right when the manual setting is selected.

3.3.9.3.3. The rocker switch shall have the ability to be safety pinned in the manual operating position. The safety pin opening shall be able to accommodate safety pin P/N A1-16-0207, or equivalent size.

3.3.9.3.4. The rocker switch assembly body shall integrate a Go/No-Go indicator. The Go/No-Go indicator shall be positioned in the rocker switch assembly such that it can be viewed by the user when the assembly is mounted in the rocker switch holder in the ejection seat assembly.

3.3.9.4. Cable assembly connector and wire bundle physical characteristics.

3.3.9.4.1. The wires between all elements of the cable assembly shall be bundled in self-extinguishing wiring sleeves. The cable assembly wire sleeves shall successfully pass FAR 25-

853, Appendix F, Part I (b) (7), sixty degree test.

3.3.9.4.2. The wire bundle shall not present any snag hazards. It shall not interfere with the operation of the seat or aircrew during a normal mission, normal ground egress, emergency ground egress, or with the ejection sequence and shall be oriented to facilitate stowage of the cable and wiring bundle in the existing survival kit retaining straps

3.3.9.4.3. Cable assembly wires shall be color-coded to facilitate their identification.

3.3.9.4.4. Wires shall be sized to perform their intended function and remain intact during handling and after exposure to ejection forces.

3.3.9.4.5. Components and wires of the assembly shall be shielded to minimize electromagnetic interference.

3.3.10. Automatic mechanical activation device. The automatic mechanical activation device shall be employed only in the configuration B/C. Automatic PLB activation shall be initiated by the complete removal of a mechanical control device, pulled on canopy deployment by a lanyard or cord connected to the parachute riser in the configuration B. Automatic PLB activation shall be initiated by the complete removal of a mechanical control device, pulled on man/seat separation by a lanyard or cord connected to the seat in the configuration C.

3.3.10.1. The PLB mechanical activation device shall be designed so that within the C/S T.001

Class 2 operating temperature range, a pull force of 15 to 25 lbs. shall cause complete extraction of the mechanical activation device. The mechanical activation device shall continue to require a pull force of 15 lbs. to 25 lbs. for a series of pulls in at least 8 cardinal directions (0°/360°, 45°, 90°, 135°, 180°, 225°, 270° 315°) around the horizontal plane with the activation plug facing up.

In the vertical plane, the activation plug shall be pulled in plane at 0° and then off plane at 45°, and 70°. Each orientation shall be done at both the high and low operational temperatures of -4°

F and +131° F.

3.3.10.2. The mechanical activation device shall be installed on the end of the PLB case which extends from the stowage pocket of the configurations B parachute (the same face of the PLB that contains the controls and connectors). The nominal pull direction is perpendicular to the plane of that face of the PLB case.

3.3.11. Lanyard. A lanyard shall be required to prevent loss of the PLB after an emergency ejection or bailout event. The lanyard shall be designed to connect the PLB case to a life raft, survival vest, or other article of clothing.

3.3.11.1. One end of the lanyard shall be securely fastened to the PLB case. The other end shall include a sliding loop, carabineer, clip, or other means to attach securely to a life raft or clothing.

This attachment shall be capable of one-handed, gloved operation and shall include a means of preventing inadvertent release.

3.3.11.2. The lanyard shall be a nylon cord, NSN 4020-10-214-5128 (MIL-C-5040, Type IA), 3

ft. ± 1 inch in length, with a break strength of 100 lbs.

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

3.4.1. Storage temperature. . The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification after storage at any temperature in the range of (-67° F to +185° F). This environmental requirement shall be IAW MIL-STD-810, Method 501.5, Procedure I, High Temperature Storage and Method 502.5, Procedure I, Low

Temperature Storage.

3.4.2. Temperature shock. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification when subjected to temperature shock through the operating temperature range. This environmental requirement shall be validated IAW MIL-STD-

810, Method 503.5 Procedure I utilizing the temperature storage extreme limits of the C/S T.001

Class 1 operating temperature range.

3.4.3. Operating temperature. The PLB shall be capable of operating per the requirements of

Section 3 of this performance specification over C/S T.001 Class 2 operating temperature range.

The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD-810, Method 501.5 and 502.5, Procedure II, and Method 502.5, Procedure II.

3.4.4. Transit shock pulse. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification after exposure to transit shock pulses. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD 810, Method 516.6, Procedure IV (Transit Drop).

3.4.5. Vibration curves. The PLB shall not be damaged and shall operate per the requirements of

Section 3 of this performance specification after exposure to vibrations representing jet and propeller aircraft, to include a gunfire profile. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD 810, Method 514.6 Procedure I, General

Vibration for the vibration curves representing jet (both C-5 and F-16) and propeller aircraft (C-

130 with four bladed propellers) at ambient ground level conditions. The vibration testing shall be performed on the same PLB used for high/low storage temperature testing which shall be performed prior to vibration testing. The PLB shall also be tested for gun fire transient vibrations

IAW MIL-STD 810, Method 519.6, Procedure II, (Stochastically Generated Materiel

Input/Response Based Upon Measured Time Trace Information), utilizing an F-16 as the representative aircraft. The PLB shall be in a non-operational state/configuration during the test with all external antennas and cables connected.

3.4.6. Functional shock. The PLB shall not be damaged and shall operate per the requirements of

Section 3 of this performance specification after exposure to functional shocks. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD 810, Method

516.6 Procedure I (Functional Shock). The PLB shall be in a non-operational state/configuration during the shock test with all external antennas and cables connected.

3.4.7. Temperature, humidity, and altitude. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification when subjected to the combined effects of temperature, altitude, and humidity. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD-810, Method 520.3, Procedure III and specific combinations listed in the table below.

Temperature Humidity Altitude Duration

-40 o

F <10% Ground 60 minutes

+68 o

F 90% 15,000’ 60 minutes

+104

F 40-60% Ground 60 minutes

3.4.8. Acceleration. The PLB shall not be damaged and shall operate per the requirements of

Section 3 of this performance specification after exposure to accelerations of 40 Gs forward, 7

Gs aft, 10 Gs up, 25 Gs down, and 14 Gs left and right as identified in MIL-STD-810, Method

513.6, Table 513.6-III (ejection seat). Directions are defined as the PLB is installed in the configurations A/C, with forward direction facing the nose of the aircraft. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD-810, Method

513.6, Procedure III.

3.4.9. Explosive atmosphere. The PLB shall operate in explosive atmospheres without causing an explosion, i.e., the PLB shall not produce any sparking when switches are operated, or when antennas or other devices are connected or disconnected. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification. This environmental requirement shall be validated IAW MIL-STD-810, Method 511.5, at +185° F with n-hexane fuel, to determine its ability to operate in explosive atmospheric conditions without causing an explosion or initiating combustion. Configurations A/C PLB shall be activated and allowed to operate in triple frequency mode for one hour under the described test conditions. In addition, the vendor shall devise a method to exercise all switches, plungers, and controls a minimum of 3 complete cycles during the one hour period within the n-hexane saturated environment.

3.4.10. Rapid decompression. The PLB shall remain structurally intact and shall operate per the requirements of Section 3 of this performance specification after exposure to rapid decompressions. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD 810, Method 500.5 Procedure III, for operation after exposure to rapid decompressions from 8,000 ft. to 60,000 ft. over a duration of 10 seconds, and then returning to ambient pressure within a 2 minute time period. The test shall be repeated for three cycles.

3.4.11. Explosive decompression. The PLB shall remain structurally intact and shall operate and meet all requirements after being subjected to the explosive decompression experienced in aircraft ejection or catastrophic loss of pressurization during flight operations. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification. This environmental requirement shall be validated IAW MIL-STD-810, Method

500.5, Procedure IV, to determine its ability to withstand explosive decompression from 8,000 ft.

to 60,000 ft. over duration of 0.1 second, and then returning to ambient pressure within a 2 minute time period.

3.4.12. Solar radiation. The PLB shall not be damaged and shall operate per the requirements of

Section 3 of this performance specification after exposure to solar radiation. The PLB shall meet all the requirements of this specification within this environment and performance shall not be

505.5, Procedure I.

3.4.13. Sand and dust. The PLB shall not be damaged and shall operate per the requirements of

Section 3 of this performance specification after exposure to blowing dust. The PLB shall meet all the requirements of this specification within this environment and performance shall not be

510.5, Procedure I and II.

3.4.14. Water resistance. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification after immersion in salt water or fresh water after exposure to 3.28 feet for 2 hours and 25 feet for 5 minutes. The PLB design shall allow operation while immersed at the specified depths when connected to an antenna located above the water's surface. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated by

MIL-STD-810, Method 512.5, Procedure I (Immersion), to determine its ability to withstand immersion and using MIL-STD-810, Method 506.5, Procedure III (Drip) to determine its ability to withstand falling water from condensation or leakage from upper surfaces.

3.4.15. Humidity. The PLB shall not be damaged and shall operate per the requirements of

Section 3 of this performance specification in relative humidity levels of 95% relative humidity at +131° F. The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD-810, Method 507.5.

3.4.16. Moisture with salt. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification during and after exposure to moisture with salt.

The PLB shall meet all the requirements of this specification within this environment and performance shall not be degraded. This environmental requirement shall be validated IAW MIL-STD-810, Method 509.5.

3.4.17. Fungus. Materials used in the fabrication of the PLB shall not support fungal growth.

Hexavalent chromium may not be used to impede fungal growth. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification. This environmental requirement shall be validated IAW MIL-STD-810, Method 508.6.

3.4.18. Electrostatic buildup and discharge. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification after being subjected to electrostatic discharge (ESD) pulses. The PLB shall not be damaged and shall operate per the requirements of Section 3 of this performance specification. This environmental requirement shall be validated IAW RTCA/DO-160, Section 25 with tailoring per IEC 61000-4-2 Level 2, direct contact discharge only method. Ten IEC 61000-4-2 Level 2- direct contact discharge positive pulses and ten IEC 61000-4-2 Level 2- direct contact discharge negative pulses shall be applied to various conductive exterior points. Connector pins will not be tested.

3.5. Reliability and maintainability.

3.5.1. Service life. The PLB shall operate and meet all specification requirements for a minimum service life of 10 years, given no bailout or ejection events occur and routine maintenance practices are observed.

3.5.1.1. For configuration A, routine maintenance is an inspection and serviceability check every

365 days, timed to coincide with ACES II seat kit removal for annual inspection.

3.5.1.2. For configuration B, routine maintenance is an inspection and serviceability check every

365 days, timed to coincide with BA series/LPP parachute inspection.

3.5.1.3. For configuration C, routine maintenance is an inspection and serviceability check every

365 days, timed to coincide with Martin Baker seat kit removal for annual inspection.

3.5.2. Maintainability. The PLB shall not require routine maintenance other than a periodic BIT functional check and battery replacement as necessary. Fault isolation, component testing, removal, and repair shall be possible by qualified Air Force Specialty Code 1T1X1 maintenance personnel accomplished using common shop tools.

3.5.2.1. Technical orders (TOs), software (if required), and vendor documentation and manuals for integration/operation and repair will include illustrated parts breakdowns, parts listings, material and safety hazards, and diagrams, theory of operation, maintenance, and troubleshooting guides. The Technical Manual supplied by the vendor, if provided, will be used as a baseline for the development of a USAF Technical Order (TO). Technical orders and software (if required) will comply with the standards and manual requirements as prescribed in Air Force Technical

Order (TO) 00-5-1, TO 00-5-3, and TO 00-5-16. Technical orders will be delivered in digital format and will be fully compatible with the Joint Computer Aided Acquisition and Logistics

Support System (JCALS).

3.5.2.2. Mean time to Repair (MTTR). The MTTR of the repairable system components shall be

0.5 hour. MTTR is defined as the total elapsed time (clock hours) for corrective maintenance divided by the total number of corrective maintenance actions during a given period of time.

3.5.3. Reliability. The minimum system reliability shall be no less than 99.5%…