PCPLT_System_Spec_(SS)_1_6.pdf

DESTRUCTION NOTICE

FOR UNCLASSIFIED, LIMITED DOCUMENTS, DESTROY BY ANY

METHOD THAT WILL PREVENT DISCLOSURE OF CONTENTS OR

RECONSTRUCTION OF THIS DOCUMENT

PMA260C21/3490/V1.6

MAY 20, 2015

DEPARTMENT OF THE NAVY

PROGRAM EXECUTIVE OFFICE PMA260

NAVAL AIR SYSTEMS COMMAND

PATUXENT RIVER, MARYLAND 20670-1547

SYSTEM SPECIFICATION

FOR THE

PNEUMATIC CABIN PRESSURE LEAKAGE TESTER

(PCPLT)

DISTRIBUTION STATEMENT A: APPROVED FOR PUBLIC RELEASE; DISTRIBUTION IS UNLIMITED.

APPROVED: ___________________________ APPROVED: ____________________________

TITLE: Logistics Integration Management TITLE: SE & ALRE Systems Engineering

(AIR-6.6) (AIR-4.8.1)

Date: _________ Date: _________

APPROVED: ____________________________

Title: Program Manager

(PMA260C)

Date: _________

REVISION HISTORY

DATE VERSION REMARKS AUTHOR

20 MAY 2014 1.0 FINAL SIGNED T. CONWAY

10 FEB 2013 1.4

MINOR CHANGES INCORPORATED PRIOR TO RFP. SEE

PCPLT SPEC COMMENT TRACKER POST SP FOR DETAILED

CHANGES.

T. CONWAY

APPVD BY

J. FRENCH

9 MARCH 2015 1.5

GLOBAL CHANGE “CANOPY SEAL” TO CANOPY/DOOR

SEAL”. PARA 4.2.4.3.4- CHANGE 90 PSI TO 80 PSI TO

MATCH PARA 3.2.2.2 FACILITY AIR LOW CONDITION

T. CONWAY

20 MAY 2015 1.6

PARA 2.2: DELETE MIL-STD-740-1, 3.2.7 TABLE 1:

ADDED SHIP SUPPLY AIR ADAPTER AND MALE NPT

ADATER, 3.3.3.1: CHANGE FACILITY SHOP AIR FITTING

FROM FEMALE TO MALE, 3.3.14.2 & 4.2.5.3: ADDED DB

LIMIT FOR SOUND,

T. CONWAY

Table of Contents i

1.0 SCOPE

1.1 Identification

1.2 Document Overview

2.0 APPLICABLE DOCUMENTS

2.1 General

2.2 Government Documents

2.3 Non- Government Documents

2.4 Order of Precedence

3.0 SYSTEM REQUIREMENTS

3.1 Definition

3.2 Characteristics

3.2.1 Performance Characteristics

3.2.1.1 Canopy/Door Seal Pressure and Flow Capability

3.2.1.2 Cabin Air Pressure and Flow Capability

3.2.2 Interface Requirements

3.2.2.1 Facility Interface

3.2.2.2 Facility Compressed Air Interface

3.2.2.2.1 Compressed Air Supply Hose

3.2.2.2.2 Compressed Air Supply Hose Shutoff

3.2.2.3 Operator Interface

3.2.2.3.1 Location of Controls and Instrumentation

3.2.2.4 Aircraft Interface

3.2.2.4.1 Canopy/Door Seal Supply Hose

3.2.2.4.2 Canopy/Door Seal Pressure Check Hose

3.2.2.4.3 Cabin Air Supply Hose

3.2.2.4.4 Cabin Air Pressure Check Hose

3.2.3 Controls

3.2.3.1 Canopy/Door Seal Pressure Regulation

3.2.3.2 Canopy/Door Seal Shutoff Control

3.2.3.3 Canopy/Door Seal Maximum Pressure Control

3.2.3.4 Cabin Air Flow Control

ii

3.2.3.5 Cabin Air Pressure Control

3.2.3.6 Cabin Air Rate of Pressure Change Control

3.2.3.7 Cabin Air Shutoff Control

3.2.3.8 Cabin Air Maximum Pressure Control

3.2.3.9 Rate of Cabin Pressure Change Shutoff Valve

3.2.3.10 Compressed Air Supply Hose Depressurization

3.2.4 Instrumentation/Indicators

3.2.4.1 Calibration

3.2.4.2 Pressure Gauges

3.2.4.2.1 Canopy/Door Seal Output Pressure

3.2.4.2.2 Canopy/Door Seal Check Pressure

3.2.4.2.3 Cabin Air Output Pressure

3.2.4.2.4 Cabin Air Check Pressure

3.2.4.2.5 Pressure Equalization Indicator/Rate of Cabin Pressure Change

3.2.4.2.6 Supply Pressure

3.2.4.3 Flow Meters

3.2.4.3.1 Canopy/Door Seal Output Flow

3.2.4.3.2 Cabin Air Output Flow

3.2.4.4 Temperature Sensors/Probes

3.2.4.4.1 Cabin Air Temperature Output

3.2.5 Filters

3.2.5.1 Servicing/Consumable Indicators

3.2.5.2 Particulate Filter Dryer

3.2.5.3 Oil/Water Separator

3.2.6 Physical Characteristics

3.2.6.1 Dimensions

3.2.6.2 Weight

3.2.7 Accessories

3.2.8 System Quality Factors

3.2.8.1 Reliability

3.2.8.1.1 Mean Time Between Failures

iii

3.2.8.2 Maintainability

3.2.8.2.1 Maintenance Provisions

3.2.8.2.2 Mean Time to Repair

3.2.8.2.3 Pressure Line Replacement

3.2.8.2.4 Interchangeability

3.2.8.2.5 Common/ Standard Tools

3.2.8.2.6 Special Tools

3.2.9 Environmental Conditions

3.2.9.1 Temperature, Storage

3.2.9.2 Temperature, Operation

3.2.9.3 Humidity

3.2.9.4 Salt Fog

3.2.9.5 Shipboard Vibration

3.2.9.6 Transportation Vibration

3.2.9.7 Shock

3.2.9.8 High-Impact Shock Tests

3.2.10 Operation Under Tilt

3.3 Design and Construction

3.3.1 Mobility

3.3.1.1 Mobility System

3.3.1.2 Tires/Wheels

3.3.1.3 Deadman Brake

3.3.1.4 Air Transportability

3.3.2 Housing

3.3.3 Access Panel

3.3.4 Lifting/ Tie Down Provisions

3.3.5 Fork Lifting

3.3.6 Storage

3.3.7 Tubes and Hoses

3.3.8 Captive Devices

3.3.9 Fastening Devices

iv

3.3.10 Coating

3.3.11 Materials

3.3.11.1 Fittings and Tubing

3.3.11.2 Corrosion Protection

3.3.11.3 Hazardous Materials

3.3.11.4 Restricted Chemicals

3.3.11.4.1 Hexavalent Chromium

3.3.11.5 Targeted Chemicals

3.3.11.6 Metal Alloys

3.3.11.7 Lead

3.3.12 Markings, Identification, and Placards

3.3.12.1 Markings

3.3.12.2 Reflective Markings

3.3.12.3 Identification Plate

3.3.12.4 Modification Plate

3.3.12.5 Caution and Warning Labels

3.3.12.5.1 Temperature Warning

3.3.12.6 Flow Schematic

3.3.12.7 Flow Meter Chart

3.3.13 Workmanship

3.3.13.1 Quality Management Systems

3.3.13.2 Workmanship (General)

3.3.14 Safety

3.3.14.1 System Design

3.3.14.2 Sound Attenuation

3.3.14.3 Grounding Provisions

3.3.15 Human Engineering

3.3.15.1 Human Factors / Human Engineering

4.0 QUALITY ASSURANCE PROVISIONS

4.1 General Quality Assurance Provisions

4.1.1 Responsibility for Compliance

v

4.1.2 Contractor Requirements

4.1.3 Classification of Tests

4.2 Pilot-Production

4.2.1 Repair of Defects

4.2.2 Final Approval and Acceptance

4.2.3 Classification of Inspections and Tests

4.2.4 Pilot-Production Test I (PPT I)

4.2.4.1 Reliability Analysis

4.2.4.2 Maintainability Demonstration

4.2.4.3 Aircraft Functional Simulation Testing

4.2.4.3.1 Maximum Pressure Controls Verification

4.2.4.3.2 Canopy/Door Seal Pressure and Leakage Flow Rate Verification

4.2.4.3.3 Cabin Air Pressure Verification

4.2.4.3.4 Cabin Air Allowable Leakage Flow Rate Verification

4.2.4.3.5 Shutdown/Depressurization

4.2.4.4 Operation Under Tilt

4.2.4.5 Mobility, General Test

4.2.4.6 General Safety Testing

4.2.4.7 Deadman Brake Test

4.2.4.8 Demonstration Test

4.2.4.9 Performance Test

4.2.4.10 Inspection

4.2.4.11 Analysis

4.2.5 Pilot-Production Test II (PPT II)

4.2.5.1 Environmental Compatibility

4.2.5.2 Duty Cycle

4.2.5.3 Sound Attenuation Test

4.2.6 Production Acceptance Tests (Accept)

5.0 PREPARATION FOR DELIVERY

5.1 Preservation

5.2 Domestic Packaging

vi

5.3 International Packaging and Preservation

5.4 Consolidated Packaging

5.5 Exterior Package Marking

6.0 NOTES

6.1 Acronyms and Abbreviations

APPENDIX A – POWDER COATING

APPENDIX B – EPOXY COATING

APPENDIX C - IDENTIFICATION PLATE

APPENDIX D - MODIFICATION PLATE

APPENDIX E – CALIBRATION REFERENCE TABLE

APPENDIX F - VERIFICATION CROSS REFERENCE MATRIX

List of Figures and Tables vii

Figures

Figure 1 – PCPLT Hose Connection Set-up

Tables

Table 1 - Accessories

Table 2 - Functional Simulation Test Settings

Table 3 - Environmental Test methods for PCPLT, Procedures and Parameters

Table 4 - Duty Cycle Test Settings

1.0 SCOPE

1.1 Identification

This document establishes the system requirements for the Pneumatic Cabin Pressure Leakage Tester (PCPLT).

1.2 Document Overview

Herein, the Pneumatic Cabin Pressure Leakage Tester (PCPLT) will be referred to as PCPLT or "the tester."

Section 2 provides a list of applicable reference documents.

Section 3 documents the required characteristics of the tester. This section begins by identifying the performance characteristics of the new tester through functionality requirements and corresponding performance requirements which will identify what the tester must be capable of doing. Next, this specification identifies the external systems, with which the tester must interact, and the physical connections, or links, used in each interaction. The specification then focuses on overall tester requirements such as those for physical characteristics, environmental considerations, design, and construction.

Section 4 indicates the quality assurance provisions of the tester. This section lists each verification method that will be used to verify that the requirements of Section 3 have been met.

Section 5 specifies the packing, packaging, and marking requirements.

Section 6 lists acronyms and abbreviations used in this document.

2.0 APPLICABLE DOCUMENTS

2.1 General

If a conflict exists between this specification and any other document specified herein, this specification takes precedence. In those instances within this specification, where commercial and military specifications and standards are indicated as “guidance only”, the contractor is given latitude in equipment selection, material selection, component selection, etc. This in no way relieves the contractor from the responsibility of successfully passing the performance tests in Section 4 of this specification. Military specifications/standards and industry standards identified in this document establish minimum performance requirements. Equivalent or better specifications and standards may be substituted upon approval of the Navy. The Current Revision and most recent Notice of Change at contract award shall be used unless otherwise stated.

2.2 Government Documents

SPECIFICATIONS & STANDARDS

Military

MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests

MIL-STD-1472 Human Engineering

MIL-STD-209 Slinging and Tiedown Provisions for Lifting and Tying Down Military

Equipment

MIL-DTL-83413 Connectors And Assemblies, Electrical, Aircraft Grounding, General

Specification For

MIL-STD-882 Standard Practice System Safety

MIL-STD-889 Dissimilar Metals

MIL-S-901 Shock Tests, H.I. (High-Impact) Shipboard Machinery, Equipment, and

Systems, Requirements For

DRAWINGS

NAVAIR 1353AS156 Coating Procedure

NAVAIR 1905AS300 Coating Procedure, Powder Coating, White

NAVAIR 3909AS9999 Identification Plate

NAWCAD 5SE00363 Modification Plate

OTHER PUBLICATIONS

Regulation

49 CFR Code of Federal Regulations Title 49: Protection

29 CFR Code of Federal Regulations Title 29: Labor

40 CFR Code of Federal Regulations, Title 40, Protection of Environment

DFARS Defense Federal Acquisition Regulation Supplement

Handbook

MIL-HDBK-470 Designing And Developing Maintainable Products And Systems

MIL-HDBK-1791 Designing for Internal Aerial Delivery in Fixed Wing Aircraft

2.3 Non- Government Documents

STANDARDS

SAE AS 8090 General Requirements for Towed Aerospace Ground Equipment

Mobility

ASTM D 4956 Standard Specification for Retroreflective Sheeting for Traffic Control

ISO 9001-2000/ISO

9001-2008 Quality Management Systems - Requirements

ISO 8573-1 Compressed air - Part 1: Contaminants and purity classes

OTHER PUBLICATIONS

2.4 Order of Precedence

In the event of a conflict between this specification and the references cited herein, the text of this specification takes precedence. If a conflict exists between an English measurement and a metric measurement, the English measurement shall take precedence. In the event of a conflict between Section 3 and Section 4 of this

Performance Specification, Section 3 shall take precedence. Nothing in this specification, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3.0 SYSTEM REQUIREMENTS

3.1 Definition

The Pneumatic Cabin Pressure Leakage Tester (PCPLT) will be used to check aircraft cabin/cockpit pressure control system components (e.g. Canopy/Door seal, pressure regulation valves, safety relief valves) for proper function and to provide troubleshooting and verification capability. The tester regulates and controls the pressure and volume of air supplied to the aircraft. Pressure gauges and flow meters are used to determine if the aircraft cabin pressure control system is operating within correct parameters. The PCPLT shall consist of a main control unit and various hoses and accessories to facilitate the proper connection to an aircraft and externally supplied compressed air source.

3.2 Characteristics

3.2.1 Performance Characteristics

The PCPLT shall perform the following requirements (3.2.1.1 and 3.2.1.2) simultaneously.

3.2.1.1 Canopy/Door Seal Pressure and Flow Capability

The PCPLT shall regulate air pressures of up to 35 PSIG at an air flow of at least 1.1 SCFM to a Canopy/Door seal.

3.2.1.2 Cabin Air Pressure and Flow Capability

The PCPLT shall be capable of regulating air pressures of up to 14 PSIG at an air flow of at least 235 SCFM to an aircraft cabin.

3.2.2 Interface Requirements

3.2.2.1 Facility Interface

The PCPLT shall be able to connect to facility compressed air with a 1 inch facility-side male NPT fitting.

3.2.2.2 Facility Compressed Air Interface

The PCPLT shall be designed for a shipboard or shore facility that can supply 110 to 300 SCFM of compressed air at pressures that may fluctuate from 80 to 155 PSIG. The maximum SFCM of regulated air flow that the

PPCLT shall be able to supply to an aircraft cabin shall not be less than 78% of the SCFM supplied by the facility.

3.2.2.2.1 Compressed Air Supply Hose

The compressed air supply hose shall be at least 1 ¼ inch inner diameter and 75 feet long. Attaching hose ends shall be at least 1 inch Quick Disconnects.

3.2.2.2.2 Compressed Air Supply Hose Shutoff

The PCPLT shall allow an operator at the control panel to quickly shut off flow and pressure to the PCPLT from the facility compressed air supply.

3.2.2.3 Operator Interface

3.2.2.3.1 Location of Controls and Instrumentation

All controls and instrumentation shall be located in a central location on top of the PCPLT so that one operator can operate the tester properly and safely while standing.

3.2.2.4 Aircraft Interface

3.2.2.4.1 Canopy/Door Seal Supply Hose

The PCPLT Canopy/Door supply hose shall be an AN6270-4 type hose assembly with 30 feet minimum length.

3.2.2.4.2 Canopy/Door Seal Pressure Check Hose

Not Required.

3.2.2.4.3 Cabin Air Supply Hose

The cabin air supply hose shall have 30 feet minimum length, a minimum 2 inch hose inner diameter, and

Quick Disconnects or hand tightened swivel fitting at both ends.

3.2.2.4.4 Cabin Air Pressure Check Hose

The PCPLT cabin air pressure check hose shall be an AN6270-4 type hose assembly with 30 feet minimum length.

3.2.3 Controls

The PCPLT controls shall provide the following capabilities.

3.2.3.1 Canopy/Door Seal Pressure Regulation

The PCPLT shall allow an operator to regulate pressure and flow to an aircraft Canopy/Door seal.

3.2.3.2 Canopy/Door Seal Shutoff Control

The PCPLT shall have a quarter turn valve to allow an operator to open and shut off pressure and air flow to the

Canopy/Door seal.

3.2.3.3 Canopy/Door Seal Maximum Pressure Control

The PCPLT shall have a safety relief valve to prevent over pressurization of the canopy/door seal adjustable from 10 to 35 psi, adjustable from the control panel.

3.2.3.4 Cabin Air Flow Control

The PCPLT shall allow an operator to regulate and maintain pressure and flow to an aircraft cabin.

3.2.3.5 Cabin Air Pressure Control

The PCPLT shall allow an operator to adjust, regulate, and set the pressure of air supplied to pressurize an aircraft cabin. The pressure regulating device shall be free from chatter.

3.2.3.6 Cabin Air Rate of Pressure Change Control

The PCPLT shall allow the operator to control the rate of pressure change to simulate cabin pressure change during an aircraft climb or descent of at least 6,000 feet per minute (ft/min). This rate shall be adjustable and allow cabin pressure to be increased or decreased at rates up to 500 ft/min at flows of 10 to 50 SCFM and up to

250 ft/min at flows of 50 to 235 SCFM.

3.2.3.7 Cabin Air Shutoff Control

The PCPLT shall have a quarter turn valve to allow an operator to open and shut off pressure and air flow to the cabin.

3.2.3.8 Cabin Air Maximum Pressure Control

The PCPLT shall have a safety relief valve for the cabin air pressure circuit adjustable by the operator from 5 psi to 10 psi, adjustable from the control panel.

3.2.3.9 Rate of Cabin Pressure Change Shutoff Valve

The PCPLT shall have a shutoff valve or similar means to isolate the rate of cabin pressure change measuring device.

3.2.3.10 Compressed Air Supply Hose Depressurization

The PCPLT shall allow an operator to safely depressurize all hoses for storage prior to disconnecting them from the tester. A caution to “Close facility’s compressed air valve prior to relieving pressure and disconnecting hose” shall be on the PCPLT in an appropriately visible area near to the point where the compressed air supply hose attaches to the PCPLT. There shall be a visual indicator notifying an operator that supply hose is still pressurized.

3.2.4 Instrumentation/Indicators

The PCPLT instrument control panel shall have all necessary instruments, gauges, and/or displays for all relevant parameters to include but not be limited to; pressure, flow, and temperature. The panel and its accessories shall be readily accessible to the operator and all items shall be mounted so that they may be easily removed for replacement or servicing. The instrumentation/control panel shall have a protective cover to prevent damage from small impacts. This cover shall remain attached to the PCPLT when the PCPLT is in use.

Instruments subject to errors from vibration shall be mounted to dampen effects of vibration.

3.2.4.1 Calibration

The PCPLT shall allow calibration of analog gauges, rate of climb indicator, and flow meters in place. Isolation shutoff valves shall be provided to allow for circuit isolation. If applicable, an access port in the housing shall be provided to allow removal of temperature sensor/probes from the discharge flow meter.

3.2.4.2 Pressure Gauges

All pressure gauges used for obtaining and displaying data on the PCPLT shall be analog. All pressure gauges shall incorporate a safety blowout device to automatically relieve the gauge case should the pressure reach 0.50

PSIG due to gauge failure.

3.2.4.2.1 Canopy/Door Seal Output Pressure

The PCPLT shall measure and display air pressure outputs to and from an aircraft canopy/door seal with a range from 0 to 30 PSIG at increments of 0.2 PSIG with an accuracy of +/- 3% of full scale.

3.2.4.2.2 Canopy/Door Seal Check Pressure

Not required.

3.2.4.2.3 Cabin Air Output Pressure

The PCPLT shall display air pressure after the flow control valve and prior to an air flow measuring device with a range from 0 to 15 PSIG in increments of 0.1 PSIG with an accuracy of +/- 0.5% of full scale.

3.2.4.2.4 Cabin Air Check Pressure

The PCPLT shall display air pressure in an aircraft cabin with a minimum range from 0 to 15 PSIG in increments of 0.1 PSIG with an accuracy of +/- 0.5% of full scale.

3.2.4.2.5 Pressure Equalization Indicator/Rate of Cabin Pressure Change

The PCPLT shall display the rate of pressure change in the aircraft cabin, via the cabin air pressure hose, as rate of climb or descent in feet per minute. A range of +/-6000 ft/min with 100 ft/min increments for pressure changes below 1500 ft/min and 500 ft/min increments for changes exceeding 1500 ft/min. the tester shall have a visual indication in red to warn the operator when pressure change goes below -5000 ft/min and when it exceeds

5000 ft/min and a caution plate warning not to increase or decrease cabin pressurization at red-lined rates. The tolerance shall be +/- 12 sec at 1000 ft, +/- 9 sec at 1500 ft, and +/- 6 sec at 5000 ft.

3.2.4.2.6 Supply Pressure

The PCPLT shall measure and display air pressure supplied to the tester from the facility with a minimum range from 0 to 160 PSIG with an accuracy of +/- 1% of full scale.

3.2.4.3 Flow Meters

A protective covering shall be provided over the flow meter to protect the operator from injury. If using a flow meter that has pressure lines, pressure lines shall be graduated in at most 2 PSIG increments throughout the pressure range.

3.2.4.3.1 Canopy/Door Seal Output Flow

Requirement removed. No longer required by any aircraft procedure.

3.2.4.3.2 Cabin Air Output Flow

The PCPLT shall measure and display air flow rate to the aircraft cabin with a minimum range from 0 to 235

SCFM for pressures up to 16 PSIG with an accuracy of +/- 5% of full scale.

3.2.4.4 Temperature Sensors/Probes

Temperature sensors/probes shall be located so that they will be easily accessible for calibration on site.

3.2.4.4.1 Cabin Air Temperature Output

The PCPLT shall measure and display the temperature of the air supplied by the tester to an aircraft cabin with a minimum range of 40 to 120F. The temperature indicator shall measure the temperature of the pressurized air on the discharge side of the flow meter. Increments shall be at most 5F for temperatures below 100F and at most 2F increments for temperatures of 100F or higher. Gauge shall be dual scale for both Fahrenheit and

Celsius with similar increments for C scale. The tolerance shall be +/- 3% of full scale from 40 to 80F and +/-

2% of full scale from 80 to 120F.

3.2.5 Filters

All filters shall be accessible through panels and shall not require the removal of components, lines, or hoses to change.

3.2.5.1 Servicing/Consumable Indicators

The PCPLT shall have visual indicators (sight gauges, differential pressure indicators) to notify an operator when consumable items (e.g. filters) have to be serviced or replaced.

3.2.5.2 Particulate Filter Dryer

The PCPLT shall be equipped with an air filter, as defined in ISO 8573-1:2010[1:3:1], to prevent contaminating the aircraft cabin/cockpit pressure control system components.

3.2.5.3 Oil/Water Separator

The PCPLT shall have an oil/water separator to clean shop air coming into the PCPLT by meeting the requirements as defined in ISO 8573-1:2010[1:3:1]. All oil/water filter housings shall provide a drain for the housing. The drain shall be positioned so that a container large enough to receive all the fluid from a full separator can be placed below the drain valve.

3.2.6 Physical Characteristics

3.2.6.1 Dimensions

The PCPLT envelope dimensions (LxWxH) shall be at maximum 42” x 42” x 48” for storage. The PCPLT shall have a minimum ground clearance of 3.5". All components shall be within these envelope dimensions.

3.2.6.2 Weight

The PCPLT shall not exceed 400 lbs. The weight shall include all hoses and adaptors.

3.2.7 Accessories

The following items shall be included as part of the unit.

Table 1 - Accessories

NOMENCLATURE DESCRIPTION

1-1/4” Adapter Used to adapt hose to aircraft. Cabin Air Supply Hose to UNF-2B 1-1/4-12 thread.

2-3/8” Adapter Used to adapt hose to aircraft. Cabin Air Supply Hose toUN-2B 2-3/8-12 thread.

Adapter, Ship Air Used to adapt supply hose to shipboard facility compressed air source, Use drawing DWG3867AS109

Adapter, Facility Used to adapt supply hose to 1" NPT facility air source.

Wrenches Service Wrenches of spans greater than 1" to connect/disconnect tester's hoses

Adapter -10 F JIC swivel fitting (fits F-35 aircraft -10 M JIC test port) to supply hose

Adapter -6 M JIC to -4 F JIC swivel

Adapter -6 M JIC to -3 F JIC swivel

Gaskets, Replaceable For 1 ¼ and 2 3/8 adapters

3.2.8 System Quality Factors

3.2.8.1 Reliability

3.2.8.1.1 Mean Time Between Failures

The PCPLT shall have a Mean Time Between Failure (MTBF) of not less than 215 hours in a Naval Sheltered

(NS) environment. A failure is defined as the PCPLT’s inability to perform all required functions to the full extent of this specification.

3.2.8.2 Maintainability

3.2.8.2.1 Maintenance Provisions

The PCPLT shall be constructed so that lubrication, adjustments, repairs, and overhaul can be easily accomplished by personnel using common hand tools. All components shall be selected and located for ease of operation, servicing, inspections, and maintenance; shall be able to service and visually inspect without removing panels or components.

3.2.8.2.2 Mean Time to Repair

The PCPLT shall have a Mean Time To Repair (MTTR or c) of 1.5 hours or less, at the Intermediate maintenance level. The MTTR shall include corrective maintenance (CM) task times and shall consist of the times of each subtask element comprising the CM action, including: fault/failure detection, localization, isolation, disassembly, interchange (remove and replace), reassembly, alignment, and checkout. The MTTR requirement shall be demonstrated in accordance with the requirements and provisions of Section 4 of this specification.

3.2.8.2.3 Pressure Line Replacement

The PCPLT pressure lines/hoses replacement shall not require the removal of components.

3.2.8.2.4 Interchangeability

All parts having the same manufacturer's part number shall be functionally and dimensionally interchangeable.

The drawing number and part numbers shall be structured in a manner to identify the item.

3.2.8.2.5 Common/ Standard Tools

The quantity of tools, accessories, and equipment required for operation, maintenance, and inspections of the tester, and any of its assemblies/components, shall be kept to a minimum.

3.2.8.2.6 Special Tools

Special tools shall not be used without prior government approval.

3.2.9 Environmental Conditions

The PCPLT shall be capable of operation in all types of environmental conditions as defined herein without failure or additional maintenance. This includes temperature extremes, humidity, and salt fog.

3.2.9.1 Temperature, Storage

The PCPLT shall be capable of operating after being stored in temperatures in the range of -65 to 180 °F.

3.2.9.2 Temperature, Operation

The PCPLT shall be capable of operating in temperatures in the range of 40 to 120 °F.

3.2.9.3 Humidity

The PCPLT shall be capable of being stored and operated in relative humidity conditions up to 95 percent.

3.2.9.4 Salt Fog

The PCPLT shall be capable of being stored and operated in salt-laden environments containing a salt concentration of 5 percent.

3.2.9.5 Shipboard Vibration

The PCPLT shall meet the requirements as defined in MIL-STD-810 Method 528, Type I while operating.

3.2.9.6 Transportation Vibration

The PCPLT shall withstand vibration as defined in MIL-STD-810, Method 514.6, Procedure I (General

Vibration), Platform: Truck/Trailer, Category: Restrained Cargo.

3.2.9.7 Shock

The PCPLT shall be tested for shock resistance in accordance with MIL-STD-810, Method 516.6, Procedure IV

(Transit Drop), Table 516.6 VI [24 inches, 8 drops, and all vertical on tires].

3.2.9.8 High-Impact Shock Tests

The PCPLT shall be tested for high-impact shock resistance in accordance with MIL-S-901, Shock Grade B.

The Shock Test Category, Equipment Class, and Shock Test Type shall be design-dependent.

3.2.10 Operation Under Tilt

The PCPLT shall be able to operate on a surface that is tilted 8.5° horizontally in any direction.

3.3 Design and Construction

3.3.1 Mobility

The PCPLT shall be able to be moved to another location by being pulled or pushed by one person, not to exceed the force limit for a high traction condition as stated in MIL-STD-1472 Table XL.

3.3.1.1 Mobility System

The PCPLT shall meet mobility requirements specified in SAE AS 8090 for Type I, Class 3, Group A, B, or C manually propelled ground support equipment.

3.3.1.2 Tires/Wheels

The PCPLT wheel or tire ratings shall meet the requirements in SAE AS 8090 for a Type I, Class 3 mobility configuration. Wheel selection and diameter shall be sufficient for the PCPLT to overcome a 1.5 inch obstruction while being pushed (without lifting required). All bearings in wheel assemblies shall be sealed.

3.3.1.3 Deadman Brake

The PCPLT shall have a mechanically or hydraulically actuated deadman brake, which shall provide sufficient braking force to hold the PCPLT at maximum gross weight, on a 15-degree incline (whether the front of the unit is facing up or down the incline) and in the direction of the incline. When a force parallel to inclined surface of

300 N (70 lbs) push or pull is applied in a high traction (µ > 0.9) condition; the deadman brake shall not disengage. There shall be a provision to release the deadman brake when the unit is being moved. The deadman brake actuator (normally on) shall be provided in a location that allows efficient operation when the unit is being moved by hand. The deadman brake shall function in such a manner that it cannot be permanently disabled. The unit shall be configured in such a manner that when the PCPLT rolls over uneven surfaces, the brakes are not actuated.

3.3.1.4 Air Transportability

The PCPLT shall be air transportable, without shoring, bracing, or protective packing in accordance with MIL-

HDBK-1791.

3.3.2 Housing

The PCPLT components shall be completely enclosed in a weather-resistant housing. The housing shall utilize doors and adjustable louvers as required. The housing shall be adequately braced to prevent distortion or excessive vibration during handling and operation of the tester or handling of the housing while being removed from the tester.

3.3.3 Access Panel

Access panels that need to be opened at least once a month will not require tools to open. Panels that do not fall into this category shall be held in place with quarter turn type fasteners.

3.3.4 Lifting/ Tie Down Provisions

Four alloy steel ring assemblies conforming to MIL-STD-209 for Type 1 equipment shall be provided for the dual purpose of lifting and tying down the PCPLT. The rings shall be securely attached near each corner of the unit and shall not extend beyond the maximum dimensions. There shall be no sign of permanent deformation of the rings or the unit when it is lifted. The notation “Lift Here” and “Tie Down” shall be indicated near each ring.

3.3.5 Fork Lifting

Equipment designed for fork lifting shall be provided with heavy-duty reinforced forklift tine guides. The forklift tine guides shall permit safe and positive insertion. The forklift tine guides shall be positioned to assure proper balancing. The forklift tine guide areas shall be constructed to permit the equipment to be lifted without damage.

3.3.6 Storage

The PCPLT shall have a compartment with appropriate trays, bracket, racks, or similar devices to securely hold all loose components, hoses, cables, and accessories within its housing during storage, movement, transportation or when not in use. Stored item name, quantity, and part number shall be listed on PCPLT and include a graphic showing location of properly stored items if specific location of store part is not labeled with item name and part number.

3.3.7 Tubes and Hoses

Tubing and hoses shall have at least a 400% safety factor based on maximum pressure for the circuit it is used

in. Plumbing connections shall be AN, NPT, SAE, or MS type fittings.

3.3.8 Captive Devices

Any cap, plug, pin, or plate requiring removal for operation, inspection, calibration, or service, prior to or during operation, shall be retained by wire rope lanyard or similar device, so that it cannot be separated from the

PCPLT.

3.3.9 Fastening Devices

Fastening devices shall be in accordance with MIL-STD-1472, Section 5.9.10.

All fasteners shall be stainless steel.

Standard threaded fasteners shall include features to prevent the loss of torque, while allowing for ease of disassembly/assembly.

An assembly torque shall be specified in the technical manual and on the drawings for critical threaded fasteners.

Threaded devices that can be easily over torqued by operators shall not be used.

Internal threads in aluminum shall not be used.

All bolted connections shall have a minimum of two and a maximum of four complete threads protruding through the nut.

In no case shall sheet metal screws be used for component installation.

For bolted assemblies that are permanently attached to the end assembly, permanent type sealing compound on the threaded joints shall be used.

Rivets, screws, bolts, pins and other fasteners shall be assembled using a wet sealant or an inhibited primer coating where the fastener is dipped or coated with the sealant/primer just prior to assembly.

For fasteners that are to be disassembled frequently during operations or for routine maintenance, a corrosion preventative antiseize coating shall be used on the fasteners.

3.3.10 Coating

Powder coating is the required corrosion protective coating system. The powder coating shall be in accordance with NAVAIR drawing 1905AS300 (White), amended for a primer coating of 2 to 3 mils (see Appendix A). On specific components where powder coating cannot be employed, the coating shall consist of an epoxy primer and a polyurethane topcoat in accordance with the NAVAIR drawing 1353AS156 (White) (see Appendix B).

3.3.11 Materials

3.3.11.1 Fittings and Tubing

Fittings and tubing shall be made of corrosion-resistant material. All components other than Stainless Steel shall be approved by the Government and be documented on Material Data Sheets. Tubes shall be made from a ridged material and tube assembly end connections shall be designed to provide maximum leakage deterrence.

Ease of fabrication shall also be a priority.

3.3.11.2 Corrosion Protection

The PCPLT shall be constructed of corrosion resistant materials to the maximum extent possible. The use of corrosion resistant steels for all applicable components is encouraged. The PCPLT design shall not permit water accumulation in pockets, creases, fissures, or depressions. Any potential water collection points shall have drain holes. Sensitive components shall be enclosed or protected to resist the effects of water intrusion, salt water and salt fog corrosion. Unless protected against electrolytic corrosion, dissimilar metals shall not be used in direct contact with each other as defined in MIL-STD-889. Where dissimilar metals are in contact, the metal which is the cathode of the galvanic couple shall be coated to provide insulation from the anode material.

Wherever possible, the anodic material shall present a larger surface area than the cathodic material. Hinges used on any door compartment shall be corrosion resistant steel.

3.3.11.3 Hazardous Materials

Hazardous materials shall be avoided at all times in the design, manufacture, testing, operation, maintenance, and disposal of the tester. A hazardous material is any material that due to its chemical, physical, or biological nature causes safety, public health, or environmental concerns. For the purpose of this contract, this includes but is not limited to the following materials:

a. Materials regulated as a hazardous material 49 CFR 173.2, or

b. Materials requiring a Material Safety Data Sheet (MSDS) per 29 CFR 1910.1200, or

c. Materials that during end use, treatment, handling, packaging, storage, transportation, or disposal meet or has the potential to meet the definition of a Hazardous Waste as defined by 40 CFR 261

Subparts A, B, C, or D, or

d. Materials regulated as an Ozone Depleting Substances (ODS) per 40 CFR 82 Subpart A, Appendices

A and B, or

e. Materials identified in the Clean Air Act as a Hazardous Air Pollutant per 40 CFR Part 63, or

f. Materials regulated as an Extremely Hazardous Substance per 40 CFR 355, Appendices A and B, or

g. Materials regulated as a toxic chemical or as a Persistent, Bio accumulative, Toxic (PBT) chemical under Section 313 of the Emergency Planning and Community Right-to-Know Act (EPCRA) per 40

CFR Part 372, or

h. Materials referred to in section 101(14) or Section 102 of the Comprehensive Environmental

Response, Compensation, and Liability Act (CERCLA) per 40 CFR 302.4, or

i. Materials identified as a Volatile Organic Chemical (VOC) per 40 CFR Part 51.100(s).

j. Materials regulated as a toxic or flammable substances under section 112(r) of the Clean Air Act per

40 CFR Part 68.

3.3.11.4 Restricted Chemicals

The following hazardous materials are identified as restricted chemicals: Asbestos, Class I ODS, Class II ODS, Hexavalent Chromium, and Polychlorinated Biphenyls (PCBs). Restricted chemicals shall be prohibited from use in all PCPLT parts/components. No exemptions shall be given for restricted chemicals with the exception of Hexavalent Chromium meeting the conditions below.

3.3.11.4.1 Hexavalent Chromium

Hexavalent Chromium exceeding 0.1 percent by weight in any homogeneous material is banned in the delivered system per DFAR 223-7008 except as provided in 223.7304 and 223.7305. Use of Hexavalent Chromium where an exception from 223.7304 does not apply requires Program Executive Office (PEO) and Corrosion Control and Prevention Executive (CCPE) approval per DON Hexavalent Chromium Authorization Process, 22

November 2011. If exemptions provided in DFAR 223.7304 and 223.7305 apply, approval by NAVAIR is required. Any use of Hexavalent Chromium not cited by DFAR 223-7008 shall also require NAVAIR approval.

Approval will not be given for any use of Hexavalent Chromium unless the contractor can document that there is no viable technically feasible alternative.

3.3.11.5 Targeted Chemicals

The following hazardous materials are identified as targeted chemicals: Arsenic & Arsenic Compounds , Benzene, Beryllium & Beryllium Compounds , Cadmium & Cadmium Compounds , Chloroform, Chromium &

Non-Hexavalent Chromium Compounds, Cyclotrimethylenetrinitramine (RDX), Cyanide Compounds, Ethylene

Glycol, Formaldehyde, Glycol Ethers, Hydrazine, Hydrofluoric Acid, Isocyanates, Lead & Lead Compounds, Mercury & Mercury Compounds, Methyl Ethyl Ketone (MEK), Methyl Isobutyl Ketone (MIBK), Methylene

Chloride, Methylene Dianiline (MDA), Naphthalene, Nickel & Nickel Compounds, Perchlorates, Perchloroethylene, Perfluorooctanoic Acid (PFOA), Phenol, Polybrominated Diphenyl Ethers (PBDEs), Radioactive Materials, Toluene, Trichloroethylene (TCE), and Xylene & Xylene Isomers. Targeted Materials shall require justification and NAVAIR approval for use in all PCPLT parts/components. Approval will not be given unless the Contractor can document that there is no viable technically feasible alternative.

3.3.11.6 Metal Alloys

Chromium and nickel as a constituent of metal alloys are exempt.

3.3.11.7 Lead

Lead as a constituent of lead solder is exempt.

3.3.12 Markings, Identification, and Placards

3.3.12.1 Markings

All items on the control panel shall be permanently marked and have a positive indication of adjustment. All ports on the PCPLT shall be marked to show function of port. The center of gravity shall be marked on the

PCPLT.

3.3.12.2 Reflective Markings

Reflective tape shall be applied along the extreme perimeter of the equipment to reflect its general outline configuration. The tape shall be in accordance with ASTM D 4956, Type II, width 2 inches, Class 1, color yellow.

3.3.12.3 Identification Plate

The identification plate shall conform to NAVAIR drawing 3909AS9999 (see Appendix C). The plate shall be securely attached to the unit in a readily accessible location.

3.3.12.4 Modification Plate

A modification plate shall conform to NAWCAD drawing 5SE00363 (see Appendix D). Plates shall be located so that they are clearly visible. Plate shall be physically stamped and filled with engravers ink with the unit’s serial number.

3.3.12.5 Caution and Warning Labels

Caution and warning labels indicating the location, nature, and extent of a hazard shall be provided on the tester. The labels shall be located as close as possible to the point of danger. Letters of the labels shall be clearly legible. Warning or caution markings shall have a high contrast between the letters and background colors.

3.3.12.5.1 Temperature Warning

The PCPLT shall have a caution plate warning that the supplied air going to the aircraft cabin shall not exceed

120F.

3.3.12.6 Flow Schematic

Placards showing the PCPLTs flow schematic shall be mounted on the tester. The placards shall be located where the maintainer or the operator can access them easily.

3.3.12.7 Flow Meter Chart

Results from flow meter shall be able to be converted to pounds per minute and adjusted for operating temperature. If graphs and charts are needed to convert or adjust flow rate they shall be close to the flow measurement display for quick reference.

3.3.13 Workmanship

3.3.13.1 Quality Management Systems

The tester shall be designed, manufactured, and tested under a quality management system in accordance with

ISO 9001-2000 or ISO 9001-2008.

3.3.13.2 Workmanship (General)

The tester shall be manufactured to a quality standard of workmanship that does not adversely affect safety, function, performance, serviceability, interchangeability, and appearance (includes painted surfaces).

Completed parts and assemblies shall not exhibit defective material, out of tolerance dimensions, or under rated materials. Defects such as: seams, laps, laminations, cracks, fins, extraneous material, visible steps or irregularities, sharp edges, nicks, scratches, burrs, tool scores, and gouges shall be avoided. Deformations, missing operations, improper assembly, missing parts, stains, corrosion, non-specified oxidation (rust), and unauthorized salvaging operations (e.g., hammering to shape, repair by welding, straightening, bending, etc.)

shall also be avoided.

3.3.14 Safety

3.3.14.1 System Design

The PCPLT shall have adequate integrated safety features to prevent injury to users or nearby personnel and damage to aircraft or the PCPLT. The approach shall be consistent with MIL-STD-882 and utilize the following hierarchy of preference for addressing safety risks: eliminate hazards through design selection; reduce risk through design alteration; incorporate engineered features or devices to interrupt the mishap sequence or reduce the risk of a mishap; provide warning devices; incorporate signage, procedures, training, and personal protective equipment.

3.3.14.2 Sound Attenuation

Sound/noise levels created by the PCPLT shall be no more than 80 dba at the operator's location and operating at its maximum capacity. The operator’s location shall be designated as within 10 feet of the instrument control panel of the PCPLT and above ground level.

3.3.14.3 Grounding Provisions

A grounding connection for static discharge shall be provided on the PCPLT. The grounding cable assembly shall be in accordance with MIL-DTL-83413 with either one or two grounding clamps in accordance with MIL-

DTL-83413/7, as applicable. The maximum resistance of the cable configuration shall not exceed 10 ohms.

Storage provisions for the grounding cable assembly shall be provided on the tester.

3.3.15 Human Engineering

3.3.15.1 Human Factors / Human Engineering

Human Factors / Human Engineering (HF/HE) design of the tester shall focus on simplicity and ease of use, efficiency of human effort, optimization of performance effectiveness and readiness, and personnel safety during operation and all other life-cycle phases. All equipment, work stations, consoles, displays, and controls involving human interface shall be designed, located, and arranged to permit efficient, reliable, and safe operation and maintenance by appropriately clothed and equipped 5th percentile female to the 95th percentile male personnel. Human engineering design criteria shall be established and incorporated for all operating and environmental conditions. MIL-STD-1472 may be used as guidance for establishing human engineering design criteria, and shall specifically address environment, anthropometry, maintainability, and controls. The tester design shall also incorporate applicable system and personnel safety factors and features, including minimizing potential human error in the operation and maintenance of the system.

4.0 QUALITY ASSURANCE PROVISIONS

4.1 General Quality Assurance Provisions

4.1.1 Responsibility for Compliance

All items shall meet all requirements of section 3. The test and inspection set forth in this specification shall become part of the contractor’s overall inspection system or quality program. The absence of any inspection requirements in the specification shall not relieve the contractor of the responsibility of assuring that all products or supplies submitted to the Government for acceptance comply with all requirements of the contract.

4.1.2 Contractor Requirements

The contractor shall develop, implement, and maintain a quality assurance inspection system covering the items in this specification. The system will provide the quality assurance required by this document and other applicable documents referenced herein. Except as otherwise approved, the supplier shall utilize his own facilities or a commercial laboratory. Inspection and approval of the facilities by the government technical representative is required. Inspection records of the examinations and tests shall be kept complete and available to the Government as specified by the contract or order.

4.1.3 Classification of Tests

The inspection and testing of the PCPLT shall include Pilot Production and Production Acceptance Tests

(PATs). Pilot Production testing shall be used to verify that the PCPLT design meets all of the requirements of this specification, while Production Acceptance Testing shall be used as part of the quality assurance of production units by verifying that each unit meets a select group of key requirements. Appendix F contains the

Verification Cross Reference Matrix which establishes the test stage at which each requirement specified in this document is to be verified. Each requirement paragraph (Section 3) in this specification is listed in this matrix with an "X" to indicate which stage(s) of testing the requirement will be verified in. Additionally, the matrix provides a reference to the verification paragraph in Section 4 that directs how the requirement is to be verified.

The matrix should be referenced while writing test procedures to ensure that they correctly cover all relevant requirements. Several sections below contain a list which simplifies the matrix to show the requirements that shall be verified by each section.

4.2 Pilot-Production

4.2.1 Repair of Defects

Defects found as a result of inspection or test shall not be corrected by the Contractor until corrective action is discussed first with the government. The contractor shall immediately stop testing, notify NAVAIR of proposed corrective action to repair deficiencies and preclude recurrence.

4.2.2 Final Approval and Acceptance

Final approval and acceptance by the Government of the pilot-production PCPLT shall be withheld until the

Pilot-Production Test II specified in paragraph 4.3.2 has been completed and a final determination has been made regarding conformity of the PCPLT to contractual requirements.

4.2.3 Classification of Inspections and Tests

The verification, inspection and test requirements specified herein are classified as Pilot-Production Test I (PPT

I), Pilot-Production Test II (PPT II) and Production Acceptance Tests.

4.2.4 Pilot-Production Test I (PPT I)

The PPT I procedures are top level performance and interface requirements the PCPLT shall meet. The

Contractor shall compile PPT I procedures based on the PPT I selected requirements in Appendix F of this specification.

4.2.4.1 Reliability Analysis

The contractor shall provide reliability predictions for the PCPLT to examine the probability that the reliability requirements of the Performance Specification will be met with the proposed design. The reliability predictions shall be performed to include all replaceable components included in I-Level maintenance. Manufacturer's data, documented engineering analysis performed in accordance with appropriate guidance, and verifiable field data may be used as sources of failure rate data for component parts. The predictions shall be performed in a NS environment. The reliability predictions shall include a margin of acceptability which shall be twice the required specification value. Therefore, the predicted MTBF of the PCPLT shall be no less than 430 hours in a

NS environment.

3.2.8.1.1 Mean Time Between Failures

4.2.4.2 Maintainability Demonstration

The Government shall witness and participate in a Maintainability Demonstration (MDEMO), performed by the contractor and Fleet personnel, using at least one Pilot Production Unit (PPU), the Pilot Production Test

Procedures, and the 90% Technical Manual, Maintenance Requirements Card (MRC) Deck, and Pre-

Operational Card. The MDEMO shall demonstrate the ability of maintainers to meet MTTR requirements of paragraph 3.2.8.2.2 and assist in the adequacy review of procedures presented in the technical documents. Any problems encountered during this MDEMO will be discussed between the Government and the Contractor and be brought to a resolution satisfactory to the Government.

The MDEMO shall include, but is not limited to, any scheduled maintenance actions that may be identified and a selection of not less than 30 corrective maintenance actions identified by the Government. Maintenance task selection, calculation of the required quantitative maintainability metrics, and pass/fail (accept/reject) criteria shall be in accordance with MIL-HDBK-470, Test Method 9, at 10% Consumer’s Risk.

3.2.5.1 Servicing/Consumable Indicators

3.2.8.2.1 Maintenance Provisions

3.2.8.2.2 Mean Time to Repair

3.2.8.2.3 Pressure Line Replacement

3.2.8.2.4 Interchangeability

3.2.8.2.5 Common/ Standard Tools

3.2.8.2.6 Special Tools

4.2.4.3 Aircraft Functional Simulation Testing

Table 2 – Functional Simulation Test Settings describes the various simulation set-ups which shall be performed. For reference, Figure 1 - PCPLT Hose Connection Set-up shows how the PCPLT and its hoses are to be configured when connecting to an aircraft. The following tests (sections 4.2.4.3.1 thru 4.2.4.3.4) shall be completed for each set-up prior to moving onto the next set-up. The facility conditions for all set-ups shall be in accordance with section 3.2.2. After each set-up, depressurize in accordance with section 4.2.4.3.5

Shutdown/Depressurization.

Table 2 - Functional Simulation Test Settings

Set-up

(a)

Aircraft

Max.

Canopy/

Door Seal

Pressure

(b)

Cabin

Air

(c)

Canopy/Door

Seal Pressure

(d)

Canopy/

Door Seal

Allowable

Flow Rate

(e)

Cabin Air

(f)

Safety Relief

(g)

Allowable

Leakage

(h)

Max. Cabin

Air Rate of

Pressure

Change

(PSIG) (PSIG) (PSIG) (SCFM) (PSIG) (PSIG) (SCFM) (ft/min)

1 24 7 20 ± 1 0 5 ± 0.23 5.5 ± 0.23 23.85 ± 5000

2 35 8 27.5 ± 2.5 0 5 ± 0.15 5.5 ± 0.15 77 ± 5000

3 22 14 18 ± 0.5 0 8.8 ± 0.2 9.45 ± 0.3 235 *

4 15 7 12.5 ± 1.5 0.1 4 ± 0.1 5.5 ± 0.3 100 N/A

5 32 5.5 25.5 ± 2.5 1.0 5 ± 0.2 5.35 ± 0.1 38 N/A

* ± 250 ft/min at flow rates 50 to 200 SCFM & ± 500 ft/min at flow rates 10 to 50 SCFM

Figure 1 – PCPLT Hose Connection Set-up

Facility Air

PCPLT

Atmosphere

Aircraft Canopy Seal Aircraft Cabin

Canopy/Door Seal

Supply/Check Hose

Compressed Air Supply Hose

Cabin Air Pressure Check Hose

Aircraft Test Ports

Compressed Air Supply Hose

4.2.4.3.1 Maximum Pressure Controls Verification

The purpose of this verification is to ensure that the PCPLT Canopy/Door seal and cabin air maximum pressure relief controls can be set and checked prior to attaching to an aircraft. This provides the PCPLT operator a level of safety that the aircraft cannot be over pressurized.