FA853309R21835______0004.pdf

AMENDMENT OF SOLICITATION/MODIFICATION OF CONTRACT 1. CONTRACT ID CODE

J

2. AMENDMENT/MODIFICATION NO.

FA8533-09-R-21835-0004

3. EFFECTIVE DATE

27 Aug 2010

4. REQUISITION/PURCHASE REQ. NO.

FD2060-09-21835

5. PROJECT NO (If applicable)

6. ISSUED BY CODE

WR ALC GRVKBB, MAJOR PROGRAMS

460 RICHARD RAY BLVD STE 200

BLDG 301 CP 478 222 1902

ROBINS AFB GA 31098-1813

BUYER: Erica R. Martin/GRVKBB Erica.Martin@robins.af.mil Phone: (478) 222- 1893 Fax: (478) 222-1854 No Collect Calls

7. ADMINISTERED BY (If other than item 6) CODEFA8533

8. NAME AND ADDRESS OF CONTRACTOR (No., street, county, State and ZIP Code)

CODE

X

9A. AMENDMENT OF SOLICITATION NO.

FA853309R21835

9B. DATED (SEE ITEM 11)

17-FEB-2010

10A. MODIFICATION OF CONTRACT/ORDER NO.

10B. DATED (SEE ITEM 13)

11. THIS ITEM ONLY APPLIES TO AMENDMENTS OF SOLICITATIONS

The above numbered solicitation is amended as set forth in item 14. The hour and date specified for receipt of Offers is extended, is not extended. Offers must acknowledge receipt of this amendment prior to the hour and date specified in the solicitation or as amended, by one of the following methods. ( a ) By completing Items 8 and 15, and returning copies of the amendment; ( b ) By acknowledging receipt of this amendment on each copy of the offer submitted; or ( c ) By separate letter or telegram which includes a reference to the solicitation and amendment numbers. FAILURE OF YOUR ACKNOWLEDGMENT TO BE RECEIVED AT THE PLACE DESIGNATED FOR THE RECEIPT OF OFFERS PRIOR TO THE HOUR AND DATE SPECIFIED MAY RESULT IN REJECTION OF YOUR OFFER. If by virtue of this amendment you desire to change an offer already submitted, such change may be made by telegram or letter, provided each telegram or letter makes reference to the solicitation and this amendment, and is received prior to the opening hour and date specified.

12. ACCOUNTING AND APPROPRIATION DATA (If required)

13. THIS APPLIES ONLY TO MODIFICATIONS OF CONTRACTS/ORDERS

IT MODIFIES THE CONTRACT/ORDER NO. AS DESCRIBED IN ITEM 14.

A. THIS CHANGE ORDER IS ISSUED PURSUANT TO: (Specify authority) THE CHANGES SET FORTH IN ITEM 14 ARE MADE IN THE CONTRACT ORDER NO. IN ITEM 10A.

B. THE ABOVE NUMBERED CONTRACT/ORDER IS MODIFIED TO REFLECT THE ADMINISTRATIVE CHANGES (such as changes in paying office, appropriation date, etc.) SET FORTH IN ITEM 14, PURSUANT TO AUTHORITY OF FAR 43.103(b).

C. THIS SUPPLEMENTAL AGREEMENT IS ENTERED INTO PURSUANT TO AUTHORITY OF:

D. OTHER (Specify type of modification and authority)

E. IMPORTANT: Contractor is not, is required to sign this document and return 1 copies to the issuing office.

14. DESCRIPTION OF AMENDMENT/MODIFICATION (Organized by UCF section headings, including solicitation/contract subject matter where feasible.)

FMS REQUIREMENT

ROUTINE

15A. NAME AND TITLE OF SIGNER (Type or print)

15B. CONTRACTOR/OFFEROR

BY ________________________________________________________

(Signature of person authorized to sign)

15C. DATE SIGNED

16A. NAME AND TITLE OF CONTRACTING OFFICER (Type or print)

16B. UNITED STATES OF AMERICA

BY ____________________________________________________

(Signature of Contracting Officer)

16C. DATE SIGNED

FACILITY CODE

NSN 7540-01-152-8070

PREVIOUS EDITION UNUSABLE

30-105 STANDARD FORM 30 (REV. 10-83)

PRESCRIBED BY GSA

FAR (48 CFR) 53.243

X

X X

Except as provided herein, all terms and conditions of the document referenced in Item 9A or 10A, as heretofore changed, remains unchanged and in full force and effect.

Amendment/Modification FA8533-09-R-21835-0004

Continuation of block 14. DESCRIPTION OF AMENDMENT/MODIFICATION

1. The purpose of this administrative amendment is to supersede PD08WRGBGBEA10 Revision C dated 17 May 2010 with PD08WRGBGBEA10 Revision D dated 24 August 2010, attached hereto.

2. Except as provided herein, all other terms and conditions of the RFP remain unchanged and in effect.

Request for Proposal FA8533-09-R-21835-0004

Request for Proposal FA8533-09-R-21835-0004

LIST OF DOCUMENTS, EXHIBITS OR ATTACHMENTS

Form Number Description/File Name Date Number of Pages Purchase Description PD08WRGBGBEA10 Revision D

24AUG2010 22

PD08WRGBGBEA10

REV D

CAGE 98752

24 August 2010

Comments, suggestions, or qu estions on this docum ent should be addressed to:

WR-ALC/GRVEC, Robins AFB GA 31098-1813.

AMSC N/A FSC 4920

DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited.

PURCHASE DESCRIPTION

TEST SET, FLIGHT CONTROL SYSTEMS

1. SCOPE

This purchase description establishes the minimum design performances and test requirements for a portable pitot and static tester (test set) to be used for the inspection and acceptance of pitot and static systems including altimeters, vertical velocity indicators, air speed indicators, and air data computer systems.

2. APPLICABLE DOCUMENTS

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

2.2 Government documents.

2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooks of the exact revision listed below form a part of this document to the extent specified herein.

FEDERAL STANDARDS

FED-STD-595C/26173 Ocean Gray, NAVSEA

DEPARTMENT OF DEFENSE SPECIFICATIONS

MIL-PRF-28800F Test Equipment for Use with Electrical and Electronic

Equipment, General Specifications for

DEPARTMENT OF DEFENSE STANDARDS

MIL-STD 882D Standard Practice for System Safety MIL-STD-130N Identification Marking of US Military Property MIL-STD-461F Requirements for the Control of Electromagnetic Interference

Characteristics of Subsystems and Equipment MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests MIL-STD-859A Standard Calibration Table for Aeronautical Pressure Measuring

Equipment MIL-STD-1472F Human Engineering

DEPARTMENT OF DEFENSE HANDBOOKS

MIL-HDBK-454B General Guidelines for Electronic Equipment MIL-HDBK-781A Reliability Test Methods, Plans, and Environments for

Engineering, Development Qualification, and Production MIL-HDBK-470A Designing and Developing Maintainable Products and Systems MIL-HDBK-217 Reliability Prediction of Electronic Equipment

2.2.2 Other Government documents.

NASA TN D-822 Tables of Airspeed, Altitude, and Mach Number Based on Latest

International Values for Atmospheric Properties and Physical Constants

2.3 Non-Government publications. The following documents of the exact revision listed below form a part of this document to the extent specified herein.

SK-ED-0017 Flush Static Port Adaptor (Cage Code 81996) US Standard Atmosphere, 1976 Defines US Standard Atmosphere

Institute of Electrical and Electronics Engineers

STD-488.1-1987 Standard for Higher Performance Protocol for the

Standard Digital Interface for Programmable Instrumentation

(Application for copies should be addressed to IEEE Publications Office, 10662 Los Vaqueros Circle, P.O. Box 3014, Los Alamitos, CA 90720-1264.)

Society of Automotive Engineers

ARP 1199 Selection, Application, and Inspection of Electric

Overcurrent Protective Devices

(Application for copies should be addresse d to SAE, Inc., 400 Comm onwealth Drive, Warrendale PA 15096.)

2.4 Order of precedence. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein (except for related specification sheets), the text takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3. REQUIREMENTS

3.1 First article. When specified (see 6.2), one sample shall be subjected to first article inspection in accordance with 4.2

3.2 Safety. The equipment shall comply with the Class II safety requirements specified in MIL-STD 882D. The design of the equipment shall not contain any system safety mishap risk categories greater than low as defined in Table A-IV of MIL-STD-882.

3.2.1 RVSM compliant. Reduced Vertical Sep aration Minimum (RVSM) reduces the vertical separation between Flight Level (FL) 290–410 from 2000 ft to 1000 ft and m akes six additional FL’s available for operation. The equipm ent shall be fully com pliant to this standard.

3.2.2 Personnel hazards . The safety criteria of MIL-STD 882D shall be m ade applicable for tasks and efforts such as the part selecti on, m anufacturing and assem bly process and any product baseline configuration. Compliance with this requirem ent shall be determ ined by visual inspection and operation.

3.2.3 Exposed-edge rounding . Exposed edges and corners sha ll be rounded sufficiently to minimize laceration and puncture hazards. The desi gn requirement is a radius of 0.0394 inches for edges and a minimum radius of 0.5 inches for corners.

3.2.4 Radioactive materials. Radioactive materials shall not be used.

3.3 Design and construction . Unless otherwise specified herei n, the equipment shall consist of all new and unused com ponents and shall co mply with Class II equipm ent design and construction requirem ents of MIL-P RF-28800 a nd shall be a m odified comm ercial-off-the-shelf (COTS) tester. The exterior f inish color of the tester shall be Ocean Gray, NAVSE A, and Color Number 26173 of FED-STD-595.

3.3.1 W eight. The eq uipment and accessories (includ ing the rem ote un it and exclud ing manuals) shall no t exceed 100 pounds. The weight of the rem ote unit shall not exceed 1 0 pounds.

3.3.2 Dimensions. The equipm ent shall not exceed 4.5 c ubic feet in volum e, when housed in the combination case with the cover closed. No external dim ension of the case shall exceed 30 inches. The rem ote unit dim ensions shall be compatible with cockpit us e, and th e maximum length and width dimensions of the remote unit shall be no greater than 10 inches by 16 inches.

3.3.3 Handles and grasp areas . The equipment shall have handles and grasp areas that comply with 5.9.11.5 of MIL-STD-1472.

3.3.4 Maneuverability . The equipment shall have wheels to allow one person transport, and shall be maneuverable over various terrain.

3.3.5 Human factors. Equipment shall be in accordance with 4.4P of MIL-STD-1472.

3.3.6 Displays, indicators, and controls. The test set and remote unit shall provide displays, controls, and status indicators to the user. Adjustable illumination shall be provided for visual displays (including display and control labels) that shall be read under darkened conditions and direct sunlight. The test set and remote unit shall have as a minimum, but not limited to, the following indicators, displays, and controls:

Elapsed time indicator Power on indication and switch Self test fault indication, selector Simulated altitude display, selector, indicator Test set ready indication Leakage test mode indication, selector Altitude slew rate display, selector, indicator Ambient barometric pressure indication, vent switch Indicated/true airspeed display

3.3.6.1 Elapsed time indicator. The elapsed tim e indicator shall indicate the total accumulated time in hours that the pump has been operating.

3.3.6.2 Test set ready indication . The test set sh all indicate when the test set is read y to accept an input from the user.

3.3.6.3 Independent display and control. The test set shall include two independent display and control units: the main unit and the hand held re mote unit. Operators s hall have the capability to select the main unit or remote unit as the p rimary controlling unit. Failure of the hand held remote unit shall not p rohibit the operator from operating the test s et main unit controls an d display.

3.3.6.4 Keyboard. A general num eric keyboard/keypad sha ll be provided as the prim ary input device for the operators to enter test points, rate s of change, etc., and needs to be usable for operators wearing MOPP IV gear or Arctic mittens.

3.3.6.5 Human error design protection. Front panel control functions shall be designed such that neither incorrect adjustment nor random sequencing of functions causes damage to the test set or the unit under test.

3.3.6.6 Display characteristics All displays shall be digital a nd direct sunlight readable. The displays shall have a minimum contrast ratio of 6 over a field of view of ± 45 degree cone with a target contrast ratio of 45 over a ± 60 degree cone. Displays shall be as listed in TABLE I.

TABLE I. Display characteristics

Number of digits Character height (minimum) (m inimum) Altitude 5 0.187 inches Airspeed 5 0.187 inches Altitude Rate 5 0.187 inches

3.3.7 Accessibility. The equipment shall be constructed as follows:

3.3.7.1 Subassemblies and chassis components. Subassemblies and chassis components can be removed without removing any other hard wired printed circuit card, subassembly, or component.

3.3.7.2 Adjustments. Adjustments can be made without removing any component, printed circuit card, or subassembly. The use of extender cards or cables is permitted.

3.3.7.3 Printed circuit cards. Printed circuit cards shall be removable without the need to unsolder cables and interconnecting wiring. Printed circuit cards (mother boards) designed primarily to distribute power and signals to other printed cards (daughter boards) are excluded from this requirement. When such mother boards are used, they shall be readily accessible.

3.3.8 Encapsulation and embedment. Encapsulation and Embedment (potting) of subassemblies, if used, shall be readily accessible.

3.3.9 Attitude. The test set shall operate in a horizontal or vertical position and shall be self supported in either position.

3.3.10 Remote unit . The rem ote unit shall be com pact, li ghtweight, and portable. It shall be housed in a case to protect it from the environmental and E MI conditions. The environm ental requirements for the remote control units are the same requirements that apply to the test set.

The connection between the rem ote unit and th e m ain unit shall be a single 20 foot long electrical cable assembly. A 50 f oot long electrical cable assem bly shall be available between the r emote unit and the m ain unit f or use as a n option for use with larger aircraf t. As a minimum, t he remote must be capable of disp laying two separate and selectable indications which shall be fully and instantaneously select able for all av ailable display outputs, per requirement. The rem ote shall hav e the capab ility to sto p all f unctions of the test se t.

Adjustable illum ination shall be p rovided on th e rem ote unit for visual displays (including display and control labels) that must be read under darkened conditions.

3.3.11 IEEE-488, RS-232, USB and ethernet bus. The IEEE-488 control bus shall operate with the remote unit connected or disconnected. An Ethernet Bus, RS-232, and Universal Serial Bus (USB) shall also be included on the test set. F or m ore on how these connections are used see3.11.7.

3.3.12 Pressure—vacuum pump. The pressure-vacuum pump shal l be a motor driven dry type pump.

3.3.13 Internal pneum atic tubing. The internal tubing system of the test set shall b e designed for ease of maintenance.

3.3.14 Protection to the unit under test. The test set shall provide protection to the unit under test and to the test set. The test set shall prevent pressure surges, pressure transients, over-pressure, and under-pressure in both, the test set and the unit under test (UUT). This protection shall have visual and/or audio warning systems. The test set shall provide pressure balance protection to the altimeter and airspeed indicator.

3.3.15 Negative differential pressure. The test set shall limit the negative differential pressure from exceeding 0.5 inches Hg.

3.3.16 Static pressure limiting. The test set shall not permit the static pressure to exceed 32.2 +/- 0.2 inches Hg.

3.3.17 Total pressure limiting. The test set shall not permit the total pressure to exceed 106.0 +/- 0.2 inches Hg.

3.3.18 Pneumatic filtering. The test set shall provide pneumatic filtering to preclude the transmission of foreign matter to the unit under test and to provide protection to the test set.

3.3.19 Water extraction. The test set shall extract any water accumulation in the internal pneumatic system of the test set. Water shall be extracted when the test set is operated on either a horizontal or a vertical attitude and removal of the unit from its enclosure shall not be required. Water extraction shall be an automatic function of the test set.

3.3.20 Pneumatic output venting. The ambient barometric pressure indication shall indicate when the pneumatic outputs of the test set are at the ambient barometric pressure. When the ambient vent switch is activated the test set shall automatically vent the pneumatic outputs to the ambient barometric pressure at a controlled rate. The ambient vent condition may be used during the “reset function” to speed up venting.

3.3.21 Pressure limiters and relief valves. Pressure and Relief Valves shall be supplied, located, and have limits such that the pressure transducers are adequately protected from potentially damaging overpressures and negative pressures.

3.3.22 Warm-up. Warm-up shall be in accordance with 3.8.1.1 of MIL-PRF-28800, except that the warm-up and auto exercise time shall function as follows:

a. Operation temperature -40 deg C to +10 deg C warm up time should not exceed 60 minutes.

b. Operation temperature +0 deg C to +10 deg C warm up time should not exceed 30minutes.

c. Operation temperature +10 deg C to +55 deg C warm up time should not exceed 15 minutes.

3.4 Parts, materials and processes. Unless otherwise specified herein, the equipment shall comply with parts, materials, and processes’ requirements of MIL-PRF-28800.

3.4.1 Restricted material. The equipment shall comply with the restricted material requirements of MIL-PRF-28800, and shall contain no combination of materials that cause deterioration of any material contained in the equipment.

3.4.2 Interchangeable. Unless otherwise specified herein, the equipment shall comply with the interchangeable requirements of MIL-PRF-28800.

3.5 Marking and identification. Unless otherwise specified herein, the equipment shall comply with the marking and identification requirements of MIL-PRF-28800.

3.5.1 CAGE Code. All replaceable assemblies, subassemblies, modules and printed circuit card assemblies shall be individually marked with the Contractor and Government Entity (CAGE) Code and the contractor’s part number.

3.5.2 Supplemental identification plate. The supplemental identification plate specified in MIL-PRF-28800 shall contain the following information:

a. Nomenclature and Type Designator

b. Contract Number

c. Serial Number

d. National Stock Number “U.S.”

e. Date of Manufacture

g. Unique Identification Number as defined by MIL-STD-130

3.5.3 Battery warning label. If a battery is used in the equipment, the equipment shall provide a battery warning label according to MIL-PRF-28800.

3.5.4 Warranty plate. An information plate containing the warranty termination date shall be affixed to each instrument.

3.6 Transportability. The equipment must be capable of be ing transported within its own case and transpo rtable in either a general purpos e commercially availab le Test Measurem ent Diagnostic Equipment (TMDE) transit case or in mobile maintenance shelters (tied down). The tester shall be capable o f withstanding mechanical shock and vibr ation characteristics with all forms of transportation.

3.7 Equipment power. The test set shall operate from any of the following power sources:

AC POWER: 110—240 volts 50 to 400 Hertz single-phase

3.7.1 Power cables. Power cables, extensions, and adapters shall conveniently connect the tester to the power source. The removable 115 V power cable shall be furnished with a non-removable, three prong, grounding connector molded to the cable jacket at the power source end. The cable assembly shall be at least 25 feet in length and meet the requirements of MIL-

PRF-28800.

3.7.2 Input power switch. The input power switch shall be as specified in MIL-PRF-28800.

The power switch shall function as an emergency power turn-off. Turning the switch to the off position at any moment during operation of the test set shall not damage the test set or the unit under test. After turn-off the test shall automatically vent all pneumatic outputs to the ambient barometric pressure at a controlled rate. A power-on indicator shall indicate whenever power is applied to the test set. An input power switch shall be located on the front panel of the set, or the remote control unit, or both.

3.7.3 Fuses and circuit breakers. Adequate instrument protection is required. Fuses, fuseholders, circuit breakers, and associated hardware shall be in accordance with MIL- HDBK-454, Requirement 39. Fuses, fuseholders, and associated hardware should be selected from SAE-ARP 1199. The load should be connected to the fuseholder terminal that terminates in the removable cap assembly. MIL-HDBK-217 provides reliability prediction models for fuses. Fusing should be so applied that fuses in branch circuits will open before the fuses in the main circuit. Common or separate fuse holders shall be provided. Fuses and circuit breakers required for equipment operation shall be according to MIL-HDBK-454. These fuses shall be standard available commercial fuses and shall be easily accessible to the operator without the use of tools or disassembly. Refer to section 4.2.2 in MIL-HDBK-454 for spare fuses.

3.7.4 External ground. The test set shall have an external ground connection.

3.7.5 Batteries. If batteries are provided for memory backup they will be batteries that are in the Government inventory. Batteries requiring replacement more frequently than annually shall be replaceable by the operator and accessible without subjecting the operator to any electrical hazard.

3.8 Accessories. All accessories necessary for proper operation and maintenance of the test set shall be provided with each instrument.

3.8.1 Hoses and connections. Hoses, clamps, couplings, sleeves, and reducers, as applicable shall connect the tester to points in the aircraft plumbing, to the pitot pressure port and to the static pressure port. The fittings shall meet the requirements of SAE AS4841, 37 degree flare, Unified Standard Class 3B thread. The material shall be corrosion resistant. The static port hose fitting shall be size no. 6 (AN Size 6), and the pitot port hose fitting shall be size no. 4 (AN Size 4). The fittings shall also be used to attach the hoses to the individual adapters used on the different airframes.

a. Pitot Static Adapter Connection Points

b. Pitot Port: SAE AS4841, 37 degree flare, Unified Standard Class 3A thread, AN Size 4

c. Static Port: SAE AS4841, 37 degree flare, Unified Standard Class 3A thread, AN Size

The Static Hose shall be color coded red and the Pitot Hose shall be color coded blue. Each hose shall be a minimum 40 +/- 2 feet in length. Local manufacture for replacement hoses shall be specified in vendor data package. Adapters shall also be provided to connect the tester directly to the instrument cases. For bench testing uninstalled instruments, valves shall be provided with the accessory hose connections to isolate the instruments being tested for leakage."

3.8.2 Commercial accessories. In addition to specified items, other standard accessories furnished with or typical of the commercial instrument shall be included with each unit upon delivery.

3.9 Environmental requirements. Except for the temperature requirements, the equipment shall comply with the Type II, class 2, Sty le C, environmental requirements specified in MIL-PRF- 28800. Temperature requirements shall meet Class 1 temperature requirements listed in MIL-

PRF-28800.

3.9.1 Temperature. The equipment shall perf orm all of its electr ical requirements as specif ied herein in the operating tem perature range of - 40 degrees Celsius to +55 degrees Celsius. The storage temperature range shall be -51 degrees Celsius to +71 degrees Celsius.

3.9.2 Electromagnetic interference (EMI).

The test set shall be in accordance with the following rad iated em ission and susceptib ility requirements of MIL-STD-461: RE102 and RS103.

3.9.3 Operating and non-operating altitude . T he test set shall m eet the performance an d accuracy requirements specified h erein when o perated in altitudes from -1000 to 15,000 feet.

Changes in the am bient -barom etric pressu re shall no t affect the pe rformance and accuracy requirements of the test set. The non-operating altitude shall range -1000 to 50,000 feet.

3.9.4 Precipitation.

3.9.4.1 Rain. The tester shall be capable of storage and operation during rainfall of five inches per hour for three consecutive hours and ten inch es per hour for 10 cons ecutive minutes, with winds of up to 35 knots; and with six inches of rain per hour impinging on the tester at angles from vertical to 45°.

3.9.4.2 Snow and ice . The tester shall be capable of storage and operation during snow accretion up to two inches per hour for at least 12 hours and up to 1.5-inches of ice.

3.9.4.3 Salt fog. The tester shall be capable of stor age and operation in high temperature, high humidity, salt laden, and sea coast environm ents without dam age or deterioration of performance.

3.9.5 Solar radiation. The tester shall not be adversely affected by full time exposure to solar radiation, such as those conditions encountered in desert environments.

3.9.6 Fungus . All m aterials used in the tes ter shall be fungus resistant or shall be suitably treated to resist fungus. Materials treated fo r fungus resistance shall retain their original electronic and physical properties, shall not present toxic hazards , and treatm ent shall last for the entire s ervice lif e of the part. The teste r shall be suitable for operation and storage in conditions encountered in a tropical environment.

3.9.7 Sand and dust . Th e tester shall be capab le of storage and operation during exposure to wind-blown sand or dust without damage or deterioration of performance.

3.10 Reliability, availability, and maintainability (RAM).

3.10.1 Reliability . The e quipment shall com ply with the Type II Reliability Requirem ents of

MIL-PRF-28800.

3.10.2 Calibration . Th e calibratio n interval s hall m eet or exceed 365 days with 85% of instruments (which have not failed) still within tolerance.

3.10.2.1 Special software . Any special software required for calibration or alignm ent must be provided with each unit on a CD or DVD, and must be Microsoft Windows compatible.

3.10.2.2 Special cables . Special cab les required for calibration or a lignment shall be kept to a minimum and must be provided with each unit.

3.10.2.3 Disassem bly or m odification. Both calibration and ali gnment sha ll n ot requ ire disassembly or m odification to the u nit and can be accomplished at the front panel, using the remote, or via an IEEE bus, at the calibrator’s discretion.

3.10.2.4 Check points. All calibration check points shall be easily accessible.

3.10.2.5 Calibrated parameters. All calibrated parameters shall have the capability to be set to their nominal value.

3.10.2.6 Calibration adjustm ents. Calib ration adjustm ents will be such that they cannot be inadvertently changed during routine use.

3.10.2.7 Calibration standards . New calibration standards shall no t be required for calibration of the test set. Calibration standards shall be selected from equipment in the governm ent inventory for this purpose.

3.10.2.8 Calibration time. Calibration time shall not exceed 3 hours and shall include all tim e required to check the equipment parameters on all range and function settings and all input and outputs. Calibration tim e does not include the time to repair and re adjust th e equipm ent because of malfunction.

3.10.2.9 Calibration record . A complete r ecord of calibration shall be stored on-board in non volatile memory. This shall include date of calibration and any offsets applied. The tester shall be shipped with NIST traceab le calibration certificates to p revent it fro m being calibrated as soon as it gets to the base that ordered it.

3.10.3 Maintenance provisions. The equipment shall meet the maintenance provisions of MIL- PRF-28800 except the accessib ility of accessories does not apply. Peculiar suppo rt equipment shall not be required for m aintenance of the test set. Support equipment selection shall be based on equipm ent already existing in the G overnment inventory, such as general purpose electronic test equipment.

3.10.4 Scheduled maintenance. The time between the scheduled maintenances of the test set shall be no less than 1500 hours. .

3.11 Performance.

3.11.1 Altitude and airspeed sim ulation. As a minimum, the test set shall simulate and display any selected altitude (feet or m eters) and airspeed (knots or kilometers per hour) condition not exceeding 4.9 Mach continuously, based on selection, with in the lim its specified herein. The pressure reg ulation system of the test set sh all not be affected by changes in the am bient barometric pressure. The altitude pressure output shall be based on a fixed barom etric pressure reference of 29.9213 inches Hg, and shall be calibrat ed to the standard a tmosphere as listed in MIL-STD-859 and in the U.S. Standard Atm osphere, 1976. The airspeed pressure output shall be calibrated to NASA TN D-822. The altitude and airspeed displays shall provide for both commanded and m easured values. All other co mmanded and displayed values shall be displayed whenever selected by th e operato r. The altitude display shall show commanded values and an indicator/display shall be provided to le t the operator know when the m easured rate is equal to the commanded rate within specified tolerances.

3.11.2 Ranges, reso lution and accu racies. Th e test set shall sim ulate p ressure/vacuums in accordance with the ran ges, resolution, units, and accuracies listed in TABLE II and TABLE III. The test set shall have the capability to display in Psi pressure units.

TABLE II. Ranges

Altitude -1,900 to 80,000 ft Altitude, related pressure 32.03 to 0.8155 inches Hg Altitude slew rate 0 to 50,000 ft/min Airspeed, indicated 20 to 1,000 knots Airspeed, ind., related pressure 0.0192 to 73.55 inches Hg Airspeed slew rate 0 to 800 knots/min Mach limit setting 0 to 4.9 Mach Static load range 5 to 250 cubic inches

(volume reduce at slew rates)

Pitot load range 5 to 250 cubic inches

TABLE III. Accuracies

Altitude 10 ft or ± 0.1% of setting (whichever is greater) across the entire operating temperature range

Altitude slew rate ± 10 ft/min or 3% of setting (whichever is greater)

Airspeed ± 3 knots from 20‐50 knots ±1.5 knots from50‐80 knots ±1 knots from 80‐150 knots ±0.5 knots from 150‐400 knots ±0.2 knots from 400‐1000 knots

Airspeed slew rate ± 2 knots/min or 3% setting (whichever is greater)

Mach limit setting 0.05 Mach

3.11.3 Simulated, true airspeed control . The test set shall sim ulate indicated airspeed and true airspeed. A control shall be provided to select the desired kind. By simulating True Airspeed it will not need to be calculated using Indicated Airspeed.

3.11.4 Pressure modulation. The test set shall provide a control mode for cycling altitude or airspeed pressure above and below the command set point value. The pressure shall cycle within user specified limits under a controlled rate condition. This mode shall have adjustable settings for range and rate as follows:

The test set shall cycle altitude pressure at a user specified range not to exceed +/-5000 feet above and below the set point command value at a rate no greater than 6000 feet per minute.

The test set shall cycle airspeed pressure at a user specified range not to exceed ± 100 knots above or below the set point command at an airspeed rate not exceeding 100 knots per minute.

3.11.5 Leakage test mode. On this mode the test set shall measure the leakage on the static and dynamic pneumatic outputs and display the corresponding leakage on the simulated altitude and airspeed displays. The test set shall be capable of performing individual and simultaneous pneumatic channel leak tests. The test set shall perform this test regardless of the starting conditions of simulated altitude and airspeed with an accuracy of 50 feet per minute on the altitude channel and one knot per minute on the airspeed channel. The leakage test mode indicator shall indicate that the test set is in this mode of operation until the mode is deactivated by the user.

3.11.6 Self test. The test set shall execute the self test routine when power to the test set (turn-

on) is applied or by front panel controls. The self test routine shall also be executable through the IEEE-488 control bus (IEEE-488 referenced in Section 3.3.14). Adequate status information or flags shall be available through the bus in case a malfunction condition exists.

If a lamp test is initiated, all lamps and other indicating devices shall illuminate. The lamp test shall include the testing of the numeric displays. A malfunction in the self test circuits shall not impair the operation of the test set. If a malfunction is detected by the self test, the test set shall vent the pneumatic outputs to the atmospheric pressure at a controlled rate. The self test sequence shall not require intervention of the user for its completion. The self test routine shall, as a minimum, test the following functions:

a. The static and dynamic pressure sensors.

b. The pressure generating system.

c. The pressure controlling system.

d. Lamp test (if applicable).

e. Num eric displays.

3.11.7 IEEE-488 Bus and RS-232 interface . T he tes t se t s hall be capable of interfacing an IEEE-488 control bus in accordance with IEEE-STD-488.1-1987 and as specified in MIL- PRF-28800 and with a RS-232 Interface. The test set shall be controlled through the IEEE-488 control bus by using an external bus controller. All functions, indicatio ns and readings on the test set shall be available through th e control bu s. It is acceptable to op erate the remote unit from the IEEE-488 bus.

3.11.8 External volum e range. The test set shall operate and pe rform as specif ied herein with any combination of external volumes connected to the pneumatic outputs. The external volume range is:

a. Connected to the static output, from 5 to 250 cubic inches.

b. Connected to the dynamic output, from 5 to 250 cubic inches.

3.11.9 Stability. The test set shall maintain stable pressure control and regulation of sim ulated altitude and airspeed, while operating into any com bination of external volumes as specified herein.

3.11.9.1 Altitude stability . The m aximum allowable a ltitude var iation of sim ulated altitud e shall be ± 3 feet or ± 0.02% of simulated altitude, whichever is greater.

3.11.9.2 Airspeed stability. The maximum allowable variation of simulated airspeed shall be ± 1 knot throughout the entire simulated airspeed range.

3.11.9.3 Oscillations within stability lim its. The test se t shall not pr oduce rapid oscillations, surges, or transien ts within th e sta bility lim its specified herein. Any oscillations shall be exhibited as a slow drif t. The duration of a drift from a maximum to a minimum stability limit shall not exceed one minute.

3.11.9.4 Stability of pressure interaction . The test set shall have minimum interaction between the simulated altitude output and the simulated airspeed output as follows:

a. At indicator readings of 5,000 feet altitude and 50 knots airspeed, an increase in airspeed to 300 knots shall not produce an altitude change in excess of ± 50 feet.

b. At indicator readings of 2000 feet altitude and 50 knots airspeed, an increase in altitude to 35,000 feet shall not produce an air speed change in excess of ± 2 knots.

3.11.10 Overshoot. Overshoot regulation shall be accomplished by automatically reducing the commanded slew rate (altitude or airspeed) when the simulated pressure at the output approaches the pressure equivalent to the commanded altitude or airspeed.

3.11.11 Test set leakage. The test set’s leakage shall not exceed 50 feet per minute and one knot per minute on the static and dynamic outputs under the conditions of 35,000 feet and 400 knots simulated altitude and airspeed.

3.12 Workmanship. 3. The unit, including all parts and accessories, shall be constructed and finished in a thoroughly workmanlike manner. Workmanship objectives shall include freedom from blemishes, defects, burrs and s harp corners and edges ; accuracy of dim ensions, surface finish, and radii of fillets; th oroughness of welding, painting, a nd riveting; m arking of parts and assemblies; and proper alignment of parts and tightness of assembly fasteners.

3.12.1 Bolted connections . Bolt h oles shall b e accu rately punched or drilled and shall be deburred. Threaded fasteners shall be tight and shall not work loose du ring testing or service usage.

3.12.2 Cleaning . The unit shall be thoroughly cleaned. Loose, spattered, or excess solder;

welding slag; stray bolts, nuts, and washers; rust; m etal part icles; pipe co mpound; and other foreign matter shall be removed during and after final assembly.

4. VERIFICATION Unless otherwise specified in the contract, the contractor is responsible for the performance of all inspection requirements as specified herein. Unless otherwise specified in the contract, any facility suitable for the performance of all inspection requirements specified herein may be used by the contractor unless disapproved by the Government. The Government reserves the right to perform or witness any of the inspections as stated in the specification. Random samples shall be selected by a Government representative. The contractor shall notify the Government before inspection of the production lot size. Bid sample testing will be performed by the Government.

4.1 Classification of inspections

a. First article inspection (see 4.2)

b. Conformance inspection (see 4.3)

4.2 First article inspection. The first article test set shall be subjected to the examinations, tests, and analyses described in 4.5.1 through 4.5.6.3. The contractor shall provide or arrange for all test equipment and facilities.

4.3 Conformance inspection. Each production test set shall be subjected to the examination and tests described in 4.5.1, and burn-in described in 4.5.2.

4.4 Inspection requirements.

4.4.1 General inspection requirements. Apparatus used in conjunction with the inspections specified herein shall be laboratory precision type, calibrated at proper intervals to ensure laboratory accuracy.

4.4.2 Data. During all testing specified herein, at least the following data, unless not applicable, shall be recorded at intervals not to exceed 30 minutes. Additional data and/or shorter intervals shall be provided as appropriate for any specific test.

a. Date.

c. Time started.

d. Time finished.

c. Ambient temperature.

4.4.3 Test rejection criteria. Throughout all tests specified herein, the test set shall be closely observed for the following conditions, which shall be cause for rejection:

a. Failure to conform to design or performance requirements specified herein or in the contractor’s technical proposal.

b. Any spillage or leakage of any liquid except as allowed herein.

c. Structural failure of any component, including permanent deformation, or evidence of impending failure.

d. Evidence of excessive wear.

e. Conditions that present a safety hazard to personnel during operation, servicing, or maintenance.

f. Evidence of corrosion or deterioration.

4.5 Test Methods.

4.5.1 Examination of product. Each test set shall be examined to verify compliance with the requirements herein, and prior to accomplishing any tests listed in section 4.5. A contractor-generated, Government-approved checklist shall be used to identify each relevant requirement not verified by a test or analysis, and to document the inspection results. Particular attention shall be given to materials, workmanship, dimensions, surface finishes, protective coatings and sealants and their application, welding, fastening, and markings. Proper operation of each test set function shall be verified. Each production test set shall be inspected to a Government-approved reduced version of the checklist, and shall include the following requirements of Table IV to ensure qualitatively the proper functioning of the equipment, including all operating controls. Certifications shall be provided in accordance with Table V. From each lot a random sample of instruments shall be selected and tested to show conformance with the performance parameters of TABLE VI. Sampling shall be according to TABLE VII. Lots in which samples exhibit any failure shall be screened for that failure before being subjected to environmental tests of TABLE VIII.

TABLE IV. Requirements

Parameter Section Requirement Pressure vacuum-pump 3.3.12 Restricted material 3.4.1 Power cables 3.7.1 Fuses and circuit breakers 3.7.3 Accessories 3.8 Hoses and connections. 3.8.1 Commercial accessories 3.8.2 Workmanship 3.12 Bolted connections 3.12.1 Cleaning 3.12.2

TABLE V. Required certifications

Paragraph Required Certification, Analyses, and Inspection 3.2.1RVSM Certification that the RVSM requirement is met.

3.3 Design and construction

Certification of compliance with requirements of MIL-PRF-28800 and FED-STD-595.

3.3.5 Human factors. Certification of compliance with requirements of MIL-STD-1472.

3.3.7 Accessibility.

Certification that accessibility of different parts in the test set meet the requirements.

3.3.11 IEEE-488, RS-232, USB

and ethernet bus.

Certification that IEEE-488 control bus can operate with the remote unit connected or disconnected.

3.3.8 Encapsulation and

embedment.

Certification that if subassemblies are potted they are readily accessible.

3.4.1 Restricted materials

Certification that no restricted materials have been used and meets the requirements of MIL-PRF-28800.

3.4 Part, materials and processes Certification that requirements of MIL-PRF-28800 have been met.

3.4.2 Interchangeable

Certification that the test set meets the interchangeable requirements of MIL-PRF-28800.

3.6 Transportability. Certification that test set meets the transportability requirements.

3.10.4 Scheduled maintenance.

Certification that the time between scheduled maintenances will be no less than 1500 hours. .

TABLE VI. Performance parameters

Parameter Section Requirements Altitude 3.11.1 Altitude rate 3.11.1 Airspeed 3.11.1 Ranges, resolution, and accuracies

3.11.2

Simulated true airspeed control

3.11.3

Pressure modulation 3.11.4 Leakage test mode 3.11.5 Self test 3.11.6 IEEE-488 Bus & RS-232 interface

3.11.7

External volume range 3.11.8 Stability 3.11.9 Overshoot 3.11.10 Test set leakage 3.11.11

TABLE VII. Production control sampling

Lot Size Sample

Size 2 to 8 * 9 to 90 8 91 to 150 12 151 to 280 19 281 to 500 21 501 to 1,200 27 1,201 to 3,200 35 3,201 to 10,000 38 10,001 to 35,000 46 35,001 to 150,000 56 over 150,001 64

NOTES: 1. *Indicates entire lot must be inspected

2. Acceptance number (failures) in all cases is zero

4.5.2 Burn-In. All units used for random sampling testing shall be subject to a minimum 10 hours on-time burn-in period before acceptance inspection/testing. During the last 3 hours of on-time burn-in, the units must operate failure free. Until this time, the units will be allowed to accumulate failures. Each unit that fails during the final 3-hour period shall be repaired and returned to test until it successfully survives a 3-hour period without failure. Failures that occur during the burn-in test shall be noted and reported, but shall not count toward the establishment of equipment mean-time-between-failure (MTBF). Before burn-in, the satisfactory operation test (SOT) shall be conducted. Daily satisfactory operation checks (SOC) shall be conducted. For the last 3-hour failure free period, a complete SOT shall be conducted before and after the period. SOT employs the necessary external input and evaluation equipment to determine if the units conform to all the requirements of the associated detail specification. SOC employs a maximum number of active circuits of the units with a minimum requirement for external input or evaluation equipment to ensure that all functions of the units are operational. If the units fail during the SOT, the entire 10 hour burn-in period must be repeated. While under burn-in, the units shall be subjected to the following conditions:

a. Ambient Temperature: 40°C +5°C -0°C (104°F +9°F -0°F)

b. Input Voltage: 115 Volts, +5%, -2%.

c. Equipment On-Off Cycling: The equipment power shall be cycled (on for 2 hours and off for 15 minutes, repeat), until a minimum of 3 full cycles have been completed. Immediately following the power cycling, the equipment shall remain on for a minimum of at least 3.25 hours, during which time the unit will operate without failure.

4.5.3 System safety hazard analysis . A system safety hazard analysis of the unit shall be conducted in accord ance with 4.2 through 4.8 of MIL-STD-882 to demonstrate com pliance with the mishap risk requirement of section 3.2.

4.5.4 Environmental

4.5.4.1 Tests. The tests of Table 3 shall be performed on instruments that have passed the required parameters of Table 2. The tests shall be performed according to MIL-PRF-28800 or MIL-STD-810 except as specified in the following subparagraphs.

4.5.4.1.1 Vibration. The tester shall conform to the specified performance and accuracy requirements during the vibration conditions specified for class 2 in MIL-PRF-28800.

4.5.4.1.2 Electromagnetic interference. The equipment shall be tested for compliance with the requirements of paragraph 3.9.2. Test procedures shall be according to the test methods of MIL-STD-461 as implemented by a contractor- prepared, Government approved test plan.

Accordingly, the emission and susceptibility requirements of CE1O2, CS1O1, CS114, RE1O2, and RS1O3 must be complied with, and shall be met by the procedures in MIL-STD-461, as outlined in the approved EMI test plan.

4.5.4.1.3 Sampling plan. From first production lot only, a random sample of three instruments shall be selected and two instruments shall be subjected to all Environmental Tests in TABLE IX except EMI. If a sample exhibits any failure, the entire lot shall be screened for that failure.

The third instrument shall be subjected to the specified EMI tests of paragraph 3.9.2, following the successful completion of other environmental testing. The EMI test failures shall not require retesting of other environmental tests unless an instrument modification is necessary. If modifications were made to the other units during any other environmental testing, they shall be incorporated into the EMI unit before EMI testing.

TABLE VIII. Environmental testing

Parameter Requirem ent Temperature 3.9.1 Electromagnetic interference 3.9.2 Operating and non-operating altitude

3.9.3

Precipitation 3.9.4

4.5.4.1.4 High temperature operation test. The first article testers shall be tested in accordance with MIL-STD-810, Method 501.5, Procedures I and II, to demonstrate compliance with the high temperature operating and storage requirements of 3.9.1. Test duration shall be one 24-hour cycle for each procedure.

4.5.4.1.5 Low temperature operation test. The first article testers shall be tested in accordance with MIL-STD-810, Method 502.5, Procedures I and II, to demonstrate compliance with the low temperature operating and storage requirements of 3.9.1. Test duration shall be one 24-hour cycle for each procedure.

4.5.4.1.6 Precipitation test.

4.5.4.1.6.1 Rain test. The first article testers shall be tested in accordance with MIL-STD-810, Method 506.5, Procedure I, to demonstrate compliance with 3.9.4.1.

4.5.4.1.6.2 Ice accretion test. The first article testers shall be tested in accordance with MIL- STD-810, Method 521.3, with an ice thickness of 1.5-inches to demonstrate compliance with the ice accretion requirement of 3.9.4.2.

4.5.4.1.6.3 Salt fog test. The first article testers shall be tested in accordance with MIL-STD- 810, Method 509.5, to demonstrate compliance with 3.9.4.3. Test duration shall be alternating 24-hour periods of salt fog exposure and drying conditions for 24-hour periods (two wet and two dry).

4.5.4.1.7 Solar radiation. Contractor shall provide certification to demonstrate compliance with 3.9.5.

4.5.4.1.8 Fungus. Contractor shall provide certification to demonstrate compliance with 3.9.6.

4.5.4.1.9 Sand and dust test. The first article testers shall be tested in accordance with MIL- STD-810, Method 510.5, Procedures I (12 hours) and II (90 minutes per side), to demonstrate compliance with 3.9.7.

4.5.5 Reliability.

4.5.5.1 Tests. After showing conformance with all safety requirements of section 3.2 , the instruments shall be tested to show conformance with all RAM requirements of TABLE IX Test Plan IVD of MIL-HDBK-781 shall apply. The contractor shall demonstrate the equipment MTBF (00) as stated in the bid— data submission. The stated value shall be equal to or greater than an upper test MTBF (00) of 500 hours. Reliability tests shall be performed on the first production lot only.

TABLE IX. RAM tests

Parameter Section Requirements Reliability, availability, and maintainability

3.10

Reliability 3.10.1 Calibration 3.10.2 Calibration time 3.10.2.8 Maintenance provisions 3.10.3 Scheduled maintenance 3.10.4

4.5.5.1.1 Sampling plan. From the first production lot only, a random sample of ten instruments shall be selected and tested to show conformance with all RAM requirements of Table 4. If the sample size, selected from TABLE VIII, from the first production lot is not of sufficient size to allow ten dedicated instruments for RAM Requirements Reliability testing, then the sample size shall be increased to a quantity sufficient to accommodate this requirement.

4.5.5.1.2 Test length. Testing shall continue until the total units’ hours, with the total count of relevant equipment failures, permit an accept or reject decision.