D-TACAN Frist Article Test

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FIRST ARTICLE TEST

AND EVALUATION PLAN (FAT&E)

For the

DEPLOYABLE TACAN (D-TACAN)

Version: 0 Version Date: 08 September 2009

Prepared By:

558 ACSS/GFEA

3001 Staff Drive, Post 2AF1-102D

Tinker AFB, OK 73145-3305

Approved By:

William P. Parker System Engineer

PRELIMINARY

Version: 1, 20090828 Page ii of ii

RECORD OF CHANGES

REVISIONS

REV DESCRIPTION DATE APPROVED

0 Original Release 08 SEPTEMBER 2009

FIRST ARTICLE TEST & EVALUATION PLAN (FAT&E)

USAF D-TACAN

DISTRIBUTION STATEMENT: This document may contain, sensitive or other non-public information not intended for disclosure outside official government channels. Do not disseminate this document or its contents (whether in full or abridged format) without the approval of the undersigned’s office. If this document is held by an unauthorized party, then destroy by any method that will prevent disclosure of the contents or reconstruction of the document.

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(Version 0)

1. GENERAL

1.1 This test plan pertains specifically to the United States Air Force Deployable Tactical Air Navigation (D- TACAN) system being purchased to replace the AN/TRN-26 by the 558 ACSS System Program Office.

1.2 It is the intention of this test to verify that the supplied system meets the requirements specified within the Commercial Item Description (CID), Document Number 200948526 (Cage 98748). All items within the CID will be tested. Testing may include desktop analysis requiring no additional physical testing by the Government using data already available to date. If desktop analysis proves that the system has already passed testing to the same or better requirements of the CID, a waiver from one or more test items will be granted. Note that requirements labeled with a number format of AAA-## (e.g. GEN-1) are fully described within the CID.

1.3 This replacement program is purchasing a non-developmental, commercial item. No prototypes will be procured to provide any preliminary data points. Preliminary data may be available from the Original Equipment Manufacturer (OEM) / vendor or possibly other users of the supplied system that have previously tested the system.

2. PLAN

2.1 An FAA flight check will be scheduled and possibly performed by Air Force Flight Standards Agency (AFFSA). Minimum acceptance is passing the flight check IAW MIL-STD-291C and AFMAN 11-225 (a.k.a. FAA Order 8200.1C) meeting the requirements listed in GEN-1 thru GEN-5 with the same or less restrictions than an AN/TRN-26C setup at the same location.

2.2 Document mobility certification to Standard Automotive Engineering, SAE AS8090. Note any restrictions and check for clear visibility of each restriction to the user. Test to Type IV standards. Minimum acceptance is Type III mobility and no damage is caused to the equipment, degradation of operational performance and that no cosmetic damage is incurred.

2.3 Transport test to verify mobility transportation modes of single aircraft (C-5, C-17 and C-130) and truck.

2.4 MIL-STD-810G environmental testing for temperature, relative humidity, altitude, wind and ice loading, snow, solar radiation and ultraviolet resistance. Minimum requirements are listed in CID ENV-1 through ENV-6 and ENV-8.

2.5 Verify functionality of remote status indicator. Induce fault to ensure properly communicated to controllers.

Check for remote on/off control.

2.6 Environmental control units (ECUs) redundancy will be tested to ensure each is capable of full heating and cooling loads and operate in an alternating start cycles or similar mechanism to ensure each ECU run periodically.

2.7 Verify source power to GEN-7 requirements.

2.8 Measure the load on the diesel generator under normal operating conditions. Verify diesel generator loading to be above 75% diesel generator normal load capacity conditions per GEN-8.

2.9 Run power failure test by turning off supplying circuit breaker and disconnecting backup generator. Should run on battery for a minimum of 4 hours.

DISTRIBUTION STATEMENT: This document may contain, sensitive or other non-public information not intended for disclosure outside official government channels. Do not disseminate this document or its contents (whether in full or abridged format) without the approval of the undersigned’s office. If this document is held by an unauthorized party, then destroy by any method that will prevent disclosure of the contents or reconstruction of the document.

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2.10 Power transfer check (switch over to generator) by turning off main supply power to ensure smooth transition to backup power generator utilizing the battery power as the changeover power source.

2.11 Check that all interconnect and field cables are provided and that all Radio Frequency (RF) cables are Heliax or equivalent.

2.12 Check for redundant operation of transmitter, receiver and monitoring equipment with automatic switch over.

Must disable each primary unit to verify that the secondary unit comes online with continuous system operation. Restore primary unit to ensure switch back to primary with continuous system operation.

2.13 Induce faults and confirm fault isolation down to Line Replaceable Unit (LRU) or next higher assembly.

Verify that remote status indicator properly indicates fault to the controllers. Restore to normal operation.

Ensure fault clears, is logged and controllers are properly notified via the remote status indicator. Verify startup and periodic diagnostics are functioning for “on line” status and fault indicators.

2.14 Connect to system remotely using Hayes compatible modem. Check for all system parameters, faults, errors, settings, report generation, user information, password control, system adjustments, resets, equipment alignment and other indicators provided. Verify MRS-1 thru MRS-17.

2.15 Verify cable surge protection is in place and wired appropriately. Cable shields shall be terminated IAW MIL-STD-188-124B and per IF-2.

2.16 Verify Electromagnetic Interference and Radio Frequency Interference (EMI/RFI) shielding for cabinetry.

2.17 Verify no dissimilar metal-to-metal joints.

2.18 Verify total facility load as less than or equal to 7.5 KVA.

2.19 Verify shelter type per its Military or ISO standard.

2.20 Verify antenna location as non-remote from the shelter/trailer subassembly.

2.21 Perform a minimum of a 100 hour, normal operation without a malfunction requiring system down time. If empirical data is available from the vendor, calculate Mean Time to Repair (MTTR) and Mean Time Between Critical Failure (MTBCF) per RM-2 and RM-3.

2.22 Verify whole system center of gravity per aircraft and truck transportation mode requirements. Verify that center of gravity is marked on the system.

2.23 Desktop analysis of RoHS (HAZ-1) and HAZMAT (HAZ-2) requirements. Material Safety Data Sheets (MSDS) should be available for all hazardous and toxic materials.

2.24 Verify IUID IAW MIL-STD-103N as well as markings for Electrostatic Discharge (ESD) sensitive LRUs as defined by MIL-STD-1686 for Class 1 or 2.

2.25 Verify wiring, wire coloring and wire marking per MIL-HDBK-454, Guideline 66.

2.26 Verify workmanship per MIL-HDBK-454, Guidelines 1, 5, 9 and 15, along with USAF T.O. 00-25-234.

2.27 Verify compliance with AFI 91-302 for OSHA.

2.28 Verify compliance with NFPA-70 (NEC).

DISTRIBUTION STATEMENT: This document may contain, sensitive or other non-public information not intended for disclosure outside official government channels. Do not disseminate this document or its contents (whether in full or abridged format) without the approval of the undersigned’s office. If this document is held by an unauthorized party, then destroy by any method that will prevent disclosure of the contents or reconstruction of the document.

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2.29 Verify compliance with MIL-STD-188-124B, NFPA-77, NFPA-780 for grounding, bonding and shielding as well as lightning detection. Verify compliance with “no painted surfaces” for lightning protection devices.

2.30 Verify chassis grounds on all LRUs along with separation of grounds and AC return lines (neutral) per SAF- 5.

2.31 Verify external chassis ground per SAF-6.

2.32 Verify grounding of all cables carrying voltages in excess of 30 VRMS or VDC.

2.33 Perform “hack” testing of all (if any) computer remote access points to ensure security measures are in place.

2.34 Inspect for safety hazards.

2.35 Verify any provided obstruction lights to be FAA L810 certified.

2.36 Additional tests to be performed per list of “best commercial practice and standards” as provided by the OEM/vendor.

3. POC

3.1 William Parker, 558 ACSS/GFEA, System Engineer, William.parker@tinker.af.mil, (405) 734-3845, DSN 884-3845.

Attachment(s):

None mailto:William.parker@tinker.af.mil�