3 SOW Attachment 1-Performance Specifications VFDR.pdf

SOW Attachment 2 Performance Specifications

Rotary Wing Voice and Flight Data Recorder Replacement

70Z03824RS0000001

The below performance specifications include both the desired specifications and the required specifications for the Rotary Wing Voice and Flight Data Recorder replacement (VFDR). The required specifications are stated as “shall” and must be included in the offerors VFDR. The desired performance specifications are those specifications stated as “desired” are preferred in the offerors VFDR, but not required. The threshold requirements are those requirements that “shall” be included in the VFDR.

VFDR Technical Specifications 1 The VFDR shall be a combination system. The system shall consist of a single digital

VFDR with 90 day underwater Acoustic Beacon (UAB), which shall store audio from the aircraft Intercom System (ICS) and area microphone and flight data parameters from aircraft systems into a Crash Survivable Memory Unit (CSMU).

2 The parametric flight data shall be output from the VFDR and stored in a non-crash survivable Digital Storage Unit (DSU) or Quick Access Recorder (QAR). The DSU/QAR may be internal or external to the VFDR and be easily accessible. The CSMU and DSU/QAR shall be readily and easily downloadable to support maintenance operations, Flight Operations Quality Assurance (FOQA)/Flight Data Monitoring (FDM) as well as mishap analysis and investigation.

3 The VFDR shall be compatible with and integrated into the MH-65E and MH-60T airframes, each resulting in a unique embedded Operational Flight Program (OFP) implementation for parameter recording.

4 The Contractor shall provide a DSU/QAR which only receives flight data from the VFDR system.

5 The VFDR system shall have an external area microphone compliant with ED-112A specifications.

6 The VFDR shall be 90-day UAB compliant with TSO-C121b specifications.

7 The VFDR system shall be at least at a DoD Technology Readiness Level (TRL) of 8.

8 The VFDR system shall be an existing, non-developmental solution that meets the form and function of the currently installed VFDRs in all the listed USCG aircraft.

9 The Contractor shall provide a comprehensive documentation package consisting of all component system information as well as well as an Installation Manual, software and electrical ICDs, User manual, Maintenance Manual, etc.

VFDR System Characteristics 10 The VFDR shall meet, at a minimum, the requirements of Technical Service Orders

(TSO) C123c and C124c. TSO C155b compliance is desired.

11 The VFDR shall begin recording parametric data as soon as the applicable bus power is applied.

12 The VFDR CSMU shall have sufficient memory to record four (4) channels of voice for a threshold of four (4) hours per channel and an objective goal of six (6) hours or more per channel. Additionally, the CSMU shall have the memory to record a minimum threshold of 25 hours of aircraft parametric flight data via digital buses with the objective of 50 hours or more.

13 The VFDR shall output the same flight data recorder within its CSMU to the DSU/QAR removable media.

14 The DSU/QAR removeable media shall record a threshold of 25 hours of parametric flight data with 50 hours desired.

15 The DSU/QAR shall have programmable logic to set conditions for recording parametric data, e.g., engine N1 (NG) > 10%=record on, engine N1 (NG) <5%=record off

16 The VFDR shall be capable of capturing and recording data from ARINC 429 (2 channels) and MIL-STD-1553 (2 channels).

17 ARINC 429 - The VFDR shall include at least four (4) configurable-speed receivers and at least one (1) configurable-speed transmitter. Additional receivers are desirable.

18 MIL-STD-1553 - The VFDR system shall include two (2), dual redundant, MIL-STD- 1553B multiplex bus interfaces. Each bus shall function concurrently in bus monitoring and remote terminal implementations. The VFDR shall respond to the 1553 bus controller (Collins CAAS) as a remote terminal without interrupting bus-monitoring functions.

19 Data Latency - The maximum time allowed between the VFDR receiving aircraft flight and audio data and the time data is captured in non-volatile memory in the CSMU for storage shall not be greater than 0.25 seconds.

20 The VFDR shall record approximately 650 parameters from the MH-65E 1553 and ARINC 429 data buses.

21 The VFDR shall record approximately 400 parameters from the MH-60T 1553 data bus.

Audio Voice

22 The VFDR shall assure recorded data fidelity sufficient to replay audio in an unambiguous interpretive manner. Three (3) narrow band channels shall capture ICS voice and one (1) wide band channel shall capture cockpit voice as well as ambient noise

23 The VFDR system shall contain a high-fidelity area microphone to capture cockpit and cabin ambient audio.

Power Requirements 24 The VFDR system shall operate using 28 (+1, -6 VDC) aircraft power IAW MIL-STD-

704A for Category B equipment.

25 The DSU/QAR shall operate using 28 (+1, -6 VDC) aircraft power IAW MIL-STD-

704A for Category B equipment.

Recorder Independent Power Supply (RIPS)

26 RIPS to provide at least 10 minutes of independent backup power that automatically engages whenever power to the recorder ceases, either by normal shutdown or loss of power to the electrical bus the VFDR is energized is desired.

Momentary Power Interruptions 27 The VFDR shall not produce a damaging or unsafe condition and shall automatically recover and be capable of full performance after a momentary power interruption upon resumption of power.

Software Requirements 28 Proprietary algorithms for data acquisition and output files shall not be used in the design of the VFDR. The Government shall have limited government rights to all source code, executable images, and object codes for VFDR associated software, including all tools.

29 The output file(s) (audio and flight data) downloaded from the VFDR and DSU shall be non-proprietary and, in its raw downloaded format, be readable and decompressed by commercially available analysis, animation and Flight Data Management (FDM) software.

30 The VFDR shall include a commercial standard port interface and capability to update embedded software to a new version while the VFDR is in a laboratory or installed and using aircraft power.

Commonality 31 The VFDR system shall have the capability to store multiple aircraft configurations so the same unit shall be utilized across all USCG rotary wing airframes without reconfiguring software.

32 The VFDR shall have the ability to automatically load the appropriate aircraft configuration depending on the aircraft it is installed on using a specified aircraft wiring scheme (strapping).

33 The VFDR shall not record over any data when the unit is operated in a lab/test function (off aircraft).

Compatibility of Data Format with Existing Systems 34 The output file shall be provided in an industry recognized commercial file format, such as American Standard Code for Information Interchange (ASCII) text or equivalent format. In addition, the output file shall contain an identification record, to include aircraft type, aircraft serial number, download software version number, date and time of download, and a parameter definition record which defines the type and format of each data parameter contained in the subsequent flight data record.

Data Extraction 35 VFDR CSMU audio and flight data files shall be extractible via commercially standard laptop port or transfer media interface using non-proprietary hardware and software tools. CSMU download shall require less than 20 minutes.

36 The Contractor shall provide Ground Service Equipment for downloading VFDR if other than standard laptop ETHERNET port.

37 The Contractor shall provide all applicable downloading harnesses and equipment required for downloading VFDR.

38 DSU/QAR data shall be extractable, without any corruption, via transfer media, or memory card extraction, using non-proprietary hardware and software tools. DSU/QAR memory download shall require less than 15 minutes, and not require aircraft power.

Data shall be extracted by segments or functional partitions. Extracted data shall be easily correlated to an aircraft mission timeline. The downloading software shall provide the capability to selectively download parametric and/or voice data based on time or flight.

39 Downloading the VFDR CSMU and/or DSU shall not erase, reset, or alter the existing data in any way.

Useful Life

44 The VFDR system shall have a useful life of not less than 20 years under any combination of operating and storage conditions, other than electromagnetic pulse, when the operational service life has not been exceeded.

45 The VFDR shall have a Mean Time Between Failures in excess of 15,000 hours.

Operational Service and Storage Life 46 The VFDR system shall have an operational service life of not less than 15,000 hours under any natural or induced combination of environmental conditions specified herein.

The VFDR system shall meet all requirements of this specification after storage for up to five (5) years in the manufacturer’s original packaging.

MH-65E Critical Frequencies

65 The frequencies of most concern are the main rotor blade pass frequencies and 2-, 3- and four-time multiples of the main rotor frequencies.

66 Main Rotor - Forward Flight 355 RPM, 5.9Hz, Blade Pass (4) 23.7 Hz, Hover 365 RPM, 6.1Hz, Blade Pass (4) 23.3 Hz.

67 Tail Rotor - Forward Flight 3717 RPM, 62.0Hz, Blade Pass (10) 619.6Hz, Hover 3822 RPM, 63.7Hz, Blade Pass (10) 637.1Hz.

MH-60T Critical Frequencies

68 The frequencies of most concern are the main rotor blade pass frequencies and 2-, 3- and four-time multiples of the main rotor frequencies.

69 Main Rotor - Forward Flight 258 RPM, 4.3Hz, Blade Pass (4) 17.2 Hz.

70 Tail Rotor - Forward Flight 1188 RPM, 19.7Hz, Blade Pass (2) 39.4Hz.

VFDR Installation and Installed Performance

71 The VFDR shall comply with ED-112A.

VFDR Physical Characteristics 72 The VFDR shall utilize positive lock data/electrical connectors. The VFDR should utilize quick connect/disconnect capability.

73 The desired size of the VFDR would be no larger than the currently installed VFDR due to space limitations. The current VFDR is the GE Aviation K3-VADR with a footprint of (L) 8.04” x (W) 4.4” x (H) 3.8”. An additional size limitation may be available in the case of a separate DSU/QAR design solution. The current DSU has a footprint of (L) 6.29” x (W) 5.75” x (H) 1.5”.

VFDR Physical Characteristics