RFI_Sources_Sought_Notice_ASM Leadplanes.pdf

REQUEST FOR INFORMATION – SOURCES SOUGHT

Aerial Supervision Module (ASM)-Leadplanes

Special Notice Number: SN-2023-LP01

Agency: United States Department of Agriculture (USDA)

Office: Forest Service

Location: National Interagency Fire Center – Boise, ID

RFI Issue Date: 1 2 / 5 / 2 0 2 2

RFI Response Date: 1 / 4/ 20 2 3 @ 1 40 0 M S T

Submittal of information:

The information requested by this Request for Information (RFI) – Sources Sought shall be provided, in writing (electronic). Provide a brief response to this Special Notice of not more than five (5) pages, excluding cover page, by 14:00 (Mountain Time) January 4, 2023 to the following email address:

shelia.stoddard@usda.gov

Synopsis: This Request for Information – Sources Sought is for Market Research and Planning purposes only.

Product Service Code: F003 – Natural Resources/Conservation – Forest-Range Fire Suppression

NAICS Code: 532411 – Commercial Air, Rail, and Water Transportation Equipment Rental and Leasing

Business Size Standard: $40 Million (annual receipts)

THE GOVERNMENT DOES NOT INTEND TO AWARD A CONTRACT ON THE BASIS OF THIS RFI OR TO OTHERWISE

PAY FOR THE INFORMATION REQUESTED.

This RFI does not constitute a solicitation for proposals or the authority to enter into negotiations to award a contract. No funds have been authorized, appropriated, or received for this contemplated effort. This RFI is for planning purposes only and shall not be considered as a request for proposal or as an obligation on the part of the Government to acquire any products or services. No entitlement to payment of direct or indirect costs or charges by the Government will arise because of contractor submission of responses to this RFI or the Government’s use of such information. The Government reserves the right to reject, in whole or in part, any contractor’s input resulting from this RFI. Responses to this RFI will not be returned. Whatever information is provided in response to this RFI may be used to assess potential tradeoffs and alternatives available for future needs. The information provided may be utilized by the US Forest Service in developing its Acquisition Strategy, Statement of Work, and/or Performance Specifications. The information resulting from this RFI may be included or combined with other submissions in one or more options considered in the analysis of alternatives. Any proprietary information that is submitted may be used in establishing requirements, but specific information will be safeguarded as proprietary providing it is marked in accordance with FAR 3.104-4.

mailto:shelia.stoddard@usda.gov

Primary Point of Contact:

Shelia Stoddard, Contracting Officer sheila.stoddard@usda.gov 623-293-8721

Technical Point of Contact:

Walter Bunt, Washington Office, National Aerial Supervision Program Manager walter.bunt@usda.gov 530-515-4016

Description:

The purpose of this announcement is to obtain information regarding interested parties who are capable of providing 15 minimum and up to 20 multi-engine turbine aircraft of the same make/model/series on a dry lease basis with contractor provided maintenance and insurance, available for the exclusive use of Government pilots for wildland fire missions and other administrative activities. The contractor must be capable of providing mission equipped aircraft as outlined in the attached Statement of Work that are suitable to meet the Government’s requirement.

Background:

To ensure the efficiency and safety of aviation operations, the Forest Service leases and deploys airborne Aerial Supervision Module (ASM) and Leadplane platforms flown by agency or contract pilots for in-flight supervision on fires and to conduct other administrative support activities.· When the aircraft is performing the low level support role (Leadplane), the mission consists of directing and guiding airtankers into fire areas and as necessary "leading" them during the actual retardant drop, at times operating below 500 feet above ground level (AGL) in steep mountainous terrain and turbulent conditions. The air attack mission (ATGS) consists of operating above 500' (AGL) and coordinating tactical use of all aircraft working at the incident. The ASM role combines both the Leadplane and ATGS role into one. The administrative support mission includes resource management, passenger and cargo transportation, law enforcement, pilot training, pilot proficiency, and administrative activities.

Response Requirement:

(1) Company name, company mailing address, and point of contact information.

(2) Company's applicable socioeconomic status and available contract ordering vehicles (include contract numbers), if available. Include past Government contracting performance if applicable.

(3) Capabilities Statement that clearly aligns with the capabilities of the company to the Statement of Work (SOW) outlined below. Include a brief list of experience on similar projects (comparable in size of program and complexity), including client/project owner, name/title/phone number of a client point of contact, prime contractor name (if applicable), size of comparable contract, brief description, period of performance.

(4) Describe your experience in providing support of leased aircraft and include your organization’s maintenance facilities and maintenance personnel qualifications.

mailto:sheila.stoddard@usda.gov mailto:walter.bunt@usda.gov

STATEMENT OF WORK

Aerial Supervision Module (ASM)-Leadplanes

TECHNICAL REQUIREMENTS AND AIRCRAFT SPECIFICATIONS

(1) The contractor shall provide specific written authorization from the aircraft manufacturer by make, model, series, and serial number for operation in the firefighting environment. The aircraft must have a manufacturer approved maintenance and inspection program that accounts for usage in the firefighting environment. The aircraft shall be FAA certificated as a

Normal, Standard, or Utility category twin-engine airplane, be certificated for single pilot operation with a minimum flight deck capacity of two with dual controls plus a minimum passenger capacity of two.

(2) Aircraft shall conform to its approved type design, be maintained in accordance with the requirements of 14 CFR Part 135 notwithstanding the aviation regulations of the States in which the aircraft may operate except those requirements specifically waived by the CO.

(3) Minimum Aircraft Performance Requirements.

a. Useful Load: 1,000 lb. or greater payload when fully equipped with 4 hours plus 30-minute reserve.

b. Speed: Cruise speed of 280 knots or greater True Airspeed (TAS) @ ISA +20 Degrees C @ 24,000 MSL.

c. Endurance: A flight endurance at maximum range power setting while maintaining four (4) hours plus 30-minute reserve or longer@ 14,000ft MSL@ ISA +20 Degrees C.

d. Power Plant: The airplane must be in current production, twin-engine, turboprop, manufacturer built (no amateur or manufacturer-built kit aircraft), new or used. The airplane must have auto feather or similar system capable of automatically feathering the propeller of a failed engine. If equipped with retractable landing gear, a gear warning horn silence button must be mounted on the pilot's yoke or power levers to facilitate silencing the horn with the flaps up or in an approach position regardless of power lever position.

e. Performance: The airplane shall have a minimum maneuvering speed (Va) of 150 Knots Indicated Airspeed (KIAS) or greater. The aircraft must have a minimum controllable airspeed (Vmca) of 100 KIAS or lower, a single engine service ceiling of 12,500 feet or higher (pressure altitude and standard temperature) and the ability to maintain a

Vyse at 130 KIAS or slower. The airplane shall have a maximum gross take-off weight of no more than 19,000 pounds.

f. Environmental: Pressurized aircraft with environmental controls.

AVIONICS

(1) MINIMUM REQUIREMENTS

a. All avionics used to meet this specification shall comply with the requirements of paragraph b. (AVIONICS

SPECIFICATIONS) and paragraph c. (AVIONICS INSTALLATION AND MAINTENANCE STANDARDS).

b. ASM aircraft shall be approved for day and night Visual Flight Rules (VFR), Instrument Flight Rules (IFR), and flight into known icing conditions. Aircraft with identical avionics, autopilots and flight directors are preferred.

c. The following are the minimum avionics which shall be installed. (Additional avionics may be required.)

i. Three VHF-AM Radios ((COM 1, COM 2, COM 3,)

ii. Three VHF-FM Radios (FM 1, FM 2 & FM 3)

iii. An Intercom System (ICS) for the PIC, SIC/observer and Instructor (directly behind the SIC/observer)

iv. Separate Audio Control systems for the PIC, SIC/observer and Instructor. Audio control systems shall not mute Receive and ICS audio during Transmit Operations.

v. Bose compatible aviation series powered headset jacks for the PIC, SIC/observer and Instructor (directly behind the SIC/observer) in addition to the JJ-033 and JJ-034 microphone and headset jacks.

vi. Controls for the PIC, SIC/observer and Instructor to each independently adjust headphone volume for each communications receiver.

vii. Individual cockpit speakers for the PIC and SIC/observer

viii. Controls for the PIC, SIC/observer to each independently select and adjust speaker volume, independent of headset audio, for each communications receiver.

ix. One IFR certified Global Positioning Systems (GPS) with moving map (xi)An Emergency Locator Transmitter

(ELT) certified to TSO-C126

x. An Automated Flight Following system (AFF)

xi. One Mode S Transponder (xiv)One Altimeter and Automatic Pressure Altitude Reporting system

xii. One Traffic Advisory System (TAS) with 1 mile display selection

xiii. A Three Axis Autopilot (Roll, Pitch, and Yaw) with Flight Director

xiv. One RADAR Altimeter

xv. One Multi-Function Display (MFD)

xvi. Equipment and lighting for night VFR operations in accordance with 14 CFR135.159 and 14 CFR 135.161

xvii. Two VOR/Localizer systems

xviii. One Glideslope system interfaced to the #1 Localizer(xxii)One Three Light Marker Beacon system

xix. One Weather RADAR system usable during all flight conditions

xx. One Satellite Weather system with XM Aviator subscription or equivalent.

xxi. One Class B Terrain Awareness and Warning System (TAWS)

xxii. 3 Dual USB charging ports at the PIC, SIC/Observer, and Instructor positions.

xxiii. Portable Electronic Device (PED) tolerance, by STC, in all phases of flight.

xxiv. ADS-B IN and OUT

xxv. Equipment for conducting aircraft Operational Load Monitoring (OLM).

xxvi. A “G” Meter with audio tone prior to exceedance

xxvii. Smoke Generator. Aircraft shall be equipped with an FAA approved smoke generating system, actuated from the controls of the left seat pilot position.

(2) AVIONICS SPECIFICATIONS

a. Communications systems

i. Transmitters shall not open squelch on, or interfere with, other AM or FM transceivers on the aircraft which are monitoring different frequencies. Transmit interlock functions shall not be used with communication transceivers.

ii. VHF-AM Radios: VHF-AM radios shall be TSO approved aeronautical transceivers, permanently installed, and operate in the frequency band of 118.000 to 136.975 MHz with a minimum of 760 channels in no greater than 25 KHz increments. Transmitters shall have a minimum of 5 Watts carrier output power.

iii. VHF-FM Radios: All aircraft approved for fire operations shall use P25 Digital VHF-FM transceivers meeting the specifications of FS/OAS A-19. FM radios used in all aircraft shall be agency approved. FS/OAS A-19 and a list of currently approved FM radios can be found on the following website:

http://www.nifc.gov/NIICD/documents.html. The following requirements shall be met.

iv. VHF-FM radios shall be aeronautical transceivers, permanently installed in a location that is convenient to the PIC and SIC/observer, and operate in the frequency band of 138 to 174 MHz. All usable frequencies shall be programmable in flight. Narrowband and digital operation shall be selectable by channel for both

MAIN and GUARD operation. Carrier output power shall be 6-10 Watts nominal.

v. Transceivers shall have a GUARD capability constantly monitoring 168.625 MHz and have a tone of 110.9 on all GUARD transmissions. Simultaneous monitoring of MAIN and GUARD is required. Scanning of GUARD is not acceptable. Aircraft not approved for Air Tactical operation only require one FM GUARD receiver

vi. Transceivers shall have the capability of encoding CTCSS sub audible tones on all channels. A minimum of

32 tones meeting the current TIA/EIA-603A standards shall be selectable.

vii. Transceivers shall have the capability to display both receiver and transmitter frequencies. Activation indicators for transmit and receive shall be provided for both MAIN and GUARD operation.

viii. The radio shall use an external broadband antenna covering the frequency band of 138 to 174 MHz

(Comant Cl-177-1 or equivalent).

b. Audio Systems

i. Intercom systems (ICS):ICS shall integrate with the aircraft audio control systems and mix with selected receiver audio. An ICS volume control and a "hot mic" capability shall be provided for the PIC and

SIC/observer. Passenger volume adjustments shall not · affect the PIC. Hot mic may be voice activated

(VOX) or controlled via an activation switch. The PIC shall have an isolation capability.

ii. Audio Control systems

iii. Controls for transmitter selection and independent receiver selection of all required radios shall be provided for each required audio control system. Each system shall have the capability to simultaneously select and utilize a different transceiver (and PA if required). Side tone shall be provided for the user as well as for cross monitoring by all installed systems. Receiver audio shall be automatically selected when the corresponding transmitter is selected. Receiver audio shall be provided to each position which requires

ICS. Aft audio control systems are not required to provide NAV audio.

iv. All required passenger positions shall utilize the SIC/observer's audio control system unless an aft audio control system is installed. Drop cords may be used provided MS3112E10-6S type 6-pin connectors are installed adjacent to the required passenger headset jacks and wired for compatibility with an appropriate drop cord (Alpine Aerotech AAL280 series or equivalent).

v. All associated audio controls shall be labeled as COM-1, COM-2, COM-3, FM-1, FM-2, FM-3 etc... with the corresponding transceiver labeled to match. Audio shall be free of distortion, noise, or crosstalk. The system shall be designed for use with 600 ohm earphones and carbon equivalent, noise cancelling, boom type microphones. All required positions shall have JJ-033 and JJ-034 type microphone and headphone jacks separated by no more than 4 inches. Cockpit speakers shall be sufficiently amplified for use in flight.

vi. Crew positions shall have radio Push-To-Talk (PTT) switches on their respective flight controls. A PTT switch shall be provided to allow the SIC/observer to transmit without touching the flight controls.

c. Drop Cord Requirements

i. Coil cord with sufficient length to provide unrestricted movement according to mission requirements

(Minimum 3 feet retracted)

ii. 6-Pin MS3476L10-6P type connector on the coil cord

iii. JJ-033 and JJ-034 type headset jacks at the housing

iv. Large clip

v. Volume control

vi. ICS switch with momentary and lock positions

vii. Radio PTT switch (only for positions which require radio transmit)

viii. Drop cords for the SIC/observer and instructor

d. Aft Audio Control systems

i. The audio controller shall be installed in a location that provides the operator directly behind the

SIC/observer unobstructed access to the controls while seated. Aft passengers shall utilize this audio control system. If multiple aft audio controllers are installed, passengers shall utilize the most logical system.

ii. The audio controller shall be installed in a location that provides the operator directly behind the

SIC/observer unobstructed access to the controls while seated. Aft passengers shall utilize the aft audio control system(s).

(3) Navigation systems

a. Global Positioning Systems (GPS)

i. Aeronautical GPS: Each required GPS shall be TSO approved, permanently installed where both the PIC and

SIC/observer can clearly view the display, use an approved external aircraft antenna, and be powered by the aircraft electrical system. The GPS shall utilize the WGS-84 datum, reference coordinates in the DM

(degrees/minutes/decimal minutes) format and have the ability to manually enter waypoints in flight. The

GPS navigation database shall be updated annually covering the geographic areas where the aircraft will operate.

ii. GPS with Moving Map: The GPS providing data to the moving map shall meet all of the above GPS requirements. The moving map's display shall be 3 inches wide, 1.5 inches high, and show the aircraft's present position relative to user selected waypoints and geographical features. The map may be integrated with the GPS.

b. Surveillance systems

i. Emergency Locator Transmitters (ELT): Emergency locator transmitters shall be automatic-fixed, installed in a conspicuous or marked location, and meet the requirements detailed in 14 CFR91.207 (excluding section f). ELT antennas shall be mounted externally to the aircraft unless installed in a location approved by the aircraft manufacturer. TSO C126 or newer ELTs are required. TSO C126 and newer ELTs require documentation of current registration from the national civil aviation authority for which the aircraft is registered.

ii. Automated Flight Following systems (AFF): Automated flight following systems shall be compatible with the government's tracking program (AFF.gov), utilize satellite communications, and use aircraft power via a dedicated circuit breaker. AFF shall be functional in all phases of flight and in all geographic areas where the aircraft will operate. The following additional requirements shall be met.

a. A subscription service shall be maintained through the equipment provider allowing position reporting via the Government AFF Program. The reporting interval shall be every two minutes while in flight.

b. AFF equipment shall be registered with AFF.gov providing all requested information. Changes to equipment and registration information shall be reported to AFF.gov ensuring the program is current prior to aircraft use. For assistance, the Fire Applications Help Desk (FAHD) may be reached at (866) 224-7677 or (360) 326-6002.

c. An AFF operational test shall be performed prior to the annual compliance inspection. This test shall ensure that the system meets all requirements and is displayed in the AFF viewer with the correct information. A username and password are required. Registration and additional information are available at https://www.aff.gov/.

d. If AFF becomes unreliable the aircraft may, at the discretion of the Government, remain available for service utilizing radio/voice systems for flight following. The system shall be returned to full operational capability within 5 calendar days after the system is discovered to be unreliable.

e. This clause incorporates the Specific Section Supplement available at https://www.aff.gov/contractspecs.asp as if it was presented as full text herein.

f. For questions about current compatibility requirements contact the AFF Program Manager listed under contacts at https://www.aff.gov.

iii. Transponders: Transponder systems shall meet the requirements of 14 CFR 91.215(a). ASM aircraft shall have a "Mode S" transponder installed. Transponder systems shall be tested and inspected every 24 calendar months as specified by 14 CFR 91.413.

iv. (Altimeter and Automatic Pressure Altitude Reporting systems: Altimeter, static pressure, and automatic pressure altitude reporting systems shall be installed and maintained in accordance with the IFR requirements of 14 CFR Part 91. These systems shall be tested and inspected every 24 calendar months as specified by 14 CFR 91.411.

v. Traffic Advisory Systems (TAS): Traffic advisory systems shall be TSO approved, use active interrogation, graphically display traffic relative to the aircraft's horizontal position, and provide alert audio to the PIC and SIC/observer audio control systems. The display shall be within view of the PIC and SIC/observer. The system must provide coverage in all directions above and below the aircraft with a maximum range of at least 10 nautical miles. The display must allow range selection of 1 mile or less, unless the 1-mile display area has a diameter of 2.75 inches or larger.

vi. Automatic Dependent Surveillance -Broadcast (ADS-B)

vii. ADS-B OUT systems must be approved to TSO C154c or TSO-C166b. Aircraft operating outside of the

United States must be equipped with systems approved to TSO-C166b.

a. ADS-B IN systems must be TSO approved, use diversity antennas on top and bottom of the aircraft, receive both UAT and 1090ES, and be interfaced to a multifunction display (MFD) capable of displaying TIS-B traffic and FIS-B weather.

i. Autopilots

a. Autopilots shall be capable of operating the aircraft controls to maintain flight and maneuver it about the three axes.

b. Autopilots in ASM aircraft shall be certified for IFR approach procedures, couple to the navigation systems for vertical and horizontal operation, interface to the PICs flight director and HSI, and provide altitude preselect, automatic trim, and PIC electric trim controls.

ii. RADAR Altimeters: RADAR altimeters shall be approved, operate from zero to a minimum of 2000 feet AGL and provide the operator an adjustable cursor which enables an altitude low (decision height) annunciation. The altitude low annunciation shall be clearly identified, and in the PIC's primary field of view.

iii. Multi-Function Displays (MFD): MFDs shall be installed within view of the PIC and display GPS navigation information on a color moving map. TAS and weather datalink information shall be displayed on the MFD when these systems are required.

iv. Cockpit Voice Recorder (CVR): Cockpit voice recorders shall meet all applicable regulations for standard https://www.aff.gov/ https://www.aff.gov/ and transport category aircraft.

v. Dual USB Charging Ports: USB charging ports must be TSO approved, capable of providing at least 2 amps of power to each port simultaneously with an output voltage of 5 VDC and installed in a location convenient to the specified users.

vi. VHF-FM Programming Ports:DB-9 type D-subminiature connectors shall be installed in a location convenient to the SIC/observer. These shall be wired for RS232 serial communication between all required

VHF-FM radios and a laptop computer. Individual connectors or an FM select switch may be used. Pin 2 shall be data transmitted from the FM. Pin 3 shall be data received by the FM. Pin 5 shall be signal ground.

Compatible radio front panel connectors may be used to meet this requirement if serial adapter cables are provided with the aircraft. For example: TDFM 136A radios s/n FDA1200 and higher.

vii. Portable Electronic Device (PED) Tolerance

a. The aircraft must be certified as tolerant to portable electronic devices (PEDs), including transmitting PEDs, in accordance with RTCA/DO-307 for all phases of flight. This must be accomplished via an STC equivalent to Liberty Partners STC11071SC with configuration LP-S001-

B03 and include approval for wireless intercom adapters. An appropriate supplement must be incorporated into the aircraft flight manual.

b. The contractor must have documented procedures and training to clearly address:

1. PEDs approved for use on board the aircraft.

2. Situations when approved PEDs can and cannot be used.

3. How and when PEDs must be secured or stowed.

4. PED modes of operation that can and cannot be used.

5. How and when to inform passengers of the contractor’s PED policies and procedures.

6. How to manage scenarios such as suspected or confirmed electromagnetic interference, PED unit or battery smoke or fire, or other scenarios.

(4) Equipment for conducting aircraft Operational Load Monitoring (OLM).

a. Contractor shall instrument aircraft with a government reviewed and approved OLM system. This system must provide to the government required and specified parameters in Table 1 below. Aircraft being offered that do not have a government approved OLM system installed shall install an OLM system that outputs data in the ".cdf' file format.

b. The recorded data shall be submitted to the Forest Service Airworthiness Branch every 14 days while on contract.

c. The recorded OLM data shall be in a “.sie or ".cdf' file format. All values in ".sie" and ".cdf' files shall be in engineering units as listed in Table 1. The SIE and CDF files shall include column header descriptions as listed in

Table 1, Channel Description (including engineering units for the values in each column). Acceleration data shall be described as either incremental or total. There shall be only one flight per recorded file.

i. The file naming convention for each flight file shall be; "Aircraft N Number''_"date

(YYYYMMDD)"_timestamp in GMT (E.g. N34VJ_20140228_1456)

a. If the OLMS system is inoperable or malfunctioning the aircraft operator shall have the problem corrected in 10 business days. If the problem is not corrected, the aircraft will be made unavailable until the OLMS is operating and properly recording data.

b. The OLM system shall be installed and approved by one of the three following methods:

i. STC

ii. Approved for installation by an FAA From 8110-3 with all DER supporting engineering substantiation documentation attached.

iii. Field Approved on an FAA form 337 for installation with supporting FAA Form 8110- 3 and all DER supporting engineering substantiation documentation.

ii. The OLM system shall have an annual calibration prior to annual pre use inspection.

a. Aircraft shall be flown by the contractor in a typical mission profile.

b. Data shall be collected for this flight.

c. The contractor shall review the data to ensure all channels are recording data and that data is correct in accordance with this contract and the contractors OLM program.

d. The contractor shall notify the USFS Airworthiness Branch of the specific flight date and time for the calibration flight. The government will review this data to ensure it meets requirements.

iii. Manage an OLM System and Program:

a. Criteria: To properly monitor the ASM usage of a specific model aircraft, a complete instrumentation package and recording device are required. The following section details the minimum required parameters and instrumentation to be recorded at a minimum sample rate of

8Hz. Accelerations shall be recorded as close to the aircraft Center of Gravity as practicable, or correction algorithms may need to be validated and applied. Systems shall have functional and calibration flights recorded annually.

b. Continuous Monitoring OLM Requirements: These are minimum system requirements for all other aircraft of a particular model in ASM operation for continuous monitoring while in ASM service. The instrumentation and equipment utilized must include all mechanical components required to measure the flight parameters listed. The system shall have detailed installation instructions, drawings and instructions for continued airworthiness (ICAs). The ICAs will also include an installation validation plan for system and scheduled calibration check due annually.

The following are minimum required parameters to be recorded at 8 Hz.

iv. G Meter with audio tone prior to exceedance

a. Install a G meter (Digital, Analog, tape, or LED Light Bar) system in the instrument panel of the aircraft in the pilot’s primary field of view. Instrument panel locations shall be approved by the government prior to installation.

b. Vertical acceleration exceedance notification/annunciation.

c. Non resettable in flight

d. Requires maintenance action during exceedance inspection to reset.

e. The exceedance notification function may be integrated with the G meter display or be separate

f. Installation of the system shall be FAA approved through DER FAA Form 8110 or STC.

i. The system may interface with existing systems or be stand alone.

ii. Limitations and annunciation of near limit and exceeding the limit shall be adjustable by maintenance activity or software update.

Table 1 Continuous Monitoring OLM Minimum Channel List

Channel Description Number of

Channels

Units Sample Rate (Hz)

Record Rate (Hz)

1. Altitude (GPS) 1 Feet 4 Hz 8 Hz

2. Groundspeed (GPS) 1 Knots 4 Hz 8 Hz

3. Vertical Speed (GPS) 1 Feet per Minute 4 Hz 8 Hz

4. Heading (GPS) 1 Degrees 4 Hz 8 Hz

5. Date and Time in GMT (GPS) 1 yyyy/mm/dd GMT 4 Hz 8 Hz

6. Latitude (GPS) 1 Degrees 4 Hz 8 Hz

7. Longitude (GPS) 1 Degrees 4 Hz 8 Hz

8. Engine Start (one engine oil pressure) 1 Discrete 8 Hz 8 Hz

9. Pitot Pressure 1 Inches Hg 8 Hz 8 Hz

10. Static Pressure 1 Inches Hg 8 Hz 8 Hz

11. Outside Air Temperature 1 Degrees C 8 Hz 8 Hz

12. Altitude (Static Pressure) 1 Feet 8 Hz 8 Hz

13. Indicated Airspeed (must be derived from Pitot / Static differential)

Knots

8 Hz

14. Equivalent Airspeed 1 Knots 8 Hz 8 Hz

15. True Airspeed 1 Knots 8 Hz 8 Hz

16. Weight On Wheels 1 Discrete 8 Hz 8 Hz

17. Flap Position 1 Degrees 8 Hz 8 Hz

18. Speed Brake / Spoiler Position (If equipped)

Degrees

19. Normal Acceleration (Nz) 1 G Force 8 Hz 8 Hz

20. Longitudinal Acceleration (Nx) 1 G Force 8 Hz 8 Hz

21. Lateral Acceleration (Nv) 1 G Force 8 Hz 8 Hz

22. Pitch 1 Degrees 8 Hz 8 Hz

23. Pitch Rate 1 Degrees per Sec. 8 Hz 8 Hz

24. Roll 1 Degrees 8 Hz 8 Hz

25. Roll Rate 1 Degrees per Sec. 8 Hz 8 Hz

26. Yaw Rate 1 Degrees per Sec. 8 Hz 8 Hz

27. Vertical Accuracy (VDOP) 1 8 Hz 8 Hz

28. Horizontal Accuracy (HOOP) 1 8 Hz 8 Hz

29. Fuel Quantity (May be manually collected on Supplemental Data Sheet)

Lbs.

30. Aircraft Gross Weight ( May be manually collected on Supplemental Data Sheet)

Lbs.