H125_purchase_AMD1specs_0001.docx

SECTION E – OFFEROR’S REPRESENTATIONS, CERTIFICATIONS AND OTHER STATEMENTS

SCHEDULE OF SUPPLIES

A1. ITEM REQUIREMENT

1. Aircraft Required: One light helicopter (Airbus H125) (equipped per section B)

Minimum Helicopter Requirements:

Seating: Five (5) insured passenger seats not including pilot, but including copilot seat in an aircraft, normally single-pilot operated.

Configuration: Left Hand (Left Seat) Pilot in Command

Landing gear: Skid-Type

Powerplant: Turbine engine

Certification: 14 CFR 27

Fuel System Crash Resistant (per 14 CFR 27.952)

Flight Data Cockpit imaging and flight data monitoring device

A2. ITEM PRICING / DELIVERY

One AS350B2 Helicopter.

SECTION A - REQUIREMENTS AND PRICES

FWS AS350 Helicopter Solicitation# 140D8022R0006 AMD 1

GENERAL REQUIREMENTS

B1 Scope of Contract

B1.1 This contract is for the purchase of one (1) new H125 (AS350-B3e) helicopter equipped as specified in Section B. The aircraft will be used by the U. S. Fish and Wildlife Service in support of wildland fire operations.

B2 Certifications

B2.1 The aircraft must have a Federal Aviation Administration (FAA) Standard Airworthiness certificate. The aircraft must be equipped in accordance with 14 CFR Parts 91.205 for visual flight rules (VFR) day and night operation. Installation of any equipment required by this contract must be FAA approved. Aircraft built from spare and surplus parts in accordance with FAA Advisory Circular 31-13 (4-5-73) and certified in accordance with 14 CFR 21.183(d)(1) are not acceptable.

B2.2 The helicopter must be certificated in accordance with 14 Code of Federal Regulations CFR Part 27.

B2.2.1 Materials and workmanship. The aircraft, component part or parts, accessories, and minimum equipment must be standard and must include all improvements in design and construction as shown in the manufacturer’s current literature and Type Certification Data Sheet for the model offered.

B2.3 The helicopter must have an FAA Standard Airworthiness certificate. The aircraft must have engineering and logistical support for continued airworthiness provided by the current type certificate holder. Installation of any equipment required by this contract must be FAA-approved.

B3 Order of Precedence (Specifications)

B3.1 In the event of inconsistencies within the technical specification, the following order will be used in such resolution: (1) typed provisions of these specifications; (2) DOI Office of Aviation Services (OAS)supplements and/or exhibits incorporated by reference; (3) 14 CFR incorporated by reference; (4) aircraft manufacturer's specifications; (5) other documents incorporated by reference.

B4 Reserved

EQUIPMENT REQUIREMENTS

B5 Condition of Equipment

The aircraft and all other required equipment must be new, operable, and free of damage. Aircraft systems and components must be free of leaks, except where specifically allowed by the manufacturer.

B5.1 The helicopter must have no history of major damage. Any minor repairs must be documented as having been performed with approved data.

B5.2 Temporary repairs to windows and windshields are unacceptable.

B5.3 Three color paint scheme. (See paint scheme exhibit to be provided)

B5.4 The helicopter must have current inspection items completed on airframe, engines, components, accessories, and instructions for continued airworthiness (ICA’s) on installed or offered equipment.

B5.5 The Government reserves the right to determine if the condition of the helicopter is acceptable.

B6 Equipment Requirements

In addition to the requirements of Section A and Section B2 through B5, the helicopter must be equipped with the following minimum equipment:

B6.1 Flight Instruments for low visibility flight conditions, including directional gyro, gyroscopic bank and pitch indicator, rate of turn indicator, and vertical speed indicator.

B6.2 One Digital Hour Meter (Part# 350A82-1613-xx) installed in a location visible by the pilot and front seat observer while seated. The meter must be wired in series with a switch on the collective control, and a switch activated by engine or transmission oil pressure or by equivalent means, to record flight time only.

B6.3 Free Air Temperature Gauge

B6.4 Fire Extinguisher

B6.5 Dual Controls (complete with throttle) (removable)

B6.6 Aircraft Floor Covers / Aermat Flooring (Part# 350-701814-01)

B6.7 Aircraft Seating Configuration (Left Hand PIC)

B6.7.1 Energy Attenuating Seats, Pilot & Copilot

B6.7.2 Fold Up Utility Seating in aft cabin

B6.8 One set of Individual Lap Belts for each installed seat.

B6.8.1 Double Strap Shoulder Harness with automatic or manual locking inertia reel for each front seat occupant. Shoulder straps and lap belts must fasten with one single-point metal-to-metal, quick-release mechanism.

B6.8.2 Shoulder Harnesses (either single-strap or double-strap) for each aft cabin occupant. Shoulder harness straps and lap belts must fasten with a single-point, metal-to-metal, quick-release mechanism.

B6.9 High-kid-type Landing Gear

B6.9.1 Full Length Carbide Skid Shoes

B6.10 Personnel Access Steps

B6.10.1 Short Cabin Entrance Steps, LH and RH (Part# 350-500194/204)

B6.10.2 Cowling Maintenance Steps, LH and RH (Part# 350-200094/104)

B6.10.3 Rear Maintenance Steps (Part# 350-500604)

B6.11 Cabin Door Configuration

B6.11.1 LH and RH Short High Visibility Doors (SAP# 1928674)

B6.11.2 Aft Cabin LH and RH Sliding Doors

B6.12 Baggage Compartment within the aircraft fuselage

B6.12.1 Aft Baggage Door Foreword Opening Mod (Part# 350-201014)

B6.12.2 Aft Baggage Extender

B6.13 Environmental/Ventilation system(s)

B6.13.1 Cabin heater, Window defogger, and Demisting Circuit.

B6.13.2 RSG Cabin Air Conditioning System (Part# 350-00-011-HP)

B6.14 Aircraft Lighting (VFR Day and Night)

B6.14.1 LED Fin Anti-Collision Light

B6.14.2 LED Position Lights

B6.14.3 LED Landing and Taxi Lights (Part # 350A82-1650-xx)

B6.14.4 Pulse Light Installation for Landing and Taxi Lights

B6.14.5 Belly Mounted Anti-Collision Light LED

B6.15 Cargo Swing with Onboard Keeperless Cargo Hook. Capabilities Extended Cargo Swing (Part# 06-27009-00-CI) Bambi Bucket/Remote Cargo Hook Controls

B6.15.1 Electrical Controller for 50Amp Long Line Release (Part# 350-900564)

B6.15.2 Part number MS 3101E-24-11S, Nine-Pin Connector, for use as the power source for a helitorch or remote cargo hook. Pin D must be airframe ground. Pin E must be switched 28VDC, protected by a manually operable, 50-amp circuit breaker. The water bucket/tank open switch must also activate this circuit.

B6.15.2.1 This connector must have Multiple Circuit Capacity sufficient to provide power and control for Contractor-furnished equipment. The longline remote hook, fixed tank, or water bucket must be wired through this connector. A list of water buckets with required pin wiring can be found in the FS/OAS Drawing A16 Exhibit 2.

B6.15.3 A Lanyard to support the connector and mounted within 12 inches of the cargo hook.

B6.16 A Water/Retardant Bucket/Remote Hook Operating Switch clearly marked for "open" and "closed," and mounted on the collective control to avoid confusion with the cargo hook release. The switch must be of a different design and must be mounted so as to not easily be confused with the RPM Control [Beep] switch.

B6.17 Onboard Load Weighing System. Cockpit-mounted External Load Indicator with readout of weight carried on the cargo hook.

B6.18 A Convex Mirror for the pilot to observe the sling load. Cargo Mirror LH.

B6.19 An Accessory Power Source consisting of an MS 3112E-12-3S three-pin connector, accessible in the cabin. Pin B must be airframe ground; pin A must be +28VDC (for 28-volt aircraft); and pin C must be +14VDC (for 14-volt aircraft). The circuit must be protected by a 5-amp circuit protection.

B6.20 Crash Resistant Fuel System

B6.20.1 Locking Cap(s) on all fuel inlet ports

B6.21 Multi-Bloc Center Console Installation (Part# 350A73-2023-01)

B6.22 Engine Inlet Barrier Filter (AFS SAP# 1938779)

B6.23 Airframe Fuel Filter (Part# 350-600044) *If approved*

B6.24 RG350 Concord Lead Acid Battery (Part# 350A82-1585-01)

B6.25 BLR Fast Fin Kit (SAP# 2043528)

B6.26 Gross Weight Increase Kit (5225 lbs) – Dual Hydraulics

B6.27 Wire strike protection system (mechanical).

B6.28 High Visibility Markings on main rotor blades as specified by the Acceptable Paint Schemes Exhibit 1.

B6.29 Main Rotor Brake

B6.30 Main Rotor Blade Tie Down Kit

B6.31 Ground-Handling Wheels

B7 Avionics Requirements

B7.1 General

B7.1.1 The Contractor must provide, install, and maintain the following systems in accordance with the manufacturer's specifications and the installation and maintenance standards of Section B7. Detailed avionics systems performance requirements are listed in Avionics Operational Test Standards (copies available upon request from OAS Avionics, or the most recent list may be found online at: https://www.nifc.gov/NIICD/docs/avionics/FSOAS_A24F.pdf.

B7.2 Avionics Installation and Maintenance Standards

B7.2.1 Strict adherence to the recommendations in the following FAA Advisory Circulars is required: AC 43.131B Chapter 11, "Aircraft Electrical Systems," and Chapter 12, "Aircraft Avionics Systems”; AC 43.132B Chapter 1, "Structural Data," Chapter 2, "Communication, Navigation, and Emergency Locator Transmitter System Installations," and Chapter 3, "Antenna Installation."

B7.2.2 All avionics systems requiring an antenna must be installed with a properly matched, aircraft-certified antenna, unless otherwise specified. Antennas must be polarized as required by the avionics system and must have a voltage standing wave ratio (VSWR) of 3.0 to 1 or better.

B7.2.3 Transmitters shall not open squelch on, or interfere with, other AM or FM transceivers in the aircraft which are monitoring different frequencies. So-called “Transmit Interlock” functions shall not be used with communication transceivers.

B7.3 Communications Systems

B7.3.1 One automatic-fixed Emergency Locator Transmitter (ELT), certified under TSO-C126 (or newer) which must be installed in a conspicuous or marked location, and meet the same requirements as those detailed for airplanes in 14 CFR 91.207 (excluding section f). ELT antennas must be mounted externally to the aircraft unless installed in a location approved by the aircraft manufacturer.

B7.3.2 Two panel-mounted VHF-AM (VHF-1, VHF-2) aeronautical transceivers, each with a minimum of 760 channels covering 118.000 to 136.975 MHz. The transceivers must have channels selectable in no greater than 25 kHz increments and a minimum of 5 watts carrier output power. The transceivers’ operational controls must be mounted so they are readily visible and accessible to the pilot. VHF-1 must be an integral part of the combined COM/NAV/GPS unit as described in B7.4.1 below, and VHF-2 must be an integral part of the combined COM/NAV/GPS unit as described in B7.4.2 below.

B7.3.3 Two P25-compliant VHF-FM transceivers. Each transceiver (FM-1, FM-2), must provide selection of narrowband analog (12.5 kHz) or narrowband digital (12.5kHz) operation on each of a minimum of 100 channels. Each transceivers’ operational controls must be located and arranged so that the pilot and observer/copilot when seated, have full and unrestricted movement of each control without interference from clothing, the cockpit structure, or the flight controls.

B7.3.3.1 Each transceiver’s operational frequency range must include the band of 136.0000 MHz to 173.9975 MHz. The operator(s) must be able to program any usable channels within that band, along with any required CTCSS tones, National Access Codes (NAC’s), or Talk Group ID’s (TGID’s), while in flight. Each transceiver must also incorporate a separate, programmable GUARD receiver, with accompanying GUARD transmit capability. Unless instructed by the Government for use on a specific project, all frequencies programmed for use under this Contract must be in the narrowband analog mode.

B7.3.3.2 Carrier output power for each transceiver must be 10 watts nominal value (original design specification). Each transceiver must be capable of displaying receiver and transmitter operating frequency, alpha-numeric channel labels, and must provide both receiver and transmitter activation indicators for MAIN and GUARD. Simultaneous monitoring of both MAIN and GUARD receivers is required. Scanning of the GUARD frequency is not acceptable.

B7.3.3.3 The following VHF-FM aeronautical transceivers are known to meet the above requirements:

Technisonics: TDFM-136, TDFM-136A, TDFM-136/NV, TDFM-136A/NV, TDFM-136B, TDFM-136B/NV.

B7.3.4 Provisions for auxiliary VHF-FM (AUX-FM) portable radio:

B7.3.4.1 Interface for installing and properly operating an auxiliary VHF-FM portable radio through the aircraft's audio control system(s). The interface must consist of the appropriate wiring from the audio control system, terminated in an ITT/Cannon type MS3112E1210S 10-pin connector conveniently located for use by the observer/copilot, and utilizing the contact assignments as specified by drawing FS/OAS A-17 in Exhibit 3.

B7.3.4.2 One weatherproof, external, broadband antenna covering the 150174 MHz band, with associated RG58A/U (or equivalent) coaxial cable and connector, terminated in a bulkhead-mounted, female BNC connector (type UG-290A), conveniently located for use by the observer/copilot adjacent to the above 10-pin connector (Comant model CI177 or equal).

B7.3.4.3 Mounting facilities for securely installing the auxiliary VHF-FM portable radio in the cockpit in accordance with the FAA AC 43.13-2B specifications. Locate and arrange the mounting facilities so that a seated observer/copilot has full and unrestricted movement of the radio's controls, without interference from the 18-inch adapter cable, clothing, cockpit structure, or flight controls.

B7.3.4.4 Positive-polarity microphone excitation voltage provided to the AUX-FM system from the aircraft DC power system through a suitable resistor network. A blocking capacitor must be provided to prevent the portable radio microphone excitation voltage from entering the system. Sidetone for the AUX-FM must also be provided (NAT model AA34-300, Premier model PA-34, or equivalent).

B7.3.5 One aviation SiriusXM receiver for XM WX Satellite Weather (Garmin GDL-69 or equal).

B7.4 Navigational Systems

B7.4.1 One permanently installed, panel-mounted combined COM/NAV/GPS (global positioning system) (GPS-1) utilizing an approved, fixed external aircraft antenna and powered by the aircraft electrical system. In addition to a VHF-1 transceiver (as described in B7.3.2 above), the system must also include a NAV (with VOR/LOC/Glideslope) receiver, and color Multi-Function Display (MFD) with a minimum diagonal measurement of 6.9 inches. The GPS must utilize the WGS-84 datum and reference latitude and longitude coordinates in the degrees/minutes/decimal minutes (DM) mode for aircraft positioning. (Garmin GTN-750 or equal)

B7.4.2 One permanently installed, panel-mounted combined COM/NAV/GPS (global positioning system) (GPS-2) utilizing an approved, fixed external aircraft antenna and powered by the aircraft electrical system. In addition to a VHF-1 transceiver (as described in B7.3.2 above), the system must also include a NAV (with VOR/LOC/Glideslope) receiver, and color Multi-Function Display (MFD) with a minimum diagonal measurement of 4.9 inches. The GPS must utilize the WGS-84 datum and reference latitude and longitude coordinates in the degrees/minutes/decimal minutes (DM) mode for aircraft positioning. (Garmin GTN-650 or equal).

B7.4.3 One advanced connectivity and avionics integration system, capable of streaming traffic, weather, and GPS information from the combined COM/NV/GPS systems above to select mobile and portable devices (Garmin Flight Stream 510 or equal).

B7.5 Audio Systems

B7.5.1 Two separate audio control systems (which may be combined in a single unit) for the pilot and observer/co-pilot to select receiver audio outputs and transmitter microphone/push to talk (PTT) audio inputs for a minimum of six (6) installed radios, plus public address (PA) systems. Each system must also allow the pilot and observer/copilot to independently adjust both the intercommunications system (ICS) and the receiver audio output levels.

B7.5.1.1 Transmitter selection and operation. Separate transmitter selection controls must be provided for both the pilot’s and observer/copilot’s microphone/PTT inputs. The system must be configured so the pilot and observer/copilot may each simultaneously select and utilize a different transmitter (or PA system when installed) via their respective microphone/PTT. Whenever a transmitter is selected, the companion receiver audio must automatically be selected for the corresponding earphone. Transmitter sidetone audio must be provided for the user as well as for cross-monitoring via the corresponding receiver selection switch on the other audio control system.

B7.5.1.1.1 The two aft cabin exit (outboard) positions must be equipped to transmit on the radio(s). Whenever a radio (or PA, when so equipped) microphone input is selected at the observer/copilot's audio control panel, the aft cabin passengers' radio microphone inputs must automatically be connected to the same radio, and they must then be capable of transmitting on that radio via their respective radio transmit PTT switches.

B7.5.1.2 Receiver selection and operation. Separate controls must be provided for both pilot and observer/copilot to select audio from one or any combination of available receivers. The ICS-equipped aft passenger positions must monitor the receiver(s) as selected by the observer/copilot. The receiver audio output must be free of excessive distortion, hum, noise, and crosstalk, and must be amplified sufficiently to facilitate ease of use in a noisy cockpit/cabin environment.

B7.5.1.3 The audio system(s) controls must be located and arranged so that both the pilot and observer/copilot, when seated, have full movement of their respective controls without interference from their clothing, the cockpit structure, or the flight controls. Labeling and marking of controls must be clear, understandable, legible, and permanent. Electronic label maker marking is acceptable.

B7.5.2 An ICS for the pilot, observer/copilot, and all aft cabin positions. ICS audio must mix with, but not mute, selected receiver audio. An ICS audio level control must be provided for each position above. Adjustment of the ICS audio level at any position must not affect the level at any other position. A "hot mic" capability, controlled via an activation switch or voice activation (VOX), must be provided for the pilot and copilot/observer positions. ICS sidetone audio must be provided for the earphones corresponding with the microphone in use. The ICS audio output must be free of excessive distortion, hum, noise, and crosstalk and must be amplified sufficiently to facilitate ease of use in a noisy cockpit/cabin environment.

B7.5.3 Earphones, microphones, PTT’s, and jacks designed for operation with 600-ohm earphones and carbon-equivalent, noise-canceling boom type microphones (Gentex electret type model 50602, military dynamic type M87/AIC with type CE100 TR preamplifier, or equivalent) with U174/U (single/male) type connector plug. The pilot position only may be configured for low impedance (dynamic) operation.

B7.5.3.1 A single U-92A/U type connector jack, which will accept a U-174/U type plug and provide the ICS and radio functions as specified above, must be furnished at each required station.

B7.5.3.2 Separate PTT switches for radio transmitter and ICS microphone operation must be provided at the pilot, observer/copilot, and any other positions required above to be furnished with both radio transmitter and ICS operation. The pilot's PTT switches must be mounted on the cyclic control. The observer/copilot's and any other required position’s PTT switches must be mounted on the cord to the earphone/microphone connector. The aft cabin positions must be furnished with cord-mounted ICS PTT switches.

B7.6 Other Avionics

B7.6.1 One air traffic control (ATC) transponder and altitude reporting system with integrated ADS-B IN & Out, meeting the requirements of 14 CFR Part 91.215 (a) and (b), and 14 CFR 91.225. (Garmin GTX-345R or equal, integrated to the G5000TXi and GTN-750).

B7.6.2 One minimum seven-inch, full color touchscreen flight display (Garmin G500 TXi or equal), equipped with FlightView Electronic Flight Instrument System (EFIS) and synthetic vision.

B7.6.3 One Electronic Standby Indicator system (L3Harris ESI-500 p/n 350A82-1645-xx or equal).

B7.6.4 One ADS-B enhanced Traffic Advisory System (TAS), capable of tracking up to 45 targets at distances of 22nm. (Garmin GTS-800 or equal).

B7.6.5 One Flight Data Monitoring (FDM) system, capable of recording cockpit images, systems audio, GPS data, pitch, roll, yaw, G forces, and rates of rotation. (Appaero Vision 1000 or equal).

B7.6.6 Each aircraft must be equipped to meet the Radar Altimeter requirements of 14 CFR 135.160, where applicable. (Garmin GRA-5500 or equal).

B7.6.7 Electronic Flight Bag (EFB) charging capability. The aircraft must be furnished with two conveniently located, circuit breaker-protected ports in the cockpit for charging FAA-approved Electronic Flight Bags (EFB). The charging ports must consist powered standard USB-type connectors.

B7.6.8 Three axis auto-pilot Garmin GFC 600H or equivalent.

AIRCRAFT MAINTENANCE REQUIREMENTS

B8 Maintenance and Record Keeping Requirements

B8.1 Manuals/Records.

The Contractor must ensure that all maintenance performed on the aircraft before delivery to the Government is recorded in the affected aircraft maintenance record in accordance with 14 CFR (reference 14 CFR 43.9, 43.11, and 91.417).

B8.1.1 The airframe and engine logbooks must be complete and contain all maintenance records since date of manufacture, including the manufacturer’s approval for return to service. A complete airworthiness limitations schedule and inspections and component overhaul schedule. This schedule must indicate aircraft total time, aircraft total time at installation/compliance, life limit of component/inspection, and time remaining.

B8.1.2 Maintenance, operating, and parts manuals for the helicopter, engine, and equipment must be furnished to the Government at time of delivery. All flight manual supplements applicable to the aircraft as delivered and optional configurations must be provided. The information provided must include instructions for continued airworthiness for all equipment and alterations accomplished to comply with this agreement.

B8.1.3 All installations must be FAA approved and documented in accordance with 14 CFR.

B8.1.4 Installation drawings and any equipment warranty information must be supplied covering the installation of avionics and all other installed equipment.

B9 Airworthiness Directives (AD’s) and Service Bulletins

B9.1 All applicable manufacturers' service bulletins and Federal Aviation Administration Airworthiness Directives must be complied with prior to delivery date. A list of FAA ADs and manufacturers' mandatory service bulletins on the make and model of aircraft offered will be made available. The list must record whether applicable or not and, if applicable, the date and airframe total time at compliance, method of compliance, next compliance due date if recurring, and authorized signature of maintenance personnel with their certificate number. The list will be similar to that shown in Advisory Circular AC 439C.

B10 Weight and Balance

B10.1 The aircraft must be delivered with a current weight and balance and equipment list with all installed equipment. Calculations showing equipment changes are not acceptable.

B10.2 The weight and balance must be determined by actual weighing of the aircraft. Scale readings must be recorded on the weight and balance record. Signature of the person verifying the accuracy of the weight and balance record is required.

B10.3 The aircraft must be weighed on scales that have been certified as accurate within the past 12 calendar months. Any accredited weights and measures laboratory may serve as the certifying agency. The weight and balance record must include the make, model, serial number, and calibration date of the scales used to weigh the aircraft.

B10.4 The equipment list must identify all equipment installed in the aircraft at the time of weighing. Each page of the equipment list must identify the specific aircraft by its serial and registration numbers and must be dated to indicate the date of weighing.

B10.4.1 Items that may be easily removed or installed for aircraft configuration changes (seats, doors, radios, cargo hook, baskets, special mission equipment, etc.) must be listed and include the name, weight, and arm of each item.

SECTION B – TECHICAL SPECIFICATIONS

EXHIBITS

1. Acceptable Paint Schemes

2. Drawing FS/OAS A-16

3. Drawing FS/OAS A-17

4. Aircraft Paint

EXHIBIT 1

ACCEPTABLE PAINT SCHEMES

1. Starting at the blade tip, paint the first 1/6 of the blade length with gloss white. Paint the second 1/6 of the blade length with yellow or orange. Paint the third 1/6 of the blade length with gloss white. Paint the next 1/3 of the blade length with yellow or orange. Paint the remaining 1/6 of the blade length with gloss white.

2. One black and one white blade (two-bladed rotor systems).

3. Paint schemes previously approved under a U.S. Forest Service or Department of the Interior, ICB, Office of Aviation Services contract.

4. High visibility paint schemes and color variations specified by manufacturer in a service bulletin, instruction, or other manufacturer-published document or text.

5.

EXHIBIT 2

DRAWING FS/OAS A-16

Accessory Connector Pin Assignments

EXHIBIT 3

DRAWING FS/OAS A-17

Auxiliary FM Radio InterfaceAUXILIARY VHF-FM RADIO INTERFACE

DRAWING FS/OAS A-17

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