Regen Dyno SOW_rev3 - 29JUL2024.docx

STATEMENT OF WORK (SOW)

AC Dynamometer System

1.0 GENERAL

The FAA requires an AC Dynamometer System for Aircraft Engine Testing.

1.1 Description of Services/Introduction

The contractor must provide equipment, software, user guide and manuals, installation and commissioning, safety and startup training.

1.2 Background

The FAA William J. Hughes Technical Center for Advanced Aerospace (WJHTCAA) located at the Atlantic City International Airport requires an AC Dynamometer System that can absorb rotational loads from aircraft engines up to 1000hp and 3500lb-ft of torque at engine speeds up to 3000RPM. The dynamometer must provide constant torque and constant power throughout a range of RPM. The system must have bi-directional capabilities with the installation in a regenerative configuration.

1.3 Objectives

This SOW outlines the requirements for an AC Dynamometer System for Aircraft Engine Testing.

1.4 Scope

The Contractor must deliver and provide installation of one AC Dynamometer System that meets the minimum specifications listed in Section 2, Minimum Specifications. Additionally, the Contractor must provide commissioning, safety and startup training, documentation, and provide a commercial 12-month warranty.

1.5 Period of Performance

The period of performance will be 6 months from date of award.

2.0 Minimum Specifications

The contractor must provide an AC Dynamometer System that meets the following requirements.

2.1 Performance Specs

2.2 Electrical Requirements

All electrical components must be packaged enclosed in a power distribution panel and must include thermal and electrical overload protection. The AC Dynamometer System must be operating on standard 480 volt 3-phase power. All electrical components and wiring must conform to National Electrical Manufacturers Association Standards. All wiring must be clearly labeled and identified with wires and terminals labeled to correspond to the electrical schematic.

The system must provide electrical and thermal overload protection for individual circuits and components.

The system must be installed in a regenerative configuration.

2.3 Cooling

The AC Dynamometer may be liquid or air-cooled. The facility in which the system will be installed, has a process water system with hookups at the installation location If the vendor proposes an air-cooled system, it must be self-contained as the FAA will not be providing blowers to remove heat from the system.

2.4 Interface

Must provide:

1. A matching driveshaft rated to 3500 ft lbs of torque.

2. Floor mounted driveshaft guard.

2.5 Available Space Dimensions

The available floor space for the AC Dynamometer, not including the driveshaft, is 5ft x 5ft.

Figure 1. Floorspace

2.6 Controls

AC Dynamometer System controls must be integrated into the FAA’s existing power amplification unit.

2.7 Software

All system software must comply with requirements specified within Department of Defense Instruction 8500.01, Cybersecurity and be compatible with Microsoft Windows 10 Professional.

3.0 Acceptance Test

The Dynamometer system must undergo acceptance testing according to Figure 2 below, where A, D, G will be below 3400 lb-ft and above 0 lb-ft. Additionally, B, E and H will be below 975 hp and above 0 hp. Finally, C, F, I will be below 2900 RPM and above 0 RPM. Exact values for A, B, C, D, E, F, G, H, I will be determined at the time of installation based on test asset availability.

Figure 2.: 6 Hour Acceptance Test Profile

4.0 Documentation

4.1 Operation Instruction Manual

Operator instruction manuals must be provided. The manuals must include wiring and plumbing schematics.

4.2 Maintenance Instruction Manual

Maintenance instruction manuals must be provided. The manuals must include wiring and plumbing schematics.

4.3 Spare Parts List

The contractor must provide a complete parts list for all systems and their sources.

4.4 Illustrated Parts Breakdown

The contractor must provide a complete illustrated parts breakdown for all systems.

4.5 Installation Drawings

Installation interconnection drawings must be furnished at the earliest possible time, but no later than 60 days after contract award to assist in facilities and installation planning. The contractor must provide procedures and system calibration requirements.

4.6 Calibration Manual

The contractor must provide calibration manuals.

4.7 Warranty

The Contractor must include a one (1) year commercial warranty effective the day of Full Operational Capability (FOC).

5.0 DELIVERY

5.1 Delivery and Installation

Delivery and installation must be provided by the contractor. Utility hookups for electrical, process water and process air will be provided by the FAA. Locations of these hookups will be finalized during the engineering phase of the project. Contractor must make appropriate connections to the provided hookups.

5.2 Packaging

All shipments must arrive in palletized packaging for ease of unloading at the location specified in Section 6.

5.3 Heavy Shipment

Any shipment exceeding four-thousand (4,000) pounds must be defined as a Heavy Shipment. Each Heavy Shipment must adhere to the following:

1. Contractor must notify the Government not less than one (1) week in advance of shipment.

2. Contractor must schedule the specific date and time of delivery.

3.Contractor must notify the Government immediately upon any deviation to the delivery schedule

4. Contractor must coordinate rigging.

6.0 Training

The Contractor must provide commissioning, safety, startup, and operation training. On-site training for approximately 10 Government personnel must be provided within 30 calendar days of installation.

7.0 Shipping Address

William J. Hughes FAA Technical Center Atlantic City International Airport NJ 08405 Building 211.

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