DetailSpec.pdf

DETAIL SPECIFICATION

FOR THE

U.S. AIR FORCE

TH-1H

TRAINING HELICOPTER

REVISION B

11 March 2010

Prepared for:

Warner Robins Air Logistics Center (WR-ALC)

573rd Aircraft Sustainment Squadron (573 ACSS)/Huey Flight 235 Byron Street, Suite 19A

Robins AFB, GA 31098-1670

Prepared by:

L-3 TCS, Inc.

324 Corder Road Warner Robins, GA 31088-3606

Under Subcontract to:

Lockheed Martin Integrated Systems 645 Tallulah Trail

Warner Robins, GA 31088

TCS Document No. 8306-600-1900 Contract No. F09603-01-D-0207-0098

CDRL A005

TH-1H DETAIL SPECIFICATION

F09603-01-D-0207-0098

8306-600-1900 REV. B, 11 March 2010

REVISION HISTORY PAGE

Revision Date Justification for Change Revision By

Draft 25 March 2005 Draft Release Dane H. Boss

Basic 30 January 2006 Update format in accordance Dane H. Boss with Government comments

A 23 March 2007 Update for Upgraded TH-1H Dane H. Boss Intercommunication System (ICS)

B 11 March 2010 Update for Main Rotor Brake Joseph R. Stanley i

TABLE OF CONTENTS

1.0 SCOPE

1.1 PURPOSE

1.2 BACKGROUND

1.3 SYSTEM DESCRIPTION

2.0 APPLICABLE DOCUMENTS

2.1 GENERAL

2.2 GOVERNMENT DOCUMENTS

2.2.1 Drawings

2.2.2 Technical Manuals (TMs)

2.2.3 Technical Orders (T.O.s)

2.2.4 Military Standards

2.2.5 Military Specifications

2.2.6 Military Handbooks

2.2.7 Technical Standard Orders (TSOs)

2.3 COMMERCIAL DOCUMENTS

2.3.1 Bell Helicopter Documents

2.3.2 Commercial Standards

3.0 REQUIREMENTS

3.1 CHARACTERISTICS

3.1.1 Three-view Drawing

3.1.2 Performance

3.2 GENERAL

3.2.1 General Interior Arrangement

3.3 AERODYNAMICS

3.4 STRUCTURAL DESIGN CRITERIA

3.4.1 Limit Flight Load Factors

3.4.2 Ultimate Ground Load Factors

3.4.3 Limit Diving Speed

3.4.4 Ditching Criteria

3.4.5 Flutter Characteristics

3.4.6 Mechanical Instability and Flywheel Type Response

3.4.7 Rotor Induced Vibration

3.4.8 Main Rotor Speed

3.4.9 Speed, Design Maximum

3.5 WING GROUP

3.6 MAIN ROTOR GROUP

3.7 TAIL ROTOR GROUP

3.8 TAIL GROUP

3.9 BODY GROUP

3.10 ALIGHTING GEAR

ii

3.11 ALIGHTING GEAR (WATER TYPE)

3.12 SURFACE CONTROL SYSTEM

3.13 ENGINE SECTION

3.14 PROPULSION

3.15 TRANSMISSION SYSTEM

3.16 AUXILIARY POWER PLANT

3.17 INSTRUMENTS AND NAVIGATION EQUIPMENT

3.17.1 Instruments

3.17.2 Navigation Equipment

3.18 HYDRAULICS

3.19 ELECTRICAL SYSTEM

3.19.1 Description

3.19.2 Electrical Power Supply

3.19.3 Electrical Power Conversion

3.19.4 Equipment Installation

3.19.5 Wiring

3.19.6 Bonding and Shielding

3.19.7 Controls

3.19.8 Lighting

3.19.9 Ignition and Starting System

3.19.10 Receptacles

3.19.11 Indicators

3.19.12 Electric Drives

3.19.13 Relays

3.19.14 Booster Coil

3.19.15 Electromagnetic Interference (EMI)

3.20 AVIONICS

3.20.1 Communications

3.20.2 Navigation

3.20.3 Surveillance

3.20.4 Emergency Locator Transmitter (ELT)

3.20.5 Avionics Installation

3.21 ARMANENT

3.22 FURNISHINGS AND EQUIPMENT

3.22.1 Accommodations For Personnel

3.22.2 Miscellaneous Equipment

3.22.3 Furnishings

3.22.4 Emergency Equipment

3.22.5 Oxygen Equipment

3.22.6 Emergency Rescue Equipment

3.22.7 Rescue Hoist

3.23 AIR CONDITIONING AND ANTI-ICING EQUIPMENT

3.24 PHOTOGRAPHIC

3.25 AUXILIARY GEAR

iii

3.26 SPECIAL EQUIPMENT

3.27 KITS OBTAINED FROM CONTRACTOR

4.0 QUALITY ASSURANCE PROVISIONS

4.1 GENERAL VERIFICATION

4.2 ELECTRICAL LOAD ANALYSIS

4.3 WEIGHT AND BALANCE ANALYSIS

4.4 STRESS ANALYSIS

4.5 EMI/EMC VERIFICATION

4.6 AERODYNAMIC ANALYSIS

4.7 HUMAN FACTORS ANALYSIS

4.8 SYSTEM SAFETY ANALYSIS

4.9 GROUND TESTING

4.10 FLIGHT TESTING

5.0 PREPARATION FOR DELIVERY

6.0 NOTES

6.1 AIRWORTHINESS

6.2 SUPPORTABILITY

iv

LIST OF FIGURES

Figure 1 TH-1H Three-View Drawing Figure 2 Instrument Panel Configuration Figure 3 MFD EFIS Display Configuration Figure 4 MFD Reversionary Display Configuration Figure 5 MFD Bezel Configuration Figure 6 MFD EICAS Display Configuration Figure 7 Electrical Power System Architecture

LIST OF TABLES

Table 1 TH-1H Performance Requirements Table 2 MFD EFIS Display Parameters Table 3 MFD Bezel Controls Table 4 AHRS Components Table 5 ADC System Components Table 6 EICAS Display Parameters Table 7 Standby Instruments Table 8 EDCU Shielded Aircraft Circuits Table 9 VHF-FM System Components Table 10 VHF-AM System Components Table 11 UHF-AM System Components Table 12 ICS Components Table 13 ICS Switch Positions Table 14 VOR/ILS Components Table 15 ADF System Components Table 16 TACAN System Components Table 17 GPS Components Table 18 RADALT System Components Table 19 Transponder System Components Table 20 ELT System Components Table 21 Supportability Requirements

1.0 SCOPE

1.1 PURPOSE: This Detail Specification defines the required TH-1H system installations, capabilities, configuration, parts, system limitations, and level of integration with existing UH-1H/V aircraft systems.

1.2 BACKGROUND: The U.S. Air Force TH-1H helicopter is a modified U.S. Army UH-1H/V Huey single-engine utility helicopter acquired and operated by the Air Force Air Education Training Command (AETC). The Air Force TH-1H helicopter is not programmed to be deployed, and is used for undergraduate helicopter pilot training at Ft Rucker, AL. The AETC TH-1H students will graduate and fly the Air Force H-1, H-60, H-53, V-22 and the future Personnel Recovery Vehicle (PRV). The V-22 and PRV aircraft have 4-5 vertical multifunction display (MFD) cockpits, making the glass cockpit a baseline requirement for the TH-1H.

1.3 SYSTEM DESCRIPTION: The Air Force TH-1H upgrade consists of the commercial Bell Helicopter Textron, Inc. (BHTI), UH-1H-II (Huey II) kit, with the Honeywell T53-L-703 commercial engine upgrade, and the Bell 212 nose installation; a communications (COMM) and navigation (NAV) systems avionics upgrade; an electronic MFD glass cockpit; an emergency locator transmitter (ELT); and crashworthy pilot, copilot and center observer (jump) seat installations.

2.0 APPLICABLE DOCUMENTS

2.1 GENERAL: Unless otherwise specified, the following documents of the issue and date shown form a part of this specification to the extent specified herein.

2.2 GOVERNMENT DOCUMENTS

AC 29-2C Certification of Transport Category Rotorcraft, Advisory Circular, Federal Aviation Administration, Change 1, 12 February 2003

DMWR 55-1520-210 Aircraft Depot Maintenance Work Requirement, UH-1H/V Helicopters, US Army Aviation and Troop Command, Change 11, 31 July 1984

DOT/FAA/AR-MMPDS-01 Metallic Materials Properties Development and Standardization (MMPDS), Scientific Report

FA8530-05-R-60029 Performance Work Specification (PWS) For The Upgrade Modification and Modification Preparation of the UH-1H/V, 8 December 2004

FD2060-05-60029 Statement of Objectives (SOO) For The Upgrade Modification and Modification Preparation of the UH-1H/V, Revision 3, 6 December 2004

JSSG-2010-7 Crew Systems Crash Protection Handbook, Department of Defense Joint Service Specification Guide

2.2.1 Drawings

3H1000 U.S. Air Force TH-1H, CAGE 0F5W6

9579776 Air Force Drawing Requirements, CAGE 98752

9579777 Air Force Drawing Requirements, CAGE 98752

2.2.2 Technical Manuals (TMs)

TM 11-1520-210-20P Technical Manual, Organizational Maintenance Repair Parts and Special Tools List For Electronic Equipment Configurations Army Models UH-1H/V Helicopters, Headquarters Department Of The Army, 17 May 1985, Change 1, 15 August 1991

TM 11-1520-210-23 Technical Manual, Unit and Intermediate Maintenance Manual, Electronic Equipment Configurations, Army Models UH-1H/V Helicopters, Headquarters Department Of The Army, 1 July 1996, Change 1, 15 January 1999

TM 11-1520-210-34P Technical Manual, Direct Support and General Support Maintenance Repair Parts and Special Tools List For Electronic Equipment Configurations Army Models UH-1H/V Helicopters, Headquarters Department Of The Army, 17 May 1985, Change 1, 15 August 1991

TM 55-1520-210-10 Operator’s Manual Army Model UH-1H/V Helicopters, Headquarters Department Of The Army, 15 February 1998, Change 19, 31 December 2002

TM 55-1520-210-23-1 Technical Manual, Aviation Unit and Intermediate Maintenance Instructions, Army Models UH-1H/V Helicopters, Headquarters Department Of The Army, 30 September 1987, Change 42, 14 April 2003

TM 55-1520-210-23-2 Technical Manual, Aviation Unit and Intermediate Maintenance Instructions, Army Models UH-1H/V Helicopters, Headquarters Department Of The Army, 30 September 1987, Change 15, 30 May 2003

TM 55-1520-210-23-3 Technical Manual, Aviation Unit and Intermediate Maintenance Instructions, Army Models UH-1H/V Helicopters, Headquarters Department Of The Army, 30 September 1987, Change 9, 21 April 2003

TM 55-1520-210-23P-1 Technical Manual, Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List For Helicopter, Utility – Tactical Transport UH-1H/V, Headquarters Department Of The Army, 27 February 1981, Change 30, 24 May 2002

TM 55-1520-210-23P-2 Technical Manual, Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List For Helicopter, Utility – Tactical Transport UH-1H/V, Headquarters Department Of The Army, 27 February 1981, Change 18, 13 November 2001

TM 55-1520-210-23P-3 Technical Manual, Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List For Helicopter, Utility – Tactical Transport UH-1H/V, Headquarters Department Of The Army, 15 March 1988, Change 4, 23 November 2001

TM 55-1520-210-BD Technical Manual, Operators, Aviation Unit, and Aviation Intermediate Maintenance Battlefield Damage Assessment and Repair For Helicopter, Utility, UH-1H/V, Headquarters Department Of The Army, 19 February 1991, Change 1, 2 September 1994

2.2.3 Technical Orders (T.O.s)

TO 1-1A-14 Aircraft Electric and Electronic Wiring, Installation and Repair Practices, Technical Manual, 1 September 2004

TO 1-1A-14-1 Aircraft Electric and Electronic Wiring, Installation Practices, Supplemental Technical Manual, 9 September 2004

TO 1-1B-50 Weight and Balance, Basic Technical Order For USAF Aircraft, Technical Manual, 1 March 2005

2.2.4 Military Standards

MIL-STD-130L Identification Marking of U.S. Military Property

MIL-STD-411F Aircrew Station Alerting Systems

MIL-STD-464A Electromagnetic Environmental Effects, Requirements For Systems

MIL-STD-810F Environmental Engineering Considerations and Laboratory Tests, Test Method Standard For

MIL-STD-882D System Safety

MIL-STD-961E Defense and Program-Unique Specifications Format and Content

MIL-STD-1472F Human Engineering

MIL-STD-3009 Lighting, Aircraft, Night Vision Imaging System (NVIS) Compatible

2.2.5 Military Specifications

MIL-C-5541E Chemical Conversion Coatings on Aluminum and Aluminum Alloys

MIL-C-6499E Clock, Aircraft, Mechanical, Type A-13A

MIL-E-7016F Electric Load and Power Source Capacity

MIL-PRF-23377H Primer Coatings: Epoxy, High-Solids

2.2.6 Military Handbooks

MIL-HDBK-514 Operational Safety, Suitability, & Effectiveness For The Aeronautical Enterprise

MIL-HDBK-516A Airworthiness Certification Criteria

MIL-HDBK-46855A Human Engineering Program Process and Procedures

2.2.7 Technical Standard Orders (TSOs)

TSO-C2d Airspeed Instruments

TSO-C3d Turn and Slip Instrument

TSO-C4c Bank and Pitch Instruments

TSO-C5e Direction Instrument, Non-magnetic (Gyroscopically Stabilized)

TSO-C6d Direction Instrument, Magnetic (Gyroscopically Stabilized)

TSO-C8d Vertical Velocity Instruments (Rate-of-Climb)

TSO-C10b Altimeter, Pressure Actuated, Sensitive Type

TSO-C34e ILS Glide Slope Receiving Equipment Operating within the Radio Frequency Range of 328.6-335.4 Megahertz (MHz)

TSO-C35d Airborne Radio Marker Receiving Equipment

TSO-C36e Airborne ILS Localizer Receiving Equipment Operating within the Radio Frequency Range of 108-112 Megahertz (MHz)

TSO-C40c VOR Receiving Equipment Operating within the Radio Frequency Range of 108-117.95 Megahertz (MHz)

TSO-C41d Airborne Automatic Direction Finding (ADF) Equipment

TSO-C50c Audio Selector Panels and Amplifiers

TSO-C66c Distance Measuring Equipment (DME) Operating within the Radio Frequency Range of 960-1215 Megahertz

TSO-C71 Airborne Static Electrical Power Converter

TSO-C73 Static Electrical Power Inverter

TSO-C87 Airborne Low-Range Radio Altimeter

TSO-C106 Air Data Computer

TSO-C112 Air Traffic Control Radar Beacon System/Mode Select (ATCRBS/Mode S) Airborne Equipment

TSO-C113 Airborne Multipurpose Electronic Displays

TSO-C126 406 MHz Emergency Locator Transmitter

TSO-C127a Rotorcraft, Transport Airplane, and Normal And Utility Airplane Seating Systems

TSO-C129a Airborne Supplemental Navigation Equipment Using Global Positioning System (GPS)

2.3 COMMERCIAL DOCUMENTS

ES2562 Engineering Specification, Engine Data Concentrator (EDC) P/N 261450-1, Astronautics Corporation of America, Revision B, 21 April 2005

PLI09566 Installation Procedures, Equipment Limitations and Operating Instructions for the Electronic Flight Instrument P/N 261400-1, Astronautics Corporation of America, Revision A, 2 May 2005

PLI09589 Installation Procedures, Equipment Limitations and Operating Instructions for the Engine Data Concentrator P/N 261450-1, Astronautics Corporation of America, Revision A, 3 May 2005

2.3.1 Bell Helicopter Documents

205-705-001-101K Kit Assembly Inspection Log (KAIL) for Huey II, Bell Helicopter Textron, Inc., 12 February 2004

205-947-304B Detail Specification for the UH-1H-II Utility Helicopter, Bell Helicopter Textron, Inc., 17 March 1993

BHT PUB-92-004-10 Technical Manual, Bell Model UH-1H-II Helicopter Operator’s Manual, 31 August 2004

BHT PUB-92-004-CL Technical Manual, Bell Model UH-1H-II Helicopter Operator and Crewmember Checklist 31 August 2004

BHT PUB-92-004-MTF Technical Manual, Bell Model UH-1H-II Helicopter Maintenance Test Flight Manual, Revision 7, 15 August 2005

BHT PUB-92-004-23 Technical Manual, Bell Model UH-1H-II Helicopter Aviation Unit & Intermediate Maintenance Manual Airframe, Revision 9, 15 August 2005

BHT PUB-92-004-23P Technical Manual, Bell Model UH-1H-II Helicopter Organizational, Intermediate and Depot Airframe Maintenance Illustrated Parts Breakdown, Revision 5, 15 August 2005

BHT 205-SI-9 Service Instructions, Rotor Brake Kit, 5 June

2.3.2 Commercial Standards

ARINC 429 MARK33 Digital Information Transfer System

RTCA/DO-160E Environmental Conditions and Test Procedures for Airborne Equipment

RTCA/DO-178B Software Considerations in Airborne Systems and Equipment Certification

RTCA/DO-254 Design Assurance Guidance For Airborne Electronic Hardware

RTCA/DO-275 Minimum Operational Performance Standards For Integrated Night Vision Imaging System Equipment

SAE ARP5369 Guidelines for Wire Identification Marking Using the Hot Stamp Process

SAE AS17983 Compass, Magnetic, Pilot’s Standby

SAE AS50881 Wiring, Aerospace Vehicle, Rev. B

SAE AS8049 Performance Standard for Seats in Civil Rotorcraft, Transport Aircraft, and General Aviation Aircraft, Rev. B

3.0 REQUIREMENTS

3.1 CHARACTERISTICS: The TH-1H training helicopter shall be prepared for the Huey II upgrade in accordance with (IAW) the Army UH-1H/V Aircraft Depot Maintenance Work Requirement (DMWR) 55-1520-210. The baseline UH-1H/V aircraft is defined by the Army Technical Manual (TM) 11-1520-210 series and the TM 55-1520-210 series publications. The DMWR shall be accomplished on all aircraft systems that are not modified by the BHTI Huey II Kit installation, or the TH-1H system upgrades defined herein. The commercial BHTI Huey II Kit installation shall be as defined by the BHTI UH-1H-II Detail Specification No.

205-947-304B, by the BHT PUB-92-004 series of Technical Manuals, and by the following BHTI Modification Kit data package:

Airframe Modification Kit, Bell Part Number (P/N) 205-705-001-001 Dynamics Modification Kit, Bell P/N 205-705-001-107 Tailboom Modification Kit, Bell P/N 205-705-001-111 Bell 212 Nose Assembly, Bell P/N 212-030-003-167A Kit Assembly Inspection Log (KAIL) P/N 205-705-001-101K

3.1.1 Three-view Drawing: The TH-1H incorporates the Bell 212 aircraft nose installation option of the BHTI UH-1H-II kit. Refer to Figure 1 for the dimensioned three-view drawing.

Figure 1. TH-1H Three-view Drawing

3.1.2 Performance: The TH-1H shall perform in accordance with (IAW) the BHTI UH-1H-II Detail Specification No. 205-947-304B, and the capabilities specified in Table 1.

PERFORMANCE REQUIREMENTS

Capability / Description Threshold

Gross Weight 10,500 lbs.

Payload (Full Fuel) 3,500 lbs.

Engine Time Between Overhaul (TBO) 5,000 Hours Max Speed Velocity Not to Exceed (Vne) 130 kts Horizontal Velocity (Vh) (cruise) 120 kts Vertical Rate of Climb (Vroc) 400 ft./min.

Service Ceiling 12,500 ft.

Max Endurance 2.0 Hours

Hover Ceiling Out of Ground Effect (OGE) 10,000 ft.

Table 1. TH-1H Performance Requirements

3.2 GENERAL: The TH-1H systems and components shall be integrated to provide the required functionality and performance capabilities specified herein. The avionics systems, electrical power architecture, and glass cockpit integration design shall provide single pilot Visual Flight Rules (VFR) and Instrument Flight Rules (IFR) operation. The integration design shall comply with the Electromagnetic Environmental Effects requirements of MIL-STD-464A or RTCA/DO-160E where applicable to military or commercial systems. The system electrical integration designs shall comply with the avionics commercial manufacturer’s instructions and recommendations to the extent possible within the constraints of the applicable military standards and specifications.

3.2.1 General Interior Arrangement: The TH-1H interior arrangement shall modify the existing aircraft forward cabin one-man jump seat configuration to accommodate the center crashworthy observer seat installation. Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B for the remaining crew and troop/passenger seat arrangements.

3.3 AERODYNAMICS: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4 STRUCTURAL DESIGN CRITERIA: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.1 Limit Flight Load Factors: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.2 Ultimate Ground Load Factors

3.4.2.1 Take-Off: Not applicable.

3.4.2.2 Landing: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.2.3 Crash Landing Load Factors, Ultimate: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.2.3.1 Crashworthy Seat Structure: The TH-1H pilot, copilot and center observer crashworthy seats installation supporting aircraft floor structure shall withstand the minimum crash loads specified in the BHTI UH-1H-II Detail Specification 205-947-304B, and shall withstand the crash load range induced by the crashworthy seat’s qualified load limit, and energy attenuating (EA) system for crewman protection. Refer to Section 3.22.1.1 for seat specifications.

3.4.2.4 Sinking Speed: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.3 Limit Diving Speed: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.4 Ditching Criteria: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.5 Flutter Characteristics: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.6 Mechanical Instability and Flywheel Type Response: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.7 Rotor Induced Vibration: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.8 Main Rotor Speed: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.4.9 Speed, Design Maximum: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.5 WING GROUP: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.6 MAIN ROTOR GROUP: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.7 TAIL ROTOR GROUP: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.8 TAIL GROUP: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.9 BODY GROUP: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.10 ALIGHTING GROUP: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.11 ALIGHTING GROUP (WATER TYPE): Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.12 SURFACE CONTROL SYSTEM: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.13 ENGINE SECTION: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.14 PROPULSION: The TH-1H propulsion systems shall be IAW BHTI UH-1H-II Detail Specification No. 205-947-304B. The TH-1H shall incorporate the Honeywell T53-L-703 engine installation, with the engine commercial conversion as defined by the following Honeywell Service Bulletins (SB):

SB 020, Engine Rotating Component Service Life Limit.

SB 124, Engine – General Overhaul of U.S. Army Maintained Engines to Align with Honeywell Commercial Standards.

3.15 TRANSMISSION SYSTEM: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.15.1 Main Rotor Brake: The TH-1H shall have a Main Rotor Brake. The main rotor brake shall meet the following requirements:

FUNCTIONAL PERFORMANCE REQUIREMENTS

Capability / Description Remarks

Operation

Manually operated from the cockpit.

Capable of stopping the rotor:

1. From 130 RPM (40% NR) in 10 seconds or less at maximum rotor brake engagement

2. From 294 RPM (60% NR ) in 40 seconds or less with braking at 130

RPM (40% NR ) .

Service Life Minimum 360 stops from 130 RPM without requiring the replacement of any parts except linings

3.16 AUXILIARY POWER PLANT: Not applicable.

3.17 INSTRUMENTS AND NAVIGATION EQUIPMENT: The TH-1H instrument panel shall be a modified Bell 212 panel, and provide three vertically-oriented 10 inch diagonal MFDs.

The MFDs shall be readable during the day under direct sunlight, and be NVG compatible IAW MIL-STD-3009. The MFDs shall be U.S. Federal Aviation Administration (FAA) TSO-C113 certified Airborne Multipurpose Electronic displays with RTCA/DO-178B certified software, and DO-160E and DO-254 certified hardware. The general cockpit instrument panel configuration is depicted in Figure 2.

Figure 2. Instrument Panel Configuration

3.17.1 Instruments: The Astronautics Corporation of America (ACA) Electronic Flight Instrument (EFI) MFDs shall be installed in the pilot, copilot, and center instrument panel positions to provide the three MFD cockpit capability, and shall be interchangeable with the same hardware and software configuration, and P/N 261400-1, in each position. The ACA MFDs shall contain software for an Electronic Flight Instrument System (EFIS) display, an Engine Instrument and Crew Alert System (EICAS) display, and a reversionary display. The MFDs shall be integrated with the NAV avionics and Glass Cockpit components by ARINC 429 digital data bus interfaces, and shall be powered by locking toggle switches in the overhead console.

3.17.1.1 Flight Instruments: The MFD Electronic Flight Instrument System (EFIS) display shall provide Primary Flight Display (PFD) with the parameters listed in Table 2 in the configuration shown in Figure 3. The pilot and copilot MFDs shall power-on default to the EFIS display.

Master Caution Annunciation Roll Indicator Check EFI Indicated Airspeed Attitude Indicator Cross-link (XLINK) Fail Ground Speed Marker Beacon Attitude Compare Inop.

True Airspeed LO Altitude (RADALT) Selected Altitude Dual Tachometer (NF/NR) Radar Altimeter (RADALT) Barometric Altitude Torque Glide Slope Target Height (RADALT) Wind Direction Localizer Vertical Speed GPS Message Rate of Turn Bearing 2 Data Primary Navigation Data Heading Selected Heading Map Reference Horizontal Situation Indicator Bearing 1 Data Lateral Deviation Selected Course

Table 2. MFD EFIS Display Parameters

Figure 3. MFD EFIS Display Configuration

HSI

ATTITUDE

VERTICAL SPEED

G

INDICATOR

LAT DEV

BEARING 1 DATA BEARING 2 DATA

SEL HDG

PRIMARY NAV

DATA

GPS

ANNUNC

DH

CHK EFI

MB

SEL CRS

MAP REF

XLINK FAIL

ATT CMPR INOP

G L I D E S L O P E

HSI

ATTITUDE

VERTICAL SPEED

DUAL

TACH

LAT DEV

ROLL INDICATOR

RATE OF TURN

HEADING

BEARING 1 DATA BEARING 2 DATA

SEL HDG

PRIMARY NAV

DATA

MASTER CAUTION

ANNUNCIATION

WIND

GPS

ANNUNC

HT

CHK EFI

MB AIRSPEED

DATA

SEL CRS

MAP REF

XLINK FAIL

ATT CMPR INOP

G L I D E S L O P E

RAD ALT

LOCALIZER

ALTITUDE DATA

GROUND SPEED

TRUE AIRSPEED

TARGET HEIGHT

SELECTED ALTITUDE

T O R Q U E

3.17.1.1.1 Reversionary Display: The MFD reversionary mode display shown in Figure 4 shall combine the EFIS and EICAS display elements. The reversionary mode display shall not be automatic, and shall be selectable by the pilot from the MFD bezel REV key.

Figure 4. MFD Reversionary Display Configuration

ATTITUDE

VERTICAL SPEED

G

INDICATOR

DH

CHK EFI

MB

XLINK FAIL

ATT CMPR INOP

G L I D E S L O P E

HSI

ATTITUDE

VERTICAL SPEED

DUAL

TACH

(N2/NR)

ROLL INDICATOR

RATE OF TURN

HEADING

PRIMARY NAV

DATA

GPS

ANNUNC

HT

CHK EFI

MB AIRSPEED

DATA

SEL

CRS

MAP REF

XLINK FAIL

ATT CMPR INOP

G L I D E S L O P E

RAD ALT

LOCALIZER

SLIP

ALTITUDE DATA

GROUND SPEED

TRUE AIRSPEED

TARGET HEIGHT

SELECTED ALTITUDE

WARNING

CAUTION

ANNUNCIATIONS

GAS

PRODUCER

(N1)

EXHAUST GAS

TEMP

ENGINE OIL

TEMP &

PRESSURE

XMSN OIL

TEMP &

PRESSURE

AMMETER

DC

VOLTMETER

AC

VOLTMETER

FUEL

QTY

FUEL

PRESS

OAT

BEARING 1

DATA

BEARING 2

DATA

SEL

CRS

T O R Q U E

3.17.1.1.2 MFD Bezel Controls: The bezel controls as shown in Figure 5 shall provide the pilot with complete adjustment and functionality of the MFD as listed in Table 3.

Figure 5. MFD Bezel Configuration

MFD Bezel Controls Function

BRT AMLCD Display Intensity RST Master Caution Acknowledge ADC Air Data Source Select REV Reversionary Display Select PAGE Display More WCAs EDC EDCU Channel Select NAV Active NAV Source Select T/M True/Mag Heading Select ↑ (Single Arrow) Bearing 1 Source Select ↑↑ (Double Arrow) Bearing 2 Source Select CRS Course Select HDG Heading Select SET Setting Adjustment Knob ALT Baro Altitude Target Setting Select RAD RADALT Target Setting Select BARO Baro Correction Setting Select FUEL Bingo Fuel Setting Select RANGE (Up/Down Arrows) Map Range Select ARC HSI Half or Full Arc Select REF Map Reference Selection RA Test RADALT Test Switch

Table 3. MFD Bezel Controls

3.17.1.1.3 Attitude Heading Reference System (AHRS): The AHRS system shall provide attitude, MAG heading, and linear and angular acceleration rates, and shall be FAA TSO-C4c/C5e/C6d certified. The AHRS cockpit control unit (CCU) shall be NVG compatible IAW MIL-STD-3009. The Litef LCR-92 AHRS listed in Table 4 shall be installed to provide the AHRS capability, and shall be ARINC 429 integrated with the MFDs and GPS.

AHRS Component Part Number Location LCR-92 AHRS 141852-3122 Lower Nose Shelf Aft GFD-11 CCU 1001-4000-05 Center Console Sperry MSU (Flux Valve) CN-405/ASN Tailboom Bracket

Table 4. AHRS Components

3.17.1.1.4 Air Data Computer (ADC): The ADC systems shall contain a primary and secondary ADC unit for dual redundant MFD air data sources. The ADC sources shall be pilot selectable on the MFD bezel. The dual ADCs shall be FAA TSO-C106 certified. The Penny and Giles Enhanced Software Configurable Air Data Unit (ESCADU) system listed in Table 5 shall provide the ADC capability, and shall be ARINC 429 integrated with the MFDs and GPS.

ADC Component Part Number Quantity Location ESCADU D51610-1704 2 Upper Nose Shelf Dual Element OAT Sensor 0129G 1 Lower FS 28, LBL 5

Table 5. ADC System Components

3.17.1.2 Propulsion Instruments: The ACA Engine Data Concentrator Unit (EDCU), P/N 261450-1, shall perform IAW ES2562 EDC Engineering Specification to convert the TH-1H engine and aircraft system analog signal to digital ARINC 429 data bus format, and transmit the data to the MFDs for the EFIS and EICAS displays. The EDCU shall be dual channel redundant with independent power supplies and EDC modules to provide dual channel redundant output to all three MFDs. The EDCU shall be FAA TSO certified with RTCA/DO-178B certified software, and DO-160E and DO-254 certified hardware.

3.17.1.2.1 EICAS Display: The MFD EICAS display shall provide engine and transmission instruments, aircraft system sensor indications, and warnings, cautions, and advisories (WCAs) to the aircrew as listed in Table 6, and shown in Figure 6.

Engine and Aircraft System Indications Warnings (Red) Cautions (Yellow) Main Rotor RPM (NR) Engine Fire Right Fuel Boost Engine Power Turbine RPM (NF) Engine Oil Pressure Left Fuel Boost Engine Gas Turbine RPM (NG) Engine Fuel Pump Fuel Filter Engine Gas Temperature (EGT) Engine Chip Detector 20 Minute Fuel Engine Oil Temperature Transmission Oil Pressure Engine Oil Filter Engine Oil Pressure Transmission Oil Hot Hydraulic Pressure Low Transmission Oil Tempurature Chip Detector Governor Emergency Transmission Oil Pressure RPM Warning DC Generator Main Generator Loadmeter External Power Standby Generator Loadmeter Fuel Pressure EFI Advisories Advisories (Green) Fuel Quantity Check EFI Cargo Hook Arm DC Voltmeter XLINK Fail Auxiliary Fuel Low Outside Air Temperature (OAT) Miscompare

Table 6. EICAS Display Parameters

Figure 6. MFD EICAS Display Configuration

3.17.1.2.2 Reversionary EICAS Display: The EICAS display parameters are combined with the EFIS parameters in the MFD Reversionary Mode. Refer to Section 3.17.1.1.1 and Figure 4.

EXHAUST GAS

TEMPERATURE

CHK EFI

GAS PRODUCER

(N1)

CHK EFI

WARNING

CAUTION

ANNUNCIATIONS

DUAL TACH

(N2/NR)

ENG OIL

PRESSURE

ENG OIL

TEMPERATURE

XMSN OIL

PRESSURE

XMSN OIL

TEMPERATURE

FUEL

PRESSURE

DC VOLTS

FUEL

QTY

STBY

AMPS

MAIN

AMPS

OAT

3.17.2 Navigation Equipment: The instrument panel shall contain standby instruments to provide a backup primary flight information to the pilots in the event of a glass cockpit system component failure. The standby instrument configuration listed in Table 7 shall include pilot and copilot 8-day mechanical analog clocks; pilot and copilot standby magnetic (MAG) compasses; an electric attitude indicator with battery backup; a mechanical slip indicator; and a barometric altimeter, airspeed indicator, and vertical velocity indicator (VVI) connected to the pitot-static system. The standby instruments illumination shall be NVG compatible.

Standby Instruments Part Number Quantity Location Mid-Continent Attitude Indicator

4300-312

1 Top Between Pilot and Center MFDs

Slip Indicator 36023 1 Lower Attitude Gyro Bezel Aerosonic 2” Airspeed Indicator 25020-8168 1 Between Pilot and Center

MFDs (in Table Order) Aerosonic 2” Barometric Altimeter 15420-8194 1 Aerosonic 3” VVI 30230-81110 1 Mechanical Clock, MIL-C-6499E Type A-13A-2 2 Lower Right MFD Corner Magnetic Compass SAE AS17983 2 Outer Pilot and Copilot

Edge of Instrument Panel

Table 7. Standby Instruments

3.18 HYDRAULICS: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19 ELECTRICAL INSTALLATION

3.19.1 Description: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.2 Electrical Power Supply: The aircraft electrical power systems shown in Figure 7 shall generate and distribute the necessary Direct Current (DC) and Alternating Current (AC) power for the avionics and electrical systems. The 115 Volt AC (VAC), 400 Hz power system shall not be required on the aircraft, and the 115 VAC inverters shall not be installed.

MAIN GEN

RESET

OFF

ON

BATTERY

40 AMP-HOUR

MAIN

GENERATOR

300 AMP

STANDBY

GENERATOR

300 AMP

STARTEREXTERNAL

POWER

PRIMARY BUS

BAT

OFF

ON

STARTER

GEN

START STBY GEN

ESS DC BUS

NON ESS DC BUS

MANUAL

NORMAL

26 VAC

INVERTER

26 VAC BUS

MAIN GEN

RESET

OFF

ON

BATTERY

40 AMP-HOUR

MAIN

GENERATOR

300 AMP

STANDBY

GENERATOR

300 AMP

STARTER

STANDBY

GENERATOR

300 AMP

STARTEREXTERNAL

POWER

PRIMARY BUS

BAT

OFF

ON

STARTER

GEN

START STBY GEN

ESS DC BUS

NON ESS DC BUS

MANUAL

NORMAL

26 VAC

INVERTER

26 VAC BUS

Figure 7. Electrical Power System Architecture

3.19.2.1 Generator: The existing 300 Amp 28 VDC main and standby starter-generators shall be retained as defined by the BHTI Huey II kit installation. Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.2.2 Battery: The TH-1H aircraft 24 VDC battery shall be a 20 cell, 40 ampere-hours nickel-cadmium battery, model Marathon MA-5-20.

3.19.3 Electrical Power Conversion:

3.19.3.1 Inverter: The TH-1H shall require a single FAA TSO-C73-certified 26 VAC Inverter.

The KGS electronics SPC-5(C) Inverter shall be installed under the lower nose shelf to provide 26 VAC reference signal to the Fuel Pressure Transmitter, and to the Glass Cockpit EDCU.

3.19.3.2. Converter: The Glass Cockpit MFD Bezels and standby instruments shall require a 5 VDC power converter for the NVIS bezel lighting. The Emi Model EMSE377 5 VDC Power Converter shall be installed under the lower nose shelf to provide the NVIS lighting.

3.19.4 Equipment Installation: The electrical component installations shall be IAW the commercial systems manufacturers’ instructions and recommendations. The avionics components and cable routing shall be designed IAW the manufacturer’s recommendations for system separation to the extent possible within the limitations of the TH-1H airframe, and the constraints of the applicable military standards and specifications.

3.19.5 Wiring: The aircraft wiring and cable harness installations shall be IAW TO 1-1A-14 and SAE AS 50881, with the exception that hot stamping identification IAW SAE ARP5369 shall be utilized on all aircraft wiring. The existing or retained UH-1H/V aircraft wiring shall be fabricated and installed IAW the Army DMWR refurbishment.

3.19.6 Bonding and Shielding: The TH-1H electrical systems shall be integrated and installed IAW MIL-STD-464A for electrical bonding, shielding, and lightning protection. The EDCU integration with the existing aircraft systems shall require shielded circuit wiring for the analog to digital conversion of the aircraft sensor parameters listed in Table 8.

EDCU Shielded Aircraft Circuits Engine Oil Temperature

Engine Oil Pressure Transmission Oil Temperature

Transmission Oil Pressure Gas Producer Tachometer

Torque Fuel Quantity Fuel Pressure

Main Generator Loadmeter Standby Generator Loadmeter

Table 8. EDCU Shielded Aircraft Circuits

3.19.7 Controls: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.7.1 Panel: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.7.2 Switches: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.7.3 Circuit Breakers: The overhead 28 VDC Circuit Breaker (CB) panel shall be modified, and reconfigured IAW the 28 VDC power distribution architecture for the essential (battery) and nonessential buses. The center pedestal (pilot side) AC CB panel shall be modified to mount flush with the pedestal side structure, and reconfigured as required by the 26 VAC power, and the 5 VDC lighting power circuits. Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B for CB type requirements.

3.19.8 Lighting: The TH-1H cockpit lighting shall be NVG compatible IAW MIL-STD-3009 or RTCA/DO-275 Night Vision Imaging System (NVIS) Standards. The existing UH-1H/V aircraft cabin and exterior lighting systems shall be retained. Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.9 Ignition and Starting System: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.10 Receptacles: The TH-1H shall remove the 115 VAC, single-phase 400 Hz power receptacle from the pilot side of the center pedestal. The 115 VAC power is removed from the aircraft. The existing DC power and external power receptacles shall be retained. Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.11 Indicators

3.19.11.1 Loadmeter: The main and standby generator loadmeters shall be integrated into the Glass Cockpit MFD EICAS display. Refer to section 3.17.1.2.

3.19.11.2 Voltmeter: The DC voltmeter shall be integrated into the Glass Cockpit MFD EICAS display. The existing aircraft voltmeter selector switch shall be retained. Refer to Section

3.17.1.2 and UH-1H-II Detail Specification No. 205-947-304B.

3.19.12 Electric Drives: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.13 Relays: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.19.14 Booster Coil: Not applicable.

3.19.15 Electromagnetic Interference (EMI): The TH-1H electrical systems shall be installed IAW MIL-STD-464A for EMI and Electromagnetic Compatibility (EMC). Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.20 AVIONICS SYSTEMS: The TH-1H shall have commercially or U.S. Department of Defense (DoD) supportable avionics installed to provide the TH-1H aircrew with COMM, NAV, surveillance, and aircraft state information.

3.20.1 Communications: The TH-1H line-of-sight (LOS) COMM systems shall provide the aircrew with Very High Frequency (VHF)-Frequency Modulation (FM), VHF-Amplitude Modulation (AM) and Ultra High Frequency (UHF)-AM band operation. The systems shall provide the capability to simultaneously monitor one frequency in each band. The COMM systems shall provide manual and preset channels, and an auto-squelch with select OFF capability. The COMM systems’ effective radiated power and operating range shall be equivalent to or greater than the existing UH-1H/V radios as defined in the Army TMs. The center console-mounted control panels shall be NVG compatible IAW MIL-STD-3009 or RTCA/DO-275 NVIS Standards.

3.20.1.1 VHF-FM: The VHF-FM COMM system shall operate in the radio frequency (RF) band of 30-87.975 MHz, with 25 kHz channel spacing and a transmitting power of 10 watts.

The Wulfsberg Electronics FLEXCOMM II RT-5000 Tactical Communications System listed in Table 9 shall be installed to provide VHF-FM COMM, and shall be integrated into the Intercommunication System (ICS) radio COMM 1 audio position.

VHF-FM Component Part Number Location RT-5000 Transceiver 400-015525-0101 Lower Nose Shelf Aft C-5000 Control Head 31300-0201-1200 Center Console AT-5000 Tunable Antenna 121-040045-01 Lower FS 192, LBL 18 FC-5000 Antenna Tuner 153-040047-01 Aft Electrical Compartment

Table 9. VHF-FM System Components

3.20.1.2 VHF-AM: The VHF-AM COMM system shall operate in the RF band of 118-136.975 MHz, with 25 kHz channel spacing and a transmitting power of 15 watts. The VHF-AM COMM shall system provide dedicated receiving of the emergency VHF Guard frequency of

121.5 MHz. The Wulfsberg Electronics FLEXCOMM II RT-5000 Tactical Communications System listed in Table 10 shall be installed to provide VHF-AM COMM with Guard, and shall be integrated into the ICS radio COMM 3 audio position.

VHF-AM Component Part Number Location RT-5000 Transceiver 400-015525-0501 Lower Nose Shelf Aft C-5000 Control Head 31300-0201-1200 Center Console AT-160 Passive Antenna 121-040129-01 Upper FS 83, LBL 22

Table 10. VHF-AM System Components

3.20.1.3 UHF-AM: The UHF-AM COMM system shall operate in the RF band of 225-399-975 MHz, with 25 kHz channel spacing and a transmitting power of 10 watts. The UHF-AM COMM system shall provide dedicated receiving of the emergency UHF Guard frequency of

243.0 MHz. The Honeywell Bendix/King KTR-909B UHF Communications System listed in Table 11 shall be installed to provide UHF-AM COMM with Guard, and shall be integrated into the ICS radio COMM 2 audio position.

UHF-AM Component Part Number Location KTR-909B Transceiver 064-01076-0101 Upper Nose Shelf KFS-599B Control Head 071-01576-0101 Center Console AT-1108/ARC Antenna AT-1108/ARC Upper FS 72, RBL 12

Table 11. UHF-AM System Components

3.20.1.4 ICS: The COMM systems shall be integrated with an aircraft ICS that provides five audio panels and crew connections at the pilot, copilot, center observer, left cabin alcove, and right cabin alcove stations. The ICS shall provide an independent selection and volume adjustment for each radio and navigation set, a “HOT-MIC” position, and non-switched audio of aircrew alerting systems for rotor/engine rotations per minute (RPM) high-low limit warning and Master Caution. The system shall provide the aircrew with selectable voice activation (VOX) keying, shall be FAA TSO-C50c certified, and shall retain the cyclic and floor switch keying capability. Five Northern Airborne Technology (NAT) N301A Audio Controllers shall be installed with an aural warning generator, as listed in Table 12, to provide the aircraft ICS capabilities. The N301A ICS switch positions shall be audio integrated into the TH-1H COMM, NAV and aircrew alerting systems as defined Table 13.

ICS Component Part Number Quantity Location NAT N301A N301A-067 5 3 Center Console, 2 Cabin NAT Aural Warning Generator 611 1 Under Lower Nose Shelf

Table 12. ICS Components

ICS Position System

COM 1 VHF-FM

COM 2 UHF-AM

COM 3 VHF-AM

VOR VOR

GPS GPS

TCN TACAN

ADF ADF

MKR MB (VOR/ILS)

Unswitched 1 RPM Warning Unswitched 2 Master Caution

Table 13. ICS Switch Positions

3.20.2 Navigation: The NAV systems shall be ARINC 429 digital data bus integrated into the Glass Cockpit MFDs to provide the pilots with visual flight rules (VFR) and instrument flight rules (IFR) NAV capability. The NAV information shall be displayed to provide single pilot IFR capabilities from both seats. The center console-mounted controls shall be NVG compatible IAW MIL-STD-3009 or RTCA/DO-275 NVIS standards.

3.20.2.1 VOR/ILS: The commercial VOR/ILS system shall be an FAA TSO-C40c certified VHF Omni-Ranging (VOR), TSO-C34e certified for Glide Slope (GS), TSO-C36e Localizer (LOC), and TSO-C35d Marker Beacon (MB) receiving NAV and landing system. The Honeywell Bendix/King KNR-634A VOR Navigation Receiver System listed in Table 14 shall be installed to provide VOR/ILS NAV capability, and shall be integrated into the ICS VOR and MKR audio positions.

VOR/ILS Component Part Number Location KNR-634A Receiver 066-01078-0014 Lower Nose Shelf Forward KFS-564A Control Panel 071-01283-0012 Center Console VOR/LOC Antenna DM N4-4 Aft Tailboom MB Antenna AT-640A/ARN Centerline Lower FS 44 GS Antenna 37P-4 Centerline Front Nose

Table 14. VOR/ILS Components

3.20.2.2 ADF: The commercial Automatic Direction Finder (ADF) system shall be an FAA TSO-C41d certified receiving NAV system. The Wulfsberg Chelton Series III DFS-43B ADF Receiver System listed in Table 15 shall be installed to provide ADF capability, and shall be integrated into the ICS ADF audio position.

ADF Component Part Number Location DF-431B Receiver 066-1105-00 Lower Nose Shelf Aft CDF-552 Control Panel 400-047552-0100 Center Console AT-434A Antenna 071-1348-00 Centerline Lower FS 115

Table 15. ADF System Components

3.20.2.3 Tactical Air Navigation (TACAN): The TACAN system shall provide NAV bearing receiving in the RF band of 960-1215 MHz, and a FAA TSO-C66c certified Distance Measuring Equipment (DME) NAV range capability. The L3 Avionics AN/ARN-154(V) TACAN System listed in Table 16 shall be installed to provide TACAN capability, shall be integrated into the ICS TCN audio position, and shall provide a suppression signal to the Transponder.

TACAN Component Part Number Location RT-1634(V) 805D0602-31 Lower Nose Shelf Forward F3849 Control Panel 805D0665-01 Center Console NY162WT Antenna 805-10033-001 Lower FS 58, RBL 16

Table 16. TACAN System Components

3.20.2.4 Global Positioning System (GPS): The GPS shall provide 12–channel Standard Positioning Service (SPS) receiving capability on the L1 frequency at 1575 MHz, and shall be FAA TSO-C129a certified for supplemental en-route IFR navigation. The GPS shall provide a serial interface capability to upload a NAV database to the receiver. The Free Flight Systems 2101 I/O Approach Plus GPS System listed in Table 17 shall be installed to provide GPS capability, and shall be integrated into the ICS GPS audio position.

GPS Component Part Number Location 2101 I/O Approach Plus Receiver 81440-12-241G Center Console L1 Antenna 16248-11 Upper Wire Cutter

Table 17. GPS Components

3.20.2.5 Radar Altimeter (RADALT): The RADALT shall have an operating altitude range of 0-2000 feet above ground level (AGL), and shall be FAA TSO-C87 certified. The Honeywell Bendix/King KRS-405B RADALT System listed in Table 18 shall be installed to provide the RADALT capability. The RADALT shall be powered by a toggle switch in the overhead console, and shall be controlled by the Glass Cockpit MFD bezel keys.

RADALT Component Part Number Quantity Location KRA-405B Receiver-Transmitter 066-01153-0101 1 Center Console KA-54A Antenna 071-1501-0000 2 Lower FS 58, BL 10

Table 18. RADALT System Components

3.20.3 Surveillance: The civil Air Traffic Control (ATC) Radar Beacon System (ATCRBS) transponder shall provide Modes 3/A and C, and Mode Select (S) surveillance capability. The system shall be connector pin-strapped with the aircraft’s permanent unique 24-bit Mode S address (code), and shall be FAA TSO-C112 certified. The transponder system and TH-1H installation shall be DoD AIMS Program certified. The Honeywell Bendix/King MST-67A Transponder system listed in Table 19 shall be installed to provide the ATCRBS and Mode S surveillance capability, shall be integrated with both ADCs for altitude data, and shall receive a suppression signal from the TACAN.

Transponder Component Part Number Quantity Location MST-67A Transponder 066-01143-1301 1 Upper Nose Shelf KFS-578A Mode S Control 071-01507-4902 1 Center Console KA-61 Antenna 071-00221-0020 2 Upper FS 100, RBL 33

Lower FS 31, LBL 16

Table 19. Transponder System Components

3.20.4 Emergency Locator Transmitter (ELT): The ELT system shall be capable of transmitting on the three primary emergency frequencies of 121.5 MHz VHF-AM, 243.0 MHz UHF-AM, and 406.028 MHz UHF Coded Digital Message. The system shall have integrated position encoding, and shall be programmed with the aircraft’s unique 24-bit address. The ELT system shall have a manual and G-switch activation capability, shall be FAA TSO-C126 certified, and shall contain an audible cockpit buzzer and NVG compatible light upon activation.

The Artex C406-N HM Helicopter ELT system listed in Table 20 shall provide the ELT capability, and shall be ARINC 429 integrated with the GPS.

ELT Component Part Number Quantity Location C406-N HM ELT 453-5061 1 Upper Pilot Door Post Cockpit Switch Panel 453-9703 1 Instrument Panel Buzzer 130-4004 1 Cabin Ceiling FS 68 Tri-band Rod Antenna 110-338 1 Upper FS 63, LBL 10

Table 20. ELT System Components

3.20.5 Avionics Installation

3.20.5.1 General: The mechanical component Line Replaceable Unit (LRU) installations shall provide for the safe operation, maintenance, and performance of all the systems. The aluminum alloy sheet metal and airframe components shall be designed and manufactured to provide the required structural integrity for the application. The aluminum components shall be treated and finished IAW MIL-C-5541E and MIL-PRF-23377H for corrosion resistance. The TH-1H system designs defined herein shall not require special tooling or processes for manufacturing or installation.

3.20.5.2 Cockpit Center Console: The TH-1H cockpit center console shall retain the UH-1H/V hydraulics, chip detector, force trim, and engine control panels. The avionics communications, navigation, and surveillance system control panels shall be installed in a configuration that allows maximum aircrew access, control and readability.

3.20.5.3 Cockpit Overhead Consoles: The forward overhead console shall contain the standard UH-1H/V control panels with the removal of the 115 VAC power control panel, the addition of the RADALT and MFD power switches, and the modification of the lighting control panel as required by the Glass Cockpit installation.

3.20.5.4 Instrument Panel: The MFDs, standby instruments, and instrument panel components shall be installed in the configuration shown in Figure 2. The instrument panel and installed components shall safely withstand the minimum crash loads specified in the BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.20.5.5 Nose Compartment: The avionics upgrade LRUs shall be installed for optimum maintenance access and cooling airflow. The components installations shall safely withstand the minimum crash loads specified in the BHT UH-1H-II Detail Specification No. 205-947-304B, and shall not interfere with the BHTI nose ballast weight installation kit.

3.20.5.6 Cabin: The cabin installations of the ELT on the pilot door post, the two ICS panels in the alcove ceilings, and the Main Rotor Brake Master Cylinder on the ceiling above the pilot seat, shall be accessible and maintainable, and shall safely withstand the minimum crash loads specified in the BHT UH-1H-II Detail Specification No. 205-947-304B.

3.20.5.7 Antennas: The TH-1H avionics antennas and sensors shall be installed to provide optimum system performance and withstand the aerodynamic loads of the aircraft. The existing UH-1H/V aircraft antenna locations shall be utilized to the fullest extent possible. The antenna installations shall utilize conductive environmental sealant gaskets, and shall be designed IAW the avionics manufacturer’s recommendations, and MIL-STD-464A where applicable.

3.21 ARMAMENT: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.22 FURNISHINGS AND EQUIPMENT

3.22.1 Accommodations For Personnel

3.22.1.1 Seats: The TH-1H shall incorporate pilot, copilot, and center observer crashworthy seats installations with headrests. The crashworthy seats shall be commercially qualified to civil Federal Aviation Regulations (FAR) Part 29 static and dynamic crash load requirements. The crashworthy seat design and human factors characteristics shall be qualified to the applicable requirements of FAA TSO-C127a for rotorcraft seating systems, AS8049 Performance Standard for Seats, and Joint Service Specification Guide JSSG-2010-7 Crash Protection Handbook.

Refer to Section 3.4.2.3 for crashworthy seat support structure requirements.

3.22.1.1.1 Pilot and Copilot: The TH-1H crashworthy pilot and copilot seats shall be the Simula H1 Crashworthy pilot seat, P/N 114700-1, which is a non-armored version of the military qualified U.S. Navy/Marine Corps UH-1Y pilot seat.

3.22.1.1.2 Observer: The TH-1H center observer’s crashworthy seat shall be the Skyline Operator’s Seat, P/N SK2100-100, which is military qualified by the Army Airborne Command and Control System (A2C2S) Program on H-60 aircraft.

3.22.1.2 Safety Belts and Harness: The TH-1H crashworthy pilot, copilot, and center observer seats shall incorporate five-point restraint harnesses for the occupants. These restraints shall be military and commercially qualified with the seat systems. Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B for the requirements of the existing troop passenger seat and litter harnesses.

3.22.2 Miscellaneous Equipment: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.22.3 Furnishings: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.22.4 Emergency Equipment: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.22.5 Oxygen Equipment: Not Applicable.

3.22.6 Emergency Rescue Equipment: Refer to BHTI UH-1H-II Detail Specification No. 205-947-304B.

3.22.7 Rescue Hoist:…