AN/ALQ-172 Countermeasures System (CMS)


4/7/98

 

 

 

 

SYSTEM REQUIREMENTS DOCUMENT (SRD)

FOR

INTEGRATION OF THE ENHANCED ALQ-172 & LOW BAND JAMMER

ON TO THE AC-130U AND MC-130H AIRCRAFT

 

PREPARED BY

ASC/LUN (SOF INTEGRATION IPT)

2275 D STREET, BLDG 16, STE 16, RM 142.

WRIGHT-PATTERSON AFB, OH 45433-

 

TABLE OF CONTENTS

SECTION

PAGE

1.0 (U) SCOPE

4

1.1 (U) GENERAL

4

1.2 (U) IDENTIFICATION

4

1.3 (U) APPLICATION

4

1.3.1 (U) DEVIATIONS

4

2.0 (U) APPLICABLE DOCUMENTS

4

2.1 (U) GOVERNMENT DOCUMENTS

4

2.2 (U) NON-GOVERNMENT DOCUMENTS

5

3.0 (U) REQUIREMENTS

5

3.1 (U) SYSTEM DEFINITION

5

3.1.1 (U) System Description

5

3.1.2 (U) Aircraft Integration Requirements

5

3.1.2.1 (U) Aircraft Modification Requirements

5

3.1.2.1.1 (U) Relocation of Existing Systems

6

3.1.2.2 (U) Computer/Avionics Interface Definition

6

3.1.2.2.1 (U) Data Bus Interface

6

3.1.2.2.2 (U) Control and Auxiliary Processors

6

3.1.2.3 (U) Mechanical Interfaces

6

3.1.2.3.1 (U) Enhanced ALQ-172 and Low Band Jammer Mounting

6

3.1.2.3.2 (U) LRU Mounting Provisions

6

3.1.2.4 (U) Thermal Interfaces

6

3.1.2.5 (U) Electrical Power Subsystem

6

3.1.2.5.1 (U) Power Quality

6

3.1.2.5.2 (U) Maximum AC Loads

7

3.1.2.5.3 (U) Maximum DC Loads

7

3.1.2.6 (U) On-board Vulnerability

7

3.1.2.7 (U) System Performance

7

3.1.2.7.1 (U) LBJ Field of View

7

3.1.2.8 (U) Aircraft Pressurization

7

3.1.2.8.1 (U) Leakage Rate

7

3.1.2.8.2 (U) Proof Pressure

7

3.1.2.9 (U) Growth Capacity

7

3.1.2.9.1 (U) Integrated Electronic Warfare (EW) Bus

7

3.1.2.9.2 (U) Monopulse and Continuous Wave (CW) Countermeasures

7

3.1.2.9.3 (U) Consolidated EW Display

7

3.1.3 (U) Service Life

7

3.2 (U) Characteristics

8

3.2.1 (U) Physical Properties

8

3.2.1.1 (U) Mass Properties

8

3.2.1.2 (U) Structural Integrity

8

3.2.2 (U) Environmental, Safety, and Health (ESH)

8

3.2.2.1 (U) System Safety

8

3.2.2.1.1 (U) Hazardous Materials

8

3.2.2.1.2 (U) Radiation Hazards

8

3.2.2.2 (U) Crashworthiness

8

3.2.2.3 (U) Design and Construction

8

3.2.3 (U) Supportability

8

3.2.3.1 (U) Reliability

8

3.2.3.2 (U) Maintainability

8

3.2.3.2.1 (U) Diagnostics

9

3.2.3.2.1.1 (U) Reprogrammability

9

3.2.3.2.1.2 (U) Support Equipment

9

3.2.3.3 (U) Levels of Maintenance

9

3.2.3.3.1 (U) Organizational Maintenance

9

3.2.3.4 (U) Maintenance Personnel

9

3.2.3.4.1 (U) Environment

9

3.2.3.4.2 (U) Manpower

9

3.2.4 (U) Environmental Conditions

9

3.2.4.1 (U) Natural Environment

9

3.2.4.1.1 (U) Lightning Protection

9

3.2.4.1.2 (U) Temperature and Altitude

10

3.2.4.1.3 (U) Water Intrusion and Rain Erosion

10

3.2.4.1.4 (U) Humidity

10

3.2.4.1.5 (U) Salt Atmosphere

10

3.2.4.1.6 (U) Sand and Dust

10

3.2.4.2 (U) Induced Environment

10

3.2.4.2.1 (U) Vibration

10

3.2.4.2.2 (U) Load Factors

10

3.2.4.2.3 (U) Acoustic Noise

10

3.2.4.2.4 (U) Gunblast

10

3.2.4.2.5 (U) Fluids

10

3.2.4.2.6 (U) Foreign Object Damage (FOD).

11

3.2.4.2.6.1 (U) Ground Conditions

11

3.2.4.2.6.2 (U) Bird FOD

11

3.2.4.2.7 (U) Electromagnetic Environmental Effects

11

3.2.4.2.7.1 (U) Electromagnetic Compatibility (EMC)

11

3.2.4.2.7.2 (U) Radio Frequency (RF) Compatibility

11

3.2.4.2.8 (U) Air Flow Field

11

4.0 (U) QUALITY ASSURANCE PROVISIONS

11

4.1 (U) GENERAL

11

4.1.1 (U) Responsibility for Inspection, Analysis, and Testing

11

4.1.1.1 (U) Records

11

4.1.2 (U) Methods of Verification

11

4.1.3 (U) Quality Conformance Inspections

12

4.1.4 (U) Test Article Configuration

12

4.2 (U) In-Process Verification Measurement

12

4.2.1 (U) Interface Control Documents (ICDs):

12

4.2.2 (U) Logistic Support Analysis (LSA) Integration

12

4.2.3 (U) Antenna Pattern and Isolation Test

12

4.2.4 (U) Jammer Effectiveness Analysis and/or Test

12

4.2.5 (U) Pre-Flight Installed Performance Test

12

4.3 (U) Quality Conformance

12

5.0 (U) PREPARATION FOR DELIVERY

16

6.0 (U) Notes

16

6.1 (U) Definitions

16

6.2 (U) Abbreviations

16

6.3 (U) Miscellaneous Notes

16

6.3.1 (U) Proprietary Data

16

6.3.2 (U) Enhanced ALQ-172 and Low Band Jammer Installation Baseline

16

6.3.3 (U) Physical Configuration Audit

17

6.3.4 (U) Configuration Control

17

1.0 (U) SCOPE

1.1 (U) GENERAL: This SRD establishes the functional, performance, & verification requirements and the objectives specifically for the integration and installation of the Enhanced ALQ-172 and Low Band Jammer (LBJ) RF Countermeasures on to the AC-130U and MC-130H aircraft. The term "Enhanced ALQ-172" refers to the upgrade/replacement of the existing ALQ-172 High Band Line Replaceable Units (LRUs) with the ALQ-172(V)3 configured High Band LRUs. The term "Low Band Jammer" or "LBJ" refers to a SOF-common system, either the ALQ-172(V)3 or the ALQ-196. Hereafter, the term "integrated aircraft system" refers to the combined Enhanced ALQ-172 & LBJ aircraft modification.

1.2 (U) IDENTIFICATION: This SRD establishes the installed performance requirements as derived from Addendum A to AFSOC ORD 006-87-I/IIIA R1 - Requirements for the AC-130U Enhanced Spectre Gunship and MAC SORD 005-83-IV B - Requirements for the MC-130H Combat Talon II. The SRD also identifies the employment & deployment environments, and constraints as they impact performance, supportability, system integrity, and system engineering management of the SOF aircraft.

Appendix A to this SRD defines the classified operational performance requirements and objectives as they apply to the Enhanced ALQ-172 and LBJ. It also defines the requirements for reboresight of the AC-130Uís High Band transmit antennas. Appendix B to this SRD defines the requirements for replacing the AC-130Uís ALR-56M Radar Warning Receiver with the ALR-69. Mission profiles for the AC-130U and MC-130H are contained in their respective System Specifications.

1.3 (U) APPLICATION: The SRD cannot be used for contractual purposes without supplemental information relating to the operational performance and interface requirements for the systems to be installed. Supplemental information defining operational performance and interface requirements for both the AC-130U and MC-130H aircraft are contained in the technical data packages provided as part of the IWSSP contract. Supplemental guidance for tracking and deriving lower level requirements definitions is identified within the applicable documents shown in Sections 2.1 and 2.2 or in the classified appendix to this SRD.

1.3.1 (U) DEVIATIONS: Prior to contract award, prospective contractors are encouraged to submit cost effective changes, operationally suitable alternatives, and improvements to the requirements of this SRD to the acquisition activity. Incorporation will depend upon the merits of the proposed change and the needs of the program. After contract award, changes will be accomplished in accordance with the applicable contract specification change notice (SCN) procedures.

2.0 (U) APPLICABLE DOCUMENTS: The following additional documents form a part of this SRD to the extent specified herein. In the event of conflict between the requirements of this document and any other referenced document, the requirements of this document shall take precedence except as specifically provided for in the contract. All conflicts shall be brought to the attention of the procuring activity.

2.1 (U) GOVERNMENT DOCUMENTS: This SRD and data on AC-130U and MC-130H aircraft performance and interface requirements contained in the IWSSP Technical Library shall apply.

(U) SPECIFICATIONS:

(U) Military:

MIL-E-7894

17 May 1955

Characteristics of Aircraft Electrical Power

(U) STANDARDS:

(U) Military:

MIL-STD 464

18 Mar 1997

Electromagnetic Environmental Effects Requirements for Systems

MIL-STD 882

19 Jan 1993

System Safety Program Requirements

AFOSH-STD 48-9

August 1997

Radio Frequency Radiation (RFR) Safety Program

(U) DOD Standards, Instructions, etc.:

DODD 4210.15

27 Jul 1989

Hazardous Material Pollution Prevention

2.2 (U) NON-GOVERNMENT DOCUMENTS

TFD 94-1644, Rev A

12 Jan 96

TIS C4366-3-001, Close-Out Report for Vibration and Acoustic Environment Flight Test

NESI Dwg. #TBD

CAGE Code TBD

Date TBD

DIRCM Documentation/Technical Data (Installation Drawings, ICDs, etc.) - Note: Preliminary data made available

RAYSE Dwg #TBD

CAGE Code TBD

Date TBD

AC-130H AN/ENHANCED ALQ-172 AND LOW BAND JAMMER Documentation/Technical Data (Installation Drawings, ICDs, etc.) - Note: Preliminary data made available

ITTAV Dwg. #2638400, Rev. D

CAGE Code 28527

May 97

(S) Prime Item Functional Specification for Countermeasures Set AN/ALQ-172(V)1, (V)2, and (V)3 Production(U) - (includes Drawings, ICDs, etc.) - Note: Preliminary data made available

Lockheed Dwg #TBD

CAGE Code TBD

Date TBD

MC-130E AN/ALQ-196 LOW BAND JAMMER Documentation/ Technical Data (Installation Drawings, ICDs, etc.) Note: Data not currently available

Sanders Dwg #TBD

CAGE Code TBD

Proprietary

See Section 6.3.1

(S) Prime Item Functional Specification for AN/ALQ-196 LBJ System (U) - (includes Drawings, ICDs, etc.)

Document # 93-0048-003

CAGE Code 26916

20 Jan 93

(S) Northrop Electronics Systems Division Interactive Defensive Avionics (IDAS) Studies Overview and Results Summaries (U)

3.0 (U) REQUIREMENTS

3.1 (U) SYSTEM DEFINITION

3.1.1 (U) System Description: The Enhanced ALQ-172 is an upgrade to the existing ALQ-172(V)1 on the AC-130U and MC-130H aircraft. This upgrade consists of upgrading LRUs 1, 3, 4, & 10 and replacing LRU 2 with LRUs of the ALQ-172(V)3 configuration. A description of these systems and nomenclature for the components are contained in ITTAVís ALQ-172 Prime Item Functional Specification (PIFS). This document also includes the description of the ALQ-172(V)3 LBJ components. The Sanderís ALQ-196 LBJ PIFS provides a description of the system and nomenclature for the components. System installation design interfaces shall be per the requirements of Section 3.1.2 and the aircraft ICDs. The preliminary DIRCM installation data is provided as reference material for an on-going SOF C-130 modification program. The data on the AC-130H is provided as an example of an existing Enhanced ALQ-172 and ALQ-172(V)3 LBJ installation on a SOF C-130. If available, the data on the MC-130E will be provided as an example of the ALQ-196 LBJ installation on a SOF aircraft.

3.1.2 (U) Aircraft Integration Requirements: The integrated aircraft system shall meet all the requirements of this SRD and Appendix A. The integration of the Enhanced ALQ-172 and LBJ with the AC-130U and MC-130H aircraft shall not compromise their ability to safely accomplish all intended operational missions defined in their respective System Specifications. The terms "minimize changes" and "not significantly degrade" are used in this context throughout this SRD.

3.1.2.1 (U) Aircraft Modification Requirements: The modification shall be designed to preclude failure of the modification and the surrounding aircraft structure. The integrated aircraft system shall minimize changes to aircraft performance, stability, and control due to modification weight, drag, shape, and location impacts. The modification shall not significantly degrade operation of any aircraft subsystem nor have its own performance significantly degraded by operation of any aircraft subsystem. The modification must withstand blast pressures from all Gunship ammunition variants.

3.1.2.1.1 (U) Relocation of Existing Systems: Existing aircraft systems shall be relocated only to the extent necessary for the integrated aircraft system to meet the performance requirements of this SRD and Appendix A. The performance of any relocated system shall not be degraded below its current level.

3.1.2.2 (U) Computer/Avionics Interface Definition: All ALQ-172 LRUs which are part of the Enhanced ALQ-172 and LBJ solution shall not be integrated to the existing avionics busses to any greater extent than the current ALQ-172(V)1. The LBJ shall not be integrated to a greater extent than is required to meet the requirements of this SRD, Appendix A, and the individual aircraft System Specifications. As a goal, the LBJ integration shouldl not cause the MC-130Hís aircraft Mission Computer Operational Flight Programs to be rewritten. Any proposed MC-130H mission computer OFP changes shall be subject to approval by the contracting officer. The system shall have the capability to be integrated with other defensive avionics using a data bus in the future. As a minimum, the integrated aircraft system shall maintain current aircraft display capabilities.

3.1.2.2.1 (U) Data Bus Interface: When installed, the Enhanced ALQ-172 and LBJ shall provide ready access to a test, reprogramming, and instrumentation interface which meets the requirements of a remote terminal. All test points shall be accessible without disassembly of the module or assembly. All LRU input/output test points shall be accessible without the use of card extenders or other devices.

3.1.2.2.2 (U) Control and Auxiliary Processors: As a minimum, the LBJ processors shall have an average of 50 percent spare memory and 50 percent spare throughput. As a goal, the spare memory and throughput should both be 75 percent.

3.1.2.3 (U) Mechanical Interfaces

3.1.2.3.1 (U) Enhanced ALQ-172 and Low Band Jammer Mounting: The Enhanced ALQ-172 and LBJ shall be mounted in accordance with the requirements of Sections 3.1.1 & 3.1.2 of this SRD while maximizing the jammerís performance as defined in Appendix A.

3.1.2.3.2 (U) LRU Mounting Provisions: All LRU mounts shall be designed to allow unambiguous installation to assure proper orientation with respect to the aircraft axes. The mounting provisions shall preclude installation of improper part numbered LRUs/radomes and to prevent mixing LRUs/radomes if they are unique to a given location (e.g., left different from right). LRUs mounted internal to the aircraft shall utilize quick disconnect captive fasteners. Vibration isolators shall consider the proximity to other LRUs and aircraft structure away space to provide sufficient separation distance in all dimensions. A means to secure external cables shall be provided to allow flight with external LRUs removed.

3.1.2.4 (U) Thermal Interfaces: The thermal interface, location of the LRUs, and heat dissipation methods for the installed Enhanced ALQ-172 and LBJ shall be chosen to minimize the heat rise in the aircraft and the thermal impacts to other aircraft systems and occupants. The configuration of the aircraft environmental control system shall be considered in the location of the LRUs. The current aircraft cooling system shall not be modified to increase its capacity. If new cooling fans are used, their as installed noise level shall not exceed 85 dB.

3.1.2.5 (U) Electrical Power Subsystem

3.1.2.5.1 (U) Power Quality: The AC-130U and MC-130H power quality is in accordance with MIL-E-7894 characteristics as modified for the transient conditions shown in the table below. The integrated aircraft system shall function in a non-degraded manner through these transient conditions.

ELECTRICAL POWER TYPE

TRANSIENT CONDITION

   

115/200 VAC, 400 Hz

272 volts peak spike for 80 ms

 

600 volts peak spike for 10 us

   

28 VDC

120 volts peak spike for 1 ms

 

-400 volts peak spike for 1 ms

 

600 volts peak spike for 10 us

   

Note: Spike Source Impedance < 50 ohms

 

3.1.2.5.2 (U) Maximum AC Loads: All ALQ-172 LRUs which are part of the integrated aircraft system shall utilize the 400 Hz electrical power consistent with the existing ALQ-172(V)1 installations on the AC-130U and the MC-130H aircraft. The ALQ-196 LBJ, if used as part of the integrated aircraft system, shall utilize the 400 Hz electrical power from the Left and/or Right AC buses only. The maximum AC load of any generator shall not exceed 50% of its rated capacity during normal electrical system operations under any condition below:

CONDITION

BUS MAXIMUM CAPACITY

ALL

120 KVA for 5 seconds

INFLIGHT

90 KVA continuous

GROUND

60 KVA continuous/90 KVA for 5 minutes

  1. (U) Maximum DC Loads: The Enhanced ALQ-172 and LBJ to aircraft 28V DC interface(s) shall not cause the sourceís rated capacity to be exceeded.

3.1.2.6 (U) On-board Vulnerability: LBJ antenna installation shall provide sufficient isolation with respect to its own components to meet its operational requirements. LBJ installation shall prevent interference to/from other onboard subsystems from direct or skin conducted radiation.

3.1.2.7 (U) System Performance: The LBJ installation shall meet the requirements of this SRD including Appendix A.

3.1.2.7.1 (U) LBJ Field of View: The LBJ installation shall minimize fuselage, wing, tail or other external structure blockage of the LBJ coverage.

3.1.2.8 (U) Aircraft Pressurization:

3.1.2.8.1 (U) Leakage Rate: Any penetration of the pressure vessel shall not cause the leakage rate to exceed the limits as defined in T.O. 1C-130H-2-10 for the MC-130H or Rockwell Acceptance Test Procedure LL509100 for the AC-130U.

3.1.2.8.2 (U) Proof Pressure: Following air vehicle modification, the pressurized enclosure shall be capable of withstanding proof pressure levels as defined in the respective aircraft system specifications.

3.1.2.9 (U) Growth Capacity:

3.1.2.9.1 (U) Integrated Electronic Warfare (EW) Bus: The integration of the Enhanced ALQ-172 and LBJ shall provide the capability to be integrated to an avionics bus for a future EW bus upgrade.

3.1.2.9.2 (U) Monopulse and Continuous Wave (CW) Countermeasures: The integration of the Enhanced ALQ-172 and LBJ shall provide the capability and all interfaces required to serve as Techniques Generator(s) for future Monopulse and CW Countermeasures upgrades.

3.1.2.9.3 (U) Consolidated EW Display: The installation of the Enhanced ALQ-172 and LBJ shall preserve sufficient console space at the Electronic Warfare (EW) Officerís Crew Station and provide the interfaces required for the future installation of a consolidated EW display subsystem.

3.1.3 (U) Service Life: The integrated aircraft system, excluding the Group B, shall have a service life of 30,000 hours using the AC-130U and MC-130H System Specification defined mission profiles. New, modified, and affected structure shall be designed to achieve the desired service life. Installation of the Enhanced ALQ-172 and LBJ shall not shorten the service lives of the AC-130U and MC-130H aircraft.

3.2 (U) Characteristics: The integrated aircraft system shall be designed, maintained, and operated to provide a safe, durable, damage tolerant, fault tolerant, fatigue resistant, and corrosion resistant platform that functions to meet the intended missions and withstands external and induced environments to which the air vehicle may be exposed.

3.2.1 (U) Physical Characteristics

3.2.1.1 (U) Mass Properties: The arrangement of the equipment for the integrated aircraft system shall be such as to maintain aircraft center of gravity (CG) within limits throughout all phases of the mission without the use of aircrew workaround procedures. The CG shall be controlled within limits by using the fuel management and payload loading procedures required to meet the mission. The installation of the Enhanced ALQ-172 and LBJ shall not cause the aircraft to exceed any of the current AC-130U or MC-130H weight limitations or restrictions.

3.2.1.2 (U) Structural Integrity: The SOF integrated aircraft system shall have sufficient structural integrity, based on the original design criteria, to insure optimum system performance in its operating environment over its service life. All new/modified safety-of-flight, maintenance critical, and mission critical structures, which are flight and/or pressure load design driven, shall have static margins of safety greater than or equal to 0.25 if not structurally proof tested to ultimate load. The Rremaining aircraft components (not on a critical parts list, crash load design driven, and previous existing structure) shall not be degraded below 0.0 (positive) static margin of safety.

3.2.2 (U) Environmental, Safety, and Health (ESH)

3.2.2.1 (U) System Safety: Safety hazards as classified in accordance with MIL-STD-882 shall be eliminated or controlled to an acceptable level of risk. Selection of appropriate integrated aircraft system equipment design features to adequately control or eliminate hazards shall be given precedence over corrective or protective feature which increase the integrated aircraft systemís complexity.

3.2.2.1.1 (U) Hazardous Materials: The integrated aircraft system, components, and support items shall be designed to minimize the introduction of hazardous or pollutant materials to operation/support personnel and the environment (DOSS 4210.15).

3.2.2.1.2 (U) Radiation Hazards: Radiation hazards associated with the installed Enhanced ALQ-172 and LBJ shall be identified and mitigated IAW MIL-STD-882 and AFOSH Std 48-9.

3.2.2.2 (U) Crashworthiness: Crashworthiness (placement and design of components) shall be considered in the safety features for personnel survival in the event of a crash. Internally or externally mounted equipment shall be designed to withstand crash loads without constituting a personal or safety hazard outside those defined above. Crash loads shall be as specified in 3.2.4.2.2. The equipment and mounting shall be designed to retain the equipment in place under crash conditions. Operations personnel and maintenance factors shall be included in the selection of safety design features.

3.2.2.3 (U) Design and Construction: Equipment shall be designed and constructed to prevent injury to personnel and equipment during installation, test, operation, maintenance, and repair.

3.2.3 (U) Supportability

3.2.3.1 (U) Reliability: The Mean Time Between Critical Failures (MTBCF) for the LBJ including the install shall be no less than 100 hours. The Enhanced ALQ-172 and LBJ installation shall not have any adverse impacts on the reliability of other aircraft systems. As a goal, the MTBCF should be greater than 120 hours. MTBCF as used in this SRD means the average time between all hardware and software critical failures occurring during mission and non-mission time. Critical failures occur when mission essential systems become inoperable or operate outside their specified range of performance.

3.2.3.2 (U) Maintainability: The Mean Repair Time (MRT) for the LBJ aircraft modification shall not exceed 2.0 hours. The maximum time to repair the modification shall be 6.0 hours or less. The Enhanced ALQ-172 and LBJ installation shall not have any adverse impacts on the maintainability of other aircraft systems. MRT as used in this SRD means the total on-equipment repair time to return the integrated aircraft system to full operational capability.

3.2.3.2.1 (U) Diagnostics: The installation of the Enhanced ALQ-172 and LBJ shall provide ready physical access to all integrated diagnostics data through the existing MLV connector. The LBJ integrated diagnostics shall have the ability to unambiguously isolate to the faulty unit 95 percent of the time; the built in test false alarm rate shall be less than 5 percent. As a minimum, the LBJís diagnostics shall be capable of identifying 95 percent of all critical faults with an objective of 100 percent. The Enhanced ALQ-172 and LBJ integration shall be capable of downloading maintenance data and performing flight line reprogramming via the existing MLV connector.

3.2.3.2.1.1 (U) Reprogrammability: The LBJ shall be 100 percent flightline reprogrammable. The emitter identification (EID) and operational flight program (OFP) shall be flightline reprogrammable in 3.0 hours or less.

3.2.3.2.1.2 (U) Support Equipment: Support equipment (SE) selection shall maximize the use of existing SE and the use of commercial off the shelf items. The variety and number of special tools and test equipment required to maintain the equipment shall be held to a minimum. When special tools are required, the tools shall be provided. Cable extenders shall be provided if required. The LBJ installation shall not require new SE for Organizational Level removal and installation.

3.2.3.3 (U) Levels of Maintenance: All integrated aircraft system components should be repairable under the current ALQ-172 three level maintenance concept. Routine periodic maintenance inspection intervals shall not be impacted. Ease of access for inspection and removal/replacement shall be provided. All Enhanced ALQ-172 and LBJ LRUs and spares shall provide a 100 percent common configuration and be interchangeable with like LRUs on similarly equipped SOF aircraft.

3.2.3.3.1 (U) Organizational Maintenance: Organizational maintenance consists of fault detection & isolation, faulty component removal & replacement, and system checkout. Maintenance personnel shall use Built in Test (BIT) to facilitate LBJ maintenance and verify equipment condition and operability. Adjustments and alignments shall not be required after LRU replacement. The equipment installation shall be designed to permit modular replacement without removal of adjacent modules. The integrated aircraft system installation shall not interfere with removal/replacement of other aircraft systems.

3.2.3.4 (U) Maintenance Personnel

3.2.3.4.1 (U) Environment: The integrated aircraft system shall be capable of being maintained in worldwide conditions to include nuclear, chemical, or biological environments by personnel wearing the required protective gear.

3.2.3.4.2 (U) Manpower: The integrated aircraft system shall not place additional manpower or personnel requirements on the user or USSOCOM. The integrated aircraft system shall not require qualitative or quantitative changes to the support segment of the force structure.

3.2.4 (U) Environmental Conditions: The integrated aircraft system shall be designed and constructed to resist any individual or probable combination of the service condition demands specified herein without mechanical or electrical damage or performance degradation. Unless otherwise specified, these requirements shall apply for storage, non-operation, operating, stand by, test, and transmit.

3.2.4.1 (U) Natural Environment. The modifications shall meet the following requirements of this SRD while operating in the worldwide conditions.

3.2.4.1.1 (U) Lightning Protection: The installation of the LBJ shall not increase the inherent susceptibility of the aircraft to lightning nor present a hazard to the aircraft, other equipment, or personnel. Subsystems which are external to the aircraft structure shall be protected against the direct effects of lightning as defined in Paragraph 5.4 and Figure 1 of MIL-STD-464. The integrated aircraft system shall be designed to prevent interference due to precipitation static charging.

3.2.4.1.2 (U) Temperature and Altitude: The integrated aircraft system shall meet the requirements of this SRD while operating in temperature and altitude conditions consistent with the equipment qualifications and the individual aircraft environments.

3.2.4.1.3 (U) Water Intrusion and Rain Erosion: The integrated aircraft system shall not be damaged when subjected to blowing rain and shall operate without degradation during a TBD rain rate throughout the aircraft operational flight envelope..

3.2.4.1.4 (U) Humidity: The integrated aircraft system shall be capable of withstanding high and low humidity environmental conditions.

3.2.4.1.5 (U) Salt Atmosphere: The integrated aircraft system shall provide for operations without degraded performance in salt atmosphere.

3.2.4.1.6 (U) Sand and Dust: The integrated aircraft system shall be capable of withstanding the sand and dust environment for ground operations in close proximity to aircraft operating over unpaved surfaces without degraded performance.

3.2.4.2 (U) Induced Environment: The integrated aircraft system shall meet the requirements of this SRD while operating in its induced environment. Specifically, the man-made (non-threat) induced environmental conditions in which the air vehicle and all its components must function are as follows:

3.2.4.2.1 (U) Vibration: The integrated aircraft system shall operate properly when subjected to the induced vibration levels encountered throughout the mission profiles identified in the AC-130U and MC-130H System Specifications. The integrated aircraft system shall meet all performance requirements while subjected to functional vibration levels. The system shall meet all performance requirements following exposure to endurance level vibrations. The TFD 94-1644 data are worst case for the AC-130U and they shall also apply to the MC-130H integrated aircraft system design. Propeller and gunfire vibration shall be considered as narrowband random excitation centered at the fundamental and harmonic frequencies.

3.2.4.2.2 (U) Load Factors: The installation of the Enhanced ALQ-172 and LBJ shall:

Operate during accelerations: Per AC-130U and MC-130H design parameters.

Operate after accelerations: Per AC-130U and MC-130H design parameters.

Crash loads: All fixed and removable equipment and their subcomponent installations, should be able to withstand the aircraft design load factors or the following load factors, whichever are greater:

Longitudinal: 9.0 forward, 1.5 aft

Lateral: 1.5 right and left

Vertical: 4.5 down, 2.0 up

3.2.4.2.3 (U) Acoustic Noise: The integrated aircraft system shall operate properly when subjected to the acoustical noise levels encountered throughout the mission profiles identified in the AC-130U and MC-130H System Specifications. Rockwell Report NA-94-1790 provides the worst case levels which shall apply to both the AC-130U and MC-130H integrated aircraft system designs.

3.2.4.2.4 (U) Gunblast: For the AC-130U only, externally mounted LRUs shall withstand the pressure pulses from normal operational firing combinations of the 25mm, 40mm, and 105mm guns at the location on the aircraft appropriate to the mountings the LRU. The magnitude of the gunblast shall be that of the pointing and firing rate of each gun that produces the maximum pressure pulses, or resonant conditions, within or on the LRU. The possible combinations of firings are: 25mm & 40 mm; 25mm & 105mm; 40mm & 105mm; and each singly (25mm, 40mm, 105mm).

3.2.4.2.5 (U) Fluids: The integrated aircraft system shall be capable of withstanding exposure to the following fluids without permanent damage or degradation to performance.

a) Jet fuel,

b) Hydraulic fluid, and

c) De-icing and anti-icing fluids conforming to SAE Type 1 and Type 2 applied to the system exterior at high pressure at a temperature of 150F.

3.2.4.2.6 (U) Foreign Object Damage (FOD).

3.2.4.2.6.1 (U) Ground Conditions: Externally mounted LRUs shall be installed in locations that minimize the impact of foreign objects associated with takeoff, landing, or ground operations while maximizing coverage.

3.2.4.2.6.2 (U) Bird FOD: The integrated aircraft system shall be fully operational after impact with a 4.5 ounce bird and shall survive (or indicate a failure if appropriate) after impact with a 4 pound bird at maximum cruise of 325 knots true air speed. Survival shall be defined to be economically repairable and not a hazard to the aircraft, other equipment and personnel.

3.2.4.2.7 (U) Electromagnetic Environmental Effects

3.2.4.2.7.1 (U) Electromagnetic Compatibility (EMC): The Enhanced ALQ-172 and LBJ installation shall be designed to meet the requirements of MIL-STD-464 Paragraphs 5.2, 5.7.1, 5.7.2, 5.8, 5.10 through 5.10.2, and 5.10.4.

3.2.4.2.7.2 (U) Radio Frequency (RF) Compatibility. Subsystems shall exhibit RF compatibility among all antenna-connected equipment, subject to mission requirements. Blanking interfaces shall be provided to and from other on-board systems as required.

3.2.4.2.8 (U) Air Flow Field: System components which alter the aircraft outer mold line shall not create an unacceptable aerodynamic environment. Flow fields adjacent to the chaff and flare dispensers shall not be impacted with regard to the performance of the dispensers. Paratrooper deployment and retrieval or Combat Talon MC-130H shall not be adversely impacted. The resulting aerodynamic environment shall not shorten the life and/or the reliability of the AC-130U gun seals.

4.0 (U) QUALITY ASSURANCE PROVISIONS

4.1 (U) GENERAL: This section specifies qualification and acceptance requirements, that verify the system level requirements of Section 3 have been met. Section 4 to Appendix A of this SRD specifies the verification methods for its Section 3 requirements.

4.1.1 (U) Responsibility for Inspection, Analysis, and Testing: Unless otherwise specified, the contractor is responsible for the performance of all inspection, analysis, demonstration, and testing requirements specified in the contract. The procuring activity reserves the right to witness any verification at its option.

4.1.1.1 (U) Records: The quality management system shall establish and require the maintenance of, a means of identifying, collecting, indexing, filling, storing, maintaining, retrieving, and disposing of pertinent quality documentation and records, as appropriate, in accordance with the best commercial practice.

4.1.2 (U) Methods of Verification: Verification of system requirements of Section 3 shall be accomplished by inspection, analysis, demonstration, test, or process control (as defined below), or a combination thereof.

a. Inspection. Inspection is defined as a visual verification that the system (including system documentation) complies with specification requirements.

b. Analysis. Analysis is defined as verification that specification requirements have been met by technical evaluation of equations, charts, reduced data, etc. This does not include the normal analysis of data generated during ground or flight testing.

c. Demonstration. Demonstration is a verification method whereby success is determined by observation. Also included in this category are tests that require simple quantitative measurements such as dimensions, time to perform, etc.

d. Test. Test is defined as verification of the specification requirements through the application of established test procedures within specified environmental conditions and subsequent compliance confirmation through analysis of the data generated. This requirement may be fulfilled by submission of data which demonstrates the required test has been successfully completed.

e. Process Control.: Process Control is the application of best commercial practices to eliminate product variation and the assignable causes in order to prevent recurrence.

4.1.3 (U) Quality Conformance Inspections: Systems, components and test apparatus shall be subject to inspection by authorized Government personnel who will be given the necessary information and facilities to determine conformance with this SRD. Quality evidence and records thereof shall be maintained as required by the applicable contract.

4.1.4 (U) Test Article Configuration: The configuration of each test article shall be identified by individual parts lists. All verification shall be accomplished using production configuration hardware and manufacturing processes.

4.2 (U) In-Process Verification Measurement: The following system level in-process verification requirements shall be successfully accomplished prior to their associated demonstration milestone as specified on the Contractor generated Integrated Master Plan/Schedule (IMP/IMS). Technical criteria and supporting technical performance measure (TPM) tracking parameters, including acceptable tolerances are specified in the Enhanced ALQ-172 and Low Band Jammer & ALR-69 Integration IMP/IMS.

4.2.1 (U) Interface Control Documents (ICDs): Development of required interface control documents shall be verified by a combination of inspection, analysis, demonstration, and/or test of the internal and external interfaces. ICDs are considered complete when the required interface verification procedures are defined and documented.

4.2.2 (U) Logistic Support Analysis (LSA) Integration: Design integration of user supportability requirements shall be verified by analysis of updates to AC-130H ALQ-172 LSA data and MC-130E ALQ-196 LSA data (if applicable) during development. This data shall be updated during the latter phase of development. The supportability requirements of 3.2.2 and 3.2.3 & subsections shall be demonstrated during operational tests and evaluations.

4.2.3 (U) Antenna Pattern and Isolation Test: Prior to Preliminary Design Review, antenna patterns and isolation for the proposed AC-130U and MC-130H LBJ antenna installation locations should be verified by testing. Antenna isolation levels shall be in concert with the appropriate TPMs (exit criteria) identified in the IMP/IMS.

4.2.4 (U) Jammer Effectiveness Analysis and/or Test: Prior to Critical Design Review, preliminary analysis and/or hardware-in-the loop (HITL) laboratory testing of jammer effectiveness for the proposed AC-130U and MC-130H Enhanced ALQ-172 and LBJ installation should be accomplished against appropriately validated, high fidelity threat models/simulators. Analytical and/or HITL effectiveness results shall be in concert with the appropriate TPMs (exit criteria) identified in the IMP/IMS.

4.2.5 (U) Pre-Flight Installed Performance Test: Prior to the first test flight of the modified aircraft, the effective radiated power, installed sensitivity, and direction finding accuracy for the AC-130U and MC-130H installations should be verified by testing.

4.3 (U) Quality Conformance: This section outlines the method(s) of verification for each Section 3, Appendix A, and Appendix B integrated aircraft system requirement. Table 4.3 is a sample cross reference matrix showing the possible verification method(s) to be used for each requirement of Section 3, Appendix A, and Appendix B. The detailed verification requirements as identified in the Contractor generated specification shall be based on this cross reference matrix.

 

Table 4.3 Sample Requirements Verification Matrix

N/A - Not Applicable 1 - Inspection

             

2 - Analysis 3 - Demonstration

             

4 - Test 5 - Process Control

             
 

Applicable Standard

Verification Method

   

N/A

1

2

3

4

5

3.0 (U) REQUIREMENTS

 

X

         

3.1 (U) SYSTEM DEFINITION

 

X

         

3.1.1 (U) System Description

   

X

X

X

X

 

3.1.2 (U) Aircraft Integration Requirements

   

X

X

X

X

 

3.1.2.1 (U) Aircraft Modification Requirements

     

X

 

X

 

3.1.2.1.1 (U) Relocation of Existing Systems

     

X

 

X

 

3.1.2.2 (U) Computer/Avionics Interface Definition

   

X

       

3.1.2.2.1 (U) Data Bus Interface

   

X

       

3.1.2.2.2 (U) Control and Auxiliary Processors

     

X

 

X

 

3.1.2.3 (U) Mechanical Interfaces

 

X

         

3.1.2.3.1 (U) Enhanced ALQ-172 and LBJ Mounting

   

X

       

3.1.2.3.2 (U) LRU Mounting Provisions

   

X

 

X

   

3.1.2.4 (U) Thermal Interfaces

   

X

X

X

   

3.1.2.5 (U) Electrical Power Subsystem

 

X

         

3.1.2.5.1 (U) Power Quality

     

X

X

   

3.1.2.5.2 (U) Maximum AC Loads

     

X

X

   

3.1.2.5.3 (U) Maximum DC Loads

     

X

X

   

3.1.2.6 (U) On-board Vulnerability

     

X

X

X

 

3.1.2.7 (U) System Performance

     

X

 

X

 

3.1.2.7.1 (U) LBJ Field of View

     

X

 

X

 

3.1.2.8 (U) Aircraft Pressurization

             

3.1.2.8.1 (U) Leakage Rate

         

X

 

3.1.2.8.2 (U) Proof Pressure

         

X

 

3.1.2.9 (U) Growth Capacity

 

X

         

3.1.2.9.1 (U) Integrated Electronic Warfare (EW) Bus

   

X

 

X

   

3.1.2.9.2 (U) Monopulse and Continuous Wave (CW) Countermeasures

   

X

 

X

   

3.1.2.9.3 (U) Consolidated EW Display

   

X

 

X

   

3.1.3 (U) Service life

     

X

 

X

 

3.2 (U) Characteristics

 

X

         

3.2.1 (U) Physical Properties

 

X

         

3.2.1.1 (U) Mass Properties

     

X

X

   

3.2.1.2 (U) Structural Integrity

     

X

 

X

 

3.2.2 (U) Environmental, Safety, and Health (ESH)

 

X

         

3.2.2.1 (U) System Safety

     

X

     

3.2.2.1.1 (U) Hazardous Materials

     

X

     

3.2.2.1.2 (U) Radiation Hazards

     

X

     

3.2.2.2 (U) Crashworthiness

     

X

     

3.2.2.3 (U) Design and Construction

     

X

     

3.2.3 (U) Supportability

 

X

         

3.2.3.1 (U) Reliability

     

X

X

   

3.2.3.2 (U) Maintainability

     

X

X

   

3.2.3.2.1 (U) Diagnostics

     

X

X

   

3.2.3.2.1.1 (U) Reprogrammability

     

X

X

   

3.2.3.2.1.2 (U) Support Equipment

     

X

X

   

3.2.3.3 (U) Levels of Maintenance

     

X

X

   

3.2.3.3.1 (U) Organizational Maintenance

       

X

   

3.2.3.4 (U) Maintenance Personnel

 

X

         

3.2.3.4.1 (U) Environment

     

X

X

   

3.2.3.4.2 (U) Manpower

   

X

       

3.2.4 (U) Environmental Conditions

     

X

X

   

3.2.4.1 (U) Natural Environment

 

X

         

3.2.4.1.1 (U) Lightning Protection

     

X

     

3.2.4.1.2 (U) Temperature and Altitude

     

X

X

X

 

3.2.4.1.3 (U) Water Intrusion and Rain Erosion

     

X

X

X

 

3.2.4.1.4 (U) Humidity

     

X

X

X

 

3.2.4.1.5 (U) Salt Atmosphere

     

X

X

X

 

3.2.4.1.6 (U) Sand and Dust

     

X

X

X

 

3.2.4.2 (U) Induced Environment

 

X

         

3.2.4.2.1 (U) Vibration

     

X

 

X

 

3.2.4.2.2 (U) Load Factors

     

X

 

X

 

3.2.4.2.3 (U) Acoustic Noise

     

X

 

X

 

3.2.4.2.4 (U) Gunblast

     

X

X

X

 

3.2.4.2.5 (U) Fluids

     

X

     

3.2.4.2.6 (U) Foreign Object Damage (FOD).

 

X

         

3.2.4.2.6.1 (U) Ground Conditions

   

X

X

     

3.2.4.2.6.2 (U) Bird FOD

     

X

 

X

 

3.2.4.2.7 (U) Electromagnetic Environmental Effects

 

X

         

3.2.4.2.7.1 (U) Electromagnetic Compatibility (EMC)

     

X

 

X

 

3.2.4.2.7.2 (U) Radio Frequency (RF) Compatibility

     

X

X

   

3.2.4.2.8 (U) Air Flow Field

     

X

X

X

 

A3.0 (U) REQUIREMENTS

             

A3.1 (U) LOW BAND JAMMER SYSTEM PERFORMANCE

             

A3.1.1 (U) Frequency Range

             

A3.1.2 (U) LBJ Spatial Coverage

             

A3.1.2.1 (U) Azimuth

             

A3.1.2.2 (U) Elevation Coverage

             

A3.1.2.2.1 (U) AC-130U Antenna Elevation Coverage

             

A3.1.2.2.2 (U) MC-130H Antenna Elevation Coverage

             

A3.1.2.3 (U) Direction Finding (DF) Accuracy

             

A3.1.3 (U) System Sensitivity

             

A3.1.4 (U) Low Band Jammer Effectiveness Characteristics

             

A3.1.4.1 (U) Jamming Elevation Coverage

             

A3.1.4.2 (U) Low Band Jammer Effectiveness

             

A3.1.4.3 (U) Multiple Engagement Capability

             

A3.2 (U) HIGH BAND JAMMER REQUIREMENTS

             

A3.2.1 (U) Operational Effectiveness

             

A3.2.2 (U) AC-130U Requirements

             

B3.0 (U) REQUIREMENTS

             

B3.1 (U) System Definition

             

B3.1.1 (U) System Description

             

B3.1.2 (U) Mission Performance

             

B3.1.3 (U) Threat

             

B3.2 (U) Performance Characteristics

             

B3.2.1 (U) The Installed ALR-69 RWR System Requirements

             

B3.2.1.1 (U) Reprogrammability

             

B3.2.1.2 (U) Frequency Range

             

B3.2.1.3 (U) Elevation Coverage

             

B3.2.1.4 (U) MUX Bus Capability

             

B3.2.1.5 (U) Display and Control Capability

             

B3.2.1.6 (U) Audio Capability

             

B3.2.1.7 (U) Test and Evaluation

             

B3.2.2 (U) Reliability

             

B3.2.3 (U) Maintainability

             

B3.2.3.1 (U) Maintenance Concept

             

B3.3 (U) Design and Construction

             

B3.3.1 (U) Hazardous Materials

             

B3.3.2 (U) System Security

             

B3.4 (U) Logistics

             

B3.5 (U) Precedence

             

5.0 (U) PREPARATION FOR DELIVERY: Not Applicable.

6.0 (U) Notes: This section contains information of a general or explanatory nature, and no requirements appear herein. It contains non-contractually binding information designed to assist in determining the applicability of the SRD and the selection of appropriate type, grade, or class of the configuration item.

6.1 (U) Definitions: Not Applicable.

6.2 (U) Abbreviations: Not Applicable.

6.3 (U) Miscellaneous Notes.

  1. (U) Proprietary Data: The data sources referenced on the ALQ-196 in Section 2.2 are proprietary. Access to and release of the documents can be obtained by contacting:

Sanders, A Lockheed Martin Company

95 Canal Street

Nashua, NH 03061

c/o Adam Marcinuk, NCA-3303

or

E-Mail: adam.j.marcinuk@lmco.com

6.3.2 (U) Enhanced ALQ-172 and Low Band Jammer Installation Baseline: The baseline installation of the Enhanced ALQ-172 and LBJ on the AC-130U and MC-130H for configuration control is defined as the configuration after successful completion of the Physical Configuration Audit (PCA).

6.3.3 (U) Physical Configuration Audit: The Government and Contractor will conduct the PCA to examine the "as-built" configuration of the Enhanced ALQ-172 and LBJ installation against its design documentation.

6.3.4 (U) Configuration Control: The integrating contractor shall extend configuration control to cover hardware, except for Group B, and documentation. The Contractor shall maintain traceability and currency of the baseline and consistency among all project documentation and system equipment.

(U) After the baseline has been established, all contractor generated changes including those that impact form, fit and function (F3), require formal approval by the Government. The Government configuration control process will ensure that all system design changes are integrated into maintenance and training documentation whether or not the change impacts F3. The Contractor shall submit Design Change Notices (DCN) to the Government prior to implementation of changes into the Logistics Support Analysis Record (LSAR) Parts Master File and the provisioning technical documentation package.

 

APPENDIX A

LOW BAND & HIGH BAND JAMMER PERFORMANCE REQUIREMENTS

(PROVIDED AS SEPARATE CLASSIFIED DOCUMENT)

APPENDIX B

AN/ALR-69 CLASS IV RADAR WARNING RECEIVER INTEGRATION ON THE AC-130U

(PROVIDED AS SEPARATE UNCLASSIFIED DOCUMENT)