Section J_Attach 2_F-15EX Propulsion System Spec_Final RFP 5 Feb 21.pdf

FA8626-21-R-0002

Section J, Attachment 2 i

PROPULSION SYSTEM SPECIFICATION

For The

F-15EX Propulsion System

Version 5.0

21 January 2021

AFLCMC / LPA

Propulsion Acquisition Division

Fighter Engine Acquisition Branch in association with the

AFLCMC / WAQ

F-15 System Division

F-15EX Integrated Weapon System (IWS) Program Office (PO)

Wright-Patterson AFB, Ohio 45433 ii

THIS PAGE INTENTIONALLY BLANK

iii

CHANGE HISTORY

Change Description Version Date

Original Draft Document 1.0 26 August 2020

Draft RFP Release Version 2.0 30 September 2020

Draft RFP 2 Release Version 3.0 16 October 2020

Final Draft RFP Release Version 4.0 16 November 2020

Final RFP Release Version 5.0 21 January 2021 iv v

TABLE OF CONTENTS

1.0 INTRODUCTION

1.1 Scope

1.2 Purpose

1.3 Overview

2.0 APPLICABLE DOCUMENTS

2.1 General

2.2 Government Documents

2.2.1 Military Specification, Standards, and Handbooks

2.2.2 Other Government Documents

2.3 Non-Government Documents

2.4 Order of Precedence

3.0 SYSTEM REQUIREMENTS

3.1 Engine System

3.1.1 Engine Specification

3.1.2 Engine Certification

3.1.3 Engine Interface Control

3.1.4 Engine Data Recording Capability

3.2 Engine Integration

3.2.1 Aircraft Interface Control

3.2.2 Aircraft Airworthiness

3.2.3 Other Integration

4.0 SYSTEM VERIFICATION

4.1 Verification Overview

4.1.1 Verification Approach

4.1.2 Verification Location

4.1.3 Verification Responsibility

4.1.4 Verification Cross Reference Matrix (VCRM)

4.2 Verification Methods

4.2.1 Not Applicable (N)

4.2.4 Inspection (I)

4.2.5 Analysis (A)

4.2.6 Demonstration (Demo)

4.2.7 Test

4.3 Requirements Verifications

5.0 DEFINITIONS

6.0 ACRONYMS AND ABBREVIATIONS

vi

LIST OF TABLES

Table 2- 1 Military Specifications, Standards, and Handbooks

Table 2- 2 Other Government Documents

Table 2- 3 Non-Government Reference Documents

Table 4- 1 Verification Cross Reference Matrix (VCRM)

1.0 INTRODUCTION.

1.1 Scope. This Propulsion System Specification presents the technical requirements for prime contractor contribution to the F-15EX Propulsion System. The F-15EX Propulsion System provides current existing engines for use in the F-15EX aircraft as Government Furnished

Equipment (GFE). The F-15EX aircraft are intended to support Air Combat Command (ACC) mission needs as replacements for the aging F-15C/D aircraft. Any system requirements outside the prime contractor’s responsibility are developed separately.

1.2 Purpose. The purpose of this Propulsion System Specification is to document the

Government’s system-level performance, functional, interface, integration and support requirements, for the prime contractor to integrate, certify, produce and deliver a propulsion system that contractually meet the full content of the requirements herein. These requirements are derived from F-15EX aircraft program-level requirements. This Propulsion System

Specification is the Government’s model contract specification.

1.3 Overview. Section 1.0 provides background and instructional information. The documents in section 2.0 list the specific references called-out in the requirements of section 3.0. Section

2.0 also contains instructional information. Contractual technical requirements are contained in

Section 3.0. Definitions, Acronyms and Abbreviations, and Appendices are part of the requirements and information where used and referenced herein. All requirements herein are considered the minimum mandatory requirements. There are no requirements identified as

Objectives. Any designated ‘Notes’ are additional clarifications and are therefore not requirements. Section 4.0 contains instructional content and contractual verification methods and sub-methods required to substantiate that the requirements have been met by the contractor’s solutions.

2.0 APPLICABLE DOCUMENTS.

2.1 General. The following documents (with revisions, versions, changes notices, dates, and titles) form part of the system specification only to the extent specified herein. Only cited reference documents and one (1) tier down, apply to this System Specification.

2.2 Government Documents.

2.2.1 Military Specification, Standards, and Handbooks.

Table 2- 1 Military Specifications, Standards, and Handbooks

Document Date Title

MIL-HDBK-516C

(with Change Notices CN-1 through CN-7)

12 December 2014

(23 May 2016, 23 May 2016, 23 May 2016, 23 May 2016, 9 November 2016, 11 April

2018, 4 December 2019)

Department of Defense

Handbook: Airworthiness

Certification Criteria

2.2.2 Other Government Documents.

Table 2- 2 Other Government Documents

Document Date Title

AWB-330A 17 April 2018 United States Air Force (USAF)

Airworthiness Bulletin (AWB) -

330A

F-15EX System Requirements

Document

1 July 1019 F-15EX System Requirements

Document (SRD)

2.3 Non-Government Documents.

Table 2- 3 Non-Government Reference Documents

Document Date Title

Contract Number FA8634-20-F-0022

Delivery Order 1 F-15EX

20 October 2020 F-15EX/F100-PW-229

Propulsion System Supplement

Contract Number FA8634-20-F-0022

Delivery Order 1 F-15EX

20 October 2020 F-15EX/F110-GE-129 Propulsion

System Supplement

2.4 Order of Precedence. In the event of a conflict between this System Specification and the reference documents cited herein, the text of the System Specification takes precedence.

Nothing in this System Specification, including the referenced documents, supersedes laws and regulations, unless a specific exemption or waiver has been obtained.

3.0 SYSTEM REQUIREMENTS.

3.1 Engine System.

3.1.1 Engine Specification. The F-15EX Propulsion System shall meet the appropriate prime contractor-provided engine specification.

3.1.2 Engine Certification. The F-15EX Propulsion System shall have sufficient attributes to successfully obtain and maintain an approved Propulsion - Military Type Certificate (P-MTC) utilizing the processes of United States Air Force (USAF) Airworthiness Bulletin (AWB) AWB-

330A (Propulsion System Type Certification), with Government accepted risks, if any.

3.1.3 Engine Interface Control. The F-15EX Propulsion System shall meet the appropriate sections of the F-15EX Interface Control Document (ICD) on the engine-side of the interfaces.

3.1.4 Engine Data Recording Capability. The F-15EX Propulsion System shall have data recording capability. Data shall be continuously recorded through an entire sortie, and shall be adequate for the purpose of engine trending and diagnostics, with consistent snapshots taken during the same flight regime (e.g. takeoff), and sufficient data surrounding engine faults.

3.2 Engine Integration.

3.2.1 Aircraft Interface Control. The F-15EX Propulsion System shall meet the appropriate sections of the F-15EX ICD on the aircraft side of the interfaces.

3.2.2 Aircraft Airworthiness. The F-15EX Propulsion System shall have sufficient attributes to successfully obtain and maintain an approved aircraft-level airworthiness Military Type

Certificate (MTC), by meeting Technical Airworthiness Authority (TAA) approved airworthiness certification basis criteria requirements tailored from MIL-HDBK-516 relating to engine and engine integration effects only, with Government accepted risks, if any.

3.2.3 Other Integration. The F-15EX Propulsion System shall meet the requirements of the

F-15EX (aircraft system) System Requirements Document (SRD) that are applicable to the engine and integration interaction effects, and not otherwise specified through the requirements and reference documents herein.

4.0 SYSTEM VERIFICATION.

4.1 Verification Overview. Section 4.0 Verification contains the general methodology for verifying the system’s design, operation, and performance to meet all requirements established in

Section 3.0 System Requirements herein.

4.1.1 Verification Approach. The basis of any verification method is the root source that establishes the data used to support requirement compliance (e.g., if analysis of another program’s flight test data is used, then the verification method is flight test). The intent of the verification approach is to maximize the collaboration of integration, airworthiness certification, and operational evaluations, in order to optimize costs, schedule, and performance.

4.1.2 Verification Location. Prime contractor, sub-contractor, commercial, and Government owned facilities acceptable to the Government, are permitted for the application(s) intended.

4.1.3 Verification Responsibility. The prime contractor is responsible for planning, execution, successful completion, and reporting for all requirement compliance verifications. The

Government formal approval of verification documentation constitutes completion. The

Government reserves the right to require additional verification effort within the confines of the required verification methods and sub-methods. The Government reserves the right to participate in and witness any of the requirement verifications.

4.1.4 Verification Cross Reference Matrix (VCRM). The VCRM (Table 4-1) provides the cross reference between each Section 3.0 requirement and the associated minimum required verification methods and sub-methods (defined below).

4.2 Verification Methods. The verification methods are defined below. The methods are independent, but are sometimes used as formal complements to other verification methods, to support substantiation, or for completeness. The methods can also be used in combination with other verification methods to convert prior existing data to directly relevant verification data.

4.2.1 Not Applicable (N). This verification method is usually reserved for Section 3.0 requirement headers or title paragraphs that do not contain requirement threshold ‘shall’ statements or objective ‘should’ statements.

4.2.2 Previously Verified (P). The requirement, and system or component are the same as a previous baseline, with no additional verification required.

4.2.3 Similarity (s). Complete or partial verification of the equipment by similarity to previously qualified equipment. The similar item has operated within the conditions and requirements of this specification, and the new item does not incorporate differences that would invalidate this criteria. Items with verifications designated as ‘similarity’ in the VCRM that are found not to meet this definition, as determined by the Government, will be subject to the root verifications methods of the earlier legacy item (also see paragraph 4.1.1 above).

4.2.4 Inspection (I). This verification method consists of actual component, system, function, installation non-destructive examination (without special or complex equipment) by sensory means, simple physical manipulation, and simple measurement; including review of authenticated documentation.

4.2.5 Analysis (A). This verification method consists of an evaluation of components and systems interacting with their intended environment, using technical calculations and mathematical modeling based on physical laws and empirical data. Analysis can include design margins. Sensitivity, similarity, and failure effects analyses are examples of this method.

Analysis associated with refining test data is not part of this method.

4.2.6 Demonstration (Demo). This verification method consists of a non-instrumented operation of the actual component or system under specified controlled conditions on the air vehicle or in an equivalent environment, where functional success is determined on a qualitative or pass-fail basis. This involves more than the simple and non-complex Inspection method. This can be at a facility, on the ground, or in-flight. Sub-methods are as follows:

4.2.6.1 Laboratory Demonstration (l). This verification sub-method consists of a demonstration at an off-air vehicle ground-based facility with a simulated environment that is relevant to the requirement.

4.2.6.2 Ground Demonstration (g). This verification sub-method consists of a static on-air vehicle demonstration on the ground.

4.2.6.3 Flight Demonstration (f). This verification sub-method consists of a demonstration in-flight.

4.2.7 Test. This general group of sub-methods consists of quantitative measuring of the characteristics or performance of actual components or systems in controlled and intended conditions (real or representative). These sub-methods include analysis of the resulting data.

Sub-methods are as follows:

4.2.7.1 Laboratory Test (L). This verification sub-method consists of testing in an on- or off-air vehicle ground-based facility with a simulation of the environment that is relevant to the requirement.

4.2.7.2 Ground Test (G). This verification sub-method consists of on-air vehicle testing during ground-static conditions.

4.2.7.3 Safety-of-Flight (S). This verification sub-method consists of select off- and on-aircraft ground testing sufficient for Flight Test release.

4.2.7.4 Flight Test (F). This verification sub-method consists of on-air vehicle testing under dynamic ground, transitions between ground and flight, and flight envelope conditions.

4.3 Requirements Verifications. In accordance with the VCRM, Table 4-1 below, the verification methods cited, with their definitions above, verify each associated Section 3.0 requirement. The requirement is successfully verified when the Government confirms the full content of the requirement is met to the extent that the specific verification method or sub-method can provide.

Table 4- 1 Verification Cross Reference Matrix (VCRM)

Para. # Paragraph Title Demo Test

N P s I A l g f L G S F

3.0 SYSTEM REQUIREMENTS N

3.1 Engine System N

3.1.1 Engine Specification P s A L G

3.1.2 Engine Certification s A

3.1.3 Engine Interface Control A L S F

3.2 Engine Integration N

3.2.1 Aircraft Interface Control L S F

3.2.2 Aircraft Airworthiness s A L S

3.2.4 Other Integration s A L

5.0 DEFINITIONS.

F-15EX Propulsion System – Two 29,000 pound thrust class engines, engine computer software, and any required on aircraft components, including computer software, previously integrated on the F-15E, F-15SA, F-15QA, or F-15EX aircraft, which meets the requirements of the Contract

Section C engine specification.

Legacy – Prior Government inventoried equipment or systems integrated on other platforms.

Provide – Includes sufficient attributes for the system to meet the full content of the requirement therein.

6.0 ACRONYMS AND ABBREVIATIONS.

A Analysis (Verification Method)

ACC Air Combat Command

AFB Air Force Base

AFLCMC Air Force Life Cycle Management Center

AWB Airworthiness Bulletin

C Legacy Air-to-Air F-15 Single-Crew Aircraft Version Designation

D Legacy Air-to-Air F-15 Dual-Crew Aircraft Version Designation

Demo Demonstration (Verification Method)

E Legacy Multi-Role F-15 Dual-Crew Aircraft Version Designation

EX Aircraft Version Designation

F Fighter (aircraft designation) f Flight Demonstration

F Flight Test (Verification Sub-Method)

F Turbofan (engine designation) g Ground Demonstration (Verification Sub-Method)

G Ground Test (Verification Sub-Method)

GFE Government Furnished Equipment

I Inspection (Verification Method)

ICD Interface Control Document

IWS Integrated Weapon System l Laboratory Demonstration (Verification Sub-Method)

L Laboratory Test (Verification Sub-Method)

LPA Fighter Engines Branch Organizational Symbol

MIL Military

N Not Applicable (Verification Method)

P Previously Verified (Verification Method)

Para. Paragraph

P-MTC Propulsion – Military Type Certificate

PO Program Office s Similarity (Verification Method)

S Safety-of-Flight (Verification Method)

SRD System Requirements Document

U.S. United States (of America)

USAF United States Air Force

VCRM Verification Cross Reference Matrix

WAQ F-15 Program Organizational Symbol