Mil Hardnes Test

L SPECIFICATION: NDTS-1500K Lockheed Martin Aeronautics DATED: August 18 2004 Code Ident. 81755 SUPERSEDING: NDTS-1500J DATED: 9 September 1999

NDTS-1500K Dated: August 18 2004 Superseding NDTS-1500J Dated 9 September 1999

HARDNESS AND CONDUCTIVITY TESTING NONDESTRUCTIVE METHODS FOR VERIFYING HEAT TREAT

CONDITION

Contract No. F33657-88-00037

This document contains Technical Data considered to be a resource under 1-402b.3 and DoD Directive 5400.7-R and is not a "record" required to be released under the Freedom of Information Act.

Copyright© 2004 Lockheed Martin corporation


HARDNESS AND CONDUCTIVITY TESTING

NONDESTRUCTIVE METHODS FOR VERIFYING HEAT TREAT CONDITION

Contract No. F33657-88-00037


TABLE OF CONTENTS Section Title Page

1.0 SCOPE ...................................................................................................................1

2.0 APPLICABLE DOCUMENTS.................................................................................1

3.0 TEST METHODS....................................................................................................1

3.1 METHOD #1 - CONDUCTIVITY TESTING (ALUMINUM FORGINGS ONLY) ... 1 3.1.1 CRITICAL PARTS.............................................................................................. 1 3.1.2 NON-CRITICAL PARTS..................................................................................... 1

3.2 METHOD #2 - CONDUCTIVITY TESTING (ALUMINUM SHEET AND LESS THAN {0.750 INCH} THICK PLATE AND ALUMINUM BARS).......................... 2

3.3 METHOD #3 - CONDUCTIVITY TESTING ( {0.750 INCH} AND GREATER THICKNESS ALUMINUM PLATE AND BAR).......................................................2

3.4 METHOD #4 - CONDUCTIVITY TESTING (ALUMINUM EXTRUSIONS).............2

3.5 METHOD #5 - HARDNESS TESTING (6XXX TUBING, SHEET, EXTRUSION, AND ANY ALUMINUM ROD WITH A DIAMETER FROM ¼” {0.250”} TO {0.750”}).......................................................................................3

3.6 METHOD #6 - CONDUCTIVITY TESTING (0.750”OR GREATER DIAMETER ALUMINUM ROD).............................................................................................. 3

3.7 METHOD #7 - CONDUCTIVITY TESTING (FOR CERTAIN MATERIALS AT SELECTED OPERATIONS AS PRESCRIBED IN SECTION 4).......................... 3

3.8 METHOD #8 - CONDUCTIVITY TESTING (FOR CERTAIN MATERIALS AT SELECTED OPERATIONS AS PRESCRIBED IN SECTION 4).......................... 3

4.0 SCHEDULING........................................................................................................3

4.1 SCHEDULE INTRODUCTION ...............................................................................3 4.1.1 ALUMINUM ALLOYS..............................................................................................4 4.1.1.1 Scheduling Requirements for Suppliers of Aluminum Products.............................4

4.1.1.1(a) Suppliers of Aluminum Forgings.............................................................................4 4.1.1.1(b) Suppliers of Aluminum Raw Materials other than aluminum forgings or castings .4 4.1.1.1(c) Suppliers of Aluminum Castings ............................................................................5 4.1.1.1(d) Suppliers of Fabricated Parts ................................................................................5 4.1.1.1(e) Suppliers of Aluminum Cut Shapes........................................................................7 4.1.1.1(f) Suppliers of Aluminum Cut-to-Size Material...........................................................7 4.1.1.1(g) Processor Responsible for Anodize Operation on Fabricated Parts/details ..........8

4.1.1.2 Scheduling Requirements for LM Aero - Fort Worth Factory QA - Upon Issuance of Aluminum to Production ......................................................................8

4.1.1.3 Scheduling Requirements for LM Aero - Fort Worth Factory QA - After Solution Heat Treatment of Aluminum...................................................................9

4.1.1.4 Scheduling Requirements for LM Aero - Fort Worth Factory QA - After In-House Aging of Aluminum Wrought Products ....................................................9 4.1.1.5 Scheduling Requirements for LM Aero - Fort Worth Factory QA - After NC Machining of Aluminum (Not Heat Treated In-House) .....................................9 4.1.1.6 Scheduling Requirements for LM Aero - Fort Worth Factory QA -Prior to Stock ...10

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TABLE OF CONTENTS (Continued) Section Title Page

4.1.2 NON-ALUMINUM ALLOYS ....................................................................................11 4.1.2.1 Scheduling Requirements for Suppliers of Non-Aluminum Products.....................11 4.1.2.2 Scheduling Requirements for Factory QA- Upon Issuance of Non-Aluminum Material to Production.............................................................................................11 4.1.2.3 Scheduling Requirements for LM Aero - Fort Worth Factory QA- After Aging / Tempering to Final Heat Treat Condition ...................................................11 4.1.2.4 Scheduling Requirements for Factory QA -After Machining ..................................12 4.1.2.5 Scheduling Requirements for Non-Aluminum Alloys Prior to Stock, but Prior to Finish Application .................................................................................12

5.0 RECORDS..............................................................................................................12

5.1 RECORDING REQUIREMENTS FOR SUPPLIERS OF ALUMINUM FORGINGS, CASTINGS, MACHINED PARTS, CUT SHAPES, AND CUT-TO-SIZE MATERIAL AFTER TESTING PER 4.1.1.1...........................................................12 5.1.1 CRITICAL ALUMINUM PARTS [EXCLUDING CUT SHAPES]..............................12 5.1.2 NON-CRITICAL ALUMINUM PARTS [EXCLUDING CUT SHAPES] ....................12 5.1.3 CUT SHAPES AND 7475-T7351 PLATE PER FMS-3004.....................................13 5.1.4 ALUMINUM CUT-TO-SIZE MATERIAL..................................................................13 5.1.5 INSPECTION FOLLOWING ANODIZING PROCESS ...........................................13

5.2 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA FOLLOWING TESTING PER 4.1.1.2............................................13 5.2.1 RECORDING REQUIREMENTS UPON TESTING FOLLOWING ISSUANCE OF ALUMINUM.......................................................................................................13

5.3 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FOLLOWING TESTING PER 4.1.1.4.....................................................................13 5.3.1 RECORDING REQUIREMENTS FOR NON-CRITICAL ALUMINUM PARTS.......13 5.3.2 RECORDING REQUIREMENTS FOR CRITICAL ALUMINUM PARTS................13

5.4 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA AND SUPPLIERS FOLLOWING TESTING OF CRITICAL PARTS PER 4.1.1.5 ...............................................................................................13

5.5 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA AND SUPPLIERS FOLLOWING TESTING OF CRITICAL PARTS PER 4.1.1.6 ...............................................................................................13

5.6 RECORDING REQUIREMENTS FOR SUPPLIERS OF NON-ALUMINUM SUPPLIERS PRODUCTS AFTER TESTING PER 4.1.2.1....................................14 5.6.1 CRITICAL PARTS ..................................................................................................14 5.6.2 NON-CRITICAL PARTS .........................................................................................14

5.7 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA FOLLOWING TESTING OF NON-ALUMINUM PARTS PER 4.1.2.3.............14



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TABLE OF CONTENTS (Continued) Section Title Page

6.0 GENERAL INFORMATION....................................................................................14

6.1 SPECIFICATION TABLES.....................................................................................14

6.2 DEFINITION OF TERMS........................................................................................14 6.2.1 CASTINGS..............................................................................................................14 6.2.2 WROUGHT MATERIALS .......................................................................................14 6.2.3 FABRICATED PARTS ............................................................................................15 6.2.4 MANUFACTURING PROCESS..............................................................................15 6.2.5 SCHEDULING (Section 4)......................................................................................15 6.2.6 CRITICAL................................................................................................................15 6.2.7 NON- CRITICAL .....................................................................................................15

LIST OF TABLES

Table Title Page

I Aluminum Material Specifications and Corresponding Alloys........................16

II Steel and Non-Aluminum Specifications and Corresponding Alloys .............17

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CHANGE NOTICE

This document has been extensively reformatted with editorial revision to remove errors and provided additional information and clarification. For this reason, no change index has been generated.

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HARDNESS AND CONDUCTIVITY TESTING (NONDESTRUCTIVE METHODS FOR VERIFYING HEAT TREAT CONDITION)

1.0 SCOPE

1.1 This document establishes procedures for verifying the heat treat condition of metallic materials at, and for, Lockheed Martin Aeronautics (LM Aero) - Ft. Worth.

1.2 NDTS 1500 is incomplete without NDTS 1501 and NDTS 1502. These three segments are intended to act together as one indivisible document.

1.3 Hardness and Conductivity testing per this specification shall be performed when NDTS 1500 is called out by the LM Aero- Fort Worth drawing, specification, or any other document.

1.4 This document provides test method and location, test frequency, inspection personnel training and certification requirement, part acceptance/rejection guidelines, and record requirement.

2.0 APPLICABLE DOCUMENTS - The following documents form a part of this specification to the extent specified within. Unless otherwise specified, the document issue in effect on the date of the Purchase Order shall be applicable.

2.1 LM AERO DOCUMENTS

FMS-3002 Aluminum Alloy 2124 Plate (1.500 - 6 inches thick)

FMS-3004 Aluminum Alloy 7475 Plate (0.250 - 4 inches thick) Fracture Toughness Tested

FMS-3008 Aluminum Alloy 2124 Plate (2.500 - 6 inches thick) Fracture Toughness Tested

FPS-3003 Traceability Requirements for F-16 Fatigue and Fracture Critical Parts Manufactured From Aluminum Alloys

FPS-3019 Traceability Requirements for F-16 Fatigue and Fracture Critical Parts Manufactured From Steel

FPS-35XX Fatigue and Fracture Control Specification for Various Part Numbers & FPS-36XX

NDTS-1501 Hardness Testing

NDTS-1502 Conductivity Testing

3.0 TEST METHODS

Test Methods are to be in conjunction with information in NDTS 1501 and NDTS 1502. In NDTS 1500, see Section 4. SCHEDULING, for applicability of each test method.

3.1 METHOD #1 - CONDUCTIVITY TESTING (ALUMINUM FORGINGS ONLY)

3.1.1 CRITICAL PARTS

Check at the locations shown in the applicable LM Aero FPS-35XX or other FPS detail processing specification or applicable drawing.

3.1.2 NON-CRITICAL PARTS

Parts When applicable, perform Conductivity checks at the thickest and thinnest locations. If forging is at least 4 inches long, check a minimum of three locations, while attempting to include the thickest and thinnest sections. If forging is less than 4 inches long, checks at least two locations, if possible.

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3.2 METHOD #2 - CONDUCTIVITY TESTING (ALUMINUM SHEET AND LESS THAN 0.750 INCH THICK PLATE AND ALUMINUM BARS)

3.2.1 A minimum of three (3) Conductivity readings shall be taken at locations indicated in the sketch below. One reading shall be taken near each end, and one near the middle.

XX

X

X - Conductivity test location

METHOD #2:

3.2.2 For 6XXX Aluminum Alloys, at least one Hardness Test is also required at any location. When possible, Webster Pliers may be used to do the testing. If a questionable reading is obtained, a Rockwell Hardness Test shall be performed.

3.3 METHOD #3 - CONDUCTIVITY TESTING (0.750 INCH AND GREATER THICKNESS ALUMINUM PLATE AND BAR)

3.3.1 A minimum of three (3) conductivity readings shall be taken at locations indicated in sketch below. One reading shall be taken near each end, and one near the middle.

Y Y Y

X X X

X - Conductivity test location

Y- alternate Conductivity locations

METHOD #3

3.3.2 For 6XXX Aluminum Alloys, at least one Hardness Test is also required at any location.

3.4 METHOD #4 - CONDUCTIVITY TESTING (ALUMINUM EXTRUSIONS)

3.4.1 A minimum of three (3) Conductivity readings shall be taken at locations indicated in sketch below. One reading shall be taken near each end, and one near the middle.

XX

XX-Conductivity test location: Exact flange or leg to be tested is optional

METHOD #4:

3.4.2 For 6XXX Aluminum Alloys, at least one Hardness Test is also required at any location. When possible, Webster Pliers may be used to do the testing. If a questionable reading is obtained, a Rockwell Hardness Test shall be performed.

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3.5 METHOD #5 - HARDNESS TESTING (6XXX TUBING, SHEET, EXTRUSION, AND ANY ALUMINUM ROD WITH A DIAMETER FROM 0.250” TO 0.750”)

3.5.1 Tubing, Sheet, and Extrusion

Portable Hardness Test each end of 6XXX tubing using Webster Pliers.

3.5.2 Rods (0.250” to 0.750” diameter)

Rockwell hardness Test each end of rod

3.6 METHOD #6 - CONDUCTIVITY TESTING (0.750”OR GREATER DIAMETER ALUMINUM ROD)

3.6.1 Conductivity Test one end on the flat surface, as shown in sketch below.

X

X-Conductivity test location

METHOD #6

3.6.2 For 6XXX Aluminum Alloys, at least one hardness test at any location is required.

3.7 METHOD #7 - CONDUCTIVITY TESTING (FOR CERTAIN MATERIALS AT SELECTED INSPECTION OPERATIONS AS PRESCRIBED IN SECTION 4)

3.7.1 One Conductivity reading at any suitable location is sufficient.

3.7.2 For 6XXX Aluminum Alloys, at least one Hardness Test is also required. When possible, Webster Pliers may be used to do the testing. If a questionable reading is obtained, a Rockwell Hardness Test shall be performed.

3.8 METHOD #8 - HARDNESS TESTING (FOR CERTAIN MATERIALS AT SELECTED INSPECTION OPERATIONS AS PRESCRIBED IN SECTION 4)

3.8.1 One valid Hardness reading at any suitable location is sufficient.

4.0 SCHEDULING

4.1 SCHEDULE INTRODUCTION

When possible, heat treat verification per this NDTS follows the schedule listed in 4.1.1 (including subparagraphs) and 4.1.2 (including subparagraphs). Recording of results shall be per requirements in section 5.

However, there are cases where the scheduled tests per 4.1.1 or 4.1.2 can not be conducted. Examples of such cases include but are not limited to the following:

a) When the indentations made by Hardness Testing are detrimental, such as certain bearings and springs.

b) When shape or size of part prohibits obtaining either a valid Hardness reading or a valid Conductivity reading.

When in doubt about such case, contact Process Control, QA, LM Aero - Fort Worth, for assistance.

In cases where testing is not possible the following guidelines shall be applied: 1) At LM Aero - Fort Worth

Forward parts to Process Control, QA, on a TALON Test Tag.

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2) Facilities other than LM Aero - Fort Worth Verify that all available paperwork (Test Reports; Heat Treat Charts) indicate that processing was correct.

4.1.1 ALUMINUM ALLOYS

Except as specified in a) below, perform hardness and conductivity tests after all applicable manufacturing processes (includes coating applications such as chemical film, anodize, prime, and paint) have been accomplished.

a) EXCEPTION: When the material is one which requires a Hardness Test (6XXX Al Alloys; 7XXX Al Forgings), perform required test at any time after aging / precipitation hardening heat treatment but prior to coating application.

Exception to perform the required test at any time after aging heat treatment but prior to coating application also applies to LM Aero - Fort Worth Factory QA checks when a coating might affect the hardness test accuracy and to suppliers of aluminum castings , aluminum forgings, and fabricated parts/details .

4.1.1.1 Scheduling Requirements for Suppliers of Aluminum Products

4.1.1.1 (a) Suppliers of Aluminum Forgings

These requirements apply to the aluminum forging company or to a distributor of raw aluminum forgings who supply forgings to LM Aero - Fort Worth facility or its subcontractors. Parts machined from raw forgings or painted parts fabricated from raw forgings shall be inspected per requirement of 4.1.1.1(d). Forgings with pilot holes or tooling tabs shall be considered raw forgings.

TESTING AND RECORDING: Conductivity check 100% of the parts as specified in METHOD #1. For 7XXX aluminum alloys, also Hardness test 10% of parts as specified in METHOD #8. If a Certification is required of a forging producer, the same obligation would apply to a distributor for that producer. Record results of tests per 5.1.

Note: Unless otherwise approved by LM Aero - Fort Worth M&P Engineering, forging shall only be heat treated by the forging producer or the producer’s sub-tier processor.

4.1.1.1 (b) Suppliers of Aluminum Raw Materials other than aluminum forgings or castings

These requirements apply to raw materials produced or procured as sheet, plate, bar, rod, tube, or extrusions.

TESTING AND RECORDING: No NDTS 1500 requirements are imposed on raw material. However, if LM Aero material specifications (such as, FMS-3004, 7475 Aluminum Plate) require inspection to this specification, then perform the test and meet requirement as specified in Method #3 or as approved by LM Aero - Fort Worth M&P Engineering. Record results of tests per 5.1. Note 1: Unless otherwise approved by LM Aero - Fort Worth M&P Engineering, material to

FMS-3002, FMS-3004, and FMS-3004 shall only be heat treated by the plate producer.

Note 2: When the raw material distributor, the part supplier, or the part supplier’s sub-tier processor performed precipitation or aging treatment on bar, rod, plate, or extruded shape to obtain T651, T6511, T851, T8511, or T81 temper per AMS 2770 on aluminum alloy per specification other than FMS-3002, FMS-3004, and FMS-3008, the material shall be tested after precipitation treatment to meet applicable material specification and the engineering drawing. The report showing test result shall be maintained as a record by the part supplier. When engineering drawing specifies heat treat verification of the part per NDTS 1500, parts fabricated from such material shall be further inspected per 4.1.1.1 (d) or 4.1.1.1 (f) as applicable.

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4.1.1.1 (c) Suppliers of Aluminum Castings

These requirements apply to the aluminum casting company or to a distributor of raw aluminum castings who supply castings to LM Aero facility or its subcontractors. Parts machined from raw castings or painted parts fabricated from raw castings shall be inspected per requirement of 4.1.1.1(d). Castings with pilot holes or tooling tabs shall be considered raw castings.

TESTING AND RECORDING:

Hardness test 100% of the parts as specified in METHOD #8. Record results of tests per 5.1.

Note: Unless otherwise approved by LM Aero M&P Engineering, casting shall only be heat treated by the casting producer or the producer’s sub-tier processor.

4.1.1.1 (d) Suppliers of Fabricated Parts (see 6.2.3) including those fabricated from raw forgings and castings

This category includes parts machined from castings, plates, bars, rods, extrusions, and forgings, as well as parts formed from sheet metal. It does not apply to material which is cut into smaller pieces for subsequent machining / forming at another company. The smaller cut pieces are covered in Para. 4.1.1.1(f), Suppliers of Aluminum Cut-to-Size Material. Parts fabricated for F-16 shall be inspected as specified in 4.1.1.1 (d) 1 and 4.1.1.1 (d) 3. Parts fabricated for F-2 shall be inspected as specified in 4.1.1.1 (d) 2 and 4.1.1.1 (d) 3. NOTE: For coated parts, the Exception detailed above in Para 4.1.1(a) applies to this section.

4.1.1.1 (d) 1 Requirements Applicable To Parts Fabricated Only For F-16 Program {Also see 4.1.1.1 (d) 3}

A) NON-CRITICAL PARTS {Also see 4.1.1.1 (d) 3} Conductivity test 100% of parts, using a test method that is applicable to the form of material involved, such as METHOD #2 for sheet metal or METHOD #4 for extrusions. The check of 100% of the parts is mandatory; it applies whether or not the acquired raw material required any additional heat treatments

B) CRITICAL PARTS {Also see 4.1.1.1 (d) 3}

1) PARTS FABRICATED BY PROCESS OTHER THAN NC-MACHINING

Conductivity test 100% of the parts at the locations shown in the applicable Engineering Manufacturing Control Specification or Engineering Drawing.

2) PARTS FABRICATED BY NC-MACHINING PROCESS

a) Machined pockets with designated inspection location

• Requirements: Conductivity test in the machined pockets designated on the applicable Part Manufacturing Plan Document (such as FPS-35XX). Record and maintain the results as a part of the traceability record per 5.4.

• Requirements for inaccessible designated location: When the designated conductivity test location specified on the engineering drawing is inaccessible and cannot be accurately conductivity tested (due to probe size or part geometry), then it is permissible to perform the conductivity check at the nearest adjacent surface. Record and maintain the results as a part of the traceability record per 5.4.

b) Machined pockets other than those with designated location In addition to the designated pockets, all other accessible pockets shall be tested, but recording of test data per 5.4 is not required.

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4.1.1.1 (d) 2 Requirements Applicable To Parts Fabricated Only For F-2 Program {Also see 4.1.1.1 (d) 3}

A) F-2 PROGRAM NON-CRITICAL PARTS {Also see 4.1.1.1 (d) 3}

1) Parts Fabricated Using Process Other Than NC-Machining

Conductivity test 100% of parts, using a test method that is applicable to the form of material involved, such as METHOD #2 for sheet metal or METHOD #4 for extrusions.

The check of 100% of the parts is mandatory. This requirement applies even when the acquired raw material was additionally heat treated and tested to meet applicable requirements.

2) Parts Fabricated Using NC-Machining Process

Conductivity check 100% of parts at each of the pockets designated on the Engineering Drawing.

B) F-2 PROGRAM CRITICAL PARTS {Also see 4.1.1.1 (d) 3}

1) PARTS FABRICATED BY PROCESS OTHER THAN NC-MACHINING

Conductivity test 100% of parts, using a test method that is applicable to the form of material involved, such as METHOD #2 for sheet metal or METHOD #4 for extrusions.

The check of 100% of the parts is mandatory. This requirement applies even when the acquired raw material was additionally heat treated and tested to meet applicable requirements.

2) PARTS FABRICATED BY NC-MACHINING PROCESS

a) Machined pockets with designated inspection location

• Requirements: Conductivity check 100% of parts at each of the pockets designated on the Engineering Drawing. Record and maintain the results as a part of the traceability record per 5.4.

• Requirements for inaccessible designated location in machined pockets: When the designated conductivity test location specified on the engineering drawing is inaccessible and cannot be accurately conductivity tested (due to probe size or part geometry), then it is permissible to perform the conductivity check at the nearest adjacent surface. Record and maintain the results as a part of the traceability record per 5.4.

b) Machined pockets other than those with designated location In addition to the designated pockets, all other accessible pockets shall be tested, but recording of test data per 5.4 is not required.

4.1.1.1 (d)3 Additional Requirements Applicable To Parts Fabricated For Both F-16 & F-2 Programs

A) NON-CRITICAL PARTS

(1) When material is furnished by LM Aero - Fort Worth

If LM Aero - Fort Worth furnishes the material in the final heat treat condition, the supplier shall submit the following statement:

“The material used in this order is the material furnished by LM Aero - Fort Worth, and no unauthorized substitution has been made.”

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(2) When material is furnished by supplier

If the supplier purchased material in the final heat treat condition, certification listing chemical and mechanical properties shall be retained by the supplier.

A) CRITICAL PARTS

(1) When material is furnished by LM Aero – Fort Worth

If LM Aero - Fort Worth furnishes the material in the final heat treat condition, the supplier shall submit the following statement:

“The material used on this order is the material furnished by LM Aero - Fort Worth, and no unauthorized substitution has been made.”

(2) When material is furnished by supplier

If the supplier purchased the material in the final heat treat condition, certification listing chemical and mechanical properties shall be submitted by the supplier. All required data shall be submitted per FPS-3003.

4.1.1.1 (e) Suppliers of Aluminum Cut Shapes

Aluminum cut shapes are materials used for bulkheads and wing skins. Prior to shipping, LM Aero - Fort Worth approved raw material producing mill or LM Aero - Fort Worth designated raw material distributor roughly cuts the shape of the part it will eventually become from a plate.

TESTING AND RECORDING REQUIREMENT FOR CUT SHAPES:

Shapes from FMS-3004 (7475 Aluminum) Plate: Conductivity check each parent plate and record results per 5.1.3.

Shapes from FMS-3002 or FMS-3008 (2124 Aluminum) Plate: No NDTS 1500 testing is required.

Note: Unless otherwise approved by LM Aero M&P Engineering, cut shapes shall only be fabricated from the material heat treated by the plate producer.

4.1.1.1 (f) Suppliers of Aluminum Cut-to-Size Material [See Note 2 in 4.1.1.1 (b)]

Cut-to-Size Materials include plates, sheets, tubing, extrusions, etc., which have been cut into segments that will later be fabricated into detail parts at LM Aero - Fort Worth or its subcontractor. In addition, plate material will have been skim-cut to facilitate eventual milling operations.

Note: When bar, rod, plate, or extruded shape is precipitation or age hardened to obtain T651, T6511, T851, T8511, or T81 temper per AMS 2770 prior to cut-to-Size operation by the material supplier or a distributor, the material shall be tested after precipitation or aging treatment to meet applicable material specification and the engineering drawing. The report showing test result shall be maintained as a record by the supplier. Also perform required test specified below on the raw material. This report shall be maintained by the part supplier or forwarded to appropriate destination as directed by LM Aero – Fort Worth QA.

TESTING AND RECORDING REQUIREMENT FOR CUT-TO-SIZE SHAPES:

Prior to any cutting, each plate, sheet, bar, rod, tube, etc., shall be checked per the following methods: Raw Material Form Inspection method Raw Material Form Inspection methodSheet, Plate, or Bar Method #2 or #3 Extrusion Method # 4

Rod Method #5 or #6 Tube (6XXX) Method #5

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Record results per 5.1.4. Those results will later be transferred to each piece cut from a given item, such as from a large sheet.

4.1.1.1 (g) Processor Responsible for Anodize Operation on Fabricated Parts/details (see 6.2.3)

This applies to the processor who actually performs the anodize process on fabricated part/detail. The processor could be subcontractor of LM Aero – Fort Worth or its sub-tier supplier. In addition to requirement in 4.1.1.1 (d), the supplier shall perform the test specified herein.

TESTING REQUIREMENT FOLLOWING ANODIZE PROCESS AND PRIOR TO ADDITONAL FINISH APPLICATIONS

The supplier shall visually inspect the part surface following anodizing process to determine existence of discrepant dark areas on the part. Such dark areas may be indicative of locally soft material. Dark areas should be analyzed with a Conductivity meter to assure proper heat treat condition. See Note 7 of Table II in NDTS-1502 for criteria. If the dark areas are “questionable” per the limits in Note 7, contact the appropriate LM Aero - Fort Worth QA representative. When the part is free of the discrepant dark areas following anodizing process, the supplier shall provide a statement that visual examination after anodizing of the part did not reveal any discrepant dark areas. Record results per 5.1.5.

4.1.1.2 Scheduling Requirements for LM Aero - Fort Worth Factory QA - Upon Issuance of Aluminum to Production

This is a sample check to ensure that the material from LM Aero - Fort Worth stock to be processed into an order of detail parts is in required heat treat condition. At LM Aero - Fort Worth, it would be Operation 001 on a Shop Order/Inspection Record (SOIR).

SAMPLING, TESTING, AND RECORDING REQUIREMENT FOR ISSUED STOCK MATERIAL:

(a) Aluminum Forgings: Check at least one forging, using Method #1.

(b) Aluminum Raw Material:

Sheet: Check at least one sheet using Method #2.

Plate: Check at least one plate using Method #2 or #3.

Extrusions: Check at least one extrusion using Method #4.

Tubing: For 6XXX only, check at least one tube using Method #5.

Bar: Check at least one bar using Method #2.

Rod: Check at least one rod using Method #5 or #6.

(c) Aluminum Castings: Check at least one casting using Method #8.

(d) Aluminum Fabricated Parts (see 6.2.3): Check at least one part using Method #2 or #4.

(e) Aluminum Cut Shapes: Check at least one shape using Method # 3.

(f) Aluminum Cut-to-Size Material: Same as that for Aluminum Raw material in (b) above.

Record results per 5.2.1 from tests per a), b), c), d), e) or f) above.

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4.1.1.3 Scheduling Requirements for LM Aero - Fort Worth Factory QA - After Solution Heat Treatment of Aluminum

TESTING REQUIREMENT:

No actual Conductivity/Hardness testing is required after Solution Heat Treat. At the next planned inspection Operation, Inspection shall examine the applicable paperwork (SOIR; Traveler) to verify that the Solution Heat Treatment was accomplished using the correct times and temperatures.

4.1.1.4 Scheduling Requirements for LM Aero - Fort Factory QA - After In-House Aging of Aluminum Wrought (see 6.2.2) Products

SAMPLING, TESTING, AND RECORDING REQUIREMENT AFTER AGING:

a) NC Machined or Formed F-16 and F-2 Parts:

Critical Parts:

Conductivity check 100% of in-house aged parts at locations shown on the drawing or in applicable FPS-35XX or FPS-36XX specification using test method prescribed below. For the F-16, three F/FC Fuselage Skins are routinely aged to 2024-T62 or FMS-3103-T62 (Al-Li per FMS-3103), and would require a 100% check (16B5301; 16B5303; 16B5304). Record results of tests per 5.3.

Non-Critical Parts: Check at least one part per SOIR. Record results of tests per 5.3.

TEST METHOD:

Flat Parts, at least 4” long: Method #2 or #4.

Flat Parts , less than 4” long: Method #7

Tubing: Method #5

Bar /Rod: Check at least one bar using Method #2

b) Aluminum Forgings: In-house heat treatment of forgings is rare, and would normally be by MRB action. Check 100% of parts using Method #1. Record results of tests per 5.3.

c) Aluminum Castings: In-house heat treatment of castings is rare, and would normally be done by MRB action. Record results of tests per 5.3.

Class I and II castings - Test 100% of parts per Method #8.

Other castings - Hardness Test at least one part per SOIR using Method #8.

4.1.1.5 Scheduling Requirements for LM Aero –Fort Worth Factory QA - After NC Machining of Aluminum (Not Heat Treated In-House)

4.1.1.5.1 FOR F-16 NC-MACHINED PARTS

(A) NON CRITICAL PARTS

No post-machining testing is imposed for non-critical F-16 parts.

(B) CRITICAL PARTS

1) F-16 Critical Parts

Pockets with Designated Test location:

100 % of the “Critical” parts shall be Conductivity Tested in the machined pockets designated in the applicable Part Manufacturing Plan Document (such as FPS-35XX). Record and maintain the results as a part of the traceability record per 5.4.

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Pockets With Inaccessible Designated Test Locations:

When the designated conductivity test location specified on the engineering drawing is inaccessible and cannot be accurately conductivity tested (due to probe size or part geometry), then it is permissible to perform the conductivity check at the nearest adjacent surface. Record and maintain the results as a part of the traceability record per 5.4.

Pockets Other Than Those With Designated Test Locations:

In addition to the designated pockets, all other accessible pockets shall be conductivity tested. Recording of acceptable test results per 5.4 is not required.

4.1.1.5.2 FOR F-2 NC-MACHINED PARTS

(A) CRITICAL AND NON CRITICAL PARTS

Pockets with Designated Test location:

100 % of the parts shall be conductivity tested in the machined pockets designated on the applicable engineering drawing. Record and maintain the results as a part of the traceability record per 5.4.

Pockets With Inaccessible Designated Test Locations:

When the designated conductivity test location specified on the engineering drawing is inaccessible and cannot be accurately conductivity tested (due to probe size or part geometry), then it is permissible to perform the conductivity check at the nearest adjacent surface. Record and maintain the results as a part of the traceability record per 5.4.

Pockets Other Than Those With Designated Test Locations:

In addition to the designated pockets, all other accessible pockets shall be conductivity tested. Recording of acceptable test results per 5.4 is not required.

4.1.1.6 Scheduling Requirements for LM Aero - Fort Worth Factory QA -Prior to Stock

a) Aluminum Forging (except those designated ‘critical’): Test 100% of parts using Method #7.

b) Critical Parts (including forgings designated as critical): Test 100% of parts using Method #7.

c) Aluminum Tubing (6XXX Aluminum Alloy): Test 100% of parts using Method #5.

1) Tubing Used in Flared; Swaged; Beaded Parts:

A) Tubing Heat Treated After Issue -

If there is a heat treat operation after material is issued, tubing which requires flaring, swaging, or beading will be Webster Pliers tested prior to the flaring, swaging, or beading operation.

B) Tubing Not Heat Treated After Issue

If there is no heat treat operations after material is issued, tubing which requires flaring, swaging, or beading need not be Webster Pliers hardness tested.

d) Non-critical Parts Fabricated from Plate (Note: Plate is.250” thick and greater), Bar, and Rod:

When part is 4” long or longer: Test 100% of parts using Method #2.

When part is less than 4” long: Test 100% of parts using Method #7.

e) Aluminum Castings: Hardness Test 100% of parts using Method #8.

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f) Non-critical Parts from Aluminum Sheet (Note: Sheets are .249” thick and less) and Extruded Shapes

When part is 4” long or longer: Test 100% of parts using Method #2.

When part is less than 4” long: Test 100% of parts using Method #7.

Results are required to be recorded per 5.5 for the only material that will be used in the fabrication of critical parts.

4.1.2 NON-ALUMINUM ALLOYS

4.1.2.1 Scheduling Requirements for Suppliers of Non-Aluminum Products

a) Raw Material:

1) No NDTS 1500 requirements are imposed. However, raw material must have mill reports showing its compliance to the applicable material specification. Mill reports must be maintained for record as required by LM Aero – Fort Worth QA.

2) When the material is heat treated by a raw material distributor or by the part supplier (not raw material producer) prior to making parts, the material shall be tested to meet applicable material specification and the engineering drawing. The report showing test results shall be maintained by the part supplier or forwarded to appropriate destination as directed by LM Aero – Fort Worth QA.. When the engineering drawing specifies heat treat verification of the part per NDTS 1500, parts fabricated from such material shall be further inspected per 4.1.2.1 c).

b) Forgings and Castings: When NDTS 1500 is specified on the Outside Production Operations Sheet (OPOS), on the Engineering Drawing, or any other LM Aero document, hardness test 100% of the parts using Method #8. Record results of tests per 5.6.

c) Fabricated Parts (see 6.2.3): When NDTS 1500 is specified on the OPOS or on the Engineering Drawing, hardness test 100% of the parts using Method #8. Record results of tests per 5.6.

For “critical fabricated parts”, all required data shall be submitted per FPS-3019.

d) Hardware (Fasteners; Washers; Fittings): Unless called out on the Specification Control drawing, no NDTS 1500 requirements are imposed.

e) Cut-to-Size Material: No NDTS 1500 requirements are imposed.

4.1.2.2 Scheduling Requirements for LM Aero - Fort Worth Factory QA- Upon Issuance of Non-Aluminum Material to Production

No NDTS 1500 requirements are imposed.

4.1.2.3 Scheduling Requirements for LM Aero - Fort Worth Factory QA- After Aging / Tempering to Final Heat Treat Condition

All Materials with Tensile Strength 180,000 psi, and above - Hardness test 100% of the parts using Method #8. Record results of tests per 5.7.

All Materials with Tensile Strength less than 180,000 psi - Using Method #8, sample hardness test the parts per applicable Sample Plan A or Plan B below. Record results of tests per 5.7.

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SAMPLE PLAN A

(For Alloy Steels & Carbon Steels with strength less than 180,000 psi) SOIR Size Sample Size

1-2 All 3-90 3 91-500 13 501-1200 20 1200-10,000 32

Note: If any part in the sample fails, inspect 100% of the parts

SAMPLE PLAN B

(For Beryllium - Copper Alloys with strength less than 180,000 psi) SOIR Size Sample Size

1-3 All 4-10 3 11-25 4 26-50 5 51 & up 10% of parts

4.1.2.4 Scheduling Requirements for LM Aero – Fort Worth Factory QA After Machining

When machined (milled, turned, routed) in final heat treat condition, Hardness check 100% of parts using Method #8. Record results of tests per 5.8.

4.1.2.5 Scheduling Requirements for Non-Aluminum Alloys Prior to Stock, but Prior to Finish Application by LM Aero – Fort Worth Factory QA

For those materials appearing in Table VI and VII of NDTS 1501, which are not heat treated at LM Aero - Fort Worth, sample Hardness Test as specified in Sample Plan A, using Method #8. Record results of tests per 5.9.

5.0 RECORDS

5.1 RECORDING REQUIREMENTS FOR SUPPLIERS OF ALUMINUM FORGINGS, CASTINGS, MACHINED PARTS, CUT SHAPES, AND CUT-TO-SIZE MATERIAL AFTER TESTING PER 4.1.1.1

5.1.1 CRITICAL ALUMINUM PARTS - [EXCLUDING CUT SHAPES ]

The test results shall be recorded for each individual Serial Number and submitted with each shipment to LM Aero - Fort Worth. For direct shipments, a copy of all test reports shall be sent to both LM Aero - Fort Worth and to the shipment destination. Required statement per 4.1.1.1 d) 4 (A) or data per 4.1.1.1 d) 4 (B) shall also be submitted with the shipment or as directed by LM Aero - Fort Worth QA.

5.1.2 NON-CRITICAL ALUMINUM PARTS - [EXCLUDING CUT SHAPES]

The minimum and the maximum reading shall be recorded for each lot. For direct shipments, a copy of all test reports shall be sent to LM Aero - Fort Worth and to the shipment destination.

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5.1.3 CUT SHAPES AND 7475-T7351 PLATE PER FMS-3004

Conductivity test results for Aluminum Cut shapes / Plates need only be submitted when required by the applicable material specification. Currently, only FMS-3004 for 7475 Aluminum Plates requires submittal of a Conductivity value for each parent plate. Submit in accordance with latest revision of FPS-3003.

5.1.4 ALUMINUM CUT-TO-SIZE MATERIAL

Record results of tests specified in Para. 4.1.1.1(f) such that they can later be transferred to each piece cut from a given item, such as from a large sheet.

5.1.5 INSPECTION FOLLOWING ANODIZING PROCESS

Critical Part: The inspection result shall be recorded for each serialized part as a record. The required statement per 4.1.1.1g shall be submitted to both LM Aero - Fort Worth and to the shipment destination. When the anodizing process is performed by a sub-tier processor of a part supplier to LM Aero, it shall submit the recorded result and the required statement to the part supplier who in turn will supply it to LM Aero - Fort Worth and to the shipment destination as a traceability data package.

Non-Critical Part: The inspection result shall be recorded for all discrepant parts. The required statement per 4.1.1.1g shall be submitted to LM Aero - Fort Worth and to the shipment destination.

5.2 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA FOLLOWING TESTING PER 4.1.1.2

5.2.1 RECORDING REQUIREMENTS UPON TESTING FOLLOWING ISSUANCE OF ALUMINUM

On Operation 001 of an SOIR, record a single minimum value and a single maximum value from the results obtained. If both Conductivity and Hardness tests were performed, as with 6XXX Aluminum Alloys, record the minimum and maximum values obtained from both types of tests.

5.3 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA FOLLOWING TESTING PER 4.1.1.4:

5.3.1 RECORDING REQUIREMENTS FOR NON-CRITICAL (see 6.2.7) ALUMINUM PARTS

a) Acceptability of the one tested part per SOIR, and therefore, of the remaining untested parts, will be indicated by the two following steps:

b) Imprinting of the acceptance stamp on the Age Operation.

c) Writing the letters “S/L” (sample lot) next to the imprinted stamp.

5.3.2 RECORDING REQUIREMENTS FOR CRITICAL (see 6.2.7) ALUMINUM PARTS

Record on the SOIR the Conductivity readings obtained from each serialized part.

5.4 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA FOLLOWING TESTING OF CRITICAL PARTS PER 4.1.1.5

Record on the SOIR the reading obtained for each designated location (A; B; C; D; E, etc.) following testing of NC-Machined parts.

5.5 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA FOLLOWING TESTING OF CRITICAL PARTS PER 4.1.1.6

Record on the SOIR a single minimum reading and a single maximum reading prior to stocking aluminum parts. Readings may be Conductivity, Hardness, or both.

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5.6 RECORDING REQUIREMENTS FOR SUPPLIERS OF NON-ALUMINUM PRODUCTS AFTER TESTING PER 4.1.2.1

5.6.1 CRITICAL PARTS {This includes any Forging (See 4.1.2.1 b) or Fabricated Part (see 4.1.2.1 c) Designated as a Critical Part}

If Hardness Testing was required, record a Hardness value for each serialized part.

5.6.2 NON-CRITICAL PARTS [This includes Casting (See 4.1.2.1 b), and any Forging (See 4.1.2.1 b) or Fabricated Part (see 4.1.2.1 c) Not Designated as a Critical Part]

If Hardness Testing was required, record the minimum and the maximum value obtained from the affected lot.

5.7 RECORDING REQUIREMENTS FOR LM AERO - FORT WORTH FACTORY QA FOLLOWING TESTING OF NON-ALUMINUM PARTS PER 4.1.2.3

After Aging / Tempering to Final Heat Treat Condition record results as follows:

a) Single Part Orders - Record the Hardness number on the SOIR.

b) Multiple Part Orders - Record the minimum and the maximum value obtained from the affected lot.


After machining of non-aluminum parts record results as follows:

a) For Part Designated as Critical Part - Record the Hardness value obtained for each serialized part.

b) Non-Critical Parts - Record the minimum value and the maximum value obtained from the affected lot.


Prior to stocking of non-aluminum parts record results as follows:

Record the minimum value and the maximum value obtained from the affected lot.

6.0 GENERAL INFORMATION

6.1 SPECIFICATION TABLES

Tables I and Table II contain a listing of material specifications and their corresponding alloys.

6.2 DEFINITION OF TERMS

6.2.1 CASTINGS

Castings are obtained by melting metallic material, pouring into a mold with a near shape of a part, let it solidify in the mold, and then heat treat to a proper condition after removal from the mold. This group does not include raw material ingots or any wrought Materials .

6.2.2 WROUGHT MATERIALS

Metal products are produced by such ingot reduction processes as rolling, extruding, drawing, or forging. Generally, the working process requires hot or cold working or a combination there of to reduce the ingot down to a specific thickness. Sheet, plate, bars, rods, tubing, extrusions, and wire are considered wrought materials. This group does not include Castings .

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6.2.3 FABRICATED PARTS

Term applied to aircraft parts produced from wrought materials or castings. The processing involved could include but are not limited to manufacturing processes such as forming, machining, welding, and coating application.

6.2.4 MANUFACTURING PROCESS

Any process employed in producing parts, including machining, heat treating, welding, forming, and coating application.

6.2.5 SCHEDULING (Section 4)

A written set of procedures which outline the following:

“Who” (which organization) is required to test per NDTS 1500

“When”, during the manufacturing sequence, testing per NDTS 1500 is required

“How” to perform the tests

Gives the Test Method (see Section 3)

Give the number of parts / amount of material to be tested

6.2.6 CRITICAL

Refers to parts identified on the engineering drawing or applicable specification (such as FPS-35XX) as critical. This includes such terms as Fracture Critical, F&FC, Durability Critical, etc.

6.2.7 NON-CRITICAL

Any part not identified as critical (see 6.2.6) is considered Non-Critical.

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Table I - Aluminum Material Specifications and Corresponding Alloys Extrusions Extruded Bar and Rod Sheet and Plate

Specification Alloy Specification Alloy Specification Alloy QQ-A-200/1 3003 QQ-A-225/1 1100 QQ-A-250/1 1100 QQ-A-200/2 2014 QQ-A-225/2 3003 QQ-A-250/2 3003 QQ-A-200/3 2024 QQ-A-225/3 2011 QQ-A-250/3 2014 (Clad) QQ-A-200/4 5083 QQ-A-225/4 2014 QQ-A-250/4 2024 QQ-A-200/5 5086 QQ-A-225/5 2017 QQ-A-250/5 2024 (Clad) QQ-A-200/6 5454 QQ-A-225/6 2024 QQ-A-250/6 5083 QQ-A-200/7 5456 QQ-A-225/7 5052 QQ-A-250/7 5086 QQ-A-200/8 6061 QQ-A-225/8 6061 QQ-A-250/8 5052 QQ-A-200/9 6063 QQ-A-225/9 7075 QQ-A-250/9 5456 QQ-A-200/10 6066 QQ-A-225/10 6062 QQ-A-250/10 5454 QQ-A-200/11 7075 QQ-A-250/11 6061 QQ-A-200/13 7178 AMS Specifications for QQ-A-250/12 7075 QQ-A-200/14 7178 Wrought Aluminum Products QQ-A-250/13 7075 (Clad) QQ-A-200/15 7075 Specification Alloy QQ-A-250/14 7178 QQ-A-200/16 6061 AMS 4050 7050 QQ-A-250/15 7178 (Clad) QQ-A-200/17 6162 AMS 4081 6061 QQ-A-250/18 7075 (Clad 1)

AMS 4107 7050 QQ-A-250/19 5085 Tubing AMS 4108 7050 QQ-A-250/20 5454

Specification Alloy AMS 4111 7049 QQ-A-250/21 7178 WW-T-700/1 1100 AMS 4149 7175 QQ-A-250/22 7178 (Clad) WW-T-700/2 3003 AMS 4156 6063 QQ-A-250/24 7075 WW-T-700/3 2024 AMS 4347 6013 QQ-A-250/25 7075 (Clad) WW-T-700/4 5052 QQ-A-250/26 7075 (Clad) WW-T-700/5 5086 QQ-A-250/28 7178 (Clad) WW-T-700/6 6061

LM Aero - Fort Worth Specifications QQ-A-250/29 2124

WW-T-700/7 7075 Specification Alloy QQ-A-250/30 2219 MIL-T-7081 6061 FMS-0033 2024 (Clad 1)

FMS-0116 2219 Castings K Drawing Extrusions FMS-1053 2024 (Clad) Specification Alloy

Specification Alloy FMS-1010 2024 MIL-A-21180 A356 or A357K# - A 2024 FMS-3002 2124 AMS-4218 A356 K# - B 6061 FMS-3004 7475 AMS-4219 A357 K# - D 7075 FMS-3008 2124 AMS-4229 A201 K# - E 2219 FMS-3013 6061

FMS-3022 2024 K# - F 6063 or 2090 FMS-3031 6061

FMS-3051 D357 (Cast) FMS-3057 7475 FMS-3061 6013 FMS-3071 2090 FMS-3072 2090 FMS-4005 7050

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Table II - Steel and Non-Aluminum Specifications and Corresponding Alloys

Beryllium-Copper Alloys Non-Hardenable CRES/Stainless Steels Specification Alloy Form Specification Alloy Form

AMS 4890 825 or C825000 Cast MIL-S-5059 300 Series Alloys Wrought MIL-C-22087 825 Cast MIL-S-7720 300 Series Alloys Wrought

QQ-C-530 172 & 173 Wrought MIL-T-8808 300 Series Alloys Wrought QQ-C-533 170 or 172 Wrought QQ-S-763 300 Series Alloys Wrought

170 (Prev.165) Wrought QQ-W-423 302 Stainless Wrought ASTM B 194 172 (Prev.25) Wrought ASTM A 582 303, 303SE Wrought 170 (Prev.165) Wrought AMS 5640 303 Stainless Wrought ASTM B 196 172 (Prev.25) Wrought MIL-T-6845 304 Wrought

MIL-T-8506 304 Wrought Copper Alloys MIL-T-5695 304 Wrought

Specification Alloy Form QQ-S-766 304 Wrought QQ-C-576 Pure Copper Wrought FMS-1080 304 Stainless Wrought

AMS 5639 304 Stainless Wrought Carbon and Alloy Steels AMS 5510 321 Stainless Wrought

Specification Alloy Form AMS 5570 321 Stainless Wrought MIL-S-7947 1095 Wrought AMS 5645 321 Stainless Wrought MIL-S-7420 52100 Wrought AMS 5512 347 Stainless Wrought MIL-S-18729 4130 Wrought MIL-T-6736 4130 Wrought Precipitation Hardening CRES/Stainless Steels AMS 6371 4130 Wrought Specification Alloy Form MIL-S-5000 4340 Wrought AMS 5629 PH13-8Mo Wrought AMS 6359 4340 Wrought FMS-3047 PH 13-8 Wrought AMS 6414 4340 Wrought AMS 5659 PH 15-5 Wrought AMS 6415 4340 Wrought AMS 5520 PH15-7Mo Wrought FMS-1012 4330V Wrought AMS 5657 PH15-7Mo Wrought MIL-S-8844 300M (Class 3) Wrought FMS-1086 PH15-7Mo Wrought AMS 6512 Maraging 250 Wrought AMS 5355 PH 17-4 Cast AMS 6527 AF 1410 Wrought AMS 5643 PH 17-4 Wrought AMS 5844 MP35N Wrought FMS-0131 PH 17-4 Wrought FMS-1011 D6ac Wrought FMS-0133 PH 17-4 Wrought

MIL-S-25043 PH 17-7 Wrought Nickel Alloys AMS 5528 PH 17-7 Wrought

Specification Alloy Form AMS 5678 PH 17-7 Wrought AMS 5581 Inconel 625 Wrought AMS 5737 A-286 Wrought AMS 5582 Inconel X750 Wrought AMS 5525 A-286 Steel Wrought AMS 5596 Inconel 718 Wrought FMS-1111 10 Ni Steel Wrought AMS 5599 Inconel 625 Wrought AMS 5662 Inconel 718 Wrought AMS 5666 Inconel 625 Wrought AMS 5667 Inconel X750 Wrought FMS-3016 Inconel 625 Wrought

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Mil Hardnes Test

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