ATTACHMENTA3322.pdf

REV: ENGINEERING DATA REQUIREMENTS

(ATTACHMENT “A”)

NOTE: MILITARY SPECIFICATIONS / STANDARDS WILL NOT BE FURNISHED IN THE BID SET.

1. THE FOLLOWING INSTRUCTIONS ARE FURNISHED FOR THE MANUFACTURE OF:

SPEED BRAKE ASSY – LOWER

2. PART NUMBER:

162D712170-1001

3. NATIONAL STOCK NUMBER:

1560-01-592-3322FJ

PREPARED BY:

JAMES SHULL

OFFICE SYMBOL:

416 SCMS/GUEAB

DATE:

20220104

HILL AFB FORM 462 Page 1 of 16

Distribution Statement: D: Distribution authorized to Department of Defense and U.S. DOD contractors only, for administrative and operational use. Date of determination is 7 March 2016. Refer other requests for this document to OO-ALC/508 ACSS/SU, Hill AFB, UT, 84056.

Destruction Notice: For classified document, follow the procedures in DOD 5220.22M, Industrial Security Manual, Section 11-19 or DOD

5200.1 R, Information Security Program Regulation, Chapter IX. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

WARNING - the documents listed on this document and the associated Engineering Data List (EDL) contain technical data whose export is restrictive by the Arms Export Control act (Title 22, U.S.C., section 2751, et seq.), or the export administration act of 1979, as amended, title 50 U.S.C, Append 2401 et seq. Violators of these export laws are subject to severe criminal penalties.

4. THE SUPPLIED TECHNICAL DATA PACKAGE (162D712170-1001) WILL BE PROVIDED IN SIEMENS NX FORMAT AS A

MODEL BASED DEFINITION (MBD) AND SHALL SERVE AS THE ENGINEERING BASELINE FOR THIS ACQUISITION. THE GEOMETRY OF THE BASELINE TECHNICAL DATA PACKAGE (TDP) IS DEFINED BY THREE DIMENSIONAL (3-D) MODELS IN THE ABOVE DESCRIBED FORMAT. THIS INCLUDES 3-D MODELS AND OTHER DATA MASTERED IN A PRODUCT LIFECYCLE MANAGEMENT (PLM) SYSTEM. THE PLM DATA FIELDS NEEDED FOR MANUFACTURING ARE ALSO OUTPUT IN A HUMAN READABLE FORMAT THAT THE GOVERNMENT WILL PROVIDE AS A “PART REPORT.”

5. THE PRIME CONTRACTOR MAY USE A TRANSLATOR TO CONVERT BETWEEN NX AND IGES/STEP IN SUPPORT OF THEIR SUBCONTRACTORS; HOWEVER, THE PRIME CONTRACTOR SHALL DEMONSTRATE THE TRANSLATION

PROCESS TO THE GOVERNMENT AND OBTAIN GOVERNMENT AUTHORIZATION TO PROCEED BEFORE

MANUFACTURING TO THE CONVERTED 3-D SOLID MODEL. FOR A TRANSLATOR TO BE AUTHORIZED, THE CONTRACTOR MUST SHOW THAT THE DELIVERED 3-D SOLID MODEL CONTAINS ALL OF THE NECESSARY INFORMATION REQUIRED TO ACCURATELY PRODUCE PARTS AS DEFINED IN THE ORIGINAL NX MODEL. THE 3-D MODELS SHALL DEFINE PRODUCT CONFIGURATION PER ASME Y14.41 MODEL ONLY (AKA “MODEL BASED

DEFINITION”) IN LIEU OF DRAWINGS.

6. THE PRIME CONTRACTOR IS RESPONSIBLE TO COMPLETELY RESEARCH THESE MODELS, MANUALS, SPECIFICATIONS, AND STANDARDS AND FULLY UNDERSTAND THE REQUIREMENTS NECESSARY FOR MANUFACTURE OF COMPONENT PARTS AND ASSEMBLIES. ALL DEVIATIONS, MINOR AND MAJOR, FROM THE ENGINEERING TDP SHALL BE SUBMITTED TO THE PROPER A-10 ENGINEERING ORGANIZATION FOR COORDINATION

AND APPROVAL.

7. WHEN MILITARY DOCUMENTS LISTED IN THE ENGINEERING TDP ARE CANCELLED THEY SHALL BE REPLACED BY

THE INDUSTRY EQUIVALENT DOCUMENT SPECIFIED ON THE MILITARY DOCUMENT'S CANCELLATION NOTICE. THE CHARACTERISTICS OF TYPE, GRADE, CLASS, ETC. SPECIFIED IN THE CANCELLED MILITARY DOCUMENT SHALL BE MAINTAINED OR EXCEED THOSE CHARACTERISTICS WHEN APPLYING THE INDUSTRY EQUIVALENT DOCUMENT(S).

THE CONTRACTOR WILL COORDINATE WITH THE PROPER A-10 ENGINEERING ORGANIZATION FOR AUTHORIZATION AND APPROVAL OF THESE SUBSTITUTIONS PRIOR TO THE MANUFACTURING OF THIS COMPONENT. WHEN THERE IS NO LISTED REPLACEMENT THE CONTRACTOR SHALL REQUEST AND RECOMMEND A SUBSTITUTE DOCUMENT FROM THE PROPER A-10 ENGINEERING ORGANIZATION BY CONTACTING THE GOVERNMENT CONTRACTING OFFICIAL.

8. USE OF NORTHROP GRUMMAN SPECIFICATION Z-R701 IN CONJUNCTION WITH MIL-STD-130 IS MANDATORY TO

ENSURE THE PROPER MARKING OF THE PARTS. (Z-R701 HAS UNLIMITED DATA RIGHTS IN JEDMICS)

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9. ITEM UNIQUE IDENTIFICATION (IUID) SHALL BE APPLIED TO THE ASSEMBLY, PER MIL-STD-130N. SUPPLIERS WILL INCORPORATE THE 2-D IUID MARKING ON THEIR INDIVIDUAL ID PLATES. THE HEIGHT OF EACH ALPHANUMERIC CHARACTER IN THE HUMAN READABLE FORMAT SHALL BE A MAXIMUM OF 0.125 INCH. MARKINGS FOR BOTH THE MACHINE READABLE FORMAT AND HUMAN READABLE FORMAT SHALL BE TO SAE AS9132 WITH AN ALLOWABLE DEPTH OF 0.0005 TO 0.0030 INCH. THE LOCATION OF THE IUID MARKING IS NOT REQUIRED ON THE ENGINEERING DRAWINGS I.E. AN ENGINEERING CHANGE ORDER TO UPDATE THE DRAWINGS IS NOT REQUIRED. THE MARKINGS SHALL ONLY BE PLACED IN AREAS THAT WILL NOT BE DETRIMENTAL TO THE PART. INTRUSIVE MARKINGS SHALL NOT BE USED TO MARK FATIGUE AND FRACTURE CRITICAL (F&FC) OR CRITICAL SAFETY ITEM (CSI) PARTS. THE CONTRACTOR SHALL IDENTIFY THESE LOCATIONS AND GAIN THE APPROPRIATE A-10 ENGINEERING AUTHORITY

APPROVAL PRIOR TO IMPLEMENTING.

10. USE OF ANY PROCESS OR MANUFACTURING TECHNIQUE WHICH CREATES A NET EDGE ON A METALLIC PART BY

RELYING ON HEAT AT OR ABOVE THE PARTS MELTING POINT TO PRODUCE THE CUT IS NOT GENERALLY AUTHORIZED (I.E. LASER CUTTING, ELECTRICAL DISCHARGE MACHINE (EDM), PLASMA CUTTING, ETC.) WITHOUT PRIOR A-10 SYSTEM PROGRAM OFFICE APPROVAL. LIKEWISE, OTHER NON-HEAT GENERATING CUTTING PROCESSES INVOLVING HIGH PRESSURE FLUIDS AND SLURRIES (I.E., WATER JET) ARE ALSO NOT CURRENTLY APPROVED FOR USE IN THE PRODUCTION OF A-10 PARTS. ONLY THOSE PROCESSES CONTROLLED BY A-10 APPROVED PROGRAM SPECIFICATIONS AND A-10 DRAWINGS ARE PERMITTED TO BE USED IN THE MANUFACTURE OF A-10 PARTS AND

ASSEMBLIES.

11. THE PRIME CONTRACTOR SHALL USE SERIAL NUMBERS TO CONTROL AND PROVIDE TRACEABILITY TO THE LOWER

SPEED BRAKE (162D712170-1001) ASSEMBLIES. THE PRIME CONTRACTOR SHALL PRESENT THE SERIALIZATION METHOD TO THE GOVERNMENT IN THE FORM OF A REVISION TO THE SERIAL NUMBER CONTROL PLAN, 162S900706, FOR APPROVAL PRIOR TO USE. THIS PLAN WILL DEFINE THE SERIALIZATION ASSIGNMENT, CONTROL, AND DOCUMENTATION. ADDITIONALLY, THE PRIME CONTRACTOR SHALL REVIEW THE EXISTING NAMEPLATES DELIVERED UNDER THE TDP FOR CONTINUED USE UNDER THIS CONTRACT. IF CHANGES ARE REQUIRED, THE PRIME CONTRACTOR SHALL PRESENT THE NECESSARY DESIGN CHANGES TO THE APPLICABLE ENGINEERING AUTHORITY.

12. FOR PART NUMBERS 162D712170-1001 AND 162D712171-2051, PART REPORT NOTE GDT-27 AND/OR GDT-02 (IF PRESENT)

SHALL NOT BE APPLIED. THESE PARTS/ASSEMBLIES SHALL MEET TDP REQUIREMENTS IN AN UN-RESTRAINED AND

UN-WEIGHTED CONDITION.

13. WHEN FABRICATING PARTS IAW S-F502 PER PART REPORT REQUIREMENTS:

A. OPTION 2 OF PARAGRAPH 4.2.2.2 SHALL NOT BE USED.

B. ALL REFERENCES TO BMS 8-79 SHALL BE DISREGARDED.

C. FM300M FILM ADHESIVE SHALL NOT BE USED.

D. WHEN CORE SPLICING OR CURING OF B-M101 FOAMING ADHESIVE IS ACCOMPLISHED OTHER THAN AS

PART OF AN ASSEMBLY BOND, THE CURE CYCLE TIME LIMITS SHALL BE 60 MINUTES MINIMUM TIME AT

TEMPERATURE AND 120 MINUTES MAXIMUM TIME AT TEMPERATURE.

14. THE REQUIREMENTS OF 160D900004 SHALL APPLY AFTER PART/ASSEMBLY INSTALLATION AND APPROPRIATE

RIGGING PROCEDURES ARE PERFORMED. THOUGH PART NUMBERS REFERENCED IN THE DRAWING REFER TO LEGACY PARTS (160D…), ALL REQUIREMENTS SHALL BE APPLICABLE FOR EQUIVALENT PARTS PROCURED (162D…).

15. FOR INFORMATION ONLY: REFERENCES TO T.O. 1A-10C-520 MAY EXIST IN THE PROVIDED TECHNICAL DATA

PACKAGE. THIS T.O. DEFINES THE REPLACEMENT OF THE THIN-SKINNED WING ASSEMBLY WITH THE ENHANCED WING ASSEMBLY. T.O. 1A-10C-520 IS NOT REQUIRED FOR THE MANUFACTURE OF PART NUMBER 162D712170-1001 OR ITS SUBCOMPONENTS. THE PARTS PROCURED UNDER THIS CONTRACT WILL BE USED ON “AIRCRAFT MODIFIED BY T.O. 1A-10C-520”.

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16. THE SPEED BRAKE ASSEMBLY IS AN INTERCHANGEABLE ITEM IN ACCORDANCE WITH MIL-I-8500 AS DEFINED BY

THE TECH DATA PACKAGE. A FIRST ARTICLE DEMONSTRATION IS REQUIRED TO PROVE INTERCHANGEABILITY IN ACCORDANCE WITH MIL-I-8500, INCLUDING BACKWARD INTERCHANGEABILITY WITH ENHANCED WING ASSEMBLY (EWA) COMPONENTS/ASSEMBLIES, AND SHALL BE COMPLETED PRIOR TO FIRST ARTICLE ACCEPTANCE. THE

CONTRACTOR SHALL BE RESPONSIBLE TO DEFINE THE METHOD OF CONTROLLING INDIVIDUAL

INTERCHANGEABLE AND REPLACEABLE (I&R) FEATURES, THROUGH THE USE OF TOOLING AND/OR OTHER MEANS.

17. THE PARTS LISTED BELOW ARE CLASSIFIED CRITICAL SAFETY ITEMS (CSI) AND SHALL BE MANAGED IN

ACCORDANCE WITH USAF INSTRUCTION – AFI 20-106, MANAGEMENT OF AVIATION CRITICAL SAFETY ITEMS. THE CRITICAL PROCESSES AND CHARACTERISTICS ARE IDENTIFIED FOR EACH PART/ASSEMBLY BELOW. THE METHOD OF SURVEILLANCE SHALL BE COMMENSURATE WITH DCMA AGENCY CSI POLICY FOR CSIs WITH DEFINED CRITICAL

CHARACTERISTICS.

162D712170-1001 SPEED BRAKE ASSY – LOWER

162D712171-2005 SKIN, UPPER, LH, PANEL ASSEMBLY, HONEYCOMB - LOWER SPEED BRAKE

162D712171-2007 SKIN, LOWER, LH, PANEL ASSEMBLY, HONEYCOMB - LOWER SPEED BRAKE

162D712171-2051 PANEL ASSEMBLY, HONEYCOMB, LH - LOWER SPEED BRAKE

162D712571-1001 FITTING ASSEMBLY- INBD HINGE & ACTUATOR ATCH, LOWER SPEED BRAKE

162D712571-2001 FITTING, LH, FITTING ASSY- INBD HINGE & ACTUATOR ATCH, LOWER SPEED

BRAKE

162D712551-5001 FORGING, LH, FORGING - HINGE & ACTR ATCH FTG SPEED BRAKE

162D712572-1001 FITTING ASSEMBLY- OUTBD HINGE ACTUATOR ATCH, LOWER SPEED BRAKE

162D712572-2001 FITTING, LH, FITTING ASSY- OUTBD HINGE ACTUATOR ATCH, LOWER SPEED

BRAKE

ATTRIBUTES/DATA LISTED IN THE FOLLOWING TABLES WITHIN BRACKETS (E.G. [FEATURE 1] OR [MINIMUM TORQUE]) CAN BE FOUND IN THE ASSOCIATED PART REPORT. REFERENCE ASSOCIATED PART REPORT(S) FOR CLARIFICATION. IF ANY DISCREPANCIES BETWEEN THE DATA IN THE TABLES BELOW AND THE ASSOCIATED

PART REPORT ARE IDENTIFIED, THE DATA IN THE PART REPORT SHALL TAKE PRECEDENCE.

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Part Number 162D712170‐1001

Description SPEED BRAKE ASSY ‐ LOWER (Configuration Item)

Critical Characteristic 1

ID‐02/03‐I only; This part/assembly is interchangeable in accordance with MIL‐I‐ 8500D and is controlled through control media. The interchangeable features of this part/assembly are: [feature1] [feature2] [feature3] [feature4] [feature5] [feature6] Mark part/assembly using P.S. 16001 rubber stamp or stencil methods only or alternatively Z‐R701, code RS or ST with the following: "INTERCHANGEABLE ‐ DO

NOT ALTER".

Critical Characteristic 2 FAST‐02/02‐Install Bolts, Nuts and Washers; Install bolts, nuts and washers in accordance with SP900. Unless otherwise noted, wrenching torque requirements for specific nut/bolt combinations shall be in accordance with 162S900704.

Critical Characteristic 3

FAST‐06/02‐Pin and Collar Install; Install threaded pin and collar/nut type fasteners in accordance with G‐F604. Unless otherwise noted, wrenching torque requirements for specific pin/nut combinations shall be in accordance with 162S900704. Care shall be taken to properly back up the structure into which pins are being installed/driven to avoid cracking.

Critical Characteristic 4

FAST‐33/02‐Edge Distance; Unless otherwise noted, minimum edge distance for all fasteners with hole diameter and tolerance defined by this assembly is the greater of .25 or twice the fastener diameter from the closest part edge to the fastener center minus .03.

Critical Characteristic 5 FAST‐08/01‐Fastener Orientation Specified; Unless otherwise noted, fastener head/tail orientation shall be as modeled.

Critical Characteristic 6 FAST‐32/01‐Hole Size Attribute; Fastener hole size and tolerance per "HOLE DIA/TOL" attribute. Standard holes sizes per the applicable fastener installation specification if the attribute is blank.

Critical Characteristic 7

GDT‐27/01‐Nominal Restraint; The part shall be capable of being brought to the datum simulators and/or its nominal condition by applying up to five pounds of force within any twelve‐inch interval or an equivalent force within a smaller interval (e.g., half the allowed force at six‐inch intervals, one quarter of the allowed force at three‐ inch intervals). Any number of allowed force units may be applied as long as the equivalent forces and intervals are maintained.

Critical Characteristic 8 MISC‐01/01‐Storage, Handling, Shipping; Storage, handling and shipping shall be in accordance with Z‐P801.

Critical Characteristic 9 MACH‐21/01‐Deburr; Deburr part per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 10 FAST‐01/02‐Common Rivet Install; Install solid common rivets and tubular rivets in accordance with G‐F601. Rivet length shown is approximate.

Critical Characteristic 11 CRIT‐03/02‐Assy With Traceable Components; This assembly/installation contains one or more traceable parts and/or assemblies. Traceability shall be in accordance with 162S900706.

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Part Number 162D712171‐2005

Description SKIN, UPPER, LH, PANEL ASSEMBLY, HONEYCOMB ‐ LOWER SPEED BRAKE

Critical Characteristic 1 CRIT‐02/01‐Class 1B; This is a Fatigue Critical part, Class 1B, in accordance with

SM160M1000.

Critical Characteristic 2

GDT‐02/01‐Restraint; The part shall be capable of being brought to the datum simulators by applying up to five pounds of force within any twelve‐inch interval or an equivalent force within a smaller interval (e.g., half the allowed force at six‐inch intervals, one quarter of the allowed force at three‐inch intervals). Any number of allowed force units may be applied as long as the equivalent forces and intervals are maintained.

Critical Characteristic 3 SHT‐04/01‐Deburr; Sharp edges or burrs shall be removed per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 4

002235/01; ROUTED EDGES OF PART TO HAVE MAXIMUM SURFACE ROUGHNESS OF

125 MICRO‐INCHES RA PER ASME B46.1 (1995). SURFACE TO BE VOID OF MACHINE

MARKS, GROOVES, AND NICKS.

Critical Characteristic 5 CM‐11/01‐Chem Mill Only; Chemically mill per P.S. 20022 or alternatively per A‐F201.

Mechanical milling shall not be used as an alternative to chemical milling.

Critical Characteristic 6 CM‐04/01‐Chem Mill Transition; Unless otherwise specified, the radius extension or transition zone for chemically milled steps shall be a maximum of four times the depth of cut.

Part Number 162D712171‐2007

Description SKIN, LOWER, LH, PANEL ASSEMBLY, HONEYCOMB ‐ LOWER SPEED BRAKE

Critical Characteristic 1 CRIT‐02/01‐Class 1B; This is a Fatigue Critical part, Class 1B, in accordance with

SM160M1000.

Critical Characteristic 2

GDT‐02/01‐Restraint; The part shall be capable of being brought to the datum simulators by applying up to five pounds of force within any twelve‐inch interval or an equivalent force within a smaller interval (e.g., half the allowed force at six‐inch intervals, one quarter of the allowed force at three‐inch intervals). Any number of allowed force units may be applied as long as the equivalent forces and intervals are maintained.

Critical Characteristic 3

002235/01; ROUTED EDGES OF PART TO HAVE MAXIMUM SURFACE ROUGHNESS OF

125 MICRO‐INCHES RA PER ASME B46.1 (1995). SURFACE TO BE VOID OF MACHINE

MARKS, GROOVES, AND NICKS.

Critical Characteristic 4 SHT‐04/01‐Deburr; Sharp edges or burrs shall be removed per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 5 CM‐11/01‐Chem Mill Only; Chemically mill per P.S. 20022 or alternatively per A‐F201.

Mechanical milling shall not be used as an alternative to chemical milling.

Critical Characteristic 6 CM‐04/01‐Chem Mill Transition; Unless otherwise specified, the radius extension or transition zone for chemically milled steps shall be a maximum of four times the depth of cut.

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Part Number 162D712171‐2051

Description HONEYCOMB PANEL ASSY

Critical Characteristic 1

(CRIT‐12) Traceability is required per 162S900706, Code T. Serialize each assembly using identification marking in accordance with P.S. 16001, rubber stamp method only or Z‐R701, code RS. Serialization marking to be located as indicated in the MBD dataset.

Critical Characteristic 2 (COMP‐01) Fabricate assembly per S‐F501, Type I (Primary Structure).

Critical Characteristic 3 (COMP‐25) Adhesively bond indicated components in accordance with S‐F501. Voids in the bondline are unacceptable.

Critical Characteristic 4 (COMP‐21) Relieve core as required to accommodate fasteners and other interfering features. Fill void areas using adhesive foam per S‐F501.

Critical Characteristic 5 (CORE‐13) Machine core/core assemblies in accordance with S‐F501.

Critical Characteristic 6 (SHT‐04) Sharp edges or burrs shall be removed per P.S. 20024 or alternatively per G‐ F101.

Critical Characteristic 7

(COMP‐27) Unless otherwise noted, core to core and core to SPAR AND CORE TO FILLER bonding shall be in accordance with S‐F501 using one layer of B‐M101, Type I core foam adhesive. A second layer of adhesive may be used in areas where it is necessary.

Critical Characteristic 8 (COMP‐20) Any disbonds at edge of core and skin in the potted area shall be rebonded prior to potting per B‐F501 using EA9330.

Critical Characteristic 9

(GDT‐27) The part shall be capable of being brought to the datum simulators and/or its nominal condition by applying up to five pounds of force within any twelve‐inch interval or an equivalent force within a smaller interval (e.g., half the allowed force at six‐inch intervals, one quarter of the allowed force at three‐inch intervals). Any number of allowed force units may be applied as long as the equivalent forces and intervals are maintained.

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Part Number 162D712571‐1001

Description FITTING ASSEMBLY‐ INBD HINGE & ACTUATOR ATCH, LOWER SPEED BRAKE

Critical Characteristic 1

BUSH‐01/01‐Press Fit Bushing Installation; Install indicated press fit bushing(s) and/or bearing(s) by applying MIL‐PRF‐23377, Type I, Class C primer to the outer diameter of the bushing or bearing and while primer is still wet, using a hydraulic/mechanical press, press bushing or bearing into hole until it is properly seated . Subsequent to bushing or bearing installation apply AMS‐S‐8802 sealant to both ends of the bushing or bearing plus 0.12 to 0.25 inches of the surrounding housing surface, covering the interface. Care shall be taken to prevent application of sealant to any part of the bushing or bearing which may interfere with its function.

Critical Characteristic 2 BUSH‐02/01‐Bushing and Bearing Ream; Ream indicated hole(s) to dimensions shown in MBD dataset.

Critical Characteristic 3 MACH‐17/01‐Machining High Strength Steels; Any machining after final heat treatment shall be in accordance with P.S. 20710 or alternatively F‐F101.

Critical Characteristic 4 MACH‐19/01‐Roughness ‐ Surface Specific; Unless otherwise noted, maximum surface finish of [feature(s)] to be [roughness] micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 5 MACH‐21/01‐Deburr; Deburr part per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 6

BUSH‐16/01‐Bearing Install‐ Roller Stake; Install indicated bearing(s) using MIL‐PRF‐ 23377, Type I, Class C primer applied to the outer diameter of the bearing. Roller swage in accordance with P.S. 17031 or alternately per NAS0331, Method 200, using the MBD dataset specified bore dimensions. Within 100 hours of primer application to the bearing, proof load bearing to [load] pounds in accordance with SP 1613. After proof load testing, apply AMS‐S‐8802 sealant to both ends of the bearing(s) plus 0.12 to 0.25 inches of the surrounding housing surface, covering the bearing/housing interface. Care shall be taken to prevent application of sealant to any part of the bearing which may interfere with its function.

Critical Characteristic 7 MACH‐19/01‐Roughness ‐ Surface Specific; Unless otherwise noted, maximum surface finish of [feature(s)] to be [roughness] micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 8

MACH‐11/01‐Mismatch; Unless otherwise specified, general surface mismatch shall not exceed [general mismatch] inches. Mismatch within 0.060 inches of the tangency of intersecting features (such as the intersection of a corner radius and the side of a stiffener) shall not exceed [feature mismatch] inches, except that mismatch at intersections of equal height flanges and stiffeners shall not exceed [height mismatch] inches. The fillet radius associated with any surface mismatch shall be [minimum fillet] inches minimum.

Critical Characteristic 9 MACH‐04/01‐Break edges; Unless otherwise noted, break all sharp edges [lower] to [limit] inches per P.S. 20024 or alternatively per G‐F101.

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Part Number 162D712571‐2001

Description FITTING, LH, FITTING ASSY‐ INBD HINGE & ACTUATOR ATCH, LOWER SPEED BRAKE

Critical Characteristic 1 CRIT‐02/01‐Class 1B; This is a Fatigue Critical part, Class 1B, in accordance with

SM160M1000.

Critical Characteristic 2 SP‐15/01‐Saturation Peen Variable; Unless otherwise noted, shot peen all surfaces per AMS 2430 to provide 200% coverage, using an Almen intensity of [intensity] and a shot size of [lower limit] to [upper limit].

Critical Characteristic 3 SP‐07/01‐Saturation Peen Variable/Local; Shot peen indicated surfaces per AMS 2430 to provide 200% coverage, using an Almen intensity of [intensity] and a shot size of [lower limit] to [upper limit].

Critical Characteristic 4 SP‐02/01‐Edge Break; Prior to shot peening, unless otherwise noted, break all sharp edges 0.02 to 0.03 inches per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 5 HT‐01/01‐HP9‐4‐30; Heat treat HP9‐4‐30 material to 220‐240 ksi ultimate tensile strength per AMS 2759/2, except that partial decarburization shall not exceed 0.003 inches.

Critical Characteristic 6

NDT‐04/01‐Mag Particle; Magnetic particle inspect per ASTM E1444. Relevant linear indications are unacceptable. Linear indications are those indications in which the length is more than three times the width. Magnetic inspection shall be performed just prior to shot peening and again after cadmium plating.

Critical Characteristic 7 MACH‐01/01‐Roughness; Unless otherwise noted, maximum surface roughness of part to be 125 micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 8 MACH‐13/01‐Local Surface Roughness; Maximum surface roughness of indicated area(s) to be [roughness] micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 9 MACH‐21/01‐Deburr; Deburr part per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 10

MACH‐11/01‐Mismatch; Unless otherwise specified, general surface mismatch shall not exceed [general mismatch] inches. Mismatch within 0.060 inches of the tangency of intersecting features (such as the intersection of a corner radius and the side of a stiffener) shall not exceed [feature mismatch] inches, except that mismatch at intersections of equal height flanges and stiffeners shall not exceed [height mismatch] inches. The fillet radius associated with any surface mismatch shall be [minimum fillet] inches minimum.

Critical Characteristic 11 MACH‐17/01‐Machining High Strength Steels; Any machining after final heat treatment shall be in accordance with P.S. 20710 or alternatively F‐F101.

Critical Characteristic 12

FIN‐14/02‐Cad Plate, 0.0005" Min Thk; Cadmium‐titanium plate per MIL‐STD‐1500, Type II, Class 1. Alternative processes are low hydrogen embrittlement cadmium plate per P.S. 13144, Type II, Class 1 or vacuum cadmium plate per AMS‐C‐8837, Type II, Class 1.

Critical Characteristic 13 HT‐11/01‐No Post HT Straighten; No straightening allowed after final heat treat.

Critical Characteristic 14 GEN‐09/01‐Material Sub; Material substitution permissible per 162S900701.

Critical Characteristic 15 MISC‐01/01‐Storage, Handling, Shipping; Storage, handling and shipping shall be in accordance with Z‐P801.

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Part Number 162D712551‐5001

Description FORGING, LH, FORGING ‐ HINGE & ACTR ATCH FTG SPEED BRAKE

Critical Characteristic 1 CRIT‐02/01‐Class 1B; This is a Fatigue Critical part, Class 1B, in accordance with

SM160M1000.

Critical Characteristic 2 MISC‐01/01‐Storage, Handling, Shipping; Storage, handling and shipping shall be in accordance with Z‐P801.

Critical Characteristic 3 NDT‐06/01‐Sonic Inspect; Ultrasonically inspect forging starting stock per AMS‐STD‐ 2154, Class A.

Critical Characteristic 4 FORG‐14/01‐Decarb; Decarburization shall not exceed 0.050 inches when measured in accordance with AMS 6526.

Critical Characteristic 5 FORG‐01/01‐First Art; Forging first article approval and production control shall be in accordance with AMS 2375.

Critical Characteristic 6 FORG‐02/01‐Grain Flow; Primary grain flow shall be as shown in the MBD dataset.

Critical Characteristic 7

FORG‐03/01‐Grain Flow; First article grain flow verification shall be accomplished by sectioning and etching per AMS 2375 at locations as shown in the MBD dataset.

Grain flow shall conform to the general shape of the forging and shall have no re‐ entrant flow lines.

Critical Characteristic 8

FORG‐34/01‐Tensile Req'ts; Minimum acceptance criteria for tensile specimen [number 1] shall be: Specimen Orientation: [orientation 1]; Ultimate Tensile Strength:

[number 2] ksi; Tensile Yield Strength: [number 3] ksi; Elongation: [number 4]%;

Reduction of Area [number 5]%.

Critical Characteristic 9

FORG‐34/01‐Tensile Req'ts; Minimum acceptance criteria for tensile specimen [number 1] shall be: Specimen Orientation: [orientation 1]; Ultimate Tensile Strength:

[number 2] ksi; Tensile Yield Strength: [number 3] ksi; Elongation: [number 4]%;

Reduction of Area [number 5]%.

Critical Characteristic 10

FORG‐34/01‐Tensile Req'ts; Minimum acceptance criteria for tensile specimen [number 1] shall be: Specimen Orientation: [orientation 1]; Ultimate Tensile Strength:

[number 2] ksi; Tensile Yield Strength: [number 3] ksi; Elongation: [number 4]%;

Reduction of Area [number 5]%.

Critical Characteristic 11

FORG‐34/01‐Tensile Req'ts; Minimum acceptance criteria for tensile specimen [number 1] shall be: Specimen Orientation: [orientation 1]; Ultimate Tensile Strength:

[number 2] ksi; Tensile Yield Strength: [number 3] ksi; Elongation: [number 4]%;

Reduction of Area [number 5]%.

Critical Characteristic 12

FORG‐34/01‐Tensile Req'ts; Minimum acceptance criteria for tensile specimen [number 1] shall be: Specimen Orientation: [orientation 1]; Ultimate Tensile Strength:

[number 2] ksi; Tensile Yield Strength: [number 3] ksi; Elongation: [number 4]%;

Reduction of Area [number 5]%.

Critical Characteristic 13 GEN‐09/01‐Material Sub; Material substitution permissible per 162S900701.

Critical Characteristic 14 FORG‐12/01‐Flash; Flash extension tolerance is [dimension 1] inches maximum.

HILL AFB FORM 462 Page 10 of 16

Critical Characteristic 15

FORG‐44/01‐First Article Tensile ‐ Steel; First article tensile property verification shall consist of testing specimen numbers [number1] thru [number2] in accordance with ASTM E8. Sample orientation and location, within the forging, shall be as shown in the MBD dataset. Specimen geometry shall be in accordance with ASTM E8 using a minimum gage diameter of 0.25 inches. Heat treat tensile samples to [tensile range] ksi ultimate tensile strength per AMS 2759/2, except that partial decarburization shall not exceed 0.003 inches.

Critical Characteristic 16

FORG‐45/01‐Recurring Tensile ‐ Steel; Recurring lot tensile property capability verification shall consist of testing specimen number(s) [number(s)] in accordance with ASTM E8. Sample orientation and location, within the forging, shall be as shown in the MBD dataset. Specimen geometry shall be in accordance with ASTM E8.

Testing frequency shall be one set of specimens per forging lot. Heat treat tensile samples to [tensile range] ksi ultimate tensile strength per AMS 2759/2, except that partial decarburization shall not exceed 0.003 inches.

HILL AFB FORM 462 Page 11 of 16

Part Number 162D712572‐1001

Description FITTING ASSEMBLY‐ OUTBD HINGE ACTUATOR ATCH, LOWER SPEED BRAKE

Critical Characteristic 1

BUSH‐01/01‐Press Fit Bushing Installation; Install indicated press fit bushing(s) and/or bearing(s) by applying MIL‐PRF‐23377, Type I, Class C primer to the outer diameter of the bushing or bearing and while primer is still wet, using a hydraulic/mechanical press, press bushing or bearing into hole until it is properly seated . Subsequent to bushing or bearing installation apply AMS‐S‐8802 sealant to both ends of the bushing or bearing plus 0.12 to 0.25 inches of the surrounding housing surface, covering the interface. Care shall be taken to prevent application of sealant to any part of the bushing or bearing which may interfere with its function.

Critical Characteristic 2 MACH‐17/01‐Machining High Strength Steels; Any machining after final heat treatment shall be in accordance with P.S. 20710 or alternatively F‐F101.

Critical Characteristic 3 BUSH‐02/01‐Bushing and Bearing Ream; Ream indicated hole(s) to dimensions shown in MBD dataset.

Critical Characteristic 4 MACH‐21/01‐Deburr; Deburr part per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 5 MACH‐19/01‐Roughness ‐ Surface Specific; Unless otherwise noted, maximum surface finish of [feature(s)] to be [roughness] micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 6

BUSH‐16/01‐Bearing Install‐ Roller Stake; Install indicated bearing(s) using MIL‐PRF‐ 23377, Type I, Class C primer applied to the outer diameter of the bearing. Roller swage in accordance with P.S. 17031 or alternately per NAS0331, Method 200, using the MBD dataset specified bore dimensions. Within 100 hours of primer application to the bearing, proof load bearing to [load] pounds in accordance with SP 1613. After proof load testing, apply AMS‐S‐8802 sealant to both ends of the bearing(s) plus 0.12 to 0.25 inches of the surrounding housing surface, covering the bearing/housing interface. Care shall be taken to prevent application of sealant to any part of the bearing which may interfere with its function.

Critical Characteristic 7 MACH‐19/01‐Roughness ‐ Surface Specific; Unless otherwise noted, maximum surface finish of [feature(s)] to be [roughness] micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 8

MACH‐11/01‐Mismatch; Unless otherwise specified, general surface mismatch shall not exceed [general mismatch] inches. Mismatch within 0.060 inches of the tangency of intersecting features (such as the intersection of a corner radius and the side of a stiffener) shall not exceed [feature mismatch] inches, except that mismatch at intersections of equal height flanges and stiffeners shall not exceed [height mismatch] inches. The fillet radius associated with any surface mismatch shall be [minimum fillet] inches minimum.

Critical Characteristic 9 MACH‐04/01‐Break edges; Unless otherwise noted, break all sharp edges [lower] to [limit] inches per P.S. 20024 or alternatively per G‐F101.

HILL AFB FORM 462 Page 12 of 16

Part Number 162D712572‐2001

Description FITTING, LH, FITTING ASSY‐ OUTBD HINGE ACTUATOR ATCH, LOWER SPEED BRAKE

Critical Characteristic 1 CRIT‐02/01‐Class 1B; This is a Fatigue Critical part, Class 1B, in accordance with

SM160M1000.

Critical Characteristic 2

NDT‐04/01‐Mag Particle; Magnetic particle inspect per ASTM E1444. Relevant linear indications are unacceptable. Linear indications are those indications in which the length is more than three times the width. Magnetic inspection shall be performed just prior to shot peening and again after cadmium plating.

Critical Characteristic 3 SP‐02/01‐Edge Break; Prior to shot peening, unless otherwise noted, break all sharp edges 0.02 to 0.03 inches per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 4 SP‐07/01‐Saturation Peen Variable/Local; Shot peen indicated surfaces per AMS 2430 to provide 200% coverage, using an Almen intensity of [intensity] and a shot size of [lower limit] to [upper limit].

Critical Characteristic 5 SP‐15/01‐Saturation Peen Variable; Unless otherwise noted, shot peen all surfaces per AMS 2430 to provide 200% coverage, using an Almen intensity of [intensity] and a shot size of [lower limit] to [upper limit].

Critical Characteristic 6 MACH‐21/01‐Deburr; Deburr part per P.S. 20024 or alternatively per G‐F101.

Critical Characteristic 7 MACH‐13/01‐Local Surface Roughness; Maximum surface roughness of indicated area(s) to be [roughness] micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 8

MACH‐11/01‐Mismatch; Unless otherwise specified, general surface mismatch shall not exceed [general mismatch] inches. Mismatch within 0.060 inches of the tangency of intersecting features (such as the intersection of a corner radius and the side of a stiffener) shall not exceed [feature mismatch] inches, except that mismatch at intersections of equal height flanges and stiffeners shall not exceed [height mismatch] inches. The fillet radius associated with any surface mismatch shall be [minimum fillet] inches minimum.

Critical Characteristic 9 MACH‐01/01‐Roughness; Unless otherwise noted, maximum surface roughness of part to be 125 micro‐inches Ra per ASME B46.1 (1995).

Critical Characteristic 10 MACH‐17/01‐Machining High Strength Steels; Any machining after final heat treatment shall be in accordance with P.S. 20710 or alternatively F‐F101.

Critical Characteristic 11 HT‐01/01‐HP9‐4‐30; Heat treat HP9‐4‐30 material to 220‐240 ksi ultimate tensile strength per AMS 2759/2, except that partial decarburization shall not exceed 0.003 inches.

Critical Characteristic 12 HT‐11/01‐No Post HT Straighten; No straightening allowed after final heat treat.

Critical Characteristic 13

FIN‐14/02‐Cad Plate, 0.0005" Min Thk; Cadmium‐titanium plate per MIL‐STD‐1500, Type II, Class 1. Alternative processes are low hydrogen embrittlement cadmium plate per P.S. 13144, Type II, Class 1 or vacuum cadmium plate per AMS‐C‐8837, Type II, Class 1.

Critical Characteristic 14 MISC‐01/01‐Storage, Handling, Shipping; Storage, handling and shipping shall be in accordance with Z‐P801.

Critical Characteristic 15 GEN‐09/01‐Material Sub; Material substitution permissible per 162S900701.

HILL AFB FORM 462 Page 13 of 16

18. IF THE PRIME CONTRACTOR IDENTIFIES ANY PROPRIETARY REQUIREMENTS (E.G. PROCESS SPECIFICATIONS, MATERIAL SPECIFICATIONS, ETC.) WITHIN THE TDP WHERE A NON-PROPRIETARY ALTERNATIVE DOESN’T EXIST, THEY SHALL DOCUMENT THE SPECIFIC CASE. THEY THEN SHALL PROVIDE A SUITABLE NON-PROPRIETARY ALTERNATIVE SOLUTION (E.G. REDESIGN, ALTERNATE NON-PROPRIETARY PROCESS SPECIFICATION, ETC.) WITH A TECHNICAL JUSTIFICATION TO INCLUDE ANALYSIS OR TEST DATA, IF APPLICABLE, TO THE GOVERNMENT IN THE

FORM OF A TDP CHANGE REQUEST.

THE FOLLOWING SPECIFICATIONS WILL NOT BE PROVIDED WITH THE TECHNICAL DATA PACKAGE DUE TO

PROPRIETARY RIGHTS (LIST MAY NOT BE ALL INCLUSIVE):

BAC5317 FIBER REINFORCED COMPOSITE PARTS

BAC

PHOSPHORIC ACID ANODIZATION OF ALUMINUM FOR STRUCTURAL BONDING

BMS 8-

GLASS FABRIC PREIMPREGNATED HIGH-TEMPERATURE-RESISTANCE EPOXY RESIN

BMS 5-

FOAMING ADHESIVES

BMS 8-

GLASS FABRIC PREIMPREGNATED EPOXY RESIN LOW TEMPERATURE CURING

P.S.

11001

CEMENTING OF RUBBER, PLASTICS, FABRICS, AND FOAMS

P.S.

11344

SEALING METHODS

P.S.

12050

PICKLING

P.S.

13144

PLATING, LOW EMBRITTLEMENT CADMIUM, ELECTRO (HIGH STRENGTH STEELS)

P.S.

13375

APPLICATION OF EPOXY PRIMER

P.S.

13555

COATING, ANTI-CHAFE

P.S.

14007

FORMING ALUMINUM ALLOY WROUGHT PRODUCTS

P.S.

14191

FABRICATION OF METAL NAMEPLATES AND PANELS-ANODIZE-PHOTOGRAPHIC

PROCESS

P.S.

16001

MARKING OF FABRICATED PARTS

P.S.

16014.1

MARKING OF ITEMS WITH A 2D MATRIX CODE (ST. CHARLES WEAPONS [NAVWEPS]

AND AIR FORCE PROGRAMS)

P.S.

17004

SAFETYING PRACTICES

P.S.

17031

BEARINGS/BUSHINGS, GROOVED OUTER RACE; STAKING OF

P.S.

17169

BONDING AND GROUNDING; ELECTRICAL

P.S.

19424

FASTENERS, RIVNUT; INSTALLATION OF

HILL AFB FORM 462 Page 14 of 16

P.S.

20022

CHEMICAL MILLING

P.S.

20024

DEBURRING, BLENDING, AND SANDING OF METAL PARTS

P.S.

20710

HIGH STRENGTH STEELS, MACHINING AND GRINDING OF

19. IF ERRORS, INCONSISTENCIES, OR PROBLEMS WITHIN THE TDP ARE ENCOUNTERED, THE PRIME CONTRACTOR

SHALL DOCUMENT THE SPECIFIC CASE AND PROVIDE A SOLUTION TO THE GOVERNMENT IN THE FORM OF TDP

CHANGE REQUEST.

20. TOOLING DEVELOPMENT: TOOLING IS REQUIRED FOR THE MANUFACTURE OF THIS PART. THE CONTRACTOR WILL

NEED TO DEVELOP/MANUFACTURE ITS OWN TOOLING AS REQUIRED. PRIOR TO TOOL DEVELOPMENT, THE CONTRACTOR SHALL ADVISE THE GOVERNMENT IN WRITING OF THEIR INTENT TO DEVELOP NEW TOOLING. THE CONTRACTOR SHALL NOT PROCEED TO DEVELOP NEW TOOLING WITHOUT THE EXPRESS CONSENT OF THE GOVERNMENT PROCURING AGENCY. THE TOOLING LISTED BELOW IS NOT CURRENTLY AVAILABLE TO CONTRACTORS FOR MANUFACTURING BUT TOOLING DRAWINGS/3-D MODELS MAY BE AVAILABLE FOR USE AS POSSIBLE TOOLING DESIGN CONCEPTS. ANY TOOLING DRAWINGS/3-D MODELS PROVIDED ARE TO BE USED FOR REFERENCE ONLY (REFERENCE ENGINEERING DATA LIST (EDL) FOR TOOLING INFORMATION). THE ACCURACY OF THESE TOOLING DRAWINGS/MODELS HAS NOT BEEN VERIFIED; IF THE CONTRACTOR CHOOSES TO USES THIS DATA IT IS AT THEIR OWN DISCRETION. THE GOVERNMENT IS NOT LIABLE FOR ANY INACCURACIES PRESENT IN THIS TECHNICAL DATA. THE CONTRACTOR MAY REQUEST TO INSPECT SIMILAR EXISTING LEGACY TOOLING.

ARRANGEMENTS FOR TOOL INSPECTION (OF THE EXISTING GOVERNMENT LEGACY TOOLING, IF REQUIRED) SHALL BE MADE BY CONTACTING THE APPROPRIATE CONTRACTING PERSONNEL AND THE ENGINEERING AUTHORITY LISTED AT THE BOTTOM OF THIS DOCUMENT THROUGH THE APPROPRIATE CONTRACTING PERSONNEL.

PARTIAL TOOL LISTING IS AS FOLLOWS:

IDENTIFICATION DESCRIPTION

162D712170-1001_AJ LOWER SPEED BRAKE ASSEMBLY JIG

160D712170-001ASF LOWER SPEED BRAKE ASSEMBLY FIXTURE – LEGACY TOOL

160D712171-001BAJ LOWER SPEED BRAKE PANEL ASSEMBLY BONDING ASSEMBLY JIG – LEGACY

TOOL

21. THE PRIME CONTRACTOR SHOULD WORK THROUGH THE GOVERNMENT PROCURING AGENCY TO CONTACT THE ENGINEERING ORGANIZATION LISTED IN THE OFFICE SYMBOL BLOCK LOCATED AT THE BOTTOM OF THIS DOCUMENT IN ORDER TO MAKE SURE ANY NEWLY DEVELOPED TOOLING AND FIXTURES WILL PRODUCE AN ACCEPTABLE PART THAT WILL FIT ON THE AIRCRAFT. THIS WILL MAKE SURE CHANGES AND CHECKS ARE DONE

EARLY TO PREVENT FAILURE OF THE FIRST ARTICLE.

22. IF POSSIBLE, THE FORGINGS SHALL BE PROCURED FROM SOURCES USING THE ORIGINAL CERTIFIED FORGING

PROCEDURES AND DIES/TOOLING.

A. PRIOR TO CONTRACT AWARD, THE DETAILED PART BIDDER SHALL PROVIDE CERTIFICATION FROM THE FORGING SOURCE TO THE GOVERNMENT THAT THE CERTIFIED DIES AND PROCEDURES ARE AVAILABLE AND

HILL AFB FORM 462 Page 15 of 16

THE FORGING SOURCE HAS AN AGREEMENT WITH THE DETAILED PART BIDDER TO PROVIDE FORGINGS FOR

THEIR USE IN THE EVENT THEY ARE THE SUCCESSFUL BIDDER.

B. PRIOR TO PRODUCTION, FORGING LOT QUALIFICATION SHALL BE ACCOMPLISHED AS SPECIFIED ON THE FORGING DRAWING. THE DETAILED PART CONTRACTOR SHALL ASSURE THAT THIS HAS BEEN ACCOMPLISHED BY THE FORGING SOURCE AND SHALL SUBMIT CERTIFIED DOCUMENTATION OF ACCOMPLISHMENT TO THE

GOVERNMENT.

HILL AFB FORM 462 Page 16 of 16

C. PRIOR TO CONTRACT AWARD, THE CONTRACTOR SHALL ADVISE THE GOVERNMENT IN WRITING OF THEIR INTENT TO PROCURE NEW FORGING DIES AND THE PROPOSED FORGING SOURCE. THE CONTRACTOR SHALL NOT PROCEED TO OBTAIN NEW DIES WITHOUT THE EXPRESS CONSENT OF THE GOVERNMENT PROCURING AGENCY. THE GOVERNMENT SHALL HAVE UNLIMITED USE OF THE DIES DEVELOPED UNDER THIS CONTRACT.

THE CONTRACTOR SHALL INFORM THE FORGING HOUSE IN WRITING AT THE SAME TIME THE ORDER FOR THE DIES IS PLACED THAT THE GOVERNMENT HAS UNLIMITED USE RIGHTS OF THE DIES AND FORWARD A COPY OF

THIS LETTER TO THE GOVERNMENT CONTRACTING OFFICER.