SOW_ATTACHMENT_B_Critical_Safety_Items_CSI_List.pdf

PDF 814 KB Posted May 25, 2018

Attached to: A-10 Thunderbolt Advanced-Wing Continuation Kit (ATTACK) Federal contract opportunity
Solicitation number: FA8202-18-R-1001
Issued by: Department of the Air Force Materiel Command Lifecycle Management Center Hill Air Force Base

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Written by GovTribe AI · Dec 31, 2023

This is a notice for a Request for Proposal from the Department of the Air Force Materiel Command Lifecycle Management Center for the A-10 Thunderbolt Advanced-Wing Continuation Kit (ATTACK). The RFP seeks proposals to provide continuation kits for the A-10 aircraft wing assembly, including required parts, materials, processes, and inspections. Proposals are due by the date specified in the RFP. The contract will involve handling of export-controlled technical data, so only contractors registered with Defense Logistics Services Center and approved to receive such data are eligible to receive full solicitation details and respond.

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SOW Attachment B - Critical Safety Items (CSI) List

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STATEMENT OF WORK ATTACHMENT B

CRITICAL SAFETY ITEMS (CSI) LIST

FOR

A-10 THUNDERBOLT ADVANCED-WING CONTINUATION

KITTING

(ATTACK)

18 May 2018

Prepared by:

AFLCMC/WWA

P Fighter/Bomber

Directorate Hill AFB, Utah 84056

REVISION

CONTROL

Note: The portion of the text affected by the current revision is indicated by vertical black lines in the outer left hand margin.

Revision Date Description Pages Changed

Initial 18 May 2018 Initial Release

1. PURPOSE

The following document, A3G-2016-185485, establishes critical safety requirements for the ATTACK wing assembly. Within this document, bracketed items, e.g., [PART #(S) OR DESC], [MIN-MAX HOLE SIZE], [feature1], [process], etc., indicate dimensions, features and/or processes that are explicitly defined in this document. This document shall be used in conjunction with all CSIs’ associated part reports.

A3G-2016-185485 Rev C

CRITICAL SAFETY ITEMS (CSI)

PROCESS LIST FOR A-10 EWA

16 May 2018 Created by:

AFLCMC/WWAE

Fighter/Bomber Directorate

Hill AFB, Utah 84056

REVISION CONTROL: Rev C

Prepared by:

Kaylon Anderson

AFLCMC/WWAEJ

A-10 Analysis Group

Approved by:

Michael Hackett, Jr.

AFLCMC/WWAE

A-10 Chief Engineer

Approved by:

Hazen Sedgwick

AFLCMC/WWAEJ

Lead, A-10 ASIP Engineer

Approved by:

Michael Anderson

AFLCMC/WWAEB

A-10 MECSIP Manager

Approved by:

George Rogers

AFLCMC/WWAEC

Lead, A-10 Repairs and Mods

Distribution Statement D: Distribution authorized to Department of Defense (DOD) and DOD Contractors only, Administrative/Operational Use, 27 April 2018. Other requests for this document shall be referred to the A-10 SPO AFLCMC/WWAE.

WARNING – This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec. 2751 et seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C. App 2401 et seq. Violations of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

DESTRUCTION NOTICE – Destroy by any method that will prevent disclosure of contents or reconstruction of the document.

.H.JR.1022907138 Date: 2018.05.18 16:34:37 -06'00'

SEDGWICK.HAZEN.LEON.127612

LEON.1276129020 9020

Date: 2018.05.18 07:00:50 -06'00'

E.P.1267570767

ROGERS.GEORGE.P.1267570767

Date: 2018.05.17 14:09:09 -06'00'

Revision Control

Revision Date Description Pages

Rev A 17 Feb 2016 Initial Release Rev B 23 March 2017 See Rev B document All Rev C 16 May 2018 See Rev C Change List All

Rev C Changes:

1. Re-evaluated the entire list on contract Legacy contract (Reference PW220003 Rev A)

2. Significant reduction of CSI processes needing to be 100% monitored.

1. The following tables constitute the A-10C Critical Safety Item (CSI) and associated Critical Safety Process (CSP) requirements for the Enhanced Wing Assembly (EWA), which will ultimately have part number 162D610010-1001.

2. The following terms are defined in accordance with USAF Instruction – AFI 20-106

a. Critical Safety Item (CSI). A part, assembly, installation equipment, launch equipment, recovery equipment, or support equipment for an aircraft or aviation weapons system that contains a characteristic any failure, malfunction, or absence of which could cause a catastrophic or critical failure resulting in the loss or serious damage to the aircraft or weapons system, an unacceptable risk of personal injury or loss of life, or an uncommanded engine shutdown that jeopardizes safety. Damage is considered serious or substantial when it would be sufficient to cause a "Class A" accident or a mishap of severity category I. The determining factor in CSIs is the consequence of failure, not the probability that the failure or consequence would occur. For the purpose of this instruction "Critical Safety Item", "Flight Safety Critical Aircraft Part", "Flight Safety Part", "Safety of Flight Item", and similar terms are synonymous. The term Critical Safety Item shall be the encompassing term used throughout this instruction.

b. Critical Safety Characteristic. Any feature, such as tolerance, finish, material composition, manufacturing, assembly or inspection process or product, which if nonconforming or missing could cause the failure or malfunction of the critical safety item.

3. These items shall be managed in accordance with USAF Instruction – AFI 20-106, Management of Aviation Critical Safety Items.

4. The method of surveillance shall be commensurate with DCMA agency CSI policy for initial and continuing surveillance of identified CSIs with defined critical characteristic(s).

5. The processes and characteristics identified under each associated part number will need to be inspected based upon item 3 above.

6. All parts on this list shall have dimensional inspection data reviewed for conformance.

7. The A3G-2016-185485, establishes critical safety requirements for the Enhanced Wing

Assembly. Within this document, bracketed items, e.g., [PART #(S) OR DESC], [MIN-MAX HOLE SIZE], [feature1], [process], etc., indicate dimensions, features and/or processes that are explicitly defined in this document. This document shall be used in conjunction with all CSIs’ associated part reports.

8. The noted Critical Characteristics refer to specific notes from the data package Part Reports. There may be multiple occurrences of a critical characteristic occurring in a Part Report. Each occurrence is considered critical. Example: 162D611604-5001 , Note FORG-53 occurs once for this part in the CSI List but twice in the Part Report. Both are considered critical items.

Part Number 162D611101-1001

Description CENTER WING - STRUCTURAL ASSEMBLY (CONFIGURATION ITEM)

Critical Characteristic 1

CW-01/02-Split Sleeve Cold Work; Cold work indicated hole(s) using the split sleeve process per FTI Process Specification 8101 or alternatively A-F302. Starting hole diameter shall be [minimum diameter] to [maximum diameter] inches.

Critical Characteristic 2 NDT-14/01-Special Hole Inspection; Inspect indicated hole(s) to quality level A1 in accordance with QATB M-40.

Part Number 162D611102-1001

Description AFT UPPER SKIN INSTL

(007993) COLD WORK INDICATED HOLE(S) IN THE 162D611212 LOWER AFT SKIN ONLY USING

THE SPLIT SLEEVE PROCESS PER FTI PROCESS SPECIFICATION 8101 OR ALTERNATIVELY PER A-

F302. STARTING HOLE DIAMETER SHALL BE .177 TO .180 INCHES. DO NOT COLD WORK THE

162D611514 COVER.

Critical Characteristic 2 (FAST-73) Torque indicated fastener(s) 2070 inch-pounds minimum to 2530 inch-pounds maximum. Apply torque to the fastener head. Fasteners to be torqued non-lubricated.

Critical Characteristic 3 (FAST-40) Torque indicated fastener(s) and/or fitting(s) 400 inch-pounds minimum to 450 inch-pounds maximum.

Part Number 162D611103-1001

Description UPPER SKIN INSTL

Part Number 162D611104-1001

Description PRECISION DRILLING ASSEMBLY

Critical Characteristic 1 (FAST-73) Torque indicated fastener(s) 1900 inch-pounds minimum to 2100

Critical Characteristic 2 (CW-01) Cold work indicated hole(s) using the split sleeve process per FTI Process Specification

8101 or alternatively A-F302. Starting hole diameter shall be .537 to .540 inches.

Part Number 162D611105-1001

Description LWR SKIN INSTL, STATION 1

Part Number 162D611106-1001

Description TORQUE BOX ASSEMBLY

Part Number 162D611201-2001

Description UPPER SKIN, FWD, CWP

Part Number 162D611201-2003

Description UPPER SKIN, FWD, CWP

Part Number 162D611201-5001

Description EXTRUSION, UPPER SKIN, FWD, CWP

Part Number 162D611202-2001

Description UPPER SKIN, AFT, CWP

Part Number 162D611208-2001

Description STIFFENER ANGLE, LOWER SKIN, AFT

Part Number 162D611208-2002

Part Number 162D611208-2003

Part Number 162D611208-2004

Part Number 162D611211-2001

Description LOWER SKIN, FWD, CWP

CW-05/01-Split Sleeve Cold Work-No Ream; Cold work indicated hole(s) using the split sleeve process per FTI Process Specification 8101 or alternatively A-F302. Starting hole diameter shall be [minimum diameter] to [maximum diameter] inches. Prior to cold working the hole, orient the gap of the sleeve as indicated, plus or minus 15 degrees. Hole diameter resulting from cold working acceptable (do not ream hole after cold working).

Part Number 162D611211-5001

Description EXTRUSION, LOWER SKIN, FWD, CWP

Part Number 162D611212-2001

Description CWP, SKIN, LOWER, AFT

CW-05;Cold work indicated hole(s) using the split sleeve process per FTI Process Specification 8101 or alternatively A-F302. Starting hole diameter shall be [minimum diameter] to [maximum diameter] inches. Prior to cold working the hole, orient the gap of the sleeve as indicated, plus or minus 15 degrees. Hole diameter resulting from cold working acceptable (do not ream hole after cold working).

Critical Characteristic 2 CW-06;All split sleeve cold working operations shall be performed after final machining and shot peening, but prior to conversion coat and fuel tank coating operations

Part Number 162D611212-2003

Description CWP, SKIN, LOWER, AFT

Critical Characteristic 2 CW-06;All split sleeve cold working operations shall be performed after final machining and shot peening, but prior to conversion coat and fuel tank coating operations

Part Number 162D611216-1001

Description FWD, UPR SKIN ASSEMBLY WS110

Part Number 162D611217-1001

Description AFT, UPR SKIN ASSEMBLY WS110

Part Number 162D611218-1001

Description SKIN ASSEMBLY, LOWER FORWARD

Part Number 162D611219-1001

Description SKIN ASSY - CWP, AFT, LWR

Part Number 162D611301-2001

Description DOOR - FRONT SPAR, WS110, LH

Part Number 162D611301-2007

Description DOOR - FRONT SPAR, WS110, RH

Part Number 162D611304-1001

Description ASSY, CWP LEADING EDGE - LWS 110 TO RWS 110

Part Number 162D611305-1001

Description CENTER SPAR INSTL

Part Number 162D611306-1001

Description REAR SPAR INSTL

Part Number 162D611310-2001

Description DOOR,CENTER SPAR

Part Number 162D611311-5001

Description EXTRUSION, FRONT SPAR, UPPER, CWP

Part Number 162D611312-5001

Description EXTRUSION, FRONT SPAR, LWR, CWP

Part Number 162D611314-5001

Description EXTRUSION- CTR SPAR, LWR, CWP

Part Number 162D611316-5001

Description EXTRUSION, AFT SPAR, LWR, CWP

Part Number 162D611317-5001

Description EXTRUSION, AUX SPAR, LWR, CWP

Part Number 162D611318-2001

Description SPAR CAP, FRONT, UPR, CWP

Part Number 162D611318-2003

Description SPAR CAP, FRONT, UPR, CWP

Part Number 162D611319-2001

Description SPAR CAP, FRONT, LWR, CWP

Part Number 162D611320-2001

Description SPAR CAP, CENTER, UPPER

Part Number 162D611321-2001

Description CENTER SPAR, LOWER, CWP be [minimum diameter] to [maximum diameter] inches. Prior to cold working the hole, orient the gap of the sleeve as indicated , plus or minus 15 degrees. Hole diameter resulting from cold working acceptable (do not ream hole after cold working).

Part Number 162D611322-2001

Description SPAR CAP, AFT, UPPER

Part Number 162D611323-2001

Description SPAR CAP, LOWER REAR, CWP

Part Number 162D611324-2001

Description AUX SPAR, LOWER REAR, CWP be [minimum diameter] to [maximum diameter] inches. Prior to cold working the hole, orient

Critical Characteristic 2

CW-06/01-Cold Work Process Sequence; All split sleeve cold working operations shall be performed after final machining and shot peening, but prior to [chemical and organic finishing] operations.

Part Number 162D611325-2001

Description CWP, FWD, SPAR, WEB

Part Number 162D611330-2007

Description CENTER SPAR WEB, LH, WS23 TO WS84, CWP

Part Number 162D611330-2009

Description CENTER SPAR WEB, RH, WS23 TO WS84, CWP

Part Number 162D611407-5001

Description FORGING, RIB - WING STA23

FORG-04/01-FA Tensile; 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.

FORG-09/01-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]%

Critical Characteristic 3

FORG-10/01-KIC Req'ts; Minimum acceptance criteria for KIC fracture toughness specimen [number 1] shall be: Specimen Orientation: [orientation 1] Fracture Toughness: [number 1] ksi-in0.5

Critical Characteristic 4

FORG-25/01-Prolongation; Forging prolongation cut line. After all processing is complete and it has been verified that suitable identification has been applied to the prolongation to be able to associate it back to the forging it was removed from, remove the prolongation from the forging.

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-46/01-Compression Stress Relief; Rib features shall be stress relieved by compressing to produce 1.75 to 4 percent permanent set. Web features shall not be compression stress relieved.

Critical Characteristic 7

FORG-07/02-Tensile; Recurring lot tensile property verification shall consist of testing specimen number [number1] and number [number 2] in accordance with ASTM E8. Sample orientation and location, within the forging prolongation, 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. Testing frequency shall be a minimum one set of specimens for every [number 3] forgings, or portion thereof, per forging lot.

Critical Characteristic 8

FORG-22/03-KIC; First article KIC fracture toughness verification shall consist of testing specimen numbers [number1] thru [number2] in accordance with ASTM E399/ASTM B645.

Sample orientation and location, within the forging, shall be as shown in the MDB dataset.

Specimen geometry shall be in accordance with ASTM E399 using a minimum B (thickness) dimension of [thickness1] inches.

Critical Characteristic 9

FORG-23/02-KIC; Recurring lot KIC fracture toughness verification shall consist of testing specimen number [number1] in accordance with ASTM E399/ASTM B645. Sample orientation and location, within the forging, shall be as shown in the MBD dataset. Specimen geometry shall be in accordance with ASTM E399 using a minimum B (thickness) dimension of [thickness1] inches. Testing frequency shall be a minimum one specimen for every [number 2] forgings, or portion thereof, per forging lot.

Part Number 162D611409-2001

Description Rib WS 23, Machine Detail

Part Number 162D611409-2003

Description RIB - WS 23.00, RH, CWP

Part Number 162D611410-2001

Description RIB, CENTER WING - WS90

Part Number 162D611410-2002

Description RIB, CWP, RH - WS90

Part Number 162D611557-1001

Description SPRT-FTG-ASSY

Part Number 162D611557-1002

Description SPRT FTG ASSY

Part Number 162D611557-2001

Description FITTING,UPR FWD INBD, WING CENTER PANEL

Part Number 162D611557-2002

Description FITTING,UPR FWD INBD, WING CENTER PANEL

Part Number 162D611559-1001

Description SUPPORT FITTING ASSY - CHAFF AND FLARE, UPR FWD OUTBD, CWP

Part Number 162D611559-1002

Description SUPPORT FITTING ASSY - CHAFF AND FLARE, UPR FWD OUTBD, WCP - RH

Part Number 162D611559-2001

Description SUPPORT FITTING - CHAFFF AND FLARE, UPR FWD OUTBD, WCP

Part Number 162D611559-2002

Description SUPPORT FITTING - CHAFF AND FLARE, UPR FWD OUTBD, WCP

Part Number 162D611561-1001

Description SUPPORT FITTING ASSY - CHAFF AND FLARE, LWR FWD INBD, CWP

Part Number 162D611561-2001

Description FITTING, CHAFF & FLARE SUPPORT, LWR FWD OUTBD, CWP

Part Number 162D611563-1001

Description FITTING ASSY, CHAFF/FLARE LWR FWD OUTBD, LH

Part Number 162D611563-1002

Description FITTING ASSY, CHAFF/FLARE LWR FWD OUTBD, RH

Part Number 162D611563-2001

Description SUPPORT FITTING, CHAFF/FLARE LWR FWD OUTBD, LH

Part Number 162D611563-2002

Description SUPPORT FITTING, CHAFF/FLARE LWR FWD OUTBD, RH

Part Number 162D611565-1001

Description FITTING ASSY - SUPPORT, CHAFF/FLARE, AFT, MLG FAIRING

Part Number 162D611565-1002

Description FITTING ASSY - SUPPORT, CHAFF/FLARE, AFT, MLG FAIRING, RHS

Part Number 162D611565-2001

Description FITTING, AFT FAIRING, LH MLG POD

Part Number 162D611565-2002

Description FITTING, AFT FAIRING, RH MLG POD

Part Number 162D611565-5001

Description FORGING - FITTING, SUPPORT, CHAFF/FLARE, AFT, MLG POD

FORG-26/01-Hand Forging Width; Material shall be forged to final thickness (ST orientation) and produced in multiples no more than [number] wide (LT orientation). Material may be forged to any suitable length (L orientation).

FORG-29/01-Hand Forging - Tensile; From each parent forging, one longitudinal (L) and one long transverse (LT) tensile specimen shall be tested. Tensile property acceptance criteria shall be in accordance with the material specification.

Part Number 162D611604-2001

Description FITTING-FORWARD, WING - FUSELAGE

24. (HT-02) Heat treat lot verification shall consist of testing a L (LONGITUDINAL) tensile specimen 1 from a 162D611604-5001 forging prolongation from the same forging lot (VAR material lot) as the parts it represents. The tensile specimen shall be heat treated along with the parts it represents. One tensile specimen shall be tested per heat treat/VAR material lot.

Testing shall be in accordance with ASTM A370 and shall meet the following minimum tensile requirements:

Part Number 162D611604-5001

Description FITTING, FWD, FORGING WING - FUSELAGE

Critical Characteristic 1 FORG-01/01-First Art; Forging first article approval and production control shall be in

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]%.

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.

FORG-48/01-KIC - First Art - Steel; First article KIC fracture toughness capability verification shall consist of testing specimen numbers [number1] thru [number2] in accordance with ASTM E399. Sample orientation and location, within the forging, shall be as shown in the MDB dataset. Specimen geometry shall be in accordance with ASTM E399 using a minimum B (thickness) dimension of [thickness1] inches. Heat treat test samples to [tensile range] ksi ultimate tensile strength per AMS 2759/2, except that partial decarburization shall not exceed

0.003 inches.

Critical Characteristic 5

FORG-50/01-Tensile - Lot Test - 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. Heat treat test samples to [tensile range] ksi ultimate tensile strength per AMS 2759/2, except that partial decarburization shall not exceed

0.003 inches. Testing frequency shall be a minimum one specimen for every [number 2]

FORG-49/01-KIC - Lot Test - Steel; Recurring lot KIC fracture toughness capability verification shall consist of testing specimen number [number1] in accordance with ASTM E399. Sample orientation and location, within the forging, shall be as shown in the MBD dataset. Specimen geometry shall be in accordance with ASTM E399 using a minimum B (thickness) dimension of [thickness1] inches. Heat treat test samples to [tensile range] ksi ultimate tensile strength per AMS 2759/2, except that partial decarburization shall not exceed 0.003 inches. Testing frequency shall be a minimum one specimen for every [number 2] forgings, or portion thereof, per forging lot.

FORG-53/01-KIC Req'ts; Minimum acceptance criteria for KIC fracture toughness specimen [forging specimen number] shall be: Specimen Orientation: [orientation] Fracture Toughness:

[minimum acceptable KIC value] ksi-in0.5 Material may be accepted when the measured KQ meets or exceeds [minimum acceptable KQ value] ksi-in0.5 and all ASTM E399 validity criteria are met except those related to specimen size (i.e., a, B>2.5(KQ/σys)2 and W-a > 2.5(KQ/σys)2)

Part Number 162D611605-2001

Description FITTING - AFT, WING - FUSELAGE

HT-02/01-HP9-4-30 Tensile; Heat treat lot verification shall consist of testing a [test specimen orientation] tensile specimen [specimen number] from a [forging part number] forging prolongation from the same forging lot (VAR material lot) as the parts it represents. The tensile specimen shall be heat treated along with the parts it represents. One tensile specimen shall be tested per heat treat/VAR material lot. Testing shall be in accordance with ASTM A370 and shall meet the following minimum tensile requirements: Ultimate Tensile Strength: 220 ksi Tensile Yield Strength: 190 ksi Elongation: 10% Reduction of Area: 40%

HT-15/01-HP9-4-30 - KIC - Heat Treat; Heat treat lot verification shall consist of testing a(n) [test specimen orientation] fracture toughness specimen number [specimen number] from a [forging part number] forging prolongation from the same forging lot (VAR material lot) as the parts it represents. The fracture toughness specimen shall be heat treated along with the parts it represents. Specimen geometry shall be in accordance with ASTM E399 using a minimum B (thickness) dimension of [specimen thickness] inches and the orientation and location as shown in the forging MBD dataset. One fracture toughness specimen shall be tested per heat treat/VAR material lot. Testing shall be in accordance with ASTM E399 and shall have a minimum KIC fracture toughness of 90 ksi-in0.5. Material may be accepted when the measured KQ meets or exceeds [minimum accetable KQ value] ksi-in0.5 and all ASTM E399 validity criteria are met except those related to specimen size (i.e., a, B > 2.5(KQ/σys)2 and W-a > 2.5(KQ/σys)2.

Part Number 162D611605-2003

Description FITTING - AFT, WING - FUSELAGE

Part Number 162D611605-5001

Description FITTING, AFT, FORGING, WING - FUSELAGE

Critical Characteristic 1 FORG-01/01-First Art; Forging first article approval and production control shall be in shall be: Specimen Orientation: [orientation 1]; Ultimate Tensile Strength: [number 2] ksi;

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.

0.003 inches.

0.003 inches. Testing frequency shall be a minimum one specimen for every [number 2]

FORG-53/01-KIC Req'ts; Minimum acceptance criteria for KIC fracture toughness specimen [forging specimen number] shall be: Specimen Orientation: [orientation] Fracture Toughness:

Part Number 162D611606-2001

Description WING SPLICE FITTING - UPPER INBD FWD, WS110.00

Part Number 162D611606-2002

Description WING SPLICE FITTING - UPPER INBD FWD, WS110.00

Part Number 162D611607-2001

Description WING SPLICE FITTING - UPPER INBD AFT, WS110.00

Part Number 162D611607-2002

Description WING SPLICE FITTING - UPPER INBD AFT, WS110.00

Part Number 162D611608-2001

Description WING SPLICE FITTING - LOWER INBD FWD, WS110.00, LH

Part Number 162D611608-2002

Description WING SPLICE FITTING - LOWER INBD FWD, WS110.00, RH

Part Number 162D611608-5001

Description FORGING, LWR-FWD WS110 FITTING

Critical Characteristic 1 FORG-01/01-First Art; Forging first article approval and production control shall be in specimen number [number1] and number [number 2] in accordance with ASTM E8. Sample orientation and location, within the forging prolongation, shall be as shown in the MBD dataset. Specimen geometry shall be in accordance with ASTM E8 using a minimum gage specimen numbers [number1] thru [number2] in accordance with ASTM E399/ASTM B645.

Sample orientation and location, within the forging, shall be as shown in the MDB dataset.

specimen number [number1] in accordance with ASTM E399/ASTM B645. Sample orientation and location, within the forging, shall be as shown in the MBD dataset. Specimen geometry shall be in accordance with ASTM E399 using a minimum B (thickness) dimension of

Part Number 162D611609-2001

Description WING SPLICE FITTING - LOWER INBD AFT, WS110.00

Part Number 162D611609-2002

Description WING SPLICE FITTING - LOWER INBD AFT, WS110.00

Part Number 162D611609-5001

Description FORGING, LWR-AFT WS110 FITTING

Sample orientation and location, within the forging, shall be as shown in the MDB dataset.

Part Number 162D611611-2001

Description FWD PYLON FITTING, CENTER SPAR - WS 0.00

Part Number 162D611611-2003

Description FWD PYLON FITTING, CENTER SPAR - WS 23.00

Part Number 162D611611-2005

Description FWD PYLON FITTING, CENTER SPAR - WS 66.00

Part Number 162D611611-2006

Description FITTING - PYLON, WS 66.00, CWP, RH

Part Number 162D611612-2001

Description FITTING, AFT - CENTER SPAR, WS 0.00

Part Number 162D611612-2003

Description FITTING, AFT - CENTER SPAR, WS 23.00

Part Number 162D611612-2005

Description FITTING, AFT - CENTER SPAR, WS 66.00

Part Number 162D611612-2006

Description FITTING, AFT - CENTER SPAR, WS 66.00

Part Number 162D611614-2001

Description PYLON FITTING, FRONT SPAR, WS 0.0

Part Number 162D611615-2001

Description PYLON FITTING FRONT SPAR WS66

Part Number 162D611615-2002

Description PYLON FITTING FRONT SPAR WS66

Part Number 162D611617-2001

Description ANGLE - SPLICE, LOWER, INBOARD, WS 110.000

Part Number 162D611617-2003

Description ANGLE - SPLICE, LOWER, INBOARD, WS 110.000

Part Number 162D611617-5001

Description WS110 LWR SPLICE ANGLES

Critical Characteristic 1 FORG-01/01-First Art; Forging first article approval and production control shall be in

Part Number 162D611618-2001

Description PIN TAPER- WING/FUS ATTACHMENT, FWD

FAST-10/01-AS 8879 Rolled Threads; Indicated [thread definition] threads shall be rolled after final heat treatment and in accordance with AS8879, except that maximum major thread diameter shall be a minimum of 0.001 inches less than actual shank diameter.

Critical Characteristic 2 FAST-47/01-UNJ Threads - Pre Heat Treat; Indicated [thread designation] threads in accordance with AS8879. Threads may be cut prior to final heat treat.

Part Number 162D611618-2003

Description PIN TAPER- WING/FUS ATTACHMENT, AFT

Critical Characteristic 2 FAST-47/01-UNJ Threads - Pre Heat Treat; Indicated [thread designation] threads in accordance with AS8879. Threads may be cut prior to final heat treat.

Part Number 162D611619-1001

Description BUSHING ASSEMBLY SPLIT TAPER

Part Number 162D611619-1003

Description BUSHING ASSEMBLY SPLIT TAPER

Part Number 162D611619-2001

Description BUSHING-WING/FUS ATTACHMENT SPLIT TAPER

Part Number 162D611619-2003

Part Number 162D611619-2005

Part Number 162D611619-2007

Part Number 162D611619-2009

Part Number 162D611619-2011

Part Number 162D611621-1001

Description ASSY - TRUNNION, MLG, CWP (CONFIGURATION ITEM)

Part Number 162D611621-1003

Description ASSY - TRUNNION, MLG, CWP (CONFIGURATION ITEM)

Part Number 162D611621-2001

Description FITTING - TRUNNION, LANDING GEAR

Part Number 162D611621-2003

Description FITTING - TRUNNION, LANDING GEAR

Part Number 162D611621-5001

Description FORGING -LANDING GEAR TRUNION FITTING

FORG-06/01-Tensile; Recurring lot tensile property verification shall consist of testing specimen number [number1] in accordance with ASTM E8. Sample orientation and location, within the forging prolongation, 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. Testing shall be: Specimen Orientation: [orientation 1] Ultimate Tensile Strength: [number 2] ksi Tensile Yield Strength: [number 3] ksi Elongation: [number 4]%

Critical Characteristic 4 FORG-01/01-First Art; Forging first article approval and production control shall be in

Part Number 162D611625-2001

Description FITTING, MLG BACKUP, FWD, WS110.00, LH

Part Number 162D611625-2002

Description FITTING, MLG BACKUP, FWD, WS110.00, RH

Part Number 162D611626-2001

Description FITTING, MLG BACKUP, AFT, WS110.00, LH

Part Number 162D611626-2002

Description FITTING, MLG BACKUP, AFT, WS110.00, RH

Part Number 162D611627-2001

Description FITTING - LANDING GEAR BACKUP, REAR SPAR

Part Number 162D611627-2002

Description FITTING - LANDING GEAR BACKUP, REAR SPAR

Part Number 162D611627-5001

Description FORGING - DIE, LANDING GEAR BACK - UP

FORG-40/01-Tensile - First Art - Subsize; First article tensile property verification shall consist of testing specimen numbers [number 1] thru [number 2] 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. Subsize specimens are allowed.

FORG-41/01-Tensile - Recurring - Subsize; Recurring lot tensile property verification shall consist of testing specimen numbers [number 1] and [number 2] 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. Subsize specimens are allowed. One forging per forging lot shall be cut up for tensile property verification.

Critical Characteristic 4 FORG-01/01-First Art; Forging first article approval and production control shall be in

Part Number 162D611628-2001

Description SPLICE ANGLE, LOWER REAR SPAR, WS 110, CWP

Part Number 162D611628-2002

Description SPLICE ANGLE, LOWER REAR SPAR, WS 110, CWP

Part Number 162D611631-1001

Description ASSY - FLAP TRACK, INBD, CWP, LH

Part Number 162D611631-1002

Description ASSY - FLAP TRACK RIB, INBD, CWP, RH

Part Number 162D611631-2001

Description RIB - FLAPTRACK, INBD, CWP, LH

Part Number 162D611631-2002

Description RIB - FLAPTRACK, INBD, CWP, RH

Part Number 162D611632-1001

Description FLAPTRACK, ASSY, CWP, OUTBD, LH

Part Number 162D611632-1002

Description FLAPTRACK, ASSY, OUTBD, CWP, RH

Part Number 162D611632-2001

Description RIB - FLAPTRACK, OUTBD, CWP, LH

Part Number 162D611632-2002

Description RIB - FLAPTRACK, OUTBD, CWP, RH

Part Number 162D611634-1001

Description ASSY, FITTING - FLAP ACTUATOR, WS95, CWP

Part Number 162D611634-1002

Description ASSY, FITTING - FLAP ACTUATOR, WS95, CWP

Part Number 162D611634-2001

Description FITTING - FLAP ACTUATOR, WS 95

Part Number 162D611634-2002

Description FITTING - FLAP ACTUATOR, WS95

Part Number 162D611634-5001

Description FITTING - FLAP ACTUATOR, WS95, FORGING

Critical Characteristic 1 FORG-01/01-First Art; Forging first article approval and production control shall be in

Sample orientation and location, within the forging, shall be as shown in the MBD dataset.

Specimen geometry shall be in accordance with ASTM E8. Subsize specimens are allowed. One forging per forging lot shall be cut up for tensile property verification.

Part Number 162D611634-5002

Description FITTING - FLAP ACTUATOR, WS95, FORGING

Critical Characteristic 1 FORG-01/01-First Art; Forging first article approval and production control shall be in

Sample orientation and location, within the forging, shall be as shown in the MBD dataset.

Specimen geometry shall be in accordance with ASTM E8. Subsize specimens are allowed. One forging per forging lot shall be cut up for tensile property verification.

Part Number 162D611635-2001

Description SPLICE FITTING-FUSELAGE LONGERON,WS23.00

Part Number 162D611635-2002

Description SPLICE FITTING-FUSELAGE LONGERON,WS23.00

Part Number 162D611645-2001

Description STUD-WS 0.00, 23.00, 63.00, PYLON ATTACHMENT

011592/01; THE FOLLOWING INSPECTION TESTS ARE REQUIRED FOR EACH LOT: A) EACH

STUD SHALL BE HARDNESS INSPECTED IAW MIL-STD-1312 TEST NO. 6. EACH STUD SHALL

HAVE A HARDNESS READING OF 409 HB (44 HRC) MINIMUM. B) FIVE STRESS DURABILITY

TESTS ARE REQUIRED IAW MIL-STD-1312 NO. 5. STRESS DURABILITY TORQUE REQUIREMENT:

1700 IN-LB. C) FIVE TENSILE STRENGTH TESTS ARE REQUIRED IAW MIL-STD-1312 NO. 8.

ULTIMATE TENSILE STRENGTH REQUIREMENT: 47,900 LB. D) ACCEPTABLE GRAIN FLOW IN

THE ROLLED THREADS SHALL BE VERIFIED ON ONE METALLOGRAPHIC SECTION PER LOT. THE

METALLOGRAPHIC SECTION SHALL BE CUT TO ALSO INCLUDE AT LEAST 0.5 INCH OF THE

ADJACENT MACHINED SHANK PORTION OF THE STUD. PROVIDE A 250X MAGNIFCATION

MICROGRAPH OF THE MACHINED SURFACE OF THE MACHINED SHANK PORTION OF THE STUD

FOR EACH GRAIN FLOW SECTION TAKEN E) VERIFICATION THAT THREADS ARE

MANUFACTURED IAW MIL-S-8879. THE NUMBER OF TESTS ARE TO BE DETERMINED IAW MIL-

STD-105 INSPECTION LEVEL II AQL 1.0. F) VERIFICATION THAT DIMENSIONS & SURFACE

ROUGHNESS ARE IAW DRAWING REQT. THE NUMBER OF TESTS ARE TO BE DETERMINED IAW

MIL-STD-105 INSPECTION LEVEL II AQL 1.0. (TEST B, C & D MAY BE CONDUCTED ON THE SAME

FIVE PIECES). G) SAMPLING REQT OF NASM8831 DO NOT APPLY.

Part Number 162D611645-2003

Description STUD-WS 0.00, 23.00, 66.00, PYLON ATTACHMENT

011593/01; THE FOLLOWING INSPECTION TESTS ARE REQUIRED FOR EACH LOT: A) EACH

HAVE A HARDNESS READING OF 409 HB (44 HRC) MINIMUM. B) FIVE STRESS DURABILITY

TESTS ARE REQUIRED IAW MIL-STD-1312 NO. 5. STRESS DURABILITY TORQUE REQUIREMENT:

1300 IN-LB. C) FIVE TENSILE STRENGTH TESTS ARE REQUIRED IAW MIL-STD-1312 NO. 8.

ULTIMATE TENSILE STRENGTH REQUIREMENT: 37,800 LB. D) ACCEPTABLE GRAIN FLOW IN

THE ROLLED THREADS SHALL BE VERIFIED ON ONE METALLOGRAPHIC SECTION PER LOT. THE

METALLOGRAPHIC SECTION SHALL BE CUT TO ALSO INCLUDE AT LEAST 0.5 INCH OF THE

ADJACENT MACHINED SHANK PORTION OF THE STUD. PROVIDE A 250X MAGNIFCATION

MICROGRAPH OF THE MACHINED SURFACE OF THE MACHINED SHANK PORTION OF THE STUD

FOR EACH GRAIN FLOW SECTION TAKEN. E) VERIFICATION THAT THREADS ARE

MANUFACTURED IAW MIL-S-8879. THE NUMBER OF TESTS ARE TO BE DETERMINED IAW MIL-

STD-105 INSPECTION LEVEL II AQL 1.0. F) VERIFICATION THAT DIMENSIONS & SURFACE

ROUGHNESS ARE IAW DRAWING REQT. THE NUMBER OF TESTS ARE TO BE DETERMINED IAW

Part Number 162D611645-2005