Attachment 0006 - MO Critical Safety Items.pdf

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Apache AH-64 Composite Main Rotor Blade
Solicitation number
W58RGZ-25-R-0071
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Written by GovTribe AI ·

These documents are M&O (Maintenance and Overhaul) Critical Safety Items (CSI) sheets for various Boeing rotary wing blade assemblies and components, primarily for military aircraft. The documents detail multiple part numbers for blade, sub-assembly, fitting, and composite assemblies, all marked as critical safety items with specific manufacturing, inspection, and repair requirements. Each document includes critical characteristics such as mandrel tool diameter conformance, repairs according to Boeing Standard 16-004, specific inspection protocols, and repair guidelines for various blade sections including weight and retention bushings, root inspections, metallic leading edges, and composite regions.

The sheets consistently show these are Boeing Company parts (CAGE code 8V613), with critical safety designations, serial number requirements, and engineering test specifications. The parts have various NSN (National Stock Numbers) and are dated between 2011 and 2023, with CSI (Critical Safety Item) dates ranging from January 2014 to January 2021. Repair instructions are extensive and reference specific Boeing standards and sections, emphasizing precise manufacturing tolerances, inspection requirements, and repair limitations to ensure safety and structural integrity of rotary wing blade assemblies.

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09/27/2022

7-5R0430100-113 1615 01 690 - 5019

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly contains CSIs.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. CC is not complete

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Blade, Rotary WingNoun YCritical Safety

YSerial Number Req'd YEngineering Test Req'd YFatigue NEndurance NInterchange

Approved M&O Sources

01/19/2021CSI Date

Approved Date

M&O CRITICAL SAFETY ITEMS

7-5R1430150-105 -

Y

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Assembly Contains CSI?s.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

Surface preparation of composite to composite, using water break testing per EPB, 18-120, paragraph 3.11.2.3.

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

SUB-ASSEMBLY M/R BLADENoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R1430200-103 -

Y

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Assembly Contains CSI?s.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

Surface preparation of composite to composite, using water break testing per EPB, 18-120, paragraph 3.11.2.3.

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

BONDED ASSY, MR BLADENoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430130-103 -

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSI?s.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. CC is not Complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. CC is not complete epairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight CC is not complete

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

ROOT FITTING ASSEMBLY, UPPERNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430131-003 -

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. CC is not complete

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

ROOT FITTING, UPPERNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

7-5R2430140-103 -

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSI?s.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. CC is not complete

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

ROOT FITTING ASSEMBLY, LOWERNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430141-003 -

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing. CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. CC is not complete Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. CC is not complete

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

ROOT FITTING, LOWERNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

7-5R2430300-101 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5

Correct Ply orientation

Correct number of Plys and sequence

Cure cycles per EPB18-120

Ensure shelf life of materials complies with HP10-7

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

ASSY, LEADING EDGENoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2011CSI Date

7-5R2430300-103 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

ASSY, LEADING EDGENoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/10/2017CSI Date

7-5R2430400-103 -

Y NN Assembly Contains CSI?s.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

SPAR ASSEMBLYNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430401-103 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

LAMINATE, SPAR, LOWERNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430402-103 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

LAMINATE, SPAR, UPPERNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430404-001 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

ASSY, LEADING EDGENoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/10/2017CSI Date

08/23/2022

7-5R0430100-107 1615 01 690 - 2799

Y NN Assembly Contains: 7-5R1430150-105.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Blade, Rotary WingNoun YCritical Safety

YSerial Number Req'd YEngineering Test Req'd YFatigue NEndurance NInterchange

Approved M&O Sources

01/05/2020CSI Date

7-5R1430150-105 -

Y

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Assembly Contains CSIs.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

Surface preparation of composite to composite, using water break testing per EPB, 18-120, paragraph 3.11.2.3.

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Sub-Assembly M/R BladeNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R1430200-103 -

Y

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Assembly Contains CSI's

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

Surface preparation of composite to composite, using water break testing per EPB, 18-120, paragraph 3.11.2.3.

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Bonded Assy, MR BladeNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSI's.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting Assembly, UpperNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting, UpperNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSIa??s.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting Assembly, LowerNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting, LowerNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

7-5R2430300-103 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Assy, Leading EdgeNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/10/2017CSI Date

7-5R2430400-103 -

Y NN Assembly Contains CSIa??s.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Spar AssemblyNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430401-103 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Laminate, Spar, LowerNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430402-103 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed, in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Laminate, Spar, UpperNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

7-5R2430404-001 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5.

Correct number of plys and sequence.

Correct ply orientation.

Cure cycles per EPB18-120.

Ensure shelf life of materials complies with HP10-7.

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Assy, Leading EdgeNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/10/2017CSI Date

7-5R0430100-109 1615 01 690 - 4995

Y

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly contains CSIs.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Section 27: Pai Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Removal. Sect Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and gouges Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Section 18:

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Composite MR Blade AssyNoun YCritical Safety

YSerial Number Req'd YEngineering Test Req'd YFatigue NEndurance NInterchange

Approved M&O Sources

01/15/2021CSI Date

7-5R1430150-101 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5

Cure cycles per EPB18-120

Ensure shelf life of materials complies with HP10-7

Surface preparation of composite to composite, using water break testing per EPB 18-120, paragraph 3.11.2.3

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Sub- Assembly M/R BladeNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/07/2011CSI Date

7-5R1430200-101 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5

Cure cycles per EPB18-120

Ensure shelf life of materials complies with HP10-7

Surface preparation of composite to composite using water break testing per EPB 18-120, paragraph 3.11.2.3

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Sub-Assembly M/R BladeNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/07/2011CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSI's.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting Assembly, UpperNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting, UpperNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSIa??s.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting Assembly, LowerNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting, LowerNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

7-5R0430100-111 1615 01 690 - 5029

Y

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly contains CSIs.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Section 27: Pai Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Removal. Sect Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and gouges Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Section 18:

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Blade, Rotary WingNoun YCritical Safety

YSerial Number Req'd YEngineering Test Req'd YFatigue NEndurance NInterchange

Approved M&O Sources

01/19/2021CSI Date

7-5R1430150-101 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5

Cure cycles per EPB18-120

Ensure shelf life of materials complies with HP10-7

Surface preparation of composite to composite, using water break testing per EPB 18-120, paragraph 3.11.2.3

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Sub- Assembly M/R BladeNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/07/2011CSI Date

7-5R1430200-101 -

Y

Y

Y

Y

Y

N

N

N

N

N

N

N

N

N

N

Absence of voids and porosity as verified through non-destructive inspections listed in EPB 18-120, Table 5

Cure cycles per EPB18-120

Ensure shelf life of materials complies with HP10-7

Surface preparation of composite to composite using water break testing per EPB 18-120, paragraph 3.11.2.3

Surface preparation of metal to Composite, using F Sol Gel per HP 4-136

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Sub-Assembly M/R BladeNoun YCritical Safety

NSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/07/2011CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSIa??s.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting Assembly, UpperNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting, UpperNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Assembly Contains CSIa??s.

Mandrel Tool Diameter conforms to the requirements of HP15-102. 100%, Inspection required prior to each use.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting Assembly, LowerNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/06/2017CSI Date

Y

Y

N

N

N

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Force Mate Bushing per HS 6088.

Lug hole diameter 1.3755 +/- .0010.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Root Fitting, LowerNoun YCritical Safety

YSerial Number Req'd NEngineering Test Req'd NFatigue NEndurance NInterchange

Approved Replacement (Spares) Sources

01/30/2014CSI Date

01/20/2023

7-5R0430100-103P 1615 01 690 - 3385

Y

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Y

Assembly contains CSIs

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical CharacteristicsM ID

Part No NSN

Composite MR Blade AssyNoun YCritical Safety

YSerial Number Req'd YEngineering Test Req'd YFatigue NEndurance NInterchange

Approved M&O Sources

01/14/2020CSI Date

01/22/2023

7-5R0430100-105P 1615 01 690 - 3394

Y

N

N

N

N

N

N

N

N

N

Y

Y

Y

Y

Y

Assembly Contains: 7-5R1430150-105.

Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 20: Aft Weight and Retention Bushing.

Section 21: Blade Root Inspection (Note that AWR 2014E-A48 takes precedence). Section 22: Station 268.375 Inspection (Note that AWR 2014E-A48 takes Precedence). Section 23: Aft Tip Repair. Section 24: Trailing Edge Composite Repair. Section 25: Fill and Fair. Section 26: Repair of Scratches, Nicks, and Gouges for Metallic Surfaces. Sectio Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 29: Resin Wash. Section 30: Sealant Repair. Section 31: Conductivity Check. Section 32: Aft Body Plug Repair a?? if for Zone A damage there is no spar damage present. Section 33: Aft Body Skin Patch Repair a?? if for Zone A damage there is no spar damage present. Section 34: Fill and Fair Locations. Section 35: Blade Balancing. Section 36: Resin Mixing. Section 37:

Paint Remo Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 3: Metallic Leading Edge except for the metallic erosion limits in Zone C. Section 4: Metallic Swept Tip Leading Edge except for the metallic erosion limits in Zone F. Section 5: Closeouts. Section 6: Metallic Root Fittings. Section 7: Composite Aft Body Region - All zones are repairable (Zone A No damage to spar allowed). Section 8: Composite Spar Region (scratches, nicks, and Repairs shall be IAW with Boeing, STN 16-004, Dated Dec 17. Section 9: Root Metallic Doublers and Fiberglass Overply. Section 10: Jumper Cables. Section 11: Root Weight Retention Studs. Section 12: Ground Conductor Strap. Section 13: Backup Bolts, Nuts, and Washers: only repair of the sealant is allowed at this time. All other damage must be evaluated by SRD. Section 16: Forward Weight Pocket Cover. Section 17: Forward Weight Pocket Studs. Sec

8V613 The Boeing Company

CAGE

Critical…

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