aa-10018

BHT 412EP INSTRUCTIONS for CONTINUED AIRWORTHINESS AA-10018 L/H AFT EQUIPMENT SHELF KIT No Revision

August 30, 2010 LAWSON AEROSPACE LLC of 30

RESTRICTED DISCLOSURE NOTICE

THE DRAWINGS, SPECIFICATIONS, DESCRIPTIONS, AND OTHER TECHNICAL DATA ATTACHED HERETO ARE PROPRIETARY AND CONFIDENTIAL TO LAWSON AEROSPACE LLC AND AERONAUTICAL ACCESSORIES, INC., AND CONSTITUTE TRADE SECRETS FOR PURPOSES OF THE TRADE SECRET AND FREEDOM OF INFORMATION ACTS. NO DISCLOSURE TO OTHERS, EITHER IN THE UNITED STATES OR ABROAD, OR REPRODUCTION OF ANY PART OF THE INFORMATION SUPPLIED IS TO BE MADE, AND NO MANUFACTURE, SALE OR USE OF ANY INVENTION OR DISCOVERY DISCLOSED HEREIN SHALL BE MADE, EXCEPT BY WRITTEN AUTHORIZATION OF LAWSON AEROSPACE LLC AND AERONAUTICAL ACCESSORIES, INC. THIS NOTICE WILL NOT OPERATE TO NULLIFY OR LIMIT RIGHTS GRANTED BY CONTRACT. THE DATA SUBJECT TO THIS RESTRICTION IS CONTAINED IN ALL SHEETS AND IS DISCLOSED TO PERSONNEL OF LAWSON AEROSPACE LLC AND AERONAUTICAL ACCESSORIES, INC., FOR THE PURPOSE(S) OF INTERNAL USE AND DISTRIBUTION ONLY.

© (2010) Lawson Aerospace LLC, Aeronautical Accessories, Inc. UNPUBLISHED - ALL RIGHTS RESERVED



LIST OF EFFECTIVE PAGES

All pages contained herein are at latest revision shown in Log of Revisions.

LIST OF EFFECTIVE PAGES 1 – 30



TABLE OF CONTENTS 1.0 INTRODUCTION ...................................................................................................................................... 7 1.1 DISTRIBUTION ......................................................................................................................................... 7 1.2 REVISION ................................................................................................................................................. 7 2.0 DESCRIPTION ......................................................................................................................................... 7 3.0 MAINTENANCE INSTRUCTIONS ............................................................................................................ 7 3.1 ANNUAL INSPECTION............................................................................................................................. 7 3.2 SPECIAL INSPECTION ............................................................................................................................ 8 3.3 REPAIR ................................................................................................................................................... 10 4.0 REMOVAL AND REPLACEMENT INFORMATION ................................................................................ 16 4.1 GENERAL INSTRUCTIONS ................................................................................................................... 16 4.2 REMOVAL 412-340-001 L/H AFT EQUIPMENT SHELF KIT ................................................................. 16 4.3 INSTALLATION 412-340-001 L/H AFT EQUIPMENT SHELF KIT ......................................................... 17 5.0 SPECIAL TOOLS NEEDED .................................................................................................................... 19 6.0 RECOMMENDED OVERHAUL PERIODS ............................................................................................. 19 7.0 AIRWORTHINESS LIMITATIONS .......................................................................................................... 19 8.0 WEIGHT AND BALANCE ....................................................................................................................... 19 9.0 PART BREAKDOWN .............................................................................................................................. 20 APPENDIX A ...................................................................................................................................................... 29

LIST OF TABLES

TABLE 1A DAMAGE AND REPAIR LIMITS FOR ALUMINUM AND STEEL COMPONENTS ............................ 8

TABLE 1B DAMAGE AND REPAIR LIMITS FOR PANEL ASSEMBLY .............................................................. 9

TABLE 2 TORQUE VALUES ............................................................................................................................. 16

TABLE 3 PART BREAKDOWN 412-340-001 L/H AFT EQUIPMENT SHELF KIT ........................................... 20

LIST OF FIGURES

FIGURE 1 SMOOTH DENTS (LESS THAN 10% OF PANEL THICKNESS).................................................. 11

FIGURE 2 SMOOTH DENTS (GREATER THAN 10% PANEL THICKNESS), SHARP DENTS, CREASES AND / OR SMALL PUNCTURES ................................................................................................... 12

FIGURE 3 HOLE THRU ONE OR BOTH SURFACES OF PANEL (LESS THAN 1 INCHIN DIAMETER AFTER CLEANUP) ........................................................................................................................ 14

FIGURE 4 DAMAGE GREATER THAN 1.0 INCH IN DIAMETER-METAL FACED PANEL ........................... 15

FIGURE 5 412-341-101 L/H AFT EQUIPMENT SHELF ASSEMBLY INSTALLATION REFERENCE (1 OF 2) ......................................................................................................................................... 22

FIGURE 5 412-341-101 L/H AFT EQUIPMENT SHELF ASSEMBLY INSTALLATION REFERENCE (2 OF 2) ......................................................................................................................................... 23

FIGURE 6 412-341-133 / -134 BRACE AND 412-341-135 / -136 RADIUS BLOCK INSTALLATION REFERENCE................................................................................................................................. 24

FIGURE 7 412-341-133 / -134 BRACE INSTALLATION REFERNCE ........................................................... 25

FIGURE 8 412-341-123 CONTOUR ANGLE INSTALLATION REFERENCE ................................................ 26

FIGURE 9 412-341-125 INBOARD ZEE ANGLE INSTALLATION REFERENCE .......................................... 26



LIST OF FIGURES (CONTINUED)

FIGURE 10 412-341-127 FWD ZEE ANGLE INSTALLATION REFERENCE ................................................ 27

FIGURE 11 412-341-129 AFT ZEE ANGLE INSTALLATION REFERENCE ................................................. 27

FIGURE 12 412-341-131 ANGLE INSTALLATION REFERENCE ................................................................. 28



1.0 INTRODUCTION These instructions contain the information necessary to inspect and maintain the LAWSON AEROSPACE LLC 412-340-001 L/H AFT EQUIPMENT SHELF KIT installed on Bell Helicopter Textron model 412EP helicopters in accordance with STC .

1.1 DISTRIBUTION These instructions are provided with each L/H Aft Equipment Shelf Kit. Any airworthiness or flight safety revisions will be immediately made available to all affected L/H Aft Equipment Shelf Kit owners. Instructions will be mailed and made available on the Lawson Aerospace LLC website: www.LawAero.com.

1.2 REVISION A Log of Revisions section is included in these instructions and will be utilized to document all changes. Change recommendations should be submitted to:

Lawson Aerospace LLC 350 W 50th St. TH1G New York, NY 10019 Email: DLawson @LawAero.com Website: www.LawAero.com

2.0 DESCRIPTION

The Lawson Aerospace LLC 412-340-001 L/H Aft Equipment Shelf Kit is for the Bell Helicopter Textron model 412EP helicopter. The L/H Aft Equipment Shelf provides a mounting surface for electrical and non-electrical components. The components can be mounted on top or from below the shelf. The shelf is located in the L/H avionics bay. The shelf is designed to carry a maximum weight of 100lbs (45.36kg).

3.0 MAINTENANCE INSTRUCTIONS

3.1 ANNUAL INSPECTION

Incorporate inspection of the 412-340-001 L/H Aft Equipment Shelf components into recommended annual inspection in accordance with BHT-412-MM. If any damage is noted during inspection, refer to Table 1 for damage and repair limits and to Section 3.3 for repair instructions. The 412-340-001 L/H Aft Equipment Shelf Annual Inspection shall consist of the following:

1. Inspect security of shelf and fasteners.

2. Inspect components for wear and / or damage.

3. Inspect components for nicks, scratches, dents, cracks, and corrosion.

4. Utilize the Inspection Record provided in Appendix A to document Inspection completion. Once Inspection is complete, include Inspection Record in permanent maintenance records.



NOTE The indications of corrosion are 1) corrosion deposits (a white or gray power on aluminum or rust colored deposits on steel), 2) pits in the aluminum or steel surface, 3) blisters, bulging or flaking of protective coatings.

3.2 SPECIAL INSPECTION In the event of a hard landing, rotor strike, or lightning strike perform the annual inspection prior to returning the aircraft to service.

TABLE 1A DAMAGE AND REPAIR LIMITS FOR ALUMINUM AND STEEL COMPONENTS

Maximum Allowable Damage And Repair Limits

Damage and corrosion may be repaired as noted in Section 3.3 Repair, if it does not exceed these limits. For damage exceeding these limits, replace components.

Scratches / Nicks Dents Cracks Corrosion

Not to exceed 10 percent of local part thickness in depth after cleanup or affect more than 20 percent of the surface area.

Not to exceed 10 percent of local part thickness in depth after cleanup or affect more than 20 percent of the surface area.

None

No corrosion allowed. Clean corrosion to a depth not to exceed 10 percent of local part thickness in depth.



TABLE 1B DAMAGE AND REPAIR LIMITS FOR PANEL ASSEMBLY

Maximum Allowable Damage And Repair Limits Damage and corrosion may be repaired as noted in Section 3.3 Repair, if it does not exceed these limits. For damage exceeding these

limits, replace components.

Voids May not exceed 0.25 square inch

No more than two skin voids allowed within a 4 inch diameter circle. Voids closer than 1.0 inch are to be considered one void.

The edge of any void must be at least 1.0 inch away from any attachment point, insert , or panel edge.

No edge separation (delamination) allowed.

Smooth dents less than 10% panel thickness in depth.

In one skin only, a maximum depth of 10% of panel thickness and a maximum of 4.0 inches in diameter.

Edge of dent at least 1 inch away from any attachment point, insert, or the panel edge.

No other damage within 4.0 inches of edge of dent.

No other damage permitted to dented portion of skin.

Smooth dents more than 10% panel thickness in depth affecting a single skin and core

Diameter of hole after cleanup does not exceed 0.50 inch diameter

No more than two damaged areas can be contained within a 4.0 inch diameter circle

Edge of the cleanup at least 3.0 inches from any attachment point, insert, or the panel edge.

Sharp dents, creases, and / or small punctures affecting a single skin and core

Diameter of hole after cleanup does not exceed 0.50 inch diameter.

No more than two damaged areas can be contained within a 4.0 inch diameter circle.

Edge of the cleanup at least 3.0 inches from any attachment point, insert, or the panel edge.

Hole thru one or both surfaces of panel less than 1.0 inch in diameter after cleanup

Maximum of two repairs per panel. The edges of each repair must be separated by a minimum of 5.0 inches.

Edge of cleanup a minimum of 3.0 inches away from any attachment point, insert, or the panel edge.

Skin repair cutout shall not exceed 1.0 inch diameter

Damage greater than 1.0 inch in diameter

Maximum length of cleanup of 5.0 inches in any direction.

Maximum of two repairs per panel which must be separated by a minimum of 5.0 inches between edges of cleanup.

Total damage a maximum of 12.0 square inches or 20% of total panel area, whichever is smaller, when only one skin and core is affected, and 10.0 square inches or 15% of total panel area, whichever is smaller, when both skins are affected.

Edge of cleanup must be a minimum of 3.0 inches from any attachment point, insert, or a panel edge.



3.3 REPAIR Replace malfunctioning components to ensure proper operation of the 412-340-001 L/H Aft Equipment Shelf Kit. Replacement components are available from Lawson Aerospace LLC. Perform all repairs per BHT-MED-SRM-1.

3.3.1 Aluminum and Steel Components

Repair scratches, nicks, and corrosion on aluminum and steel components as follows:

1. Lightly hand sand affected area using a Scotchbrite pad or abrasive paper 320 grit or finer, blending surface smooth. Ensure the limits presented in Table 1 are not exceeded. Take care to remove as little of the component protective coating as possible.

2. Remove sanding residue with solvent or detergent.

3. Apply chemical treatment to area as follows:

a. Mix a solution of 1 part Turco W.O. #1 (Alcoholic Phosphoric Acid) to 3 parts water by volume. Solution should be at the ambient temperature.

b. Using a Scotchbrite pad, apply acid solution to affected area. Treatment time is 5 to 30 minutes with periodic scrubbing.

4. Rinse surface with water within 30 minutes of acid solution application and dry using clean cloth, sponge, or blowing with 10 to 15 psi compressed air

5. Inspect depth of reworked surface to ensure that it does not exceed the restrictions presented in Table 1.

6. After repair is complete, clean repaired area with isopropyl alcohol. For aluminum parts ONLY, apply chemical film per MIL-DTL-81706.

3.3.2 Panel Assembly CAUTION

Chemical paint strippers are not to be used to remove paint finishes on bonded parts / panels. Chemical paint strippers may contribute to contamination of core, deteriorate adhesive bond line and edging. This may ultimately cause parts / panel to be rejected.

Trichloroethylene and vapor degreasers are not to be used to clean or strip surfaces adjacent to a damaged area for the same reasons.

Methyl-Ethyl-Ketone (MEK) and acetone are acceptable solvents for removal of paint from aluminum skins and panel edging. However, excessive application of MEK or acetone may affect adhesives used in a bond. It is preferable to wipe surface to be stripped using a moist rag rather than by soaking.



3.3.2.1 Voids:

1. Detect voids or bonding separations by tapping. A dead or flat sound will be produced if a void exists. Outline area with a grease pencil.

2. No repair is required.

3.3.2.2 Smooth Dents less than 10% panel thickness in depth (Refer to Figure 1):

1. Clean and remove finish from damaged area 1.75 inches beyond the edge of dent.

CAUTION Do not clean area from which finish was removed with solvent.

2. Fill dent above contour with filler adhesive and allow to cure.

3. Sand cured adhesive to contour and prepare area for bonding.

4. Prepare .025” thick 2024-T3 Aluminum doubler.

5. Bond doubler in position.

6. Prime repaired area.

7. Finish as required.

FIGURE 1 SMOOTH DENTS (LESS THAN 10% OF PANEL THICKNESS)



3.3.2.3 Smooth dents more than 10% panel thickness in depth affecting a single skin and core (Refer to Figure 2):

1. Cut 0.50 inch maximum diameter hole through skin (centered on damaged area), 50% of core thickness deep.

2. Undercut core from skin 0.25 inch.

3. Deburr hole, remove chips and loose material.

4. Fill hole above contour with adhesive and allow to cure.


5. Sand cured adhesive to contour.

6. Prime repair.


FIGURE 2 SMOOTH DENTS (GREATER THAN 10% PANEL THICKNESS), SHARP DENTS, CREASES AND / OR SMALL PUNCTURES



3.3.2.4 Sharp dents, creases, and / or small punctures affecting a single skin and core (Refer to Figure 2)

1. Cut 0.50 inch maximum diameter hole through skin (centered on damaged area), 50% of core thickness deep.

2. Undercut core from skin 0.25 inch.

3. Deburr hole. Remove chips and loose material.

4. Fill hole above contour with adhesive and allow to cure.


5. Sand cured adhesive to contour.

6. Prime repair.


3.3.2.5 Hole thru one or both surfaces of panel less than 1.0 inch in diameter after cleanup (Refer to Figure 3):

1. Cut out damaged area. When all cracks, tears and rough edges are removed, repair area must not exceed damage limits listed in Table 1B.

2. Undercut core approximately 0.25 inch.

3. Deburr skins. Remove chips and loose material.

4. Remove finish from damaged area and 1.5 inches beyond edge of cutout (using abrasive paper).

5. Fill prepared area with filler adhesive. Allow to cure. Sand smooth to contour.

6. Prepare .025” thick 2024-T3 Aluminum doubler and position on repair. Drill doubler and panel for eight equally spaced fasteners. Provide 0.38 minimum edge distance between fastener and edge of doubler or cutout. Remove doubler and deburr all holes. Prepare surfaces of doubler and panel for bonding. Bond and rivet doubler in position on panel. Wet install rivets.

7. Seal edges of repair.

8. Prime surface of repair. Allow to dry.




FIGURE 3 HOLE THRU ONE OR BOTH SURFACES OF PANEL (LESS THAN 1 INCHIN DIAMETER AFTER CLEANUP)

3.3.2.6 Damage greater than 1.0 inch in diameter (Refer to Figure 4):

1. Cut out skin(s) in damaged area allowing for a minimum of 0.25 inch undamaged core to protrude from skin cutout all around. Ensure core is not damaged while cutting out skin(s).

2. Cut out damaged core leaving a minimum of 0.25 inch of core protruding from the skin cutout all around.

3. Deburr skin(s). Remove loose material.

NOTE Core plug is required to be .500” thick x 1/8” cell x 3.1 density x .0007” thick 5052 Aluminum Honeycomb non-perforated per MIL-C-7438.

4. Prepare core plug. Align the plug ribbon direction with existing core in panel.



NOTE Doubler(s) required to be .025” thick 2024-T3 Aluminum. Doubler(s) to extend 1.5 inches minimum beyond repair cutout on all sides.

5. Position doubler(s) on repair location and drill holes for blind fasteners. Provide 0.38 inch edge distance minimum from edge of doubler and edge of repair cutout. Space holes equally at 0.90 to 1.30 inches, 1.12 inch desired.

6. Remove doublers. Deburr all parts. Remove chips and loose material.

CAUTION Do not allow any solvent to contaminate core portion or edge of honeycomb panel.

7. Remove paint and dirt from repair and clean in preparation for bonding.

8. Bond core plug in position. Ensure core ribbon direction matches existing core.

NOTE Filler(s) required to be.020” thick 2024-T3 Aluminum. Dimensions to fit in skin cutout(s).

9. Bond filler(s) in position.

10. Bond and rivet doubler(s) in position. Wet install rivets.

11. Apply primer to bare metal surfaces. Allow to dry.

12. Seal edges of repair.


FIGURE 4 DAMAGE GREATER THAN 1.0 INCH IN DIAMETER-METAL FACED PANEL



4.0 REMOVAL AND REPLACEMENT INFORMATION (Refer to Figures 5 thru 12)

4.1 GENERAL INSTRUCTIONS

1. Tag all parts, including attaching hardware, removed to gain access to work areas. Protect parts from damage until re-installed.

2. Temporarily relocate wire bundles as required to allow clear access to kit components.

3. When installing ground wires or components requiring electrical bonding, clean surface to provide proper electrical contact.

4. When installing components where dissimilar materials are in contact, apply AMS-S-8802 Sealant between faying surfaces.

5. Torque fasteners per Table 2 unless otherwise noted. Due to variations in aircraft installation, fastener length only can be adjusted to one grip length longer or shorter than specified.

TABLE 2 TORQUE VALUES

Fastener Size Torque (in-lbs) 8-32 12-15

10-32 20-25

4.2 REMOVAL 412-340-001 L/H AFT EQUIPMENT SHELF KIT (Refer to Figures 5 thru 12)

1. Locate 412-341-101 L/H Aft Equipment Shelf Assembly.

2. Remove and retain four (4) MS27039-1-07 Screws and NAS1149D0332J Washers securing 412-341-134 Brace R/H and 412-341-136 Radius Block R/H.

3. Remove and retain 412-341-134 Brace R/H and 412-341-136 Radius Block R/H.

4. Remove and retain four (4) MS27039-1-07 Screws and NAS1149D0332J Washers securing 412-341-133 Brace L/H and 412-341-135 Radius Block L/H.

5. Remove and retain 412-341-133 Brace L/H and 412-341-135 Radius Block L/H.

6. Remove and retain fifteen (15) AN3-10A Bolts and NAS1149D0332J Washers securing 412-341-101 L/H Aft Equipment Shelf Assembly.

7. Remove and retain 412-341-101 L/H Aft Equipment Shelf Assembly.

8. Remove and retain seven (7) MS27039-0808 Screws, twenty-eight (28) NAS1149DN832J Washers and seven (7) MS21042L08 Nuts securing 412-341-125 Inboard Zee Angle to 212-030-163-XXX Support Angle.

9. Remove and retain 412-341-125 Inboard Zee Angle.

10. Remove and retain three (3) MS27039-0808 Screws, twelve (12)



NAS1149DN832J Washers, and three (3) MS21042L08 Nuts securing 412-341-129 Aft Zee Angle to 205-030-405-XXX Support L/H.

11. Remove and retain 412-341-129 Aft Zee Angle.

12. Remove and retain ten (10) MS27039-0808 Screws, forty (40) NAS1149DN832J Washers, and ten (10) MS21042L08 Nuts securing 412-341-127 Forward Zee Angle to 205-030-711-XXX Support L/H.

13. Remove and retain 412-341-127 Forward Zee Angle.

14. Remove and retain five (5) MS27039-1-07 Screws and NAS1149D0332J Washers securing 412-341-131 Angle to bulkhead.

15. Remove and retain 412-341-131 Angle.

16. Drill out thirty (30) MS20426AD4-6 Rivets securing 412-341-123 Contour Angle.

17. Remove and retain 412-341-123 Contour Angle.

18. Removal complete.

4.3 INSTALLATION 412-340-001 L/H AFT EQUIPMENT SHELF KIT (Refer to Figures 5 thru 12)

NOTE If replacing any 412-340-001 L/H Aft Equipment Shelf Kit component, match drill hole pattern from removed part to replacement part.

NOTE If replacing 412-341-101 L/H Aft Equipment Shelf Assembly, install fifteen (15) 80-011-P10D1-0 Thru-Bolt Plugs, 80-011-S10D08-0 Thru-Bolt Sleeves, and four (4) 80-005-2-8 Inserts per AAI report AA-10003.

1. Locate installation location of 412-340-001 L/H Aft Equipment Shelf Kit.

2. Align holes of 412-341-123 Contour Angle to those in L/H door track.

3. Install 412-341-123 Contour Angle using thirty (30) MS20426AD4-6 Rivets wet with 099-050-222 Sealant.

4. Attach 412-341-131 Angle to bulkhead using retained five (5) MS27039-1-07 Screws and NAS1149D0332J Washers.

NOTE Prior to installing Zee Angles, maintain electrical boding of local grounds.

5. Attach 412-341-127 Forward Zee Angle to 412-341-131 Angle and 205-030-711-XXX Support L/H using retained ten (10) MS27039-0808 Screws, forty (40) NAS1149DN832J Washers, and ten (10) MS2102L08 Nuts.

6. Attach 412-341-129 Aft Zee Angle to 205-030-405-XXX Support L/H using retained three (3) MS27039-0808 Screws, twelve (12) NAS1149DN832J Washers, and



three (3) MS21042L08 Nuts.

7. Attach 412-341-125 Inboard Zee Angle to 212-030-163-XXX Support Angle using retained seven (7) MS27039-0808 Screws, twenty-eight (28) NAS1149DN832J Washers, and seven (7) MS21042L08 Nuts.

8. Position 412-341-101 L/H Aft Equipment Shelf Assembly and secure using retained fifteen (15) AN3-10A Bolts and NAS1149D0332J Washers.

9. Attach 412-341-134 Brace R/H and 412-341-136 Radius Block R/H using retained four (4) MS27039-1-07 Screws and NAS1149D0332J Washers.

10. Attach 412-341-133 Brace L/H and 412-341-135 Radius Block L/H using retained four (4) MS27039-1-07 Screws and NAS1149D0332J Washers.

11. If installing replacement 412-341-101 L/H Aft Equipment Shelf Assembly, attach 412-341-137 Decal in required position.

12. Installation complete.



5.0 SPECIAL TOOLS NEEDED

No special tools needed for this type design change.

6.0 RECOMMENDED OVERHAUL PERIODS

No component overhaul required for this type design change.

7.0 AIRWORTHINESS LIMITATIONS

No airworthiness limitations associated with this type design change.

The Airworthiness Limitations section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403, unless an alternative program has been FAA approved.

8.0 WEIGHT AND BALANCE

Kit Weight Station Lateral Arm 412-340-001 L/H Aft Equipment Shelf Kit 6 lbs 193.0 in -25.65 in (2.72 kg) (4902.2 mm) (-651.51 mm)

WARNING WEIGHT IN SECTION 8.0 REFLECTS WEIGHT OF THE L/H AFT EQUIPMENT SHELF KIT ONLY; IT DOES NOT INCLUDE THE WEIGHT(S) OF ANY EQUIPMENT THAT MIGHT BE INSTALLED.

NOTE After installation is complete, the aircraft should be weighed in accordance with the applicable Maintenance Manual instructions and ballast adjusted as necessary to return the helicopter empty weight Center of Gravity to within allowable limits.



9.0 PART BREAKDOWN

Table 3 contains Part Breakdown data for the 412-340-001 L/H Aft Equipment Shelf Kit. The column Availability Code (AV Code) specifies the procurement status for each part. The codes to identify if a part is procurable, procedure details to get an assembly or local manufacture code are as follows:

AV Code

Details

0 Nonprocurable part 1 Procurable part 2 Procure as detail parts only 3 Procurable as Next Higher Assembly 4 Local manufacture. Contact Lawson Aerospace LLC 5 Part replacement requires a fixture or special equipment. Contact Lawson Aerospace

LLC 6 Non-stock procurable part

TABLE 3 PART BREAKDOWN 412-340-001 L/H AFT EQUIPMENT SHELF KIT

Qty Part Number Description AV Code

2 099-050-121 Adhesive, Magnobond 6398 A & B 1 1 099-050-222 Sealant, CS3204B2 1 1 412-341-101 L/H Aft Equipment Shelf Assembly 1 1 412-341-123 Contour Angle 1 1 412-341-125 Inboard Zee Angle 1 1 412-341-127 Forward Zee Angle 1 1 412-341-129 Aft Zee Angle 1 1 412-341-131 Angle 1 1 412-341-133 Brace L/H 1 1 412-341-134 Brace R/H 1 1 412-341-135 Radius Block L/H 1 1 412-341-136 Radius Block R/H 1 1 412-341-137 Decal 1

13 80-005-2-8 Insert 1 15 80-011-P10D1-0 Thru-Bolt Plug 1 15 80-011-S10D08-0 Thru-Bolt Sleeve 1 15 AN3-10A Bolt 1 30 MS20426AD3-4 Rivet 1 30 MS20426AD4-6 Rivet 1 20 MS21042L08 Nut 1 15 MS21059L3 Nut Plate 1 20 MS27039-0808 Screw 1 13 MS27039-1-07 Screw 1 28 NAS1149D0332J Washer 1 80 NAS1149DN832J Washer 1



REFERENCE INSTALLATION FIGURES

Figures 5 thru 12, ARE NOT TO SCALE and are provided as reference parts installation location and identification information for the 412-340-001 L/H Aft Equipment Shelf Kit.

Contact: Lawson Aerospace LLC 350 W 50th St. TH1G New York, NY 10019 Email: DLawson @LawAero.com for applicable engineering drawing information



FIGURE 5 412-341-101 L/H AFT EQUIPMENT SHELF ASSEMBLY INSTALLATION REFERENCE (1 OF 2)



FIGURE 5 412-341-101 L/H AFT EQUIPMENT SHELF ASSEMBLY INSTALLATION REFERENCE (2 OF 2)



FIGURE 6 412-341-133 / -134 BRACE AND 412-341-135 / -136 RADIUS BLOCK INSTALLATION REFERENCE



FIGURE 7 412-341-133 / -134 BRACE INSTALLATION REFERNCE



FIGURE 8 412-341-123 CONTOUR ANGLE INSTALLATION REFERENCE

FIGURE 9 412-341-125 INBOARD ZEE ANGLE INSTALLATION REFERENCE



FIGURE 10 412-341-127 FWD ZEE ANGLE INSTALLATION REFERENCE

FIGURE 11 412-341-129 AFT ZEE ANGLE INSTALLATION REFERENCE



FIGURE 12 412-341-131 ANGLE INSTALLATION REFERENCE



APPENDIX A



Inspection Record

Work Order Number: ______________________

Registration Number: ______________________

Serial Number: ______________________

Total Time: ______________________

Date: ______________________

Inspect in accordance with Section 3.0, Maintenance Instructions.

1. Inspect security of shelf and fasteners.

2. Inspect components for wear and / or damage.

3. Inspect components for nicks, scratches, dents, cracks, and corrosion.

NOTE The indications of corrosion are 1) corrosion deposits (a white or gray power on aluminum or rust colored deposits on steel), 2) pits in the aluminum or steel surface, 3) blisters, bulging or flaking of protective coatings.

Signature ________________________ A & P No. _________________________

Signature _________________________ Inspector _________________________

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