for CONTINUED AIRWORTHINESS CROSSTUBES

RESTRICTED DISCLOSURE NOTICE ON PAGE 2

P.O. BOX 3689 BRISTOL, TENNESSEE 37625-3689 USA TELEPHONE: 423-538-5151 TOLL FREE: 800-251-7094

TELEFAX: 423-538-8469 E-MAIL: [email protected] [email protected]

INSTRUCTIONS for

CONTINUED AIRWORTHINESS for

CROSSTUBES STC: SR00646AT (LOW SKID GEAR)

P/N 212-320-103 / 212-320-104 P/N 412-320-104 / 412-320-154

STC: SR01052AT (HIGH SKID GEAR) P/N 212-321-103 (S/N 1250 and Sub)

P/N 412-321-104 / 412-321-304 (S/N 1274 and Sub) FOR

BELL HELICOPTER TEXTRON MODEL 205A, 205A-1, 205B, 212, 412, 412EP, 412CF HELICOPTERS

AGUSTA S.P.A. MODEL AB412, AB412EP HELICOPTERS

STC: SR01924AT (LOW OR HIGH SKID GEAR) P/N 212-321-103 (S/N 1250 and Sub) / 212-321-104

FOR RESTRICTED CATEGORY UH-1B, UH-1H, SW204, SW205

GARLICK HELICOPTERS, US HELICOPTERS, INC., WESTERN INTERNATIONAL AVIATION, INC., SOUTHWEST FLORIDA

AVIATION HELICOPTERS

Report Number AA-01136 Revision K

February 15, 2012

mailto:[email protected]


BHT 205A, 205A-1, 205B INSTRUCTIONS for CONTINUED AIRWORTHINESS AA-01136

212, 412, 412EP, 412CF, CROSSTUBES Revision K AGUSTA AB412, AB412EP, UH-1B, UH-1H, SW204, SW205

AERONAUTICAL ACCESSORIES February 15, 2012 Page 2 of 78

RESTRICTED DISCLOSURE NOTICE THE DRAWINGS, SPECIFICATIONS, DESCRIPTIONS, AND OTHER TECHNICAL DATA ATTACHED HERETO ARE PROPRIETARY AND CONFIDENTIAL TO BELL HELICOPTER TEXTRON, INC (BHTI) 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 BHTI. THIS NOTICE WILL NOT OPERATE TO NULLIFY OR LIMIT RIGHTS GRANTED BY CONTRACT. THE DATA SUBJECT TO THIS RESTRICTION JS CONTAINED IN ALL SHEETS AND IS DISCLOSED TO PERSONNEL OF BHTI, FOR THE PURPOSE(S) OF INTERNAL USE AND DISTRIBUTION ONLY.

© (2012) BHTI UNPUBLISHED – ALL RIGHTS RESERVED




LOG OF REVISIONS

Date Revision Description Pages

09/04/01 NR Original Release All

02/21/02 A Deleted 3.1, 3.2, 3.3 5 – 7

Added 3.1, 3.1.1, 3.1.2, 3.2, 3.2.1, 3.2.2 6 – 9

Revised Crosstube weights in Table 6 19

04/22/02 B Deleted Figures 3 and 4 16

Added 412CF Model Effectivity, 205B & 412CF to report header, crosstube damage NOTE to 3.0, torque value to Table 2, 5.7 and 5.8, Figures 4 and 5

All, All, 6,10,14,19,

20

Revised 3.1.2 (#2, a) and 3.2.2 (#2, a), Table 1, Section 3.4 Repair, Figure 2 and Table 5, 212-320-104 weight in Table 6, 412 Low & 412 High Skid Crosstube Parts Lists in 12.0, Appendix A

7,8,9,10, 16,17,23,24

,25,28

Changed Figure 5 to Figure 3 and added “205/212 ONLY” effectivity to Aft Crosstube Assembly, changed washer quantity in 212-320-203 Hardware Kit, changed part reference on Hardware Kit Table for 412-320-230 & 412-321-200

18, 25, 26

07/30/02 C Revised 3.1.2 (2, b), 3.2.2 (2, b), Table 2, 5.3 (3, Note), 5.4, 5.8 (Note), Figure 3, 12.0 Parts List, Appendix A

7,8,10,12 13,14,19, 25–27,31

Changed MIL Spec reference from MIL-C-5541 to MIL-DTL-81706, and MIL-S-8802 to AMS-S-8802

10, 12, 13, 14

08/29/06 D Reformatted, reorganized document All

Added UH-1H, SW205 model effectivity All

Revised Section 1.0, Introduction 7

Revised Section 2.0, Description 7

Revised Table 1, Damage and Repair Limits: added metric equivalents

11

Revised Table 2, Torque Values: added metric equivalents 12

Added Section 5.9, Removal – Plate Assembly 17

Added Section 5.10, Installation – Plate Assembly 17

Deleted Section 8.0, Recommended Overhaul Periods; renumbered subsequent sections

-

Section 8.0, Airworthiness Limitations: Incorporated information from (deleted) Recommended Overhaul Periods section

18

Revised Section 9.0, Weight and Balance: added metric equivalents 19

Revised Section 11.0, Parts Breakdown: reformatted, revised Tables 4 thru 11

20 – 25

Reorganized Figures 1 thru 7 36 – 32

06/24/09 E Reformatted, reorganized document. Incorporated engineering updates. Complete revision

All




LIST OF EFFECTIVE PAGES

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

LIST OF EFFECTIVE PAGES 1 – 78



TABLE OF CONTENTS

Identification Title Page


1.0 INTRODUCTION ................................................................................................ 11

1.1 DISTRIBUTION .................................................................................................. 11 1.2 REVISION .......................................................................................................... 11

2.0 DESCRIPTION ................................................................................................... 11 3.0 MAINTENANCE INSTRUCTIONS ...................................................................... 12 3.1 CROSSTUBE INSPECTION – ALL .................................................................... 13

3.1.1 DAILY INSPECTION (SERIES 1 INSPECTION) // 25 HOUR / 30 DAY INSPECTION (SERIES 2 INSPECTION) ................................................. 14

3.1.2 100 HOUR / 12 CALENDAR MONTH INSPECTION (SERIES 1 INSPECTION) // 300 HOUR INSPECTION (SERIES 2 INSPECTION) ... 14

3.2 CROSSTUBE INSPECTION, 212-321-103 HIGH FORWARD CROSSTUBE ONLY ................................................................................................................. 15

3.2.1 AT 7500 TAKEOFF/LANDINGS AND FOLLOWING EVERY SUBSEQUENT 200 TAKEOFF/LANDINGS THEREAFTER VISUAL INSPECTION ........................................................................................... 15

3.2.2 AT 10,000 TAKEOFF/LANDINGS AND FOLLOWING EVERY SUBSEQUENT 12 MONTHS OR 2500 TAKEOFF/LANDINGS, WHICHEVER COMES FIRST, THEREAFTER DIMENSIONAL INSPECTION ........................................................................................... 16

3.2.3 AT 12,500 TAKEOFF/LANDINGS AND EVERY SUBSEQUENT 5000 TAKEOFF/LANDINGS THEREAFTER INSPECTION AND OVERHAUL 17

3.3 CROSSTUBE INSPECTION, 412-321-104 AND 412-321-304 HIGH AFT CROSSTUBES ONLY ....................................................................................... 20

3.3.1 AT 2500 TAKEOFF/LANDINGS AND FOLLOWING EVERY SUBSEQUENT 450 TAKEOFF/LANDINGS THEREAFTER VISUAL INSPECTION ........................................................................................... 20

3.3.2 AT 2500 TAKEOFF/LANDINGS AND EVERY 12 MONTHS / 2500 TAKEOFF/LANDINGS, WHICHEVER COMES FIRST, THEREAFTER DIMENSIONAL INSPECTION ................................................................. 21

3.3.3 AT 7500 TAKEOFF/LANDINGS AND EVERY SUBSEQUENT 5000 TAKEOFF/LANDINGS THEREAFTER INSPECTION AND OVERHAUL 22

3.4 HARD LANDING CROSSTUBE DEFLECTION INSPECTION ........................... 25 3.5 REPAIR .............................................................................................................. 26

3.6 CLEANING REQUIREMENTS ........................................................................... 27 3.7 ADJUSTMENTS ................................................................................................. 27



TABLE OF CONTENTS



4.0 TROUBLESHOOTING INFORMATION ............................................................. 28

5.0 REMOVAL AND REPLACEMENT INFORMATION ............................................ 29 5.1 REMOVAL – CROSSTUBES ............................................................................. 29 5.2 INSTALLATION – CROSSTUBES ..................................................................... 29 5.3 REMOVAL – CROSSTUBE SUPPORTS ........................................................... 30 5.4 INSTALLATION – CROSSTUBE SUPPORTS ................................................... 30

5.5 REMOVAL – BEAM ASSEMBLY ........................................................................ 31

5.6 INSTALLATION – BEAM ASSEMBLY ................................................................ 31 5.7 REMOVAL – CLAMP ASSEMBLY ..................................................................... 31

5.8 INSTALLATION – CLAMP ASSEMBLY ............................................................. 32

5.9 REMOVAL – PLATE ASSEMBLY ...................................................................... 32 5.10 INSTALLATION – PLATE ASSEMBLY .............................................................. 32

6.0 STRUCTURAL FASTENER DATA ..................................................................... 33 7.0 SPECIAL TOOLS NEEDED ............................................................................... 33 8.0 TOWING AIRCRAFT .......................................................................................... 33

9.0 WEIGHT AND BALANCE ................................................................................... 33 9.1 LOW SKID GEAR CROSSTUBE ........................................................................ 33

9.2 HIGH SKID GEAR CROSSTUBE ....................................................................... 33 10.0 AIRWORTHINESS LIMITATIONS ...................................................................... 34

10.1 RETIREMENT LIFE ............................................................................................ 34 11.0 PARTS BREAKDOWN ....................................................................................... 35

11.1 LOW SKID GEAR PARTS BREAKDOWN.......................................................... 36 11.1.1 212-320 SERIES LOW GEAR CROSSTUBES ........................................ 36 11.1.2 412-320 SERIES LOW GEAR CROSSTUBES ........................................ 38

11.2 HIGH SKID GEAR PARTS BREAKDOWN ......................................................... 40 11.2.1 212-321 SERIES HIGH GEAR CROSSTUBES ....................................... 40

11.2.2 412-321 SERIES HIGH GEAR CROSSTUBES ....................................... 42 12.0 REFERENCE CROSSTUBE FIGURES ............................................................. 44



TABLE OF CONTENTS



APPENDIX A: DAILY (SERIES 1) // 25 HOUR / 30 DAY (SERIES 2) INSPECTION RECORD ............................................................................................................ 55

APPENDIX B: 100 HOUR / 12 MONTH (SERIES 1) 300 HOUR (SERIES 2) INSPECTION RECORD ..................................................................................... 57

APPENDIX C: AT 7500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 200 TAKEOFF/LANDINGS 212-321-103 HIGH FORWARD CROSSTUBE ONLY INSPECTION RECORD ..................................................................................... 59

APPENDIX D: AT 10,000 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 12 MONTH / 2500 TAKEOFF/LANDINGS DIMENSIONAL INSPECTION 212-321-103 HIGH FORWARD CROSSTUBE ONLY INSPECTION RECORD ............... 62

APPENDIX E: AT 12,500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 5,000 TAKEOFF/LANDINGS 212-321-103 HIGH FORWARD CROSSTUBE ONLY INSPECTION/OVERHAUL RECORD ................................................................ 64

APPENDIX F: AT 2500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 450 TAKEOFF/LANDINGS 412-321-104 / 412-321-304 HIGH AFT CROSSTUBE ONLY INSPECTION RECORD .......................................................................... 68

APPENDIX G: AT 2,500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 12 MONTH / 2,500 TAKEOFF/LANDINGS DIMENSIONAL INSPECTION 412-321-104 / 412-321-304 HIGH AFT CROSSTUBE ONLY INSPECTION RECORD ................... 71

APPENDIX H: AT 7,500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 5,000 TAKEOFF/LANDINGS 412-321-104 / 412-321-304 HIGH AFT CROSSTUBE ONLY INSPECTION/OVERHAUL RECORD ...................................................... 73

APPENDIX I: HISTORICAL SERVICE RECORD........................................................ 77



LIST OF TABLES

Table Title Page


TABLE 1. DAMAGE AND REPAIR LIMITS .................................................................. 26

TABLE 2. TORQUE VALUES ...................................................................................... 27 TABLE 3. TROUBLESHOOTING ................................................................................. 28 TABLE 4. PARTS BREAKDOWN, LOW SKID GEAR CROSSTUBES, 212-320-103

FORWARD / 212-320-104 AFT(1) CROSSTUBE ASSEMBLY ............................ 36 TABLE 5. PARTS BREAKDOWN, 212-320-203 / 212-320-207 HARDWARE KIT ....... 36

TABLE 6. PARTS BREAKDOWN, CROSSTUBE ASSEMBLIES 605-013-101 FORWARD // 605-015-101(1) AFT ...................................................................... 37

TABLE 7. PARTS BREAKDOWN, LOW SKID GEAR AFT CROSSTUBES 412-320-104(1) / 412-320-154(1) AFT CROSSTUBE ASSEMBLIES ................... 38

TABLE 8. PARTS BREAKDOWN, 412-320-203 HARDWARE KIT .............................. 38 TABLE 9. PARTS BREAKDOWN, 605-015-201 AFT CROSSTUBE ASSEMBLY ....... 39

TABLE 10. PARTS BREAKDOWN, HIGH SKID GEAR CROSSTUBES, 212-321-103 FORWARD CROSSTUBE ASSEMBLY 212-321-104(1) / 212-321-304(1) AFT CROSSTUBE ASSEMBLY ................................................................................. 40

TABLE 11. PARTS BREAKDOWN, 212-321-203 / 212-321-207 HARDWARE KIT ..... 40 TABLE 12. PARTS BREAKDOWN, CROSSTUBE ASSEMBLIES 605-003-101

FORWARD // 605-005-101(1) AFT CROSSTUBE ASSEMBLY ........................... 41 TABLE 13. PARTS BREAKDOWN, HIGH SKID GEAR AFT CROSSTUBES,

412-321-106(1) / 412-321-306(1) AFT CROSSTUBE ASSEMBLY ....................... 42 TABLE 14. PARTS BREAKDOWN, HIGH SKID GEAR AFT CROSSTUBES,

412-321-104(1) / 412-321-304(1) AFT CROSSTUBE ASSEMBLY ....................... 42 TABLE 15. PARTS BREAKDOWN, 412-321-200 HARDWARE KIT ............................ 43 TABLE 16. PARTS BREAKDOWN, 605-005-201 AFT CROSSTUBE ASSEMBLY ..... 43



LIST OF FIGURES

Figure Title Page


FIGURE 1. CLEAR COAT AND INSPECTION AREA, 212-321-103 HIGH FORWARD CROSSTUBE (S/N AA-1250 AND SUBSEQUENT) ........................................... 44

FIGURE 2. CLEAR COAT AND INSPECTION AREA, 412-321-104 AND 412-321-304 HIGH AFT CROSSTUBE (S/N AA-1274 AND SUBSEQUENT) ......................... 45

FIGURE 3 (SHEET 1 OF 2). CROSSTUBE DAMAGE LIMITS AND REPAIR ZONES 46 FIGURE 3 (SHEET 2 OF 2). CROSSTUBE DAMAGE LIMITS AND REPAIR ZONES 47

FIGURE 4. CROSSTUBE DEFLECTION LIMITS ........................................................ 48 FIGURE 5. PAINT REMOVAL AREA, 212-321-103 HIGH FORWARD CROSSTUBE 49

FIGURE 6. PAINT REMOVAL AREA, 412-321-104 / 412-321-304 HIGH AFT CROSSTUBE ..................................................................................................... 49

FIGURE 7. 212-321-103 HIGH FORWARD CROSSTUBE ASSEMBLY ...................... 50 FIGURE 8. 212-321-104 / 212-321-304 HIGH AFT CROSSTUBE ASSEMBLY .......... 51

FIGURE 9. 412-321-104 / 212-321-304 HIGH AFT CROSSTUBE ASSEMBLY .......... 52 FIGURE 10. 412-320 /412-321 SERIES AFT CROSSTUBE ASSEMBLIES ................ 53 FIGURE 11. CROSSTUBE TO SKID TUBE ATTACHMENT ....................................... 54




1.0 INTRODUCTION

These instructions contain the information necessary for inspection and maintenance of AERONAUTICAL ACCESSORIES REPLACEMENT CROSSTUBES installed on Bell Helicopter Textron model 205A, 205A-1, 205B, 212, 412, 412EP, 412CF; and Agusta model AB412, AB412EP helicopters in accordance with STC SR00646AT (Low Skid Gear) or SR01052AT (High Skid Gear); and on Restricted Category model UH-1B, UH-1H, SW204, and SW205 helicopters in accordance with STC SR01924AT High or Low Skid Gear.

1.1 DISTRIBUTION

These instructions are provided with each Crosstube. Any airworthiness or flight safety revisions will be immediately made available to all affected Crosstube owners.

1.2 REVISION

A Log of Revision section Js included in these instructions and will be utilized to document all changes. Change recommendations should be submitted to: Aeronautical Accessories Bell Helicopter Piney Flats Technical Support P.O. Box 3689 Bristol, TN 37625-3689 Email: [email protected]

2.0 DESCRIPTION

Aeronautical Accessories Crosstubes are complete assemblies which include Crosstube Supports. As direct replacements for OEM crosstubes, Aeronautical Accessories Crosstubes are interchangeable with Bell Helicopter and Agusta S.p.A. crosstubes for use with other OEM landing gear components.

The Crosstubes are designed to provide an interface between the Landing Gear Skids and the helicopter and to absorb landing loads.

The Forward and Aft Crosstubes for model 205 and 212 helicopters are fitted with two supports, which contact mating Support Fittings in the helicopter structure.

The Aft Crosstube for model 412 variant helicopters utilizes a Beam Assembly, which contacts mating Support Fittings in the helicopter structure. The function of the Beam Assembly on the Aft Crosstube is to reduce the possibility of ground resonance.





3.0 MAINTENANCE INSTRUCTIONS

Maintenance Instructions for Aeronautical Accessories Crosstubes consist of two differing series of inspections. Aeronautical Accessories Series 1 and Series 2 Scheduled Inspections coincide with the Bell Helicopter Part A and Part B Scheduled Inspections for the convenience of the operator. Either inspection series may be employed. However, once a specific inspection series has been established, the helicopter shall remain on that specific inspection series except for the following.

NOTE Scheduled inspection interval tolerances shall be 10% or up to a maximum of 100 hours operating time / 30 calendar days, whichever is less.

1. If the Crosstubes are being reviewed on Series 1 Inspection and are desired to be changed to Series 2 Inspection, a complete 100 Hour / 12 Calendar Months Inspection shall be implemented before changing the helicopter to Series 2 beginning with the 25 Hour / 30 Day Inspection.

2. If the Crosstubes are being reviewed on Series 2 Inspection and it is desired to change to Series 1 Inspection, a complete 300 Hour Inspection shall be implemented before changing the helicopter to Series 1 beginning with the Daily Inspection.

NOTE All Crosstube damage is unacceptable and shall be repaired. Refer to Table 1 for damage and repair limits and Section 3 for repair criteria.

NOTE If Crosstube repair is required, refer to Section 5 for removal of Crosstubes from helicopter.

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

CAUTION Helicopter towing operations must be conducted in accordance with the applicable aircraft model’s Maintenance Manual. Manufacturer towing requirements are applicable to any aircraft being towed with weight on gear which includes towing aircraft with ground handling wheels installed or aircraft resting on moveable platforms. Failure to follow manufacturer towing instructions may result in crosstube damage and/or failure.




3.1 CROSSTUBE INSPECTION – ALL

Crosstubes shall be inspected utilizing Series 1 Inspection or Series 2 Inspection and applicable additional inspections as summarized below.

NOTE Crosstube visual inspection Js conducted with aircraft at rest on skid landing gear; minimum gross weight at inspection Js 9,000 pounds.

NOTE P/N 412-321-104 High Aft Crosstubes, serial number AA-1274 and subsequent, and P/N 212-321-103 High Forward Crosstubes, serial number AA-1250 and subsequent, are manufactured with two primed and clear-coated inspection areas.

CROSSTUBE INSPECTIONS

ALL CROSSTUBES

Section Inspection

3.1.1 Daily Inspection (Series 1) // 25 Hour / 30 Day Inspection (Series 2)

3.1.2 100 Hour / 12 Calendar Month (Series 1) // 300 Hour (Series 2)

3.4 Hard Landing Crosstube Deflection Inspection

212-321-103 HIGH FORWARD CROSSTUBES ONLY

3.2.1 At 7500 Takeoff/Landings and Following Every Subsequent 200 Takeoff/Landings Thereafter Visual Inspection

3.2.2 At 10,000 Takeoff/Landings and Following Every Subsequent 12 Month Or 2500 Takeoff / Landings, Whichever Comes First, Thereafter Dimensional Inspection

3.2.3 At 12,500 Takeoff/Landings and Following Every Subsequent 5000 Takeoff/Landings Thereafter Inspection and Overhaul

412-321-104 / 412-321-304 HIGH AFT CROSSTUBES ONLY

3.3.1 At 2500 Takeoff/Landings and Following Every Subsequent 450 Takeoff/Landings Thereafter Visual Inspection

3.3.2 At 2500 Takeoff/Landings and Following Every Subsequent 12 Month Or 2500 Takeoff/Landings, Whichever Comes First, Thereafter Dimensional Inspection

3.3.3 At 7500 Takeoff/Landings and Following Every Subsequent 5000 Takeoff/Landings Thereafter Inspection and Overhaul




3.1.1 DAILY INSPECTION (SERIES 1 INSPECTION) // 25 HOUR / 30 DAY INSPECTION (SERIES 2 INSPECTION)

1. Inspect the Crosstubes for condition.

2. Inspect Crosstube Supports for condition and security of attachment (evidence of debonding and/or movement).

NOTE If any evidence of debonding and/or movement of the Upper and Lower Supports are found, complete the Support removal and rebonding procedures, Section 5.

3. Visually inspect Crosstube inspection windows, as applicable, for evidence of cracking.

4. Utilize the Inspection Record provided in Appendix A to document inspection.

3.1.2 100 HOUR / 12 CALENDAR MONTH INSPECTION (SERIES 1 INSPECTION) // 300 HOUR INSPECTION (SERIES 2 INSPECTION)

1. Perform Daily Inspection (Series 1 Inspection) // 25 hour / 30 Day Inspection (Series 2 Inspection).

2. Inspect forward and aft caps holding Crosstubes to helicopter for security, and the rubber pads for looseness and/or deterioration.

3. Visually inspect Crosstubes for damage as follows:

NOTE Particular care should be taken to inspect in the areas of the Supports at the aircraft attach points.

a. Inspect the Crosstube for scratches, nicks, dents, and corrosion and note the depth of the damage. (Refer to the zones and limits shown in Figure 3.) The minimal longitudinal distance between repairs is 3.0 inches. Crosstubes exceeding the damage limits shown in Table 1 must be replaced.

NOTE The limits of the damage are also restricted axially and radially as shown in Figure 3.

b. Visually inspect the Supports for nicks, dents, and corrosion. Support damage and repair limits: .020 in. depth for a maximum area of 1.0 square inch. No more than two repairs per support are allowed. Replace Support if damaged beyond limits.

4. Check the torque [80 – 100 in-lbs (9.0 – 11.3 Nm)] on the U-bolts that attach the Supports. Re-torque if necessary.

5. Utilize the Inspection Record provided in Appendix B to document inspection.




3.2 CROSSTUBE INSPECTION, 212-321-103 HIGH FORWARD CROSSTUBE ONLY

3.2.1 AT 7500 TAKEOFF/LANDINGS AND FOLLOWING EVERY SUBSEQUENT 200 TAKEOFF/LANDINGS THEREAFTER VISUAL INSPECTION

(See Figure 1.)

1. Use MIL-PRF-87937 cleaning compound prepared in accordance with the manufacturer’s recommendations to clean all residue and dirt from the cross tube surfaces shown in Figure 1.

2. Using at least 10X magnification and a strong light source, visually inspect the clear coated crosstube areas for indications of cracking.

3. If cracking is suspected, remove clear coat and primer per steps 4 thru 6 below and inspect per step 7.

WARNING IF CRACKING IS DISCOVERED, THE CROSSTUBE IS NO LONGER AIRWORTHY AND MUST BE IMMEDIATELY REPLACED. REMOVE AND REPLACE CROSSTUBE PER SECTION 5 OF THIS REPORT.

4. Apply MIL-R-81294, Type I or II chemical paint remover with a brush and allow it to set from 15 to 45 minutes to soften paint.

5. Using a stiff fiber brush and clean water, rinse paint from crosstube. If required, use abrasive pad (Scotch-Brite, Type A) and MIL-R-81294, Type I or II chemical paint remover to aid in lifting paint. Brush crosstube with abrasive pad in the longitudinal direction, using care so as not to abrade crosstube metal surface.

WARNING DO NOT SAND CROSSTUBE IN A CIRCUMFERENTIAL DIRECTION.

6. Rinse part clean with clean water and dry thoroughly.

NOTE Reapplication of chemical paint remover may be required to ensure that paint and primer is completely removed so that the metal surface of the cross tube is clearly visible. If required, repeat steps 4 thru 6.

7. Using at least 10X magnification and a strong light source, visually inspect the stripped areas for indications of cracking. If cracking is suspected, fluorescent penetrant inspect crosstube per ASTM E1417, Type I, Method B, C, or D, Level 2 in accordance with Bell Helicopter Standard Practices Manual (BHT-ALL-SPM).





8. Following crosstube inspection, coat the stripped crosstube area with MIL-PRF-85582 primer (.0006 – .0009 thick) by spraying in accordance with manufacturer’s instructions. Allow primer to cure per manufacturer instructions.

NOTE The MIL-PRF-85582 primer (PRC-DeSoto EWDE 072A/B) [packaged as a 1-gallon, 1-qt (Parts A&B) kit (P/N EWDE072)] and the MIL-PRF-85285, Type I clear coat paint (Deft 03X085) [packaged as a 3-qt kit (P/N MIL-PRF-85285)]

may be procured from a Bell Helicopter Supply Center. The primer and paint may also be procured [packaged in 1-qt, primer and paint, kits (P/N 1272K)] from Aerospace Products, Inc., 6413 Midway Road, Halton City, TX 76117 (817-332-1669).

9. Following primer cure, paint the area with MIL-PRF-85285 polyurethane clear coat paint by spraying in accordance with manufacturer’s instructions. Allow paint to cure per manufacturer instructions.

Utilize the Inspection Record provided in Appendix C to document inspection.

3.2.2 AT 10,000 TAKEOFF/LANDINGS AND FOLLOWING EVERY SUBSEQUENT 12 MONTHS OR 2500 TAKEOFF/LANDINGS, WHICHEVER COMES FIRST, THEREAFTER DIMENSIONAL INSPECTION

1. Perform Hard Landing Crosstube Deflection Inspection per Section 3.4.

2. Utilize the Inspection Record provided in Appendix D to document inspection.




3.2.3 AT 12,500 TAKEOFF/LANDINGS AND EVERY SUBSEQUENT 5000 TAKEOFF/LANDINGS THEREAFTER INSPECTION AND OVERHAUL (See Figures 1 and 5.)

NOTE Neither the assignment of a time period overhaul of a component nor failure to assign a time period for overhaul of a component constitutes a warranty of any kind. The only warranty applicable to the component is that warranty included in the Purchase Agreement for the component. Time between overhauls and inspection periods is based upon experience, testing, and engineering judgment and is subject to change at the sole discretion of Aeronautical Accessories or an appropriate government agency.

WARNING ALL PARTS REMOVED, DUE TO REACHING THEIR LIMITS OR AS A RESULT OF AN ACCIDENT/INCIDENT AND DEEMED UNAIRWORTHY, SHALL BE PERMANENTLY MARKED AS SCRAP OR PHYSICALLY DESTROYED TO THE EXTENT THAT THERE IS NO CHANCE OF REPAIR OR INSTALLATION ON ANY HELICOPTER OR COMPONENT.

1. Remove fairings from Forward Crosstube Assembly, if installed.

2. Hoist or jack the helicopter until no weight is on the skid tubes.

3. Remove forward straps and associated hardware from forward fuselage fittings.

4. Remove aft straps and associated hardware from aft fuselage fittings.

5. Raise helicopter until it is clear of skid landing gear, and remove landing gear.

6. Remove crosstube supports from Forward Crosstube Assembly in accordance with Section 5.





7. Remove aged sealant from Crosstube by scraping with a sharp piece of plastic. Use of a heat gun to soften the sealant may facilitate removal. Finish by lightly sanding with 400 grit abrasive cloth or paper in the longitudinal direction of the crosstube.

8. Prepare crosstube by chemically removing crosstube paint and primer to top of saddles.

a. Apply MIL-R-81294, Type I or II chemical paint remover with a brush and allow it to set from 15 to 45 minutes to soften paint.

b. Using a stiff fiber brush and clean water, rinse paint from crosstube. If required, use abrasive pad (Scotch-Brite, Type A) and MIL-R-81294, Type I or II chemical paint remover to aid in lifting paint. Brush crosstube with abrasive pad in the longitudinal direction, using care so as not to abrade crosstube metal surface.


c. Rinse part clean with clean water and dry thoroughly. Reapplication of chemical paint remover may be required to ensure that paint and primer is completely removed so that the (bare) metal surface of the cross tube is clearly visible

9. When crosstube is not to be processed immediately after cleaning, apply corrosion preventive oil, to all parts to protect against corrosion. Wrap parts in barrier material and secure with tape.

10. Inspect the stripped areas of the Crosstubes using fluorescent penetrant method per ASTM E1417, Type I, Method B, C, or D, Level 2, in accordance with Bell Helicopter Standard Practices Manual (BHT-ALL-SPM). Refer to BHT-ALL-SPM for fluorescent penetrant inspection procedures.


11. Repair damage within repairable limits in accordance with Section 3.




12. Refinish crosstube by applying MIL-PRF-85582 primer and MIL-PRF-85285 paint (or equivalent) per manufacturer instructions to the stripped areas. The areas to be inspected per Section 3 should be masked to omit MIL-PRF-85285 paint as shown in Figure 1. Paint inspection areas with MIL-PRF-85285 Type I Gloss Clear coat per manufacturer instructions and Figure 1.

13. Reinstall Forward Crosstube straps and fittings per Section 5.

14. Reinstall landing gear/Crosstubes to aircraft per Section 5.

15. Reinstall fairings, as applicable, and return aircraft to service.

16. Utilize the Inspection Record provided in Appendix E to document inspection.




3.3 CROSSTUBE INSPECTION, 412-321-104 AND 412-321-304 HIGH AFT CROSSTUBES ONLY

3.3.1 AT 2500 TAKEOFF/LANDINGS AND FOLLOWING EVERY SUBSEQUENT 450 TAKEOFF/LANDINGS THEREAFTER VISUAL INSPECTION

(See Figure 2.)














WARNING IF CRACKING IS DISCOVERED, THE CROSSTUBE IS NO LONGER AIRWORTHY AND MUST BE IMMEDIATELY REPLACED. REPLACE CROSSTUBE PER SECTION 5 OF THIS REPORT.


NOTE The MIL-PRF-85582 primer (PRC-DeSoto EWDE 072A/B) [packaged as a 1-gallon, 1-qt (Parts A&B) kit (P/N EWDE072)] and the MIL-PRF-85285, Type I clear coat paint (Deft 03X085) [packaged as a 3-qt kit (P/N MIL-PRF-85285)]

may be procured from a Bell Helicopter Supply Center. The primer and paint may also be procured [packaged in 1-qt, primer and paint, kits (P/N 1272K)] from Aerospace Products, Inc., 6413 Midway Road, Halton City, TX 76117 (817-332-1669).


10. Utilize the Inspection Record provided in Appendix F to document inspection.

3.3.2 AT 2500 TAKEOFF/LANDINGS AND EVERY 12 MONTHS / 2500 TAKEOFF/LANDINGS, WHICHEVER COMES FIRST, THEREAFTER DIMENSIONAL INSPECTION

1. Perform Hard Landing Crosstube Deflection Inspection per Section 3.

2. Utilize the Inspection Record provided in Appendix G to document inspection.




3.3.3 AT 7500 TAKEOFF/LANDINGS AND EVERY SUBSEQUENT 5000 TAKEOFF/LANDINGS THEREAFTER INSPECTION AND OVERHAUL

(See Figures 2 and 6.)

NOTE Neither the assignment of a time period overhaul of a component nor failure to assign a time period for overhaul of a component constitutes a warranty of any kind. The only warranty applicable to the component is that warranty included in the Purchase Agreement for the component. Time between overhauls and inspection periods is based upon experience, testing, and engineering judgment and is subject to change at the sole discretion of Aeronautical Accessories or an appropriate government agency.

WARNING ALL PARTS REMOVED DUE TO REACHING THEIR LIMITS OR AS A RESULT OF AN ACCIDENT/INCIDENT AND DEEMED UNAIRWORTHY SHALL BE PERMANENTLY MARKED AS SCRAP OR PHYSICALLY DESTROYED TO THE EXTENT THAT THERE IS NO CHANCE OF REPAIR OR INSTALLATION ON ANY HELICOPTER OR COMPONENT.

1. Remove fairings from Aft Crosstube Assembly, if installed.





6. Remove Aft Crosstube Assembly, Aft Crosstube Beam Assembly, and both Aft Crosstube Clamp Assemblies in accordance with Section 5.

NOTE The Upper Center Support on the Aft Crosstube is bonded with structural adhesive and is not designed for removal.







CAUTION Protect Upper Center Support area on aft high crosstube to prevent contamination by paint strippers and penetrant inspection chemicals.






10. Inspect the stripped areas of the Crosstube using fluorescent penetrant method per ASTM E1417, Type I, Method B, C, or D, Level 2, in accordance with Bell Helicopter Standard Practices Manual (BHT-ALL-SPM). Refer to BHT-ALL-SPM for fluorescent penetrant inspection procedures.







13. Reinstall Aft Crosstube Clamp Assemblies and Aft Crosstube Beam Assembly in accordance with Section 5.



16. Utilize the Inspection Record provided in Appendix H to document inspection.




3.4 HARD LANDING CROSSTUBE DEFLECTION INSPECTION

Crosstube hard landing inspection shall be conducted after a known or suspected hard landing. Inspect Crosstubes for deflection as follows:


2. Measure the lateral distance between the two forward Crosstube attachment straps. Measure the lateral distance between the two aft Crosstube attachment straps. Divide these dimensions by two to determine the helicopter centerline, BL 0.00.

3. Measure the Crosstube horizontal deflection from the centerline of the helicopter, BL 0.00, to the outside of the skid tubes.

4. The Crosstube horizontal deflection as measured in step 3 above must be within the limits as shown in Figure 4. Crosstubes that measure outside of the limits must be replaced.




3.5 REPAIR

Repair all damage (scratches, nicks, dents) and corrosion as follows. Refer to Table 1 for damage/repair limits:

TABLE 1. DAMAGE AND REPAIR LIMITS

Component

Maximum Allowable Damage And Repair Limits *

(Damage and corrosion may be repaired as noted in Section 3.5 Repair, if it does not exceed these limits.)

Scratches/Nicks/Dents And Corrosion Cracks/Holes

Crosstube Refer to Figure 3, sheets 1 and 2 None

Forward Support To a depth of .020” (.508mm) for a maximum area of 1.0 square inch (25.4mm2). No more

than two repairs per support allowed. None

Aft Support To a depth of .020” (.508mm) for a maximum area of 1.0 square inch (25.4mm2). No more

than two repairs per support allowed. None

Clamp Assembly To a depth of .005” (.127mm) None

Notes The following apply to Crosstube damage and repair:

a. All Crosstube damage is unacceptable and shall be repaired.

b. Damage limits apply to the surface areas of the Crosstube as indicated by Figure 3. Circumferential grooves or grind marks are not acceptable.

c. All corrosion shall be cleaned up to twice the visible corrosion depth and shall not exceed the damage limits allowed (refer to Figure 3).

d. The orientation of scratches and corrosion damage is limited by the dimensions in Figure 3.

e. The minimal longitudinal distance between repairs is 3.0 inches.

CAUTION Abrasive blending-out strokes must be parallel to the Crosstube, not circumferential.

1. Polish the affected area in a longitudinal direction using Scotch-Brite or No. 400 to 600 abrasive paper or cloth. Ensure the limits presented in Table 1 and Figure 3 are not exceeded.

2. Clean repaired area with isopropyl alcohol, brush Alodine bare aluminum areas per MIL-DTL-81706 or equivalent, and reprime with Epoxy Polyamide primer per MIL-PRF-23377 or equivalent.

3. Paint repaired area to match existing finish.




3.6 CLEANING REQUIREMENTS

Any dirt, sand, or debris should be cleaned from the Replacement Crosstubes using a mild, nonabrasive soap. Wipe surfaces dry with a nonabrasive cloth or paper before cleaning agent evaporates.

3.7 ADJUSTMENTS

Adjustment of the Replacement Crosstubes is not required. Apply the following torque to all noted fasteners during component or fastener replacement (torque all fasteners in accordance with Table 2):

1. Torque the fasteners attaching the T-Bolt and Clamps (10 Fastener Size).

2. Torque the fasteners attaching the U-Bolt and Supports (1/4 Fastener Size).

3. Torque the fasteners attaching the Saddles to the Crosstubes (1/4 or 3/8 Fastener Size).

TABLE 2. TORQUE VALUES

Fastener Size Torque (In-lbs) Torque (Nm)

10 30 – 40 3.4 – 4.5

1/4 80 – 100 9.0 – 11.3

1/4 (AN4-XXX) 30 – 40 3.4 – 4.5

1/4 (NAS6604-XX) 50 – 70 5.6 – 7.9

3/8 (AN6-XXX) 95 – 100 10.7 – 11.3

3/8 (NAS6606-XX) 160 – 190 18.1 – 21.5




4.0 TROUBLESHOOTING INFORMATION

TABLE 3. TROUBLESHOOTING

Problem Probable Cause Remedy

Landing Gear - Replacement Crosstube is loose or has excessive vibration.

Attachment components or fasteners loose, damaged, or missing.

Check security of crosstube attachment components. Check torque on all fasteners according to Table 2.

Replacement Crosstube is damaged allowing movement.

Check Crosstube for cracks or other damage in accordance with Table 1. Repair / replace as needed.

Aircraft does not sit level

Forward or Aft Crosstube is spread.

Perform Crosstube Hard Landing Inspection per Section 3.4. Replace Components as required.




5.0 REMOVAL AND REPLACEMENT INFORMATION

5.1 REMOVAL – CROSSTUBES

1. Remove fairings, if installed, per manufacturer instructions.





6. Remove the skid tubes and the associated hardware from the Crosstubes.

7. If necessary, remove the Beam Assembly (refer to Section 5.5) and attaching hardware from 412 Aft Crosstubes.

5.2 INSTALLATION – CROSSTUBES

NOTE If skid tubes were removed from Crosstubes, complete steps 1 thru 6. If skid tubes were not removed from Crosstubes, proceed to step 7.

1. Reinstall Crosstubes into skid tube saddles with existing hardware. Apply sealant (AMS-S-8802) under each screw head. Do not torque fasteners at this time.

2. Reinstall the Beam Assembly (refer to Section 5.6) on 412 Aft Crosstubes if previously removed.

3. Install the landing gear on aircraft while keeping the skids off the ground.

4. Torque all screws attaching the Crosstubes to the saddles per Table 2.

5. Lower the helicopter to the ground.

6. Apply a fillet of sealant (AMS-S-8802) around top edge of the saddle.

7. Attach the skid gear to the helicopter with the existing cap assemblies and the attaching hardware. Torque all bolts 100 – 140 in-lbs (11.3 – 15.8 Nm).




5.3 REMOVAL – CROSSTUBE SUPPORTS

NOTE The 604-026-001 Upper Aft Support on the model 412 Aft Crosstubes is bonded with structural adhesive and is not designed for removal. Contact Aeronautical Accessories Bell Helicopter Piney Flats Technical Support for assistance if replacement is required.

1. Remove the Support U-bolts from the Crosstube Assembly.

2. Remove the Supports from the Crosstube Assembly. Use of a heat gun to soften the sealant may facilitate removal.

3. Using a plastic scraper, remove the old sealant from Crosstube and Supports. Clean with a clean cloth and alcohol.

NOTE Inspect the inner surface coating material for deterioration (pealing, cracking, or wear). 604-025-001 / 604-025-003 / 604-025-011 / 604-025-013 and 604-026-003 Supports have black Nylon coating and 205-050-132-001 / 205-050-132-003 and 205-050-133-001 / 205-050-133-003 / 412-050-007-101 Supports have EC2216 adhesive coating. Replace Supports if Nylon coating has separated or has worn through. For EC2216 coated Supports, two coats of EC2216 adhesive may be applied for restoration of the protective barrier. Allow 24 hours for the adhesive to cure.

5.4 INSTALLATION – CROSSTUBE SUPPORTS

NOTE The 604-026-001 Upper Aft Support on the model 412 Aft Crosstubes is not designed for field replacement. Contact Aeronautical Accessories Bell Helicopter Piney Flats Technical Support for assistance if replacement is required.

NOTE Do not reinstall any Aeronautical Accessories Support if uncoated. Aeronautical Accessories coated Supports must be used for reinstallation. Replace coated Supports if damaged or worn. (This note is not applicable to alternate BHT uncoated Supports.)

1. Scuff the faying surface of the Crosstube and the Supports with 180 grit abrasive paper. Do no remove paint from the Crosstube or Nylon/EC2216 coating from the Supports.




2. Clean the sanding residue from the Crosstube and Supports using alcohol and a clean cloth.

3. Apply one layer (approx. 1/16 inch thick) of sealant (AMS-S-8802) to inside surface of the Supports prior to assembly.

4. Reassemble the Upper and Lower Supports and the U-Bolts on the Crosstube, Refer to Figures 7 thru 10.

5. Remove excess sealant or adhesive and wipe clean after assembly.

6. Torque the U-bolt nuts to 80 – 100 in-lbs (9.0 to 11.3 Nm) within 30 minutes after application of sealant or adhesive.

a. Verify torque after cure is complete (72 hours at room temperature). Re-torque as required.

b. Apply fillet of 099-050-222 Sealant to edges of the Support and Crosstube. (Sealant to have no voids.)

CAUTION Flight/landing operations prior to full cure (72 hours at room temperature) could result in Crosstube Support movement.

5.5 REMOVAL – BEAM ASSEMBLY

1. Remove the Cotter Pin, the Nut, the Washers, and the Bolt from the Beam Assembly and the Aft Center Support.

2. Remove the Beam Assembly.

5.6 INSTALLATION – BEAM ASSEMBLY

1. Use the Bolt, the Washers, and the Nut and install the Beam Assembly on the Aft Center Support.

2. Safety the Nut with a new Cotter Pin.

5.7 REMOVAL – CLAMP ASSEMBLY

1. Remove the Nuts from the Clamp Assembly.

2. Remove the Clamp Assembly from the Crosstube Assembly. Use of a heat gun to soften the sealant may facilitate removal.

3. Using a plastic scraper, remove the old sealant from Crosstube and Clamp Assembly. Clean with a clean cloth and alcohol.

NOTE Inspect the Nylon coating on the faying surface of the Clamp for condition. Replace if coating has separated or has worn through.




5.8 INSTALLATION – CLAMP ASSEMBLY

NOTE Do not reinstall any Clamp if uncoated. Coated Clamps must be used for reinstallation. Replace if damaged or worn.

1. Scuff the faying surface of the Crosstube and the Clamps with 180 grit abrasive paper. Do no remove paint from the Crosstube or Nylon Coating from the Clamps.

2. Clean the sanding residue from the Crosstube and Clamps using alcohol and a clean cloth.

3. Apply a layer (approx. 1/16 inch thick) of sealant (AMS-S-8802) to inside surface of the Clamp prior to assembly.

4. Reassemble the Clamp Assembly on the Crosstube (refer to Figures 9 and 10).

5. Remove excess sealant and wipe clean after assembly.

NOTE Use of a wire/string may be required to keep the Clamp Assemblies from sliding down the Crosstube when torque is being applied.

6. Torque the Nuts to 30 – 40 in-lbs (3.4 – 4.5 Nm) within 30 minutes after application of sealant. Check torque after 15 minutes. Re-torque as required.

a. Apply fillet of 099-050-222 Sealant to edges of the Clamp. (Sealant to have no voids.)

5.9 REMOVAL – PLATE ASSEMBLY

1. Remove the Crosstubes from the helicopter per Section 5.1.

2. Using #30 drill bit (.127 – .133), drill out the rivets securing the Plate Assembly to the Crosstube.

3. Remove the Plate Assembly.

5.10 INSTALLATION – PLATE ASSEMBLY

1. Slide the Plate Assembly into the Crosstube until the Saddle bolt holes align with the Plate Assembly bolt holes.

2. Temporarily secure the Plate Assembly in place with crosstube/saddle bolts of the appropriate diameter using washers as spacers if required.

3. Match drill Crosstube rivet holes to the Plate Assembly using a #30 drill bit (.127 – .133).

4. Remove crosstube/saddle bolts and slide Plate Assembly out from Crosstube. Deburr and apply one coat of Epoxy Polyamide Primer per MIL-PRF-23377 or equivalent to Plate Assembly rivet holes.




5. Slide the Plate Assembly into the Crosstube until the Saddle bolt and rivet holes align with the Plate Assembly bolt and rivet holes.

6. Wet Install rivets with Sealant per AMS-S-8802.

6.0 STRUCTURAL FASTENER DATA

For hardware identification and torque refer to Tables 2 and 4 thru 12, and Figures 1 thru 11.

7.0 SPECIAL TOOLS NEEDED

Torque Wrench

8.0 TOWING AIRCRAFT

Helicopter towing operations must be conducted in accordance with applicable model Bell Helicopter Maintenance Manual. Manufacturer towing requirements are applicable to any aircraft being towed with weight on gear. This includes towing aircraft with ground handling wheels installed and aircraft resting on moveable platforms.

CAUTION Failure to follow manufacturer towing instructions may result in crosstube damage and/or failure.

9.0 WEIGHT AND BALANCE

9.1 LOW SKID GEAR CROSSTUBE

Part Number Weight

(lbs) Weight

(kg) FS (in)

FS (mm)

BL (in)

BL (mm)

212-320-103 – Forward 25.19 11.43 71.65 1820 0.00 0.00

212-320-104 – Aft 36.31 16.47 163.00 4140 0.00 0.00

412-320-104 – Aft 42.51 19.28 163.00 4140 0.00 0.00

412-320-154 – Aft (Including Beam Assembly)

53.52 24.28 163.00 4140 0.00 0.00

9.2 HIGH SKID GEAR CROSSTUBE

Part Number Weight

(lbs) Weight

(kg) FS (in)

FS (mm)

BL (in)

BL (mm)

212-321-103 – Forward 32.08 14.55 71.65 1820 0.00 0.00

212-321-104 / 212-321-304 – Aft 44.67 20.26 163.00 4140 0.00 0.00

412-321-104 / 412-321-304 – Aft 49.33 22.38 163.00 4140 0.00 0.00

412-321-106 / 412-321-306 – Aft (Including Beam Assembly)

60.34 27.37 163.00 4140 0.00 0.00




10.0 AIRWORTHINESS LIMITATIONS

10.1 RETIREMENT LIFE

A retirement life has been established for High Aft Crosstubes P/Ns 412-321-304 and 412-321-104 (Serial number 1274 and subsequent) and 212-321-304 (Serial number 1250 and subsequent). An Historical Record is provided (Appendix I) for recording of takeoff/landing operations for the listed life-limited Crosstubes.

PART NUMBER (1) COMPONENT LIFE LIMIT (RIN) (2)

212-321-304 (3) Aft Crosstube, High Skid Gear 24,000 Takeoff/Landings



NOTES:

(1) The airworthiness limitation for part number listed applies to all successive dash numbers for that component unless otherwise specified.

(2) RIN (Retirement Index Number) is the retirement life based on fatigue damage from normal helicopter lifts and takeoffs. New components will begin with an accumulated RIN of zero that will be increased as takeoffs and landings are performed. Operators must record the number of takeoffs/landings and increase the accumulated RIN by 1 for each takeoff/landing. When the maximum RIN is reached, the component will be removed from service.

(3) Applicable to BHT model 205 and 212 helicopters.

(4) Applicable to BHT model 412 helicopters.

The Airworthiness Limitations Section Js FAA approved and specifies maintenance required under §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved.

AIRWORTHINESS LIMITATIONS REVISION HISTORY FAA APPROVAL DATE

Report revision NR thru D N/A –

Report revision E Lance T. Gant 04/14/10

Report revision F: No Change N/A –

Report revision G: No Change N/A –

Report revision H: No Change N/A –

Report revision I: No Change N/A –

Report revision J: No Change N/A –

Report revision K: No Change N/A –




11.0 PARTS BREAKDOWN

Tables 4 thru 16 contain Parts Breakdown data for Aeronautical Accessories Replacement Crosstubes for model 205A, 205A-1, 205B, 212, 412, 412EP, 412CF, AB412, AB412EP, UH-1B, UH-1H, SW204, and SW205 helicopters.

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 Product Support Engineering (PSE)

5 Part replacement requires a fixture or special equipment. Contact PSE

6 Non-stock procurable part




11.1 LOW SKID GEAR PARTS BREAKDOWN

11.1.1 212-320 SERIES LOW GEAR CROSSTUBES

TABLE 4. PARTS BREAKDOWN, LOW SKID GEAR CROSSTUBES,

212-320-103 FORWARD / 212-320-104 AFT(1)

CROSSTUBE ASSEMBLY

Qty -103

Qty -104 Part Number Description

AV Code

1 212-320-203 Hardware Kit 1

1 212-320-207 Hardware Kit 1

1 1 099-091-001 Decal (Alt: 099-091-011) 1

1 605-013-101 Forward Crosstube Assembly 3

1 605-015-101 Aft Crosstube Assembly 3

Notes:

1. 212-320-104 Assembly not for use on 412 models

TABLE 5. PARTS BREAKDOWN, 212-320-203 / 212-320-207 HARDWARE KIT

Qty -203


AV Code

4 NAS1149D0416J Washer 1

8 12 NAS1149D0616J Washer 1

4 NAS6604-11 Bolt 1

8 12 NAS6606-9 Bolt 1

12 NAS6606-11 Bolt 1




TABLE 6. PARTS BREAKDOWN, CROSSTUBE ASSEMBLIES

605-013-101 FORWARD // 605-015-101(1)

AFT

Qty -013-101

Qty -015-101 Part Number Description

AV Code

1 604-003-001 Forward Crosstube 3

1 604-005-001 Aft Crosstube 3

4 604-023-101 Plate Assembly 1

4 4 604-023-103 Plate Assembly 1


2 604-025-001(2)

Upper Forward Support (Alt: 205-050-132-001(3)

) 1

2 604-025-003(2)

Lower Forward Support (Alt: 205-050-133-001(3)

) 1

4 604-025-005 U-Bolt 1

2 604-025-011(2)

Upper Aft Support (Alt: 205-050-132-003(3)

) 1

2 604-025-013(2)

Lower Aft Support (Alt: 205-050-133-003(3)

) 1

4 604-025-015 U-Bolt 1

1 1 099-050-222 Sealant (Alt: 099-050-223) 1

1 4067 Plug 1

20 CR3212-4-8 Rivet 1

20 CR3212-5-8 Rivet 1

8 8 MS21043-4 Nut 1

8 8 NAS1149C0463R Washer (Alt: AN960C416) 1

Notes:

1. Assembly not for use on 412 models

2. Aeronautical Accessories Coated Support

3. BHT Uncoated Support




11.1.2 412-320 SERIES LOW GEAR CROSSTUBES

TABLE 7. PARTS BREAKDOWN, LOW SKID GEAR AFT CROSSTUBES

412-320-104(1)

/ 412-320-154(1)

AFT CROSSTUBE ASSEMBLIES

Qty -104


AV Code

1 412-320-203 Hardware Kit 1

1 099-091-001 Decal (Alt: 099-091-011) 1



1 604-030-001 Beam Assembly (Alt: 412-050-003-109 / -111 / -113) 1

1 412-050-008-101(2)

Bolt (Alt: 604-028-001) 1

1 MS14145L8(2)

Nut 1

1 MS24665-287(2)

Cotter Pin 1

1 NAS1149D1063K(2)

Washer 1

Notes:

1. Assembly for use on BHT 412, 412EP, 412CF, Agusta AB412, AB412EP models only

2. Used to attach Beam Assembly to Crosstube

TABLE 8. PARTS BREAKDOWN, 412-320-203 HARDWARE KIT

Qty Part Number Description AV

Code


12 NAS6606-11 Bolt 1




TABLE 9. PARTS BREAKDOWN, 605-015-201 AFT CROSSTUBE ASSEMBLY


Code




1 604-026-001 Upper Aft Support (Alt: 412-050-006-101A) 1

1 604-026-003 Lower Aft Support (Alt: 412-050-007-101) 1

2 604-026-015 Aft U-Bolt (Alt: 214-052-008-101) 1

2 604-027-001 Clamp Assembly (Alt: 604-027-002) 1

2 604-027-103 Abrasion Strip 1

1 099-050-121 Adhesive 1

1 099-050-222 Sealant (Alt: 099-050-223) 1

20 CR3212-5-9 Rivet 1

1 EC 9324B Adhesive Primer 1

1 LARSON L100 Adhesive 1

8 MS21043-4 Nut 1

8 NAS1149C0463R Washer (Alt: AN960C416) 1




11.2 HIGH SKID GEAR PARTS BREAKDOWN

11.2.1 212-321 SERIES HIGH GEAR CROSSTUBES

TABLE 10. PARTS BREAKDOWN, HIGH SKID GEAR CROSSTUBES, 212-321-103 FORWARD CROSSTUBE ASSEMBLY

212-321-104(1)

/ 212-321-304(1)

AFT CROSSTUBE ASSEMBLY

Qty -103

Qty -104


AV Code

1 212-321-203 Hardware Kit 1

1 1 212-321-207 Hardware Kit 1

1 1 1 099-091-001 Decal 1

1 605-003-101 Forward Crosstube Assembly 3

1 1 605-005-101 Aft Crosstube Assembly 3

Notes:


TABLE 11. PARTS BREAKDOWN, 212-321-203 / 212-321-207 HARDWARE KIT

Qty -203


AV Code

12 NAS6606-11 Bolt 1

8 12 NAS6606-9 Bolt 1

12 12 NAS1149D0616J Washer 1




TABLE 12. PARTS BREAKDOWN, CROSSTUBE ASSEMBLIES

605-003-101 FORWARD // 605-005-101(1)


Qty -003-101

Qty -005-101 Part Number Description

AV Code

2 605-005-121 Decal 1

1 604-003-011 Forward Crosstube 3




2 604-025-001(2)

Upper Forward Support (Alt: 205-050-132-001(3)

) 1

2 604-025-003(2)

Lower Forward Support (Alt: 205-050-133-001(3)

) 1

4 604-025-005 U-Bolt 1

2 604-025-011(2)

Upper Aft Support (Alt: 205-050-132-003(3)

) 1

2 604-025-013(2)

Lower Aft Support (Alt: 205-050-133-003(3)

) 1

4 604-025-015 U-Bolt 1

1 1 099-050-222 Sealant (Alt: 099-050-223) 1

1 4067 Plug 1

20 CR3212-4-9 Rivet 1

20 CR3212-5-9 Rivet 1

8 8 NAS1149C0463R Washer 1

8 8 MS21043-4 Nut 1

Notes:


2. Aeronautical Accessories Coated Support

3. BHT Uncoated Support




11.2.2 412-321 SERIES HIGH GEAR CROSSTUBES

TABLE 13. PARTS BREAKDOWN, HIGH SKID GEAR AFT CROSSTUBES,

412-321-106(1)

/ 412-321-306(1)


Qty -106

Qty -306

Part Number Description AV

Code



1 1 604-028-001(2)

Bolt (Alt: 412-050-008-101) 1

1 1 604-030-001 Beam Assembly (Alt: 412-050-003-109 / -111 / -113) 1

1 1 MS14145L8(2)

Nut 1

1 1 MS24665-287(2)

Cotter Pin 1

1 1 NAS1149D1063K(2)

Washer 1

Notes:


2. Used to attach Beam Assembly to Crosstube

TABLE 14. PARTS BREAKDOWN, HIGH SKID GEAR AFT CROSSTUBES,

412-321-104(1)

/ 412-321-304(1)


Qty -104

Qty -304

Part Number Description AV

Code

1 1 412-321-200 Hardware Kit 1

1 1 099-091-001 Decal (Alt: 099-091-011) 1

1 1 605-005-201 Aft Crosstube Assembly 3

Notes:





TABLE 15. PARTS BREAKDOWN, 412-321-200 HARDWARE KIT


Code


12 NAS6606-11 Bolt 1

TABLE 16. PARTS BREAKDOWN, 605-005-201 AFT CROSSTUBE ASSEMBLY


Code

2 605-005-121 Decal 1




1 604-026-001 Upper Aft Support (Alt: 412-050-006-101A) 1

1 604-026-003 Lower Aft Support (Alt: 412-050-007-101) 1

2 604-026-015 Aft U-Bolt (Alt: 214-052-008-101) 1

2 604-027-002 Clamp Assembly 1

2 604-027-103 Abrasion Strip 1

1 099-050-222 Sealant (Alt: 099-050-223) 1

20 CR3212-5-9 Rivet 1

1 EC 3924B Adhesive Primer 1

1 Larson L100 Adhesive 1

4 MS21043-4 Nut 1

4 NAS1149C0463R Washer (Alt: AN960C416) 1




12.0 REFERENCE CROSSTUBE FIGURES

NOTE Reference Crosstube figures are NOT TO SCALE.

FIGURE 1. CLEAR COAT AND INSPECTION AREA, 212-321-103 HIGH FORWARD CROSSTUBE (S/N AA-1250 AND SUBSEQUENT)




FIGURE 2. CLEAR COAT AND INSPECTION AREA, 412-321-104 AND 412-321-304 HIGH AFT CROSSTUBE (S/N AA-1274 AND SUBSEQUENT)




FIGURE 3 (SHEET 1 OF 2). CROSSTUBE DAMAGE LIMITS AND REPAIR ZONES




Model 205 / 212 Crosstube Damage Limits

Zone Forward Crosstube Aft Crosstube

in. mm in. mm

A1 .005 .127 .005 .127

A2 .015 .381 .015 .381

A3 .005 .127 .005 .127

A4 .015 .381 .015 .381

B1 .015 .381 .015 .381

B2 .015 .381 .015 .381

B3 .015 .381 .015 .381

B4 .015 .381 .015 .381

C1 .010 .254 .012 .305

C2 .010 .254 .012 .305

C3 .010 .254 .012 .305

C4 .010 .254 .012 .305

D .030 .762 .038 .965

Model 412 Crosstube Damage Limits

Zone Forward Crosstube Aft Crosstube

in. mm in. mm

A1 .005 .127 .005 .127

A2 .015 .381 .015 .381

A3 .005 .127 .005 .127

A4 .015 .381 .015 .381

B1 .005 .127 .005 .127

B2 .015 .381 .015 .381

B3 .005 .127 .005 .127

B4 .015 .381 .015 .381

C1 .010 .254 .012 .305

C2 .010 .254 .012 .305

C3 .005 .127 .005 .127

C4 .010 .254 .012 .305

D .030 .762 .038 .965

FIGURE 3 (SHEET 2 OF 2). CROSSTUBE DAMAGE LIMITS AND REPAIR ZONES




Crosstube, Low Skid Gear Part Number

Model Effectivity “A” “B”

in. mm in. mm

212-320-103 (Forward) 205 / 212 / 412 52.00 1321 54.00 1372

212-320-104 (Aft) 205 / 212 52.00 1321 54.00 1372

412-320-154 / 412-320-104 (Low) 412 52.00 1321 54.00 1372

Crosstube, High Skid Gear Part Number

Model Effectivity “A” “B”

in. mm in. mm

212-321-103 (Forward) 205A / 205A-1 / 205B / 212 / 412 / 412EP / 412CF / AB412 / AB412EP / UH-1B / UH-1H / SW204 / SW205

57.00 1448 59.00 1499

212-321-104 / 212-321-304 (Aft) 205 / 212 57.00 1448 59.00 1499

412-321-104 / 412-321-304 (Aft) 412 57.00 1448 59.00 1499

FIGURE 4. CROSSTUBE DEFLECTION LIMITS




FIGURE 5. PAINT REMOVAL AREA, 212-321-103 HIGH FORWARD CROSSTUBE

FIGURE 6. PAINT REMOVAL AREA, 412-321-104 / 412-321-304 HIGH AFT CROSSTUBE




SYMMETRY

CL

13.97013.940

2.547.5

CL

ARC LENGTH

2.00

47.5

45°

45°

VIEW B - B VIEW D - D

CLEARCOAT/INSPECTION AREA

LEFT SIDE AND RIGHT SIDE OF TUBE

APPLY LAYER (APPROX. 1/16" THK) OF

SEALANT TO INSIDE SURFACE OF SUPPORT

PRIOR TO ASSEMBLY WITH CROSSTUBE.

SEALANT TO HAVE NO VOIDS AROUND EDGE.





APPLY FILLET OF SEALANT TO EDGE

OF U-BOLTS/SUPPORT/CROSSTUBE.


CL

13.940-13.970

604-025-001 UPPER FORWARD SUPPORT

604-025-003 LOWER FORWARD SUPPORT

604-025-005 U-BOLT

(2 PLACES)

605-005-121 DECAL

212-321-103 FORWARD CROSSTUBE ASSEMBLY

SECTION C - C

SYMMETRY

VIEW A

MS21043-4 NUT

NAS1149C0463R WASHER

TORQUE 80 - 100 IN-LBS WITHIN 30 MINUTES OF APPLYING SEALANT.

RECHECK TORQUE AFTER SEALANT HAS CURED (72 HOURS)

(4 PLACES)

FIGURE 7. 212-321-103 HIGH FORWARD CROSSTUBE ASSEMBLY




FIGURE 8. 212-321-104 / 212-321-304 HIGH AFT CROSSTUBE ASSEMBLY

SYMMETRY

CL

13.97013.940









APPLY FILLET OF SEALANT TO EDGE

OF U-BOLTS/SUPPORT/CROSSTUBE.


CL

MS21043-4 NUT


TORQUE 80 - 100 IN-LBS WITHIN 30 MINUTES OF APPLYING SEALANT.


(4 PLACES)

13.940-13.970

604-025-011 UPPER AFT SUPPORT

604-025-013 LOWER AFT SUPPORT

604-025-015 U-BOLT

(2 PLACES)

212-321-104 / 212-321-304 AFT CROSSTUBE ASSEMBLY

SECTION C - C

SYMMETRY

VIEW A




FIGURE 9. 412-321-104 / 212-321-304 HIGH AFT CROSSTUBE ASSEMBLY

SYMMETRY

CL

CL

ARC LENGTH

2.00 45°

45°

VIEW C - CVIEW D - D

CLEARCOAT/INSPECTION AREA

LEFT SIDE AND RIGHT SIDE OF TUBE

605-005-121 DECAL

412-321-104 / 412-321-304


12.0

12.0

15.81018.0

55°-65°

120° REF

604-027-002 CLAMP ASSY

604-027-103 ABRASION STRIP REF.

15.81

APPLY LAYER (APPROX. 1/16" THK) OF SEALANT TO INSIDE SURFACE OF CLAMP

PRIOR TO ASSEMBLY WITH CROSSTUBE. REMOVE EXCESS AND WIPE CLEAN.

APPLY FILLET SEALANT AROUND OUTSIDE EDGE.

TORQUE CLAMP 30 - 40 IN-LBS WITHIN 30 MINUTES OF APPLYING SEALANT.

RECHECK CLAMP TORQUE AFTER 15 MINUTES.

604-027-103 ABRASION STRIP

VIEW A

SECTION E - E

SYMMETRY

CL

604-026-003


604-026-001 UPPER AFT SUPPORT604-026-015 AFT U-BOLT

(2 PLACES)

VIEW B

SECTION F - F

MS21043-4 NUT


TORQUE 80 - 100 IN-LBS WITHIN 30 MINUTES OF APPLYING SEALANT


(4 PLACES)




FIGURE 10. 412-320 /412-321 SERIES AFT CROSSTUBE ASSEMBLIES

SYMMETRY

LC

604-030-001 BEAM ASSEMBLY

LOW GEAR412-050-008-101 BOLT

NAS1149D1063K WASHER

MS14145L8 NUT

MS24665-287 COTTER PIN

INSTALLED WITH THREADS FACING FORWARD

HIGH GEAR604-028-001 BOLT

NAS1149D1063K WASHER

MS14145L8 NUT

MS24665-287 COTTER PIN

INSTALLED WITH THREADS FACING FORWARD

412-320-104

AFT CROSSTUBE ASSEMBLY (LOW GEAR)

412-321-104 / 412-321-304

AFT CROSSTUBE ASSEMBLY (HIGH GEAR)

412-320-154 AFT CROSSTUBE ASSEMBLY (LOW SKID GEAR)

412-321-106 / 412-321-306 AFT CROSSTUBE ASSEMBLY (HIGH SKID GEAR)

412-320-104

AFT CROSSTUBE ASSEMBLY (LOW GEAR)

412-321-104 / 412-321-304

AFT CROSSTUBE ASSEMBLY (HIGH GEAR)

412-320-104 AFT CROSSTUBE ASSEMBLY (LOW SKID GEAR)

412-321-104 / 412-321-304 AFT CROSSTUBE ASSEMBLY (HIGH SKID GEAR)

099-091-001 DECAL

APPLIED ON LOWER SURFACE

SYMMETRY

LC

605-015-201 AFT CROSSTUBE ASSEMBLY (LOW GEAR)

605-005-201 AFT CROSSTUBE ASSEMBLY (HIGH GEAR)

604-026-001 UPPER AFT SUPPORT


604-027-001 CLAMP ASSEMBLY (LOW GEAR)

604-027-002 CLAMP ASSEMBLY (HIGH GEAR)

604-027-001 CLAMP ASSEMBLY (LOW GEAR)

604-027-002 CLAMP ASSEMBLY (HIGH GEAR)




FIGURE 11. CROSSTUBE TO SKID TUBE ATTACHMENT

212-320-103 FORWARD CROSSTUBE ASSEMBLY (LOW)

212-321-103 FORWARD CROSSTUBE ASSEMBLY (HIGH)

412-320-104 AFT CROSSTUBE ASSEMBLY (LOW) /

412-320-154 AFT CROSSTUBE ASSEMBLY (LOW) (SHOWN)

412-321-106 AFT CROSSTUBE ASSEMBLY (HIGH)

SECTION A - A

LOW GEAR(4) NAS6606-11 BOLT (INSTALL TIP WET)

(4) NAS1149D0616J WASHER

TORQUE BOLTS 160 - 190 IN-LBS

LOW GEAR(2) NAS6604-11 BOLT (INSTALL TIP WET)



HIGH GEAR(2) NAS6606-11 BOLT (INSTALL TIP WET)



LOW OR HIGH GEAR(4) NAS6606-11 BOLT (INSTALL TIP WET)



LOW SKID GEAR ASSEMBLY

(AA P/N 412-320-500 / 412-320-502)

HIGH SKID GEAR ASSEMBLY

(AA P/N 412-321-500 / 412-321-502)

SECTION B - B

099-050-221 SEALANT

099-050-221 SEALANT

LOW OR HIGH GEAR(2) NAS6606-11 BOLT


INSTALL WET WITH SEALANT (AMS-S-8802)


HIGH GEAR(4) NAS6606-9 BOLT (INSTALL TIP WET)





Daily (Series 1) // 25 Hour / 30 Day (Series 2) Inspection Record


APPENDIX A: DAILY (SERIES 1) //

25 HOUR / 30 DAY (SERIES 2) INSPECTION RECORD



Daily (Series 1) // 25 Hour / 30 Day (Series 2) Inspection Record


Work Order Number: _________________________

Registration Number: _________________________

Serial Number: _________________________

Total Time: _________________________

Date: _________________________

Inspect in accordance with Section 3. The inspection shall consist of the following items:

1. Inspect the Crosstubes for condition.

2. Inspect Crosstube Supports for condition and security of attachment (evidence of debonding and/or movement).

NOTE If any evidence of debonding and/or movement of the Upper and Lower Supports are found, complete the Support removal and rebonding procedures, Section 5.

3. Visually inspect Crosstube inspection windows, as applicable, for evidence of cracking.

Signature ________________________ A & P No. _________________________

Signature ________________________ Inspector _________________________



100 Hour / 12 Month (Series 1) // 300 Hour (Series 2) Inspection Record


APPENDIX B: 100 HOUR / 12 MONTH (SERIES 1)

300 HOUR (SERIES 2) INSPECTION RECORD



100 Hour / 12 Month (Series 1) // 300 Hour (Series 2) Inspection Record




Serial Number: _________________________

Total Time: _________________________

Date: _________________________


1. Perform Daily Inspection (Series 1 Inspection) / 25 hour / 30 Day Inspection (Series 2 Inspection).

2. Inspect forward and aft caps holding Crosstubes to helicopter for security, and the rubber pads for looseness and/or deterioration.

3. Visually inspect Crosstubes for damage as follows:

NOTE Particular care should be taken to inspect in the areas of the Supports at the aircraft attach points.

a. Inspect the Crosstube for scratches, nicks, dents, and corrosion and note the depth of the damage. (Refer to the zones and limits shown in Figure 3.) The minimal longitudinal distance between repairs is 3.0 inches. Crosstubes exceeding the damage limits shown in Table 1 must be replaced.

NOTE The limits of the damage are also restricted axially and radially as shown in Figure 3.

b. Visually inspect the Supports for nicks, dents, and corrosion. Support damage and repair limits: .020 in. depth for a maximum area of 1.0 square inch. No more than two repairs per support are allowed. Replace Support if damaged beyond limits

5. Check the torque on the U-bolts that attach the Supports (80 – 100 in-lbs / 9.0 – 11.3 Nm). Retorque if necessary.

Signature ________________________ A & P No. _________________________




At 7500 Takeoff/Landings // Every Subsequent 200 Takeoff/Landings 212-321-103 High Forward Crosstube ONLY Inspection Record


APPENDIX C: AT 7500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 200 TAKEOFF/LANDINGS

212-321-103 HIGH FORWARD CROSSTUBE ONLY INSPECTION RECORD







Serial Number: _________________________

Total Time: _________________________

Date: _________________________


















NOTE The MIL-PRF-85582 primer (PRC-DeSoto EWDE 072A/B) [packaged as a 1-gallon, 1-qt (Parts A&B) kit (P/N EWDE072)] and the MIL-PRF-85285, Type I clear coat paint (Deft 03X085) [packaged as a 3-qt kit (P/N MIL-PRF-85285)] may be procured from a Bell Helicopter Supply Center. The primer and paint may also be procured [packaged in 1-qt, primer and paint, kits (P/N 1272K)] from Aerospace Products, Inc., 6413 Midway Road, Halton City, TX 76117 (817-332-1669).


Signature ________________________ A & P No. _________________________




At 10,000 Takeoff/Landings // Every Subsequent 12 Month / 2500 Takeoff/Landings Dimensional Inspection

212-321-103 High Forward Crosstube ONLY Inspection Record


APPENDIX D: AT 10,000 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 12 MONTH /

2500 TAKEOFF/LANDINGS DIMENSIONAL INSPECTION 212-321-103 HIGH FORWARD CROSSTUBE ONLY INSPECTION RECORD



At 10,000 Takeoff/Landings // Every Subsequent 12 Month / 2500 Takeoff/Landings Dimensional Inspection

212-321-103 High Forward Crosstube ONLY Inspection Record




Serial Number: _________________________

Total Time: _________________________

Date: _________________________






Signature ________________________ A & P No. _________________________




At 12,500 Takeoff/Landings // Every Subsequent 5,000 Takeoff/Landings 212-321-103 High Forward Crosstube ONLY Inspection/Overhaul Record


APPENDIX E: AT 12,500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 5,000 TAKEOFF/LANDINGS 212-321-103 HIGH FORWARD CROSSTUBE ONLY INSPECTION/OVERHAUL RECORD







Serial Number: _________________________

Total Time: _________________________

Date: _________________________

NOTE Neither the assignment of a time period overhaul of a component nor failure to assign a time period for overhaul of a component constitutes a warranty of any kind. The only warranty applicable to the component is that warranty included in the Purchase Agreement for the component.

Time between overhauls and inspection periods is based upon experience, testing, and engineering judgment and is subject to change at the sole discretion of Aeronautical Accessories or an appropriate government agency.



1. Remove fairings from Forward Crosstube Assembly, if installed.




5. Raise helicopter until it is clear of skid landing gear, and remove landing gear

6. Remove crosstube supports from Forward Crosstube Assembly in accordance with Section 5.





















13. Reinstall Forward Crosstube straps and fittings per Section 5.



Signature ________________________ A & P No. _________________________




At 2500 Takeoff/Landings // Every Subsequent 450 Takeoff/Landings 412-321-104 / 412-321-304 High Aft Crosstube ONLY Inspection Record


APPENDIX F: AT 2500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 450 TAKEOFF/LANDINGS 412-321-104 / 412-321-304 HIGH AFT CROSSTUBE ONLY INSPECTION RECORD







Serial Number: _________________________

Total Time: _________________________

Date: _________________________


















NOTE The MIL-PRF-85582 primer (PRC-DeSoto EWDE 072A/B) [packaged as a 1-gallon, 1-qt (Parts A&B) kit (P/N EWDE072)] and the MIL-PRF-85285, Type I clear coat paint (Deft 03X085) [packaged as a 3-qt kit (P/N MIL-PRF-85285)] may be procured from a Bell Helicopter Supply Center. The primer and paint may also be procured [packaged in 1-qt, primer and paint, kits (P/N 1272K)] from Aerospace Products, Inc., 6413 Midway Road, Halton City, TX 76117 (817-332-1669).


Signature ________________________ A & P No. _________________________




At 2,500 Takeoff/Landings // Every Subsequent 12 Month / 2,500 Takeoff/Landings Dimensional Inspection

412-321-104 / 412-321-304 High Aft Crosstube ONLY Inspection Record


APPENDIX G: AT 2,500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 12 MONTH /

2,500 TAKEOFF/LANDINGS DIMENSIONAL INSPECTION 412-321-104 / 412-321-304 HIGH AFT CROSSTUBE ONLY INSPECTION RECORD



At 2,500 Takeoff/Landings // Every Subsequent 12 Month / 2,500 Takeoff/Landings Dimensional Inspection

412-321-104 / 412-321-304 High Aft Crosstube ONLY Inspection Record




Serial Number: _________________________

Total Time: _________________________

Date: _________________________






Signature ________________________ A & P No. _________________________




At 7,500 Takeoff/Landings // Every Subsequent 5,000 Takeoff/Landings 412-321-104 / 412-321-304 High Aft Crosstube ONLY

Inspection/Overhaul Record


APPENDIX H: AT 7,500 TAKEOFF/LANDINGS // EVERY SUBSEQUENT 5,000 TAKEOFF/LANDINGS

412-321-104 / 412-321-304 HIGH AFT CROSSTUBE ONLY INSPECTION/OVERHAUL RECORD








Serial Number: _________________________

Total Time: _________________________

Date: _________________________

NOTE Neither the assignment of a time period overhaul of a component nor failure to assign a time period for overhaul of a component constitutes a warranty of any kind. The only warranty applicable to the component is that warranty included in the Purchase Agreement for the component.

Time between overhauls and inspection periods is based upon experience, testing, and engineering judgment and is subject to change at the sole discretion of Aeronautical Accessories or an appropriate government agency.



1. Remove fairings from Aft Crosstube Assembly, if installed.




5. Raise helicopter until it is clear of skid landing gear, and remove landing gear

6. Remove Aft Crosstube Assembly, Aft Crosstube Beam Assembly, and both Aft Crosstube Clamp Assemblies in accordance with Section 5.

NOTE The Upper Center Support on the Aft Crosstube is bonded with structural adhesive and is not designed for removal.









CAUTION Protect Upper Center Support area on aft high crosstube to prevent contamination by paint strippers and penetrant inspection chemicals.




c. Rinse part clean with clean water and dry thoroughly. Reapplication of chemical paint remover may be required to ensure that paint and primer is completely removed so that the (bare) metal surface of the cross tube is clearly visible.











13. Reinstall Aft Crosstube Clamp Assemblies and Aft Crosstube Beam Assembly in accordance with Section 5.



Signature ________________________ A & P No. _________________________




HISTORICAL SERVICE RECORD


APPENDIX I: HISTORICAL SERVICE RECORD



HISTORICAL SERVICE RECORD


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