# BOMBARDIER MODIFICATION SUMMARY PACKAGE CERTIFYING AUTHORITY NO. 2 MODEL/TYPE 3 MODSUM NO. COMPLETE IX] 4 SHEET N/A DHC-8-400 15405450003 

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## -0 REVISION ' 6 PRIME DESIGN ACTIVITY BOMBARDIER INC. 

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BOMBARDIER INC.. MONTREAL 

## 0 88308 LEARJET INC. 

## 0 24210 BOMBARDIER INC., TORONTO IX] 71867 SHORT BROTHERS PLC 

## 0 K4585 8 TITLE 10 APPROVED INITIATING DOCUMENT



### Trimming ofStiffeners On LHS/RHS Nacelle MLG A-Frame 

### PCR 44059 

### Assembly P/N 85414025 9 MAJOR ASSY OR COMPONENT AFFECTED

Nacelle MLG A-Frame Assembly P/N 85414025 BASKET MODSUM 

## 0 SEE INDIVIDUAL AUTH DOCUMENTS 11 DESCRIPTION OF MODIFICATION

This IS-Modsum defines trimming of Horizontal and Vertical Stiffeners on MLG A-Frame, in both Left Hand and Right Hand Nacelles.

12 REASON FOR MODIFICATION

This IS-Modsum is developed to improve clearance with MLG Stabilizer Brace, pin 46400-27 and Subs.

13 ENGINEERING REMARKS



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(40113776 Structures, 40126562 Electrical) N/A (IS402400028 Electrical,**~Q1 1Q9A:)li001-4~**  I) (IS402400029 Electricai. .Jie91 I IC[)**~0** -'-l'ilj) ,;.., ".Q-2-"f-1· 15 ENGINEERING VALIDITY 1 # 17 RECOMMENDED SERVICE**EFF~TY**

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## 0 BT0206-02A MW REV 2004-10 ""OCCPOR "ACRL & SOC OR FAA FORM8110-3 REQUIRED © 2004 Bombardier Inc.

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DES REP SIGNATURE Y CERT AUTH DES REP NAME H REV V AIRWORTHINESS CLASSIFICATION ··LEVEL 1 "LEVEL 2 LEVEL 3 W DISCIPLINE CODE X CERT AUTH

DES REP SIGNATURE Y CERT AUTH DES REP NAME BT0206-07 MW REV 2004-10 

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**APP~QVAL.** DCCPOR ACRL &SOC OR FAA FORM8110-3 REQUIRED

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### MODIFICATION SUMMARY PACKAGE 3 MODSUMNO. 4 SHEET 15405450003 Q..
Location of Modification I On LHS and RHS Nacelle Rework Location A-Frame- Main View (Hidden)

D LHS Outbd Up RHS Outbd 

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c Main View View Looking Fwd On A-Frame Assembly P/N 85414025 

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Section A- A shown, Section B-B opp IS4Q5450003 

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Looking Down On A-Frame Assembly Horizontal Stiffener

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### MODIFICATION SUMMARY PACKAGE 3 MODSUM NO. IS4Q5450003

Detail View Showing Blending ofCorner

Detail View Showing Final Trim on Horizontal Stiffener '4 SHEET 

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Looking Up/Left On A-Frame Assembly Vertical Stiffener 

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Detail View Showing Trimming Dimensions on Vertical Stiffener R.4/1.0 4 SHEET 

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Detail View Showing Final Trim on Vertical Stiffener ,.4 SHEET 

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### -C... Engineering Instructions This procedure is to be completed in conjunction with Installation of Main Landing Gear Brace 46400-27 and Subs 1. Identify the retrofit areas in LH and RH Nacelles as shown on sheet 3. 2. Mark trim lines to dimensions shown on sheets 4 and 7. 3. Remove the material from the A-Frame Stiffeners as shown on sheets 4 through 8. 4. Break sharp edges and deburr cut metal edges ofthe A-Frame. 10



### 5. Clearance Check: After completion of metal removal, cycle the gearto ensure there is 0.100" minimum clearance between the MLG Stabilizer Brace, adjacent harness assemblies, and newly reworked A-Frame Stiffeners. Ifclearance limit to the Harnesses can not be met, see IS402400028 (AJC 4056-4090) or IS4Q2400029 (A/C 4090-4411) for re-dressing the routing. Contact BombardierAerospace for other reduced clearances between the Brace and Structure. ·I 

### 6. Solvent clean cut metal edges per Aircraft Maintenance Manual, Chapter 51-27-01. 7. Inspect reworked area and adjacent area using Eddy Current or Flourescent Dye Penetrant to ensure that the material does not indicate cracking. 8. Shot Peen cut areas using a Roto Peen Flap Assembly, to a Roto Peen Intensityof 10 (equivalent to an Almen "A" Intensity of 8). 9. Improve cut metal edges to

## achie~e a surface finish of 125RMS orfiner.**~** 

### 10.Solvent clean cut metal edges per Aircraft Maintenance Manual, Chapter 51-27-01. 11.Apply Alodine C1 per Dash 8 Structural Repair Manual PSM 1-84-3, Chapter 51-21-10, to bare areas. 12.Apply Epoxy Primer F19 per Dash 8 Structural Repair Manual PSM 1-84-3, Chapter 51-25-10, to Alodined areas. 13.Apply Polyurethane Enamel F24 per Dash 8 Structural Repair Manual PSM 1-84-3, I I Chapier 51-25-15, to Primed areas. 14.Applythe markings 15405450003-1 adjacent to the existing serial plates and adjacent to the reworked areas on the A-Frame using an indelible permanent marker per Aircraft Maintenance Manual, PSM 1-84-2, Chapter20-00-01. 15.After the markings have dried, apply a ClearCoat (no colour) of F24 polyurethane enamel over the applied 15405450003-1 markings per the Dash-8 Structural Repair Manual, PSM 1-84-3, Chapter 51-25-15. 16. Reference: See IS4Q2400028 (AJC 4056-4090} or IS402400029 (AJC 4090-4411) affectin_g.Jhe surrounding electrical harnesses within the nacelle cavity. IJoalANGE

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