Revision ‘C’ 05 Mar 2015 DHC ---8 (DASH 8) SERVICE BULLETIN 84 ---54 ---20 Nacelles --- A ---Frame --- Retrofit --- Flanges Trimmed for Clearance to Retracted MLG Stabilizer Brace --- ModSum 4 ---113776 This page transmits Revision ‘C’ of Service Bulletin 84 ---54 ---20, pages 1 thru 26, dated 05 Mar 2015. This service bulletin is re ---issued in its entirety for the reasons that follow: --- the Compliancesection is revised to add the reference to AD CF ---2014 ---45 Part II --- the Referencessection is revised to convey the latest revision of the service bulletin and engineering documentation --- theACCOMPLISHMENT INSTRUCTIONSsection is revised to move the Job Set ---Up instructions that are applicable only to the rework to Proceduresection Part ---B --- Rework --- the Proceduressection is revised to change the AMM TASK reference in step (j) from 32 ---31 ---00 ---710 ---301 to 32 ---31 ---00 ---710 ---801. The Compliance in the previous issue(s) of this service bulletin is not affected by this revision. No additional rework to the aircraft is introduced by this revision. Remove the previous revision of Service Bulletin 84 ---54 ---20 and replace with attached. Previous issue(s) of Service Bulletin 84 ---54 ---20: Initial issue --- Pages 1 thru 24 dated 25 Apr 2013 Revision ‘A’ --- Pages 1 thru 24 dated 09 Apr 2014 Revision ‘B’ --- Pages 1 thru 26 dated 02 Oct 2014

# D

S.B. 84 ---54 ---20 Page 1 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB 

# SERVICE BULLETIN Customer Support ATA SYSTEM: 5420 NUMBER: 84 ---54 ---20 

### BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND URGE OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Nacelles --- A ---Frame --- Retrofit --- Flanges Trimmed for Clearance to Retracted MLG Stabilizer Brace --- ModSum 4 ---113776

1. PLANNING INFORMA TION A. Effectivity Aircraft Affected: In ---Service: DHC ---8 Aircraft Models 401 and 402 Serial Numbers 4056 thru 4426. NOTE: If ModSum IS4Q5450003 was previously accomplished, no further action is required. NOTE: It is highly recommended that this Service Bulletin be accomplished concurrently with service bulletin 84 ---32 ---114. Production: ModSum 4 ---123818 will be installed before delivery on applicable DHC ---8 Aircraft at Serial Numbers 4427 thru 4454, 4456, 4457, 4459, 4460 and 4463. ModSum 4 ---170073 will be installed before delivery on applicable DHC ---8 Aircraft at Serial Number 4455. ModSum 4 ---170060 will be installed before delivery on applicable DHC ---8 Aircraft at Serial Numbers 4458, 4461, 4462, 4464 and subsequent.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 2 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB NOTE: The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery on the aircraft or as changed by Bombardier Aerospace Service Bulletin(s). Before you do this bulletin, examine all STC or equivalent action changes to make sure this bulletin can be completed. Spares Affected: None B. Reason Problem: There is insufficient clearance between the main landing gear (MLG) stabilizer brace and nacelle A ---Frame. Impact between the MLG stabilizer brace and nacelle A ---Frame may lead to reduced structural integrity of the nacelle A ---Frame and MLG stabilizer brace. Solution: This service bulletin introduces ModSum 4 ---113776. The ModSum reworks the nacelle A ---Frame flanges to improve the clearance between the MLG stabilizer brace and the nacelle A ---Frame. C. Description The procedures in this service bulletin give the instructions to do the tasks that follow: --- nose landing gear lock is engaged --- main landing gear lock pins are installed thru each main gear and main gear door mechanism --- aircraft is lifted on jacks --- main landing gear forward doors are removed --- pressure in the No. 1, 2 & 3 hydraulic systems is depleted --- all aircraft electrical power systems are selected to OFF --- work platforms or ladders are set up and properly grounded --- main landing gear stabilizer struts, and harnesses if necessary, are removed

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 3 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB --- LH and RH nacelle A ---Frame flanges are reworked and inspected --- reworked areas are flap peened and re ---finished with alodine, F19 epoxy primer and F24 polyurethane enamel --- fluorescent penetrant inspection or high frequency eddy current inspection of the reworked and adjacent areas is done --- flap peen of the reworked area is done --- expose surfaces are cleaned and treated --- removed harnesses and tie mounts are re ---installed --- clearance between nacelle A ---Frame and MLG stabilizer brace in the reworked areas is measured --- Bombardier Technical Help Desk is contacted if clearance is not within limits --- LH and RH A ---Frame assemblies are re ---identified and coated if clearance is within limits --- landing gear is extended --- main landing gears forward doors are re ---installed --- aircraft is lowered and jacks are removed --- close out. D. Compliance Bombardier Inc. highly recommends that ModSum 4 ---113776 be incorporated at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority. Transport Canada Airworthiness Directive CF ---2014 ---45 Part II. E. Approval The technical content of this service bulletin has been approved under the authority of the Transport Canada Civil Aviation (TCCA) Design Approval Organization No: DAO #93 ---Q ---02.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 4 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB F. Manpower It will take an estimated 21 man ---hours to complete this service bulletin. The breakdown of the man ---hours is shown in the table that follows: TASK MAN ---HOURS Job Set ---Up 0.50 Procedure 20.00 Test / RTS 0.00 Close ---Out 0.50 For any on---site labor assistance, please speak with a Fleet Services representative for a quote. The Fleet Services group can be contacted via the Q Series Technical Help Desk by telephone at 416---375---4000 or email at: thd.qseries@aero.bombardier.com. G. Material --- Price and Availability The ModKit required to do this service bulletin is listed in the table below. Operators should submit a purchase order through the Customer Accounts Service Team (CAST) at Bombardier Aerospace Regional Aircraft division specifying aircraft serial number(s) to: Bombardier Aerospace Customer Accounts Services Team (Mail Stop N11 ---32) 123 Garratt Blvd. Toronto Ontario Canada M3K ---1Y5 Facsimile: (416) 375 ---3060 Telephone: (416) 375 ---3920

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 5 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Facsimile: International: (416) 375 ---3334 European: (416) 373 ---5966 Americas East: (416) 373 ---5964 Americas West: (416) 373 ---5965 Telephone: International: (416) 375 ---3706 European: (416) 373 ---3704 Americas East: (416) 375 ---3700 Americas West: (416) 373 ---5888 E ---mail addresses: International: cast.international@aero.bombardier.com European: cast.europe@aero.bombardier.com Americas East: cast.americaseast@aero.bombardier.com Americas West: cast.americaswest@aero.bombardier.com

Kit Number Description 8DK4205 ---001 Drawing Kit --- Nacelle, A ---Frame
The part(s) and material(s) detailed in Paragraph 2.A. may be either furnished or fabricated from the operator’s existing stock, purchased as single items from Bombardier Aerospace Regional Aircraft or purchased directly from industry sources. DK parts are to be manufactured and approved locally (refer to disclaimer in the related text or illustration). In some cases, an equivalent to the DK part may be available from Bombardier under the production part number shown as reference in Parts Required Per Aircraft.
H. Tooling --- Price and Availability

Part Number Description Remarks 85414787 ---115 ---76 Marking Tool

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 6 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB I. Weight and Balance None
J. Electrical Load Data Not affected
K. Publications Affected Dash 8 Illustrated Parts Catalogue PSM 1 ---84 ---4

.................... ModSums Manual PSM 1 ---84 ---12

.................................. L. References Revision ‘C’ of this service bulletin was prepared to the engineering drawings and related data that follows:
DRAWING SHEET REV

8DK4205 1

--- ---

8Z9566 1 A
ModSum 4Q113776 Rev. ‘D’ ModSum 4 ---113776 Rev. ‘D’ ModSum 4Y123798 Rev. ‘B’ ModSum 4 ---123798 Rev. ‘B’ ModSum 4Y123818 Rev. ‘H’ ModSum 4 ---123818 Rev. ‘H’ ModSum 4Q126562 Rev. ‘F’ ModSum 4 ---126562 Rev. ‘F’

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 7 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB ModSum 4D170073 Rev. ‘A’ ModSum 4 ---170073 Rev. ‘A’ ModSum 4D170060 Rev. ‘D’ ModSum 4 ---170060 Rev. ‘D’ ModSum IS4Q5450003 Rev. ‘C’ Service Bulletin 84 ---32 ---114 ModSum IS4Q2400028 Rev. ‘B’ ModSum IS4Q2400029 Rev. ‘A’ All Operator Message (AOM) 389 PCA 44059 Revision 3 (for internal reference only) Transport Canada Airworthiness Directive CF ---2014 ---45 2. MATERIAL INFORMA TION A. Parts Required Per Aircraft (1) Drawing Kit 8DK4205 ---001 (2) Detailed Kit Content:

Quantity Per Kit ---001 Part Number Description Remarks

--- 8Z9566 Retrofit Drawing Drawing Only

--- 8DK4205 Kit Drawing Only

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 8 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB NOTE: This service bulletin is self ---contained (illustrated). No drawings will be supplied.
NOTE: Operators who would like the drawings to be supplied to them should follow the instructions given in AOM 389.
(3) In addition to the above part(s), the following material(s) are required for the completion of this service bulletin and may be procured as single items from Bombardier Aerospace Regional Aircraft or purchased directly from industry sources. Addresses of manufacturers and suppliers not shown below are listed in either Maintenance Manual Chapter 20 or in Structural Repair Manual Chapter 51 or, for 400 Series Aircraft, in Consumable Products Manual PSM 1 ---84 ---18.

Part No/ Product ID No. Qty. Per Aircraft Description Remarks

05 ---11 or 05 ---23 or 05 ---34 As Required Adhesive, Epoxy Adhesive, Acrylic DHMS CA6.09 Fastweld #10 CB200 or CB200 ---40 07 ---02 1/4 Pint Primer, Chromated Epoxy DHMS C4.01 or MIL ---PRF ---23377 07 ---08 1/4 Pint Coating, Polyurethane Enamel (F24) MIL ---PRF ---85285 DHMS C4.04 Type 4 07 ---21 1/2 Ounce Coating, Chemical Conversion MIL ---C ---5541 13 ---65 As Required Fluorescent Penetrant ASTM ---E ---1417

NOTE: Refer to CPM PSM 1 ---84 ---18 for the list of approved alternative consumable products under each Product ID No., any of which can be used unless a note states otherwise.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 9 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB B. Parts Required to Modify Spares None C. Special Tools and Equipment Required

Reference Description Remarks

--- Eddy Current instrument Phasec 2200 (Hocking) or equivalent Commercially available

--- Calibration Test Standard, Hocking, P/N (CTS) SRS 0824A or equivalent Commercially available

NOTE: The above tools/equipment are only necessary if a high frequency eddy current (HFEC) inspection is done.
D. Existing Parts Accountability The following parts may be affected by this service bulletin. Indented parts are components of the next higher assembly. The quantity (Qty.) column lists the quantity that may be affected per aircraft for non ---indented parts and the quantity per next higher assembly for indented parts.

Existing Part Number Description Qty. IC DC New Part Number PNC 85414787 ---107 or 85414787 ---109 or 85414787 ---111 or 85414787 ---113 or 85414787 ---115 A ---Frame (LH) 1 A RWK 8Z9566 ---001 R

85414787 ---108 or 85414787 ---110 or 85414787 ---112 or 85414787 ---114 or 85414787 ---116 A ---Frame (RH) 1 A RWK 8Z9566 ---002 R

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 10 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB IC Interchangeability Code A Not interchangeable. B Removed Part. No direct replacement. C Conditionally Interchangeable. Installation of superseded part negates the intent of this service bulletin. DC Disposition DIS Discard Part. MUI Multiple Usage Item: Return to stock if serviceable. RWK Rework existing part in accordance with this service bulletin. RWI Rework existing part per ..... SAL Salvage. Return to operator’s stores for salvage consideration. PNC Part Number Code N No equivalent Bombardier Inc. part number for reworked part. Indicate on part that this service bulletin has been accomplished. R Part number after rework. S Superseding or equivalent part number. X Reworked part and superseding part are functionally and physically equivalent but not identical. 3. ACCOMPLISHMENT INSTRUCTIONS
A. Job Set ---Up

NOTE: If ModSum IS4Q5450003 is previously accomplished, no further rework is necessary. (1) Make sure the nose gear ground lock is engaged. (2) Make sure that lock pins are installed through each main gear and main gear door mechanism.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 11 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB B. Procedure Part A --- Inspection (1) Inspect the LH and RH A ---frames and the upper surface stabilizer brace lug as follows: (a) Do a detailed visual inspection of the A ---frame (refer to Figure 2, Sheet 1) and of the upper surface of stabilizer brace lug (refer to Figure 3, Sheet 2 and Figure 4). (b) If damage is found, contact the Q Series Technical Help Desk by telephone at 416---375---4000 or email at: thd.qseries@aero.bombardier.com for approved repair. Part B --- Rework (1) Jack the aircraft (refer to AMM TASK 07 ---10 ---00 ---582 ---801). (2) Remove the LH and RH MLG forward doors (refer to AMM TASK 32 ---12 ---11 ---000 ---801). (3) Deplete hydraulic pressure in the No. 1, 2 & 3 systems (refer to AMM TASKs 29 ---00 ---00 ---863 ---802 and 29 ---00 ---00 ---863 ---804). (4) Install a warning sign on the external hydraulic connection. (5) Placard and select all aircraft electrical power to OFF. Obey all relevant WARNINGS and CAUTIONS (refer to AMM TASKs 24 ---00 ---00 ---861 ---802 and 24 ---00 ---00 ---910 ---801). (6) Set up work platforms or ladders as required to gain access to the stabilizer brace in the No. 1 and/or No. 2 wheel well (refer to Figure 1). Make sure that the work platforms or ladders are electrically grounded. (7) Remove the LH and RH MLG Stabilizer struts (refer to AMM TASK 32 ---11 ---16 ---000 ---801).

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 12 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB (8) If necessary, remove the MLG harnesses to gain access to the rework area (refer to Figure 5). If a harness tie mount is installed on the rework area, mark/record the position and remove it before doing PART B ---Rework of this service bulletin (refer to Figure 5). (9) Rework the LH and RH A ---Frame flanges as follows (refer to Figure 2): (a) Mark intersection point of flanges as shown in Figure 2 Sheet 2 DETAILS E and F. Mark flange trim locations as shown in Figure 2 Sheet 1 DETAIL A from this point.

NOTE: For ease of marking, the use of marker tool P/N 85414787 ---115 ---76 is acceptable. (b) Remove material from A ---Frame (refer to Figure 2 Sheet 3 SECTION B ---B, Sheet 4 DETAILS G and H, Sheet 5 SECTION C ---C, Sheet 6 Section D ---D and Figure 5). (c) Finish edges (refer to applicable instructions in SRM 51 ---14 ---00) and deburr and clean cut metal edges (refer to applicable instructions in SRM 51 ---26 ---00). (d) Inspect reworked area and adjacent area for cracks using FPI (preferred method) per ASTM ---E ---1417 using Type 1 Method C Level 3 Form d or using HFEC inspection (alternate method) per PSM 1 ---84 ---7A NDT Manual Part 6 51 ---00 ---01. If crack is found, contact the Q Series Technical Help Desk by telephone at 416---375---4000 or email at: thd.qseries@aero.bombardier.com for approved disposition/action. (e) If fluorescent penetrant inspection (FPI) of the reworked area and adjacent area will be done, perform etching of the area to be inspected per SRM 51 ---20 ---00. (f) Flap peen reworked areas per MIL ---R ---81841 or equivalent. Make sure the intensity is 0.006A to 0.008A.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 13 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB (g) Clean and treat exposed surfaces with Alodine (Product ID No. 07 ---21) and then apply epoxy primer (Product ID No. 07 ---02) and polyurethane enamel (Product Id No. 07 ---08) on all applicable rework areas (refer to CPM PSM 1 ---84 ---18 for approved alternatives and to applicable instructions in AMM TASKs 51 ---25 ---16 ---390 ---801, 51 ---25 ---26 ---370 ---801 and 51 ---25 ---31 ---370 ---801). (h) Re ---install harnesses and the harness tie mount that was removed to the recorded location. Attached tie mount with adhesive 05 ---11 or 05 ---23 or 05 ---34 (refer to AMM TASK 20 ---10 ---08 ---400 ---802 and Figure 5) NOTE: Harnesses can be rerouted per SB 84 ---32 ---114 or ModSum IS4Q2400028 (A/C 4056 ---4089) or ModSum IS4Q2400029 (A/C 4090 ---4411). (i) Remove all tools, equipment and unwanted materials from the nacelle work area. (j) Measure the clearance between the nacelle A ---Frame and MLG stabilizer brace assembly in the reworked area as follows (refer to Figure 3 and Figure 4): 1 Re ---install the LH and RH MLG stabilizer struts (refer to AMM TASK 32 ---11 ---16 ---400 ---801). 2 With the LH and RH forward doors still removed from aircraft, do the Operational Test of the Landing Gear Primary Extension and Retraction System (refer to AMM TASK 32 ---31 ---00 ---710 ---801). Swing the landing gear up and leave in the up and locked position. 3 With the MLG in retracted position, measure the clearance between the A ---frame and MLG stabilizer brace assembly in the reworked areas (refer to Figure 3 per flagnote 1 in VIEW A and SECTIONs C ---C and D ---D.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 14 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB NOTE: If the clearance limit to the harness cannot be met, re ---dress the harness routing per SB 84 ---32 ---114 (or ModSum IS4Q2400028 on aircraft s/n’s 4056 thru 4089 or ModSum IS4Q2400029 on aircraft 4090 thru 4411) and ModSum 4Y123798 on aircraft s/n’s 4412 thru 4426. (k) If the minimum clearance is less than 0.100 in. (2.54 mm), contact the Q Series Technical Help Desk by telephone at 416---375---4000 or email at: thd.qseries@aero.bombardier.com for approved disposition/action. (l) If the clearance is equal or more than 0.100 in. (2.54 mm), re ---identify the LH A ---Frame as 8Z9566 ---001 and RH A ---Frame as 8Z9566 ---002 with indelible marking. After the identification markings have dried, apply a clear coat (no color) of polyurethane enamel (Product ID No. 07 ---08) (refer to CPM PSM 1 ---84 ---18 and to applicable instructions in AMM TASK 51 ---25 ---31 ---370 ---801). (m) Extend the landing gear (refer to applicable instructions in AMM Task 32 ---31 ---00 ---867 ---801). (n) Re ---install the MLG forward doors (refer to AMM TASK 32 ---12 ---11 ---400 ---801) and rig the doors (refer to AMM TASK 32 ---12 ---11 ---830 ---801). (o) Lower the aircraft on jacks and remove the jacks (refer to applicable instructions in AMM Task 07 ---10 ---00 ---582 ---801). C. Close Out (1) Remove all tools and equipment from the work area. (2) On incorporation of this ModSum, make an entry that conforms to local regulatory requirements in the applicable logbook(s). Enter component serial numbers if applicable. Enter this ModSum number only after complete and functional incorporation of all work defined in this service bulletin.

THE DESIGN OF THE PART IN THIS DRAWING HAS BEEN APPROVED BY DE HAVILLAND INC. FOR MANUFACTURE BY OR ON BEHALF OF THE RECIPIENT. THE RECIPIENT IS RESPONSIBLE FOR (A) PROPER MANUFACTURE OF THE PART USING THE SPECIFIED MATERIALS AND FOR INCORPORATION OF THE MODIFICATION, ALL IN ACCORDANCE WITH THE DRAWING AND RELATED INSTRUCTIONS, AND (B) APPROVAL OF THE FINAL INSTALLATION BY THE RELEVANT AIRWORTHINESS AUTHORITY. DE HAVILLAND INC. AND BOMBARDIER INC. (BOMBARDIER AEROSPACE REGIONAL AIRCRAFT) DISCLAIM ANY RESPONSIBILITY FOR INCIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING WITHOUT LIMITATION LOSS OF USE, LOSS OF REVENUE OR LOSS OF PROFIT, ARISING FROM SUCH MANUFACTURE, INCORPORATION AND INSTALLATION.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 15 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Retrofit --- Nacelle A ---Frame Figure 1 AREA OF RETROFIT

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 16 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Retrofit --- Nacelle A ---Frame Figure 2 (Sheet 1)NOTE:All dimesions are in inches.DETAILED VISUAL INSPECTION FOR DAMAGE

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 17 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Retrofit --- Nacelle A ---Frame Figure 2 (Sheet 2) 

### NOTE: All dimesions are in inches.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 18 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Retrofit --- Nacelle A ---Frame Figure 2 (Sheet 3)NOTE:All dimesions are in inches. 

## G

H

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 19 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Retrofit --- Nacelle A ---Frame Figure 2 (Sheet 4)NOTE: All dimesions are in inches.



### DETAIL 

## G

DETAIL 

## H

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 20 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Retrofit --- Nacelle A ---Frame Figure 2 (Sheet 5) 

### NOTE: All dimesions are in inches.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 21 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Retrofit --- Nacelle A ---Frame Figure 2 (Sheet 6) 

### NOTE: All dimesions are in inches.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 22 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB STABILIZER BRACE A ---FRAME

Nacelle A ---Frame and MLG Stabilizer Brace --- Clearance Measurement Figure 3 (Sheet 1) WITH THE MAIN LANDING GEAR RETRACTED, MEASURE THE CLEARANCE BETWEEN THE NACELLE A ---FRAME AND MLG STABILIZER BRACE.

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 23 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB STABILIZER BRACE P/N 46400 ---25 SHOWN

WITH THE MAIN LANDING GEAR RETRACTED, MEASURE THE CLEARANCE BETWEEN THE NACELLE A ---FRAME AND MLG STABILIZER BRACE.
Nacelle A ---Frame and MLG Stabilizer Brace --- Clearance Measurement Figure 3 (Sheet 2) STABILIZER BRACE P/N 46400 ---27 SHOWN

0.100 IN. (2.54 MM) MIN

0.100 IN. (2.54 MM) MIN (MINIMAL DISTANCE BETWEEN STOP BRACKET AND A ---FRAME)

(MINIMAL DISTANCE BETWEEN STABILIZER BRACE STRUCTURE AND A ---FRAME) DETAILED VISUAL INSPECTION FOR DAMAGE

DETAILED VISUAL INSPECTION FOR DAMAGE SECTION C ---C SECTION D ---D

SECTION C ---C SECTION D ---D

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 24 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Nacelle A ---Frame and MLG Stabilizer Brace --- Clearance Measurement Figure 4 INSPECTION AREA (A ---FRAME AND MLG STABILIZER BRACE) CLEARANCE BETWEEN MLG BRACE ASSEMBLY AND A ---FRAME MINIMUM 0.100 IN. (2.54 MM) DARK AREA SHOWING MATERIAL TO BE REMOVED

NOTE: If clearance limit to the harnesses cannot be met. redress the harness routing per SB 84 ---32 ---114 or ModSum IS4Q2400028 (a/c 4056 thru 4089) or ModSum IS4Q2400029 (a/c 4090 thru 4411).

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 25 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB Trimmed Nacelle A ---Frame Figure 5 2 3 4

IF NECESSARY, REMOVE WIRING HARNESS TO GAIN ACCESS TO THE REWORK AREA. 2 IF A HARNESS TIE MOUNT IS INSTALLED ON THE REWORK AREA, MARK/RECORD THE 3 POSITION AND REMOVE IT BEFORE REWORK. AFTER REWORK, RE ---INSTALL HARNESS TIE MOUNT TO THE RECORDED LOCATION. 4 ATTACHED TIE MOUNT WITH ADHESIVE 05 ---11, OR 05 ---23 OR 05 ---34 (REFER TO AMM TASK 20 ---10 ---08 ---400 ---802). HARNESSES CAN BE REROUTED PER SB 84 ---32 ---114 OR IS4Q2400028 (A/C 4056 ---4089) OR IS4Q2400029 (A/C 4090 ---4411).

### SERVICE BULLETIN 84 ---54 ---20

S.B. 84 ---54 ---20 Page 26 of 26 25 Apr 2013 Revision ‘C’ 05 Mar 2015 NB 

### This Page Intentionally Blank 1Jan 2009 SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION --- Q SERIES DASH 8 AIRCRAFT To: CMDB Focal Facsimile: (1) 416 375 4538 E --mail: cmdb.requests@aero.bombardier.com
From: Company: Phone: Extn: Facsimile: Date:

E --mail: The data that you provide below will help us record the incorporation of this ModSum and the aircraft effectivity in the maintenance manual. Operator: Service Bulletin:

__________________Revision:

_________ Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: 

## Fax this sheet to (1) 416 375 4538 or Email PDF to: 

# cmdb.requests@aero.bombardier.comFeb 2009 SERVICE BULLETIN (SB) --- COMMENT SHEET --- Q SERIES DASH 8 AIRCRAFT

To: SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538 E --mail: syed.rizvi@aero.bombardier.com
From: Company: Phone: Extn: Facsimile: Date:

E --mail: Select appropriate box(es) and add comments or suggestions you would like us to know that may enhance the quality of our service bulletins. Service Bulletin: Revision: ModSum: 1. PLANNING INFORMATION V Effectivity V Reason V Description V Compliance V Approval V Manpower V Material V Weight and Balance V Electrical Load V Tooling V References V Publications Affected 2. MATERIAL INFORMATION V Kit Content V Special Tools/Equipment V Parts to Modify Spares V Consumables V Disposition of Existing Parts V Other
3. ACCOMPLISHMENT INSTRUCTIONS V Job Set ---Up V Procedure V Close---Out V Test V Illustration(s) V Other 4. COMMENTS, REMARKS, SUGGESTIONS



## Fax this sheet to (1) 416 375 4538 or Email PDF to: syed.rizvi@aero.bombardier.com