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 Compliance section is revised to add the reference to AD CF ---2014 ---45

Part II

--- the References section is revised to convey the latest revision of the service

bulletin and engineering documentation

--- the ACCOMPLISHMENT INSTRUCTIONS section is revised to move the

Job Set ---Up instructions that are applicable only to the rework to

Procedure section Part ---B --- Rework

--- the Procedures section 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

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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 INFORMATION

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

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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

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--- 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

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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

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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
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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’
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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 INFORMATION

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

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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 PenetrantASTM ---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

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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
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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.
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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).
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(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.
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(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.
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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

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Retrofit --- Nacelle A ---Frame

Figure 1

AREA OF RETROFIT
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Retrofit --- Nacelle A ---Frame

Figure 2 (Sheet 1)

NOTE:All dimesions are in inches.

DETAILED VISUAL INSPECTION FOR DAMAGE
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Retrofit --- Nacelle A ---Frame

Figure 2 (Sheet 2)

NOTE: All dimesions are in inches.
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Retrofit --- Nacelle A ---Frame

Figure 2 (Sheet 3)

NOTE: All dimesions are in inches.

G

H
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Retrofit --- Nacelle A ---Frame

Figure 2 (Sheet 4)

NOTE: All dimesions are in inches.

DETAIL G

DETAIL H
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Retrofit --- Nacelle A ---Frame

Figure 2 (Sheet 5)

NOTE: All dimesions are in inches.
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Retrofit --- Nacelle A ---Frame

Figure 2 (Sheet 6)

NOTE: All dimesions are in inches.
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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.
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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
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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).
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Trimmed Nacelle A ---Frame

Figure 5

2 3 4

2 IF NECESSARY, REMOVE WIRING HARNESS TO GAIN ACCESS TO THE REWORK AREA.

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).
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This Page Intentionally Blank

1
Jan 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.com
Feb 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:

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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