Revision ‘A’ 06 Aug 2012

DHC-8 (DASH 8)

SERVICE BULLETIN 84-57-24

Wings - Center Section -Special Inspection - Heat Shield & D Nose -

Relocation of Anchor Nut on Outboard Heat Shield to Avoid Harness

Fouling on Leading Edge Rib - ModSum 4-110440

This page transmits Revision ‘A’ of Service Bulletin 84-57-24, pages 1 thru

14 dated 06 Aug 2012.

This service bulletin is re-issued in its entirety for the reasons that follow:

- the format of this service bulletin is updated to the latest standard. Revision

bars are not applied to any format changes. Revision bars are applied only

beside subject matter to identify technical changes or new information

- added EMPHASIS statement before SUBJECT

- the Compliance section is revised with new statement. Added AD number

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

bulletin and engineering documentation

- revised part of step 3.B.(1) the ACCOMPLISHMENT INSTRUCTIONS

section from ‘visually inspect’ to ‘do a detailed inspection of’

- revised part of step 3.B.(8) the ACCOMPLISHMENT INSTRUCTIONS

section from ‘and Figure 3 or Figure 4’ to ‘and Figure 4 or Figure 5’.

The Compliance in the previous issues of this service bulletin is not affected

by this revision. No additional rework to the aircraft is introduced by this

revision.

Remove Service Bulletin 84-57-24 Initial Issue and replace with attached.

Previous issues of Service Bulletin 84-57-24:

Initial issue - Pages 1 thru 14 dated 30 Sep 2011
Revision ‘A’ 06 Aug 2012
D

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 5700 NUMBER: 84-57-24

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT Wings - Center Section -Special Inspection - Heat Shield & D Nose -

Relocation of Anchor Nut on Outboard Heat Shield to Avoid Harness

Fouling on Leading Edge Rib - ModSum 4-110440

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4001,

4003 thru 4382.

Verification: ModSum 4-110440 has been incorporated on DHC-8 Aircraft

Model 402 Serial Number 4249 per Post Verification Service

Bulletin 84-57-24.

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: Operator’s have reported wire chafing damage at the inboard end rib of the

landing light assembly on both left hand and right hand sides.
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Cause: A potential fouling condition exists between a wire harness and the inboard

end rib of the landing light assembly on both the left hand and right hand

sides. This harness includes wires for the flare and approach lights, the

position lights and the dual distributing valves.

Solution: Do an inspection of the affected wire harness and repair the harness if

chafing exists. In addition, relocate and install a new anchor nut to

eliminate the fouling condition between the wiring harness and the leading

edge rib.

NOTE: Relocation and installation of new anchor nut to be completed on both

the left and right hand sides, even if there are no signs of chafing.

C. Description

The procedures in this service bulletin give the instructions to do the tasks that

follow:

- aircraft is put into standard configuration for maintenance

- aircraft electrical power is removed

- the nose landing gear lock is engaged

- the main landing gear lock pins are installed thru each main gear and main gear

door mechanism

- the left and right hand nacelle forward fairing assemblies and landing light

leading edge assemblies are removed

- the wiring harness on the left or right hand side is visually inspected for chafing.

The harness is repaired if damage is found

- abrasion protection is installed to the harness

- if installed, the existing plastic grommet is removed and discarded

- the anchor nut is removed and replaced with a new one relocated down by one

fastener pitch on the leading edge rib

- the wiring harness is installed to the anchor nut with the existing clamps, washer

and a new screw and spacer

- a new grommet is installed to the hole

- the rework is done on the opposite side

- the nacelle forward fairing assemblies and the landing light leading edge

assemblies are installed
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- an operational test of the landing lights is done

- close out.

D. Compliance

Bombardier Inc. highly recommend that ModSum 4-110440 be incorporated at the

earliest opportunity unless otherwise directed by the operator’s airworthiness

authority.

Transport Canada Airworthiness Directive CF-2012-05.

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.

This Service Bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance Inspections (DTIs).

F. Manpower

It will take an estimated 8.50 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 3.00

Inspection/Procedure 2.00

Test / RTS 0.50

Close-Out 3.00

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 part(s) and material(s) detailed in Paragraph(s) 2.A. and 2.B. 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.

H. Tooling - Price and Availability

None
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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 ‘A’ of this service bulletin was prepared to the engineering drawings and

related data that follows:

DRAWING SHEET REV

8DK4179 1 A

8Z9340 1 A

ModSum 4Q110440 Rev. ‘B’

ModSum 4-110440 Rev. ‘B’

PCA 43644 Revision 3 (for internal reference only)

Transport Canada Airworthiness Directive CF-2012-05.

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Detailed Parts List:

Quantity

Per Aircraft

Part Number Description Remarks

2 NAS1801-3-24 Screw (full thread)

2 NAS43DD3-64FC Spacer
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Quantity

Per Aircraft

Part Number Description Remarks

6 B0205016AD4-4S Rivet see NOTE: 1

2 B0204033-3-4 Anchor Nut see NOTE: 2

2 MS21266-1N Grommet

NOTE 1: B0205016AD4-4S is equivalent to MS20470AD4-4S.

NOTE 2: B0204033-3-4 is equivalent to T8059S1032B-1CPC (Textron Cherry) or

52LHA71-4-02 (SPS Technologies) or T8059S1032B-1CPC (Republic

Fasteners).

(2) In addition to the above parts, the following materials 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 Number Qty. Per Aircraft Description

DHMS C4.01 as required Epoxy Primer, Type 2 F19

MIL-C-5541 as required Chemical Conversion Coating, C1

DHMS A6.09 Epoxy Adhesive

9 oz or

- Adhesive, Fastweld #10

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None
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D. Existing Parts Accountability

None

3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set-Up

(1) Placard and select all aircraft electrical power to OFF. Refer to AMM TASK

24-00-00-861-802, TASK 24-00-00-910-801 and obey all relevant WARNINGS

and CAUTIONS.

(2) Make sure that lock pins are installed thru each main gear and main gear door

mechanism.

(3) Make sure the nose gear ground lock is engaged.

(4) Refer to Figure 1 and set up work platforms or ladders as required to gain

access to the wing leading edges at the nacelles. Make sure the work platforms

or ladders are electrically grounded.

(5) Refer to Figure 2 and the applicable steps in AMM TASK 57-23-01-000-801 and

remove and keep left and right hand side landing light leading edge assemblies

85720301 (512AL-left hand side and 612AR-right hand side).

(6) Refer to Figure 3 and AMM TASK 54-12-01-000-801 and remove and keep

nacelle forward fairing assemblies 87144008 (412CT-left hand side and

422CT-right hand side).

B. Procedure

(1) Refer to Figure 6 and do a detailed inspection of the wire harness at left or right

hand anchor nut location for chafing damage. If damaged, repair the wiring

harness per Wiring Diagram Manual Chapter 20-16-10 and Chapter 20-16-20.

(2) Add abrasion protection to the harness if required in accordance with Wiring

Diagram Manual 20-12-10-201-Wiring Maintenance Practices-Section 10,

Installation of Edging Grommet and Spiral Wrap.

(3) If installed, remove and discard existing plastic grommet.

(4) Refer to Figure 4 (left hand side) or Figure 5 (right hand side) and remove and

keep existing clamps DSC184-9 and MS21919WDG6. Discard spacer and

screw, keep washer.

(5) Remove and discard existing anchor nut.

(6) Refer to SRM TASK 51-42-05-00-01, Figure 4 or Figure 5 and plug top rivet hole

using one rivet B0205016AD4-4S.
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(7) Refer to SRM TASK 51-42-05-00-01, Figure 4 or Figure 5 and install new anchor

nut B0204033-3-4 at location shown using two rivets B0205016AD4-4S.

(8) Refer to SRM TASK 51-22-45-02-01 or TASK 51-22-35-02-01, AMM TASK

20-00-33-400-801 and Figure 4 or Figure 5 and install new grommet

MS21266-1N as shown with DHMS A6.09 epoxy adhesive or Fastweld #10

adhesive.

(9) Install wiring harness with removed clamps DSC184-9 and MS21919WDG6 to

new anchor nut using kept washer NAS1149D0316H, new spacer

NAS43DD3-64FC and new screw NAS1801-3-24. Torque screw to 20 - 25 inch

pounds.

(10) Re-finish any scuffed surface on the leading edge rib with C1 alodine & F19

epoxy primer.

(11) Temporarily install landing light leading edge assembly 85720301 with four

screws. Do a visual inspection of the relocated harness support area for any

fouling condition.

(12) Remove landing light leading edge assembly 85720301.

(13) Repeat steps B.(1) thru B.(12) for the opposite side.

C. Close Out

(1) Refer to AMM TASK 54-12-01-400-801 and install nacelle forward fairing

assemblies 87144008 (412CT-left hand side and 422CT-right hand side).

(2) Refer to applicable steps in AMM TASK 57-23-01-400-801 and install landing

light leading edge assemblies 85720301 (512AL-left hand side and 612AR-right

hand side).

(3) Refer to the steps in section 5. A., B., C., D. of AMM TASK 33-41-01-400-801 and

do an operational test of the landing lights.

(4) Remove all tools and equipment from the work area.

(5) 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.
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Location of Rework

Figure 1
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Removal / Installation of Landing Light Leading Edge

Figure 2

LEGEND

1. BOLT

2. SILICONE SEAL

3. LEADING EDGE

1

2

3

1

512AL-LEFT HAND SIDE

612AR-RIGHT HAND SIDE
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Removal / Installation of Leading Edge Fairing - Forward Nacelle

Figure 3

412CT-LEFT HAND SIDE

422CT-RIGHT HAND SIDE
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Looking Inboard on Leading Edge Rib - LH Side

Figure 4

SCREW

NAS1801-3-24

SPACER

NAS43DD3-64FC

RIVET

B0205016AD4-4S

PLASTIC GROMMET

MS21266-1N

ADHESIVE

FASTWELD #10

OR

EPOXY DHMS A6.09

ANCHOR NUT

B0204033-3-4

RIVET

B0205016AD4-4S

CLAMP

(DSC184-9

OR DSC184-10)

MAKE SURE CLAMP

DOES NOT CONTACT

PLASTIC GROMMET

CLAMP

(MS21919WDG6)

RIVET EDGE DISTANCE MIN. FROM CUT OUT EDGE
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Looking Inboard on Leading Edge Rib - RH Side

Figure 5

SCREW

NAS1801-3-24

SPACER RIVET NAS43DD3-64FC B0205016AD4-4S

ANCHOR NUT

B0204033-3-4

RIVET

B0205016AD4-4S

PLASTIC GROMMET

MS21266-1N

ADHESIVE

FASTWELD #10

OR

EPOXY DHMS A6.09

CLAMP

(MS21919WDG6)

RIVET EDGE DISTANCE

FROM CUT OUT EDGE

MIN.

CLAMP

(DSC184-9

OR DSC184-10)

MAKE SURE CLAMP

DOES NOT CONTACT

PLASTIC GROMMET
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Fouling Condition On Leading Edge Rib - Pre Mod Illustration

Figure 6

INBOARD
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2
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:

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