# De Havilland Canada Service Bulletin 84-55-05

Copy: Revision C ("84-55-05 Rev C"), 26 pages: PDF https://openairdocs.org/files/sha256/95/22/9522e32f25f6f5f1c05c78f1df3fbd1628164a61b6223710d193772456d07ce9; text https://openairdocs.org/service-documents/bombardier/sb-84-55-05/file/9522e32f25f6.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2022-1403; AD 2023-07-06 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md) (issued as De Havilland Canada)
- Type: Service bulletin (Service Bulletin)
- Number: 84-55-05
- Latest revision known: 84-55-05, Revision C, dated August 19, 2021 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-55-05

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2023-07-06](https://openairdocs.org/ad/2023-07-06.md), effective Jun 20, 2023: Revisions A, B and C

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-55-05/proposed.md).

## Text (26 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2022-1403; AD 2023-07-06 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

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Revision ‘C’ 19 Aug 2021
T x L t r S B 8 4 --- 5 5 --- 0 5
P a g e1o f2
AA
DHC - - -8 (DASH 8)
SERVICE BULLETIN 84 - - -55 - - -05
Horizontal Stabilizer - - - Lower Skin Center Section - - - Special Inspection For
Corrosion, Rectification And Addition of Enhanced Corrosion Protection - - -
ModSum 4 - - -113903
This page transmits Revision ‘C’ of Service Bulletin 84- - - 55- - - 05, pages 1 thru 22
dated 19 Aug 2021.
This service bulletin is re- - -issued in its entirety for the reasons that follow:
--- t h eReferences section is revised to convey the latest revision of the service
bulletin
-- Figure 3, Figure 4 and Figure 5 are revised according to the latest modsum
revision.
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- - -55- - -05 and replace
with attached.
Previous issue(s) of Service Bulletin 84- - - 55- - - 05:
Initial issue - - - Pages 1 thru 20 dated 12 Jan 2016
Revision ’A’ - - - Pages 1 thru 20 dated 03 Jun 2016
Revision ’B’ - - - Pages 1 thru 22 dated 26 Feb 2021

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SERVICE BULLETIN 84- - -55- - -05
Revision ‘C’ 19 Aug 2021 T x L t r S B 8 4 --- 5 5 --- 0 5
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AA
This Page Intentionally Blank

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SERVICE BULLETIN
ATA SYSTEM: 5510 NUMBER: 84- - -55- - -05
SUBJECT : Horizontal Stabilizer - - - Lower Skin Center Section - - - Special Inspection
For Corrosion, Rectification An d Addition of Enhanced Corrosion
Protection - - - ModSum 4- - - 113903
1. PLANNING INFORMA TION
A. Effectivity
Aircraft Affected:
In- - -Service: DHC- - -8 Aircraft Models 401 and 402 Serial Numbers 4001 thru
4549.
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 DHC 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

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B. Reason
Problem: An operator of a DHC- - -8- - -400 aircraft has reported finding advanced
corrosion on the inside surface of the horizontal tail’s lower center skin
panel during a zonal inspection in accordance with task card
000- - -05- - -900- - -306.
Subsequent inspection has determined that the same type of corrosion
exists on a few other aircraft on the same skin. Structural degradation and
loss of strength may occur if the corrosion is left untreated.
Cause: Investigation into this corrosion issue has determined that the primer
applied to the inside surface of the lower skin (machined 2024- - -T3
aluminum) during the manufacturing process may not provide all of the
corrosion protection required and that application of additional protection
is necessary.
Solution: The horizontal stabilizer is inspected for corrosion and repaired if
necessary. The skin is treated with alodine, epoxy primer and an additional
layer of polyurethane enamel paint and a layer of F13 moisture
displacement compound.
C. Description
The procedures in the ACCOMPLISHMENT INSTRUCTIONS in this service bulletin
give the instructions to do the tasks that follow:
--- p a r aA . J o b S e t --- U pincludes removal of all aircraft electrical power, make sure that
the nose landing gear lock is engaged and the main landing gear lock pins are
installed thru each main gear and main gear door mechanism
- - - also the vertical stabilizer fairing and the horizontal stabilizer are removed from the
aircraft tail section

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--- p a r aB. Procedure section Part A gives the instructions to do a general visual
inspection of the horizontal stabilizer ins ide surface of the lower center skin looking
for corrosion
- - - if corrosion is found the technician is directed to Part B in the Procedure section of
this service bulletin
- - - if no corrosion is found the entire inside skin surface is solvent cleaned to remove the
existing moisture displacement compound then it’s treated with alodine, epoxy
primer, grey polyurethane enamel and a moisture displacement compound
- - - the area around each round access hole in the upper skin is solvent cleaned
- - - pressure sensitive tape is applied to cover each round access hole in the upper skin
to prevent moisture ingress
- - - upon completion of the instructions inPart A ---Inspection the technician is directed
to the Close Out section of this service bulletin
--- p a r aB. Procedure section Part B gives the instructions to solvent clean the entire
inside skin surface to remove the existing moisture displacement compound, remove
all corrosion and repair the damaged skin as required, in addition the entire inside skin
is then treated with alodine, epoxy primer, grey polyurethane enamel and a moisture
displacement compound
- - - the area around each round access hole in the upper skin is solvent cleaned
- - - pressure sensitive tape is applied to cover each round access hole in the upper skin
to prevent moisture ingress
- - - upon completion of the instructions inPart B ---Corrosion Removal and Repair the
technician is directed to the Close Out section of the service bulletin
--- p a r aC. CloseOut section gives the instructions to apply a new part number
”8DK4299- - -001” adjacent to either oval access hole in the lower skin, install the
vertical stabilizer fairing and the horizontal stabilizer per existing AMM instructions and
remove all tools and equipment from the work area

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- - - the enclosed “Response Form” located at the end of this service bulletin if filled out
and returned to the Q Series T echnical Help Desk at: thd@dehavilland.com
- - - log book entries are made.
D. Compliance
For aircraft with findings during zonal inspection in accordance with task card
000- - -05- - -900- - -306, DHC highly recommends accomplishment of this service bulletin
(84- - -55- - -05 ModSum 4Q113903). Corrosion if found must be addressed by a repair
drawing (RD) or this SB (if within rework limits) prior to return to service.
A Transport Canada Airworthiness Directive Pending.
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
# 9 3 --- Q --- 0 2 .
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage
T olerance Inspections (DTIs).
F. M a n p o w e r
It will take an estimated 108 man- - -hours to complete this service bulletin. The
breakdown of the man- - -hours is shown in the table that follows:
TASK M A N --- H O U R S
J o b S e t --- U p 38.00
Procedure 8.00
(See NOTE Below)
T e s t/R T S 15.00
Close- - -Out 47.00

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NOTE : A minimum of 8 hours is required if no evidence of corrosion is found
during the inspection. MAN- - -HOURS to accomplish corrective action
a r en o ti n c l u d ei nt h i se s t i m a t e .
This estimate is for direct labour done by an experienced crew and it does not
include, planning, familiarization, cure tim e, part fabrication, tool acquisition or lost
time.
G. Material - - - Price and Availability
Kit Number Description
8DK4299 Drawing Kit - - - Corrosion Protection,
Lower Skin, Center Section,
H/Stabilizer
Drawing Kit(s) (DKs) listed in the table above are drawings only. No parts will be
supplied.
The part(s) and material(s) required are listed in Paragraph 2.A. The parts required
may be either furnished or fabricated from the operator’s existing stock, purchased as
single items from DHC 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 equivalen t to the DK part may be available from DHC
under the production part number shown as reference in Parts Required Per Aircraft.
This service bulletin is fully illustrated. Procurement of the 8DK drawing is not
necessary. If required the related 8DK drawings listed in the T able above can be
requested by writing to the e- - -mail address that follows:
dwg.request@dehavilland.com
Follow the instructions per All Operator Message (AOM) 389 (DHC- - -8- - -400).

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H. T ooling - - - Price and Availability
None
I. Weight and Balance
Not affected
J. Electrical Load Data
Not affected
K. Publications Affected
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
8DK4299 1 D
ModSum 4Q113903 Rev. K
ModSum 4- - -113903 Rev. K
Related ModSum 4Q114029
Related ModSum 4D180048
Related ModSum 4D180061
PCA 45486 Rev 1 (for internal reference only)

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2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft
(1) Drawing Kit 8DK4299- - -001:
(2) Detailed Kit Content:
Quantity Per Kit
--- 0 0 1
Part Number Description Remarks
1 8DK4299 Retrofit Drawing Only DWG
NOTE: This service bulletin is self- - -contained (illustrated). No drawings will be
supplied.
Listed drawings that are required to complete the kits above can be requested by
writing to the following e- - -mail address:
dwg.request@dehavilland.com
(3) Detailed Parts List:
Quantity
Per Aircraft
Part Number Description Remarks
A/R HST1087TF- - -6 Collar 3/16
A/R HST1087TF- - -5 Collar 5/32
A/R H S T 1 2 A G --- 6 --- 5Bolt, Hi- - -Lite 3/16
A/R H S T 1 2 A G --- 6 --- 4Bolt, Hi- - -Lite 3/16
A/R H S T 1 2 A G --- 5 --- 5Bolt, Hi- - -Lite 5/32
A/R H S T 1 2 A G --- 5 --- 4Bolt, Hi- - -Lite 5/32

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(4) 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
DHC or purchased directly from industry sources.
Each consumable product listed in the table below is given its own unique
Product ID Number. The number is used to identify a particular recommended
product, the specifications and the trade names any of which can be used
unless specified otherwise (refer to PSM 1- - -84- - -18 Consumable Products
Manual).
Consumable
Product ID
Number
Qty. Per Aircraft Description Remarks
05 - - - 23 Adhesive, Epoxy Fastweld #10
06 - - - 02 Sealant, D H M S S 3 . 0 6 C --- 8 0
07- - -01 2l i t e r Compound, corro-
sion preventive,
Grade 3
(F13)
07- - -02 2l i t e r Primer, Fluid- - -Re-
sistant, Chromate
Epoxy
DHMS C4.01 T ype 2
07- - -29A 500 milliliters Chemical Conver-
sion Coating
(Manual Applica-
tion)
MIL- - -C- - -5541
Revision E
(Alodine)
14- - -18 T ape, Pressure
Sensitive
BAMS 535- - -004
(E&H 70- - -1C)

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(5) The parts/consumables listed in the table that follows are not shown in the
Consumable Products Manual and must be procured by the operator as single
items from DHC or purchased directly from industry sources.
Parts Qty. Per Aircraft Description Remarks
--- --- 2l i t e r Polyurethane
Enamel
MIL- - -C- - -83286
(Gray)
B. Parts Required to Modify Spares
None
C. Special T ools and Equipment Required
None
D. Existing Parts Accountability
None
3. ACCOMPLISHMENT INSTRUCTIONS
A . J o b S e t --- U p
(1) Placard and select all aircraft electrical power to OFF . Obey all relevant
W A R N I N G S a n d C A U T I O N S ( r e f e r t o A M M T A S K ’ s 2 4 --- 0 0 --- 0 0 --- 8 6 1 --- 8 0 2 a n d
24- - -00- - -00- - -910- - -801).
(2) Make sure that lock pins are installed through each main gear and main gear
door mechanism.
(3) Make sure the nose gear ground lock is engaged.
(4) Set wheel chocks in front and behind the landing gear tires.

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(5) Remove the vertical stabilizer fairing and the horizontal stabilizer from the aircraft
tail section (refer to applicable instructions in PSM 1- - -84- - -2 AMM TASK
55- - -10- - -00- - -000- - -801).
B. Procedure
Part A - - - Inspection
(1) Do a general visual inspection of the horizontal stabilizer inside surface of the
lower center skin looking for corrosion. Access for the inspection is gained
through the two oval access holes in the lower skin (refer to drawing (dwg)
Figure 2 & 3). Make sure to use adequate lighting when doing the inspection.
(2) If no evidence of corrosion is found during the inspection continue with the next
step. If corrosion is found continue with Part B - - - Corrosion Removal and
Repair step (1) and subsequent.
(3) Solvent clean then apply a layer of alodine (07- - -29A), epoxy primer (07- - -02),
grey polyurethane enamel (MIL- - -C- - -83286) and a moisture displacement
compound (07- - -01) to the inside surface of the lower center skin (refer to Figure
1 Sheet 1 flagnotes 9 , 10, 11 , 12 and Figure 4 and 5).
(4) Solvent clean the entire area around each round access hole in the upper skin
(refer to Figure 6 flagnote 21 ). Wipe dry the affected area with a clean dry
cloth.
(5) Apply pressure sensitive tape (consumable item 14- - -18) to cover each round
access hole in the skin.
(6) Refer to the Close Out s e c t i o ns t e p( 1 )a n ds u b s e q u e n t .

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Part B - - - Corrosion Removal and Repair
(1) If corrosion is found on the horizontal stabilizer inside surface of the lower center
skin refer to Figure 1 Sheet 2 and accomplish flagnote 13 through 20.
(2) Solvent clean the area around each round access hole in the upper skin (refer to
Figure 4). Wipe dry the affected area with a clean dry cloth.
(3) Apply pressure sensitive tape (consumable item 14- - -18) to cover each upper
round hole in the upper skin.
(4) Refer to the Close Out s e c t i o ns t e p( 1 )a n ds u b s e q u e n t .
C. Close Out
(1) After the re- - -work described in Part A and/or Part B above is complete apply
new part number ”8DK4299- - -001” adjacent to either oval access hole (on the
outside surface) using a black indelible ink marker (refer to Figure 3 flagnote
22 ).
(2) Install the vertical stabilizer fairing and t he horizontal stabilizer (refer to applicable
instructions in AMM TASK 55- - -10- - -00- - -400- - -801).
(3) Remove all tools and equipment from the work area.
(4) On incorporation of this Service Bulle tin and/or ModSum, make sure to fill in the
a t t a c h e df o r ma n de m a i lr e s u l t st ot h eQS e r i e sT e c h n i c a lH e l pD e s ka t :
thd@dehavilland.com

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(5) On incorporation of this Service Bulletin make an entry that conforms to local
regulatory requirements in the applicable logbook(s). If only part of this Service
Bulletin is completed use only this service bulletin number as reference and
detail exact limit of work completed. Enter the ModSum number only after
complete and functional incorporation of a ll work defined in this service bulletin.

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Notes
Figure 1 Sheet 1
F i g u r e 4 v i e w A --- A F i g u r e 5 v i e w B --- B

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Notes
Figure 1 Sheet 2
(ref Figure 5).

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Notes
Figure 1 Sheet 3
HOLES IN UPPER SKIN.
NOTE: ACCESS HOLES IN LOWER SKIN ARE LEFT UNCOVERED.
TO COVER THE ACCESS
OR CORROSION THAT HAS MIGRATED UNDER SPAR CAPS AND RIBS.
STATED IN DETAIL C (Ref Fig 5),
THE DEHAVILLAND AIRCRAFT OF CANADA HELP DESK FOR
NOT REFLECTED ON DRAWING ORCORROSION CONDITIONS

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Locator View
Figure 2
(See Figure 6)

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Lower Skin Details
Figure 3
S e eF i g u r e4
S e eF i g u r e5

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Section A- - - A
Figure 4

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Section B - - - B
Figure 5
LOWER SKIN

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View on Arrow D
Figure 6

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Response Form For:
Service Bulletin 84- - - 55- - - 05 / ModSum 4- - - 113903
Horizontal Stabilizer - - - Lower Skin Center Section - - - Special Inspection For Corrosion,
Rectification And Addition of Corrosion Protection.
Aircraft
Serial
Number
Date of SB
Incorpora-
tion
Airframe
Hours
Airframe
Cycles
Corrosion
Found
(yes/no)
Corrosion
in excess
of SB al-
lowance
(yes/no)
Corrosion
to ribs and
stiffeners
(yes/no)
Airline Name:__________________________________________________________________________
Maintenance facility:____________________________________________________________________
1

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This Page Intentionally Blank
2

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Oct 2019
SERVICE BULLETIN (SB) - - - RECORD OF INCORPORATION
DASH 8 AIRCRAFT
To : CMDB Focal
Email: cmdb.request@dehavilland.com
From:
Company:
Phone: Extn:
Facsimile: Date:
Email:
The data that you provide below will help us record the incorporation of this Service
Bulletin 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:
Email PDF to:
cmdb.request@dehavilland.com

### Page 26

Oct 2019
SERVICE BULLETIN (SB) - - - COMMENT SHEET - - - DASH 8 AIRCRAFT
To : SB Focal, DE HAVILLAND AIRCRAFT OF CANADA LIMITED
Phone: 1 (416) 373 - - -5098
Email: george.moffatt@dehavilland.com
From:
Company:
Phone: Extn:
Facsimile: Date:
Email:
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 T ooling V References V Publications Affected
2. MATERIAL INFORMATION
V Kit Content V Special T ools/Equipment V Parts to Modify Spares
V Consumables V Disposition of Existing Parts V Other
3. ACCOMPLISHMENT INSTRUCTIONS
V J o b S e t --- U p V Procedure V Close- - -Out V Te s t
V Illustration(s) V Other
4. COMMENTS, REMARKS, SUGGESTIONS
Email PDF to:
george.moffatt@dehavilland.com

---
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