# De Havilland Canada Service Bulletin 84-57-35

Copy: Revision B ("84-57-35B"), 18 pages: PDF https://openairdocs.org/files/sha256/e0/9e/e09ef59c97a36d84e2f0815aa1f576377cd10af18a3b8f8fcf4575780dcf8dee; text https://openairdocs.org/service-documents/bombardier/sb-84-57-35/file/e09ef59c97a3.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2021-0694; AD 2022-03-02 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: 84-57-35
- Latest revision known: 84-57-35, Revision B, dated June 9, 2021 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-57-35

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

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

- [AD 2022-03-02](https://openairdocs.org/ad/2022-03-02.md), effective Mar 17, 2022: Revisions A and B

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-57-35/proposed.md).

## Text (18 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2021-0694; AD 2022-03-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Revision ‘B’ 09 Jun 2021
T x L t r S B 8 4 --- 5 7 --- 3 5
P a g e1o f2
JV
DHC - - -8 (DASH 8)
SERVICE BULLETIN 84 - - -57 - - -35
Wings - - - Outer Wing - - - T op Skin Access Panel - - - Revision of Access Panel
No. 6 Flange - - - ModSum 4 - - -114015
This page transmits Revision ‘B’ of Service Bulletin 84- - -57- - -35, pages 1 thru 14
dated 09 Jun 2021.
This service bulletin is re- - -issued in its entirety for the reasons that follow:
--- t h eCompliance section is revised to include a text stating that Transport
Canada AD CF- - - 2021- - - 08 has been issued.
--- t h eReferences section is revised to convey the latest revision of the service
bulletin
--- t h eMATERIAL INFORMATION section revises NOTE 2
--- t h eExisting Parts Accountability section is revised to add a note.
--- t h eACCOMPLISHMENT INSTRUCTIONS section, Procedure B, revised
NOTE and steps to include all part numbers of access panel #6, P/N
85714233 (Dash number, NIEO and NCR)
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- - -57- - -35 and replace
with attached.
Previous issue(s) of Service Bulletin 84- - - 57- - - 35:
Initial issue - - - Pages 1 thru 14 dated 01 Oct 2020
Revision ’A’ - - - Pages 1 thru 14 dated 11 Feb 2021

### Page 2

SERVICE BULLETIN 84- - -57- - -35
Revision ‘B’ 09 Jun 2021 T x L t r S B 8 4 --- 5 7 --- 3 5
P a g e2o f2
JV
This Page Intentionally Blank

### Page 3

S . B . 8 4 --- 5 7 --- 3 5
Page 1 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
SERVICE BULLETIN
ATA SYSTEM: 5700 N U M B E R : 8 4 --- 5 7 --- 3 5
DE HAVILLAND AIRCRAFT OF CANADA LIMITED (DHC) CONSIDERS
URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS
THIS SERVICE BULLETIN TO BE PARTICULARL Y SIGNIFICANT AND
SUBJECT : Wings - - - Outer Wing - - - T op Skin Access Panel - - - Revision of Access
Panel No. 6 Flange - - - ModSum 4 - - -114015
1. PLANNING INFORMA TION
A. Effectivity
Aircraft Affected:
In- - -Service: DHC - - - 8 Aircraft Models 401 and 402 Serial Numbers 4001,
4003 thru 4628.
Production: ModSum 4- - - 114015 will be installed before delivery on
applicable DHC- - -8 Aircraft at Serial Number 4629 and
subsequent.
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.

### Page 4

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 2 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
Spares Affected:
The following is a list of spares affected by this change. Review spares and
procurement systems to determine the existence of any listed parts. See
Paragraph 2.D., Existing Parts Accountability , for disposition.
Part Number Description
85714233 Panel Assembly
B. Reason
Problem: It was reported by the operator that during pressure auto refueling, the LH
fuel tank refueling didn’t stop at selected refuel fuel quantity causing for the
LH fuel tank to be overfilled and fuel leak from the NACA scoops on airport
apron.
Solution: Extensive operator troubleshooting found that the root cause for the event
was no. 6 access panel assembly P/Ns (85714233- - - 005 and
85714233- - - 006) stiffener flange contact with the no. 2 High Level Sensor
(HLS) top terminal screw head that shortened the HLS signal to the
ground.
This service bulletin provides the necessary instructions to revise the
access panel no. 6 flange location to eliminate the potential interference
with HLS.
C. Description
The procedures in this service bulletin give the instructions to do the tasks that follow:
- - - 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
- - - Both the existing LH and RH no. 6 outer wing fuel access panel assembly are removed
- - - New LH and RH no. 6 outer wing fuel access panel assembly are installed to the outer
wing access panel installation (85714219- - - 001 and 85714219- - - 002) respectively - - -
as per PART A procedure
or

### Page 5

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 3 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
- - - The reworked LH and RH no. 6 outer wing fuel access panel assembly are installed
to the outer wing access panel installation (85714219- - - 001 and 85714219- - - 002)
respectively using the stiffener and rivets - - - as per PART B procedure
- - - Close out.
D. Compliance
De Havilland Aircraft of Canada Limited highly recommends that ModSum 4- - - 114015
be incorporated at the earliest opportunity unless otherwise directed by the operator’s
airworthiness authority.
Transport Canada Airworthiness Directive AD CF- - - 2021- - - 08 has been issued.
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
#19- - - Q - - - 01.
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage
T olerance Inspections (DTIs).
F . Manpower
P a r t A ---#6 Access Panel Replacement
It will take an estimated 10 man- - -hours to complete P A R TA of the
ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man
- - - hours required for the #6 access panel replacements is shown in the table that
follows:
TASK M A N --- H O U R S
J o b S e t --- U p 2.50
Procedure in Part A 2.00
T e s t/R T S 3.00
Close- - -Out 2.50

### Page 6

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 4 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
This estimate is for direct labour done by an experienced crew and it does not
include, planning, familiarization, cure time, part fabrication, tool acquisition or lost
time.
P a r t B ---#6 Access Panel Rework
It will take an estimated 13 man- - -hours to complete P A R TB of the
ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man
- - -hours required for the #6 access panel rework is shown in the table that follows:
TASK M A N --- H O U R S
J o b S e t --- U p 2.50
Procedure in Part B 5.00
T e s t/R T S 3.00
Close- - -Out 2.50
This estimate is for direct labour done by an experienced crew and it does not
include, planning, familiarization, cure time, part fabrication, tool acquisition or lost
time.
G. Material - - - Price and Availability
The ModKit required to do this service bulletin is listed in the table below.
Kit Number Description
8MK4864- - - 001 Retrofit Kit - - - Access Panel No. 6 - - - T op
Outer Wing
Operators should submit a purchase order through the Customer Response Center
(CRC) to the Customer Accounts Service T eam (CAST) at DHC specifying aircraft
serial number(s). Submit the purchase order to:
De Havilland Aircraft of Canada Limited
Material Services
123 Garratt Blvd.
T oronto
Ontario
Canada M3K- - -1Y5

### Page 7

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 5 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
DHC Phone Numbers :
North America:Toll Free: 1 (844) - - - CRC - - - CRC0 (1 (844) 272- - - 2720) or
Direct: 1 (514) 855- - - 8500
DHC Emails:
Parts: Europe, Middle East, Africa, and Russia: emear.parts@dehavilland.com
Americas and Rest of World: parts@dehavilland.com
H. T ooling - - - Price and Availability
None
I. Weight and Balance
Not affected
J. Electrical Load Data
Not affected
K. Publications Affected
Aircraft Illustrated Parts Catalog P S M 1 --- 8 4 --- 4......................
ModSums Manual P S M 1 --- 8 4 --- 1 2..................................
L. References
Revision ’B’ of this service bulletin was prepared to the engineering drawings and
related data that follows:
DRAWING Sheet REV
8MK4864 1 --- A
8Z10231 1 --- B
8Z10231 2 --- A
85714247 1 --- A

### Page 8

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 6 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
ModSum 4Q114015 Rev. ‘E’
ModSum 4- - - 114015 Rev. ‘E’
PCA 47537 Revision 1 (for internal reference only)
2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft
(1) Modification Kit 8MK4864- - - 001
(2) Detailed Kit Content:
Quantity Per Kit
- - -001
Part Number Description Remarks
30 B0205017AD5- - - 7SRivet, Solid, CSK See Note 1 below
2 85714247- - - 101 Stiffener See Note 1 below
1 85714233- - - 010 Panel Assy RH See Note 2 below
1 85714233- - - 009 Panel Assy LH See Note 2 below
REF 8Z10231 Retrofit Drawing only
NOTE 1: These items are not included in the kit and must be obtained through
spares from De Havilland Aircraft of Canada Limited. These items are
required for PART B of this service bulletin.
NOTE 2: These items are not included in the kit and must be obtained through
spares from De Havilland Aircraft of Canada Limited. These items are
required for PART A of this service bulletin.
Listed drawings that are required to complete the kit above can be requested by
writing to the following email address:
dwg.request@dehavilland.com

### Page 9

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 7 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
(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
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
06- - - 01A A/R Sealant, T empera-
ture Resistant, Inte-
gral Fuel T anks,
High Adhesion
DHMS S3.01/B2
Type II
06- - - 02 A/R Sealant, Corrosion
Inhibiting
DHMS S3.06 Type I
Class C- - -8 0
B. Parts Required to Modify Spares
Part Number Quantity
Per Unit
Description Remarks
85714247- - - 101 1 Stiffener See Note below
B0205017AD5- - - 7S 15 Rivet, Solid, CSK See Note below
NOTE: These items are required for PART B of this service bulletin.
C. Special T ools and Equipment Required
None

### Page 10

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 8 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
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
85714233- - - 003/- - - 005Panel Assembly LH 1 B SAL 85714233- - - 009 S
85714233- - - 003/- - - 005Panel Assembly LH 1 A RWK 8Z10231- - - 051 R
85714233- - - 004/- - - 006Panel Assembly RH 1 B SAL 85714233- - - 010 S
85714233- - - 004/- - - 006Panel Assembly RH 1 A RWK 8Z10231- - - 052 R
NOTE: Affected part numbers include all NIEO’s and NCR’s.
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 DHC 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.

### Page 11

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 9 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
3. ACCOMPLISHMENT INSTRUCTIONS
If it is not possible to complete all the instructions of this service bulletin because of the
configuration of the aircraft, speak with a representative of DHC in the CRC at 1 (844)
272- - - 2720 (1 (844) CRC - - - CRC0) or email at thd@dehavilland.comfor analysis and to get an
approved disposition to complete this service bulletin.
A . J o b S e t --- U p
WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE MAIN LANDING
GEAR. MAKE SURE YOU ENGAGE THE NOSE GEAR LOCK. IF YOU
DO NOT DO THIS, THE LANDING GEAR CAN ACCIDENTALL Y
RETRACT . THIS CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO THE EQUIPMENT .
WARNING: MAKE SURE YOU INSTALL THE LOCKPINS IN THE DOOR
MECHANISMS OF THE MLG AND NLG. THE DOOR MECHANISMS
CAN ACCIDENTALL Y CLOSE THE LANDING GEAR DOORS. THIS
CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE
EQUIPMENT .
(1) Placard and select all aircraft electrical power to OFF . Obey all relevant
WARNINGS and CAUTIONS (Refer to AMM TASK 24- - - 00- - - 00- - - 861- - - 802 and
TASK 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.

### Page 12

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 10 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
B. Procedure
NOTE: This modification kit reworks outer wing fuel access panel assembly #6,
part number 85714233- - - 005/- - - 006, in installation 85714219- - - 001/- - - 002.
The retrofit applies to the current production configuration part number
85714233- - - 005/- - - 006 and all other part numbers (Dash number, NIEO,
NCR) installed in lieu of the current production part numbers.
Operators have a choice to either remove the existing access panel and
replace it with a new revised panel - - - P A R TA or rework the existing
a c c e s s p a n e l ---P A R TB.
Part A - - - #6 Access Panel Replacement
(1) Remove and retain hardware LH and RH no. 6 outer wing fuel access panels
524FT and 624FT P/Ns (85714233- - - 003/- - - 005 and 85714233- - - 004/- - - 006 and all
other affected part numbers) from the outer wing respectively. (Refer to the
Figure 1 (Sheet 2) and the AMM TASK 57- - - 21- - - 01- - - 000- - - 801).
(2) Install new LH and RH no. 6 outer wing fuel access panel assembly P/Ns
(85714233- - - 009 and 85714233- - - 010) to the outer wing access panel
respectively with retained hardware (Refer to the Figure 1 (Sheet 1) and the
AMM TASK 57- - - 21- - - 01- - - 400- - - 801).
Part B - - - #6 Access Panel Rework
(1) Remove and retain hardware LH and RH no. 6 outer wing fuel access panels
524FT and 624FT P/Ns (85714233- - - 003/- - - 005 and 85714233- - - 004/- - - 006 and all
other affected part numbers installed in lieu of the current production part
numbers) from the outer wing respectively (Refer to Figure 1 (Sheet 2) and the
AMM TASK 57- - - 21- - - 01- - - 000- - - 801).
(2) Remove the flange adjacent to the gravity refueling adapter as shown in the
section view B- - - B and the detail C (Refer to the Figure 1 (Sheet 3)). Deburr the
sharp edges after removing the flange. Inspect the rework area for crack
indications using Eddy Current (preferred method) (Refer to Part 6 of the NDT
manual, TASK 51- - - 00- - - 01- - - 250- - - 801) or Fluorescent Liquid Penetrant (Refer to
Part 8 of the NDT manual, TASK 51- - - 00- - - 01- - - 230- - - 801). No crack indications
are permitted.
(3) Finish the rework area with C1 Alodine (Refer to SRM 51- - - 21- - - 10- - - 02- - - 01) and
F21 coating (Refer to SRM 51- - - 25- - - 40- - - 02- - - 01).
(4) Install stiffener P/N 85714247- - - 101 as shown in the section view D- - - D (Refer to
the Figure 1 (Sheet 3)).
(a) If required, remove the sealant from the existing rivets to achieve the
stiffener location as shown in the section view D- - -D.
(5) If required, install shim between access panel assembly and the stiffener P/N
85714247- - - 101 (Refer to AMM TASK 20- - - 10- - - 28- - - 420- - - 801).

### Page 13

SERVICE BULLETIN 84- - -57- - -35
S . B . 8 4 --- 5 7 --- 3 5
Page 11 of 14
01 Oct 2020
JVRevision ‘B’ 09 Jun 2021
(6) Fay seal the interfacing surfaces of the access panel assembly and stiffener P/N
85714247- - - 101 and shim if required using sealant (06- - - 02) (Refer to AMM TASK
51- - - 23- - - 00- - - 390- - - 801).
(7) Install rivets P/N B0205017AD5- - - 7S to the stiffener P/N 85714247- - - 101 (Refer to
S R M 5 1 --- 4 2 --- 0 5 --- 0 2 --- 0 1 ) .
(8) Re- - -apply sealant (06- - -01A) on the rivets (Refer to AMM TASK
51- - - 23- - - 00- - - 390- - - 801) after the stiffener P/N 85714247- - - 101 installation and to
rivets that had sealant previously removed.
(9) If required, fill voids between the access panel assembly and stiffener P/N
85714247- - - 101 using sealant (06- - - 01A) (Refer to Figure 1 (Sheet 3) and the
AMM TASK 51- - - 23- - - 00- - - 390- - - 801).
(10) Fillet seal around the stiffener P/N 85714247- - - 101 using sealant (06- - - 01A) (Refer
to Figure 1 (Sheet 3 of 3) and AMM TASK 51- - - 23- - - 00- - - 390- - - 801).
(11) Re- - - identify reworked LH panel assembly P/N 85714233- - - 003/- - - 005 and all
other affected LH part numbers as 8Z10231- - - 051 and RH panel assembly P/N
85714233- - - 004/- - - 006 and all other affected RH part numbers as 8Z10231- - - 052
respectively (Refer to AMM TASK 20- - - 00- - - 01- - - 910- - - 802).
NOTE: Reworked access panel assembly P/Ns 8Z10231- - - 051/- - - 052 are
one- - -way interchangeable with the access panel assembly P/Ns
85714233- - - 003/- - - 004, 85714233- - - 005/- - - 006 and all other affected
NIEO and RNC part numbers and are two- - -way interchangeable with
the access panel assembly P/Ns 85714233- - - 009/- - - 010 respectively.
(12) Install reworked LH and RH no. 6 outer wing fuel access panel assembly P/Ns
(8Z10231- - - 051 and 8Z10231- - - 052) to the outer wing access panel with existing
hardware (Refer to Figure 1 (Sheet 2) and the AMM TASK
57- - - 21- - - 01- - - 400- - - 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). If only part of this ModSum is
completed, use only this service bulletin number as reference and detail exact
limit of work completed. Enter component serial numbers if applicable. Enter this
ModSum number only after complete and functional incorporation of all work
defined in this service bulletin.

### Page 14 (OCR)

SERVICE BULLETIN 84-57-35
>
Y-389.019
Y-407.019
Y-425.019
(85714233-009/-010)
PANEL ASSEMBLY LH/RH
ACCESS PANEL NO.6)
OUTBD
(85714219-001/-002)
8Z10231-001 INSTALATION - PART A  cg5851a01.dg. ss. oct10/2019
LH SHOWN, RH OPPOSITE
01 Oct 2020  S.B. 84-57-35
Page 12 of 14
Revision 'B' 09 Jun 2021  JV

### Page 15 (OCR)

SERVICE BULLETIN 84-57-35
Y-425.019  Y-389.019
-(STGR 4)
B)4
(STGR 6)  OUTBD
85714233-005/-006
and all other affected
NIEO and RNC part
PANEL ASSEMBLY LH/RH
LH SHOWN, RH OPPOSITE
(VIEW PRIOR TO REWORK)
Y-389.019
Y-425.019  Y-407.019  (B0205017AD5-7S)
RIVET (QTY 15)
(8Z10231-051/-052)
PANEL ASSEMBLY LH/RH
ACCESS PANEL NO.6)
(85714219-001/-002)
8Z10231-003 INSTALATION - PART B  OUTBD
LH SHOWN, RH OPPOSITE  (AFTER REWORK)  cg5851a02.dg, ss, oct10/2019
NOTE
Dome seal rivets P/N (B0205017AD5-7S) on inside of
panel assembly using sealant (06-01A).
01 Oct 2020  S.B. 84-57-35
Page 13 of 14
Revision 'B' 09 Jun 2021  JV

### Page 16 (OCR)

SERVICE BULLETIN 84-57-35
B-B
(85/14233-003/-004/-005/-006)
PANEL ASSÉMBLY LH/RH
REMOVE
FLANGE
(8Z10231-051/-052)
PANEL ASSEMBLY LH/RH
SOR
POL
(85714247-101)
STIFFENER
O-0
0.69 INCH
NOTES
2 If required fill voids between access panel and stiffener  P/N (85714247-101) using sealant (06-01A).  cg5851a03.dg, ss, oct14/2019
/3) Fillet seal around stiffener P/N (85714247-101)
using sealant (06-01A).
01 Oct 2020  S.B. 84-57-35
Page 14 of 14
Revision 'B' 09 Jun 2021  JV

### Page 17

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 18

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

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.