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Revision ‘B’ 17 Feb 2017 D H C --- 8 ( D A S H 8 ) S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 Equipment and Furnishings - - - Flight Compartment - - - Instrument Panel
- - - Pilot and Copilot Side - - - Wiring Shrouds Inspection and Rectification
- - - ModSum 4- - - 113902 This page transmits Revision ‘B’ of Service Bulletin 84- - -25- - -169, pages 1 thru 16, dated 17 Feb 2017.
This service bulletin is re- - -issued in its entirety for the reasons that follow:
--- t h eCompliance section is revised to convey the Transport Canada AD number (CF- - -2016- - -27) --- t h eReferences section is revised to convey the latest revision of the service bulletin and the Transport Canada AD number (CF- - -2016- - -27) --- t h eParts Required Per Aircraft section is revised to change the Consumable Product ID Number 07- - -29 to 07- - -29A in Step (3) consumable table --- t h eProcedure section is revised to replace all occurrences of “ Alodine C1 (07- - -29)” to “ Alodine C1 (07- - -29A)”.
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 issue of Service Bulletin 84- - -25- - -169 and replace with attached.
Previous issue(s) of Service Bulletin 84- - -25- - -169:
Initial issue - - - Pages 1 thru 16 dated 17 Dec 2015 Revision ‘A’ - - - Pages 1 thru 16 dated 25 Apr 2016
No text on this page: it may be a figure. Open the PDF to see it.
D S.B. 84- - -25- - -169 Page 1 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017
SERVICE BULLETIN Customer Support ATA SYSTEM: 2500 NUMBER: 84- - -25- - -169
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS
SERVICE BULLETIN TO BE PARTICULARL Y SIGNIFICANT AND
URGE OPERATORS TO PROMPTL Y EVALUATE THE CONTENTS SUBJECT : Equipment and Furnishings - - - Flight Compartment - - - Instrument Panel
- - - Pilot and Copilot Side - - - Wiring Shrouds Inspection and Rectification
- - - ModSum 4- - - 113902
1. PLANNING INFORMA TION A. Effectivity Aircraft Affected:
In- - -Service: DHC- - -8 Aircraft Models 401 and 402 Serial Numbers 4003 and subsequent.
Spares Affected:
None B. Reason Problem: Operators have experienced wires falling below the cockpit instrument panel. Subsequent inadvertent contact with the wires could cause instruments to misfunction. ModSum IS4Q2500035 has been issued to install a shroud that will prevent the wires from falling. However, an operator who incorporated the ModSum IS4Q2500035 has subsequently reported an obstruction of the pilot’s or co- - -pilot’s feet. Obstruction of the pilot’s or co- - -pilot’s foot at a critical phase of flight or ground operations can cause loss of of control of the aircraft.
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 2 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017 Solution: This service bulletin provides the instructions to inspect the aircraft to verify if the wiring shrouds are installed and, if installed, to rework the shrouds to remove the obstruction.
C. Description The procedures in this service bulletin give the instructions to do the tasks that follow:
- - - 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 aircraft electrical power is removed
- - - the pilot and co- - -pilot seats are removed
- - - the applicable pilot and co- - -pilot display units are removed for access as necessary
- - - the wiring shrouds are removed
- - - the stiffeners are removed from the wiring shrouds
- - - the wirings under the instrument panels are inspected for conditions and installation
- - - the wiring shrouds are re- - -installed
- - - an operational check of affected systems are done
- - - close out.
D. Compliance Bombardier Inc. highly recommend that this inspection and rectification service bulletin be accomplished at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority.
Transport Canada Airworthiness Directive CF- - -2016- - -27 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 # 9 3 --- Q --- 0 2 .
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage T olerance Inspections (DTIs).
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 3 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017 F. M a n p o w e r It will take an estimated 0.50 man- - -hrs to complete PART A of this service bulletin. It will take an estimated 6.50 man- - -hours to complete PART B of this service bulletin.
The breakdown of the man- - -hours to complete PART B is shown in the table that follows:
TASK M A N --- H O U R S J o b S e t --- U p 1.00 Procedure 3.00 T e s t/R T S 1.50 Close- - -Out 1.00 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 8DK4296- - -001 Kit Installation LHS - - - Wiring Shroud - - - Instrument Panel 8DK4296- - -002 Kit Installation RHS - - - Wiring Shroud - - - Instrument Panel 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 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 illustra tion). 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.
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 4 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017 If required the related 8DK drawings listed in the T able above can be requested by writing to the e- - -mail address that follows:
qseriesdwgrequest@aero.bombardier.com Follow the instructions per All Operator Messages (AOM) 389.
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 ‘B’ of this service bulletin was prepared to the engineering drawings and related data that follows:
DRAWING SHEET REV 8DK4296 1 --- --- 8Z8446 1 --- --- 8Z8446 2 --- --- ModSum 4Q113902 Rev. ‘A’ ModSum 4- - -113902 Rev. ‘B’ ModSum IS4Q2500035 Rev. ‘C’ A l lO p e r a t o rM e s s a g e s( A O M )3 8 9 PCA 45650 Revision 0 (for internal reference only) Transport Canada Airworthiness Directive CF- - -2016- - -27.
2. MATERIAL INFORMA TION A. Parts Required Per Aircraft
(1) Drawing Kits 8DK4296- - -001 and - - -002
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 5 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017
(2) Detailed Kit Content:
Quantity Per Kit --- 0 0 2 --- 0 0 1 Part Number Description Remarks 1 --- NAS9304E- - -5- - -02 Blind Rivet Acceptable alternative M7885/6- - -5- - -02 or CR3243- - -5- - -02 1 --- NAS9304E- - -4- - -02 Blind Rivet Acceptable alternative M7885/6- - -4- - -02 or CR3243- - -4- - -02 20 20 NAS1149D0332J Washer Acceptable alternatives AN960JD10L, AN960KD10L 10 10 MS21042- - -3 Nut 10 10 NAS1801- - -3- - -7 Screw 1 --- 8Z8446- - -102 Wiring Shroud Make from IS4Q2500035- - -1 --- 1 8Z8446- - -101 Wiring Shroud Make from IS4Q2500035- - -2 REF REF 8Z8446 8Z Rework Drawing only REF REF 8DK4296 Drawing Kit Drawing only NOTE: This service bulletin is self- - -contained (illustrated). No drawings will be supplied.
(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.
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).
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 6 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017 Consumable Product ID Number Qty. Per Aircraft Description Remarks 07- - -02A as required Primer, Fluid Resistant Epoxy (F19 T ype 2) DHMS C4.01 MIL- - -PRF- - -23377 07- - -29A as required Coating, Chemical Conversion (Alodine C1) MIL- - -C- - -5541 08- - -12 as required Solvent, Degreaser MIL- - -T- - -81533 or equivalent B. Special T ools and Equipment Required None C. Existing Parts Accountability Existing Part Number Description Qty. IC DC New Part Number PNC IS4Q2500035- - -1 Wiring Shroud LHS 1 C RWK 8Z8446- - -101 R IS4Q2500035- - -2 Wiring Shroud RHS 1 C RWK 8Z8446- - -102 R IC Interchangeability Code A Not interchangeable.
B Removed Part. No direct replacement.
C Conditionally Interchangeable. Inst allation of superseded part negates the intent of this service bulletin.
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 7 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017 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 . J o b S e t --- U p
(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.
(3) Set wheel chocks in front and behind the landing gear tires.
(4) 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).
B. Procedure Part A - - - Inspection
(1) Verify if the wiring shrouds are installed.
(2) If the wiring shrouds are not installed, go to Close Out.
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 8 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017
(3) If the wiring shrouds are installed go to PART - - - B - - - Rectificationbelow.
Part B - - - Rectification - - - Rework of Existing Wiring Shrouds
(1) Remove the pilot and co- - -pilot seat (refer to applicable instructions in AMM TASK 25- - -11- - -01- - -000- - -801).
(2) Remove the pilot and co- - -pilot display units as necessary (refer to applicable instructions in AMM TASK 31- - -61- - -01- - -000- - -801).
NOTE: If the wiring shroud is attached to the bottom of the instrument panel frame assembly using screws, washers and anchor nuts, it may not be necessary to remove the display units. If the wiring shroud is attached using screws, washers and hex nuts, the display units have to be removed.
(3) Disconnect the ground wires at 3428- - -GS1 and 3428- - -GS3 from the bottom of the co- - -pilot instrument panel (refer to Figure 5 View on Arrow E- - -E).
(4) Remove the existing wiring shrouds IS4Q2500035- - -1 and .IS4Q2500035- - -2 from under the instrument panel frame assembly (refer to Figure 3).
NOTE: It is acceptable to retain serviceabl e hardware for re- - -installation.
(5) Rework each wiring shroud as follows:
CAUTION: MAKE SURE NOT TO DAMAGE THE SHROUD WHEN DRILLING OFF THE RIVETS AS SHROUD IS TO BE USED AGAIN.
(a) Remove the four stiffeners from the shroud (refer to Figure 6 Details G and H).
(b) Leave the csk rivet holes open. Make sure there are no sharp edges.
(c) Clean the wiring shrouds with solvent (08- - -12). (refer to applicable instructions i n S R M T A S K 5 1 --- 2 6 --- 0 0 --- 0 2 --- 0 1 ) .
(d) Refinish csk’s and damaged surface with Alodine C1 (07- - -29A) and F19 Epoxy Primer (07- - -02A) (refer to the applicable instructions in SRM TASKs 5 1 --- 2 1 --- 1 0 --- 0 2 --- 0 1 a n d 5 1 --- 2 5 --- 1 0 --- 0 2 --- 0 1 ) .
(e) Use an indelible ink marker to part mark wiring shroud IS4Q2500035- - -1 as 8Z8446- - -101 and wiring shroud IS4Q2500035- - -2 as 8Z8446- - -102.
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 9 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017
(6) Prepare the shroud and instrument panel frame assembly for electrical bonding through direct contact (refer to the applicable instructions in AMM Chapter 51- - -80- - -00). Make sure shroud and instrument panel contact correspond and refinish areas with Alodine C1 (07- - -29A).
(a) The contact areas are defined by X- - -hatched diameter shown in Fig 3 and Figure 6 Details G and H.
(b) Make sure the shroud and instrument panel contact correspond.
(c) Refinish areas with Alodine C1 (07- - -29A) refer to the applicable instructions in S R M T A S K 5 1 --- 2 1 --- 1 0 --- 0 2 --- 0 1 ) .
(7) On the pilot side, if the tie mount exists as shown in Figure 4 View on Arrow D- - -D and Figure 5 Detail J, remove the tie mount and replace the fastener as noted in Figure 5 Detail J (refer to the applicable instructions in SRM TASK 5 1 --- 4 2 --- 1 5 --- 0 2 --- 0 1 ) .
(8) Install the wiring shrouds 8Z8446- - -101 (Pilot Side) and 8Z8446- - -102 (Co- - -pilot Side) on the bottom of the instrument panel frame assembly as follows (refer to Figure 6 View on Arrow F- - -F):
(a) Inspect the conditions of the wirings.
(b) If hex nuts are used instead of anchor nuts:
1 Make sure wirings are not pinched before tightening the screws.
2 Install washers under both the screw heads and nuts.
3 Tighten the screws with a suitable wrench until the screw head and base of the nut rest against the parts being tightened and resistance increases sharply (refer to applicable instructions in SRM TASKs 51- - -41- - -00- - -00- - -01 and 51- - -41- - -05- - -00- - -01). Tighten a further 1/4 turn.
(c) If anchor nuts are used instead of hex nuts:
1 Install washers under the screw heads.
2 Tighten the screws with a suitable wrench until the screw head and base of the nut rest against the parts being tightened and resistance increases sharply (refer to applicable instructions in SRM TASKs 51- - -41- - -00- - -00- - -01 and 51- - -41- - -05- - -00- - -01). Tighten a further 1/4 turn.
S E R V I C E B U L L E T I N 8 4 --- 2 5 --- 1 6 9 S.B. 84- - -25- - -169 Page 10 of 16 17 Dec 2015 NB Revision ‘B’ 17 Feb 2017
(9) After the wiring shrouds have been installed, do an inspection of the wirings as follows:
( a ) M a k es u r en ow i r e sa r ep i n c h e do rd a m a g e d .
(b) Make sure no wires are touching the shrouds. If necessary, install click bond fasteners for dressing the wires (refer to applicable instructions in AMM TASK 20- - -10- - -08- - -400- - -802).
(10) Re- - -connect the ground wires at 3428- - -GS1 and 3428- - -GS3 on the bottom co- - -pilot instrument panel (refer to Figure 5 View on Arrow E- - -E).
(11) Re- - -install the display units (refer to the applicable instructions in AMM TASK 31- - -61- - -01- - -400- - -801).
(12) Check for wire clearances on area LRUs and structure. If necessary, reposition (add tie wraps) and protect (refer to WDM 20- - -12- - -10- - -201 - - - Wiring Maintenance Practices and to Figure 4 View on Arrow D- - -D).
(13) Install the pilot and co- - -pilot seats (refer to the applicable instructions in AMM TASK 25- - -11- - -01- - -400- - -801).
(14) Do the Operational T est of the Rudder Control System (refer to AMM TASK 27- - -20- - -00- - -710- - -802).
C. Close Out
(1) Remove all tools and equipment from the work area.
(2) On incorporation of ModSum 4- - -113902, 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 BE- HALF OF THE RECIPIENT . THE RECIPIENT IS RESPONSIBLE FOR (A) PROPER MANUFACTURE OF THE PART USING THE SPECI-
FIED MATERIALS AND FOR INCORPORATION OF THE MODIFICATION, ALL IN ACCORDANCE WITH THE DRAWING AND RELATED INSTRUCTIONS, AND (B) APPROVAL OF THE FINAL INSTALLATI ON BY THE RELEVANT AIRWORTHINESS AUTHORITY . DE HAVIL- LAND INC. AND BOMBARDIER INC. (BOMBARDIER AEROSPACE REGIONAL AIRCRAFT) DISCLAIM ANY RESPONSIBILITY FOR IN-
CIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING WITHOUT LIMITATION LOSS OR USE, LOSS OF REVENUE OR LOSS OF PROFIT , ARISING FROM SUCH MANUFACTURE, INCORPORATION AND INSTALLATION.