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Revision ‘A’ 29 Nov 2018 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 8 --- 2 6 Fuel - - - Fuel System - - - Vent Line Isolator Locations - - - Electrical Bonding Check of Threaded Couplings P/N B0305119- - - 16A between Wing Station Yw 42.000 and Yw 60.900 This page transmits Revision ‘A’ of Service Bulletin 84- - -28- - -26, pages 1 thru 12, dated 29 Nov 2018.
This service bulletin is re- - -issued in its entirety for the reasons that follow:
--- t h eEffectivity section is revised to include TCCA approved Airworthiness Limitation Change Request (ACR) list and AD number --- t h eCompliance section is revised to include Transport Canada Airworthiness Directive (AD) CF- - -2017- - -04R2 --- t h eReferences section is revised to convey the latest revision of the service bulletin and engineering documentation --- t h eClose Out section is revised to add Revision ‘A’ to step (5) The Compliance in the previous issue of this service bulletin is not affected by this revision. No additional rework to the aircraft is introduced by this revision.
Remove the initial issue of Service Bulletin 84- - -28- - -26 and replace with attached.
Previous issue(s) of Service Bulletin 84- - -28- - -26:
Initial issue - - - Pages 1 thru 12 dated 14 Aug 2018
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D S . B . 8 4 --- 2 8 --- 2 6 Page 1 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018
SERVICE BULLETIN Customer Support ATA SYSTEM: 2812 NUMBER: 84- - -28- - -26
BOMBARDIER AEROSPACE CONSIDER THIS
SERVICE BULLETIN TO BE PARTICULARL Y SIGNIFICANT AND
URGE OPERATORS TO PROMPTL Y EVALUATE THE CONTENTS SUBJECT : Fuel - - - Fuel System - - - Vent Line Isolator Locations - - - Electrical Bonding Check of Threaded Couplings P/N B0305119- - - 16A between Wing Station Yw 42.000 and Yw 60.900
1. PLANNING INFORMA TION A. Effectivity Aircraft Affected:
In- - -Service: DHC- - -8 Aircraft Models 401 and 402 Serial Numbers 4001 and 4003 thru 4489, 4491 thru 4575 that have incorporated SB 8 4 --- 2 8 --- 2 1 R e v A b u t h a v eNOT completed IS4Q2800032 Revision A or that have NOT previously complied with any of the TCCA approved Airworthiness Limitation Change Request (ACR) listed in T able below, before the effective date of AD CF- - -2017- - -04R2 (9 October 2018).
ACR Number Dated ACR 400- - -072 23 January 2018 ACR 400- - -073 23 January 2018 ACR 400- - -074 24 January 2018 ACR 400- - -077 27 February 2018
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 2 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018 ACR 400- - -078 21 March 2018 ACR 400- - -079 18 April 2018 ACR 400- - -080 30 April 2018 ACR 400- - -081 04 May 2018 ACR 400- - -082 04 May 2018 ACR 400- - -083 04 June 2018 ACR 400- - -084 18 May 2018 NOTE: Aircraft MSN 4576 to 4581 inclusive (post production modification 4- - -113969) are also required to complete this SB 84- - -28- - -26.
NOTE: Electrical Bonding of the threaded couplings was completed on verification aircraft S/N 4490. MSN 4490 is not required to complete this SB 84- - -28- - -26.
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: ModSum 4- - -113970 (revision A of SB 84- - -28- - -21) has not been included with specific instructions for electrical bonding checks of threaded couplings located on the vent line between wing station Yw 42.000 and Yw 60.900.
Operators have requested a procedure to complete electrical bonding checks of threaded couplings.
Solution: This service bulletin gives the instructions to do the electrical bonding checks of threaded couplings located on the vent line between wing station Yw 42.000 and Yw 60.900 (LH and RH).
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 3 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018 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 through each main gear and main gear door mechanism
- - - fuel tank is prepared for access
- - - access panels are opened
- - - upper part of the inboard fuel tank partition panels are removed as required
- - - access is gained through collector bay to the isolators installed on inboard vent tube between wing stations Yw 42.000 and Yw 60.900
- - - electrical bonding checks of threaded couplings on the vent line between wing stations Yw 42.000 and Yw 60.900 (LH and RH) are done
- - - electrical bonding check of the fuel tank partition panels are completed
- - - close out.
D. Compliance Bombardier Inc. highly recommends the accomplishment of this inspection and rectification service bulletin at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority.
Transport Canada Airworthiness Directive CF- - -2017- - -04R2.
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
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 4 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018 It will take an estimated 4.00 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 1.00 Procedure 2.00 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 Not Applicable H. T ooling - - - Price and Availability Not Applicable I. Weight and Balance Not affected J. Electrical Load Data Not affected K. Publications Affected Maintenance Requirement Manual PSM 1- - -84- - -7....................
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:
ModSum IS4Q2800032 Rev. ‘A’
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 5 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018 PCA 46423 Revision 10 (for internal reference only) Transport Canada Airworthiness Directive CF- - -2017- - -04R2
2. MATERIAL INFORMA TION A. Parts Required Per Aircraft None B. Parts Required to Modify Spares None C. Special T ools and Equipment Required Reference Designation Remarks Biddle DLRO #247001, or BCD MI bonding meter, or equivalent Digital Low Resistance Ohmmeter Commercially Available D. Existing Parts Accountability None
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 Bombardier in the CRC at 1- - -844- - -272- - -2720 (1- - -844- - -CRC- - -CRC0) or email at thd.qseries@aero.bombardier.comfor analysis and to get an approved disposition to complete this service bulletin.
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 6 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018 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 .
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO
WORK ON THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT . IF YOU DO NOT YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT .
WARNING: YOU MUST REMOVE THE FUEL FROM THE FUEL TANK IN AN OPEN AREA. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT .
WARNING: DRAIN THE FUEL TANK BEFORE YOU REMOVE THE ACCESS PANELS. IF YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO THE WING STRUCTURE.
(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.
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 7 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018
(4) Set wheel chocks in front and behind the landing gear tires.
(5) Defuel the aircraft (refer to AMM TASK 12- - -10- - -28- - -650 802).
( 6 ) M a k es u r et od e - - - e n e r g i z et h ea i r c r a f te l e c t r i c a ls y s t e m( r e f e rt oA M MT A S K 24- - -00- - -00- - -861- - -802).
(7) Set up work platforms or ladders around and/or under the left and right wing to permit access to the fuel tanks. Make sure that the work platforms or ladders are electrically grounded.
(8) Make sure to obey the fuel system safety precautions (refer to AMM TASK 28- - -00- - -00- - -910- - -801).
(9) Obey the electrical/electronic safety precautions (refer to AMM TASK 24- - -00- - -00- - -910- - -801).
(10) Obey the electrostatic discharge safety precautions (refer to AMM TASK 24- - -00- - -00- - -910- - -802).
(11) Prepare the left and right wing fuel tanks for access (refer to AMM TASK 28- - -10- - -00- - -840- - -801).
(12) Remove the applicable left and right wing panels that follow:
ACCESS DESIGNATION 522AT (left wing) 622AT (right wing) Wet Bay Fuel Access Panels
(a) For removal of the wet bay fuel access panel refer to AMM TASK 57- - -11- - -01- - -000- - -801.
(13) Remove the fuel fumes (refer to AMM TASK 28- - -10- - -00- - -840- - -802).
(14) Remove the upper part of the inboard sid e partition panel assemblies as required (refer to the applicable instructions in AMM TASK 57- - -14- - -00- - -000- - -801).
WARNING: FUEL PLUMBING SYSTEMS ARE DESIGNED WITH ELECTRICAL BONDING FEATURES INCLUDING BONDING JUMPERS. SELF
BONDING COUPLINGS, CONDUCTIVE FITTINGS AND COMPONENTS WITH CONDUCTIVE INTERFACES. THESE DESIGN FEATURES ARE
CLASSIFIED AS CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL) ITEMS. THE INTEGRITY OF THESE CRITICAL
DESIGN FEATURES MUST BE MAINTAINED TO ENSURE THAT UNSAFE CONDITIONS DO NOT DEVELOP THROUGH MAINTENANCE.
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 8 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018 B. Procedure WARNING: DO NOT DAMAGE THE PROTECTIVE SLEEVE (HOSE). THE
PROTECTIVE SLEEVE (HOSE) IS NECESSARY TO PROVIDE
ELECTRICAL ISOLATION BETWEEN THE FUEL TANK VENT - - - LINES AND THE ADJACENT STRUCTURE. DAMAGE TO THE PROTECTIVE
SLEEVE CAN POSSIBL Y CAUSE AN IGNITION SOURCE INSIDE THE FUEL TANK DURING A LIGHTNING STRIKE.
The procedures that follow give the instructions to do the electrical bonding check in the left side fuel tank. Procedure for the right side is similar.
(1) Gain access to the two threaded couplings installed adjacent to the isolator on the inboard vent tube (left wing) between wing stations Yw - - -42.000 and Yw
- - -60.900 (refer to Figure 1).
(2) Do the electrical bonding test of the threaded couplings (two locations) installed adjacent to the isolator on the inboard vent tube as follows:
(a) Connect one lead of a digital low resistance ohmmeter (DLRO) on the fuel vent line approximately 1.0 inch from the swaged threaded ferrule as shown in Figure 2.
(b) Connect the other lead of the DLRO on the ferrule of the isolator as shown in the Figure 2.
(c) Make sure that the resistance is less than or equal to 1000 milliohms.
(d) If the reading exceeds 1000 milliohms, remove the nut of the threaded coupling (refer to Figure 3 and the applicable instructions given in AMM TASK 28- - -12- - -01- - -000- - -801) and make sure the split ring is seated properly and not damaged.
(e) Re- - -install the threaded coupling (refer to Figure 3 and the applicable instructions given in AMM TASK 28- - -12- - -01- - -400- - -801).
(f) Repeat the electrical bonding check and make sure that the resistance is less than or equal to 1000 milliohms.
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 9 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018
(3) Do the the above procedure (Step 1 and 2) at the right side (two locations) of the fuel tank and make sure that the resistance is less than or equal to 1000 milliohms.
C. Close Out
(1) Install the upper part of the inboard side partition assemblies (refer to the applicable instructions in AMM TASK 57- - -14- - -00- - -400- - -801).
(2) Do the required electrical bonding checks of the collector bay panels at TP223 and TP227 (refer to AMM TASK 51- - -80- - -00- - -760- - -810 Figure 280 Sheet 12 of 12, step AI and T able 35).
(3) Install the applicable left and right wing panels that follow:
ACCESS DESIGNATION 522AT (left wing) 622AT (right wing) Wet Bay Fuel Access Panels
(a) For installation of the wet bay fuel access panel refer to AMM TASK 57- - -11- - -01- - -400- - -801.
(4) Remove all tools and equipment from the work area.
(5) On completion of this service bulletin, make the following entry in the appropriate logbooks: “Service Bulletin 84- - -28- - -26 Revision ‘A’ {Fuel - - - Fuel System - - - Vent Line Isolator Locations - - - Electrical Bonding Check of Threaded Couplings P/N B0305119- - -16A between Wing Station Yw 42.000 and Yw 60.900} is accomplished.”
S E R V I C E B U L L E T I N 8 4 --- 2 8 --- 2 6 S . B . 8 4 --- 2 8 --- 2 6 Page 10 of 12 14 Aug 2018 PM Revision ‘A’ 29 Nov 2018 Inboard Vent Tube Location (Wi ng Station - - - Yw 42.000- - - Yw 60.900) Figure 1