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T x L t r S B 8 --- 2 7 --- 1 2 3 Page 1 of 2 Revision ‘A’ 08 Sep 2020 FQ 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 --- 2 7 --- 1 2 3 Flight Controls - - - Rudder Actuator Bracket Nuts - - - Inspection and Rectification This page transmits Revision ‘A’ of Service Bulletin 8- - -27- - -123, pages 1 thru 14, dated 08 Sep 2020.
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 and engineering documentation --- T h eAccomplishment Instruction section is revised to make a minor editorial change and add a NOTE.
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 initial issue of Service Bulletin 8- - -27- - -123 and replace with attached.
Previous issue(s) of Service Bulletin 8- - -27- - -123:
Initial issue - - - Pages 1 thru 14 dated - - - 20 Dec 2019
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 T x L t r S B 8 --- 2 7 --- 1 2 3 Page 2 of 2 Revision ‘A’ 08 Sep 2020 FQ This Page Intentionally Blank 1
S . B . 8 --- 2 7 --- 1 2 3 Page 1 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020
SERVICE BULLETIN ATA SYSTEM: 2720 NUMBER: 8- - -27- - -123
DE HAVILLAND AIRCRAFT OF CANADA LIMITED (DHC) CONSIDERS
THIS SERVICE BULLETIN TO BE PARTICULARL Y SIGNIFICANT AND
URGES OPERATORS TO PROMPTL Y EVALUATE THE CONTENTS SUBJECT : Flight Controls - - - Rudder Actuator Bracket Nuts - - - Inspection and Rectification - - - ModSum 8Q113038
1. PLANNING INFORMA TION A. Effectivity Aircraft Affected:
In- - -Service: DHC- - -8 Aircraft Models 102, 103, 106, 201, 202, 301, 311, 314 and 315 Serial Numbers 003 thru 672.
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
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 2 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020 B. Reason Problem: Corrosion, cracks or missing of MS21042- - -type rudder actuator bracket mounting nuts have been reported in the fleet. Eight MS21042- - -4 nuts are installed in between the rudder actuator brackets and the rear spar.
Solution: This service bulletin provides the instructions to do a detailed visual inspection of the MS21042- - -4 nuts attaching the rudder actuator brackets to the rear spar. If corrosion, cracks, or missing nuts are found, the MS21042- - -4 nuts are replaced with NAS9926- - -4L nuts.
This service bulletin also provides th e necessary instructions if damage is found. If required, MS21042- - -4 nuts are to be replaced with NAS9926- - -4L nuts.
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
- - - Rudder center hinge access panels are removed
- - - Eight rudder actuator bracket nuts on the rear spar are inspected.
- - - If any nut is corroded, cracked, or missing, all eight nuts, bolts and associated hardware are replaced
- - - Rudder center hinge access panels are installed
- - - if required, a rudder system operational test is done
- - - Close out.
D. Compliance DE HAVILLAND AIRCRAFT OF CANADA LIMITED highly recommends that ModSum 8Q113038 be incorporated at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority.
Transport Canada Airworthiness Directive Pending.
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 3 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020 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 # 1 9 --- Q --- 0 1 .
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 3.00 to 5.00 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 0.50 Procedure (Inspection) 1.00 Procedure (Rectification) 2.00 T e s t/R T S 1.00 Close- - -Out 0.50 This estimate is for direct labor 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 Kit Number Description 8DK4355- - -001 Drawing Kit - - - Rudder Actuator Bracket Nuts, Inspection and Rectification Drawing Kit(s) (DKs) listed in the table above are drawings only. No parts will be supplied.
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 4 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020 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.
See the contact information below.
DE HAVILLAND AIRCRAFT OF CANADA LIMITED Material Services 123 Garratt Blvd.
To r o n t o Ontario Canada M3K- - -1Y5 DHC Phone Numbers :
North America:T oll 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 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 H. T ooling - - - Price and Availability None I. Weight and Balance Not affected
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 5 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020 J. Electrical Load Data Not affected K. Publications Affected Aircraft Illustrated Parts Catalog PSM 1- - -8- - -4 and......................
P S M 1 --- 8 2 --- 4 a n d P S M 1 --- 8 3 --- 4 Modifications Manual PSM 1- - -813- - -12................................
L. References REvision ‘A’ of this service bulletin was prepared to the engineering drawings and related data that follows:
DRAWING SHEET REV 8DK4355 1 A ModSum 8Q113038 Rev. ‘D’ PCA 08262 Revision 0 (for internal reference only) Transport Canada Airworthiness Directive Pending
2. MATERIAL INFORMA TION A. Parts Required Per Aircraft
(1) Drawing Kit 8DK4355- - -001
(2) Detailed Parts List:
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 6 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020 Quantity Per Kit --- 0 0 1 Part Number Description Remarks 16 NAS1149D0416J Washer 8 NAS6604- - -14 Bolt 8 NAS9926- - -4L Self Locking Nut
(3) In addition to the above part(s), the follow ing consumable product is 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 “REF ITEM” identification number that is used to identify a particular recommended product, the specifications and the trade names any of which can be used u n l e s s s p e c i f i e d o t h e r w i s e ( r e f e r t o P S M 1 --- 8 --- 2 , 1 --- 8 2 --- 2 o r 1 --- 8 3 --- 2 A i r c r a f t Maintenance Manual (AMM) Chapter 51- - -31- - -00 CONSUMABLE MATERIALS - - - MAINTENANCE PRACTICES).
REF ITEM Qty. Per Aircraft Description Remarks 07- - -01 1/2 Quart F 1 3 C o a t i n g --- Compound, Corrosion Preventive, (hard, soft film, moisture displacing) F13, Grade 2 B. Parts Required to Modify Spares None C. Special T ools and Equipment Required Borescope equivalent to: ITI (Instrument T echnology Inc) Model 123010- - -40, (40 degrees with right angle adapter, 10 mm diameter 60 cm. long)
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 7 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020 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 MS21042- - -4 Self Locking Nut 8 C DIS NAS9926- - -4L S 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.
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.
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 8 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020
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) Pressurize the No. 1 and No. 2 hydraulic systems (refer to AMM 12- - -00- - -03).
(2) Move the flaps to 5 deg or greater. Obey all safety warnings for moving flight control surfaces (refer to AMM 27- - -50- - -00).
(3) Hold the rudder pedals to full rudder- - -left.
(4) Remove pressure from the No. 1 and No. 2 hydraulic systems (refer to AMM 12- - -00- - -03).
(5) Release the rudder pedals. Make sure ru dder remains in the full left position for access.
(6) 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 P S M 1 --- 8 --- 2 , 1 --- 8 3 --- 2 o r A M M C h a p t e r s 1 2 and 24 or 1- - -82- - -2 TASK 12- - -00- - -05- - -03 and TASK 24- - -00- - -00- - -910- - -803).
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 9 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020
(7) Make sure that lock pins are installed through each main gear and main gear door mechanism.
(8) Make sure the nose gear ground lock is engaged.
(9) Position suitable stand or lift to gain access to the inspection area.
B. Procedure
(1) Remove the access panels 323FR and 323GR (refer to AMM 06- - -40- - -10 or AMM 06- - -41- - -00 and drawing 8DK4355 sheet 1 flag note 7).
(2) Examine the visible ends of the rudder actuator bracket mounting nuts. Make sure that there are no cracks, corrosion, missing nut or other damage (refer to Figure 2).
NOTE: Use a light source, inspection mirror, magnifying glass and/or borescope as necessary.
(3) If cracks, corrosion, missing nut, or other damage is found do the instructions that follow:
(a) Remove the access panels 322DL and 322HR (refer to applicable i n s t r u c t i o n s i n A M M 2 7 --- 2 0 --- 3 6 a n d A M M 0 6 --- 4 0 --- 1 0 o r A M M 0 6 --- 4 1 --- 0 0 ) .
NOTE: It is not necessary to remove the actuators for rectification (nut replacement).
(b) Replace fastener at each location with new nut NAS9926- - -4L, new bolt NAS6604- - -14 and new washers NAS1149D0416J (1 under bolt head and 1 under nut) (refer to Figure 1). Coat shank of bolt with F13, Grade 2 compound (07- - -01).
(c) Remove and install one nut and bolt at a time. T orque the nut to 67 lbs- - -in
(7.6 N- - -m) before proceeding to next fastener location (refer to AMM 20- - -14- - -01). All eight nuts and bolts must be replaced.
(d) Install the access panels 322DL and 322HR (refer to applicable instructions i n A M M 2 7 --- 2 0 --- 3 6 a n d A M M 0 6 --- 4 0 --- 1 0 o r A M M 0 6 --- 4 1 --- 0 0 ) .
(e) Do an operational test of the rudder control system (refer to AMM 2 7 --- 2 0 --- 0 0 o r A M M 2 7 --- 2 0 --- 0 1 ) .
S E R V I C E B U L L E T I N 8 --- 2 7 --- 1 2 3 S . B . 8 --- 2 7 --- 1 2 3 Page 10 of 1420 Dec 2019 FQRevision ‘A’ 08 Sep 2020
(4) If no cracks, corrosion, missing nuts or other damage is found in any existing nuts MS21042- - -4, the undamaged nuts and all other hardware can remain in service.
NOTE: At the operator’s discretion it is acceptable to replace all eight nuts even if no missing nuts or damage is found.
(5) Install the access panels 323FR and 323GR (refer to AMM 06- - -40- - -10 or AMM 06- - -41- - -00).
C. Close Out
(1) Remove all tools and equipment from the work area.
(2) Complete the enclosed inspection forms (Appendix A) with inspection results and submit to the T echnical Help Desk.
(3) On completion of this service bulletin, make the following entry in the appropriate logbooks: “Service Bulletin 8- - -27- - -123 {Flight Controls - - - Rudder Actuator Bracket Nuts - - - Inspection and Rectification - - - ModSum 8Q113038} accomplished.”