Revision ‘B’ 11 Feb 2014

DHC ---8 (DASH 8)

SERVICE BULLETIN 84 ---27 ---44

Flight Controls --- Rudder Control Surfaces --- Fore Rudder --- Special

Inspection for Correct Installation of Bearings

This page transmits Revision ‘B’ of Service Bulletin 84 ---27 ---44, pages 1 thru

16, dated 11 Feb 2014.

This service bulletin is re ---issued in its entirety for the reasons that follow:

--- the PLANNING INFORMATION section D. Compliance on page 3 is

revised to add Transport Canada Airworthiness Directive CF ---2013 ---34.

--- the PLANNING INFORMATION section L. References on page 4 is revised

to show Revision ‘B’ of this service bulletin was prepared to the related data

that follows and also to add Transport Canada Airworthiness Directive

CF ---2013 ---34.

--- the ACCOMPLISHMENT INSTRUCTIONS section B. Procedure on page 8

NOTE is clarified.

--- the ACCOMPLISHMENT INSTRUCTIONS section C. Close Out on page 9

step (5) is revised to correct the referenced task number. Was TASK

27 ---20 ---01 ---710 ---802 now TASK 27 ---20 ---00 ---710 ---802.

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 Service Bulletin 84 ---27 ---44 Revision A and replace with attached.

Previous issue of Service Bulletin 84 ---27 ---44:

Initial issue --- Pages 1 thru 14 dated 13 Apr 2009

Rev A --- Pages 1 thru 16 dated 10 Jun 2009

D

S.B. 84 ---27 ---44

Page 1 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 2723 NUMBER: 84 ---27 ---44

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Flight Controls --- Rudder Control Surfaces --- Fore Rudder --- Special

Inspection for Correct Installation of Bearings

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In ---Service: DHC ---8 Aircraft Models 401 and 402 Serial Numbers 4166

thru 4175.

Production: A line check is done before delivery of DHC ---8 Models 401

and 402 Serial Number 4176 and subsequent per Line Check

37422.

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.
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 2 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

Spares Affected:

None

B. Reason

Problem: Bombardier production line inspection have reported that (upper and/or

lower) installed bearings in the fore rudder have migrated from their

housing on several aircraft.

Cause: The bearings had not been properly installed with adhesive (Loctite

Grade AA ) and sealed per engineering requirements.

Solution: A special inspection and if required rectification is accomplished to

confirm that affected bearings are correctly installed and sealed.

C. Description

The procedures in this service bulletin give the instructions to do the tasks that

follow:

--- #1 and #2 hydraulic systems are pressurized

--- the flaps are set to greater than 5 degrees

--- the rudder is swung full trailing ---edge left and held

--- #1 and #2 hydraulic systems are de ---pressurized

--- safety stands are placed behind the rudder

--- access panels 323CR and 323BR are removed from the fore rudder

--- rivets are drilled off and cover 85547207 ---103 is removed, if required, to proof

load test installed bearing

--- PCU actuator rod is detached from existing fore rudder hinge bracket assembly

--- existing bearings are then visually inspected and then proof load tested, if the

bearing passes proof load, no additional action is required

--- PART A INSPECTION of the Procedures section gives the instructions to

inspect the bearing for correct installation in the fore rudder

--- PART B RECTIFICATION of the Procedures section gives the instructions for

removal of bearings, inspection of the existing bore, installation of bearing with

adhesive Loctite Grade AA, proof load bearing test and the application of

sealant to the existing bearings in the fore rudder

--- the PCU actuator rod is attached to the existing fore rudder hinge bracket

assembly using retained hardware

--- cover 85547207 ---103 is installed to fore rudder with rivets
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 3 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

--- previously removed access panels are installed with retained hardware

--- an operational check of the rudder system is done

--- close out.

D. Compliance

Bombardier Inc. recommend that the special inspection/rectification be

incorporated at the earliest opportunity unless otherwise directed by the operator’s

airworthiness authority.

Transport Canada Airworthiness Directive CF ---2013 ---34.

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 #93 ---Q ---02.

F. Manpower

PART A --- Special Inspection for Correct Installation of Bearings --- Fore Rudder

It will take an estimated 6.50 man ---hours to complete PART A of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

---hours is shown in the table that follows:

TASK MAN ---HOURS

Job Set ---Up 2.00

Procedure in Part A 1.50

Test / RTS 1.00

Close ---Out 2.00

PART B --- Rectification Procedure for Incorrect Installation of Bearing --- Fore

Rudder

It will take an estimated 8.0 man ---hours to complete PART B of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

---hours is shown in the table that follows:

TASK MAN ---HOURS

Job Set ---Up 2.00

Procedure in Part B 3.00

Test / RTS 1.00

Close ---Out 2.00
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 4 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

G. Material --- Price and Availability

None

H. Tooling --- Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

None

L. References

Revision ‘B’ of this service bulletin was prepared to the related data that follows:

PCA 42445 Revision --- (for internal reference only)

Transport Canada Airworthiness Directive CF ---2013 ---34.

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

None

NOTE: This service bulletin is self ---contained (illustrated). No drawings will be

supplied.

(1) The following materials 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.

Addresses of manufacturers and suppliers not shown below are listed in 400

Series Aircraft, in Consumable Products Manual PSM 1 ---84 ---18.
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 5 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

Part Number Qty. Per Aircraft Description Remarks

MIL ---R ---81533 1 Ounce Solvent Trichloroethane,

1,1,1 or

DHMS S5.01 Class 2 1 Ounce Solvent Dynamold, Spec

AMS 3167

MIL ---S ---22473 1 Ounce Sealant Loctite, Grade AA

Loctite 7387 1 Ounce Sealant,Activator Loctite, Activator,

Grade N

DHMS S3.01,Type II,

Class B

1 Ounce Sealant PR1776M B1/2

or PR1776M B2

As Required Wiper Cloth White, Cotton

Lint ---Free Cloth

1 Marker Red Marker Martex Corp.

B0205018AD4 ---4S 8 Rivet

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

Part Number Description Remarks

Dillon Model U 30354 ---0058

or Equivalent Force Gage

Force Gage See Note 1

C ---Clamp

NAS43HT10 ---8 Spacer (Qty 1) See Note 2

NAS43HT14 ---8 Spacer (Qty 1) See Note 2

AN970 ---4 Washer

NOTE 1: Commercially available support hardware for proof loading may be

substituted for equivalent to suit individual force gage geometry.

NOTE 2: In the event that spacers listed are difficult to procure, operators are

permitted to locally manufacture spacers if required. Refer to Figure 6
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 6 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

for equivalent spacer dimensions and material specifications.

D. Existing Parts Accountability

None

3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set ---Up

WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE

MOVEMENT OF FLIGHT CONTROL SURFACES. MOVEMENT OF THE

FLIGHT CONTROL SURFACES CAN CAUSE INJURIES TO PERSONS

AND DAMAGE TO THE EQUIPMENT.

(1) Pressurize # 1 and # 2 hydraulic systems. Refer to Aircraft Maintenance Manual

PSM 1 ---84 ---2, TASK 29 ---00 ---00 ---863 ---801.

(2) Set flaps to greater than 5 degrees.

(3) Apply rudder pedal full trailing ---edge left and hold.

(4) De ---pressurize #1 and #2 hydraulic systems. Refer to Aircraft Maintenance

Manual PSM 1 ---84 ---2, TASK 29 ---00 ---00 ---863 ---802.

(5) Release rudder pedal and make sure no further pedal input is applied. The

rudder should remain in the deflected left position.

(6) Placard and select all aircraft electrical power to OFF. Obey all relevant

WARNINGS and CAUTIONS detailed in Maintenance Manual PSM 1 ---84 ---2.

Refer to Aircraft Maintenance Manual PSM 1 ---84 ---2, TASK

24 ---00 ---00 ---861 ---802.

(7) Install workstands on both sides of the rudder to safely reach the center main

hinge fittings as required. Make sure the workstands are electrically grounded.

WARNING: BE SURE THAT THE HYDRAULIC PRESSURE IS OFF, AND THAT

THERE IS NO PRESSURE IN THE HYDRAULIC SYSTEM. IF YOU DO

NOT DO THIS YOU CAN INJURIES TO PERSONS AND DAMAGE TO

THE EQUIPMENT.

(8) Remove and retain fore rudder hinge bracket assembly access panels 323 CR

and 323 BR, (RHS) and mounting hardware. Refer to Figure 1.

(9) Carefully drill off rivets B0205018AD4 ---4S attaching cover 85547207 ---103 to fore

rudder. Do not elongate rivet holes or damage countersink. Remove cover

85547207 ---103 to allow proof load tool to access fore rudder hinge bracket

assembly 85547217 ---001 and ---002. Refer to Figure 2.
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 7 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

NOTE: The skin consists of three parts, cover 85547207 ---103, Rib

85547208 ---103 and shim CSP 471 ---160 ---030 ---070 ---048.

(10) Disconnect each rudder PCU rod from the hinge bracket assembly as follows :

(a) Remove and discard the cotter pin MS24665 ---302. Refer to Figure 3.

(b) Remove and retain nut MS1414L6 and washer AN960D616L.

(c) Remove and retain the bolt NAS6706D14 from the end of the PCU actuator

rod and fore rudder hinge bracket assembly.

B. Procedure

NOTE: Instructions in PART A and PART B are given for upper hinge bracket

assembly 85547217 ---001. Repeat procedure in PART A and PART B for

lower bracket assembly 85547217 ---002.

PART A INSPECTION

(1) Set up proof load tester, Dillon Model U 30354 ---0058 or equivalent force gage

and C ---clamp, to the fore rudder hinge bracket assembly 85547217 ---001. Refer

to Figure 5.

(2) Proof load existing bearing DSC8 ---6 in ---situ to 132 lbs. Apply load by slowly

tightening C ---Clamp. During proof load testing, any slippage or freeplay (relative

movement between the bearing and fitting) is deemed as unacceptable.

(3) If bearing fails proof load test, refer to PART B RECTIFICATION section.

NOTE: Make sure spacer, (support) NAS43HT10 ---8 or equivalent, contacts

bearing race only .

NOTE: Make sure spacer, (support) NAS43HT14 ---8 or equivalent, contacts fitting

85574217 ---001 and washer, (support) AN970 ---4 on C ---Clamp.

(4) If existing bearing passes the proof load test, no further additional action is

required. Refer to C. Close Out section.

(5) Inspect area adjacent to the proof load tested bearings for a small red dot, if no

dot is present, identify area using a Dalo marker or equivalent paint marker.

Refer to Figure 5.

(6) If bearings have not been sealed, apply sealant DHMS S3.01, Type II, Class B

between the outside circumference of the installed bearing (both sides) and fore

rudder hinge bracket assembly 85547217 ---001.
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 8 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

NOTE: Do not allow sealant to enter bearings.

PART B RECTIFICATION

(1) If existing bearing fails proof load test, remove bearing DSC8 ---6 from fore

rudder hinge bracket assembly 85547217 ---001.

(2) Carefully remove sealant (if applicable) with a plastic or phenolic scraper from

bearing and top/bottom surfaces of fore rudder hinge bracket assembly.

NOTE: Do not use metal scrapers to remove sealant. Metal scrapers will damage

the surface.

(3) Inspect bearing DSC8 ---6 for damage, corrosion and dimension conformity.

Outside diameter of bearing should be 0.8120 to 0.8125 inch diameter.

NOTE: The existing bearings DSC8 ---6 may be reused if no damage, corrosion

and dimensional non ---conformity is evident.

(4) Inspect fitting bore of the fore rudder hinge bracket assembly 85547217 ---001 as

follows:

(a) Carefully inspect bore of the fore rudder hinge bracket assembly, using

flashlight and inspection mirror, for damage, corrosion and dimension

conformity.

(b) If damage, corrosion or dimensional non ---conformity is evident, carefully

ream the inside diameter with a 0.8140 inch diameter reamer.

(c) If bore is worn or damaged beyond 0.8140 inch diameter, a repair

disposition (RD) will be required from Bombardier. Contact the Technical

Help Desk department.

(5) Install new or existing DSC8 ---6 bearing into the fore rudder hinge bracket

assembly 85547217 ---001 with sealant MIL ---S ---22473 as follows:

(a) Solvent wipe the fitting bore of the fore rudder hinge bracket assembly and

bearings with a clean, cotton lint ---free cloth dampened with solvent

MIL ---R ---81533 or solvent DHMS S5.01, Class 2. Refer to Structural Repair

Manual, PSM 1 ---84 ---3 , 51 --- 22 ---40, Loctite Sealant Bonding procedure.

Refer to Figure 5.

NOTE: When cleaning sealed, grease lubricated bearings, make sure that no

solvent enters the sealed bearing and contaminates the lubricant.

NOTE: Handle all clean parts with clean lint ---free cotton gloves.
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 9 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

(6) Proof load installed bearings to 132 pounds with Dillon Model U 30354 ---0058 or

equivalent force gage. Refer to Figure 5.

(7) Identify proof loading test by applying a small red dot adjacent to the bearing

using a Dalo marker or equivalent.

(8) Seal the outer circumference of the installed bearing DSC8 ---6 to fore rudder

hinge bracket assembly 85547217 ---001 (on both sides of installed bearing) with

sealant DHMS S3.01, Type II, Class B. Refer to Figure 5.

NOTE: Do not allow sealant to enter bearings.

(9) Identify fore rudder hinge bracket assembly 85547217 ---001 with “SB

84 ---27 ---44” in a suitable area using a thin permanent marker.

C. Close Out

(1) Reconnect the rudder PCU rod to the hinge bracket. Install with retained bolt

NAS6706D14, retained washers AN960D616L (one under bolt head), retained

MS14144L6 nut and new cotter pin MS24665 ---302. Refer to Figure 3.

(2) Make sure the shim CSP 471 ---160 ---030 ---070 ---048 is installed between the rib

85547208 ---103 and cover 85547207 ---103. Install cover 85547207 ---103 with

rivets B0205018AD4 ---4S. Refer to Figure 2.

(3) Install access panels 323CR and 323BR with retained hardware.

(4) Remove all tools and equipment from the work area.

(5) Do the operational check of the rudder control system. Refer to Aircraft

Maintenance Manual, PSM 1 ---84 ---2, TASK 27 ---20 ---00 ---710 ---802.

(6) On completion of this service bulletin, make the following entry in the

appropriate logbooks: “Service Bulletin 84 ---27 ---44 Flight Controls --- Rudder

Control Surfaces --- Fore Rudder --- Special Inspection for Correct Installation of

Bearings accomplished”.
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 10 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

Fore Rudder Access Panels

Figure 1

FORE

RUDDER

mhwf1a01.cgm

COVER

85547207 ---103

323CL

323BL

323CR

323BR

(REFERENCE)

(REFERENCE)

ACCESS PANEL

ACCESS PANEL

Z107

110.031

ACCESS PANEL

ACCESS PANEL

Z107

124.031

D

B
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 11 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

Removal/Installation of Cover

Figure 2

COVER

85547207 ---103

RIB

85547208 ---103

SHIM

CSP471 ---160 ---030 ---070 ---048

NOTE:

ACCESS PANEL

323CR

ACCESS PANEL

323BR

COVER 85547207 ---103 CONSISTS OF RIB 85547208 ---103

RIVET

B0205018AD4 ---4S

AND SHIM CSP471 ---160 ---030 ---070 ---048

(QTY 8 REQUIRED)

FORE RUDDER

HINGE LINE

D

Z107

110.031

124.031

Z107

ALL MEASUREMENTS ARE IN INCHES

NOTE:
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 12 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

Removal/Installation of PCU Rudder Actuator Rod

Figure 3

BOLT

NAS6706D14

PCU ACTUATOR ROD

WASHER

AN960D616L

NUT

AN960D616L

WASHER

MS14144L6

COTTER PIN

MS24665 ---302

BEARING

DSC8 ---6

FORE RUDDER

HINGE BRACKET

ASSEMBLY

85547217 ---001/ ---002

RUDDER PCU

B
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 13 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

Installation/Removal of Bearing DSC8 ---6

Figure 4

BEARING

DSC8 ---6

BEARING

DSC8 ---6

FORE RUDDER

HINGE BRACKET

ASSEMBLY

85547217 ---001

FORE RUDDER

FORE RUDDER

HINGE BRACKET

ASSEMBLY

85547217 ---002

D

D
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 14 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

MIL ---S ---22473

FITTING

85547217 ---001/ ---002 BEARING

DSC8 ---6

INSTALL BEARING DSC8 ---6 WITH SEALANT

PROOF MARK WITH DALO

MARKER OR EQUIVALENT

BETWEEN FITTING AND THE OUTER CIRCUMFERENCE

OF THE INSTALLED BEARING DSC8 ---6 (BOTH SIDES)

APPLY SEALANT DHMS S3.01, TYPE II, CLASS B

Proof Loading Bearing Test / Sealant Application

Figure 5

PROOF LOAD BEARING

DSC8 ---6 TO 132 POUNDS

FITTING

BEARING

DSC8 ---6

85547217 ---001/ ---002

DILLON MODEL U

30354 ---0058 FORCE

GAGE OR EQUIVALENT

C ---CLAMP

SPACER, (SUPPORT)

NAS43HT14 ---8 OR EQUIVALENT

WASHER, (SUPPORT)

AN970 ---4 OR EQUIVALENT

SPACER, (SUPPORT)

NAS43HT10 ---8 OR EQUIVALENT

PROOF LOAD BEARING TEST

APPLICATION OF ADHESIVE AND SEALANT TO BEARING

1
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 15 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

ALLOY STEEL TUBING

NAS43HT --- (DIAMETER DASH NUMBER) --- (LENGTH DASH NUMBER)

GENERAL CODE

MATERIAL

10 0.120

0.927

0.735 0.765 0.627 0.677

14 0.130 0.985 1.015 0.877

NOTE: 1. ALL DIMENSIONS IN INCHES

Equivalent Spacer Dimensions and Material Specifications

Figure 6

2. REMOVE ALL BURRS

TO

LENGTH

0.120

0.130

3. SPACERS ARE SUPPORT HARDWARE FOR PROOF LOADING.

THEY ARE NOT PART OF THE AIRCRAFT.

MIN TO MAX

4. LISTED DIMENSIONS ARE SUGGESTED DIMENSION TO SUIT

DILLON MODEL U FORCE GAGE. IF ALTERNATE FORCE GAGE

IS USED, OPERATORS ARE PERMITTED TO DEVIATE FROM

LISTED DIMENSIONS TO SUIT INDIVIDUAL FORCE GAGE

GEOMETRY.
SERVICE BULLETIN 84 ---27 ---44

S.B. 84 ---27 ---44

Page 16 of 16

13 Apr 2009

Revision ‘B’ 11 Feb 2014

MD

This Page Intentionally Blank

1