Hydraulic Power − Hydraulic System No. 1 and No. 2 − Inspection of the

Accumulator Screw−Caps

These pages transmit:

Revision B of Alert Service Bulletin A670BA−29−011,

pages 1 thru 20, dated Dec 22/2010.

and

Revision A of Appendix A

pages A1 thru A9, dated Jul 27/2010.

The changes in this revision have no effect on aircraft that have incorporated a

previous issue of this service bulletin.

Reason:

Revised Planning Information, paragraph 1., to:

Remove aircraft serial numbers 10315 thru 10999, 15233, 15234, 15239, and

15259 thru 15990 from the effectivity of the service bulletin.

Add a note in Compliance paragraph 1.D.

Add Bombardier Regional Jet Series All Operator Message (AOM), No. 614,

Parker Service Information Letter 900096−29−225, and to change Parker

Service Bulletin 900096−1−29−391 Revision 1 for Revision 2 in References

paragraph 1.K.

This revision also includes small editorial changes that do not have an effect on the

technical content.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 1 of 2

Dec 22/2010

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CL−600−2C10, CL−600−2D15, CL−600−2D24 and CL−600−2E25

CANADAIR REGIONAL JET (CRJ) AIRCRAFT

SUBJECT:
Document Instructions:

Discard the copy of Alert Service Bulletin A670BA−29−011, Revision A, dated Jul

27/2010. Replace with the copy attached.

Service Bulletin History:

Initial issue, dated Oct 18/2007.

Revision A, dated Jul 27/2010.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 2 of 2

Dec 22/2010

REVISION TRANSMITTAL SHEET
Hydraulic Power − Hydraulic System No. 1 and No. 2 − Inspection of the

Accumulator Screw−Caps

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

Service Bulletin: CL−600−2C10 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 10003 thru 10314.

Production: There is no production effectivity.

Service Bulletin: CL−600−2D15 Canadair Regional Jet (CRJ) and

CL−600−2D24 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 15001 thru 15232, 15235

thru 15238, and 15240 thru 15258.

Production: There is no production effectivity.

NOTE: The instructions in this service bulletin are only applicable to the

systems and parts installed at the time of delivery of the aircraft or

as changed by Bombardier Aerospace Service Bulletin. Before you

do this bulletin, examine all STC, STA or equivalent action changes

to make sure this bulletin can be completed.

ATA SYSTEM: 29−11 NUMBER: A670BA−29−011

S.B. A670BA−29−011

Page 1 of 20

Oct 18/2007

Revision B, Dec 22/2010

ALERT SERVICE BULLETIN

Technical

Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT,

THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

TRANSFERRED SPARES IN THE LAST SIX MONTHS, THIS SERVICE BULLETIN MUST BE SENT TO THE

NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT

DIVISION HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST.

SUBJECT:
B. Reason

(1) Condition

It is possible for the screw−caps of the system No. 1 and No. 2 accumulators

to have cracks in the inner shoulder. This can cause the screw−cap to

rupture and cause damage to the aircraft structure and systems.

(2) Evidence

A screw−cap ruptured and disconnected on the hydraulic side of hydraulic

system No. 1 on a CRJ 200 aircraft.

(3) Objective/Benefit

This service bulletin gives the procedure to do a detailed inspection and an

ultrasonic inspection on the screw−caps of the accumulator of hydraulic

system No. 1 and No. 2. This will prevent damage to the accumulators,

aircraft structure and systems.

C. Description

This service bulletin is divided in two parts: PART A and PART B.

PART A − Hydraulic Systems No. 1 and No. 2, Detailed Inspection of the

Accumulator Screw−Caps

The aft−equipment compartment door is opened. The hydraulic pressure is

released from systems No. 1 and No. 2. The electrical power is removed. The

circuit breakers are opened. The nitrogen pressure is bled from the system No. 1

and No. 2 accumulators. A visual inspection is done on the screw−caps of the

accumulators.

The circuit breakers are closed. The servicing of the accumulator is done. The

aft−equipment compartment door is closed.

PART B − Ultrasonic Inspection of the Accumulator Screw−Caps

The aft−equipment compartment door is opened. The hydraulic pressure is

released from systems No. 1 and/or No. 2. The electrical power is removed. The

circuit breakers are opened. The nitrogen pressure is bled from the system No. 1

and/or No. 2 accumulators. The applicable accumulator(s) is removed. An

ultrasonic inspection is done on the accumulator screw−caps.

The accumulator(s) is installed. The circuit breakers are closed. If necessary

hydraulic system No. 1. and/or No. 2 is filled. The servicing of the accumulator is

done. The nitrogen leak test is done. The applicable hydraulic system(s) is bled.

The aft−equipment compartment door is closed.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 2 of 20

Oct 18/2007

Revision B, Dec 22/2010
D. Compliance

Alert Service Bulletin.

NOTE: It is not necessary to do this service bulletin when Service Bulletin

670BA−29−014, Hydraulic Power − Hydraulic System No. 1 and No. 2 −

Replacement of Accumulator P/N 900096−1 by P/N 900121−1, is done.

Bombardier Aerospace recommends that this service bulletin be done as shown

in the table below, unless otherwise directed by the airworthiness authority of the

operator:

NOTE: The letter ‘M’ added at the end of the serial number of accumulators P/N

900096−1 identifies that the new screw−caps were installed as shown in

Parker Service Bulletin 900096−1−29−391.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 3 of 20

Oct 18/2007

Revision B, Dec 22/2010
APPLICABLE COMPLIANCE

INSPECTION RESULTS ACTION

For hydraulic

system No. 1 and

No. 2:

Accumulators P/N

900096−1 with

serial numbers

without letter ‘M’ at

the end (For the

list of serial

numbers see

TABLE 1 and the

note below).

For accumulators

that have 4500 flight

cycles or less, it is

necessary to do

PART A of this

service bulletin

before the

accumulators have

5000 flight cycles.

If a crack is found

during the

detailed

inspection (PART

A), it is necessary

to replace the

accumulator

before next flight.

The crack must

be identified by

an ultrasonic

inspection

described in

PART B.

It is

necessary to

repeat the

detailed

inspection

(PART A)

every 500

flight cycles

from the

initial

inspection

Or

It is not

necessary to

do or repeat

PART A if

PART B is

done.

For accumulators

that have more than

4500 flight cycles, it

is necessary to do

PART A of this

service bulletin no

more than 500 flight

cycles from the issue

date on this service

bulletin.

For accumulators

that have 3000 flight

cycles or less, it is

necessary to do

PART B of this

service bulletin

before the

accumulators have

5000 flight cycles.

If a crack is found

during the

ultrasonic

inspection (PART

B), it is necessary

to replace the

accumulator

before next flight.

It is

necessary to

do PART B

of this

service

bulletin every

1500 flight

cycles from

the initial

PART B

inspection.

For accumulators

that have more than

3000 flight cycles, it

is necessary to do

PART B of this

service bulletin

before 2000 flight

cycles from the issue

date of this service

bulletin.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 4 of 20

Oct 18/2007

Revision B, Dec 22/2010
APPLICABLE COMPLIANCE

INSPECTION RESULTS ACTION

For hydraulic

system No. 1 and

No. 2:

Accumulators P/N

900096−1 with

serial numbers

with letter ‘M’ at

the end.

It is not necessary to do this service bulletin.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 5 of 20

Oct 18/2007

Revision B, Dec 22/2010
TABLE 1

60206−0001 thru 60206−0010

60206−0012 thru 60206−0015

60206−0017 thru 60206−0019

60206−0021 thru 60206−0024

60206−0026 thru 60206−0041

60206−0043 thru 60206−0045

60206−0047 thru 60206−0049

60206−0052

60206−0054 thru 60206−0057

60206−0059

60206−0061 thru 60206−0069

60206−0072 thru 60206−0074

60206−0076 thru 60206−0079

60206−0081

60206−0084 thru 60206−0085

60206−0088 thru 60206−0091

60206−0093 thru 60206−0106

60206−0108

60206−0110 thru 60206−0119

60206−0121 thru 60206−0126

60206−0129

60206−0131 thru 60206−0140

60206−0142 thru 60206−0153

60206−0157 thru 60206−0163

60206−0166 thru 60206−0173

60206−0175 thru 60206−0177

60206−0180

60206−0182 thru 60206−0202

60206−0204 thru 60206−0218

60206−0220 thru 60206−0229

60206−0231 thru 60206−0249

60206−0251 thru 60206−0256

60206−0258 thru 60206−0259

60206−0262 thru 60206−0264

60206−0266 thru 60206−0279

60206−0281 thru 60206−0290

60206−0292

60206−0294 thru 60206−0300

60206−0303 thru 60206−0332

60206−0334 thru 60206−0351

60206−0353

60206−0355 thru 60206−0396

60206−0398 thru 60206−0408

60206−0410 thru 60206−0415

60206−0417 thru 60206−0427

60206−0429 thru 60206−0439

60206−0441 thru 60206−0461

60206−0463 thru 60206−0494

60206−0496 thru 60206−0498

60206−0501 thru 60206−0502

60206−0504 thru 60206−0527

60206−0530 thru 60206−0553

60206−0555 thru 60206−0566

60206−0568 thru 60206−0580

60206−0582 thru 60206−0590

60206−0592 thru 60206−0597

60206−0599 thru 60206−0622

60206−0624 thru 60206−0627

60206−0629 thru 60206−0630

60206−0632

60206−0634 thru 60206−0643

60206−0645 thru 60206−0658

60206−0660 thru 60206−0674

60206−0677 thru 60206−0679

60206−0682 thru 60206−0684

60206−0687 thru 60206−1003

60206−1005 thru 60206−1017

60206−1019 thru 60206−1031

60206−1033 thru 60206−1051

60206−1053 thru 60206–1054

NOTE: For serial numbers listed in TABLE 2 below, the new screw−caps were

installed by Parker, but it is necessary to incorporate Parker Service

Bulletin 900096−1−29−391 to add the letter ‘M’ at the end of the serial

numbers.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 6 of 20

Oct 18/2007

Revision B, Dec 22/2010
TABLE 2

60206−0011

60206−0016A

60206−0020

60206−0025

60206−0042A

60206−0046

60206−0050

60206−0051

60206−0053

60206−0058A

60206−0060A

60206−0070

60206−0071A

60206−0075A

60206−0080

60206−0082

60206−0083

60206−0086

60206−0087

60206−0092A

60206−0107

60206−0109B

60206−0120

60206−0127

60206−0128

60206−0130

60206−0141

60206−0154

60206−0155A

60206−0156

60206−0164

60206−0165

60206−0174

60206−0178

60206−0179

60206−0181

60206−0203

60206−0219

60206−0230

60206−0250

60206−0257

60206−0260

60206−0261

60206−0265

60206−0280

60206−0291

60206−0293

60206−0301

60206−0302

60206−0333

60206−0352

60206−0354

60206−0397

60206−0409

60206−0416

60206−0428

60206−0440

60206−0462

60206−0495

60206−0499

60206−0500

60206−0503

60206−0528

60206−0529

60206−0554

60206−0567

60206−0581

60206−0591

60206−0598

60206−0623

60206−0628

60206−0631

60206−0633

60206−0644

60206−0659

60206−0675

60206−0676

60206−0680

60206−0681

60206−0685

60206−0686

60206−1004

60206−1018

60206−1032

60206−1052

60206–1055

thru

60206−1514

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance Inspections (DTIs).

E. Approval

The technical content of this service bulletin has been approved under the

authority of the TCCA Design Approval Organization No: DAO #93−Q−02.

F. Manpower

The man−hours given below are an estimate for direct labor done by an

experienced crew on an aircraft prepared for maintenance.

These estimates do not include the time necessary for:

− Administrative functions such as planning, liaison, familiarization, and

report writing.

− Non productive elapsed time such as rest time, having meals, and crew

shift changes.

− Elapsed time such as for paint to dry, sealant to cure, and fuel tank

venting.

− Preparation for modification (unless specified in the accomplishment

instructions) such as cleaning and getting parts, tools, consumables, and

ground equipment.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 7 of 20

Oct 18/2007

Revision B, Dec 22/2010
− Quality assurance inspections, troubleshooting and/or correction of

discrepancies found when a task is done.

− All other activities that are not considered by Bombardier Aerospace as

directly related to the accomplishment of this procedure.

For on−site labor assistance, please speak with a Fleet Services

representative for a quote. The Fleet Services team can be contacted via

the CRC at 514−855−8500 or email at thd.crj@aero.bombardier.com.

PART A − Hydraulic Systems No. 1 and No. 2, Detailed Inspection of the

Accumulator Screw−Caps

It will take an estimated 3.0 man−hours to complete PART A of this service

bulletin. The man−hours are divided as shown in the table that follows:

TASK MAN−HOURS

(1) Job Set−Up 1.0

(2) Procedure 0.5

(3) Test 1.0

(4) Job Close−Out 0.5

NOTE: The man−hours for the procedure do not include the hours to replace

damaged parts. If replacement is necessary, add 2 hours for each

accumulator.

PART B− Ultrasonic Inspection of the Accumulator Screw−Caps

It will take an estimated 5.5 man−hours to complete PART B of this service

bulletin. The man−hours are divided as shown in the table that follows:

TASK MAN−HOURS

(1) Job Set−Up 1.0

(2) Procedure 3.0

(3) Test 1.0

(4) Job Close−Out 0.5

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 8 of 20

Oct 18/2007

Revision B, Dec 22/2010
G. Material − Price and Availability

(1) There are no kits for this service bulletin.

(2) Refer to paragraph 3.C. for a list of consumables for this service bulletin.

H. Tooling − Price and Availability

(1) The tool kit in the table that follows is available from Bombardier commercial

aircraft.

NOTE: For a list of the kit contents, refer to paragraph 3.A.

KIT NUMBER NAME

670BA32021K90 NDT Calibration Tool

NOTE: 601R32−103K90 NDT calibration tool can be used as an alternative

tool.

(2) Please send a purchase order to the address below to schedule the kit(s):

Bombardier

Service Bulletin Kit Support Team

123 Garratt Blvd, N42−24

Toronto, Ontario

Canada M3K 1Y5

Fax: 416−375−3060

Phone: 416−375−3920

email: sbkits@aero.bombardier.com

Please contact your Service Bulletin Kit Support Team at the address above

for terms and conditions.

I. Weight and Balance

Not changed.

J. Electrical Load Data

Not changed.

K. References

− Restriction and/or Special Instruction (RSI), C−29−1030−00, Revision C.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 9 of 20

Oct 18/2007

Revision B, Dec 22/2010
− Parker Service Bulletin 900096−1−29−391, Revision 2, dated Sept

30/2010.

− Bombardier Regional Jet Series All Operator Message (AOM), No. 614.

− Parker Service Information Letter 900096−29−225.

− Aircraft Maintenance Manual (AMM), CSP B−001.

− Nondestructive Testing Manual (NDT), CSP B−010.

− For Bombardier Aerospace reference only: PCA 72957.

L. Other Publications Affected

None.

M. Relationship Chart

Not applicable.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 10 of 20

Oct 18/2007

Revision B, Dec 22/2010
2. ACCOMPLISHMENT INSTRUCTIONS

PART A − Hydraulic Systems No. 1 and No. 2, Detailed Inspection of the Accumulator

Screw−Caps

A. Job Set−Up

(1) Reference Information

REFERENCE DESIGNATION

AMM 12−00−00−867−801 Standard Aircraft Configuration for

Maintenance

AMM 12−00−06−862−802 Release Hydraulic Pressure of

System No. 1 and No. 2

AMM 12−12−29−614−801 Servicing of the Hydraulic System

Accumulators

AMM 24−00−00−861−802 Remove Electrical Power from the

Aircraft

AMM 24−00−00−910−801 Electrical/Electronic Safety

Precautions

(2) Standard Practices Information

REFERENCE DESIGNATION

AMM 51−26−00−110−801 Solvent Cleaning

NDT 51−20−009−210 Visual − Inspection Procedures

(3) Make sure that the aircraft is in standard configuration for maintenance

(AMM 12−00−00−867−801).

(4) Open aft equipment−compartment door 311 BB.

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO

MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC

EQUIPMENT. YOU CAN CAUSE INJURY TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(5) Obey all the electrical/electronic safety precautions (AMM

24−00−00−910−801).

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 11 of 20

Oct 18/2007

Revision B, Dec 22/2010
(6) Remove the electrical power from the aircraft (AMM 24−00−00−861−802).

WARNING: OBEY ALL HYDRAULIC SAFETY PRECAUTIONS WHEN YOU

DO WORK ON THE HYDRAULIC SYSTEM AND HYDRAULIC

SYSTEM COMPONENTS. YOU CAN CAUSE INJURY TO

PERSONS AND DAMAGE TO THE EQUIPMENT.

(7) Release the hydraulic pressure from hydraulic system(s) No. 1 and/or No. 2

(AMM 12−00−06−862−802).

Refer to Figure 2.

WARNING: USE PROTECTIVE GLOVES TO CAREFULLY LOOSEN THE

VALVE NUT ON THE NITROGEN CHARGING VALVE. KEEP

YOUR HANDS AWAY FROM THE NITROGEN LEAKAGE. THE

NITROGEN LINE IS PRESSURIZED AND CAN CAUSE INJURY.

(8) Release the nitrogen pressure as follows:

(a) Remove the dust cap (4) from the nitrogen charge valve (3).

(b) Carefully loosen the thin nut on the nitrogen charge valve (3).

(c) Let the nitrogen pressure go to zero.

B. Procedure

Refer to Figures 1 and 2.

WARNING: OBEY ALL CLEANING SAFETY PRECAUTIONS. YOU CAN

CAUSE INJURIES TO PERSONS AND DAMAGE TO THE

EQUIPMENT.

(1) Clean the tapered section of the accumulator screw−caps with isopropyl

alcohol and a dry clean cloth.

(2) Do a visual inspection of the accumulator screw−caps (two per accumulator)

for indications of a crack.

(3) If there is a crack or an indication of a crack on the accumulator do PART B.

NOTE: Make sure there is a crack with an ultrasonic inspection as described in

PART B.

C. Job Close−Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 12 of 20

Oct 18/2007

Revision B, Dec 22/2010
(2) Replenish the hydraulic system(s) No. 1 and/or No. 2 accumulator(s) (1)

(AMM 12−12−29−614−801).

(3) Close aft equipment−compartment door 311 BB.

(4) When PART A of this service bulletin is completed, make this entry in the

applicable logbook as follows: "Alert Service Bulletin A670BA−29−011,

Revision B, Hydraulic Power − Hydraulic System No. 1 and No. 2 −

Inspection of the Accumulator Screw−Caps, PART A incorporated."

PART B − Ultrasonic Inspection of the Accumulator Screw−Caps

A. Job Set−Up

(1) Reference Information

REFERENCE DESIGNATION

AMM 12−00−00−867−801 Standard Aircraft Configuration for

Maintenance

AMM 12−00−06−862−802 Release Hydraulic Pressure of

System No. 1 and No. 2

AMM 12−12−29−611−801 Servicing of the Hydraulic System

No. 1 and No. 2 Reservoirs

AMM 12−12−29−614−801 Servicing of the Hydraulic System

Accumulators

AMM 24−00−00−861−802 Remove Electrical Power from the

Aircraft

AMM 24−00−00−910−801 Electrical/Electronic Safety

Precautions

AMM 29−10−00−870−801 Bleed Hydraulic systems No. 1 and

No. 2

AMM 29−11−11−000−801 Removal of the System No. 1 and

No. 2 Accumulator

AMM 29−11−11−400−801 Installation of the System No. 1 and

No. 2 Accumulator

AMM 29−11−11−720−803 Functional Test of the System No. 1

and No. 2 Accumulator Pressure

Decay Rate

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 13 of 20

Oct 18/2007

Revision B, Dec 22/2010
(2) Make sure that the aircraft is in standard configuration for maintenance

(AMM 12−00−00−867−801).

(3) Open aft equipment−compartment door 311 BB.

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO

MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC

EQUIPMENT. YOU CAN CAUSE INJURY TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(4) Obey all the electrical/electronic safety precautions (AMM

24−00−00−910−801).

(5) Remove the electrical power from the aircraft (AMM 24−00−00−861−802).

WARNING: OBEY ALL HYDRAULIC SAFETY PRECAUTIONS WHEN YOU

DO WORK ON THE HYDRAULIC SYSTEM AND HYDRAULIC

SYSTEM COMPONENTS. YOU CAN CAUSE INJURY TO

PERSONS AND DAMAGE TO THE EQUIPMENT.

(6) Release hydraulic pressure from hydraulic system(s) No. 1 and/or No. 2

(AMM 12−00−06−862−802).

(7) For hydraulic system No. 1, open, safety, and tag the circuit breaker that

follows:

CB−PANEL CB NO. NAME

CBP−1 F14 HYD SYST AC PUMP CONT 2

(8) For hydraulic system No. 2, open, safety, and tag the circuit breaker that

follows:

CB−PANEL CB NO. NAME

CBP−2 F13 HYD SYST AC PUMP CONT 1

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 14 of 20

Oct 18/2007

Revision B, Dec 22/2010
Refer to Figure 2.

WARNING: USE PROTECTIVE GLOVES TO CAREFULLY LOOSEN THE

VALVE NUT ON THE NITROGEN CHARGING VALVE. KEEP

YOUR HANDS AWAY FROM THE NITROGEN LEAKAGE. THE

NITROGEN LINE IS PRESSURIZED AND CAN CAUSE INJURY.

(9) Release the nitrogen pressure as follows:

(a) Remove the dust cap (4) from the nitrogen charge valve (3).

(b) Carefully loosen the thin nut on the nitrogen charge valve (3).

(c) Let the nitrogen pressure go to zero.

(10) Remove the hydraulic system(s) No. 1 and/or No. 2 accumulator(s) (AMM

29−11−11−000−801).

B. Procedure

(1) Do an ultrasonic inspection on the screw−caps of the hydraulic system No. 1

and/or No. 2 accumulator(s) (Refer to Appendix A).

(2) If there is a crack do as follows:

(a) Send the accumulator(s) to:

Bombardier

CRJ In Service Engineering

13100 Boulevard Henri Fabre, Mirabel

Quebec, Canada J7N 3C6

C/O ISE group

Dept# 662

(b) Install a new accumulator (AMM 29−11−11−400−801).

(3) If there is no crack, install the hydraulic system(s) No. 1 and/or No. 2

accumulator(s) (AMM 29−11−11−400−801).

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 15 of 20

Oct 18/2007

Revision B, Dec 22/2010
ba4874a01.cgm

A

B

2. Screw cap.

LEGEND

1. System accumulator.

C

B NO.2 SYSTEM

2

1

2

C

C

A NO.1 SYSTEM

ALERT SERVICE BULLETIN A670BA−29−011

Accumulator Location

Figure 1

S.B. A670BA−29−011

Page 16 of 20

Oct 18/2007

Revision B, Dec 22/2010
ba4874a02.cgm

1

1

2

1

2

F

F

D

E

D

NO. 2 

HYDRAULIC SYSTEM 

SERVICE PANEL

5

3

4

E

NO. 1 

HYDRAULIC SYSTEM 

SERVICE PANEL

LEGEND

1. System accumulator.

2. Screw cap.

3. Nut.

4. Dust cap.

5. Pressure gauge.

F

1

A NO.1 SYSTEM

1 Inspection area.

NOTE

ALERT SERVICE BULLETIN A670BA−29−011

Accumulator Inspection Location

Figure 2

S.B. A670BA−29−011

Page 17 of 20

Oct 18/2007

Revision B, Dec 22/2010
C. Job Close−Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

(2) For hydraulic system No. 1, remove the tags and close the circuit breaker

that follows:

CB−PANEL CB NO. NAME

CBP−1 F14 HYD SYST AC PUMP CONT 2

(3) For hydraulic system No. 2, remove the tags and close the circuit breaker

that follows:

CB−PANEL CB NO. NAME

CBP−2 F13 HYD SYST AC PUMP CONT 1

(4) Replenish the hydraulic system(s) No. 1 and/or No. 2 reservoir(s) (AMM

12−12−29−611−801).

(5) Replenish the hydraulic system(s) No. 1 and/or No. 2 accumulator(s) (1)

(AMM 12−12−29−614−801).

(6) Bleed hydraulic system(s) No. 1 and/or No. 2 (AMM 29−10−00−870−801).

(7) Do the functional test for the applicable hydraulic system No. 1 and/or No. 2

accumulator pressure decay rate (AMM 29−11−11−720−803).

(8) Close aft equipment−compartment door 311BB.

(9) When PART B of this service bulletin is completed, make this entry in the

applicable logbook as follows: "Alert Service Bulletin A670BA−29−011,

Revision B, Hydraulic Power − Hydraulic System No. 1 and No. 2 −

Inspection of the Accumulator Screw−Caps, PART B incorporated."

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 18 of 20

Oct 18/2007

Revision B, Dec 22/2010
3. MATERIAL INFORMATION

A. Kit Information

Kit Content:

KIT 670BA32021K90

PART

NUMBER

QUANTITY NAME ALTERNATE

PART(S)

NOTES

T11330 1 NDT

Calibration

Tool

[1] Refer to paragraph 1.H. for special terms and conditions.

B. Consumable Information

The material that follows is necessary to do this service bulletin and can be ordered

from Bombardier Aerospace Regional Aircraft or purchased directly from industry

sources. If the material is ordered from Bombardier Aerospace Regional Aircraft,

there can be some lead time because of shelf life of the material.

CONSUMABLES

SPECIFICATION QUANTITY NAME REFERENCE

MIL−C−85043 As

necessary

Cloths, cleaning,

low lint

05−001 [1]

TT−I−735 As

necessary

Alcohol,

isopropyl

11−004 [1]

[1] Refer to AMM 51−31−00−992−801.

NOTE: To complete this list of consumables, refer to the different tasks and

Appendix A given as references in this service bulletin.

C. Special Tools and Equipment

For a list of special tools and equipment, refer to the different tasks and Appendix A

given as references in this service bulletin.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 19 of 20

Oct 18/2007

Revision B, Dec 22/2010
D. Disposition of Parts

Not applicable.

ALERT SERVICE BULLETIN A670BA−29−011

S.B. A670BA−29−011

Page 20 of 20

Oct 18/2007

Revision B, Dec 22/2010
 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A1 of A9

PROCEDURE 

The procedure contained in this appendix is given as references in the 

ACCOMPLISHEMENT INSTRUCTION of Service Bulletin A670BA-29-011 
Appendix A 

Ultrasonic Inspection of the Accumulator Screw-Caps 

1. General 

A. Function 

Refer to Figure A1. 

This inspection procedure is used to detect subsurface cracks at the internal 

shoulder of the Screw Caps (Gas and Fluid ends, item 2) of the system No. 1 or 

No. 2 Accumulator (1). 

B. Reference Information 

For additional data that is necessary to do this inspection, refer to manuals that 

follow: 

- Nondestructive Testing Manual (NDTM CSP B-010) Part 1, 51-20-004-270-

A01, General Information. 

- Structural Repair Manual (SRM) 

- Aircraft Maintenance Manual (AMM) 

C. Location 

The inspection area is in Zone 310 (Refer to AMM 06-20-00-992-801-AA1). 

D. Parts Examined in this procedure 

DESCRIPTION PART 

NUMBER 

VENDOR 

PART NUMBER 

MATERIAL 

System Accumulator 900096-1 7075-T73 Al Alloy 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A2 of A9
Appendix A 

2. Tools and Equipment 

Refer to Figure A2. 

A. Use the items that follow, or their equivalent (Refer to the NDTM Part 1, 51-

20-004-270-A01). 

NOTE: Equivalent ultrasonic equipment can be used provided that it satisfies 

the requirements of this procedure and is capable of resolving the reference 

notch(es) in the calibration reference standard (CRS) at the required level of 

sensitivity. 

- Ultrasonic flaw detector, Sonatest Model: UFDS 

- Potted angle beam contact transducer, 70 degrees refractive angle in 

aluminum, 5.0 MHz frequency, contact surface 0.32 in. (8.13 mm) by 0.70 in. 

(17.78 mm) 

UTX Model: CX-118 

- Microdot to BNC type coaxial cable. 

- Tactair Calibration Reference Standard: T11330, similar in geometry as the 

part to be inspected containing several electrical discharge machined (EDM) 

notches (Figure A2). 

- Inspectech LTD: Gorptech Industrial Ultrasonic Couplant Gel. 

B. Location 

3. Inspection for Subsurface Cracks on the Screw Cap Inner Shoulder of the 

Accumulator 

A. Cleaning 

Refer to Figure A1. 

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU USE 

CHLORINATED OR OTHER SOLVENTS TO CLEAN THE WORK SURFACES. 

MAKE SURE THAT THERE IS A SUFFICIENT SUPPLY OF FRESH AIR. USE 

PROTECTIVE CLOTHING AND SAFETY GLASSES. IF THIS IS NOT DONE, 

INJURIES TO PERSONS CAN OCCUR. 

(1) With solvent, clean the entire (360 degrees around) tapered section of the 

screw caps where the transducer is to make contact during the inspection. 

Refer to AMM 51-26-00-110-801. Refer to Figure A1. 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A3 of A9
Appendix A 

B. Equipment Calibration 

NOTE: Make sure that you follow the manufacturer's instructions when 

operating the test equipment. 

NOTE: Do not allow the ultrasonic couplant to dry on the inspection surface. If 

necessary, add more couplant, to replenish the surface. 

Refer to Figure A2, and Figure A3. 

(1) Attach the 70 degree angle beam transducer to coaxial cable and connect the 

cable to the ultrasonic instrument. 

(2) Turn on the power and set the ultrasonic instrument to pulse-echo test mode 

and 5 MHz test frequency. 

(3) Apply couplant to tapered section of the calibration reference standard (CRS) 

T11330. 

(4) Place the transducer firmly to the tapered section on the CRS such that 

sound beam is directed towards the internal shoulder of the screw cap. 

(5) Manipulate the transducer to obtain a maximized amplitude signal from EDM 

notch A (NA) and adjust the instrument GAIN control to set the signal at 80% full 

screen height (FSH). 

(6) Adjust and position the leading edge of the notch signal at 50% of the 

horizontal baseline and the signal from the external shoulder at approximately 

75% of the horizontal baseline. 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A4 of A9
Appendix A 

C. Inspection Procedure 

Refer to Figure A1, Figure A3, and Figure A4. 

(1) After calibration as outlined in section 3.B., apply an even layer of couplant to 

the tapered section on the brake accumulator screw cap (2 caps per 

accumulators) to be inspected. 

(2) Place the transducer firmly to the tapered section of the Screw Cap such that 

the sound beam is towards to internal shoulder. 

(3) Manipulate the transducer towards and away from the shoulder with a slight 

swiveling motion. 

(4) Inspect 360 degrees around the cap for cracks. 

D. Evaluation of Indications 

(1) Any indication with an amplitude signal of 60% FSH or greater at 

approximately 50% of the horizontal baseline limit is considered a suspect 

indication and is cause for further evaluation. 

(2) Verify and ensure the indication is not from the external shoulder i.e. the 

transducer moved too forward to the edge of the external shoulder or the 

baseline has shifted accidentally. 

(3) If the indication is a crack, determine the approximate length of crack by 

scanning in both directions from the peak signal until the signal has dropped 

to 40% FSH and mark the center point of the transducer. The circumferential 

crack length is the distance between the two points. 

E. Acceptance or Rejection Criteria: 

(1) All distinct indications with an amplitude signal of 60% FSH or greater 

appearing at approximately 50% of the horizontal baseline is classified as a 

crack indication and is caused for rejection. 

(4) Record results. 

4. Close-out 

A. Refer to the Close-Out section of Alert Service Bulletin A670BA-29-011 

B. PART B. 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A5 of A9
Appendix A 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A6 of A9ba4873a01.cgm

1

A

B

C

2. Screw cap.

LEGEND

1. System accumulator.

D

D

A NO.1 SYSTEM

B NO.2 SYSTEM

1

1

2

1

2

C

C

D

1 Inspection area.

NOTE

Systems Accumulator Screw Cap Locations 

Figure A1 
Appendix A 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A7 of A9ba4396a01.cgm, lr, oct12/2006

0.050 in.

(1.27 mm)

DP

NOTCH B

0.075 in.

(1.90 mm)

BOTH SIDES

NOTCH A NOTCH C

0.050 in.

(1.27 mm)

BOTH SIDES

0.050 in.

(1.27 mm)

DP

0.050 in.

(1.27 mm)

DP

0.100 in.

(2.54 mm)

BOTH SIDES

45 DEGREE

45 DEGREE

C

D

E

C D E

A A

B

B

A A

B B

Tactair CRS Number T11330 

Figure A2 
Appendix A 

CRT Display Calibration and Familiarization 

Figure A3 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A8 of A9
Appendix A 

Oct 18/2007 APPENDIX A

Revision A, Jul 27/2010 Page A9 of A9 ba4398a01.cgm, lr, oct12/2006

EXTERNAL

SHOULDER

POTENTIAL CRACK

AT INTERNAL

SHOULDER

TRANSDUCER

PLACEMENT AND

SCANNING MOVEMENT

Transducer placement 

Figure A4 
THANK YOU FOR ANSWERING THIS EVALUATION FORM 

UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 

450-476-7300 

SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET 

(YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS) 

SERVICE BULLETIN : 670BA-29-011 ISSUE: B

 STRONGLY DISAGREE NEUTRAL AGREE STRONGLY 

 DISAGREE AGREE 

• Instructions to do the Service Bulletin 

were accurate. 

Comments:

    

• Illustration(s), figure(s), picture(s) and/or 

kit drawing(s) were helpful to carry out 

instructions. 

Comments:

    

• If a parts kit was required, did the kit 

contents received agree with the 

contents listed in the bulletin? 

Comments: 

    

• Aircraft hands-on work was 

accomplished in estimated time. 

 Comments:

    

• Overall, I was satisfied with this Service 

Bulletin. 

 Comments: 

    

PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: 

OPERATOR: NAME (Please print) 

SERVICE CENTER: TELEPHONE: 

AIRCRAFT SERIAL NO.: FACSIMILE: 

DATE OF SB 

INCORPOARTION