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 SHEETHydraulic 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 22/2010D. 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 22/2010APPLICABLE 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 22/2010APPLICABLE 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 22/2010TABLE 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 22/2010TABLE 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 22/2010G. 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 22/20102. 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 22/2010Refer 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 22/2010ba4874a01.cgm A B

2. Screw cap. LEGEND 1. System accumulator. C

NO.2 SYSTEM B

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 22/2010ba4874a02.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 Inspection area. 1 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 22/2010C. 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 22/20103. 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 22/2010D. 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 22/2010Oct 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 det ect 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, re fer to manuals that follow: - Nondestructive Testing Manual (NDT M 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 follo w, or their equivalent (Ref er to the NDTM Part 1, 51- 20-004-270-A01). NOTE: Equivalent ultrasoni c equipment can be used pr ovided that it satisfies the requirements of this procedure and is capable of resolving the reference notch(es) in the calibration reference st andard (CRS) at the required level of sensitivity.
- Ultrasonic flaw detecto r, Sonatest Model: UFDS - Potted angle beam contact transduc er, 70 degrees refractive angle in aluminum, 5.0 MHz frequency, contact surf ace 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 Standar d: T11330, similar in geometry as the part to be inspected containing several electrical discharge machined (EDM) notches (Figure A2). - Inspectech LTD: Gorptech I ndustrial Ultrasonic Couplant Gel. B. Location
3. Inspection for Subsurface Cracks on th e 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 SUFFICI ENT SUPPLY OF FRESH AIR. USE PROTECTIVE CLOTHING AND SAFETY GL ASSES. 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 t he manufacturer's instructions when operating the test equipment.
NOTE: Do not allow the ultr asonic 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 transduc er to coaxial cable and connect the cable to the ultrasonic instrument. (2) Turn on the power and set the ultrasoni c 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 in ternal 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 an d the signal from the external shoulder at approximately 75% of the horiz ontal 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 accu mulator screw cap (2 caps per accumulators) to be inspected. (2) Place the transducer firml y to the tapered section of the Screw Cap such that the sound beam is towards to internal shoulder. (3) Manipulate the transducer towards and aw ay 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 si gnal 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, determi ne 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 distanc e between the two points.

E. Acceptance or Rejection Criteria: (1) All distinct indications with an am plitude signal of 60% FSH or greater appearing at approximately 50% of the horizontal base line 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

NO.2 SYSTEM B
1

1

2 1 2

C

C

D Inspection area. 1 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 A9ba4398a01.cgm, lr, oct12/2006 EXTERNAL SHOULDER

POTENTIAL CRACK AT INTERNAL SHOULDER

TRANSDUCER PLACEMENT AND SCANNING MOVEMENT

Transducer placement Figure A4THANK YOU FOR ANSWERING THIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 450-476-7300 

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