Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations 64633 

electric furnaces and boilers, BOH = 

100(2080)(0.77)DHR/(Ein 3.412)(AFUE)) 

Where: 

100 = to express a percent as a decimal 

2,080 = as specified in 10.2.1 of this 

appendix 

0.77 = as specified in 10.2.1 of this appendix 

DHR = as defined in 10.2.1 of this appendix 

3.412 = conversion to express energy in terms 

of KBtu instead of kilowatt-hours 

AFUE = as defined in 11.1 of ANSI/ASHRAE 

Standard 103—1993 (incorporated by 

reference, see § 430.3) in percent 

E in = Steady-state electric rated power, in 

kilowatts, from section 9.3 of ANSI/ 

ASHRAE Standard 103—1993 

(incorporated by reference, see § 430.3). 

[FR Doc. 2010–26369 Filed 10–19–10; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1036; Directorate 

Identifier 2009–NM–247–AD; Amendment 

39–16480; AD 2010–22–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767–200, –300, and 

–300F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires repetitive inspections 

for fatigue cracking and corrosion of the 

upper link fuse pin of the nacelle struts, 

and related investigative and corrective 

actions if necessary. The existing AD 

also provides terminating action for the 

repetitive inspections. This AD revises 

certain criteria for the terminating 

action. This AD was prompted by two 

reports of cracked upper link fuse pins. 

We are issuing this AD to prevent 

fatigue cracking or corrosion of the 

upper link fuse pin, which could result 

in failure of the fuse pin and consequent 

reduced structural integrity of the 

nacelle strut and possible separation of 

the strut and engine from the airplane 

during flight. 

DATES: This AD is effective November 4, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 4, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 5, 2009 (74 FR 

50692, October 1, 2009). 

We must receive comments on this 

AD by December 6, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 18, 2009, we issued AD 

2009–20–09, Amendment 39–16032 (74 

FR 50692, October 1, 2009), for certain 

Model 767–200, –300, and –300F series 

airplanes. That AD requires repetitive 

inspections for fatigue cracking and 

corrosion of the upper link fuse pin of 

the nacelle struts, and related 

investigative and corrective actions if 

necessary. That AD also provides 

terminating action for the repetitive 

inspections. That AD resulted from two 

reports of cracked upper link fuse pins. 

We issued that AD to prevent fatigue 

cracking or corrosion of the upper link 

fuse pin, which could result in failure 

of the fuse pin and consequent reduced 

structural integrity of the nacelle strut 

and possible separation of the strut and 

engine from the airplane during flight. 

Actions Since Existing AD Was Issued 

We have learned that paragraph (h) of 

AD 2009–20–09 incorrectly identifies 

the pin replacement as acceptable for 

compliance with the optional strut 

modification specified in paragraph (g) 

of that AD. Rather, replacing the pin 

terminates only the repetitive 

inspections of the pins as required by 

paragraph (g) of this AD; replacing the 

pin does not terminate the requirement 

for the strut modification. We have 

removed credit for replacement of the 

fuse pins with new fuse pins from 

paragraph (h) of the existing AD 

(specified as paragraph (i) in this AD) 

because it is not a terminating action. 

We have added new paragraph (j) in this 

AD to specify that replacement of the 

fuse pins terminates the repetitive 

inspection requirements of paragraph (g) 

of this AD, and the strut modification is 

still required. 

We have also revised paragraph (b) of 

this AD to clarify that certain 

requirements of this AD terminate 

certain requirements of AD 2000–19–09, 

Amendment 39–11910 (65 FR 58641, 

October 2, 2000), and AD 2004–16–12, 

Amendment 39–13768 (69 FR 51002, 

August 17, 2004). 

Explanation of Additional Paragraph in 

the AD 

We have added a new paragraph (d) 

to this AD to provide the Air Transport 

Association (ATA) of America subject 

code 54: Nacelles/Pylons. This code is 

added to make this AD parallel with 

other new AD actions. We have 

reidentified subsequent paragraphs 

accordingly. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 


emcdonald on DSK2BSOYB1PROD with RULES
64634 Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations 

AD Requirements 

This AD requires repetitive 

inspections for fatigue cracking and 

corrosion of the upper link fuse pin of 

the nacelle struts, and related 

investigative and corrective actions if 

necessary. This AD also provides 

terminating action for the repetitive 

inspections. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because this AD shortens the time 

for the repetitive intervals. Therefore, 

we find that notice and opportunity for 

prior public comment are impracticable 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2010–1036; Directorate Identifier 2009– 

NM–247–AD;’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 354 

airplanes of U.S. registry. This new AD 

adds no new costs to affected operators. 

The current costs for this AD are 

repeated for the convenience of affected 

operators, as follows: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection of fuse pins (requirement of AD 2009–20– 

09).

4 work-hours × $85 per hour 

= $340 per inspection cycle.

$0 $340 per inspection cycle ..... $120,360 per inspection cycle. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ The FAA amends § 39.13 by removing 

airworthiness directive (AD) 2009–20– 

09, Amendment 39–16032 (74 FR 

50692, October 1, 2009), and adding the 

following new AD: 

2010–22–01 The Boeing Company: 

Amendment 39–16480; Docket No. 

FAA–2010–1036; Directorate Identifier 

2009–NM–247–AD. 

Effective Date 

(a) This AD is effective November 4, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–20–09, 

Amendment 39–16032. Certain requirements 

of this AD terminate certain requirements of 

AD 2000–19–09, Amendment 39–11910, and 

AD 2004–16–12, Amendment 39–13768. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 767–200, –300, and –300F 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

767–54A0074, Revision 1, dated April 24, 

2008. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Unsafe Condition 

(e) This AD was prompted by two reports 

of cracked upper link fuse pins. We are 

issuing this AD to prevent fatigue cracking or 

corrosion of the upper link fuse pin, which 

could result in failure of the fuse pin and 

consequent reduced structural integrity of the 

nacelle strut and possible separation of the 

strut and engine from the airplane during 

flight. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 


emcdonald on DSK2BSOYB1PROD with RULES
Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations 64635 

Restatement of Requirements of AD 2009– 

20–09, With Revised Credit Provisions in 

Paragraph (I) of This AD 

Initial and Repetitive Inspections/ 

Investigative and Corrective Actions 

(g) Inspect the upper link fuse pin of the 

nacelle struts for fatigue cracking and 

corrosion at the applicable time specified in 

Table 1 of this AD. Do the applicable 

inspection by doing all the applicable actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–54A0074, Revision 1, dated April 24, 

2008; and do all applicable related 

investigative and corrective actions before 

further flight. Repeat the applicable 

inspection at intervals not to exceed 3,000 

flight cycles or 24 months, whichever is first, 

until the requirements of paragraph (h) of 

this AD have been done. 

TABLE 1—COMPLIANCE TIMES

Engine type 

At the later of: 

Initial inspection threshold Grace period 

JT9D .................. 14,000 total flight cycles .......................... Within 3,000 flight cycles or 18 months after November 5, 2009 (the effective 

date of AD 2009-20–09), whichever is first. 

CF6–80A ........... 24,000 total flight cycles .......................... Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. 

PW4000 ............. 8,000 total flight cycles ............................ Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. 

CF6–80C2 ......... 10,000 total flight cycles .......................... Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. 

RB211 ................ 24,000 total flight cycles .......................... Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. 

Note 1: The upper link inspections can be 

done with the pylon and/or engine in any 

position. 

Note 2: In paragraph 3.B, Steps 4.b.(1)(a) 

and 4.b.(2)(b)(2){a} of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–54A0074, Revision 1, dated April 24, 

2008, the procedures specify to apply two 

layers of Boeing Material Specification (BMS) 

10–11 primer to the inside surface of the fuse 

pin if no crack indication is found. However, 

two layers of primer are only necessary to 

touch up bare areas on the fuse pin if no 

crack indication is found. 

Terminating Action in AD 2000–19–09, 

Amendment 39–11910, and AD 2004–16–12, 

Amendment 39–13768 

(h) Accomplishment of the modification 

specified in paragraph (h)(1) or (h)(2) of this 

AD, as applicable, terminates the inspections 

required by paragraph (g) of this AD. 

(1) For Model 767 series airplanes powered 

by Rolls-Royce RB211 series engines, as 

identified in AD 2000–19–09: Modification of 

the nacelle strut and wing structure, as 

required by paragraphs (a) and (b) of AD 

2000–19–09. 

(2) For Model 767–200, –300, and –300F 

series airplanes powered by Pratt & Whitney 

and General Electric engines, as identified in 

AD 2004–16–12: Modification of the nacelle 

strut and wing structure, as required by 

paragraphs (a), (b), (d), and (e) of AD 2004– 

16–12. 

Credit for Inspection Done Using Previous 

Service Information 

(i) Inspection of the fuse pins before 

November 5, 2009, in accordance with 

Boeing Service Bulletin 767–54–0074, dated 

March 27, 1997, is acceptable for compliance 

with the inspections required by paragraph 

(g) of this AD, except that operator’s 

equivalent procedures are not allowed. 

New Requirements of This AD 

Optional Terminating Action for Inspections 

(j) Replacement of the fuse pins with new 

fuse pins (not serviceable fuse pins), in 

accordance with Boeing Service Bulletin 

767–54–0074, dated March 27, 1997; or 

Boeing Alert Service Bulletin 767–54A0074, 

Revision 1, dated April 24, 2008; terminates 

the repetitive inspections of the fuse pins 

required by paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

AMOCs that specified using new pins (not 

serviceable pins) approved previously in 

accordance with AD 2009–20–09, 

Amendment 39–16032, are approved as 

AMOCs for the corresponding provisions of 

paragraph (h) of this AD. 

Related Information 

(l) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6577; fax (425) 

917–6590. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin 767–54A0074, Revision 1, dated 

April 24, 2008, to do the actions required by 

this AD, unless the AD specifies otherwise. 

If you accomplish the optional terminating 

actions specified in this AD, you must use 

Boeing Alert Service Bulletin 767–54A0074, 

Revision 1, dated April 24, 2008; or Boeing 

Service Bulletin 767–54–0074, dated March 

27, 1997; to perform those actions, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Service Bulletin 767–54–0074, dated 

March 27, 1997, under 5 U.S.C. 552(a) and 

1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Alert Service Bulletin 

767–54A0074, Revision 1, dated April 24, 

2008, on November 5, 2009 (74 FR 50692, 

October 1, 2009). 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/

ibr_locations.html. 


emcdonald on DSK2BSOYB1PROD with RULES
64636 Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations 

Issued in Renton, Washington, on October 

6, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–26224 Filed 10–19–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1037; Directorate 

Identifier 2010–NM–202–AD; Amendment 

39–16481; AD 2010–22–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Seven cases of on-ground hydraulic 

accumulator screw cap/end cap failure have 

been experienced on CL–600–2B19 

aeroplanes, resulting in the loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. * * * 

* * * * * 

A detailed analysis of the calculated line 

of trajectory of a failed screw cap/end cap for 

each of the accumulators has been 

conducted, resulting in the identification of 

several areas where systems and/or structural 

components could potentially be damaged. 

Although all of the failures to date have 

occurred on the ground, an in-flight failure 

affecting such components could potentially 

have an adverse effect on the controllability 

of the aeroplane. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

November 4, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 4, 2010. 

We must receive comments on this 

AD by December 6, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Alfano, Aerospace 

Engineer, Airframe and Mechanical 

Systems Branch, ANE–171, FAA, New 

York Aircraft Certification Office (ACO), 

1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7340; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–24, 

dated August 3, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Seven cases of on-ground hydraulic 

accumulator screw cap/end cap failure have 

been experienced on CL–600–2B19 

aeroplanes, resulting in the loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. The lowest number of flight cycles 

accumulated at the time of failure, to date, 

has been 6,991 flight cycles. 

The part numbers (P/N) of the 

accumulators currently installed on CL–600– 

2B19 aeroplanes are 601R75138–1 (08– 

60163–001 or 08–60163–002) [Hydraulic 

System No. 1, Hydraulic System No. 2, 

Inboard Brake and Outboard Brake 

accumulators] and 601R75138–3 (08–60164– 

001 or 08–60164–002) [Hydraulic System No. 

3 accumulator]. 

A detailed analysis of the calculated line 

of trajectory of a failed screw cap/end cap for 

each of the accumulators has been 

conducted, resulting in the identification of 

several areas where systems and/or structural 

components could potentially be damaged. 

Although all of the failures to date have 

occurred on the ground, an in-flight failure 

affecting such components could potentially 

have an adverse effect on the controllability 

of the aeroplane. 

This directive gives instructions to amend 

the Airplane Flight Manual (AFM), remove 

two accumulators (Hydraulic System No. 2 

and No. 3) from the aeroplane and conduct 

repetitive ultrasonic inspections [for cracks] 

of the Hydraulic System No. 1, Inboard Brake 

and Outboard Brake accumulators that are 

not identified by the letter ‘‘T’’ after the serial 

number (S/N) on the identification plate for 

cracks until they are replaced by new 

accumulators P/N 601R75139–1 (11093–4). 

Required actions also include 

deactivating the hydraulic system No. 3 

accumulator. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Bombardier has issued Canadair 

Regional Jet Temporary Revision (TR) 

RJ/186–1, dated August 24, 2010, to the 

Limitations section, Normal Procedures 

section, and Abnormal Procedures 

section of the Canadair Regional Jet 

Airplane Flight Manual (AFM), CSP A– 

012. Canadair Regional Jet TR RJ/186–1, 

dated August 24, 2010, advises the 

flightcrew that for certain airplanes the 

hydraulic 3B pump is selected ‘‘on’’ 

instead of ‘‘auto’’ for all phases of flight. 

Bombardier has issued the service 

information in the following table: 

BOMBARDIER SERVICE BULLETINS

Document Revision Date 

Bombardier Alert Service Bulletin A601R–29–029, including Appendix A, dated October 18, 

2007.

B ................................ May 11, 2010. 

Bombardier Alert Service Bulletin A601R–29–031 ......................................................................... A ................................ March 26, 2009. 


emcdonald on DSK2BSOYB1PROD with RULES