Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 38065 

Related Information 

(i) Refer to MCAI Civil Aviation Authority 

of Israel (CAAI) Airworthiness Directive 57– 

10–06–18, dated July 27, 2010; and 

Gulfstream Service Bulletin 200–51–366, 

dated March 30, 2010, including Appendix 

A: Israel Aircraft Industries Document 

IS951400E, Radiographic Inspection of SelfLocking Nut P/N MS21042L3, Revision A, 

dated January 25, 2010; for related 

information. 

Issued in Renton, Washington, on June 21, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–16314 Filed 6–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0648; Directorate 

Identifier 2010–NM–276–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed 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. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by August 15, 2011. 

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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; 

e-mail thd.crj@aero.bombardier.com; 

Internet http://www.bombardier.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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0648; Directorate Identifier 

2010–NM–276–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

On October 7, 2010, we issued AD 

2010–22–02, Amendment 39–16481 (75 

FR 64636, October 20, 2010). That AD 

required actions intended to address an 

unsafe condition on Bombardier, Inc. 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) airplanes. 

Since we issued AD 2010–22–02, we 

have determined that further 

rulemaking is necessary. While AD 

2010–22–02 did not require the removal 

of the hydraulic system No. 3 

accumulator, or replacement of the 

hydraulic system No. 1, inboard brake, 

and outboard brake accumulators, as 

specified in Part IV and Part VII of the 

Canadian Airworthiness Directive CF– 

2010–24, dated August 3, 2010, this 

NPRM proposes to require those actions. 

Also, for airplanes on which 

Bombardier Service Bulletin 601R–29– 

035, dated May 11, 2010, is done and 

reducer having part number 

MS21916D8–6 installed, this NPRM 

proposes to require replacing the 

reducer with a new reducer. We have 

coordinated with Transport Canada 

Civil Aviation (TCCA) on this issue. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 601R–29–035, Revision A; and 

Service Bulletin 601R–32–107, Revision 

B; both dated December 8, 2010. The 

actions described in this service 

information as outlined in the 

‘‘Discussion’’ section above, are 

intended to correct the unsafe condition 

identified in the MCAI. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 2010–22–02. Since 

AD 2010–22–02 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 


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38066 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2010–22–02 

Corresponding 

requirement in this 

proposed AD 

paragraph (j) paragraph (o) 

paragraph (k) paragraph (j) 

paragraph (l) paragraph (k) 

paragraph (m) paragraph (p) 

paragraph (n) paragraph (l) 

paragraph (o) paragraph (m) 

paragraph (p) paragraph (r) 

paragraph (q) paragraph (n) 

paragraph (r) paragraph (s) 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 605 products of U.S. 

registry. 

The actions that are required by AD 

2010–22–02 and retained in this 

proposed AD take about 19 work-hours 

per product, at an average labor rate of 

$85 per work hour. Based on these 

figures, the estimated cost of the 

currently required actions is $1,615 per 

product. 

We estimate that it would take about 

14 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $3,054 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these costs. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $2,567,620, or $4,244 per 

product. 

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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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] 

2. The FAA amends § 39.13 by 

removing Amendment 39–16481 (75 FR 

64636, October 20, 2010) and adding the 

following new AD: 

Bombardier, Inc.: Docket No. FAA–2011– 

0648; Directorate Identifier 2010–NM– 

276–AD. 

Comments Due Date 

(a) We must receive comments by August 

15, 2011. 

Affected ADs 

(b) This AD supersedes AD 2010–22–02, 

Amendment 39–16481. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model CL–600–2B19 (Regional Jet Series 100 

& 440) airplanes, certificated in any category, 

serial numbers 7003 and subsequent. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29 and 32: Hydraulic Power 

and Landing Gear, respectively. 

Reason 

(e) The mandatory continuing 

airworthiness information (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. * * * 

* * * * * 

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. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 


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Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 38067 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2010– 

22–02, With Revised Service Information 

Airplane Flight Manual (AFM) Revision 

(g) Within 30 days after November 4, 2010 

(the effective date of AD 2010–22–02), revise 

the Limitations section, Normal Procedures 

section, and Abnormal Procedures section of 

the AFM by incorporating Canadair Regional 

Jet Temporary Revision (TR) RJ/186–1, dated 

August 24, 2010, into the applicable section 

of Canadair Regional Jet AFM, CSP A–012. 

Thereafter, except as provided by paragraph 

(t) of this AD, no alternative actions specified 

in Canadair Regional Jet TR RJ/186–1, dated 

August 24, 2010, may be approved. 

Note 1: The actions required by paragraph 

(g) of this AD may be done by inserting a 

copy of Canadair Regional Jet TR RJ/186–1, 

dated August 24, 2010, into the applicable 

section of the Canadair Regional Jet AFM, 

CSP A–012. When this TR has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and this TR removed, provided that the 

relevant information in the general revision 

is identical to that in Canadair Regional Jet 

TR RJ/186–1, dated August 24, 2010. 

Deactivation of the Hydraulic System No. 3 

Accumulator 

(h) Within 250 flight cycles after November 

4, 2010, deactivate the hydraulic system No. 

3 accumulator, in accordance with Part A of 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A601R– 

29–031, Revision A, dated March 26, 2009. 

Doing the removal of the hydraulic system 

No. 3 accumulator in paragraph (o) of this AD 

is an alternate method of compliance with 

the requirements of this paragraph. The 

actions in this paragraph apply to all 

accumulators in hydraulic system No. 3. 

Removal of the Hydraulic System No. 2 

Accumulator 

(i) Within 500 flight cycles after November 

4, 2010, remove the hydraulic system No. 2 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–29–032, Revision A, 

dated January 26, 2010. The actions in this 

paragraph apply to all accumulators in 

hydraulic system No. 2. 

Initial and Repetitive Ultrasonic Inspection 

of Hydraulic System No. 1, Inboard Brake, 

and Outboard Brake Accumulators 

(j) For hydraulic system No. 1, inboard 

brake, and outboard brake accumulators 

having P/N 601R75138–1 (08–60163–001 or 

08–60163–002): At the applicable 

compliance times specified in paragraph (l) 

of this AD, do the inspections required by 

paragraphs (j)(1) and (j)(2) of this AD. Repeat 

the inspections for each accumulator having 

P/N 601R75138–1 (08–60163–001 or 08– 

60163–002) thereafter at intervals not to 

exceed 500 flight cycles until the 

replacement specified in this paragraph is 

done or the replacement specified in 

paragraph (p) of this AD is done. If any crack 

is found, before further flight, replace the 

accumulator with a new accumulator having 

P/N 601R75138–1 (08–60163–001 or 08– 

60163–002) and having the letter ‘‘T’’ after 

the serial number on the identification plate, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in table 1 or table 2 of this AD. 

(1) Do an ultrasonic inspection for cracks 

on each accumulator, in accordance with Part 

B of the Accomplishment Instructions of the 

applicable service bulletin identified in table 

1 of this AD. 

TABLE 1—BOMBARDIER SERVICE INFORMATION FOR ACCUMULATOR INSPECTION

Accumulator Document Revision Date 

Hydraulic System No. 1 ................. Bombardier Alert Service Bulletin A601R–29–029, including Appendix 

A, dated October 18, 2007.

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

Inboard and Outboard Brake ......... Bombardier Alert Service Bulletin A601R–32–103, including Appendix 

A, Revision A, dated October 18, 2007.

D ............ May 11, 2010. 

(2) Do an ultrasonic inspection for cracks 

on the screw cap, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in table 

2 of this AD. 

TABLE 2—BOMBARDIER SERVICE INFORMATION FOR SCREW CAP INSPECTION

Accumulator Document Revision Date 

Hydraulic System No. 1 ................. Bombardier Service Bulletin 601R–29–033, including Appendix A, 

dated May 5, 2009.

A ............ May 11, 2010. 

Inboard and Outboard Brake ......... Bombardier Service Bulletin 601R–32–106, including Appendix A ....... A ............ May 11, 2010. 

(k) For hydraulic system No. 1, inboard 

brake, and outboard brake accumulators 

having P/N 601R75138–1 (08–60163–001 or 

08–60163–002): Do the inspections specified 

in paragraph (j) of this AD at the applicable 

time in paragraph (k)(1), (k)(2), and (k)(3) of 

this AD. 

(1) For any accumulator not having the 

letter ‘‘T’’ after the serial number on the 

identification plate and with more than 4,500 

flight cycles on the accumulator as of 

November 4, 2010: Inspect within 500 flight 

cycles after November 4, 2010. 

(2) For any accumulator not having the 

letter ‘‘T’’ after the serial number on the 

identification plate and with 4,500 flight 

cycles or less on the accumulator as of 

November 4, 2010: Inspect prior to the 

accumulation of 5,000 flight cycles on the 

accumulator. 

(3) If it is not possible to determine the 

flight cycles accumulated for any 

accumulator not having the letter ‘‘T’’ after 

the serial number on the identification plate: 

Inspect within 500 flight cycles after 

November 4, 2010. 

Note 2: For any accumulator having P/N 

601R75138–1 (08–60163–001 or 08–60163– 

002) and the letter ‘‘T’’ after the serial 

number on the identification plate, or if the 

accumulator P/N is not listed in paragraph (j) 

of this AD, the inspection specified in 

paragraph (j) of this AD is not required. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(l) Deactivating the hydraulic system No. 3 

accumulator before November 4, 2010, in 

accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A601R–29–031, dated 

December 23, 2008, is acceptable for 

compliance with the requirements of 

paragraph (h) of this AD. 

(m) Removing the hydraulic system No. 2 

accumulator in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–29–032, dated 

November 12, 2009, before November 4, 

2010, is acceptable for compliance with the 

requirements of paragraph (i) of this AD. 

(n) An ultrasonic inspection for cracks 

done before November 4, 2010, in accordance 

with Part B of the Accomplishment 

Instructions of the applicable service bulletin 

identified in table 3 of this AD, or the 

Accomplishment Instructions of the 

applicable service bulletin identified in table 

4 of this AD, is acceptable for compliance 


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38068 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 

with the corresponding ultrasonic inspection 

required by paragraph (j) of this AD. 

TABLE 3—BOMBARDIER CREDIT SERVICE INFORMATION FOR ACCUMULATOR INSPECTION

Document Revision Date 

Bombardier Alert Service Bulletin A601R–29–029 .............................................. Original .................................................. October 18, 2007. 

Bombardier Alert Service Bulletin A601R–29–029 .............................................. A ............................................................ November 12, 2009. 

Bombardier Alert Service Bulletin A601R–32–103 .............................................. Original .................................................. November 21, 2006. 

Bombardier Alert Service Bulletin A601R–32–103 .............................................. A ............................................................ March 7, 2007. 

Bombardier Alert Service Bulletin A601R–32–103 .............................................. B ............................................................ October 18, 2007. 

Bombardier Alert Service Bulletin A601R–32–103 .............................................. C ........................................................... February 26, 2009. 

TABLE 4—BOMBARDIER CREDIT SERVICE INFORMATION FOR SCREW CAP INSPECTION

Document Revision Date 

Bombardier Service Bulletin 601R–29–033 ......................................................... Original .................................................. May 5, 2009. 

Bombardier Service Bulletin 601R–32–106 ......................................................... Original .................................................. May 5, 2009. 

New Requirements of This AD 

Removal of the Hydraulic System No. 3 

Accumulator 

(o) Within 1,000 flight cycles after the 

effective date of this AD, remove the 

hydraulic system No. 3 accumulator, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A601R–29–031, 

Revision A, dated March 26, 2009. Doing the 

action in this paragraph terminates the 

requirements of paragraph (h) of this AD. 

Replacement of the Hydraulic System No. 1, 

Inboard Brake, and Outboard Brake 

Accumulators 

(p) Within 4,000 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first, replace any hydraulic system No. 

1, inboard brake, or outboard brake 

accumulator having P/N 601R75138–1 (08– 

60163–001 or 08–60163–002), with a new 

accumulator having P/N 601R75139–1 

(11093–4), in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in table 

5 of this AD. Doing the action in this 

paragraph terminates the requirement for the 

inspections in paragraph (j) of this AD for 

that accumulator. As of the effective date of 

this AD, use only Bombardier Service 

Bulletin 601R–29–035, Revision A; or 601R– 

32–107, Revision B; both dated December 8, 

2010; as applicable. 

TABLE 5—BOMBARDIER SERVICE INFORMATION FOR ACCUMULATOR REPLACEMENT

Accumulator Document Revision Date 

Hydraulic System No. 1 ........ Bombardier Service Bulletin 601R–29–035 ....................... Original ................................ May 11, 2010. 

Hydraulic System No. 1 ........ Bombardier Service Bulletin 601R–29–035 ....................... A .......................................... December 8, 2010. 

Inboard and Outboard Brake Bombardier Service Bulletin 601R–32–107 ....................... A .......................................... June 17, 2010. 

Inboard and Outboard Brake Bombardier Service Bulletin 601R–32–107 ....................... B .......................................... December 8, 2010. 

Action for Airplanes on Which Bombardier 

Service Bulletin 601R–29–035, Dated May 

11, 2010 Is Done and Reducer Having P/N 

MS21916D8–6 Is Installed 

(q) For airplanes on which Bombardier 

Service Bulletin 601R–29–035, dated May 11, 

2010, is done, and reducer having P/N 

MS21916D8–6 is installed: Within 1,200 

flight cycles or 8 months after the effective 

date of this AD, replace the reducer of the 

hydraulic system No. 1 with a new reducer 

in accordance with Part B of Bombardier 

Service Bulletin 601R–29–035, Revision A, 

dated December 8, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(r) Removing the hydraulic system No. 3 

accumulator in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin A601R–29–031, dated 

December 23, 2008, before November 4, 2010, 

is acceptable for compliance with the 

requirements of paragraph (o) of this AD. 

(s) Replacing any hydraulic system No. 1, 

inboard brake, or outboard brake accumulator 

before November 4, 2010, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–32–107, 

dated May 11, 2010, is acceptable for 

compliance with the corresponding 

requirements of paragraph (p) of this AD. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: The 

actions specified in Canadian Airworthiness 

Directive CF–2010–24, dated August 3, 2010, 

apply only to Tactair accumulators. The 

actions required by paragraphs (h), (i), and 

(o) of this AD apply to all accumulators in 

the positions specified in paragraphs (h), (i), 

and (o) of this AD. 

Note 4: While Canadian Airworthiness 

Directive CF–2010–24, dated August 3, 2010, 

does not require replacement of the reducer 

of the hydraulic system No. 1 with a new 

reducer, paragraph (q) of this AD does. 

Other FAA AD Provisions 

(t) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to Attn: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(u) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–24, dated August 3, 2010; 

Canadair Regional Jet Temporary Revision 

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

Canadair Regional Jet Airplane Flight 


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Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 38069 

Manual, CSP A–012; and the service bulletins listed in table 6 of this AD; for 

related information. 

TABLE 6—RELATED SERVICE INFORMATION

Document Revision Date 

Bombardier Alert Service Bulletin A601R–29–029 .............................................. B ............................................................ May 11, 2010. 

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

Bombardier Alert Service Bulletin A601R–32–103 .............................................. D ........................................................... May 11, 2010. 

Bombardier Service Bulletin 601R–29–032 ......................................................... A ............................................................ January 26, 2010. 

Bombardier Service Bulletin 601R–29–033 ......................................................... A ............................................................ May 11, 2010. 

Bombardier Service Bulletin 601R–29–035 ......................................................... A ............................................................ December 8, 2010. 

Bombardier Service Bulletin 601R–32–106 ......................................................... A ............................................................ May 11, 2010. 

Bombardier Service Bulletin 601R–32–107 ......................................................... B ............................................................ December 8, 2010. 

Issued in Renton, Washington, on June 16, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–16365 Filed 6–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0647; Directorate 

Identifier 2010–NM–193–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes) and A310 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

Surface defects were visually detected on 

the rudder of an Airbus A319 and an A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A310 and A300–600 

aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by August 15, 2011. 

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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS– 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0647; Directorate Identifier 

2010–NM–193–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0144, 

dated July 16, 2010 (referred to after this 

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

condition for the specified products. 

The MCAI states: 

Surface defects were visually detected on 

the rudder of an Airbus A319 and an A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 


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