This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

71241 

Vol. 76, No. 222 

Thursday, November 17, 2011 

DEPARTMENT OF AGRICULTURE 

Agricultural Marketing Service 

7 CFR Part 1214 

[Document No. AMS–FV–10–0008–FR–1A] 

RIN 0581–AD00 

Christmas Tree Promotion, Research, 

and Information Order; Stay of 

Regulations 

AGENCY: Agricultural Marketing Service, 

USDA. 

ACTION: Final rule; stay of regulations. 

SUMMARY: On November 8, 2011, a final 

rule was published in the Federal 

Register (76 FR 69094) establishing an 

industry-funded promotion, research, 

and information program for fresh cut 

Christmas trees, effective November 9, 

2011. Due to recent events, the 

regulations are stayed in order to 

provide all interested persons, including 

the Christmas tree industry and the 

general public, an opportunity to 

become more familiar with the program. 

DATES: Effective November 17, 2011 

Subpart A of 7 CFR part 1214 is stayed 

indefinitely. 

FOR FURTHER INFORMATION CONTACT: 

Patricia A. Petrella, Marketing 

Specialist, Research and Promotion 

Division, Fruit and Vegetable Programs, 

AMS, USDA, 1400 Independence 

Avenue SW., Room 1406, Stop 0244, 

Washington, DC 20250–0244; telephone: 

(301) 334–2891; or facsimile: (301) 334– 

2896; or email: 

Patricia.Petrella@ams.usda.gov. 

SUPPLEMENTARY INFORMATION: The 

Department of Agriculture (Department) 

published in the Federal Register on 

November 8, 2011, (76 FR 69094) a final 

rule that established a Christmas Tree 

Promotion, Research, and Information 

Order (Order). This Order was issued 

pursuant to the Commodity Promotion, 

Research, and Information Act of 1996 

(7 U.S.C. 7411–7425). While we are 

confident that the Christmas Tree 

program is compliant with all 

applicable law and supported by the 

domestic Christmas tree industry, the 

program will be stayed to provide 

additional time for the Department to 

reach out to the Christmas Tree industry 

and the public to explain how a 

research and promotion program is a 

producer driven program to support 

American farmers. 

Accordingly, the regulations 

establishing the Order published 

November 8, 2011 (76 FR 69094) are 

stayed indefinitely. 

Authority: 7 U.S.C. 7411–7425. 

Dated: November 14, 2011. 

David R. Shipman, 

Acting Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2011–29713 Filed 11–16–11; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0648; Directorate 

Identifier 2010–NM–276–AD; Amendment 

39–16859; AD 2011–23–08] 

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. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to certain Bombardier, Inc. 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) airplanes. 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. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 4, 2010 (75 FR 

64636, October 20, 2010). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

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 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 29, 2011 (76 FR 38065), 

and proposed to supersede AD 2010– 

22–02, Amendment 39–16481 (75 FR 

64636, October 20, 2010). That NPRM 

proposed to correct an unsafe condition 

for the specified products. 

Since we issued AD 2010–22–02, 

Amendment 39–16481 (75 FR 64636, 

October 20, 2010), we have determined 


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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 

Canadian Airworthiness Directive CF– 

2010–24, dated August 3, 2010, this AD 

requires those actions. Also, for 

airplanes on which Bombardier Service 

Bulletin 601R–29–035, dated May 11, 

2010, is done, and a reducer having part 

number MS21916D8–6 installed, this 

AD requires replacing the reducer with 

a new reducer. We have coordinated 

with Transport Canada Civil Aviation 

(TCCA) on this issue. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request for Restatement of All 

Compliance Requirements of AD 2010– 

22–02, Amendment 39–16481 (75 FR 

64636, October 20, 2010) 

Comair, Inc. (the commenter) 

requested that we revise the NPRM (76 

FR 38065, June 29, 2011) to restate all 

the compliance requirements of AD 

2010–22–02, Amendment 39–16481 (75 

FR 64636, October 20, 2010), and 

reasoned that it is less confusing and 

more accurate to completely restate all 

the compliance requirements of AD 

2010–22–02. The commenter expressed 

that the way the NPRM was written, a 

copy of AD 2010–22–02 must be onhand to fully cross reference between 

AD 2010–22–02 and the NPRM. The 

commenter stated that as an example, 

paragraph (h) of the NPRM, in part, 

states: ‘‘Doing the removal of the 

hydraulic system No. 3 accumulator in 

paragraph (o) of this AD is an alternative 

method of compliance with the 

requirements of this paragraph,’’ but 

that AD 2010–22–02 actually references 

paragraph (j) instead of paragraph (o) of 

the NPRM. The commenter explained 

that the content of paragraphs (j) and 

(m) of AD 2010–22–02 is not included 

in the NPRM. 

We agree to clarify. We have restated 

the requirements of AD 2010–22–02, 

Amendment 39–16481 (75 FR 64636, 

October 20, 2010), in this final rule. We 

provided a table in the Change to 

Existing AD paragraph in the NPRM (76 

FR 38065, June 29, 2011) to identify and 

cross-reference paragraph requirements 

in AD 2010–22–02 with the 

corresponding paragraph requirements 

in this AD. That table did not identify 

the paragraphs that did not change from 

AD 2010–22–02 to the NPRM. The 

actions specified in paragraph (j) of AD 

2010–22–02 are specified in paragraph 

(o) of this AD. The actions specified in 

paragraph (m) of AD 2010–22–02 are 

specified in paragraph (p) of this AD. No 

changes have been made to this AD in 

this regard. 

Request for Clarification of Intent of 

Paragraph (o) of the NPRM (76 FR 

38065, June 29, 2011) 

The commenter requested that action 

specified in paragraph (o) of the NPRM 

(76 FR 38065, June 29, 2011) be 

considered a superseding requirement, 

instead of an ‘‘alternate method of 

compliance’’ for the actions specified in 

paragraph (h) of the NPRM. The 

commenter did not provide a reason for 

this request. 

We agree that the wording in 

paragraph (h) of this final rule should be 

revised to clarify the intent of paragraph 

(o) of this AD. We have revised 

paragraph (h) of this final rule to specify 

that paragraph (o) of this final rule is 

terminating action instead of an 

alternative method of compliance 

(AMOC) for the requirements of 

paragraph (h) of this final rule, by 

replacing ‘‘is an alternate method of 

compliance’’ with ‘‘terminates.’’ 

Request for Consideration of Other 

AMOCs 

The commenter requested that we 

revise the NPRM (76 FR 38065, June 29, 

2011) to allow for previous AMOCs, 

which would, among other actions, 

allow for the relocation of the No. 3 

Accumulator using ‘‘SB 601R–29–0 Rev 

B.’’ The commenter proposed that we do 

this as a separate paragraph or optional 

paragraph, or to include this in 

paragraph (t)(1) of the NPRM. 

For the reasons stated by the 

commenter, we agree to allow for 

previous approved AMOCs in 

accordance with AD 2010–22–02, 

Amendment 39–16481 (75 FR 64636, 

October 20, 2010) in this final rule. We 

have revised paragraph (t)(1) of this 

final rule accordingly. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 605 products of U.S. registry. 

The actions that are required by AD 

2010–22–02, Amendment 39–16481 (75 

FR 64636, October 20, 2010), and 

retained in this AD take about 19 workhours 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 will take about 14 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will 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 parts. 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 

this AD to the 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. 


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Federal Register / Vol. 76, No. 222 / Thursday, November 17, 2011 / Rules and Regulations 71243 

Regulatory Findings 

We determined that 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 this AD: 

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 AD and placed it in the AD docket. 

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 the NPRM (76 FR 38065, June 

29, 2011), 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. 

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] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–16481 (75 FR 

64636, October 20, 2010) and adding the 

following new AD: 

2011–23–08 Bombardier, Inc.: Amendment 

39–16859. Docket No. FAA–2011–0648; 

Directorate Identifier 2010–NM–276–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 22, 2011. 

Affected ADs 

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

Amendment 39–16481 (75 FR 64636, October 

20, 2010). 

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 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2010– 

22–02, Amendment 39–16481 (75 FR 64636, 

OCTOBER 20, 2010), 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, 

Amendment 39–16481 (75 FR 64636, October 

20, 2010)), revise the Limitations section, 

Normal Procedures section, and Abnormal 

Procedures section of the Canadair Regional 

Jet AFM, CSP A–012, 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 this AFM, the 

general revisions may be inserted into this 

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 

terminates 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 Inspections 

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. 


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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 

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 ......................................................................................... .................. October 18, 2007. 

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

Bombardier Alert Service Bulletin A601R–32–103 ......................................................................................... .................. 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 Date 

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

Bombardier Service Bulletin 601R–32–106 .......................................................................................................................... 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 


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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, dated 

December 8, 2010; or Bombardier Service 

Bulletin 601R–32–107, Revision B, 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 ............................ .................. 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 

Alert 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; or Bombardier Service 

Bulletin 601R–32–107, Revision A, dated 

June 17, 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: (1) 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. 

(2) 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. AMOCs approved previously in 

accordance with AD 2010–22–02, 

Amendment 39–16481 (75 FR 64636, October 

20, 2010), are approved as AMOCs for the 

corresponding provisions of 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 

Manual, CSP A–012; Bombardier Alert 

Service Bulletin A601R–29–029, Revision B, 

dated May 11, 2010, including Appendix A, 

dated October 18, 2007; Bombardier Alert 

Service Bulletin A601R–29–031, Revision A, 

dated March 26, 2009; Bombardier Alert 

Service Bulletin A601R–32–103, Revision D, 

dated May 11, 2010, including Appendix A, 

Revision A, dated October 18, 2007; 

Bombardier Service Bulletin 601R–29–032, 

Revision A, dated January 26, 2010; 

Bombardier Service Bulletin 601R–29–033, 

Revision A, dated May 11, 2010, including 

Appendix A, dated May 5, 2009; Bombardier 

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

dated December 8, 2010; Bombardier Service 

Bulletin 601R–32–106, Revision A, including 

Appendix A, dated May 11, 2010; and 

Bombardier Service Bulletin 601R–32–107, 

Revision B, dated December 8, 2010; for 

related information. 

Material Incorporated by Reference 

(v) You must use the following service 

information, as applicable, to do the actions 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this service information under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(1) Canadair Regional Jet Temporary 

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

the Canadair Regional Jet Airplane Flight 

Manual, CSP A–012 (previously approved for 

incorporation by reference on November 4, 

2010 (75 FR 64636, October 20, 2010)); 

(2) Bombardier Alert Service Bulletin 

A601R–29–029, Revision B, dated May 11, 

2010, including Appendix A, dated October 

18, 2007 (previously approved for 

incorporation by reference on November 4, 

2010 (75 FR 64636, October 20, 2010))*; 

(3) Bombardier Alert Service Bulletin 

A601R–29–031, Revision A, dated March 26, 

2009 (previously approved for incorporation 

by reference on November 4, 2010 (75 FR 

64636, October 20, 2010)); 

(4) Bombardier Alert Service Bulletin 

A601R–32–103, Revision D, dated May 11, 

2010, including Appendix A, Revision A, 

dated October 18, 2007 (previously approved 

for incorporation by reference on November 

4, 2010 (75 FR 64636, October 20, 2010))*; 

(5) Bombardier Service Bulletin 601R–29– 

032, Revision A, dated January 26, 2010 

(previously approved for incorporation by 

reference on November 4, 2010 (75 FR 64636, 

October 20, 2010)); 

(6) Bombardier Service Bulletin 601R–29– 

033, Revision A, dated May 11, 2010, 

including Appendix A, dated May 5, 2009 

(previously approved for incorporation by 

reference on November 4, 2010 (75 FR 64636, 

October 20, 2010))*; 

(7) Bombardier Service Bulletin 601R–29– 

035, Revision A, dated December 8, 2010 

(approved for incorporation by reference on 

December 22, 2011); 

(8) Bombardier Service Bulletin 601R–32– 

106, Revision A, including Appendix A, 

dated May 11, 2010 (previously approved for 

incorporation by reference on November 4, 

2010 (75 FR 64636, October 20, 2010))*; and 

(9) Bombardier Service Bulletin 601R–32– 

107, Revision B, dated December 8, 2010 

(approved for incorporation by reference on 

December 22, 2011). 

Note 4: * In Appendix A to these 

documents, the document number is shown 

only on page A1 of these appendices. 

(10) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone (514) 855–5000; fax (514) 

855–7401; email 


pmangrum on DSK3VPTVN1PROD with RULES
71246 Federal Register / Vol. 76, No. 222 / Thursday, November 17, 2011 / Rules and Regulations 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(11) 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. 

(12) 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 NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on October 

20, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–29680 Filed 11–16–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0954; Directorate 

Identifier 2011–CE–028–AD; Amendment 

39–16865; AD 2011–24–01] 

RIN 2120–AA64 

Airworthiness Directives; Piaggio Aero 

Industries S.p.A. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Piaggio 

Aero Industries S.p.A. Model P–180 

airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued 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: 

Some lock sleeves (part number (P/N) 

114146681), which were installed in some 

Main Landing Gear (MLG) actuators, had 

been incorrectly manufactured. 

If left uncorrected, this condition could 

lead to failure to lock the MLG actuator or 

to its unlock from the correct position, with 

subsequent possible damage to the aeroplane 

and injuries to occupants during landing. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD is effective December 

22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 22, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact Piaggio Aero Industries 

S.p.A. Airworthiness Office; Via Luigi 

Cibrario, 4–16154 Genova–Italy; 

telephone: +39 010 6481353; fax: +39 

010 6481881; Email: 

airworthiness@piaggioaero.it. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 

329–4090; email: mike.kiesov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on September 1, 2011 (76 FR 

54403). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Some lock sleeves (part number (P/N) 

114146681), which were installed in some 

Main Landing Gear (MLG) actuators, had 

been incorrectly manufactured. 

If left uncorrected, this condition could 

lead to failure to lock the MLG actuator or 

to its unlock from the correct position, with 

subsequent possible damage to the aeroplane 

and injuries to occupants during landing. 

This AD requires replacing defective MLG 

actuators with serviceable ones. 

Defective actuators can be repaired by the 

manufacturer and identified with the ‘‘P180– 

32–29’’ marking on the name plate. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Comment Issue: MLG Actuator 

Compliance Time 

Carlo Cardu, Piaggio Aero Industries, 

stated the MLG actuator has a life-limit 

based on landings and most operators 

note the landings accrued on the 

actuator. Mr. Cardu reasoned that for 

operators with a higher hours time-inservice (TIS)/landing ratio (more than 

1), the AD compliance limit presented 

in hours TIS would be more stringent 

than required. As for operators with a 

lower hours TIS/landing ratio, the AD 

compliance limit presented in hours TIS 

would be relaxed with reference to the 

compliance time of the service 

information. Mr. Cardu recommended 

changing the actuator replacement 

compliances times to read: 

before affected MLG actuators reach 3000 

landings, replace * * *; only if landings data 

are not available, replace the affected 

actuator before 3000 FH TIS * * * or similar 

statement 

The FAA agrees with the commenter 

and we changed paragraph (f)(3) of the 

AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 required 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 AD. 

Costs of Compliance 

We estimate that this AD will affect 

102 products of U.S. registry. We also 

estimate that it will take about 0.5 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $4,335, or $43 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 7 work-hours and require parts 

costing $64,822, for a cost of $65,417 

per product. There are a maximum of 17 

actuators that are identified by the 


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