### 41104 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations

Service Bulletin 777–27A0078, dated September 10, 2009, which is not incorporated by reference in this AD.

(2) For Groups 3 through 5, as identified in Boeing Alert Service Bulletin 777– 27A0078, dated September 10, 2009: This paragraph provides credit for actions required by paragraph (g) of this AD, except for the actions required for bonding jumpers 21 and 22, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, which is not incorporated by reference in this AD. If a review of the airplane’s maintenance records positively determines that bonding jumpers 21 and 22 were inspected before the effective date of this AD in accordance with Option 1 of Work Package 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, this paragraph provides credit for the actions required by paragraph (g) of this AD for the inspected bonding jumpers.

(3) For Groups 3 through 5, as identified in Boeing Alert Service Bulletin 777– 27A0078, dated September 10, 2009: This paragraph provides credit for actions specified in paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, which is not incorporated by reference in this AD; provided that a review of the airplane’s maintenance records positively determines that bonding jumpers 21 and 22 were replaced in accordance with Option 2 of Work Package 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–27A0078, dated September 10, 2009, or were replaced using the new Category 2 fay sealed direct ground stud installation
method.

(4) This paragraph provides credit for actions required by paragraph (i)(1) of this AD if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–55A0010, dated October 26, 2000, which is not incorporated by reference in this AD.

(5) This paragraph provides credit for actions required by paragraph (i)(2) of this AD if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–55A0014, dated May 8, 2008, which is not incorporated by
reference in this AD.

(l) Alternative Methods of Compliance (AMOCs)

(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 paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 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.

(m) Related Information

(1) For more information about this AD, contact Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6482; fax: 425–917–6590; email: Georgios.Roussos@ faa.gov.

(2) Service information identified in this AD that is not incorporated by reference may be viewed at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD.

(n) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Boeing Service Bulletin 777–27A0078, Revision 1, dated April 1, 2013.

(ii) Boeing Service Bulletin 777–55A0010, Revision 1, dated April 17, 2001.

(iii) Boeing Service Bulletin 777–55A0014, Revision 1, dated April 1, 2010.

(3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–
5680; Internet https:// www.myboeingfleet.com.

(4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this 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/cfr/ibrlocations.html.

Issued in Renton, Washington, on May 14,

2014. Michael J. Kaszycki,
Acting Manager Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–15435 Filed 7–14–14; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0296; Directorate Identifier 2012–NM–102–AD; Amendment**  **39–17861; AD 2014–11–10]**

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding Airworthiness Directive (AD) 2008–08– 09 for certain Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008–08–09 required revising the airworthiness limitations (AWL) section of the Instructions for Continued Airworthiness by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units and corrective actions if necessary. This new AD requires replacing certain PFS units with new redesigned PFS units, which would terminate the repetitive functional tests; and both adding and removing certain airplanes from the applicability. This AD was prompted by reports that the shear pin in the input
lever of several PFS units failed due tofatigue; and by the development of a redesigned PFS unit, which eliminates the need for repetitive functional tests. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane.

**DATES :**  This AD becomes effective August 19, 2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 19, 2014.

**ADDRESSES :**  You may examine the AD
docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0296; or in person at the Docket 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.

For service information identified in this AD, contact Bombardier, Inc., 400

Co

ˆ te-Vertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@


### 41105 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations

aero.bombardier.com ; Internet http://
www.bombardier.com . You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA,
call 425–227–1221.

**FOR FURTHER INFORMATION CONTACT :**  Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax

516–794–5531.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008). AD 2008–08–09 applied to certain Bombardier, Inc. Model CL– 600–2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM published in
the Federal Register on April 9, 2013 (78 FR 21074).

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2005–41R1, dated May 10, 2012 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI

states:

The shear pin in the input lever of several Pitch Feel Simulators (PFS) units has failed due to fatigue. The shear pin failure is not always detectable by the flight crew in normal operation. Failure of the shear pins in both PFS units on an aeroplane could result in loss of pitch feel forces and reduced controllability of the aeroplane.

Recently, Transport Canada has certified the new design of the PFS unit—part number (P/N) 601R92300–7 as a terminating action. Revision 1 of this [Canadian] AD mandates
the retrofit of all in-service CL–600–2B19 aeroplanes with the redesigned PFS unit. Required actions include revising the
AWLs section of the Instructions for Continued Airworthiness, repetitive functional testing of the pilot input lever of the PFS unit, and corrective actions if necessary, and replacing the PFS units having part number (P/N) 601R92300–3 (vendor P/N TY1910– 50A) or 601R92300–5 (vendor P/N TY1910–51A) with PFS units having P/N 601R92300–7 (vendor P/N TY1910– 54A), which terminates the actions required by AD 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008). This AD also adds airplanes having serial numbers (S/Ns) 7991 through 7999 inclusive, and removes airplanes having S/Ns 8111 and subsequent. You may examine the
MCAI in the AD docket on the Internet

at http://www.regulations.gov/ #!docketDetail;D=FAA-2013-0296

.
Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (78 FR 21074, April 9, 2013) and the FAA’s response
to each comment.

Request To Revise the Applicability by Adding Part Numbers

Air Wisconsin Airlines Corporation (Air Wisconsin) requested that we revise paragraph (c) of the proposed AD (78 FR 21074, April 9, 2013) by adding the part numbers of the PFS units, in addition to the airplane serial numbers. Air Wisconsin stated that the part numbers
that should be added are P/N 601R92300–3 (vendor P/N TY1910– 50A) and P/N 601R92300–5 (vendor P/N TY1910–51A). Air Wisconsin provided no justification for this request.

We do not agree to add the requested part numbers to the applicability of this AD. The functional check of the input lever required by this AD must be done on all airplanes having the serial numbers identified in the applicability of this AD. We have made no changes to paragraph (c) of this AD in this regard.

Request To Clarify Instructions Regarding Airworthiness Limitations

Air Wisconsin requested that we clarify how an operator is to update the AWLs when the task for doing the
functional test of the PFS unit was
deleted. Air Wisconsin stated that paragraph (g) of the proposed AD (78 FR 21074, April 9, 2013) refers to Task R27–31–A024–01, which was deleted by Bombardier on February 23, 2007. Air Wisconsin pointed out that Task R27– 31–A024–01 was specified in Bombardier Temporary Revision (TR) 2B–1784, dated October 24, 2003, to the Canadair CL–600–2B19 Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, which is no longer
available or relevant.

We agree. We removed proposed paragraph (g) (78 FR 21074, April 9, 2013) from this AD, and redesignated subsequent paragraphs accordingly. The functional test specified in paragraph (h) of the proposed AD (78 FR 21074, April 9, 2013) (redesignated as paragraph (g) of this AD) is now required in paragraph (g) of this AD. Request To Revise Applicability To
Exclude a Certain Serial Number

Air Wisconsin requested that we revise paragraph (h) of the proposed AD (78 FR 21074, April 9, 2013) (redesignated as paragraph (g) of this AD) to match the Effectivity section of
Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012. Air Wisconsin stated that paragraph (h) of the proposed AD applies to airplanes having S/Ns 7003 through 7990 inclusive, and S/Ns 8000 through 8111 inclusive. Air Wisconsin stated that, while the Effectivity section
of the service information varies between revisions, Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012, excludes the airplane having S/N 8111.

We agree with Air Wisconsin’s request to revise the applicability of this final rule for the reason provided. We have confirmed that the airplane having S/N 8111 is not affected by the unsafe condition addressed by this AD. Therefore, we have revised paragraphs (c) and (g) of this AD (designated as paragraphs (c) and (h) of the proposed AD (78 FR 21074, April 9, 2013)) to remove the airplane having S/N 8111. We have coordinated this change with
TCCA and Bombardier.

Request To Clarify Instructions Regarding Functional Test

Air Wisconsin requested that we clarify how an operator is to perform the functional test identified in paragraph (j) of the proposed AD (78 FR 21074, April 9, 2013) (redesignated as paragraph (i) of this AD) when the task
for the functional test has been deleted. Air Wisconsin stated that paragraph (j) of the proposed AD refers to Task R27– 31–A024–01, which was deleted by Bombardier on February 23, 2007. Air
Wisconsin stated that this task was specified in Bombardier TR 2B–1784, dated October 24, 2003, to the Canadair CL–600–2B19 Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, which is no longer available or
relevant.

We agree for the reason stated by Air Wisconsin. We have revised paragraph (i) of this AD (designated as paragraph (j) in the proposed AD (78 FR 21074, April 9, 2013)) by removing the
reference to Task R27–31–A024–01.

Request To Revise Wording in Paragraph (k) of the Proposed AD (78 FR 21074, April 9, 2013)

Air Wisconsin requested that the term ‘‘detected’’ in paragraph (k) of the proposed AD (78 FR 21074, April 9, 2013) (redesignated as paragraph (j) of


### 41106 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations

this AD) be changed to ‘‘disconnected.’’
Air Wisconsin asserted that FAA’s intent was probably to use the term
‘‘disconnected.’’

We partially agree. We agree that paragraph (j) of this AD (78 FR 21074, April 9, 2013) (designated as paragraph (k) of the proposed AD) should read differently. Paragraph 2.B.(4)(c) of the Accomplishment Instructions of
Bombardier Service Bulletin A601R–27– 144, Revision E, dated October 2, 2012, states, ‘‘If the input lever moves freely, or the input lever is loose, the PFS is ‘‘defective. . . .’’ Therefore, we have revised paragraphs (i) and (j) of this AD (designated as paragraphs (j) and (k) of the proposed AD) by changing the word
‘‘disconnected’’ to ‘‘defective.’’

Request To Clarify Airplanes Affected by New PFS Unit Replacement

Air Wisconsin requested that paragraph (l) of the proposed AD (78 FR 21074, April 9, 2013) (redesignated as paragraph (k) of this AD) be revised to add vendor P/Ns TY1910–50A, TY1910–51A, and TY1910–54A for clarity.

We agree with Air Wisconsin’s request to add vendor part numbers in paragraph (k) of this AD (designated as paragraph (l) in the proposed AD (78 FR 21074, April 9, 2013). We have revised paragraph (k) of this AD by adding the vendor part numbers with the manufacturer part numbers.

Request To Add Compliance Time When Total Flight Hours are Unknown

Air Wisconsin requested that paragraph (l) of the proposed AD (78 FR 21074, April 9, 2013) (redesignated as paragraph (k) of this AD) be revised to add a replacement compliance time for PFS units on which the total flight
hours are unknown. Air Wisconsin suggested the compliance time for PFS units with unknown total flight hours be 3,000 flight hours or 18 months after the
effective date of this AD.

We agree with Air Wisconsin’s request to specify a compliance time for PFS units with unknown total flight hours. We have revised paragraph (k)(4) of this AD (78 FR 21074, April 9, 2013) to add the suggested compliance time for PFS units having P/N 601R92300–3 (vendor P/N TY1910–50A) or 601R92300–5 (vendor P/N TY1910– 51A) for which the total flight hours are
unknown or cannot be determined.

Explanation of Changes Made to This

AD

We have reformatted paragraph (l) of this AD (designated as paragraph (m) of the proposed AD (78 FR 21074, April 9, 2013). We have added new paragraph (l)(1) to this AD. Paragraph (l)(1) of this AD gives credit for doing a functional test
if done before the effective date of AD 2006–05–11 R1, Amendment 39–14528 (71 FR 15323, March 28, 2006), using
Bombardier Alert Service Bulletin A601R–27–144, including Appendix A, dated September 15, 2005.

We redesignated paragraphs (m)(1), (m)(1)(i), (m)(1)(ii), and (m)(2) of the proposed AD (78 FR 21074, April 9, 2013) as paragraphs (l)(2), (l)(2)(i), (l)(2)(ii), and (l)(5) of this AD.

Conclusion

We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes:

• Are consistent with the intent that was proposed in the NPRM (78 FR 21074, April 9, 2013) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 21074, April 9, 2013).

Costs of Compliance

We estimate that this AD affects 574 airplanes of U.S. registry.

The actions that are required by AD 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008), and retained in this AD take about 2 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost $0 per product. Based on these figures, the
estimated cost of the actions that were required by AD 2008–08–09 is $170 per product.

We also estimate that it will take about 8 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $2,500 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 on U.S. operators to be $1,825,320, or $3,180 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 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 the 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.

Examining the AD Docket

You may examine the AD docket on
the Internet at http:// www.regulations.gov/#!docketDetail;

D=FAA-2013-0296; 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 Operations office (telephone 800–647–5527) is in the **ADDRESSES** section.

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:


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**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 Airworthiness Directive (AD) 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008), and adding the following new AD:

2014–11–10 Bombardier: Amendment 39– 17861. Docket No. FAA–2013–0296;
Directorate Identifier 2012–NM–102–AD.

(a) Effective Date

This AD becomes effective August 19,

2014.

(b) Affected ADs

This AD supersedes AD 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008).

(c) Applicability

This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers (S/Ns) 7003 through 8110 inclusive.

(d) Subject

Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) Reason

This AD was prompted by reports that the shear pin in the input lever of several pitch feel simulator (PFS) units failed due tofatigue; and by the development of a redesigned PFS unit, which eliminates the need for repetitive functional testing. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Retained Functional Test of Input Lever
With Revised Service Information

This paragraph restates the requirements of paragraph (g) of AD 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008), with revised service information. For airplanes having S/Ns 7003 through 7990 inclusive, and S/Ns 8000 through 8110 inclusive: Before the accumulation of 4,000 total flight hours, or within 100 flight hours after March 27, 2006 (the effective date of AD 2006–05–11 R1, Amendment 39–14528 (71 FR 15323, March 28, 2006), whichever occurs later, do a functional test of the pilot input
lever of the PFS units to determine if the lever is disconnected, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Repeat the test at intervals not to exceed 100 flight hours. As of the effective date of this AD, only
Bombardier Alert Service Bulletin A601R– 27–144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006, may be used to accomplish the actions required by this paragraph.

(1) Bombardier Alert Service Bulletin A601R–27–144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005.

(2) Bombardier Alert Service Bulletin A601R–27–144, Revision B, dated December 20, 2006, including Appendix A, Revision A, dated December 20, 2006.

(3) Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006.

(h) Retained Replacement With Revised
Service Information

This paragraph restates the requirements of paragraph (h) of AD 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008), with revised service information. If any lever is found to be disconnected during any functional test required by paragraph (g) of this AD: Before further flight, replace the defective PFS unit with a serviceable PFS unit, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. As of the effective date of this AD, only Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006, may be used to accomplish the actions required by this paragraph.

(1) Bombardier Alert Service Bulletin A601R–27–144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005.

(2) Bombardier Alert Service Bulletin A601R–27–144, Revision B, dated December 20, 2006, including Appendix A, Revision A, dated December 20, 2006.

(3) Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006.

(i) New Functional Test of Input Lever

For airplanes having S/Ns 7991 through
7999 inclusive: At the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, do a functional test of the pilot input
lever of the PFS units to determine if the lever is defective, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006. Repeat the test thereafter at intervals not to exceed 100 flight hours.

(1) Before the accumulation of 4,000 total flight hours.

(2) Within 100 flight hours from the
effective date of this AD.

(j) New Replacement of Defective Pitch Feel
Simulator Unit

For airplanes having S/Ns 7991 through 7999 inclusive: If any defective lever is found during any functional test required by paragraph (i) of this AD, before further flight, replace the defective PFS unit with a serviceable PFS unit, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20,

2006.

(k) New Replacement of Pitch Feel Simulator
Units

At the applicable time specified in paragraph (k)(1), (k)(2), (k)(3), or (k)(4) of this AD: Replace PFS units having part number (P/N) 601R92300–3 (vendor P/N TY1910– 50A) or 601R92300–5 (vendor P/N TY1910– 51A), with PFS units having P/N 601R92300– 7 (vendor P/N TY1910–54A), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–139, Revision A, dated May 28, 2012. Accomplishment of the replacement required by this paragraph terminates the requirements of paragraphs (g), (h), (i), and (j) of this AD, and does not alter the approved maintenance program for the new redesigned PFS unit P/N 601R92300–7 (vendor P/N TY1910–54A).

(1) For PFS units having P/N 601R92300– 3 (vendor P/N TY1910–50A) or 601R92300– 5 (vendor P/N TY1910–51A), that have accumulated less than 18,000 total flight
hours as of the effective date of this AD: Within 6,000 flight hours after the effective date of this AD, but not to exceed 23,000 total flight hours on the PFS unit, or within 36 months after the effective date of this AD,
whichever occurs first.

(2) For PFS units having P/N 601R92300– 3 (vendor P/N TY1910–50A) or 601R92300– 5 (vendor P/N TY1910–51A), that have accumulated more than or equal to 18,000 total flight hours, but less than 19,000 total flight hours as of the effective date of this AD: Within 5,000 flight hours after the effective date of this AD, but not to exceed 23,000 total flight hours on the PFS unit, or
within 30 months after the effective date of this AD, whichever occurs first.

(3) For PFS units having P/N 601R92300– 3 (vendor P/N TY1910–50A) or 601R92300– 5 (vendor P/N TY1910–51A), that have accumulated more than or equal to 19,000 total flight hours, but less than 20,000 total flight hours as of the effective date of this AD: Within 4,000 flight hours after the effective date of this AD, but not to exceed 23,000 total flight hours on the PFS unit, or
within 24 months after the effective date of this AD, whichever occurs first.

(4) For PFS units having P/N 601R92300– 3 (vendor P/N TY1910–50A) or 601R92300– 5 (vendor P/N TY1910–51A) that have accumulated more than or equal to 20,000 total flight hours as of the effective date of this AD, or for which the total flight hours
are unknown or cannot be determined: Within 3,000 flight hours or 18 months after the effective date of this AD, whichever
occurs first.

(l) Credit for Previous Actions

(1) This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before March 27, 2006 (the effective date of AD 2006–05–11 R1, Amendment 39–14528


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(71 FR 15323, March 28, 2006)), using
Bombardier Alert Service Bulletin A601R– 27–144, including Appendix A, dated September 15, 2005, which is not incorporated by reference in this AD.

(2) This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using a service bulletin identified in paragraph (l)(2)(i) or (l)(2)(ii) of this AD.

(i) Bombardier Alert Service Bulletin A601R–27–144, Revision C, dated July 21, 2008, including Appendix A, dated December 20, 2006, which is not incorporated by reference in this AD.

(ii) Bombardier Alert Service Bulletin A601R–27–144, Revision D, dated December 22, 2011, including Appendix A, dated December 20, 2006, which is not incorporated by reference in this AD.

(3) This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before March 27, 2006 (the effective date of AD 2006–05– 11 R1, Amendment 39–14528 (71 FR 15323, March 28, 2006)), using Bombardier Alert Service Bulletin A601R–27–144, Revision B, dated December 20, 2006, including Appendix A, Revision A, dated December 20,

2006.

(4) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before May 19, 2008 (the effective date of AD 2008–08– 09, Amendment 39–15461 (73 FR 19979, April 14, 2008)), using Bombardier Alert Service Bulletin A601R–27–144, Revision B, dated December 20, 2006, including Appendix A, Revision A, dated December 20,

2006.

(5) This paragraph provides credit for replacement of the PFS units required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 601R–27–139, dated December 22, 2011, which is not incorporated by reference in this

AD.

(m) Other FAA AD Provisions

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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. Send information to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 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 2008–08–09, Amendment 39–15461 (73 FR 19979, April 14, 2008), are approved as AMOCs for the corresponding actions specified in paragraphs (g) and (h) 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.

(n) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2005–41R1, dated May 10, 2012, for related information. You may examine the MCAI in the AD

docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA2013-0296

.

(2) Service information identified in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD.

(o) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

(i) Bombardier Alert Service Bulletin A601R–27–144, Revision E, dated October 2, 2012, including Appendix A, Revision A, dated December 20, 2006.

(ii) Bombardier Service Bulletin 601R–27– 139, Revision A, dated May 28, 2012.

(3) For service information identified in this AD, contact Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@

aero.bombardier.com ; Internet http://

www.bombardier.com

.

(4) You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this 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/cfr/ibrlocations.html

.

Issued in Renton, Washington, on May 27,

2014. Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–15655 Filed 7–14–14; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–1070; Directorate Identifier 2013–NM–175–AD; Amendment**  **39–17892; AD 2014–13–16]**

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702), CL–600–2D15 (Regional Jet Series 705), CL–600–2D24 (Regional Jet Series 900), and CL–600–2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by the finding of an uncertified main landing gear (MLG) inboard retractionactuator bracket pin installed on an inservice airplane. This AD requires inspection of the MLG inboard retraction actuator bracket for a part number, and replacement if necessary. We are issuing this AD to detect and correct uncertified pins in the MLG inboard retraction actuator bracket, which could result in pin failure, leading to an MLG extension without damping, and a potential for MLG structural damage and possible collapse during landing.

**DATES :**  This AD becomes effective August 19, 2014.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 19, 2014.

**ADDRESSES :**  You may examine the AD
docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-1070; or in person at the Docket 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.

For service information identified in this AD, contact Bombardier, Inc., 400

Co

ˆ te-Vertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd. crj@ aero.bombardier.com ; Internet http://
www.bombardier.com . You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the