48968 Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations 

changed 233W3202–12 panel is 233W3202– 

18, and the correct part number for the 

changed 233W3202–13 panel is 233W3202– 

19. 

(ii) Put back the P210 power panel to the 

correct standard, in accordance with the 

Accomplishment Instructions of GE Aviation 

Service Bulletin 6000ELM–24–614, Revision 

1, dated November 9, 2009; or GE Aviation 

Service Bulletin 6200ELM–24–616, Revision 

1, dated March 5, 2010. 

(2) This paragraph provides credit for the 

actions specified in paragraph (i)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Service Bulletin 777–23–0176, dated January 

9, 2003; or Boeing Service Bulletin 777–23– 

0176, Revision 1, dated March 11, 2004; 

which are not incorporated by reference in 

this AD; provided that the actions specified 

in Boeing Service Bulletin 777–23–0141, 

dated June 14, 2001, were done prior to or 

concurrently with the actions specified in 

Boeing Service Bulletin 777–23–0176, dated 

January 9, 2003; or Boeing Service Bulletin 

777–23–0176, Revision 1, dated March 11, 

2004. 

(3) This paragraph provides credit for the 

actions specified in paragraph (i)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Service Bulletin 777–24–0087, dated July 24, 

2003; or Boeing Service Bulletin 777–24– 

0087, Revision 1, dated December 18, 2003; 

which are not incorporated by reference in 

this AD; provided that the actions specified 

in Boeing Service Bulletin 777–24–0087, 

dated July 24, 2003; or Boeing Service 

Bulletin 777–24–0087, Revision 1, dated 

December 18, 2003; were done concurrently 

with the actions specified in the service 

information identified in paragraphs (j)(3)(i) 

through (j)(3)(v) of this AD. 

(i) Boeing Service Bulletin 777–24–0077, 

dated August 21, 2003, which is not 

incorporated by reference in this AD. 

(ii) Boeing Service Bulletin 777–24–0077, 

Revision 1, dated May 24, 2007, which is not 

incorporated by reference in this AD. 

(iii) Boeing Service Bulletin 777–24–0077, 

Revision 2, dated December 17, 2009, 2007, 

which is not incorporated by reference in this 

AD. 

(iv) Boeing Service Bulletin 777–24–0077, 

Revision 3, dated December 6, 2011, 2007, 

which is not incorporated by reference in this 

AD. 

(v) Boeing Service Bulletin 777–24–0077, 

Revision 4, dated October 17, 2012. 

(k) 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 (l) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Ray Mei, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6467; fax: 425–917– 

6590; email: raymont.mei@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3), (m)(4), (m)(5), and (m)(6) 

of this AD, as applicable. 

(m) 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) BAE Systems Service Bulletin 

233W3202–24–04, Revision 2, dated October 

2, 2006. 

(ii) Boeing Service Bulletin 777–23–0176, 

Revision 2, dated October 26, 2006. 

(iii) Boeing Service Bulletin 777–24–0077, 

Revision 4, dated October 17, 2012. 

(iv) Boeing Service Bulletin 777–24–0087, 

Revision 2, dated August 16, 2007. 

(v) Boeing Service Bulletin 777–28A0039, 

Revision 2, dated September 20, 2010. 

(vi) GE Aviation Service Bulletin 

6000ELM–24–614, Revision 1, dated 

November 9, 2009. 

(vii) GE Aviation Service Bulletin 

6200ELM–24–616, Revision 1, dated March 

5, 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) For BAE Systems service information 

identified in this AD, contact BAE Systems, 

Attention: Commercial Product Support, 600 

Main Street, Room S18C, Johnson City, NY 

13790–1806; phone: 607–770–3084; fax: 607– 

770–3015; email: CS-Customer.Service@

baesystems.com; Internet: http://

www.baesystems-ps.com/customersupport. 

(5) For GE service information identified in 

this AD, contact GE Aviation, Customer 

Support Center, 1 Neumann Way, Cincinnati, 

OH 45215; phone: 513–552–3272; email: 

cs.techpubs@ge.com; Internet: http://

www.geaviation.com. 

(6) 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. 

(7) 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 August 

1, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–18905 Filed 8–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0129; Directorate 

Identifier 2013–NM–105–AD; Amendment 

39–17931; AD 2014–16–07] 

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) 2011–15– 

09 for certain Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes. 

AD 2011–15–09 required repetitive 

inspections for proper operation of the 

main landing gear (MLG) alternate 

extension system (AES), and corrective 

actions if necessary. This new AD 

requires, for certain airplanes, new 

repetitive inspections for proper 

operation of the MLG AES, and 

corrective actions if necessary. This new 

AD also requires eventually replacing 

the MLG AES cam mechanism assembly 

with a new assembly, which terminates 

the repetitive inspections for those 

airplanes. This AD was prompted by a 

determination that, for certain airplanes 

not affected by AD 2011–15–09, a 

different MLG AES cam mechanism 

assembly was installed, resulting in 

input lever fractures and inability to 

open the MLG door; those assemblies 

could be subject to the same unsafe 

condition in AD 2011–15–09. We are 

issuing this AD to prevent improper 

operation of the cam mechanism or 

rupture of the door release cable, which 


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Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations 48969 

could result in loss of control of the 

airplane during landing. 

DATES: This AD becomes effective 

September 23, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 23, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of August 2, 2011 (76 FR 

42033, July 18, 2011). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0129; 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., QSeries Technical Help Desk, 123 Garratt 

Boulevard, Toronto, Ontario M3K 1Y5, 

Canada; telephone 416–375–4000; fax 

416–375–4539; email thd.qseries@

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 2011–15–09, 

Amendment 39–16756 (76 FR 42033, 

July 18, 2011). AD 2011–15–09 applied 

to certain Bombardier, Inc. Model DHC– 

8–400, –401, and –402 airplanes. The 

NPRM published in the Federal 

Register on March 5, 2014 (79 FR 

12428). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2011–01R2, 

dated May 21, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes. 

The MCAI states: 

Two cases of the main landing gear (MLG) 

alternate extension system (AES) cam 

mechanism failure were found during line 

checks. The cam mechanism operates the 

cable to open the MLG door and releases the 

MLG uplock in sequence. In the case where 

it is necessary to deploy the MLG using the 

AES, the failure of the MLG AES cam 

mechanism on one side will lead to an unsafe 

asymmetrical landing configuration. 

Preliminary investigation indicates that the 

cam mechanism failure may have occurred 

and remained dormant after a previous AES 

operation. The cam mechanism may not have 

fully returned to the normal rested position. 

With the cam mechanism out of normal 

rested position, normal powered landing gear 

door operation could introduce sufficient 

loads to fracture the cam mechanism or 

rupture the door release cable. 

This [Canadian] AD mandates the initial 

and subsequent [detailed] inspections for 

proper operation of the MLG AES cam 

mechanism, and rectify [repair or replace 

cam assembly with new or serviceable cam 

assembly] as necessary. 

Since the original issue of this [Canadian] 

AD, Bombardier Inc. has determined that the 

existing inspection procedure is insufficient 

for verification of proper MLG AES cam 

mechanism operation, and has superseded 

this inspection procedure. Revision 1 of this 

[Canadian] AD mandates the use of the 

revised inspection [and rectification] 

procedure. 

Prior to the introduction of MLG AES cam 

mechanism assembly part number (P/N) 

48510–5 as terminating action, an interim 

MLG AES cam mechanism assembly P/N 

48510–3 was introduced. 

Revision 2 of this [Canadian] AD updates 

the applicability paragraph, updates the MLG 

AES cam mechanism inspection criteria and 

mandates the terminating action. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0129. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supported the NPRM (79 FR 

12428, March 5, 2014). 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (79 FR 12428, March 5, 

2014), we proposed to prevent the use 

of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (79 FR 12428, March 5, 2014) 

about these proposed changes. However, 

a comment was provided for an NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013). The commenter stated the 

following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 


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48970 Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, TCCA, or Bombardier, 

Inc.’s TCCA Design Approval 

Organization (DAO). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DAO, the approval must include 

the DAO-authorized signature. The DAO 

signature indicates that the data and 

information contained in the document 

are TCCA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DAO-authorized signature approval are 

not TCCA-approved, unless TCCA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013) pointed out that in many cases the 

foreign manufacturer’s service bulletin 

and the foreign authority’s MCAI might 

have been issued some time before the 

FAA AD. Therefore, the DOA might 

have provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘DAH with State of 

Design Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 

Change to Paragraph (g)(3) of This AD 

For clarity purposes, we have revised 

paragraph (g)(3) of this AD by adding 

new paragraphs (g)(3)(i) and (g)(3)(ii) to 

this AD. 

Conclusion 

We reviewed the available data, 

including the comment 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 minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

12428, March 5, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 12428, 

March 5, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 75 

airplanes of U.S. registry. 

ESTIMATED COSTS

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

Inspection in AD 2011–15–09, 

Amendment 39–16756 (76 FR 

42033, July 18, 2011).

Up to 24 work-hours × $85 per 

hour = up to $2,040 per inspection cycle.

$2,609 ................. Up to $4,649 per inspection cycle.Up to $348,675 per inspection cycle. 

Inspection [new action] .................... 1 work-hour × $85 per hour = $85 

per inspection cycle.

$0 ........................ $85 per inspection 

cycle.

$6,375 per inspection 

cycle. 

Replacement of both cam assemblies [new terminating action].4 work-hours × $85 per hour = 

$680 [$340 per cam assembly].

$7,676 (2 cam assemblies).$80,167 ....................... $601,200. 

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 


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Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations 48971 

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-2014-0129; 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: 

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) 

2011–15–09, Amendment 39–16756 (76 

FR 42033, July 18, 2011), and adding the 

following new AD: 

2014–16–07 Bombardier, Inc.: Amendment 

39–17931. Docket No. FAA–2014–0129; 

Directorate Identifier 2013–NM–105–AD. 

(a) Effective Date 

This AD becomes effective September 23, 

2014. 

(b) Affected ADs 

This AD replaces AD 2011–15–09, 

Amendment 39–16756 (76 FR 42033, July 18, 

2011). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

4001, 4003 through 4418 inclusive, 4422 and 

4423. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a determination 

that a different main landing gear (MLG) 

alternate extension system (AES) cam 

mechanism assembly was installed resulting 

in input lever fractures and inability to open 

the MLG door; those assemblies could be 

subject to the same unsafe condition in the 

existing AD. We are issuing this AD to 

prevent improper operation of the cam 

mechanism or rupture of the door release 

cable, which could result in loss of control 

of the airplane during landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Detailed Inspection for Proper 

Operation of the MLG 

This paragraph restates the requirement in 

paragraph (i) of AD 2011–15–09, Amendment 

39–16756 (76 FR 42033, July 18, 2011), with 

revised service information. For airplanes 

with a MLG AES cam mechanism assembly 

having part number (P/N) 48510–1: Within 

50 flight hours or 10 days after August 2, 

2011 (the effective date of AD 2011–15–09, 

Amendment 39–16756 (76 FR 42033, July 18, 

2011)), whichever occurs first, do a detailed 

inspection for proper operation of the MLG 

AES cam mechanism, in accordance with 

paragraph A) of Bombardier Repair Drawing 

8/4–32–0160, Issue 3, dated February 15, 

2011; or Bombardier Repair Drawing 8/4–32– 

0160, Issue 6, dated June 27, 2012. As of the 

effective date of this AD, use only 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012. Repeat the 

inspection thereafter at intervals not to 

exceed 50 flight hours or 10 days, whichever 

occurs first. 

(1) If the cam mechanism is found to reset 

to the normal rested position without any 

sticking or binding, it is operating properly. 

(2) If the cam mechanism has not reset to 

its normal rested position, or if any sticking 

or binding is observed, before further flight, 

remove the cam assembly, in accordance 

with paragraph A) of Bombardier Repair 

Drawing 8/4–32–0160, Issue 3, dated 

February 15, 2011; or Bombardier Repair 

Drawing 8/4–32–0160, Issue 6, dated June 27, 

2012, and do the actions in paragraph (g)(2)(i) 

or (g)(2)(ii) of this AD. As of the effective date 

of this AD, use only Bombardier Repair 

Drawing 8/4–32–0160, Issue 6, dated June 27, 

2012. 

(i) Repair the cam mechanism assembly, 

including doing detailed inspections for 

discrepancies (an inspection to determine 

proper operation, an inspection for damage, 

an inspection for corrosion and cadmium 

coating degradation, and inspections to 

determine dimensions are within the limits 

specified in paragraph B) of Bombardier 

Repair Drawing 8/4–32–0160, Issue 3, dated 

February 15, 2011; or Bombardier Repair 

Drawing 8/4–32–0160 Issue 6, dated June 27, 

2012, in accordance with paragraph B) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011; and install 

the repaired cam assembly in accordance 

with paragraph C) of Bombardier Repair 

Drawing 8/4–32–0160, Issue 3, dated 

February 15, 2011; or Bombardier Repair 

Drawing 8/4–32–0160, Issue 6, dated June 27, 

2012. As of the effective date of this AD, use 

only Bombardier Repair Drawing 8/4–32– 

0160, Issue 6, dated June 27, 2012. 

(ii) Install a new or serviceable cam 

assembly, in accordance with paragraph C) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011; or 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012. As of the 

effective date of this AD, use only 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012. 

(3) If the cam mechanism is found 

damaged or inoperative during the repair 

specified in paragraph (g)(2)(i) of this AD; or 

if any discrepancies are found and 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011, or 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012, does not specify 

repairs for those discrepancies; or repairs 

specified in paragraph (g)(2)(i) of this AD 

cannot be accomplished: Before further 

flight, accomplish paragraph (g)(3)(i) or 

(g)(3)(ii) of this AD. 

(i) Repair and reinstall using a method 

approved by the Manager, New York ACO, 

ANE–170, Engine and Propeller Directorate, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(ii) Install a new or serviceable cam 

assembly, in accordance with paragraph C) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011; or 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012. As of the 

effective date of this AD, use only 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012, to install the 

cam assembly. 

(h) New Inspection for Proper Operation of 

the MLG Replacement Part 

For airplanes with a MLG AES cam 

mechanism assembly having P/N 48510–3: 

Within 1,800 flight hours or 9 months after 

installation of the assembly, whichever 

occurs first after the effective date of this AD, 

do a detailed inspection for proper operation 

of the MLG AES cam mechanism, in 

accordance with paragraph A) of Bombardier 

Repair Drawing 8/4–32–0160, Issue 6, dated 

June 27, 2012. Repeat the inspection 

thereafter at intervals not to exceed 600 flight 

hours or 3 months, whichever occurs first. 

(1) If the cam mechanism is found to reset 

to the normal rested position without any 

sticking or binding, it is operating properly. 

(2) If the cam mechanism has not reset to 

its normal rested position, or if any sticking 

or binding is observed, before further flight, 

remove the cam assembly, in accordance 

with paragraph A) of Bombardier Repair 

Drawing 8/4–32–0160, Issue 6, dated June 27, 

2012, and do the actions required by 

paragraphs (h)(2)(i) or (h)(2)(ii) of this AD. 

(i) Repair the cam mechanism assembly, 

including doing detailed inspections for 

discrepancies (an inspection to determine 

proper operation, an inspection for damage, 

an inspection for corrosion and cadmium 

coating degradation, and inspections to 

determine dimensions are within the limits 

specified in paragraph B) of Bombardier 

Repair Drawing 8/4–32–0160, Issue 6, dated 

June 27, 2012), in accordance with paragraph 


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48972 Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations 

B) of Bombardier Repair Drawing 8/4–32– 

0160, Issue 6, dated June 27, 2012; and install 

the repaired cam assembly in accordance 

with paragraph C) of Bombardier Repair 

Drawing 8/4–32–0160, Issue 6, dated June 27, 

2012. 

(ii) Install a new or serviceable cam 

assembly, in accordance with paragraph C) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012. 

(3) If the cam mechanism is found 

damaged or inoperative during the repair 

specified in paragraph (h)(2)(i) of this AD; or 

if any discrepancies are found and 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012, does not specify 

repairs for those discrepancies; or repairs 

specified in paragraph (h)(2)(i) of this AD 

cannot be accomplished: Before further 

flight, do the applicable actions required by 

paragraph (h)(3)(i) or (h)(3)(ii) of this AD. 

(i) Repair and reinstall using a method 

approved by the Manager, ANE–170, New 

York ACO, FAA, or TCCA; or Bombardier, 

Inc.’s TCCA Design Approval Organization 

(DAO). If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(ii) Install a new or serviceable cam 

assembly, in accordance with paragraph C) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 6, dated June 27, 2012. 

(i) New Credit for Previous Actions for 

Paragraphs (g) and (h) of This AD 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Repair Drawing 8/4–32–0160, Issue 5, dated 

June 6, 2012, which is not incorporated by 

reference in this AD. 

(j) New Terminating Action 

Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first, replace any MLG AES cam 

mechanism assembly having P/N 48510–1 or 

P/N 48510–3 with a new MLG AES cam 

mechanism assembly having P/N 48510–5, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–32–100, Revision A, dated August 30, 

2012. Accomplishing this replacement 

terminates the repetitive inspections required 

by this AD. 

(k) New Credit for Previous Actions for 

Paragraph (j) of This AD 

This paragraph provides credit for actions 

required by paragraph (j) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 84–32–100, dated August 15, 2012, 

which is not incorporated by reference in this 

AD. 

(l) 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. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2011–01R2, 

dated May 21, 2013, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail;D=FAA2014-0129. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(5) and (n)(6) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 23, 2014. 

(i) Bombardier Repair Drawing 8/4–32– 

0160, Issue 6, dated June 27, 2012. The issue 

dates for this document are identified only 

on sheets 1 and 1A of this document. 

(ii) Bombardier Service Bulletin 84–32– 

100, Revision A, dated August 30, 2012. 

(4) The following service information was 

approved for IBR on August 2, 2011 (76 FR 

42033, July 18, 2011). 

(i) Bombardier Repair Drawing 8/4–32– 

0160, Issue 3, dated February 15, 2011. The 

issue dates for this document are identified 

only on the first page of this document. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(6) You may view this 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. 

(7) 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 July 30, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19150 Filed 8–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0250; Directorate 

Identifier 2013–NM–165–AD; Amendment 

39–17930; AD 2014–16–06] 

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–600–2B16 

(CL–604 Variant) airplanes. This AD 

was prompted by reports of in-flight 

uncommanded rudder movements. This 

AD requires revising the airplane flight 

manual (AFM) to incorporate an 

uncommanded yaw motion procedure. 

We are issuing this AD to prevent inflight uncommanded rudder 

movements, which could lead to 

structural failure and subsequent loss of 

the airplane. 

DATES: This AD becomes effective 

September 23, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 23, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0250 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 

Coˆte-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://


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