49434 Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0233, dated November 7, 

2012, for related information. This MCAI 

may be found in the AD docket on the 

Internet at http://www.regulations.gov/ 

#!documentDetail;D=FAA-2014-0124-0002. 

(l) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on August 

4, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19549 Filed 8–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1065; Directorate 

Identifier 2011–NM–230–AD; Amendment 

39–17915; AD 2014—15–13] 

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) 2005–15– 

04 for certain Bombardier, Inc. Model 

CL–600–1A11 (CL–600), CL–600–2A12 

(CL–601), and CL–600–2B16 (CL–601– 

3A, CL–601–3R, and CL–604 Variants) 

airplanes. AD 2005–15–04 required 

operators to assign serial numbers or 

part numbers to certain landing gear 

parts; establish the number of landings 

on the parts, if necessary; and revise the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continued 

Airworthiness (ICA) to reflect the new 

life limits of the landing gear parts. This 

new AD adds airplanes to the 

applicability, requires operators to 

assign serial numbers or part numbers to 

certain additional landing gear parts to 

establish the number of landings on the 

parts if necessary, and requires 

operators to record in all required 

airplane technical records and manuals 

the new part numbers, serial numbers, 

and landings assigned to these parts. 

This AD was prompted by reports that 

landing gear parts that have safe-life 

limits but do not have serial numbers or 

part numbers can be removed from one 

landing gear and re-installed on another, 

making tracking difficult. We are issuing 

this AD to prevent life-limited landing 

gear parts from being used beyond their 

safe-life limits, which could lead to 

collapse of the landing gear. 

DATES: This AD becomes effective 

September 25, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 25, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 30, 2005 (70 FR 

43032, July 26, 2005). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov/ 

#!docketDetail;D=FAA-2013-1065; 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 Bombardier, Inc./Canadair 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 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.com. For 

Messier-Dowty service information 

identified in this AD, contact Messier 

Services Americas, Customer Support 

Center, 45360 Severn Way, Sterling, VA 

20166–8910; phone: 703–450–8233; fax: 

703–404–1621; Internet: https:// 

techpubs.services/messier-dowty.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: 

Andreas Rambalakos, 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) 228–7345; 

fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, 

July 26, 2005). AD 2005–15–04 applied 

to certain Bombardier, Inc. Model CL– 

600–1A11 (CL–600), CL–600–2A12 (CL– 

601), and CL–600–2B16 (CL–601–3A, 

CL–601–3R, and CL–604 Variants) 

airplanes. The NPRM published in the 

Federal Register on December 30, 2013 

(78 FR 79329). The NPRM was 

prompted by reports that landing gear 

parts that have safe-life limits but do not 

have serial numbers or part numbers 

can be removed from one landing gear 

and re-installed on another, making 

tracking difficult. The NPRM proposed 

to add airplanes to the applicability, 

require operators to assign serial 

numbers or part numbers to certain 

additional landing gear parts to 

establish the number of landings on the 

parts if necessary, and requires 

operators to record in all required 

airplane technical records and manuals 

the new part numbers, serial numbers, 

and landings assigned to these parts. We 

are issuing this AD to prevent lifelimited landing gear parts from being 

used beyond their safe-life limits, which 

could lead to collapse of the landing 

gear. 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, has issued 

Canadian Airworthiness Directives CF– 

2003–18R2, dated September 28, 2011; 

CF–2003–20R1, dated September 28, 

2011; and CF–2003–21R2, dated 

September 28, 2011 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’); to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–1A11 (CL–600), CL–600–2A12 (CL– 

601), and CL–600–2B16 (CL–601–3A, 

CL–601–3R, and CL–604 Variants) 

airplanes. The MCAI states: 

Certain landing gear parts that are listed in 

the aeroplane model Airworthiness 

Limitations Section, as safe life items with 

structural life limits, could be rotable and 

may not have been serialized, making 

tracking difficult. This [Canadian 

airworthiness] directive mandates that such 

parts be serialized. This [Canadian 

airworthiness] directive also provides the 

procedure to determine the number of 

landings for those parts where the service 

history cannot be established. 

* * * * * 

[T]his [Canadian Airworthiness] directive 

* * * mandate[s] serialization of * * * 

additional landing gear parts. 

This AD also adds airplanes to the 

applicability. The unsafe condition is 

using life-limited landing gear parts 

beyond their safe-life limits, which 

could lead to collapse of the landing 

gear. You may examine the MCAI in the 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 49435 

AD docket on the Internet at http:// 

www.regulations.gov/ 

#!documentDetail;D=FAA-2013-1065- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 79329, December 30, 2013) or on the 

determination of the cost to the public. 

‘‘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. 

We have become 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 ADmandated 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 

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, Transport Canada Civil 

Aviation (TCCA), or Bombardier’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. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (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. 

Conclusion 

We reviewed the available data 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 (78 FR 

79329, December 30, 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 79329, 

December 30, 2013). 

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 419 

airplanes of U.S. registry. 

The actions that were required by AD 

2005–15–04, Amendment 39–14193 (70 

FR 43032, July 26, 2005), that are 

retained in this AD take up to 13 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 up to 

$1,105 per product. 

We estimate that it would take about 

9 work-hours per product to comply 

with the new basic requirements of this 

AD. The average labor rate is $85 per 

work-hour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $320,535, or $765 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-2013-1065; 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. 


tkelley on DSK3SPTVN1PROD with RULES
49436 Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 

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) 

2005–15–04, Amendment 39–14193 (70 

FR 43032, July 26, 2005), and adding the 

following new AD: 

2014–15–13 Bombardier, Inc.: Amendment 

39–17915. Docket No. FAA–2013–1065; 

Directorate Identifier 2011–NM–230–AD. 

(a) Effective Date 

This AD becomes effective September 25, 

2014. 

(b) Affected ADs 

This AD replaces AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005). 

(c) Applicability 

This AD applies to Bombardier, Inc. 

airplanes, certificated in any category, as 

identified in paragraphs (c)(1) through (c)(4) 

of this AD. 

(1) Model CL–600–1A11 (CL–600) 

airplanes, serial numbers 1004 through 1085 

inclusive. 

(2) Model CL–600–2A12 (CL–601) 

airplanes, serial numbers 3001 through 3066 

inclusive; 

(3) Model CL–600–2B16 (CL–601–3A and 

CL–601–3R Variants) airplanes, serial 

numbers 5001 through 5194 inclusive. 

(4) Model CL–600–2B16 (CL–604 Variant) 

airplanes, serial numbers 5301 through 5573 

inclusive, 5579, and 5595. 

(5) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections). Compliance 

with these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by this AD, the operator 

may not be able to accomplish the actions 

described in the revisions. In this situation, 

to comply with 14 CFR 91.403(c), the 

operator must request approval for an 

alternative method of compliance according 

to paragraph (r) of this AD. The request 

should include a description of changes to 

the required actions that will ensure the 

continued damage tolerance of the affected 

structure. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports that 

landing gear parts that have safe-life limits 

but do not have serial numbers (S/Ns) or part 

numbers (P/Ns) can be removed from one 

landing gear and re-installed on another, 

making tracking difficult. We are issuing this 

AD to prevent life-limited landing gear parts 

from being used beyond their safe-life limits, 

which could lead to collapse of the landing 

gear. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Requirement To Add S/Ns or 

P/Ns 

This paragraph restates the actions 

required by paragraph (f) of AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005), with revised affected airplanes. Except 

for Model CL–600–2B16 airplanes having S/ 

Ns 5514 through 5595 inclusive: At the 

applicable compliance time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD, 

add serial numbers and part numbers, as 

applicable, to the parts identified in the 

applicable service bulletin specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

Do all actions in accordance with the 

applicable service bulletin specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

(1) For parts identified in Bombardier 

Service Bulletin 600–0710, Revision 01, 

dated December 15, 2003; and Bombardier 

Service Bulletin 601–0546, Revision 01, 

dated December 15, 2003; as having a 

compliance time of ‘‘five years for the parts 

listed in Part A’’: Within 60 months after 

August 30, 2005 (the effective date of AD 

2005–15–04, Amendment 39–14193 (70 FR 

43032, July 26, 2005)). 

(2) For parts identified in Bombardier 

Service Bulletin 600–0710, Revision 01, 

dated December 15, 2003; and Bombardier 

Service Bulletin 601–0546, Revision 01, 

dated December 15, 2003; as having a 

compliance time of ‘‘ten years for the parts 

listed in Part B’’: Within 120 months after 

August 30, 2005 (the effective date of AD 

2005–15–04, Amendment 39–14193 (70 FR 

43032, July 26, 2005)). 

(3) For parts identified in Bombardier 

Service Bulletin 604–32–014, dated May 31, 

2002, as having a compliance time of ‘‘no 

later than a calendar time of 8 years’’: Within 

96 months after August 30, 2005 (the 

effective date of AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005)). 

Note 1 to paragraph (g) of this AD: The 

Bombardier service bulletins identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD 

refer to the Messier-Dowty service bulletins 

identified in table 1 to paragraph (g) of this 

AD as additional sources of guidance for 

adding part numbers or serial numbers by 

vibro-peening the numbers on main landing 

gear (MLG) and nose landing gear (NLG) 

components that do not have them; and for 

determining the number of landings for parts 

without a part number or serial number on 

which the time since new (TSN) and cycles 

since new (CSN) have not been tracked. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—MESSIER-DOWTY SERVICE BULLETINS

Model— Landing gear component— 

Corresponding bombardier service bulletin(s)— 

Messier–Dowty service bulletin— 

CL–600–1A11 (CL–600), CL–600–2A12 (CL– 

601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

MLG side strut retraction actuator eye 

bolt.

600–0710 and 601– 

0546.

M–DT SB104467009/010–32–1, dated March 

19, 2001. 

CL–600–2B16 (CL–604) airplanes ................... MLG shock strut ......... 604–32–014 ............... M–DT SB19090–32–4, dated March 19, 

2001. 

CL–600–2B16 (CL–604) airplanes ................... NLG shock strut ......... 604–32–014 ............... M–DT SB20020–32–5, dated July 12, 2001. 

CL–600–1A11 (CL–600), CL–600–2A12 (CL– 

601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

NLG drag brace hinge 

pin.

600–0710 and 601– 

0546.

M–DT SB200814001–32–3, dated March 19, 

2001. 

CL–600–1A11 (CL–600) airplanes ................... MLG shock strut ......... 600–0710 ................... M–DT SB200922001/2–32–6, dated March 

19, 2001. 

CL–600–1A11 (CL–600) airplanes ................... NLG shock strut ......... 600–0710 ................... M–DT SB200924003/004–32–16, dated July 

12, 2001. 

CL–600–2A12 (CL–601) and CL–600–2B16 

(CL–601–3A and CL–601–3R) airplanes.

MLG shock strut pin ... 601–0546 ................... M–DT SB6100–32–10, dated March 19, 

2001. 


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Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 49437 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—MESSIER-DOWTY SERVICE BULLETINS—Continued 

Model— Landing gear component— 

Corresponding bombardier service bulletin(s)— 

Messier–Dowty service bulletin— 

CL–600–1A11 (CL–600), CL–600–2A12 (CL– 

601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

MLG side strut retraction actuator.600–0710 and 601– 

0546.

M–DT SB6500–32–1, dated March 19, 2001. 

CL–600–1A11 (CL–600), CL–600–2A12 (CL– 

601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

NLG drag brace hinge 

pin.

600–0710 and 601– 

0546.

M–DT SB7200–32–6, dated March 19, 2001. 

CL–600–2A12 (CL–601) and CL–600–2B16 

(CL–601–3A and CL–601–3R) airplanes.

NLG shock strut ......... 601–0546 ................... M–DT SB7300–32–16, dated July 12, 2001. 

(h) Retained Requirement—Establishment of 

the Number of Landings 

This paragraph restates the actions 

required by paragraph (g) of AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005), with revised affected airplanes. Except 

for Model CL–600–2B16 airplanes having S/ 

Ns 5314 through 5595 inclusive: At the 

applicable time specified in paragraph (g) of 

this AD, if a component does not have a 

serial number and the CSN or TSN were not 

tracked, use the formula in the applicable 

Messier-Dowty service bulletin specified in 

table 1 to paragraph (g) of this AD to establish 

the TSN or CSN, and record the newly 

calculated TSN or CSN in the airplane log 

books. 

(i) Retained Requirement To Revise the 

Airworthiness Limitations Section (ALS) 

This paragraph restates the revision 

required by paragraph (h) of AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005), with revised affected airplanes. Except 

for Model CL–600–2B16 airplanes having S/ 

Ns 5514 through 5595 inclusive: Within 30 

days after August 30, 2005 (the effective date 

of AD 2005–15–04), revise the ALS of the 

applicable Instructions for Continued 

Airworthiness to reflect the new life limits of 

the landing gear parts by inserting copies of 

the Canadair temporary revisions (TR) 

specified in table 2 to paragraph (i) of this AD 

into the ALS of the applicable Canadair 

Time-Limits/Maintenance Check Manual. 

When the contents of the TRs are included 

in the general revisions of the ALS, these TRs 

may be removed provided the relevant 

information in the ALS is identical to that in 

the TRs. 

TABLE 2 TO PARAGRAPH (i) OF THIS AD—CANADAIR TEMPORARY REVISIONS

Model— Canadair temporary revision— Manual section— 

Applicable canadair time–

limits/maintenance check 

manual— 

CL–600–1A11 (CL–600) airplanes ............................................ 5–116, dated April 11, 2002 ... 5–10–10 PSP 605. 

CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

5–190, dated April 11, 2002 ... 5–10–10 PSP 601–5. 

CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

5–191, dated April 11, 2002 ... 5–10–11 PSP 601–5. 

CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

5–192, dated April 11, 2002 ... 5–10–12 PSP 601–5. 

CL–600–2B16 (CL–604) airplanes ............................................ 5–2–6, dated April 11, 2002 ... 5–10–10 CL–604. 

CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

5–204, dated April 11, 2002 ... 5–10–10 PSP 601A–5. 

CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

5–205, dated April 11, 2002 ... 5–10–11 PSP 601A–5. 

CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and 

CL–601–3R) airplanes.

5–206, dated April 11, 2002 ... 5–10–12 PSP 601A–5. 

(j) Retained Parts Installation Limitation 

This paragraph restates the limitations 

specified in paragraph (i) of AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005), with revised affected airplanes. Except 

for Model CL–600–2B16 airplanes having 

serial numbers 5514 through 5595 inclusive: 

As of August 30, 2005 (the effective date of 

AD 2005–15–04), no person may install on 

any airplane a landing gear part, unless it has 

had the applicable part number or serial 

number added in accordance with paragraph 

(g) of this AD; and has had the number of 

landings established in accordance with 

paragraph (h) of this AD. 

(k) Retained Stipulation of Information of 

No Reporting 

This paragraph restates the stipulation 

specified in paragraph (j) of AD 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005). Although the service bulletins 

identified in paragraph (g) of this AD specify 

that operators should submit incorporation 

notices to Bombardier after each new part 

number or serial number and landings 

assigned to these parts is added, this AD does 

not include that action. 

(l) New Requirement of this AD: Add Serial 

Numbers and Part Numbers 

(1) For Model CL–600–2B16 (CL–604 

Variant) airplanes: Within 96 months after 

the effective date of this AD, add serial 

numbers and part numbers, as applicable, to 

the parts identified in paragraphs (l)(1)(i) and 

(l)(1)(ii) of this AD, as applicable, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

604–32–014, Revision 02, dated May 9, 2011, 

including Appendix 1, dated May 9, 2011, 

and Service Bulletin Information Sheet, 

dated July 6, 2010. 

(i) For airplanes having S/Ns 5301 through 

5513 inclusive: Main fitting/drag stay pin of 

the NLG having P/N 200811721. 

(ii) For airplanes having S/Ns 5301 through 

5573 inclusive, 5579, and 5595: NLG 

crossbeam pins having P/N 200814601 and 

NLG center hinge pins having P/N 

200814624. 

(2) For Bombardier Model CL–600–2A12 

(CL–601) airplanes and Model CL–600–2B16 

(CL–601–3A and CL–601–3R Variants) 

airplanes: Within 60 months after the 

effective date of this AD, add serial numbers 

and part numbers, as applicable, to left and 

right MLG side strut pins having P/N 6318– 

1 or 6318–3; and to left and right MLG hinge 

pins having P/N 6329–3; in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 601–0546, 

Revision 03, dated May 9, 2011, including 

Appendix 1, dated May 9, 2011, and Service 


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49438 Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 

Bulletin Information Sheet, dated July 6, 

2010. 

(3) For Bombardier Model CL–600–2A12 

(CL–601) airplanes and Model CL–600–2B16 

(CL–601–3A and CL–601–3R Variants) 

airplanes: Within 120 months after the 

effective date of this AD, add serial numbers 

and part numbers, as applicable, to NLG 

main fitting/drag stay pins having P/N 

200811721; NLG drag brace pivot pins having 

P/N 200814601; and left and right MLG 

pintle pins having P/N 6324–1; in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 601–0546, 

Revision 03, dated May 9, 2011, including 

Appendix 1, dated May 9, 2011, and Service 

Bulletin Information Sheet, dated July 6, 

2010. 

(4) For Bombardier Model CL–600–1A11 

(CL–600) airplanes: Within 120 months after 

the effective date of this AD, add serial 

numbers and part numbers, as applicable, to 

NLG main fitting/drag stay pins having P/N 

200811721 and NLG drag brace pivot pins 

having P/N 200814601, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 600–0710, 

Revision 03, dated May 9, 2011, including 

Appendix 1, dated May 9, 2011, and Service 

Bulletin Information Sheet, dated July 6, 

2010. 

(m) New Requirement of This AD: Establish 

the Number of Landings (CSN) 

At the applicable times specified in 

paragraph (l) of this AD: If a component does 

not have a serial number and the CSN were 

not tracked, use Appendix 1, dated May 9, 

2011, of the applicable service bulletin 

specified in paragraph (m)(1), (m)(2), or 

(m)(3) of this AD to establish the number of 

landings (CSN). 

(1) Bombardier Service Bulletin 604–32– 

014, Revision 02, dated May 9, 2011, 

including Service Bulletin Information Sheet, 

dated July 6, 2010 (for Bombardier Model 

CL–600–2B16 (CL–604 Variant) airplanes). 

(2) Bombardier Service Bulletin 601–0546, 

Revision 03, dated May 9, 2011, including 

Service Bulletin Information Sheet, dated 

July 6, 2010 (for Model CL–600–2A12 (CL– 

601) airplanes and Model CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes). 

(3) Bombardier Service Bulletin 600–0710, 

Revision 03, dated May 9, 2011, including 

Service Bulletin Information Sheet, dated 

July 6, 2010 (for Bombardier Model CL–600– 

1A11 (CL–600) airplanes). 

(n) New Requirement of This AD: Records 

Update 

Concurrently with the actions specified in 

paragraphs (l) and (m) of this AD: Record any 

newly calculated CSN, new part numbers, 

and new serial numbers in the airplane 

technical records and manuals. 

(o) New Requirement of This AD: Parts 

Installation Limitation 

As of the effective date of this AD, no 

person may install on any airplane a landing 

gear part identified in paragraph (l) of this 

AD, unless it has had the applicable part 

number or serial number added as required 

by paragraph (l) of this AD, and had the CSN 

established as required by paragraph (m) of 

this AD. 

(p) New Action of This AD: Optional Method 

of Compliance 

Accomplishing the action required by 

paragraph (g) of this AD, in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin specified in 

paragraph (p)(1), (p)(2), or (p)(3) of this AD, 

is acceptable for compliance with the 

requirements of paragraph (g) of this AD. 

(1) Bombardier Service Bulletin 601–0546, 

Revision 03, dated May 9, 2011, including 

Appendix 1, dated May 9, 2011, and Service 

Bulletin Information Sheet, dated July 6, 

2010 (for Model CL–600–2A12 (CL–601) 

airplanes and Model CL–600–2B16 (CL–601– 

3A and CL–601–3R Variants) airplanes). 

(2) Bombardier Service Bulletin 604–32– 

014, Revision 02, dated May 9, 2011, 

including Appendix 1, dated May 9, 2011, 

and Service Bulletin Information Sheet, 

dated July 6, 2010 (for Model CL–600–2B16 

(CL–604 Variant) airplanes). 

(3) Bombardier Service Bulletin 600–0710, 

Revision 03, dated May 9, 2011, including 

Appendix 1, dated May 9, 2011, and Service 

Bulletin Information Sheet, dated July 6, 

2010 (for Model CL–600–1A11 (CL–600) 

airplanes). 

(q) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before 

August 30, 2005 (the effective date of AD 

2005–15–04, Amendment 39–14193 (70 FR 

43032, July 26, 2005)), using the applicable 

service bulletin specified in paragraph 

(q)(1)(i), (q)(1)(ii), or (q)(1)(iii) of this AD, 

which are not incorporated by reference in 

this AD. 

(i) Bombardier Service Bulletin 601–0546, 

dated May 31, 2002 (for Model CL–600–2A12 

(CL–601) airplanes and Model CL–600–2B16 

(CL–601–3A and CL–601–3R Variants) 

airplanes). 

(ii) Bombardier Service Bulletin 600–0710, 

dated May 31, 2002 (for ModelCL–600–1A11 

(CL–600) airplanes). 

(iii) Bombardier Service Bulletin 604–32– 

014, dated May 31, 2002 (for Model CL–600– 

2B16 (CL–604 Variant) airplanes). 

(2) This paragraph provides credit for the 

addition of serial numbers and part numbers 

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

actions were performed before the effective 

date of this AD using the applicable service 

bulletin specified in paragraph (q)(2)(i), 

(q)(2)(ii), or (q)(2)(iii) of this AD, which are 

not incorporated by reference in this AD. 

(i) Bombardier Service Bulletin 604–32– 

014, Revision 01, dated October 29, 2007 (for 

Bombardier Model CL–600–2B16 (CL–604 

Variant) airplanes). 

(ii) Bombardier Service Bulletin 601–0546, 

Revision 02, dated October 29, 2007 (for 

Model CL–600–2A12 (CL–601) airplanes and 

Model CL–600–2B16 (CL–601–3A and CL– 

601–3R Variants) airplanes). 

(iii) Bombardier Service Bulletin 600–0710, 

Revision 02, dated October 29, 2007 (for 

Bombardier Model CL–600–1A11 (CL–600) 

airplanes). 

(3) This paragraph provides credit for the 

establishment of the CSN required by 

paragraph (m) of this AD, if those actions 

were performed before the effective date of 

this AD using the applicable service bulletin 

information sheet specified in paragraph 

(q)(3)(i), (q)(3)(ii), or (q)(3)(iii) of this AD. 

(i) Service Bulletin Information Sheet, 

dated July 6, 2010, of Bombardier Service 

Bulletin 604–32–014, Revision 01, dated 

October 29, 2007 (for Bombardier Model CL– 

600–2B16 (CL–604 Variant) airplanes). 

(ii) Service Bulletin Information Sheet, 

dated July 6, 2010, of Bombardier Service 

Bulletin 601–0546, Revision 02, dated 

October 29, 2007 (for Bombardier Model CL– 

600–2A12 (CL–601) and Model CL–600–2B16 

(CL–601–3A and CL–601–3R Variants) 

airplanes). 

(iii) Service Bulletin Information Sheet, 

dated July 6, 2010, of Bombardier Service 

Bulletin 600–0710, Revision 02, dated 

October 29, 2007 (for Bombardier Model CL– 

600–1A11 (CL–600) airplanes). 

(r) 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. If sending information 

directly to the ACO, send it 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 2005–15–04, 

Amendment 39–14193 (70 FR 43032, July 26, 

2005), are approved as AMOCs for the 

corresponding provisions of 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 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(s) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directives specified in 

paragraphs (s)(1)(i), (s)(1)(ii), and (s)(1)(iii) of 

this AD for related information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-1065-0002. 

(i) Canadian Airworthiness Directive CF– 

2003–18R2, dated September 28, 2011. 

(ii) Canadian Airworthiness Directive CF– 

2003–20R1, dated September 28, 2011. 

(iii) Canadian Airworthiness Directive CF– 

2003–21R2, dated September 28, 2011. 


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Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations 49439 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (t)(5) and (t)(6) of this 

AD. 

(t) 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 25, 2014. 

(i) Bombardier Service Bulletin 600–0710, 

Revision 03, dated May 9, 2011, including 

Appendix 1, dated May 9, 2011, and Service 

Bulletin Information Sheet, dated July 6, 

2010. 

(ii) Bombardier Service Bulletin 601–0546, 

Revision 03, dated May 9, 2011, including 

Appendix 1, dated May 9, 2011, and Service 

Bulletin Information Sheet, dated July 6, 

2010. 

(iii) Bombardier Service Bulletin 604–32– 

014, Revision 02, dated May 9, 2011, 

including Appendix 1, dated May 9, 2011, 

and Service Bulletin Information Sheet, 

dated July 6, 2010. 

(4) The following service information was 

approved for IBR on August 30, 2005 (70 FR 

43032, July 26, 2005). 

(i) Bombardier Service Bulletin 600–0710, 

Revision 01, dated December 15, 2003. 

(ii) Bombardier Service Bulletin 601–0546, 

Revision 01, dated December 15, 2003. 

(iii) Bombardier Service Bulletin 604–32– 

014, dated May 31, 2002. 

(iv) Canadair Temporary Revision 5–116, 

dated April 11, 2002. 

(v) Canadair Temporary Revision 5–190, 

dated April 11, 2002. 

(vi) Canadair Temporary Revision 5–191, 

dated April 11, 2002. 

(vii) Canadair Temporary Revision 5–192, 

dated April 11, 2002. 

(viii) Canadair Temporary Revision 5–2–6, 

dated April 11, 2002. 

(ix) Canadair Temporary Revision 5–204, 

dated April 11, 2002. 

(x) Canadair Temporary Revision 5–205, 

dated April 11, 2002. 

(xi) Canadair Temporary Revision 5–206, 

dated April 11, 2002. 

(xii) Messier-Dowty Service Bulletin M–DT 

SB104467009/010–32–1, dated March 19, 

2001. 

(xiii) Messier-Dowty Service Bulletin M– 

DT SB19090–32–4, dated March 19, 2001. 

(xiv) Messier-Dowty Service Bulletin M– 

DT SB20020–32–5, dated July 12, 2001. 

(xv) Messier-Dowty Service Bulletin M–DT 

SB200814001–32–3, dated March 19, 2001. 

(xvi) Messier-Dowty Service Bulletin M– 

DT SB200922001/2–32–6, dated March 19, 

2001. 

(xvii) Messier-Dowty Service Bulletin M– 

DT SB200924003/004–32–16, dated July 12, 

2001. 

(xviii) Messier-Dowty Service Bulletin M– 

DT SB6100–32–10, dated March 19, 2001. 

(xix) Messier-Dowty Service Bulletin M– 

DT SB6500–32–1, dated March 19, 2001. 

(xx) Messier-Dowty Service Bulletin M–DT 

SB7200–32–6, dated March 19, 2001. 

(xxi) Messier-Dowty Service Bulletin M– 

DT SB7300–32–16, dated July 12, 2001. 

(5) For Bombardier, Inc./Canadair 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://www.bombardier.com. For MessierDowty service information identified in this 

AD, contact Messier Services Americas, 

Customer Support Center, 45360 Severn 

Way, Sterling, VA 20166–8910. 

(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 17, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17549 Filed 8–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0511; Directorate 

Identifier 2014–CE–023–AD; Amendment 

39–17953; AD 2014–15–51] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Embraer S.A. Model EMB–500 

airplanes. This AD was sent previously 

to all known U.S. owners and operators 

of these airplanes as an emergency AD. 

This AD requires an inspection and 

replacement as necessary of the barrel 

nuts at the horizontal stabilizer to 

vertical stabilizer attachment joint. This 

AD was prompted by mandatory 

continuing airworthiness information 

(MCAI) issued by the aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as cracking of the 

barrel nuts at the horizontal stabilizer to 

vertical stabilizer attachment joint. We 

are issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective August 21, 

2014 to all persons except those persons 

to whom it was made immediately 

effective by Emergency AD 2014–15–51, 

issued on July 25, 2014, which 

contained the requirements of this 

amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication identified in this 

AD as of August 21, 2014. 

We must receive comments on this 

AD by October 6, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Maill: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact: EMBRAER S.A., 

Phenom Maintenance Support, Avenida 

Brigadeiro Faria Lima, 2170, Putim, 

CEP: 12227–901, Sao Jose dos Campos, 

Sao Paulo, Brasil; phone: (+55 12) 3927– 

1000; Fax: (+55 12) 3927–6600, Ext. 

1448; email: phenom.reliability@

embraer.com.br: Internet: http://www.

embraerexecutivejets.com/en-US/

customer-support/Pages/Service-CenterNetwork.aspxt. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0511; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 


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