42024 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations 

AD 2016–04–01, effective April 4, 2016, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0008. 

(2) For more information about this AD, 

contact Ana Martinez Hueto, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone 

425–227–1622; fax 425–227–1320. 

(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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 11, 2017. 

(i) Appendix A, Airworthiness Limitations 

(AL), of the EMBRAER ERJ 190/195 

Maintenance Review Board Report, MRB– 

1928, Revision 9, dated August 14, 2015. 

(ii) Appendix A, Airworthiness Limitations 

(AL), of the EMBRAER Lineage 1000/1000E 

Maintenance Planning Guide, MPG–2928, 

Revision 4, dated July 14, 2014. 

(iii) EMBRAER MPG—Temporary Revision 

4–2, dated February 13, 2015. 

(iv) EMBRAER MPG—Temporary Revision 

4–3, dated October 30, 2015. 

(v) EMBRAER MRB—Temporary Revision 

9–1, dated October 27, 2015. 

(vi) EMBRAER MRB—Temporary Revision 

9–3, dated October 27, 2015. 

(4) The following service information was 

approved for IBR on January 14, 2013 (77 FR 

73270, December 10, 2012). 

(i) EMBRAER Temporary Revision (TR) 5– 

1, dated February 11, 2011, to Part 2— 

Airworthiness Limitation Inspections (ALI)— 

Structures, of Appendix A, Airworthiness 

Limitations (AL), of the EMBRAER 190 

Maintenance Review Board Report, MRB– 

1928, Revision 5, dated November 11, 2010. 

(ii) Appendix A, Airworthiness Limitation 

(AL), of the EMBRAER 190 Maintenance 

Review Board Report, MRB–1928, Revision 5, 

dated November 11, 2010. 

(5) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone 

+55 12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.com. 

(6) You may view this service information 

at the FAA, Transport Standards Branch, 

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 28, 

2017. 

John P. Piccola, Jr., 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–16667 Filed 9–5–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0474; Product 

Identifier 2016–NM–096–AD; Amendment 

39–19007; AD 2017–17–17] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificate Previously 

Held by Bombardier, Inc.; Canadair 

Limited) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–03– 

08, which applied to certain 

Bombardier, Inc., Model CL–215–1A10 

(CL–215), CL–215–6B11 (CL–215T 

Variant), and CL–215–6B11 (CL–415 

Variant) airplanes. AD 2011–03–08 

required an inspection to determine the 

number of flight cycles accumulated by 

certain accumulators installed on the 

airplane, and repetitive inspections of 

the accumulators for cracks, and 

replacement if necessary. This AD 

retains those inspections and the 

accumulator replacement if necessary, 

and adds a new terminating action to 

address the identified unsafe condition. 

This AD was prompted by the 

development of a terminating action for 

the repetitive inspections. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 11, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 11, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 14, 2011 (76 FR 

6536, February 7, 2011). 

ADDRESSES: For service information 

identified in this final rule, contact 

Viking Air Limited, 1959 de Havilland 

Way, Sidney, British Columbia V8L 

5V5, Canada; telephone +1–250–656– 

7227; fax +1–250–656–0673; email acstechnical.publications@vikingair.com; 

Internet http://www.vikingair.com. You 

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0474. 

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–2017– 

0474; 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 address for the 

Docket Office (telephone 800–647–5527) 

is 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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Cesar A. Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Section, FAA, New York ACO Branch, 

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 2011–03–08, 

Amendment 39–16592 (76 FR 6536, 

February 7, 2011) (‘‘AD 2011–03–08’’). 

AD 2011–03–08 applied to certain 

Bombardier, Inc., Model CL–215–1A10 

(CL–215), CL–215–6B11 (CL–215T 

Variant), and CL–215–6B11 (CL–415 

Variant) airplanes. The NPRM 

published in the Federal Register on 

May 18, 2017 (82 FR 22766). The NPRM 

was prompted by the development of a 

terminating action (relocation of the 

affected accumulators, and 

incorporation of new airworthiness 

limitations), which addresses the unsafe 

condition. The NPRM proposed to 

continue to require an inspection to 

determine the number of flight cycles 

accumulated by applicable 

accumulators (i.e., brake, aileron, 

elevator, and rudder accumulators) 

installed on the airplane, repetitive 

ultrasonic inspections of the 

accumulators for cracks, and 


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replacement of any accumulator in 

which a crack is detected. The NPRM 

also proposed to require a new 

terminating action for the repetitive 

inspections. We are issuing this AD to 

prevent failure of the screw cap or end 

cap of certain accumulators, which 

could result in impact damage to 

various components, potentially 

resulting in fuel spillage, uncommanded 

flap movement, or loss of aileron 

control. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2009–42R2, 

dated May 30, 2016 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ’’the 

MCAI’’), to correct an unsafe condition 

for certain Viking Air Limited Model 

CL–215–1A10 (CL–215), CL–215–6B11 

(CL–215T Variant), and CL–215–6B11 

(CL–415 Variant) airplanes. The MCAI 

states: 

Seven cases of on-ground hydraulic 

accumulator screw cap or end cap failure 

have been experienced on CL–600–2B19 

(CRJ) aeroplane, resulting in loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. To date, the lowest number of 

flight cycles accumulated at the time of 

failure has been 6991. 

Although there have been no failures to 

date on any CL–215–1A10 (CL–215) or CL– 

215–6B11 (CL–215T and CL–415) aeroplane, 

similar accumulators, Part Number (P/N) 08– 

8423–010 (MS28700–3), to those installed on 

the CL–600–2B19, are installed on the 

aeroplane models listed in the Applicability 

section of this [Canadian] AD. 

A detailed analysis of the systems and 

structure in the potential line of trajectory of 

a failed screw cap/end cap for each 

accumulator has been conducted. It has 

identified that the worst-case scenarios 

would be impact damage to various 

components, potentially resulting in fuel 

spillage, uncommanded flap movement, or 

loss of aileron control. 

This [Canadian] AD mandates repetitive 

[ultrasonic] inspections of the accumulators 

for cracks and replacement of any 

accumulator in which a crack is detected. 

Revision 1 of this [Canadian] AD clarified 

the text of the [Canadian] AD, including the 

P/N of the affected accumulators. 

This revision provides the terminating 

action [relocation of affected accumulators 

and incorporation of new airworthiness 

limitations] to this [Canadian] AD. It also 

modifies the applicability range for the CL– 

215–1A10 (CL–215); the CL–215 is out of 

production and the last aeroplane produced 

was serial number 1125. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0474. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Changes Made to This 

Final Rule 

We have revised this final rule to 

identify the legal name of the 

manufacturer as published in the most 

recent type certificate data sheet for the 

affected airplane models. 

In the proposed AD, we inadvertently 

listed the wrong publication dates for 

service information in two places. Table 

4 to paragraph (o) of the proposed AD 

referred to Bombardier Service Bulletin 

215–4470, Revision 1, dated December 

13, 2013. We have corrected the 

publication date for this document to 

June 27, 2014, in this AD. Additionally, 

paragraph (r)(1)(iii) of the proposed AD 

referred to Bombardier Service Bulletin 

215–3158, dated March 28, 2012. We 

have corrected the publication date for 

this document to March 21, 2012, in 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 changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Bombardier, Inc., has issued the 

following service information: 

• Bombardier Service Bulletin 215– 

552, Revision 2, dated June 18, 2015. 

This service information describes 

procedures to relocate the aileron 

hydraulic accumulator aft of its current 

location. 

• Bombardier Service Bulletin 215– 

3158, Revision 2, dated April 15, 2014; 

and Bombardier Service Bulletin 215– 

4423, Revision 5, dated March 17, 2016. 

This service information describes 

procedures to relocate the aileron, 

elevator, and rudder hydraulic 

accumulators aft and outboard of their 

current locations. These documents are 

distinct since they apply to different 

airplane models. 

• Bombardier Service Bulletin 215– 

557, Revision 1, dated June 27, 2014; 

Bombardier Service Bulletin 215–3182, 

Revision 1, dated June 27, 2014; and 

Bombardier Service Bulletin 215–4470, 

Revision 1, dated June 27, 2014. This 

service information describes 

procedures to establish the number of 

flight hours for each accumulator and 

determine if it has been used on another 

type of aircraft. These documents are 

distinct since they apply to different 

airplane models. 

• Bombardier Temporary Revision 5– 

56, dated December 13, 2013; 

Bombardier Temporary Revision 295/7, 

dated December 13, 2013; Bombardier 

Temporary Revision LLC–1, dated 

December 13, 2013; and Bombardier 

Temporary Revision LLC–3, dated 

December 13, 2013. This service 

information provides a 10,000-hour 

accumulator life limitation for certain 

accumulators. These documents are 

distinct since they apply to different 

airplane models. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 7 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Ultrasonic inspection (retained action from 

AD 2011–03–08).

7 work-hours × $85 per hour = $595 ............. $0 $595 $4,165 

Relocation, determination of accumulator 

hours and usage, and maintenance or inspection program revision (new action).

56 work-hours × $85 per hour = $4,760 ........ 0 4,760 33,320 


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We estimate the following costs to do 

any necessary replacement that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of cracked part (retained action from AD 

2011–03–08).

6 work-hours × $85 per hour = $510 ........................... $4,055 $4,565 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

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. 

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) 

2011–03–08, Amendment 39–16592 (76 

FR 6536, February 7, 2011), and adding 

the following new AD: 

2017–17–17 Viking Air Limited (Type 

Certificate Previously Held by 

Bombardier, Inc.; Canadair Limited): 

Amendment 39–19007; Docket No. 

FAA–2017–0474; Product Identifier 

2016–NM–096–AD. 

(a) Effective Date 

This AD is effective October 11, 2017. 

(b) Affected ADs 

This AD replaces AD 2011–03–08, 

Amendment 39–16592 (76 FR 6536, February 

7, 2011) (‘‘AD 2011–03–08’’). 

(c) Applicability 

This AD applies to Viking Air Limited 

(Type Certificate previously held by 

Bombardier, Inc.; Canadair Limited) 

airplanes, certificated in any category, as 

identified in paragraphs (c)(1) through (c)(3) 

of this AD. 

(1) Model CL–215–1A10 (CL–215) 

airplanes, serial numbers 1001 through 1125 

inclusive. 

(2) Model CL–215–6B11 (CL–215T Variant) 

airplanes, serial numbers 1056 through 1125 

inclusive. 

(3) Model CL–215–6B11 (CL–415 Variant) 

airplanes, serial numbers 2001 through 2990 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic power. 

(e) Reason 

This AD was prompted by reports of onground hydraulic accumulator screw cap or 

end cap failure resulting in a loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. We are issuing this AD to prevent 

failure of the screw cap or end cap, which 

could result in impact damage to various 

components, potentially resulting in fuel 

spillage, uncommanded flap movement, or 

loss of aileron control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection To Determine Flight 

Cycles, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–03–08, with no 

changes. Within 50 flight hours after March 

14, 2011 (the effective date of AD 2011–03– 

08), inspect to determine the number of flight 

cycles accumulated by each of the applicable 

accumulators (i.e., brake, aileron, elevator, 

and rudder accumulators) having part 

number 08–8423–010 (MS28700–3) installed 

on the airplane. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the number of flight cycles 

accumulated can be conclusively determined 

from that review. 

(h) Retained Initial Ultrasonic Inspection for 

Model CL–215–1A10 (CL–215) and CL–215– 

6B11 (CL–215T Variant) Airplanes, With No 

Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–03–08, with no 

changes. For Model CL–215–1A10 (CL–215) 

and CL–215–6B11 (CL–215T Variant) 

airplanes: Do an ultrasonic inspection for 

cracking of the accumulator at the applicable 

time specified in paragraph (h)(1) or (h)(2) of 

this AD, in accordance with Part B of the 

Accomplishment Instructions of the 


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applicable service bulletin listed in table 1 to 

paragraphs (h), (i), and (k) of this AD. 

TABLE 1 TO PARAGRAPHS (h), (i), AND

(k) OF THIS AD—SERVICE BULLETINS

For model— Use bombardier service 

bulletin— 

CL–215–1A10 (CL–215) 215–541, Revision 1, 

dated March 12, 2010. 

CL–215–6B11 (CL–215T 

Variant).

215–3155, Revision 1, 

dated March 12, 2010. 

CL–215–6B11 (CL–415 

Variant).

215–4414, Revision 1, 

dated March 12, 2010. 

(1) For any accumulator on which the 

inspection required by paragraph (g) of this 

AD shows an accumulation of more than 875 

total flight cycles, or on which it is not 

possible to determine the number of total 

accumulated flight cycles, do the inspection 

within 125 flight cycles after March 14, 2011 

(the effective date of AD 2011–03–08). 

(2) For any accumulator on which the 

inspection required by paragraph (g) of this 

AD shows an accumulation of 875 total flight 

cycles or fewer, do the inspection before the 

accumulation of 1,000 flight cycles on the 

accumulator. 

(i) Retained Initial Ultrasonic Inspection for 

Model CL–215–6B11 (CL–415 Variant) 

Airplanes, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–03–08, with no 

changes. For Model CL–215–6B11 (CL–415 

Variant) airplanes, do an ultrasonic 

inspection for cracking of the accumulator at 

the applicable time specified in paragraph 

(i)(1) or (i)(2) of this AD, in accordance with 

Part B of the Accomplishment Instructions of 

the applicable service bulletin listed in table 

1 to paragraphs (h), (i), and (k) of this AD. 

(1) For any accumulator on which the 

inspection required by paragraph (g) of this 

AD shows an accumulation of more than 750 

flight cycles, or on which it is not possible 

to determine the number of total 

accumulated flight cycles, do the inspection 

within 250 flight cycles after March 14, 2011 

(the effective date of AD 2011–03–08). 

(2) For any accumulator on which the 

inspection required by paragraph (g) of this 

AD shows an accumulation of 750 total flight 

cycles or fewer, do the inspection before the 

accumulation of 1,000 flight cycles on the 

accumulator. 

(j) Retained Repetitive Inspections, With 

New Terminating Action 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–03–08, with new 

terminating action. If no cracking is found 

during any inspection required by paragraph 

(h) or (i) of this AD, repeat the inspection 

thereafter at intervals not to exceed 750 flight 

cycles until the actions required by 

paragraphs (n), (o), and (p) of this AD have 

been done. 

(k) Retained Replacement of Cracked 

Accumulators and Repetitive Inspections, 

With New Terminating Action 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–03–08, with new 

terminating action. If any cracking is found 

during any inspection required by paragraph 

(h) or (i) of this AD, before further flight, 

replace the accumulator with a serviceable 

accumulator, in accordance with Part B of the 

Accomplishment Instructions of the 

applicable service bulletin listed in table 1 to 

paragraphs (h), (i), and (k) of this AD. Doing 

the replacement does not end the inspection 

requirements of paragraphs (h) and (i) of this 

AD. Repeat the inspections required by 

paragraph (h) or (i) of this AD, as applicable, 

at intervals not to exceed 750 flight cycles 

until the actions required by paragraphs (n), 

(o), and (p) of this AD have been done. 

(l) Retained Parts Installation Limitation, 

With No Changes 

This paragraph restates the parts 

installation limitation in paragraph (l) of AD 

2011–03–08, with no changes. As of March 

14, 2011 (the effective date of AD 2011–03– 

08), no person may install an accumulator, 

part number 08–8423–010 (MS28700–3), on 

any airplane unless the accumulator has been 

inspected in accordance with the 

requirements of paragraph (h) or (i) of this 

AD. 

(m) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the credit provided 

in paragraph (m) of AD 2011–03–08, with no 

changes. Inspections accomplished before 

March 14, 2011 (the effective date of AD 

2011–03–08), in accordance with the 

applicable service bulletin listed in table 2 to 

paragraph (m) of this AD are considered 

acceptable for compliance with the 

corresponding action specified in paragraph 

(h), (i), (j), or (k) of this AD. 

TABLE 2 TO PARAGRAPH (m) OF THIS

AD—CREDIT SERVICE BULLETINS

For model— Use Bombardier Service 

Bulletin— 

CL–215–1A10 (CL–215) 215–541, dated July 9, 

2009. 

CL–215–6B11 (CL–215T 

Variant).

215–3155, dated July 9, 

2009. 

CL–600–6B11 (CL–415 

Variant).

215–4414, dated July 9, 

2009. 

(n) New Relocation of Affected 

Accumulators 

Within 12 months after the effective date 

of this AD, relocate affected hydraulic 

accumulators, in accordance with the 

Accomplishment Instructions of the 

applicable Bombardier service bulletin 

specified in table 3 to paragraph (n) of this 

AD. 

TABLE 3 TO PARAGRAPH (n) OF THIS AD—SERVICE INFORMATION FOR RELOCATING ACCUMULATORS

For model— Affected accumulators— Use Service Bulletin— 

CL–215–1A10 (CL–215) ................. Aileron, if installed ......................... Bombardier Service Bulletin 215–552, Revision 2, dated June 18, 

2015. 

CL–215–6B11 (CL–215T Variant) .. Aileron, rudder, and elevator ......... Bombardier Service Bulletin 215–3158, Revision 2, dated April 15, 

2014. 

CL–215–6B11 (CL–415 Variant) ..... Aileron, rudder, and elevator ......... Bombardier Service Bulletin 215–4423, Revision 5, dated March 17, 

2016. 

(o) New Establishment of Flight Hours on the 

Accumulator, Determination of Previous Use 

of the Accumulator, and Replacement if 

Necessary 

Within 12 months after the effective date 

of this AD, establish the number of flight 

hours for each accumulator, and determine 

whether any accumulator has been used in 

service on another type of airplane other than 

Model CL–215–1A10 (CL–215), CL–215– 

6B11 (CL–215T Variant), or CL–215–6B11 

(CL–415 Variant), in accordance with the 

Accomplishment Instructions in the 

applicable Bombardier service bulletin 

specified in table 4 to paragraph (o) of this 

AD. If any accumulator is found that has 

been in service on another type of airplane 

other than Model CL–215–1A10 (CL–215), 

CL–215–6B11 (CL–215T Variant), or CL–215– 

6B11 (CL–415 Variant), replace the 

accumulator within 50 flight hours after 

determining an affected accumulator is 

installed. 

TABLE 4 TO PARAGRAPH (o) OF THIS AD—ESTABLISHMENT OF NUMBER OF FLIGHT HOURS ON THE ACCUMULATOR

For model— Use Service Bulletin— 

CL–215–1A10 (CL–215) ..................................... Bombardier Service Bulletin 215–557, Revision 1, dated June 27, 2014 (applicable to 

MS28700–3 accumulator). 


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TABLE 4 TO PARAGRAPH (o) OF THIS AD—ESTABLISHMENT OF NUMBER OF FLIGHT HOURS ON THE ACCUMULATOR— 

Continued 

For model— Use Service Bulletin— 

CL–215–6B11 (CL–215T Variant) ...................... Bombardier Service Bulletin 215–3182, Revision 1, dated June 27, 2014. 

CL–215–6B11 (CL–415 Variant) ........................ Bombardier Service Bulletin 215–4470, Revision 1, dated June 27, 2014. 

(p) New Airworthiness Limitations 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

10,000-hour accumulator life limitation 

specified in the applicable Time Limits/ 

Maintenance Checks (TLMC) Manual 

temporary revisions (TRs) listed in table 5 to 

paragraph (p) of this AD. The initial 

compliance time for accomplishing the 

replacement of the accumulator is within the 

limitation specified in the applicable TR 

specified in table 5 to paragraph (p) of this 

AD, or within 30 days after the effective date 

of this AD, whichever occurs later. 

TABLE 5 TO PARAGRAPH (p) OF THIS AD—AIRWORTHINESS LIMITATIONS

For model— Comply with Bombardier 

TLMC manual— Bombardier TR No.— Dated— 

CL–215–1A10 (CL–215) ................................................................. PSP 295 ......................... 295/7 .............................. December 13, 2013. 

CL–215–6B11 (CL–215T Variant) .................................................. PSP 395 ......................... LLC–3 ............................ December 13, 2013. 

CL–215–6B11 (CL–215T Variant) .................................................. PSP 395–1 ..................... LLC–1 ............................ December 13, 2013. 

CL–215–6B11 (CL–415 Variant) .................................................... PSP 495 ......................... 5–56 ............................... December 13, 2013. 

(q) No Alternative Actions and Intervals 

After accomplishment of the revision 

required by paragraph (p) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions and 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (s)(1) of this AD. 

(r) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (n) of this AD, 

if those actions were performed before the 

effective date of this AD using any applicable 

service information specified in paragraphs 

(r)(1)(i) through (r)(1)(ix) of this AD. 

(i) Bombardier Service Bulletin 215–552, 

dated December 16, 2013. 

(ii) Bombardier Service Bulletin 215–552, 

Revision 1, dated September 12, 2014. 

(iii) Bombardier Service Bulletin 215–3158, 

dated March 21, 2012. 

(iv) Bombardier Service Bulletin 215–3158, 

Revision 1, dated December 16, 2013. 

(v) Bombardier Service Bulletin 215–4423, 

Revision NC, dated April 4, 2011. 

(vi) Bombardier Service Bulletin 215–4423, 

Revision 1, dated September 28, 2011. 

(vii) Bombardier Service Bulletin 215– 

4423, Revision 2, dated May 30, 2012. 

(viii) Bombardier Service Bulletin 215– 

4423, Revision 3, dated December 16, 2013. 

(ix) Bombardier Service Bulletin 215–4423, 

Revision 4, dated December 3, 2015. 

(2) This paragraph provides credit for 

actions required by paragraph (o) of this AD, 

if those actions were performed before the 

effective date of this AD using any applicable 

service information specified in paragraphs 

(r)(2)(i) through (r)(2)(iii) of this AD. 

(i) Bombardier Service Bulletin 215–557, 

Revision NC, dated December 13, 2013. 

(ii) Bombardier Service Bulletin 215–3182, 

Revision NC, dated December 13, 2013. 

(iii) Bombardier Service Bulletin 215–4470, 

Revision NC, dated December 13, 2013. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO 

Branch, 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 certification office, 

send it to ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 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. 

(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 Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Viking Air Limited’s TCCA 

Design Approval Organization (DAO). If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2009–42R2, 

dated May 30, 2016, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2017–0474. 

(2) For more information about this AD, 

contact Cesar A. Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7318; fax 516–794–5531. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (u)(5) and (u)(6) of this AD. 

(u) 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 October 11, 2017. 

(i) Bombardier Service Bulletin 215–552, 

Revision 2, dated June 18, 2015. 

(ii) Bombardier Service Bulletin 215–557, 

Revision 1, dated June 27, 2014. 

(iii) Bombardier Service Bulletin 215–3158, 

Revision 2, dated April 15, 2014. 

(iv) Bombardier Service Bulletin 215–3182, 

Revision 1, dated June 27, 2014. 

(v) Bombardier Service Bulletin 215–4423, 

Revision 5, dated March 17, 2016. 

(vi) Bombardier Service Bulletin 215–4470, 

Revision 1, dated June 27, 2014. 

(vii) Bombardier Temporary Revision 5–56, 

dated December 13, 2013. 

(viii) Bombardier Temporary Revision 295/ 

7, dated December 13, 2013. 

(ix) Bombardier Temporary Revision LLC– 

1, dated December 13, 2013. 

(x) Bombardier Temporary Revision LLC– 

3, dated December 13, 2013. 

(4) The following service information was 

approved for IBR on March 14, 2011 (76 FR 

6536, February 7, 2011). 

(i) Bombardier Service Bulletin 215–541, 

Revision 1, dated March 12, 2010. 

(ii) Bombardier Service Bulletin 215–3155, 

Revision 1, dated March 12, 2010. 

(iii) Bombardier Service Bulletin 215–4414, 

Revision 1, dated March 12, 2010. 

(5) For service information identified in 

this AD, contact Viking Air Limited, 1959 de 


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Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations 42029 

Havilland Way, Sidney, British Columbia 

V8L 5V5, Canada; telephone +1–250–656– 

7227; fax +1–250–656–0673; email acstechnical.publications@vikingair.com; 

Internet http://www.vikingair.com. 

(6) You may view this service information 

at the FAA, Transport Standards Branch, 

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 

16, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–17838 Filed 9–5–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0638; Product 

Identifier 2017–CE–018–AD; Amendment 

39–19019; AD 2017–18–10] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries GmbH Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Diamond Aircraft Industries GmbH 

Models DA 42, DA 42 M–NG, and DA 

42 NG airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as crack 

formation on the flap bell crank, which 

could cause the flap bell crank to fail. 

We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective October 11, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 11, 2017. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0638; or in person at Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

For service information identified in 

this AD, contact Diamond Aircraft 

Industries GmbH, N.A. Otto-Stra+e 5, 

A–2700 Wiener Neustadt, Austria, 

telephone: +43 2622 26700; fax: +43 

2622 26780; email: office@diamondair.at; Internet: http://

www.diamondaircraft.com. You may 

view this referenced service information 

at the FAA, Policy and Innovation 

Division, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

Docket No. FAA–2017–0638. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Standards Branch, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4144; fax: (816) 329–4090; email: 

mike.kiesov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Diamond Aircraft 

Industries GmbH Models DA 42, DA 42 

M–NG, and DA 42 NG airplanes. The 

NPRM was published in the Federal 

Register on June 23, 2017 (82 FR 28594). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. The MCAI 

states: 

Cracks and deformation have been found 

on the flap bell crank Part Number (P/N) 

D60–2757–11–00. Frequent high load 

conditions have been identified as the root 

cause. 

This condition, if not detected and 

corrected, could lead to failure of the flap 

bell crank and consequent reduced control of 

the aeroplane. 

To address this potential unsafe condition, 

Diamond Aircraft Industries (DAI) issued 

Mandatory Service Bulletin (MSB) 42–126/ 

MSB 42NG–066 and the corresponding Work 

Instruction (WI) MSB 42–126/WI–MSB 

42NG–066 (single document), hereafter 

referred to as ‘the applicable MSB’ in this 

[EASA] AD, providing inspection and 

modification instructions. 

For the reason described above, this 

[EASA] AD requires modification of the flap 

control system by installing two spacers to 

replace a single long spacer, repetitive 

inspections of the flap bell crank, and, 

depending on findings, replacement of the 

flap bell crank with an improved part. 

Installation of an improved flap bell crank 

constitutes terminating action for the 

repetitive inspections required by this 

[EASA] AD. 

The MCAI can be found in the AD 

docket on the Internet at https://

www.regulations.gov/ 

document?D=FAA-2017-0638-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Diamond Aircraft 

Industries GmbH Mandatory Service 

Bulletin MSB 42–126 MSB/42NG–066, 

dated March 27, 2017 (single 

document), and Work Instruction WI– 

MSB 42–126/WI–MSB 42NG–066, dated 

March 27, 2017 (single document). In 

combination, this service information 

describes procedures for repetitively 

inspecting the flap bell crank for cracks, 

replacing the flap bell crank if cracks are 

found, and modification of the flap 

control system. This service information 

is reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of this AD. 

Costs of Compliance 

We estimate that this AD will affect 

190 products of U.S. registry. We also 

estimate that it will take about 4 workhours per product to comply with the 

initial inspection requirement of this 

AD. The average labor rate is $85 per 

work-hour. 

Based on these figures, we estimate 

the cost of the initial inspection 

requirement of this AD on U.S. 

operators to be $64,000, or $340 per 

product. 

We also estimate that it will take 

about 2 work-hours per product to 


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