37768 Federal Register / Vol. 83, No. 149 / Thursday, August 2, 2018 / Proposed Rules 

(d) Subject 

Air Transport Association (ATA) of 

America Code 38, Water/waste. 

(e) Reason 

This AD was prompted by leakage of 

shrouded pipe T-boxes in the potable water 

system. We are issuing this AD to address the 

possible leakage of water into the avionics 

bay. This condition, if not corrected, could 

lead to the loss of systems/equipment located 

inside the avionics bay and possible loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 36 months after the effective date 

of this AD: Replace the affected potable water 

T-boxes and clamps with new parts in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A350– 

38–P004, dated April 11, 2018. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards 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 International Section, send it 

to the attention of the person identified in 

paragraph (i)(2) of this AD. Information may 

be emailed to: 9–ANM–116–AMOC– 

REQUESTS@faa.gov. 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, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus SAS’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2018–0111R1, dated 

May 30, 2018, 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– 

2018–0637. 

(2) For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3218. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, Rond-Point Emile Dewoitine 

No: 2, 31700 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 45 80; email continuedairworthiness.a350@airbus.com; internet 

http://www.airbus.com. You may view this 

service information at the FAA, Transport 

Standards Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

Issued in Des Moines, Washington, on July 

23, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–16488 Filed 8–1–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0638; Product 

Identifier 2018–NM–016–AD] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificate Previously 

Held by Bombardier, Inc.; Canadair 

Limited) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–11– 

03, which applies to certain Viking Air 

Limited Model CL–215–1A10 and CL– 

215–6B11 (CL–215T Variant) airplanes. 

AD 2013–11–03 requires repetitive 

detailed inspections for cracking of the 

left-hand (LH) and right-hand (RH) wing 

lower skin, and repair if necessary. AD 

2013–11–03 was prompted by reports of 

a fractured wing lower rear spar cap and 

reinforcing strap. Since we issued AD 

2013–11–03, further analysis has 

indicated the need for repetitive eddy 

current and borescope inspections. This 

proposed AD would require repetitive 

borescope inspections of the LH and RH 

wing lower skin and repetitive eddy 

current inspections of the LH and RH 

wing front and rear lower spar caps. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by September 17, 

2018. 

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. 

• Mail: 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 NPRM, 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 acs-technical.publications@

vikingair.com; internet http://

www.vikingair.com. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

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–2018– 

0638; 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 NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Andrea Jimenez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Section, FAA, New York ACO Branch, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7330; fax 516–794–5531. 

SUPPLEMENTARY INFORMATION: 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 149 / Thursday, August 2, 2018 / Proposed Rules 37769 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0638; Product Identifier 2018– 

NM–016–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued AD 2013–11–03, 

Amendment 39–17463 (78 FR 32353, 

May 30, 2013) (‘‘AD 2013–11–03’’), for 

certain Viking Air Limited Model CL– 

215–1A10 and CL–215–6B11 (CL–215T 

Variant) airplanes. AD 2013–11–03 

requires repetitive detailed inspections 

for cracking of the LH and RH wing 

lower skin, and repair if necessary. AD 

2013–11–03 resulted from reports of a 

fractured wing lower rear spar cap and 

reinforcing strap. We issued AD 2013– 

11–03 to detect and correct cracked 

wing structure, which could result in 

failure of the wing. 

Actions Since AD 2013–11–03 Was 

Issued 

Since we issued AD 2013–11–03, an 

operator reported damage to the wing 

lower skin and rear spar of an airplane. 

This damage was noticed 95 flight hours 

after an ultrasonic inspection. Further 

analysis by the airplane manufacturer 

and the FAA has determined that the 

ultrasonic inspection might not have 

been adequate to detect a crack in the 

spar cap, and there is a need for 

repetitive eddy current and borescope 

inspections. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive, CF–2013– 

11R1, dated October 30, 2017 (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 and CL–215–6B11 

(CL–215T Variant) airplanes. The MCAI 

states: 

While performing modifications on a CL– 

215–1A10 aeroplane, an operator discovered 

that the wing lower rear spar cap and 

reinforcing strap were fractured at Wing 

Stations (WS) 49.5 and 50 respectively and 

the rear spar web and wing lower skin were 

also cracked. It is suspected that a crack 

initiated at the wing lower spar cap, leading 

to its failure, the subsequent failure of the 

reinforcing strap and cracking of the spar 

web and wing lower skin. The damage was 

outside of the area addressed by the 

repetitive ultrasonic inspections required by 

[Canadian] AD CF–1992–26R2 [which 

corresponds to FAA AD 2012–11–04, 

Amendment 39–17067 (77 FR 32892, June 4, 

2012)] and was found 95 hours air time after 

the last ultrasonic inspection. 

Failure and cracking of the above-noted 

wing structure, if not detected, could result 

in failure of the wing. 

In order to mitigate the unsafe condition, 

[Canadian] AD CF–2013–11 [which 

corresponds to FAA AD 2013–11–03] was 

released. However, further analysis has 

indicated the need for repetitive eddy current 

and borescope inspections. Therefore, 

Revision 1 of this [Canadian] AD mandates 

a repetitive detailed inspection of the wing 

lower skin using a borescope, changes the 

one-time eddy current inspection of the 

lower front and rear spar caps to a repetitive 

inspection and eliminates the one-time 

detailed inspection with fuel bladders 

removed. 

The requirements of [Canadian] AD CF– 

1992–26R2 remain applicable. 

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–2018– 

0638. 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Alert Service 

Bulletin 215–A558, Revision 3, dated 

June 3, 2016. This service information 

describes procedures for detecting 

cracks using repetitive borescope 

inspections of the LH and RH wing 

lower skin and repetitive eddy current 

inspections of the LH and RH wing front 

and rear lower spar caps. 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. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

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

Borescope and eddy current inspections.8 work-hours × $85 per hour = 

$680 per inspection cycle.

$0 $680 per inspection cycle ........ $2,720 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 


daltland on DSKBBV9HB2PROD with PROPOSALS
37770 Federal Register / Vol. 83, No. 149 / Thursday, August 2, 2018 / Proposed Rules 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2013–11–03, Amendment 39–17463 (78 

FR 32353, May 30, 2013), and adding 

the following new AD: 

Viking Air Limited (Type Certificate 

Previously Held by Bombardier, Inc.; 

Canadair Limited): Docket No. FAA– 

2018–0638; Product Identifier 2018– 

NM–016–AD. 

(a) Comments Due Date 

We must receive comments by September 

17, 2018. 

(b) Affected ADs 

This AD replaces AD 2013–11–03, 

Amendment 39–17463 (78 FR 32353, May 30, 

2013) (‘‘AD 2013–11–03’’). 

(c) Applicability 

This AD applies to the Viking Air Limited 

(Type Certificate previously held by 

Bombardier, Inc.; Canadair Limited) 

airplanes identified in paragraphs (c)(1) and 

(c)(2) of this AD, certificated in any category. 

(1) Model CL–215–1A10 airplanes, serial 

numbers (S/Ns) 1001 through 1125 inclusive. 

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

airplanes, S/Ns 1056 through 1125 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking of the wing lower skin and rear spar. 

We are issuing this AD to address cracked 

wing structure, which could result in failure 

of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Borescope Inspection 

Within 50 flight hours after the effective 

date of this AD: Using a borescope, do a 

detailed inspection for cracking of the lefthand (LH) and right-hand (RH) wing lower 

skin between wing station (WS) 45.00 and 

51.00, in accordance with Part A of 

Bombardier Alert Service Bulletin 215–A558, 

Revision 3, dated June 3, 2016. Repeat the 

inspection thereafter at intervals not to 

exceed 50 flight hours until the initial eddy 

current inspection required by paragraph (h) 

of this AD has been accomplished. After 

accomplishment of the initial eddy current 

inspection required by paragraph (h) of this 

AD, the borescope inspection interval 

required by this paragraph may be extended 

to 300 flight hours. 

(h) Repetitive Eddy Current Inspections 

Within 300 flight hours after the effective 

date of this AD: Do an eddy current 

inspection for cracking of the LH and RH 

wing front and rear lower spar caps, in 

accordance with Parts C–1 and C–2 of 

Bombardier Alert Service Bulletin 215–A558, 

Revision 3, dated June 3, 2016. Repeat the 

inspection thereafter at intervals not to 

exceed 300 flight hours. 

(i) Corrective Actions 

If any crack, as defined in Bombardier 

Alert Service Bulletin 215–A558, Revision 3, 

dated June 3, 2016, is found during any 

inspection required by paragraph (g) or 

paragraph (h) of this AD: Before further 

flight, repair using a method approved by the 

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. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

initial inspections required by paragraphs (g) 

and (h) of this AD if those actions were 

performed before the effective date of this AD 

using Bombardier Alert Service Bulletin 215– 

A558, Revision 1, dated January 10, 2014; or 

Bombardier Alert Service Bulletin 215–A558, 

Revision 2, dated January 17, 2014. 

(k) No Reporting Requirement 

Although Bombardier Alert Service 

Bulletin 215–A558, Revision 3, dated June 3, 

2016, specifies to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

(l) Other FAA AD Provisions 

(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. 

(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 TCCA; or Viking Air Limited’s TCCA 

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–2013–11R1, 

dated October 30, 2017, 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–2018–0638. 

(2) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

Airframe and Mechanical Systems Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7330; fax 516–794–5531. 

(3) For service information identified in 

this AD, 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 service information at the FAA, 

Transport Standards Branch, 2200 South 

216th St., Des Moines, WA. For information 

on the availability of this material at the 

FAA, call 206–231–3195. 

Issued in Des Moines, Washington, on July 

23, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–16490 Filed 8–1–18; 8:45 am] 

BILLING CODE 4910–13–P 


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