Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes, 37768-37770 [2018-16490]

Download as PDF 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. daltland on DSKBBV9HB2PROD with PROPOSALS (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. VerDate Sep<11>2014 16:26 Aug 01, 2018 Jkt 244001 (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. 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. [Docket No. FAA–2018–0638; Product Identifier 2018–NM–016–AD] 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. RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes 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: 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 ADDRESSES: E:\FR\FM\02AUP1.SGM 02AUP1 Federal Register / Vol. 83, No. 149 / Thursday, August 2, 2018 / Proposed Rules 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. 37769 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 Labor cost Borescope and eddy current inspections. daltland on DSKBBV9HB2PROD with PROPOSALS Action 8 work-hours × $85 per hour = $680 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: VerDate Sep<11>2014 16:26 Aug 01, 2018 Jkt 244001 Parts cost $0 Cost per product $680 per inspection cycle ........ 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 PO 00000 Frm 00006 Fmt 4702 Cost on U.S. operators Sfmt 4702 $2,720 per inspection cycle. 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 E:\FR\FM\02AUP1.SGM 02AUP1 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: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [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: daltland on DSKBBV9HB2PROD with PROPOSALS ■ 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. VerDate Sep<11>2014 16:26 Aug 01, 2018 Jkt 244001 (j) Credit for Previous Actions This AD replaces AD 2013–11–03, Amendment 39–17463 (78 FR 32353, May 30, 2013) (‘‘AD 2013–11–03’’). 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. (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 PART 39—AIRWORTHINESS DIRECTIVES § 39.13 (b) Affected ADs 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. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (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 E:\FR\FM\02AUP1.SGM 02AUP1

Agencies

[Federal Register Volume 83, Number 149 (Thursday, August 2, 2018)]
[Proposed Rules]
[Pages 37768-37770]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16490]


-----------------------------------------------------------------------

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 [email protected]; 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: 

[[Page 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
----------------------------------------------------------------------------------------------------------------
                                                             Parts                              Cost on U.S.
              Action                      Labor cost          cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Borescope and eddy current          8 work-hours x $85            $0  $680 per inspection   $2,720 per
 inspections.                        per hour = $680 per               cycle.                inspection cycle.
                                     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

[[Page 37770]]

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

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2. The FAA amends Sec.  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 
left-hand (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 [email protected]; 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]
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