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Proposed Rule

Airworthiness Directives; Airbus Airplanes

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Start Preamble

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320 and A321 series airplanes. This AD requires revising the maintenance or inspection Start Printed Page 27725program to incorporate new or more restrictive airworthiness limitations. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the principal structural elements and certain life-limited parts are subject to widespread fatigue damage (WFD). We are proposing this AD to address the unsafe condition on these products.

DATES:

We must receive comments on this proposed AD by July 30, 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 Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@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.

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-2018-0512; 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.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

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-2018-0512; Product Identifier 2017-NM-170-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention.

The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved.

The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions.

In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes.

This AD was prompted by an evaluation by the DAH indicating that the principal structural elements and certain life-limited parts are subject to WFD.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017-0231, dated November 21, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or “the MCAI”), to correct an unsafe condition for all Airbus Model A318, A319, A320 and A321 series airplanes. The MCAI states:

The airworthiness limitations for the A320 family aeroplanes are currently defined and published in the Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) document(s). The Damage Tolerant Airworthiness Limitation Items are published in ALS Part 2, approved by EASA. The instructions contained in the ALS Part 2 have been identified as mandatory actions for continued airworthiness.

Failure to comply with these instructions could result in an unsafe condition.

Previously, EASA issued AD 2016-0239 [which corresponds to FAA AD 2017-22-03, Amendment 39-19083 (82 FR 49091, October 24, 2017) (“AD 2017-22-03”)] to require accomplishment of all maintenance tasks as described in ALS Part 2 at Revision 05, and [EASA] AD 2015-0038 (later revised) [which corresponds to FAA AD 2016-09-06, Amendment 39-18504 (81 FR 26113, May 2, 2016) (“AD 2016-09-06”)] to require the implementation of reduced thresholds and intervals for the detailed inspection of the forward engine mount on both right hand and left hand sides of aeroplanes equipped with CFM56-5A/5B engines, as specified in the ALS task 712111-01.

Since those [EASA] ADs were issued, Airbus published Revision 06 of the ALS Part Start Printed Page 277262, and variations up to 6.3, including new and/or more restrictive items, and new A320 family models were certified and added to the Applicability of the ALS. The ALS Part 2 Revision 06 also includes the reduced threshold and intervals required by EASA AD 2015-0038R1.

For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016-0239 and EASA AD 2015-0038R1, which are superseded, requires accomplishment of all maintenance tasks as described in the ALS Part 2 Revision 06, and ALS Part 2 variations 6.1, 6.2 and 6.3 (hereafter collectively referred to as “the ALS” in this [EASA] AD), and maintains specific compliance times for ALS task 572021-01-1 (Wide Spread Fatigue Damage related).

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-2018-0512.

Relationship Between Proposed AD, AD 2016-09-06 and AD 2017-22-03

This NPRM would not supersede AD 2016-09-06 and AD 2017-22-03. Rather, we have determined that a stand-alone AD would be more appropriate to address the changes in the MCAI. This NPRM would require revising the maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. Accomplishment of the proposed actions would then terminate the requirements of paragraphs (g) and (j) of AD 2016-09-06. Accomplishment of the proposed actions would also terminate paragraphs (g)(2) and (i) of 2017-22-03.

Related Service Information Under 1 CFR Part 51

Airbus has issued A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017. The service information describes new or more restrictive airworthiness limitations.

Airbus has also issued the following variations to A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT—ALI), Revision 06, dated April 10, 2017.

  • A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017. The service information describes ALI tasks applicable to certain Model A320-200 and A321-200 airplane configurations.
  • A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017. The service information describes ALI tasks applicable to Model A321-271N and -272N airplanes.
  • A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, October 24, 2017. The service information describes ALI tasks associated with door stops for certain Model A318, A319, A320, and A321 series airplanes.

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.

This proposed AD would require revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j)(1) of this proposed AD. The request should include a description of changes to the required actions that will ensure the continued damage tolerance of the affected structure.

Differences Between This Proposed AD and the MCAI

The MCAI specifies that if there are findings from the airworthiness limitations section (ALS) inspection tasks, corrective actions must be accomplished in accordance with Airbus maintenance documentation. However, this proposed AD does not include that requirement. Operators of U.S.-registered airplanes are required by general airworthiness and operational regulations to perform maintenance using methods that are acceptable to the FAA. We consider those methods to be adequate to address any corrective actions necessitated by the findings of ALS inspections required by this proposed AD.

Airworthiness Limitations Based on Type Design

The FAA recently became aware of an issue related to the applicability of ADs that require incorporation of an ALS revision into an operator's maintenance or inspection program.

Typically, when these types of ADs are issued by civil aviation authorities of other countries, they apply to all airplanes covered under an identified type certificate (TC). The corresponding FAA AD typically retains applicability to all of those airplanes.In addition, U.S. operators must operate their airplanes in an airworthy condition, in accordance with 14 CFR 91.7(a). Included in this obligation is the requirement to perform any maintenance or inspections specified in the ALS, and in accordance with the ALS as specified in 14 CFR 43.16 and 91.403(c), unless an alternative has been approved by the FAA.

When a type certificate is issued for a type design, the specific ALS, including revisions, is a part of that type design, as specified in 14 CFR 21.31(c).

The sum effect of these operational and maintenance requirements is an obligation to comply with the ALS defined in the type design referenced in the manufacturer's conformity statement. This obligation may introduce a conflict with an AD that requires a specific ALS revision if new airplanes are delivered with a later revision as part of their type design.

To address this conflict, the FAA has approved alternative methods of compliance (AMOCs) that allow operators to incorporate the most recent ALS revision into their maintenance/inspection programs, in lieu of the ALS revision required by the AD. This eliminates the conflict and enables the operator to comply with both the AD and the type design.

However, compliance with AMOCs is normally optional, and we recently became aware that some operators choose to retain the AD-mandated ALS revision in their fleet-wide maintenance/inspection programs, including those for new airplanes delivered with later ALS revisions, to help standardize the maintenance of the fleet. To ensure that operators comply with the applicable ALS revision for newly delivered airplanes containing a later revision than that specified in an AD, we plan to limit the applicability of Start Printed Page 27727ADs that mandate ALS revisions to those airplanes that are subject to an earlier revision of the ALS, either as part of the type design or as mandated by an earlier AD.

This proposed AD therefore applies to certain Model Airbus Model A318, A319, A320 and A321 series airplanes with an original certificate of airworthiness or original export certificate of airworthiness that was issued on or before the date of approval of the ALS revision identified in this proposed AD. Operators of airplanes with an original certificate of airworthiness or original export certificate of airworthiness issued after that date must comply with the airworthiness limitations specified as part of the approved type design and referenced on the type certificate data sheet.

Costs of Compliance

We estimate that this proposed AD affects 1,180 airplanes of U.S. registry.

We estimate the following costs to comply with this proposed AD:

We have determined that revising the maintenance or inspection program takes an average of 90 work-hours per operator, although we recognize that this number may vary from operator to operator. In the past, we have estimated that this action takes 1 work-hour per airplane. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), we have determined that a per-operator estimate is more accurate than a per-airplane estimate. Therefore, we estimate the total cost per operator to be $7,650 (90 work-hours × $85 per work-hour).

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 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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

  • Air transportation
  • Aircraft
  • Aviation safety
  • Incorporation by reference
  • Safety
End List of Subjects

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

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

End Amendment Part Start Authority

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

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

End Amendment Part

Airbus: Docket No. FAA-2018-0512; Product Identifier 2017-NM-170-AD.

(a) Comments Due Date

We must receive comments by July 30, 2018.

(b) Affected ADs

This AD affects AD 2016-09-06, Amendment 39-18504 (81 FR 26113, May 2, 2016) (“AD 2016-09-06”) and AD 2017-22-03, Amendment 39-19083 (82 FR 49091, October 24, 2017) (“AD 2017-22-03”).

(c) Applicability

This AD applies to all Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any category; with an original certificate of airworthiness or original export certificate of airworthiness issued on or before October 24, 2017.

(1) Model A318-111, -112, -121, and -122 airplanes.

(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.

(3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, and -271N airplanes.

(4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, 271N, and -272N airplanes.

(d) Subject

Air Transport Association (ATA) of America Code 05, Time Limits/Maintenance Checks.

(e) Reason

This AD was prompted by an evaluation by the design approval holder, which indicates that principal structural elements and certain life-limited parts are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already done.

(g) New Maintenance or Inspection Program Revision

(1) Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the airworthiness limitations (ALIs) specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017; and A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, October 24, 2017. Except for ALIs identified in paragraphs (g)(2) and (g)(3) of this AD, the initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017; A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, October 24, 2017; or within 90 days after the effective date of this AD, whichever occurs later; without exceeding the inspection intervals in Start Printed Page 27728the ALIs required by paragraph (i) of AD 2017-22-03.

(2) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017, or within 90 days after the effective date of this AD, whichever occurs later; without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03.

(3) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the maintenance or inspection program, as applicable, to incorporate the ALIs specified in A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017, or within 90 days after the effective date of this AD, whichever occurs later; without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03.

(h) No Alternative Actions, Intervals, and Critical Design Configuration Control Limitations (CDCCLs)

After the maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD.

(i) Terminating Action for Other FAA ADs

(1) Accomplishing the action required by paragraph (g) of this AD terminates the requirements of paragraphs (g) and (j) of AD 2016-09-06.

(2) Accomplishing the action required by paragraph (g) of this AD terminates the requirements of paragraphs (g)(2) and (i) of AD 2017-22-03.

(j) 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 (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.

(i) 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.

(ii) AMOCs previously approved for AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015) that required incorporation of the service information in paragraphs (j)(1)(ii)(A), (j)(1)(ii)(B), (j)(1)(ii)(C), or (j)(1)(ii)(D), are approved as AMOCs for the corresponding provisions of this AD.

(A) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017.

(B) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017.

(C) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2 -Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017.

(D) A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, October 24, 2017.

(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's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(k) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0231, dated November 21, 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-2018-0512.

(2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

(3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@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.

Start Signature

Issued in Des Moines, Washington, on June 6, 2018.

Michael Kaszycki,

Acting Director, System Oversight Division, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2018-12733 Filed 6-13-18; 8:45 am]

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