Airworthiness Directives; Airbus Airplanes, 24654-24656 [2018-11659]

Download as PDF 24654 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations Administrator, the following special conditions are issued as part of the type certification basis for Bombardier Model BD–700–2A12 and Model BD–700– 2A13 airplanes. Autobraking System Structural Loads A landing pitchover condition must be addressed that takes into account the effect of the autobrake system. The airplane is assumed to be at the design maximum landing weight, or at the maximum weight allowed with the autobrake system on. The airplane is assumed to land in a tail-down attitude at the speeds defined by § 25.481. Following main gear contact, the airplane is assumed to rotate about the main gear wheels at the highest pitch rate generated by the autobrake system. This is considered a limit load condition from which ultimate loads must also be determined. Loads must be determined for a critical fuel and payload distribution and centers of gravity. Nose gear loads, as well as airframe loads, must be determined. The airplane must support these loads as described in § 25.305. Issued in Des Moines, Washington, on May 23, 2018. Victor Wicklund, Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2018–11506 Filed 5–29–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0492; Product Identifier 2018–NM–083–AD; Amendment 39–19303; AD 2018–11–15] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A320–271N airplanes, and Model A321–271N, –271NX, –272N and –272NX airplanes. This AD requires replacing certain full authority digital engine control (FADEC) electronic engine controllers (EECs); or installing software standard FCS4.4 and reidentifying the FADEC EECs. This AD was prompted by a report that, when sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 operated at low speed and high engine thrust, an engine did not restart following a fuel interruption shorter than five seconds. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective May 30, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 30, 2018. We must receive comments on this AD by July 16, 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 https://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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, 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 https://www.airbus.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. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0492. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0492; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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 206–231–3323. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0110, dated May 18, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A320–271N airplanes, and Model A321–271N, –271NX, –272N, and –272NX airplanes. The MCAI states: During certification test flights of an A320– 271N aeroplane, it has been identified that, when operated at low speed and high engine thrust, the tested engine did not re-start in case of a fuel interruption shorter than 5 seconds. Investigation revealed that this was due to the software logic implemented in the FADEC EEC of affected A320 family models. This condition, if not corrected, could prevent restart of a shut down engine while operating in high power conditions [after a single or dual in-flight engine shutdown]. To address this potentially unsafe condition, software (SW) standard FCS4.4 for the FADEC EEC has been developed, and Airbus published the SB [Airbus Service Bulletin A320–73–1128, Revision 01, dated May 17, 2018] providing modification instructions. For the reasons described above, this [EASA] AD requires modification of aeroplanes by [replacing the affected FADEC EECs or by] installation of this FADEC EEC SW [software] standard [and re-identification of the affected FADEC EECs]. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0492. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–73–1128, Revision 01, dated May 17, 2018. This service information describes procedures for replacing affected FADEC EECs and for installing software standard FCS4.4 and reidentifying affected FADEC EECs. 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 AD This product has been approved by the aviation authority of another E:\FR\FM\30MYR1.SGM 30MYR1 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations defect might prevent restart of an engine after a single or dual in-flight engine shutdown under certain conditions. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2018–0492; Product Identifier 2018–NM–083–AD’’ FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because a FADEC EEC software 24655 at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 16 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators Up to 7 work-hours × $85 per hour = Up to $595 ....................... (1) Up to $595 ................................ Up to $9,520. 1 We have received no definitive data that would enable us to provide cost estimates for parts needed to comply with the actions specified in this AD. sradovich on DSK3GMQ082PROD with RULES Authority for This Rulemaking Regulatory Findings 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. 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. VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 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: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 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 adding the following new airworthiness directive (AD): ■ 2018–11–15 Airbus: Amendment 39–19303; Docket No. FAA–2018–0492; Product Identifier 2018–NM–083–AD. (a) Effective Date This AD becomes effective May 30, 2018. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers (MSN). (1) Model A320–271N airplanes. (2) Model A321–271N, –271NX, –272N and –272NX airplanes. (d) Subject Air Transport Association (ATA) of America Code 72, Turbine/turboprop engine. (e) Reason This AD was prompted by a report that, when operated at low speed and high engine thrust, an engine did not restart following a fuel interruption shorter than five seconds. We are issuing this AD to address engines that might not restart while operating in high E:\FR\FM\30MYR1.SGM 30MYR1 24656 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations (2) The installation of the FADEC EEC or software standard must be accomplished in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. power conditions after a single or dual inflight engine shutdown. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions (1) For the purposes of this AD, an affected full authority digital engine control (FADEC) electronic engine controller (EEC) is one with a part number listed in table 1 to paragraph (g)(1) of this AD. TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—AFFECTED FADEC EEC PART NUMBERS Affected FADEC EEC part No. 5315126 5315126SK02 5323434 5323745 5323746 5324836 5324836–001 5324836–002 5324837 5325185 5325971 5325975 (2) For the purposes of this AD, Group 1 airplanes are defined as those that have an affected FADEC EEC installed. (3) For the purposes of this AD, Group 2 airplanes are defined as those that do not have an affected FADEC EEC installed. (h) Modification For Group 1 airplanes: Within 30 days after the effective date of this AD, modify the airplane by replacing affected FADEC EECs installed on both engines with FADEC EEC part number 5327582 (software standard FCS4.4), or by installing software standard FCS4.4 and re-identifying the affected FADEC EEC, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–73–1128, Revision 01, dated May 17, 2018. (i) Parts Installation Limitation sradovich on DSK3GMQ082PROD with RULES As of 30 days after the effective date of this AD, do not install an affected FADEC EEC on any airplane. (j) Later-Approved Parts Installation on an airplane of a FADEC EEC or software standard having a part number approved after the effective date of this AD is acceptable for compliance with the requirements of paragraph (h) of this AD, provided the conditions in paragraphs (j)(1) and (j)(2) of this AD are met. (1) The FADEC EEC or software standard part number must be 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. VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 (k) Clarification of Affected Airplanes An airplane on which Airbus modification 163473 has been embodied in production is not affected by the requirements of paragraph (h) of this AD, provided it can be conclusively determined that no affected FADEC EEC is installed on that airplane. (l) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–73–1128, dated May 15, 2018. (m) 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 (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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 EASA; or Airbus’s EASA 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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2018–0110, dated May 18, 2018, for related information. You PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0492. (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– 231–3323. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) 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. (i) Airbus Service Bulletin A320–73–1128, Revision 01, dated May 17, 2018. (ii) Reserved. (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 https://www.airbus.com. (4) 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. (5) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on May 23, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–11659 Filed 5–29–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Parts 375 and 388 [Docket No. RM16–15–001; Order No. 833–A] FAST Act Section 61003—Critical Electric Infrastructure Security and Critical Energy Infrastructure Information Federal Energy Regulatory Commission. ACTION: Order on clarification and rehearing. AGENCY: E:\FR\FM\30MYR1.SGM 30MYR1

Agencies

[Federal Register Volume 83, Number 104 (Wednesday, May 30, 2018)]
[Rules and Regulations]
[Pages 24654-24656]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11659]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0492; Product Identifier 2018-NM-083-AD; Amendment 
39-19303; AD 2018-11-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A320-271N airplanes, and Model A321-271N, -271NX, -272N 
and -272NX airplanes. This AD requires replacing certain full authority 
digital engine control (FADEC) electronic engine controllers (EECs); or 
installing software standard FCS4.4 and re-identifying the FADEC EECs. 
This AD was prompted by a report that, when operated at low speed and 
high engine thrust, an engine did not restart following a fuel 
interruption shorter than five seconds. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD becomes effective May 30, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 30, 
2018.
    We must receive comments on this AD by July 16, 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 https://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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this final rule, 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 [email protected]; internet https://www.airbus.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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0492.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0492; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

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 206-231-3323.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0110, dated May 18, 2018 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A320-271N airplanes, and Model 
A321-271N, -271NX, -272N, and -272NX airplanes. The MCAI states:

    During certification test flights of an A320-271N aeroplane, it 
has been identified that, when operated at low speed and high engine 
thrust, the tested engine did not re-start in case of a fuel 
interruption shorter than 5 seconds. Investigation revealed that 
this was due to the software logic implemented in the FADEC EEC of 
affected A320 family models.
    This condition, if not corrected, could prevent restart of a 
shut down engine while operating in high power conditions [after a 
single or dual in-flight engine shutdown].
    To address this potentially unsafe condition, software (SW) 
standard FCS4.4 for the FADEC EEC has been developed, and Airbus 
published the SB [Airbus Service Bulletin A320-73-1128, Revision 01, 
dated May 17, 2018] providing modification instructions.
    For the reasons described above, this [EASA] AD requires 
modification of aeroplanes by [replacing the affected FADEC EECs or 
by] installation of this FADEC EEC SW [software] standard [and re-
identification of the affected FADEC EECs].

    You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0492.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-73-1128, Revision 01, dated 
May 17, 2018. This service information describes procedures for 
replacing affected FADEC EECs and for installing software standard 
FCS4.4 and re-identifying affected FADEC EECs. 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 AD

    This product has been approved by the aviation authority of another

[[Page 24655]]

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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because a 
FADEC EEC software defect might prevent restart of an engine after a 
single or dual in-flight engine shutdown under certain conditions. 
Therefore, we determined that notice and opportunity for public comment 
before issuing this AD are impracticable and that good cause exists for 
making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2018-0492; Product 
Identifier 2018-NM-083-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 16 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
            Labor cost                Parts cost      Cost per product            Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 7 work-hours x $85 per hour             (1)   Up to $595..........  Up to $9,520.
 = Up to $595.
----------------------------------------------------------------------------------------------------------------
1 We have received no definitive data that would enable us to provide cost estimates for parts needed to comply
  with the actions specified in this 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 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

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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2018-11-15 Airbus: Amendment 39-19303; Docket No. FAA-2018-0492; 
Product Identifier 2018-NM-083-AD.

(a) Effective Date

    This AD becomes effective May 30, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers (MSN).
    (1) Model A320-271N airplanes.
    (2) Model A321-271N, -271NX, -272N and -272NX airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 72, Turbine/
turboprop engine.

(e) Reason

    This AD was prompted by a report that, when operated at low 
speed and high engine thrust, an engine did not restart following a 
fuel interruption shorter than five seconds. We are issuing this AD 
to address engines that might not restart while operating in high

[[Page 24656]]

power conditions after a single or dual in-flight engine shutdown.

(f) Compliance

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

(g) Definitions

    (1) For the purposes of this AD, an affected full authority 
digital engine control (FADEC) electronic engine controller (EEC) is 
one with a part number listed in table 1 to paragraph (g)(1) of this 
AD.

 Table 1 to Paragraph (g)(1) of This AD--Affected FADEC EEC Part Numbers
------------------------------------------------------------------------
                       Affected FADEC EEC part No.
-------------------------------------------------------------------------
5315126
5315126SK02
5323434
5323745
5323746
5324836
5324836-001
5324836-002
5324837
5325185
5325971
5325975
------------------------------------------------------------------------

    (2) For the purposes of this AD, Group 1 airplanes are defined 
as those that have an affected FADEC EEC installed.
    (3) For the purposes of this AD, Group 2 airplanes are defined 
as those that do not have an affected FADEC EEC installed.

(h) Modification

    For Group 1 airplanes: Within 30 days after the effective date 
of this AD, modify the airplane by replacing affected FADEC EECs 
installed on both engines with FADEC EEC part number 5327582 
(software standard FCS4.4), or by installing software standard 
FCS4.4 and re-identifying the affected FADEC EEC, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-73-
1128, Revision 01, dated May 17, 2018.

(i) Parts Installation Limitation

    As of 30 days after the effective date of this AD, do not 
install an affected FADEC EEC on any airplane.

(j) Later-Approved Parts

    Installation on an airplane of a FADEC EEC or software standard 
having a part number approved after the effective date of this AD is 
acceptable for compliance with the requirements of paragraph (h) of 
this AD, provided the conditions in paragraphs (j)(1) and (j)(2) of 
this AD are met.
    (1) The FADEC EEC or software standard part number must be 
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.
    (2) The installation of the FADEC EEC or software standard must 
be accomplished in accordance with a method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.

(k) Clarification of Affected Airplanes

    An airplane on which Airbus modification 163473 has been 
embodied in production is not affected by the requirements of 
paragraph (h) of this AD, provided it can be conclusively determined 
that no affected FADEC EEC is installed on that airplane.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-73-
1128, dated May 15, 2018.

(m) 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 (n)(2) of this AD. Information 
may be emailed to: [email protected]. 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 EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2018-0110, dated May 18, 2018, 
for related information. You may examine the MCAI on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2018-0492.
    (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 206-231-3323.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) 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.
    (i) Airbus Service Bulletin A320-73-1128, Revision 01, dated May 
17, 2018.
    (ii) Reserved.
    (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 [email protected]; internet https://www.airbus.com.
    (4) 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.
    (5) 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on May 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-11659 Filed 5-29-18; 8:45 am]
BILLING CODE 4910-13-P

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