83 FR 24654 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 104 (May 30, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 104 (May 30, 2018)
| Page Range | 24654-24656 | |
| FR Document | 2018-11659 |
[Federal Register Volume 83, Number 104 (Wednesday, May 30, 2018)] [Rules and Regulations] [Pages 24654-24656] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-11659] ----------------------------------------------------------------------- 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 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: 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 http://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 http://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 http://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 http://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 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 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 http://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 http://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: http://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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Administrator, the following special operated at low speed and high engine FOR FURTHER INFORMATION CONTACT:
conditions are issued as part of the type thrust, an engine did not restart Sanjay Ralhan, Aerospace Engineer,
certification basis for Bombardier Model following a fuel interruption shorter International Section, Transport
BD–700–2A12 and Model BD–700– than five seconds. We are issuing this Standards Branch, FAA, 2200 South
2A13 airplanes. AD to address the unsafe condition on 216th St., Des Moines, WA 98198;
these products. telephone and fax 206–231–3323.
Autobraking System Structural Loads
DATES: This AD becomes effective May SUPPLEMENTARY INFORMATION:
A landing pitchover condition must 30, 2018.
be addressed that takes into account the The Director of the Federal Register Discussion
effect of the autobrake system. The approved the incorporation by reference The European Aviation Safety Agency
airplane is assumed to be at the design of a certain publication listed in this AD (EASA), which is the Technical Agent
maximum landing weight, or at the as of May 30, 2018. for the Member States of the European
maximum weight allowed with the We must receive comments on this Union, has issued EASA AD 2018–0110,
autobrake system on. The airplane is AD by July 16, 2018. dated May 18, 2018 (referred to after
assumed to land in a tail-down attitude ADDRESSES: You may send comments, this as the Mandatory Continuing
at the speeds defined by § 25.481. using the procedures found in 14 CFR Airworthiness Information, or ‘‘the
Following main gear contact, the 11.43 and 11.45, by any of the following MCAI’’), to correct an unsafe condition
airplane is assumed to rotate about the methods: for all Airbus Model A320–271N
main gear wheels at the highest pitch • Federal eRulemaking Portal: Go to airplanes, and Model A321–271N,
rate generated by the autobrake system. http://www.regulations.gov. Follow the –271NX, –272N, and –272NX airplanes.
This is considered a limit load instructions for submitting comments. The MCAI states:
condition from which ultimate loads • Fax: 202–493–2251.
must also be determined. Loads must be • Mail: U.S. Department of During certification test flights of an A320–
Transportation, Docket Operations, M– 271N aeroplane, it has been identified that,
determined for a critical fuel and when operated at low speed and high engine
payload distribution and centers of 30, West Building Ground Floor, Room thrust, the tested engine did not re-start in
gravity. Nose gear loads, as well as W12–140, 1200 New Jersey Avenue SE, case of a fuel interruption shorter than 5
airframe loads, must be determined. The Washington, DC 20590. seconds. Investigation revealed that this was
airplane must support these loads as • Hand Delivery: U.S. Department of due to the software logic implemented in the
described in § 25.305. Transportation, Docket Operations, M– FADEC EEC of affected A320 family models.
30, West Building Ground Floor, Room This condition, if not corrected, could
Issued in Des Moines, Washington, on May W12–140, 1200 New Jersey Avenue SE, prevent restart of a shut down engine while
23, 2018. operating in high power conditions [after a
Washington, DC, between 9 a.m. and 5
Victor Wicklund, p.m., Monday through Friday, except single or dual in-flight engine shutdown].
Manager, Transport Standards Branch, Policy Federal holidays. To address this potentially unsafe
and Innovation Division, Aircraft For service information identified in condition, software (SW) standard FCS4.4 for
Certification Service. the FADEC EEC has been developed, and
this final rule, contact Airbus,
[FR Doc. 2018–11506 Filed 5–29–18; 8:45 am] Airbus published the SB [Airbus Service
Airworthiness Office—EIAS, 1 Rond Bulletin A320–73–1128, Revision 01, dated
BILLING CODE 4910–13–P Point Maurice Bellonte, 31707 Blagnac May 17, 2018] providing modification
Cedex, France; telephone +33 5 61 93 36 instructions.
96; fax +33 5 61 93 44 51; email For the reasons described above, this
DEPARTMENT OF TRANSPORTATION account.airworth-eas@airbus.com; [EASA] AD requires modification of
internet http://www.airbus.com. You aeroplanes by [replacing the affected FADEC
Federal Aviation Administration EECs or by] installation of this FADEC EEC
may view this referenced service
information at the FAA, Transport SW [software] standard [and re-identification
14 CFR Part 39 of the affected FADEC EECs].
Standards Branch, 2200 South 216th St.,
[Docket No. FAA–2018–0492; Product Des Moines, WA. For information on the You may examine the MCAI on the
Identifier 2018–NM–083–AD; Amendment availability of this material at the FAA, internet at http://www.regulations.gov
39–19303; AD 2018–11–15] call 206–231–3195. It is also available by searching for and locating Docket No.
on the internet at http:// FAA–2018–0492.
RIN 2120–AA64
www.regulations.gov by searching for
Related Service Information Under 1
Airworthiness Directives; Airbus and locating Docket No. FAA–2018–
CFR Part 51
Airplanes 0492.
Airbus has issued Service Bulletin
AGENCY: Federal Aviation Examining the AD Docket A320–73–1128, Revision 01, dated May
Administration (FAA), DOT. You may examine the AD docket on 17, 2018. This service information
ACTION: Final rule; request for the internet at http:// describes procedures for replacing
comments. www.regulations.gov by searching for affected FADEC EECs and for installing
and locating Docket No. FAA–2018– software standard FCS4.4 and re-
SUMMARY: We are adopting a new 0492; or in person at the Docket identifying affected FADEC EECs. This
airworthiness directive (AD) for all Operations office between 9 a.m. and 5 service information is reasonably
Airbus Model A320–271N airplanes, p.m., Monday through Friday, except available because the interested parties
and Model A321–271N, –271NX, –272N Federal holidays. The AD docket have access to it through their normal
sradovich on DSK3GMQ082PROD with RULES
and –272NX airplanes. This AD requires contains this AD, the regulatory course of business or by the means
replacing certain full authority digital evaluation, any comments received, and identified in the ADDRESSES section.
engine control (FADEC) electronic other information. The street address for
engine controllers (EECs); or installing the Docket Operations office (telephone FAA’s Determination and Requirements
software standard FCS4.4 and re- 800–647–5527) is in the ADDRESSES of This AD
identifying the FADEC EECs. This AD section. Comments will be available in This product has been approved by
was prompted by a report that, when the AD docket shortly after receipt. the aviation authority of another
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country, and is approved for operation defect might prevent restart of an engine at the beginning of your comments. We
in the United States. Pursuant to our after a single or dual in-flight engine specifically invite comments on the
bilateral agreement with the State of shutdown under certain conditions. overall regulatory, economic,
Design Authority, we have been notified Therefore, we determined that notice environmental, and energy aspects of
of the unsafe condition described in the and opportunity for public comment this AD. We will consider all comments
MCAI and service information before issuing this AD are impracticable received by the closing date and may
referenced above. We are issuing this and that good cause exists for making amend this AD based on those
AD because we evaluated all pertinent this amendment effective in fewer than comments.
information and determined the unsafe 30 days. We will post all comments we
condition exists and is likely to exist or receive, without change, to http://
Comments Invited
develop on other products of these same www.regulations.gov, including any
type designs. This AD is a final rule that involves personal information you provide. We
requirements affecting flight safety, and will also post a report summarizing each
FAA’s Determination of the Effective we did not precede it by notice and substantive verbal contact we receive
Date opportunity for public comment. We about this AD.
An unsafe condition exists that invite you to send any written relevant
requires the immediate adoption of this data, views, or arguments about this AD. Costs of Compliance
AD. The FAA has found that the risk to Send your comments to an address We estimate that this AD affects 16
the flying public justifies waiving notice listed under the ADDRESSES section. airplanes of U.S. registry. We estimate
and comment prior to adoption of this Include ‘‘Docket No. FAA–2018–0492; the following costs to comply with this
rule because a FADEC EEC software Product Identifier 2018–NM–083–AD’’ 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.
Authority for This Rulemaking Regulatory Findings PART 39—AIRWORTHINESS
DIRECTIVES
Title 49 of the United States Code We determined that this AD will not
specifies the FAA’s authority to issue have federalism implications under ■ 1. The authority citation for part 39
rules on aviation safety. Subtitle I, Executive Order 13132. This AD will continues to read as follows:
section 106, describes the authority of not have a substantial direct effect on Authority: 49 U.S.C. 106(g), 40113, 44701.
the FAA Administrator. Subtitle VII: the States, on the relationship between
Aviation Programs, describes in more the national government and the States, § 39.13 [Amended]
detail the scope of the Agency’s or on the distribution of power and ■ 2. The FAA amends § 39.13 by adding
authority. responsibilities among the various the following new airworthiness
We are issuing this rulemaking under levels of government. directive (AD):
the authority described in Subtitle VII, For the reasons discussed above, I
Part A, Subpart III, Section 44701: 2018–11–15 Airbus: Amendment 39–19303;
certify that this AD: Docket No. FAA–2018–0492; Product
‘‘General requirements.’’ Under that Identifier 2018–NM–083–AD.
section, Congress charges the FAA with 1. Is not a ‘‘significant regulatory
promoting safe flight of civil aircraft in action’’ under Executive Order 12866; (a) Effective Date
air commerce by prescribing regulations 2. Is not a ‘‘significant rule’’ under the This AD becomes effective May 30, 2018.
for practices, methods, and procedures DOT Regulatory Policies and Procedures (b) Affected ADs
the Administrator finds necessary for (44 FR 11034, February 26, 1979);
None.
safety in air commerce. This regulation 3. Will not affect intrastate aviation in
is within the scope of that authority Alaska; and (c) Applicability
because it addresses an unsafe condition This AD applies to the Airbus airplanes
that is likely to exist or develop on 4. Will not have a significant identified in paragraphs (c)(1) and (c)(2) of
products identified in this rulemaking economic impact, positive or negative, this AD, certificated in any category, all
action. on a substantial number of small entities manufacturer serial numbers (MSN).
under the criteria of the Regulatory (1) Model A320–271N airplanes.
This AD is issued in accordance with
Flexibility Act. (2) Model A321–271N, –271NX, –272N and
authority delegated by the Executive –272NX airplanes.
Director, Aircraft Certification Service, List of Subjects in 14 CFR Part 39
as authorized by FAA Order 8000.51C. (d) Subject
In accordance with that order, issuance Air transportation, Aircraft, Aviation Air Transport Association (ATA) of
of ADs is normally a function of the safety, Incorporation by reference, America Code 72, Turbine/turboprop engine.
sradovich on DSK3GMQ082PROD with RULES
Compliance and Airworthiness Safety.
(e) Reason
Division, but during this transition Adoption of the Amendment This AD was prompted by a report that,
period, the Executive Director has when operated at low speed and high engine
delegated the authority to issue ADs Accordingly, under the authority thrust, an engine did not restart following a
applicable to transport category delegated to me by the Administrator, fuel interruption shorter than five seconds.
airplanes to the Director of the System the FAA amends 14 CFR part 39 as We are issuing this AD to address engines
Oversight Division. follows: that might not restart while operating in high
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power conditions after a single or dual in- (2) The installation of the FADEC EEC or may examine the MCAI on the internet at
flight engine shutdown. software standard must be accomplished in http://www.regulations.gov by searching for
accordance with a method approved by the and locating Docket No. FAA–2018–0492.
(f) Compliance Manager, International Section, Transport (2) For more information about this AD,
Comply with this AD within the Standards Branch, FAA; or EASA; or contact Sanjay Ralhan, Aerospace Engineer,
compliance times specified, unless already Airbus’s EASA DOA. If approved by the International Section, Transport Standards
done. DOA, the approval must include the DOA- Branch, FAA, 2200 South 216th St., Des
authorized signature. Moines, WA 98198; telephone and fax 206–
(g) Definitions 231–3323.
(1) For the purposes of this AD, an affected (k) Clarification of Affected Airplanes (3) Service information identified in this
full authority digital engine control (FADEC) An airplane on which Airbus modification AD that is not incorporated by reference is
electronic engine controller (EEC) is one with 163473 has been embodied in production is available at the addresses specified in
a part number listed in table 1 to paragraph not affected by the requirements of paragraph paragraphs (o)(3) and (o)(4) of this AD.
(g)(1) of this AD. (h) of this AD, provided it can be
(o) Material Incorporated by Reference
conclusively determined that no affected
FADEC EEC is installed on that airplane. (1) The Director of the Federal Register
TABLE 1 TO PARAGRAPH (g)(1) OF approved the incorporation by reference
THIS AD—AFFECTED FADEC EEC (l) Credit for Previous Actions (IBR) of the service information listed in this
PART NUMBERS This paragraph provides credit for the paragraph under 5 U.S.C. 552(a) and 1 CFR
actions required by paragraph (h) of this AD, part 51.
Affected FADEC EEC part No. if those actions were performed before the (2) You must use this service information
effective date of this AD using Airbus Service as applicable to do the actions required by
5315126 Bulletin A320–73–1128, dated May 15, 2018. this AD, unless this AD specifies otherwise.
5315126SK02 (i) Airbus Service Bulletin A320–73–1128,
(m) Other FAA AD Provisions Revision 01, dated May 17, 2018.
5323434
5323745 The following provisions also apply to this (ii) Reserved.
5323746 AD: (3) For service information identified in
5324836 (1) Alternative Methods of Compliance this AD, contact Airbus, Airworthiness
5324836–001 (AMOCs): The Manager, International Office—EIAS, 1 Rond Point Maurice
5324836–002 Section, Transport Standards Branch, FAA, Bellonte, 31707 Blagnac Cedex, France;
has the authority to approve AMOCs for this telephone +33 5 61 93 36 96; fax +33 5 61
5324837
AD, if requested using the procedures found 93 44 51; email account.airworth-eas@
5325185
in 14 CFR 39.19. In accordance with 14 CFR airbus.com; internet http://www.airbus.com.
5325971
39.19, send your request to your principal (4) You may view this service information
5325975
inspector or local Flight Standards District at the FAA, Transport Standards Branch,
Office, as appropriate. If sending information 2200 South 216th St., Des Moines, WA. For
(2) For the purposes of this AD, Group 1 information on the availability of this
directly to the International Section, send it
airplanes are defined as those that have an to the attention of the person identified in material at the FAA, call 206–231–3195.
affected FADEC EEC installed. paragraph (n)(2) of this AD. Information may (5) You may view this service information
(3) For the purposes of this AD, Group 2 be emailed to: 9-ANM-116-AMOC- that is incorporated by reference at the
airplanes are defined as those that do not REQUESTS@faa.gov. Before using any National Archives and Records
have an affected FADEC EEC installed. approved AMOC, notify your appropriate Administration (NARA). For information on
(h) Modification principal inspector, or lacking a principal the availability of this material at NARA, call
inspector, the manager of the local flight 202–741–6030, or go to: http://
For Group 1 airplanes: Within 30 days after standards district office/certificate holding www.archives.gov/federal-register/cfr/ibr-
the effective date of this AD, modify the district office. locations.html.
airplane by replacing affected FADEC EECs (2) Contacting the Manufacturer: For any
installed on both engines with FADEC EEC Issued in Des Moines, Washington, on May
requirement in this AD to obtain corrective 23, 2018.
part number 5327582 (software standard actions from a manufacturer, the action must
FCS4.4), or by installing software standard be accomplished using a method approved James Cashdollar,
FCS4.4 and re-identifying the affected by the Manager, International Section, Acting Director, System Oversight Division,
FADEC EEC, in accordance with the Transport Standards Branch, FAA; or EASA; Aircraft Certification Service.
Accomplishment Instructions of Airbus or Airbus’s EASA DOA. If approved by the [FR Doc. 2018–11659 Filed 5–29–18; 8:45 am]
Service Bulletin A320–73–1128, Revision 01, DOA, the approval must include the DOA- BILLING CODE 4910–13–P
dated May 17, 2018. authorized signature.
(i) Parts Installation Limitation (3) Required for Compliance (RC): If any
service information contains procedures or
As of 30 days after the effective date of this tests that are identified as RC, those DEPARTMENT OF ENERGY
AD, do not install an affected FADEC EEC on procedures and tests must be done to comply
any airplane. with this AD; any procedures or tests that are Federal Energy Regulatory
(j) Later-Approved Parts not identified as RC are recommended. Those Commission
procedures and tests that are not identified
Installation on an airplane of a FADEC EEC as RC may be deviated from using accepted 18 CFR Parts 375 and 388
or software standard having a part number methods in accordance with the operator’s
approved after the effective date of this AD maintenance or inspection program without [Docket No. RM16–15–001; Order
is acceptable for compliance with the obtaining approval of an AMOC, provided No. 833–A]
requirements of paragraph (h) of this AD, the procedures and tests identified as RC can
provided the conditions in paragraphs (j)(1) be done and the airplane can be put back in FAST Act Section 61003—Critical
and (j)(2) of this AD are met. an airworthy condition. Any substitutions or Electric Infrastructure Security and
sradovich on DSK3GMQ082PROD with RULES
(1) The FADEC EEC or software standard changes to procedures or tests identified as Critical Energy Infrastructure
part number must be approved by the RC require approval of an AMOC. Information
Manager, International Section, Transport
Standards Branch, FAA; or the European (n) Related Information AGENCY: Federal Energy Regulatory
Aviation Safety Agency (EASA); or Airbus’s (1) Refer to Mandatory Continuing Commission.
EASA Design Organization Approval (DOA). Airworthiness Information (MCAI) EASA ACTION: Order on clarification and
If approved by the DOA, the approval must Airworthiness Directive 2018–0110, dated
rehearing.
include the DOA-authorized signature. May 18, 2018, for related information. You
VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\30MYR1.SGM 30MYR1](https://thefederalregister.org/doc/83_FR_24758/page/3.svg)
Document Created: 2018-05-30 01:01:26
Document Modified: 2018-05-30 01:01:26
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective May 30, 2018. | |
| 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. | |
| FR Citation | 83 FR 24654 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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