83 FR 62690 - Airworthiness Directives; Airbus SAS Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 234 (December 6, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 234 (December 6, 2018)
| Page Range | 62690-62693 | |
| FR Document | 2018-26362 |
[Federal Register Volume 83, Number 234 (Thursday, December 6, 2018)] [Rules and Regulations] [Pages 62690-62693] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-26362] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0512; Product Identifier 2017-NM-170-AD; Amendment 39-19513; AD 2018-25-02] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. 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). This AD requires revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 10, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 10, 2019. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; internet http:// [[Page 62691]] 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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0512. 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 Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. 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. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A318, A319, A320 and A321 series airplanes. The NPRM published in the Federal Register on June 14, 2018 (83 FR 27724). The NPRM was prompted by an evaluation by the DAH indicating that the principal structural elements and certain life-limited parts are subject to WFD. The NPRM proposed to require revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. We are issuing this AD to address prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane. 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 SAS 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 2, 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. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comment received on the NPRM and the FAA's response to that comment. Request To Use the Latest Service Information Lufthansa Technik requested that we use the latest service information in the NPRM. Lufthansa Technik stated that Airbus issued A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 07, dated June 13, 2018, which is the latest revision of the document. We disagree with the commenter's request. We, along with the EASA, have not determined that Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 07, dated June 13, 2018, is required for airplanes that do not include Revision 07 as part of the type design. In the future, should we determine that Revision 07 is required, we would consider issuing additional rulemaking at that time. However, operators may request approval to incorporate Revision 07 as an alternative method of compliance (AMOC) under the provisions of paragraph (j) of this AD. We have not changed this AD in this regard. Change to Language for Previous Approved AMOCs We have revised paragraph (j)(1)(ii) of this AD to state that AMOCs previously approved for AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015) (``AD 2015-05-02''), as applicable to ALS Part 2, are approved as AMOCs for the corresponding provisions of this AD. In paragraphs (j)(1)(ii)(A), (j)(1)(ii)(B), (j)(1)(ii)(C), and (j)(1)(ii)(D) of the proposed AD, we had identified specific ALS documents. However, any previously approved AMOC for AD 2015-05-02, as applicable to ALS Part 2, is acceptable for the corresponding requirements of this AD. Removal of Terminating Action for AD 2016-09-06 We have removed paragraph (i)(1) of the proposed AD, which specified that accomplishing the action required by paragraph (g) of this AD terminates the requirements of paragraphs (g) and (j) of AD 2016-09-06. However, we have determined that the actions required by this AD, do not terminate the requirements specified in AD 2016-09-06. The actions specified in paragraph (g) of AD 2016-09-06 were not incorporated into Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT- ALI), Revision 06, dated April 10, 2017, which is specified in paragraph (g) of this AD. We have coordinated this issue with EASA. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this [[Page 62692]] final rule with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. 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. This service information describes damage tolerant 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. This 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, dated October 24, 2017. This 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. Costs of Compliance We estimate that this AD affects 1,180 airplanes of U.S. registry. We estimate the following costs to comply with this AD: We have determined that revising the existing 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 x $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 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 and associated appliances to the Director of the System Oversight Division. Regulatory Findings 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): 2018-25-02 Airbus SAS: Amendment 39-19513; Docket No. FAA-2018-0512; Product Identifier 2017-NM-170-AD. (a) Effective Date This AD is effective January 10, 2019. (b) Affected ADs This AD affects 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 SAS 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 [[Page 62693]] 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 existing 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 Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated 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, and Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 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. (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 existing 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 existing 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 6.2, 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 or Intervals After the existing 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 AD 2017-22-03 Accomplishing the applicable actions 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: [email protected]. (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), as applicable to Airworthiness Limitations Section (ALS) Part 2, are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the 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. (l) 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 A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017. (ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017. (iii) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT- ALI), Variation 6.2, dated May 24, 2017. (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 24, 2017. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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 November 23, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-26362 Filed 12-4-18; 8:45 am] BILLING CODE 4910-13-P
![62690 Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations
certification requirements of 14 CFR To maintain the same level of safety sources of engine- and APU-generated
part 36. envisioned by the existing rule with electrical power inoperative (electrical
The FAA issues special conditions, as traditional mechanical flight controls, power sources excluding the battery and
defined in 14 CFR 11.19, in accordance the Textron Model 700 airplane design any other standby electrical sources).
with § 11.38, and they become part of must not be time-limited in its operation The airplane operation should be
the type certification basis under under all reasonably foreseeable considered at the critical phase of flight,
§ 21.17(a)(2). conditions, including loss of all normal and should include the ability to restart
sources of engine or auxiliary power the engines and maintain flight for the
Novel or Unusual Design Features unit (APU)-generated electrical power. maximum diversion-time capability
The Textron Model 700 airplane will Textron must demonstrate that the being certified.
incorporate the following novel or airplane can maintain safe flight and Issued in Des Moines, Washington, on
unusual design feature: A fly-by-wire landing (including rollout and brake November 30, 2018.
rudder-control system that requires a control through full stop) with the use Paul Siegmund,
continuous source of electrical power to of its emergency/alternate electrical- Acting Manager, Transport Standards
maintain an operable rudder flight- power systems. These electrical-power Branch, Policy and Innovation Division,
control system. The loss of this system systems, or the minimum restorable Aircraft Certification Service.
may result in loss of flight control and electrical-power sources, must be able to [FR Doc. 2018–26455 Filed 12–4–18; 8:45 am]
may be catastrophic to the airplane. power loads that are essential for BILLING CODE 4910–13–P
continued safe flight and landing,
Discussion including those required for the
The Textron Model 700 airplane has maximum length of approved flight DEPARTMENT OF TRANSPORTATION
a fly-by-wire rudder-control system that diversion.
requires a continuous source of These special conditions contain the Federal Aviation Administration
electrical power to maintain an operable additional safety standards that the
flight-control system. Section Administrator considers necessary to 14 CFR Part 39
25.1351(d), operation without normal establish a level of safety equivalent to
[Docket No. FAA–2018–0512; Product
electrical power, requires safe operation that established by existing Identifier 2017–NM–170–AD; Amendment
in visual flight rule (VFR) conditions for airworthiness standards. 39–19513; AD 2018–25–02]
at least 5 minutes after loss of normal Applicability
electrical power, excluding the battery. RIN 2120–AA64
This rule is structured around As discussed above, these special
conditions are applicable to the Textron Airworthiness Directives; Airbus SAS
traditional designs that use mechanical Airplanes
control cables and linkages for flight Model 700 airplane. Should Textron
control. These manual controls allow apply at a later date for a change to the AGENCY: Federal Aviation
the crew to maintain aerodynamic type certificate to include another Administration (FAA), Department of
control of the airplane for an indefinite model incorporating the same novel or Transportation (DOT).
time after loss of all electrical power. unusual design feature, the special ACTION: Final rule.
Under these conditions, a mechanical conditions would apply to that model as
flight-control system provides the crew well. SUMMARY: We are adopting a new
with the ability to fly the airplane while Conclusion airworthiness directive (AD) for certain
attempting to identify the cause of the Airbus SAS Model A318, A319, A320,
This action affects only certain novel and A321 series airplanes. This AD was
electrical failure, restart engine(s) if
or unusual design features on one model prompted by an evaluation by the
necessary, and attempt to re-establish
of airplane. It is not a rule of general design approval holder (DAH)
some of the electrical-power-generation
applicability. indicating that the principal structural
capability.
A critical assumption in § 25.1351(d) List of Subjects in 14 CFR Part 25 elements and certain life-limited parts
is that the airplane is in VFR conditions are subject to widespread fatigue
Aircraft, Aviation safety, Reporting damage (WFD). This AD requires
at the time of an electrical failure. This and recordkeeping requirements.
is not a valid assumption in today’s revising the existing maintenance or
airline operating environment, where Authority Citation inspection program to incorporate new
airplanes fly much of the time in or more restrictive airworthiness
The authority citation for these
instrument-meteorological conditions limitations. We are issuing this AD to
special conditions is as follows:
on air-traffic-control-defined flight address the unsafe condition on these
Authority: 49 U.S.C. 106(g), 40113, 44701, products.
paths. Another assumption in the 44702, 44704.
existing rule is that the loss of all DATES: This AD is effective January 10,
normal electrical power is the result of The Special Conditions 2019.
the loss of all engines. The 5-minute Accordingly, pursuant to the The Director of the Federal Register
period in the rule is to allow at least one authority delegated to me by the approved the incorporation by reference
engine to be restarted, following an all- Administrator, the following special of certain publications listed in this AD
engines power loss, to continue the conditions are issued as part of the type as of January 10, 2019.
flight to a safe landing. However, service certification basis for Textron Model ADDRESSES: For service information
khammond on DSK30JT082PROD with RULES
experience on airplanes with similar 700 airplanes. identified in this final rule, contact
electrical-power-system architecture as In lieu of 14 CFR 25.1351(d), the Airbus SAS, Airworthiness Office—
the Textron Model 700 airplane has following special condition applies: EIAS, Rond-Point Emile Dewoitine No:
shown that at least the temporary loss Textron must show, by test or 2, 31700 Blagnac Cedex, France;
of all electrical power for causes other combination of test and analysis that the telephone +33 5 61 93 36 96; fax +33 5
than all-engine failure is not extremely airplane is capable of continued safe 61 93 44 51; email account.airworth-
improbable. flight and landing with all normal eas@airbus.com; internet http://
VerDate Sep<11>2014 16:05 Dec 04, 2018 Jkt 247001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\06DER1.SGM 06DER1](https://thefederalregister.org/doc/83_FR_62924/page/1.svg)
![Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations 62691
www.airbus.com. You may view this an unsafe condition for all Airbus SAS Limitation Items (DT–ALI), Revision 07,
service information at the FAA, Model A318, A319, A320 and A321 dated June 13, 2018, which is the latest
Transport Standards Branch, 2200 series airplanes. The MCAI states: revision of the document.
South 216th St., Des Moines, WA. For The airworthiness limitations for the A320 We disagree with the commenter’s
information on the availability of this family aeroplanes are currently defined and request. We, along with the EASA, have
material at the FAA, call 206–231–3195. published in the Airbus A318/A319/A320/ not determined that Airbus A318/A319/
It is also available on the internet at A321 Airworthiness Limitations Section A320/A321 Airworthiness Limitation
http://www.regulations.gov by searching (ALS) document(s). The Damage Tolerant Section Part 2—Damage Tolerant
for and locating Docket No. FAA–2018– Airworthiness Limitation Items are published Airworthiness Limitation Items (DT–
0512. in ALS Part 2, approved by EASA. The ALI), Revision 07, dated June 13, 2018,
instructions contained in the ALS Part 2 have is required for airplanes that do not
Examining the AD Docket been identified as mandatory actions for
include Revision 07 as part of the type
continued airworthiness.
You may examine the AD docket on Failure to comply with these instructions design. In the future, should we
the internet at http:// could result in an unsafe condition. determine that Revision 07 is required,
www.regulations.gov by searching for Previously, EASA issued AD 2016–0239 we would consider issuing additional
and locating Docket No. FAA–2018– [which corresponds to FAA AD 2017–22–03, rulemaking at that time. However,
0512; or in person at Docket Operations Amendment 39–19083 (82 FR 49091, October operators may request approval to
between 9 a.m. and 5 p.m., Monday 24, 2017) (‘‘AD 2017–22–03’’)] to require incorporate Revision 07 as an
through Friday, except Federal holidays. accomplishment of all maintenance tasks as alternative method of compliance
described in ALS Part 2 at Revision 05, and (AMOC) under the provisions of
The AD docket contains this final rule, [EASA] AD 2015–0038 (later revised) [which
the regulatory evaluation, any corresponds to FAA AD 2016–09–06, paragraph (j) of this AD. We have not
comments received, and other Amendment 39–18504 (81 FR 26113, May 2, changed this AD in this regard.
information. The address for Docket 2016) (‘‘AD 2016–09–06’’)] to require the Change to Language for Previous
Operations (phone: 800–647–5527) is implementation of reduced thresholds and
Approved AMOCs
U.S. Department of Transportation, intervals for the detailed inspection of the
Docket Operations, M–30, West forward engine mount on both right hand We have revised paragraph (j)(1)(ii) of
Building Ground Floor, Room W12–140, and left hand sides of aeroplanes equipped this AD to state that AMOCs previously
with CFM56–5A/5B engines, as specified in approved for AD 2015–05–02,
1200 New Jersey Avenue SE, the ALS task 712111–01.
Washington, DC 20590. Amendment 39–18112 (80 FR 15152,
Since those [EASA] ADs were issued, March 23, 2015) (‘‘AD 2015–05–02’’), as
FOR FURTHER INFORMATION CONTACT: Airbus published Revision 06 of the ALS Part
applicable to ALS Part 2, are approved
Sanjay Ralhan, Aerospace Engineer, 2, and variations up to 6.3, including new
and/or more restrictive items, and new A320 as AMOCs for the corresponding
International Section, Transport
family models were certified and added to provisions of this AD. In paragraphs
Standards Branch, FAA, 2200 South
the Applicability of the ALS. The ALS Part (j)(1)(ii)(A), (j)(1)(ii)(B), (j)(1)(ii)(C), and
216th St., Des Moines, WA 98198;
2 Revision 06 also includes the reduced (j)(1)(ii)(D) of the proposed AD, we had
telephone and fax 206–231–3223. threshold and intervals required by EASA identified specific ALS documents.
SUPPLEMENTARY INFORMATION: AD 2015–0038R1. However, any previously approved
For the reason described above, this AMOC for AD 2015–05–02, as
Discussion [EASA] AD retains the requirements of EASA applicable to ALS Part 2, is acceptable
We issued a notice of proposed AD 2016–0239 and EASA AD 2015–0038R1,
for the corresponding requirements of
rulemaking (NPRM) to amend 14 CFR which are superseded, requires
accomplishment of all maintenance tasks as this AD.
part 39 by adding an AD that would
apply to certain Airbus SAS Model described in the ALS Part 2 Revision 06, and Removal of Terminating Action for AD
ALS Part 2 variations 6.1, 6.2 and 6.3 2016–09–06
A318, A319, A320 and A321 series (hereafter collectively referred to as ‘‘the
airplanes. The NPRM published in the ALS’’ in this [EASA] AD), and maintains We have removed paragraph (i)(1) of
Federal Register on June 14, 2018 (83 specific compliance times for ALS task the proposed AD, which specified that
FR 27724). The NPRM was prompted by 572021–01–1 (Wide Spread Fatigue Damage accomplishing the action required by
an evaluation by the DAH indicating related). paragraph (g) of this AD terminates the
that the principal structural elements You may examine the MCAI in the requirements of paragraphs (g) and (j) of
and certain life-limited parts are subject AD docket on the internet at http:// AD 2016–09–06. However, we have
to WFD. The NPRM proposed to require www.regulations.gov by searching for determined that the actions required by
revising the existing maintenance or and locating Docket No. FAA–2018– this AD, do not terminate the
inspection program to incorporate new 0512. requirements specified in AD 2016–09–
or more restrictive airworthiness 06. The actions specified in paragraph
limitations. Comments (g) of AD 2016–09–06 were not
We are issuing this AD to address We gave the public the opportunity to incorporated into Airbus A318/A319/
prevent fatigue cracking, accidental participate in developing this final rule. A320/A321 Airworthiness Limitation
damage, or corrosion in principal The following presents the comment Section Part 2—Damage Tolerant
structural elements, and WFD, which received on the NPRM and the FAA’s Airworthiness Limitation Items (DT–
could result in reduced structural response to that comment. ALI), Revision 06, dated April 10, 2017,
integrity of the airplane. which is specified in paragraph (g) of
The European Aviation Safety Agency Request To Use the Latest Service
this AD. We have coordinated this issue
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(EASA), which is the Technical Agent Information
with EASA.
for the Member States of the European Lufthansa Technik requested that we
Union, has issued EASA Airworthiness use the latest service information in the Conclusion
Directive 2017–0231, dated November NPRM. Lufthansa Technik stated that We reviewed the relevant data,
21, 2017 (referred to after this as the Airbus issued A318/A319/A320/A321 considered the comment received, and
Mandatory Continuing Airworthiness Airworthiness Limitation Section Part determined that air safety and the
Information, or ‘‘the MCAI’’), to correct 2—Damage Tolerant Airworthiness public interest require adopting this
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![62692 Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations
final rule with the changes described hours per operator, although we Procedures (44 FR 11034, February 26,
previously and minor editorial changes. recognize that this number may vary 1979),
We have determined that these minor from operator to operator. In the past, (3) Will not affect intrastate aviation
changes: we have estimated that this action takes in Alaska, and
• Are consistent with the intent that 1 work-hour per airplane. Since (4) Will not have a significant
was proposed in the NPRM for operators incorporate maintenance or economic impact, positive or negative,
addressing the unsafe condition; and inspection program changes for their on a substantial number of small entities
• Do not add any additional burden affected fleet(s), we have determined under the criteria of the Regulatory
upon the public than was already that a per-operator estimate is more Flexibility Act.
proposed in the NPRM. accurate than a per-airplane estimate. List of Subjects in 14 CFR Part 39
We also determined that these Therefore, we estimate the total cost per
changes will not increase the economic operator to be $7,650 (90 work-hours × Air transportation, Aircraft, Aviation
burden on any operator or increase the $85 per work-hour). safety, Incorporation by reference,
scope of this final rule. Safety.
Authority for This Rulemaking
Related Service Information Under 1 Adoption of the Amendment
Title 49 of the United States Code
CFR Part 51 specifies the FAA’s authority to issue Accordingly, under the authority
Airbus has issued A318/A319/A320/ rules on aviation safety. Subtitle I, delegated to me by the Administrator,
A321 Airworthiness Limitation Section section 106, describes the authority of the FAA amends 14 CFR part 39 as
Part 2—Damage Tolerant Airworthiness the FAA Administrator. Subtitle VII: follows:
Limitation Items (DT–ALI), Revision 06, Aviation Programs, describes in more
dated April 10, 2017. This service detail the scope of the Agency’s PART 39—AIRWORTHINESS
information describes damage tolerant authority. DIRECTIVES
airworthiness limitations. We are issuing this rulemaking under ■ 1. The authority citation for part 39
Airbus has also issued the following the authority described in Subtitle VII, continues to read as follows:
variations to A318/A319/A320/A321 Part A, Subpart III, Section 44701:
Airworthiness Limitation Section Part ‘‘General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701.
2—Damage Tolerant Airworthiness section, Congress charges the FAA with § 39.13 [Amended]
Limitation Items (DT–ALI), Revision 06, promoting safe flight of civil aircraft in
dated April 10, 2017. air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding
• A318/A319/A320/A321 for practices, methods, and procedures the following new airworthiness
Airworthiness Limitation Section Part the Administrator finds necessary for directive (AD):
2—Damage Tolerant Airworthiness safety in air commerce. This regulation 2018–25–02 Airbus SAS: Amendment 39–
Limitation Items (DT–ALI), Variation is within the scope of that authority 19513; Docket No. FAA–2018–0512;
6.1, dated May 18, 2017. The service because it addresses an unsafe condition Product Identifier 2017–NM–170–AD.
information describes ALI tasks that is likely to exist or develop on (a) Effective Date
applicable to certain Model A320–200 products identified in this rulemaking This AD is effective January 10, 2019.
and A321–200 airplane configurations. action.
• A318/A319/A320/A321 This AD is issued in accordance with (b) Affected ADs
Airworthiness Limitation Section Part authority delegated by the Executive This AD affects AD 2017–22–03,
2—Damage Tolerant Airworthiness Director, Aircraft Certification Service, Amendment 39–19083 (82 FR 49091, October
Limitation Items (DT–ALI), Variation as authorized by FAA Order 8000.51C. 24, 2017) (‘‘AD 2017–22–03’’).
6.2, dated May 24, 2017. This service In accordance with that order, issuance (c) Applicability
information describes ALI tasks of ADs is normally a function of the
This AD applies to all Airbus SAS
applicable to Model A321–271N and Compliance and Airworthiness airplanes identified in paragraphs (c)(1),
–272N airplanes. Division, but during this transition (c)(2), (c)(3), and (c)(4) of this AD; certificated
• A318/A319/A320/A321 period, the Executive Director has in any category; with an original certificate
Airworthiness Limitation Section Part delegated the authority to issue ADs of airworthiness or original export certificate
2—Damage Tolerant Airworthiness applicable to transport category of airworthiness issued on or before October
Limitation Items (DT–ALI), Variation airplanes and associated appliances to 24, 2017.
6.3, dated October 24, 2017. This service the Director of the System Oversight (1) Model A318–111, –112, –121, and –122
information describes ALI tasks Division. airplanes.
associated with door stops for certain (2) Model A319–111, –112, –113, –114,
Model A318, A319, A320, and A321 Regulatory Findings –115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –216,
series airplanes. This AD will not have federalism
–231, –232, –233, –251N, and –271N
This service information is reasonably implications under Executive Order airplanes.
available because the interested parties 13132. This AD will not have a (4) Model A321–111, –112, –131, –211,
have access to it through their normal substantial direct effect on the States, on –212, –213, –231, –232, –251N, –253N,
course of business or by the means the relationship between the national –271N, and –272N airplanes.
identified in the ADDRESSES section. government and the States, or on the
(d) Subject
distribution of power and
Costs of Compliance Air Transport Association (ATA) of
responsibilities among the various
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We estimate that this AD affects 1,180 America Code 05, Time Limits/Maintenance
levels of government.
Checks.
airplanes of U.S. registry. For the reasons discussed above, I
We estimate the following costs to certify that this AD: (e) Reason
comply with this AD: (1) Is not a ‘‘significant regulatory This AD was prompted by an evaluation by
We have determined that revising the action’’ under Executive Order 12866, the design approval holder, which indicates
existing maintenance or inspection (2) Is not a ‘‘significant rule’’ under that principal structural elements and certain
program takes an average of 90 work- the DOT Regulatory Policies and life-limited parts are subject to widespread
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![Federal Register / Vol. 83, No. 234 / Thursday, December 6, 2018 / Rules and Regulations 62693
fatigue damage (WFD). We are issuing this as applicable, to incorporate the ALIs (k) Related Information
AD to prevent fatigue cracking, accidental specified in Airbus A318/A319/A320/A321 (1) Refer to Mandatory Continuing
damage, or corrosion in principal structural Airworthiness Limitation Section Part 2— Airworthiness Information (MCAI) EASA AD
elements, and WFD, which could result in Damage Tolerant Airworthiness Limitation 2017–0231, dated November 21, 2017, for
reduced structural integrity of the airplane. Items (DT–ALI), Variation 6.2, dated May 24, related information. This MCAI may be
(f) Compliance 2017. The initial compliance time for
found in the AD docket on the internet at
accomplishing the actions is at the applicable
Comply with this AD within the http://www.regulations.gov by searching for
time identified in the ALIs specified in
compliance times specified, unless already and locating Docket No. FAA–2018–0512.
Airbus A318/A319/A320/A321
done. (2) For more information about this AD,
Airworthiness Limitation Section Part 2—
contact Sanjay Ralhan, Aerospace Engineer,
(g) New Maintenance or Inspection Program Damage Tolerant Airworthiness Limitation
International Section, Transport Standards
Revision Items (DT–ALI), Variation 6.2, dated May 24,
2017; or within 90 days after the effective Branch, FAA, 2200 South 216th St., Des
(1) Within 90 days after the effective date Moines, WA 98198; telephone and fax 206–
of this AD, revise the existing maintenance date of this AD; whichever occurs later,
without exceeding the inspection intervals in 231–3223.
or inspection program, as applicable, to
incorporate the airworthiness limitations the ALIs required by paragraph (i) of AD (l) Material Incorporated by Reference
(ALIs) specified in Airbus A318/A319/A320/ 2017–22–03.
(1) The Director of the Federal Register
A321 Airworthiness Limitation Section Part (h) No Alternative Actions or Intervals approved the incorporation by reference
2—Damage Tolerant Airworthiness (IBR) of the service information listed in this
Limitation Items (DT–ALI), Revision 06, After the existing maintenance or
inspection program has been revised as paragraph under 5 U.S.C. 552(a) and 1 CFR
dated April 10, 2017; and Airbus A318/
required by paragraph (g) of this AD, no part 51.
A319/A320/A321 Airworthiness Limitation
Section Part 2—Damage Tolerant alternative actions (e.g., inspections) or (2) You must use this service information
Airworthiness Limitation Items (DT–ALI), intervals may be used unless the actions or as applicable to do the actions required by
Variation 6.3, dated October 24, 2017. Except intervals are approved as an alternative this AD, unless this AD specifies otherwise.
for ALIs identified in paragraphs (g)(2) and method of compliance (AMOC) in (i) Airbus A318/A319/A320/A321
(g)(3) of this AD, the initial compliance time accordance with the procedures specified in Airworthiness Limitation Section Part 2—
for accomplishing the actions is at the paragraph (j)(1) of this AD. Damage Tolerant Airworthiness Limitation
applicable time identified in the ALIs Items (DT–ALI), Revision 06, dated April 10,
specified in Airbus A318/A319/A320/A321 (i) Terminating Action for AD 2017–22–03 2017.
Airworthiness Limitation Section Part 2— Accomplishing the applicable actions (ii) Airbus A318/A319/A320/A321
Damage Tolerant Airworthiness Limitation required by paragraph (g) of this AD Airworthiness Limitation Section Part 2—
Items (DT–ALI), Revision 06, dated April 10, terminates the requirements of paragraphs Damage Tolerant Airworthiness Limitation
2017, and Airbus A318/A319/A320/A321 (g)(2) and (i) of AD 2017–22–03. Items (DT–ALI), Variation 6.1, dated May 18,
Airworthiness Limitation Section Part 2— 2017.
Damage Tolerant Airworthiness Limitation (j) Other FAA AD Provisions
(iii) Airbus A318/A319/A320/A321
Items (DT–ALI), Variation 6.3, dated October The following provisions also apply to this Airworthiness Limitation Section Part 2—
24, 2017; or within 90 days after the effective AD: Damage Tolerant Airworthiness Limitation
date of this AD; whichever occurs later, (1) Alternative Methods of Compliance Items (DT–ALI), Variation 6.2, dated May 24,
without exceeding the inspection intervals in (AMOCs): The Manager, International 2017.
the ALIs required by paragraph (i) of AD Section, Transport Standards Branch, FAA, (iv) Airbus A318/A319/A320/A321
2017–22–03. has the authority to approve AMOCs for this Airworthiness Limitation Section Part 2—
(2) For airplanes identified in Airbus AD, if requested using the procedures found Damage Tolerant Airworthiness Limitation
A318/A319/A320/A321 Airworthiness in 14 CFR 39.19. In accordance with 14 CFR Items (DT–ALI), Variation 6.3, dated October
Limitation Section Part 2—Damage Tolerant 39.19, send your request to your principal
Airworthiness Limitation Items (DT–ALI), 24, 2017.
inspector or local Flight Standards District (3) For service information identified in
Variation 6.1, dated May 18, 2017: Office, as appropriate. If sending information
Concurrently with the revision required by this AD, contact Airbus SAS, Airworthiness
directly to the International Section, send it Office—EIAS, Rond-Point Emile Dewoitine
paragraph (g)(1) of this AD, revise the to the attention of the person identified in
existing maintenance or inspection program, No: 2, 31700 Blagnac Cedex, France;
paragraph (k)(2) of this AD. Information may telephone +33 5 61 93 36 96; fax +33 5 61
as applicable, to incorporate the ALIs
be emailed to: 9-ANM-116-AMOC- 93 44 51; email account.airworth-eas@airbus.
specified in Airbus A318/A319/A320/A321
REQUESTS@faa.gov. com; internet http://www.airbus.com.
Airworthiness Limitation Section Part 2—
(i) Before using any approved AMOC, (4) You may view this service information
Damage Tolerant Airworthiness Limitation
Items (DT–ALI), Variation 6.1, dated May 18, notify your appropriate principal inspector, at the FAA, Transport Standards Branch,
2017. The initial compliance time for or lacking a principal inspector, the manager 2200 South 216th St., Des Moines, WA. For
accomplishing the actions is at the applicable of the local flight standards district office/ information on the availability of this
time identified in the ALIs specified in certificate holding district office.
material at the FAA, call 206–231–3195.
Airbus A318/A319/A320/A321 (ii) AMOCs previously approved for AD
(5) You may view this service information
Airworthiness Limitation Section Part 2— 2015–05–02, Amendment 39–18112 (80 FR
that is incorporated by reference at the
Damage Tolerant Airworthiness Limitation 15152, March 23, 2015), as applicable to
National Archives and Records
Items (DT–ALI), Variation 6.1, dated May 18, Airworthiness Limitations Section (ALS) Part
Administration (NARA). For information on
2017; or within 90 days after the effective 2, are approved as AMOCs for the
the availability of this material at NARA, call
date of this AD; whichever occurs later, corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any 202–741–6030, or go to: http://
without exceeding the inspection intervals in www.archives.gov/federal-register/cfr/ibr-
the ALIs required by paragraph (i) of AD requirement in this AD to obtain corrective
actions from a manufacturer, the action must locations.html.
2017–22–03.
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(3) For airplanes identified in Airbus be accomplished using a method approved Issued in Des Moines, Washington, on
A318/A319/A320/A321 Airworthiness by the Manager, International Section, November 23, 2018.
Limitation Section Part 2—Damage Tolerant Transport Standards Branch, FAA; or the John P. Piccola,
Airworthiness Limitation Items (DT–ALI), European Aviation Safety Agency (EASA); or
Airbus SAS’s EASA Design Organization Acting Director, System Oversight Division,
Variation 6.2, dated May 24, 2017:
Aircraft Certification Service.
Concurrently with the revision required by Approval (DOA). If approved by the DOA,
paragraph (g)(1) of this AD, revise the the approval must include the DOA- [FR Doc. 2018–26362 Filed 12–4–18; 8:45 am]
existing maintenance or inspection program, authorized signature. BILLING CODE 4910–13–P
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Document Created: 2018-12-05 02:36:31
Document Modified: 2018-12-05 02:36:31
| 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. | |
| Dates | This AD is effective January 10, 2019. | |
| 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. | |
| FR Citation | 83 FR 62690 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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