Airworthiness Directives; Airbus SAS Airplanes, 44457-44460 [2018-18736]

Download as PDF Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations Conclusion This action affects only certain novel or unusual design features on the balloon models specified in these special conditions. It is not a rule of general applicability and it affects only the applicant who applied to the FAA for approval of these features on the airplane. These special conditions are identical in intent to the EASA special conditions, although the formatting has been altered to meet these special condition requirements. List of Subjects in 14 CFR Part 31 Aircraft, Aviation safety. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701– 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Ultramagic S.A. Model M–56, M–56C, M–65, M–65C, M–77, M–77C, M–90, M–105, M–120, M–130, M–145, M–160, N–180, N–210, N–250, N–300, N–355, N–425, S–70, S–90, S–105, S– 130, S–160, T–150, T–180, T–210, V–56, V–65, V–77, V–90, and V–105 balloons with a basket Model no. CV–08. ■ 1. Hot Air Balloon Crashworthiness Requirements for Seat Installations and Restraints for Seated and Restrained Occupants a. Occupant Mass For calculation purposes, it should be assumed the mass of an occupant is at least 86 kilograms (190 pounds). daltland on DSKBBV9HB2PROD with RULES b. Seats, Safety Belts, and Harnesses Factor of Safety For each seat, safety belt, and harness, its attachment to the structure must be shown, by analysis, tests, or both, to be able to withstand the inertia forces prescribed in paragraph (c) of these special conditions multiplied by a fitting factor of 1.33. c. Emergency Landing Conditions— General The balloon—although it may be damaged under emergency landing conditions—must be designed to give each occupant every reasonable chance of avoiding serious injury in a crash landing—when seat belts provided for in the design are properly used—and the occupant is subject to the following ultimate inertia forces acting relative to the surrounding structure as well as independently of each other. (1) Forward 6g VerDate Sep<11>2014 16:04 Aug 30, 2018 Jkt 244001 (2) Sideways 6g (3) Downward 6g d. Seats and Seatbelts (1) Each seat and its supporting structure must be designed for an occupant mass in accordance paragraph (a) of these special conditions and for the maximum load factors corresponding to the specified flight and ground load conditions, including the emergency landing conditions prescribed in paragraph (c) of these special conditions. (2) Each seat or berth shall be fitted with an individual approved seat belt or harness. (3) Seat belts installed on the balloon must not fail under flight or ground load conditions or emergency landing conditions in accordance with paragraph (c) of these special conditions, taking into account the geometrical arrangement of the belt attachment and the seat. Issued in Kansas City, Missouri, on August 23, 2018. Pat Mullen, Manager, Small Airplane Standards Branch, Aircraft Certification Service. [FR Doc. 2018–18885 Filed 8–30–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0169; Product Identifier 2017–NM–095–AD; Amendment 39–19372; AD 2018–17–18] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2015–02– 17, which applied to all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes. AD 2015– 02–17 required revising the electrical emergency configuration procedure in the Emergency Procedures section of the airplane flight manual (AFM) to include procedures for deploying the ram air turbine manually to provide sufficient hydraulic power and avoid constant speed motor/generator (CSM/G) shedding. Since we issued AD 2015–02– 17, we have determined that replacement or modification of the two SUMMARY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 44457 flight warning computers (FWCs) is necessary to address the identified unsafe condition. This AD requires the replacement or modifications of the two FWCs. This AD also removes airplanes from the applicability. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 5, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 5, 2018. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of February 13, 2015 (80 FR 4762, January 29, 2015). ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, 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 account.airwortheas@airbus.com; internet https:// www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0169. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0169; 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 Docket Operations, 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: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2015–02–17, E:\FR\FM\31AUR1.SGM 31AUR1 44458 Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations daltland on DSKBBV9HB2PROD with RULES Amendment 39–18084 (80 FR 4762, January 29, 2015) (‘‘AD 2015–02–17’’). AD 2015–02–17 applied to all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes. The NPRM published in the Federal Register on April 16, 2018 (83 FR 16248). The NPRM was prompted by a determination that replacement or modification of the two FWCs is necessary to address the identified unsafe condition. The NPRM proposed to require the replacement or modification of the two FWCs. The NPRM also proposed to remove airplanes from the applicability. We are issuing this AD to address the identified unsafe condition. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017– 0105R1, dated July 17, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A330–200, A330–200 Freighter, and A330–300 series airplanes. The MCAI states: The Constant Speed Motor/Generator (CSM/G), as installed on Airbus A330 aeroplanes, is qualified for an overload condition of 9.5 kVA [kilovolt-ampere] for 30 minutes. This duration is sufficient to perform safe landing and go-around. However, electrical load analysis revealed that the hydraulic power might not be sufficient to supply the CSM/G during slat/ flap extension, when only one engine is running. This condition, if not corrected, and in conjunction with the loss of main system, could lead to a scenario where the crew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration to support a safe landing. To initially address this potential unsafe condition, Airbus issued an Aircraft Flight Manual (AFM) Temporary Revision (TR) to amend the electrical emergency configuration ‘‘ELEC EMER CONFIG’’ procedure to require the pilot to deploy the ram air turbine manually before setting the Landing Recovery to ‘‘ON’’ position, which provides sufficient hydraulic power and avoids CSM/ G shedding under worst-case operational conditions. Consequently, EASA issued AD 2014–0273 to require amendment of the AFM by incorporating the applicable Airbus TR. After finding that [EASA] AD 2014–0273 contained some incorrect and incomplete information, EASA issued AD 2014–0281 [which corresponds to FAA AD 2015–02–17], retaining the requirements of EASA AD 2014–0273, which was superseded, but VerDate Sep<11>2014 16:04 Aug 30, 2018 Jkt 244001 correcting the information related to premod/ pre Service Bulletin (SB) or post-mod/post SB aeroplane configurations. Since EASA AD 2014–0281 was issued, in order to improve the ‘‘ELEC EMER CONFIG’’ procedure, Airbus developed modifications to install improved FWCs, which is embodied in production through Airbus modification (mod) 205228, and to be embodied in service with Airbus SB A330– 31–3232 * * *. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014–0281, which is superseded, and requires installation of a software standard upgrade [or replacement] of the two FWCs and removal of the applicable AFM TR once the aeroplane is modified. Since EASA AD 2017–0105 was issued, it was identified that there was no need to require removal of applicable AFM TR, nor incorporation of a later AFM revision, as the contents are identical. This revised [EASA] AD deletes the requirement of paragraph (3) [of EASA AD 2017–0105]. * * * * * You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0169. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. The Air Line Pilots Association, International (ALPA), indicated its support for the NPRM. Request for Additional Credit Delta Air Lines requested that paragraph (l) of the proposed AD, ‘‘Credit for Previous Actions,’’ include Airbus Service Bulletin A330–31–3232, Revision 01, dated February 14, 2017, as well as Airbus Service Bulletin A330– 31–3232, dated May 4, 2016. We disagree this change is necessary. Paragraph (f) of this AD requires compliance with this AD unless already done. Paragraph (j) of this AD mandates actions in accordance with Airbus Service Bulletin A330–31–3232, Revision 01, dated February 14, 2017. Therefore, as specified in paragraph (f) of this AD, having previously accomplished the actions specified in Airbus Service Bulletin A330–31–3232, Revision 01, dated February 14, 2017, means compliance with paragraph (j) of this AD has already been established. In paragraph (l) of this AD, we give credit PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 to operators that have previously accomplished an earlier revision of the required service information identified in paragraph (j) of this AD; therefore, as specified in paragraph (l) of this AD, having accomplished Airbus Service Bulletin A330–31–3232, dated May 4, 2016, prior to the effective date of this AD means compliance with paragraph (j) of this AD has already been established. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule as proposed, except for 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. Related Service Information Under 1 CFR Part 51 Airbus SAS has issued A330/A340 Airplane Flight Manual (AFM) Temporary Revision (TR) TR427, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014; and A330/A340 AFM TR TR428, UPDATE OF ELEC— EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. This service information describes updated electrical emergency configuration procedures in the AFM. This service information is distinct because it applies to airplanes in different configurations. Airbus SAS has issued Service Bulletin A330–31–3232, Revision 01, including Appendix 01, dated February 14, 2017. This service information describes procedures for replacement or modification of the FWCs. 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 105 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\31AUR1.SGM 31AUR1 Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations 44459 ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators 4 work-hour × $85 per hour = $340 ............................................................................................ $0 $340 $35,700 According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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. daltland on DSKBBV9HB2PROD with RULES 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: VerDate Sep<11>2014 16:04 Aug 30, 2018 Jkt 244001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–02–2017, Amendment 39–18084 (80 FR 4762, January 29, 2015), and adding the following new AD: ■ 2018–17–18 Airbus SAS: Amendment 39– 19372; Docket No. FAA–2018–0169; Product Identifier 2017–NM–095–AD. (a) Effective Date This AD is effective October 5, 2018. (b) Affected ADs This AD replaces AD 2015–02–17, Amendment 39–18084 (80 FR 4762, January 29, 2015) (‘‘AD 2015–02–17’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those airplanes with Airbus modification 205228 embodied in production. (1) Airbus SAS Model A330–201, –202, –203, –223, and –243 airplanes. (2) Airbus SAS Model A330–223F and –243F airplanes. (3) Airbus SAS Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 (d) Subject Air Transport Association (ATA) of America Code 24, Electrical power. (e) Reason This AD was prompted by an electrical load analysis that revealed that hydraulic power might not be sufficient to supply the constant speed motor/generator (CSM/G) during slat/flap extension when only one engine is running and a determination that replacement or modification of the two flight warning computers (FWCs) is necessary to address the identified unsafe condition. We are issuing this AD to prevent such a condition which, in conjunction with the loss of the main electrical system, could lead to the scenario where the flight crew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Airplane Flight Manual (AFM) Revision, With a New Exception This paragraph restates the requirements of paragraph (g) of AD 2015–02–17, with a new exception. Except for airplanes identified in paragraph (h) of this AD: Within 15 days after February 13, 2015 (the effective date of AD 2015–02–17), revise the Emergency Procedures section of the Airbus A330/A340 AFM to include the information in the applicable Airbus temporary revision (TR) specified in paragraph (g)(1) or (g)(2) of this AD. This may be done by inserting a copy of the applicable TR specified in paragraph (g)(1) or (g)(2) of this AD into the AFM. Operate the airplane according to the procedures in the applicable TR. When the information in the applicable TR has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, provided the relevant information in the general revision is identical to that in the TR, and the TR may be removed. (1) For airplanes in Airbus premodification 47930 configuration and preAirbus Service Bulletin A330–28–3067 configuration: Airbus A330/A340 AFM TR TR427, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. (2) For airplanes in Airbus postmodification 47930 configuration or postAirbus Service Bulletin A330–28–3067 configuration: Airbus A330/A340 AFM TR TR428, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. E:\FR\FM\31AUR1.SGM 31AUR1 44460 Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations (h) New Airplanes Not Affected by the Retained AFM Revision Airplanes operated with an AFM that incorporates the information in Airbus EMERGENCY PROCEDURES/24– ELECTRICAL POWER/ELEC—EMER CONFIG Documentary Unit (DU) 00005218.0001001 (for airplanes in Airbus pre-modification 47930 configuration and pre-Airbus Service Bulletin A330–28–3067 configuration), or DU 00005218.0002001 (for airplanes in an Airbus post-modification 47930 configuration or post-Airbus Service Bulletin A330–28–3067 configuration), as applicable, are compliant with the requirements of paragraph (g) of this AD, provided that the applicable DU is not removed from the AFM. (i) New Definitions (1) For the purposes of this AD, an affected FWC is an FWC standard lower than T7–0. An FWC that is not affected is an FWC standard T7–0 having part number (P/N) LA2E20202T70000, or higher standard. (2) For the purposes of this AD: Group 1 airplanes are those equipped with an affected FWC (as defined in paragraph (i)(1) of this AD) as of the effective date of this AD. Group 2 airplanes are those equipped with FWCs that are not affected (as defined in paragraph (i)(1) of this AD) as of the effective date of this AD. (j) New Requirement of This AD: FWC Replacement or Modification For Group 1 airplanes: Within 24 months after the effective date of this AD: Replace or modify an affected FWC with an FWC that is not affected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–31–3232, Revision 01, including Appendix 01, dated February 14, 2017. (k) Parts Installation Prohibition (1) For Group 1 airplanes: After accomplishing the actions required by paragraph (j) of this AD, no person may install an affected FWC on the modified airplane. (2) For Group 2 airplanes: As of the effective date of this AD, no person may install an affected FWC on any airplane. daltland on DSKBBV9HB2PROD with RULES (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330–31–3232, dated May 4, 2016. (m) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. VerDate Sep<11>2014 16:04 Aug 30, 2018 Jkt 244001 (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 approved previously for AD 2015–02–17 are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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. (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 AD 2017–0105R1, dated July 17, 2017, for related information. This MCAI may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0169. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(5) and (o)(6) 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. (3) The following service information was approved for IBR on October 5, 2018. (i) Airbus Service Bulletin A330–31–3232, Revision 01, including Appendix 01, dated February 14, 2017. (ii) Reserved. (4) The following service information was approved for IBR on of February 13, 2015 (80 FR 4762, January 29, 2015). (i) Airbus A330/A340 Airplane Flight Manual (AFM) Temporary Revision TR427, UPDATE OF ELEC—EMER CONFIG PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 PROCEDURE, Issue 1.0, dated November 7, 2014. (ii) Airbus A330/A340 AFM Temporary Revision TR428, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 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 account.airworth-eas@ airbus.com; internet https://www.airbus.com. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on August 17, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–18736 Filed 8–30–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0361; Product Identifier 2017–NM–160–AD; Amendment 39–19373; AD 2018–17–19] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, and A320 series airplanes, and Model A321– 111, –112, –131, –211, –212, –213, –231, –232, –251N, –253N, and –271N airplanes. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. SUMMARY: E:\FR\FM\31AUR1.SGM 31AUR1

Agencies

[Federal Register Volume 83, Number 170 (Friday, August 31, 2018)]
[Rules and Regulations]
[Pages 44457-44460]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-18736]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0169; Product Identifier 2017-NM-095-AD; Amendment 
39-19372; AD 2018-17-18]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-02-17, 
which applied to all Airbus Model A330-200, A330-200 Freighter, and 
A330-300 series airplanes. AD 2015-02-17 required revising the 
electrical emergency configuration procedure in the Emergency 
Procedures section of the airplane flight manual (AFM) to include 
procedures for deploying the ram air turbine manually to provide 
sufficient hydraulic power and avoid constant speed motor/generator 
(CSM/G) shedding. Since we issued AD 2015-02-17, we have determined 
that replacement or modification of the two flight warning computers 
(FWCs) is necessary to address the identified unsafe condition. This AD 
requires the replacement or modifications of the two FWCs. This AD also 
removes airplanes from the applicability. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective October 5, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 5, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
February 13, 2015 (80 FR 4762, January 29, 2015).

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 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 https://www.airbus.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195. It is also available on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2018-0169.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0169; 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 Docket Operations, 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: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2015-02-17,

[[Page 44458]]

Amendment 39-18084 (80 FR 4762, January 29, 2015) (``AD 2015-02-17''). 
AD 2015-02-17 applied to all Airbus Model A330-200, A330-200 Freighter, 
and A330-300 series airplanes. The NPRM published in the Federal 
Register on April 16, 2018 (83 FR 16248). The NPRM was prompted by a 
determination that replacement or modification of the two FWCs is 
necessary to address the identified unsafe condition. The NPRM proposed 
to require the replacement or modification of the two FWCs. The NPRM 
also proposed to remove airplanes from the applicability. We are 
issuing this AD to address the identified unsafe condition.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0105R1, dated July 17, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus SAS Model A330-200, A330-200 
Freighter, and A330-300 series airplanes. The MCAI states:

    The Constant Speed Motor/Generator (CSM/G), as installed on 
Airbus A330 aeroplanes, is qualified for an overload condition of 
9.5 kVA [kilovolt-ampere] for 30 minutes. This duration is 
sufficient to perform safe landing and go-around. However, 
electrical load analysis revealed that the hydraulic power might not 
be sufficient to supply the CSM/G during slat/flap extension, when 
only one engine is running.
    This condition, if not corrected, and in conjunction with the 
loss of main system, could lead to a scenario where the crew is not 
clearly warned that the electrical system has switched on the 
battery and thus has a limited duration to support a safe landing.
    To initially address this potential unsafe condition, Airbus 
issued an Aircraft Flight Manual (AFM) Temporary Revision (TR) to 
amend the electrical emergency configuration ``ELEC EMER CONFIG'' 
procedure to require the pilot to deploy the ram air turbine 
manually before setting the Landing Recovery to ``ON'' position, 
which provides sufficient hydraulic power and avoids CSM/G shedding 
under worst-case operational conditions. Consequently, EASA issued 
AD 2014-0273 to require amendment of the AFM by incorporating the 
applicable Airbus TR.
    After finding that [EASA] AD 2014-0273 contained some incorrect 
and incomplete information, EASA issued AD 2014-0281 [which 
corresponds to FAA AD 2015-02-17], retaining the requirements of 
EASA AD 2014-0273, which was superseded, but correcting the 
information related to premod/pre Service Bulletin (SB) or post-mod/
post SB aeroplane configurations.
    Since EASA AD 2014-0281 was issued, in order to improve the 
``ELEC EMER CONFIG'' procedure, Airbus developed modifications to 
install improved FWCs, which is embodied in production through 
Airbus modification (mod) 205228, and to be embodied in service with 
Airbus SB A330-31-3232 * * *.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0281, which is superseded, and requires 
installation of a software standard upgrade [or replacement] of the 
two FWCs and removal of the applicable AFM TR once the aeroplane is 
modified.
    Since EASA AD 2017-0105 was issued, it was identified that there 
was no need to require removal of applicable AFM TR, nor 
incorporation of a later AFM revision, as the contents are 
identical. This revised [EASA] AD deletes the requirement of 
paragraph (3) [of EASA AD 2017-0105].
* * * * *
    You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0169.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment. The Air Line Pilots 
Association, International (ALPA), indicated its support for the NPRM.

Request for Additional Credit

    Delta Air Lines requested that paragraph (l) of the proposed AD, 
``Credit for Previous Actions,'' include Airbus Service Bulletin A330-
31-3232, Revision 01, dated February 14, 2017, as well as Airbus 
Service Bulletin A330-31-3232, dated May 4, 2016.
    We disagree this change is necessary. Paragraph (f) of this AD 
requires compliance with this AD unless already done. Paragraph (j) of 
this AD mandates actions in accordance with Airbus Service Bulletin 
A330-31-3232, Revision 01, dated February 14, 2017. Therefore, as 
specified in paragraph (f) of this AD, having previously accomplished 
the actions specified in Airbus Service Bulletin A330-31-3232, Revision 
01, dated February 14, 2017, means compliance with paragraph (j) of 
this AD has already been established. In paragraph (l) of this AD, we 
give credit to operators that have previously accomplished an earlier 
revision of the required service information identified in paragraph 
(j) of this AD; therefore, as specified in paragraph (l) of this AD, 
having accomplished Airbus Service Bulletin A330-31-3232, dated May 4, 
2016, prior to the effective date of this AD means compliance with 
paragraph (j) of this AD has already been established. We have not 
changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule as proposed, except for 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.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued A330/A340 Airplane Flight Manual (AFM) 
Temporary Revision (TR) TR427, UPDATE OF ELEC--EMER CONFIG PROCEDURE, 
Issue 1.0, dated November 7, 2014; and A330/A340 AFM TR TR428, UPDATE 
OF ELEC--EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. This 
service information describes updated electrical emergency 
configuration procedures in the AFM. This service information is 
distinct because it applies to airplanes in different configurations.
    Airbus SAS has issued Service Bulletin A330-31-3232, Revision 01, 
including Appendix 01, dated February 14, 2017. This service 
information describes procedures for replacement or modification of the 
FWCs.
    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 105 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 44459]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
4 work-hour x $85 per hour = $340............................              $0             $340          $35,700
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

    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 removing Airworthiness Directive (AD) 
2015-02-2017, Amendment 39-18084 (80 FR 4762, January 29, 2015), and 
adding the following new AD:

2018-17-18 Airbus SAS: Amendment 39-19372; Docket No. FAA-2018-0169; 
Product Identifier 2017-NM-095-AD.

(a) Effective Date

    This AD is effective October 5, 2018.

(b) Affected ADs

    This AD replaces AD 2015-02-17, Amendment 39-18084 (80 FR 4762, 
January 29, 2015) (``AD 2015-02-17'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers, except those airplanes with Airbus 
modification 205228 embodied in production.
    (1) Airbus SAS Model A330-201, -202, -203, -223, and -243 
airplanes.
    (2) Airbus SAS Model A330-223F and -243F airplanes.
    (3) Airbus SAS Model A330-301, -302, -303, -321, -322, -323, -
341, -342, and -343 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
power.

(e) Reason

    This AD was prompted by an electrical load analysis that 
revealed that hydraulic power might not be sufficient to supply the 
constant speed motor/generator (CSM/G) during slat/flap extension 
when only one engine is running and a determination that replacement 
or modification of the two flight warning computers (FWCs) is 
necessary to address the identified unsafe condition. We are issuing 
this AD to prevent such a condition which, in conjunction with the 
loss of the main electrical system, could lead to the scenario where 
the flight crew is not clearly warned that the electrical system has 
switched on the battery and thus has a limited duration that would 
allow a safe landing.

(f) Compliance

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

(g) Retained Airplane Flight Manual (AFM) Revision, With a New 
Exception

    This paragraph restates the requirements of paragraph (g) of AD 
2015-02-17, with a new exception. Except for airplanes identified in 
paragraph (h) of this AD: Within 15 days after February 13, 2015 
(the effective date of AD 2015-02-17), revise the Emergency 
Procedures section of the Airbus A330/A340 AFM to include the 
information in the applicable Airbus temporary revision (TR) 
specified in paragraph (g)(1) or (g)(2) of this AD. This may be done 
by inserting a copy of the applicable TR specified in paragraph 
(g)(1) or (g)(2) of this AD into the AFM. Operate the airplane 
according to the procedures in the applicable TR. When the 
information in the applicable TR has been included in the general 
revisions of the AFM, the general revisions may be inserted into the 
AFM, provided the relevant information in the general revision is 
identical to that in the TR, and the TR may be removed.
    (1) For airplanes in Airbus pre-modification 47930 configuration 
and pre-Airbus Service Bulletin A330-28-3067 configuration: Airbus 
A330/A340 AFM TR TR427, UPDATE OF ELEC--EMER CONFIG PROCEDURE, Issue 
1.0, dated November 7, 2014.
    (2) For airplanes in Airbus post-modification 47930 
configuration or post-Airbus Service Bulletin A330-28-3067 
configuration: Airbus A330/A340 AFM TR TR428, UPDATE OF ELEC--EMER 
CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014.

[[Page 44460]]

(h) New Airplanes Not Affected by the Retained AFM Revision

    Airplanes operated with an AFM that incorporates the information 
in Airbus EMERGENCY PROCEDURES/24-ELECTRICAL POWER/ELEC--EMER CONFIG 
Documentary Unit (DU) 00005218.0001001 (for airplanes in Airbus pre-
modification 47930 configuration and pre-Airbus Service Bulletin 
A330-28-3067 configuration), or DU 00005218.0002001 (for airplanes 
in an Airbus post-modification 47930 configuration or post-Airbus 
Service Bulletin A330-28-3067 configuration), as applicable, are 
compliant with the requirements of paragraph (g) of this AD, 
provided that the applicable DU is not removed from the AFM.

(i) New Definitions

    (1) For the purposes of this AD, an affected FWC is an FWC 
standard lower than T7-0. An FWC that is not affected is an FWC 
standard T7-0 having part number (P/N) LA2E20202T70000, or higher 
standard.
    (2) For the purposes of this AD: Group 1 airplanes are those 
equipped with an affected FWC (as defined in paragraph (i)(1) of 
this AD) as of the effective date of this AD. Group 2 airplanes are 
those equipped with FWCs that are not affected (as defined in 
paragraph (i)(1) of this AD) as of the effective date of this AD.

(j) New Requirement of This AD: FWC Replacement or Modification

    For Group 1 airplanes: Within 24 months after the effective date 
of this AD: Replace or modify an affected FWC with an FWC that is 
not affected, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-31-3232, Revision 01, including 
Appendix 01, dated February 14, 2017.

(k) Parts Installation Prohibition

    (1) For Group 1 airplanes: After accomplishing the actions 
required by paragraph (j) of this AD, no person may install an 
affected FWC on the modified airplane.
    (2) For Group 2 airplanes: As of the effective date of this AD, 
no person may install an affected FWC on any airplane.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(j) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A330-31-3232, dated 
May 4, 2016.

(m) Other FAA AD Provisions

    (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].
    (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 approved previously for AD 2015-02-17 are approved as 
AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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.
    (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 AD 2017-0105R1, dated July 17, 2017, for related 
information. This MCAI may be found in the AD docket on the internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2018-0169.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3229.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(5) and (o)(6) 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.
    (3) The following service information was approved for IBR on 
October 5, 2018.
    (i) Airbus Service Bulletin A330-31-3232, Revision 01, including 
Appendix 01, dated February 14, 2017.
    (ii) Reserved.
    (4) The following service information was approved for IBR on of 
February 13, 2015 (80 FR 4762, January 29, 2015).
    (i) Airbus A330/A340 Airplane Flight Manual (AFM) Temporary 
Revision TR427, UPDATE OF ELEC--EMER CONFIG PROCEDURE, Issue 1.0, 
dated November 7, 2014.
    (ii) Airbus A330/A340 AFM Temporary Revision TR428, UPDATE OF 
ELEC--EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014.
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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 
https://www.airbus.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on August 17, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-18736 Filed 8-30-18; 8:45 am]
 BILLING CODE 4910-13-P
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