83 FR 16248 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 73 (April 16, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 73 (April 16, 2018)
| Page Range | 16248-16251 | |
| FR Document | 2018-06591 |
[Federal Register Volume 83, Number 73 (Monday, April 16, 2018)] [Proposed Rules] [Pages 16248-16251] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-06591] [[Page 16248]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0169; Product Identifier 2017-NM-095-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-02- 17, which applies to all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2015-02-17 requires 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 proposed AD would add a requirement to replace or modify the two FWCs. This proposed AD would also remove airplanes from the applicability. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by May 31, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. 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- 0169; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0169; Product Identifier 2017-NM-095-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2015-02-17, Amendment 39-18084 (80 FR 4762, January 29, 2015) (``AD 2015-02-17''), for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2015-02-17 requires revising the electrical emergency configuration procedure in the Emergency Procedures section of the AFM to include procedures for deploying the ram air turbine manually to provide sufficient hydraulic power and avoid CSM/G shedding. AD 2015-02-17 resulted from an electrical load analysis that revealed that hydraulic power might not be sufficient to supply the CSM/G during slat/flap extension when only one engine is running. We issued AD 2015-02-17 to prevent CSM/G shedding in conjunction with the loss of the main electrical system, which 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. Actions Since AD 2015-02-17 Was Issued Since we issued AD 2015-02-17, we have determined that replacement or modification of the two FWCs is necessary 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 Airworthiness Directive 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 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 pre-mod/pre Service Bulletin (SB) or post- mod/post SB aeroplane configurations. [[Page 16249]] Since EASA AD 2014-0281 was issued, in order to improve the ``ELEC EMER CONFIG'' procedure, Airbus developed modifications to install improved Flight Warning Computer (FWC), 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0169. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330-31-3232, Revision 01, dated February 14, 2017. The 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Differences Between This Proposed AD and the MCAI or Service Information The MCAI applies to all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes. However, this proposed AD excludes airplanes on which Airbus modification 205228 has been embodied in production. Modification 205228 addresses the unsafe condition specified in this proposed AD. We have coordinated this difference with EASA. Costs of Compliance We estimate that this proposed AD affects 105 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- AFM revision (retained actions from AD 1 work-hour x $85 per $0 $85 $8,925 2015[dash]02[dash]17). hour = $85. FWC modification or replacement (new 3 work-hours x $85 per 0 255 26,775 proposed action). hour = $255. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this proposed 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 proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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) [[Page 16250]] 2015-02-17, Amendment 39-18084 (80 FR 4762, January 29, 2015), and adding the following new AD: Airbus: Docket No. FAA-2018-0169; Product Identifier 2017-NM-095-AD. (a) Comments Due Date We must receive comments by May 31, 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 Model A330-201, -202, -203, -223, and -243 airplanes. (2) Airbus Model A330-223F and -243F airplanes. (3) Airbus 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. 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 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. (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 a FWC standard lower than T7-0. An FWC that is not affected is a 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, 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (ii) AMOCs approved previously for AD 2015-02-17 are approved as an AMOC 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'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 http://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) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. [[Page 16251]] Issued in Des Moines, Washington, on March 22, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-06591 Filed 4-13-18; 8:45 am] BILLING CODE 4910-13-P
![16248 Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
DEPARTMENT OF TRANSPORTATION internet: http://www.airbus.com. You 02–17 resulted from an electrical load
may view this referenced service analysis that revealed that hydraulic
Federal Aviation Administration information at the FAA, Transport power might not be sufficient to supply
Standards Branch, 2200 South 216th St., the CSM/G during slat/flap extension
14 CFR Part 39 Des Moines, WA. For information on the when only one engine is running. We
[Docket No. FAA–2018–0169; Product availability of this material at the FAA, issued AD 2015–02–17 to prevent CSM/
Identifier 2017–NM–095–AD] call 206–231–3195. G shedding in conjunction with the loss
Examining the AD Docket of the main electrical system, which
RIN 2120–AA64 could lead to the scenario where the
You may examine the AD docket on flight crew is not clearly warned that the
Airworthiness Directives; Airbus the internet at http:// electrical system has switched on the
Airplanes www.regulations.gov by searching for battery and thus has a limited duration
AGENCY: Federal Aviation and locating Docket No. FAA–2018– that would allow a safe landing.
Administration (FAA), DOT. 0169; or in person at the Docket
Management Facility between 9 a.m. Actions Since AD 2015–02–17 Was
ACTION: Notice of proposed rulemaking Issued
and 5 p.m., Monday through Friday,
(NPRM). except Federal holidays. The AD docket Since we issued AD 2015–02–17, we
SUMMARY: We propose to supersede contains this NPRM, the regulatory have determined that replacement or
Airworthiness Directive (AD) 2015–02– evaluation, any comments received, and modification of the two FWCs is
17, which applies to all Airbus Model other information. The street address for necessary to address the identified
A330–200, A330–200 Freighter, and the Docket Operations office (telephone: unsafe condition.
A330–300 series airplanes. AD 2015– 800–647–5527) is in the ADDRESSES The European Aviation Safety Agency
02–17 requires revising the electrical section. Comments will be available in (EASA), which is the Technical Agent
emergency configuration procedure in the AD docket shortly after receipt. for the Member States of the European
the Emergency Procedures section of the FOR FURTHER INFORMATION CONTACT: Union, has issued EASA Airworthiness
airplane flight manual (AFM) to include Vladimir Ulyanov, Aerospace Engineer, Directive 2017–0105R1, dated July 17,
procedures for deploying the ram air International Section, Transport 2017 (referred to after this as the
turbine manually to provide sufficient Standards Branch, FAA, 2200 South Mandatory Continuing Airworthiness
hydraulic power and avoid constant 216th St., Des Moines, WA 98198; Information, or ‘‘the MCAI’’), to correct
speed motor/generator (CSM/G) telephone and fax 206–231–3229. an unsafe condition for all Airbus
shedding. Since we issued AD 2015–02– SUPPLEMENTARY INFORMATION: Model A330–200, A330–200 Freighter,
17, we have determined that and A330–300 series airplanes. The
Comments Invited
replacement or modification of the two MCAI states:
flight warning computers (FWCs) is We invite you to send any written The Constant Speed Motor/Generator
necessary to address the identified relevant data, views, or arguments about (CSM/G), as installed on Airbus A330
unsafe condition. This proposed AD this proposed AD. Send your comments aeroplanes, is qualified for an overload
would add a requirement to replace or to an address listed under the condition of 9.5 kVA [kilovolt-ampere] for 30
ADDRESSES section. Include ‘‘Docket No. minutes. This duration is sufficient to
modify the two FWCs. This proposed
AD would also remove airplanes from FAA–2018–0169; Product Identifier perform safe landing and go-around.
2017–NM–095–AD’’ at the beginning of However, electrical load analysis revealed
the applicability. We are proposing this that the hydraulic power might not be
AD to address the unsafe condition on your comments. We specifically invite
comments on the overall regulatory, sufficient to supply the CSM/G during slat/
these products. flap extension, when only one engine is
economic, environmental, and energy
DATES: We must receive comments on running.
aspects of this proposed AD. We will This condition, if not corrected, and in
this proposed AD by May 31, 2018. consider all comments received by the conjunction with the loss of main system,
ADDRESSES: You may send comments, closing date and may amend this could lead to a scenario where the crew is
using the procedures found in 14 CFR proposed AD based on those comments. not clearly warned that the electrical system
11.43 and 11.45, by any of the following We will post all comments we has switched on the battery and thus has a
methods: receive, without change, to http:// limited duration to support a safe landing.
• Federal eRulemaking Portal: Go to www.regulations.gov, including any To initially address this potential unsafe
http://www.regulations.gov. Follow the personal information you provide. We condition, Airbus issued an Aircraft Flight
instructions for submitting comments. will also post a report summarizing each Manual (AFM) Temporary Revision (TR) to
• Fax: 202–493–2251. substantive verbal contact we receive amend the electrical emergency configuration
• Mail: U.S. Department of ‘‘ELEC EMER CONFIG’’ procedure to require
about this proposed AD. the pilot to deploy the ram air turbine
Transportation, Docket Operations, M–
Discussion manually before setting the Landing
30, West Building Ground Floor, Room Recovery to ‘‘ON’’ position, which provides
W12–140, 1200 New Jersey Avenue SE, We issued AD 2015–02–17, sufficient hydraulic power and avoids CSM/
Washington, DC 20590. Amendment 39–18084 (80 FR 4762, G shedding under worst-case operational
• Hand Delivery: Deliver to Mail January 29, 2015) (‘‘AD 2015–02–17’’), conditions. Consequently, EASA issued AD
address above between 9 a.m. and 5 for all Airbus Model A330–200, A330– 2014–0273 to require amendment of the AFM
p.m., Monday through Friday, except 200 Freighter, and A330–300 series by incorporating the applicable Airbus TR.
daltland on DSKBBV9HB2PROD with PROPOSALS
Federal holidays. airplanes. AD 2015–02–17 requires After finding that [EASA] AD 2014–0273
For service information identified in revising the electrical emergency contained some incorrect and incomplete
information, EASA issued AD 2014–0281
this NPRM, contact Airbus SAS, configuration procedure in the
[which corresponds to FAA AD 2015–02–17],
Airworthiness Office—EAL, 1 Rond Emergency Procedures section of the retaining the requirements of EASA AD
Point Maurice Bellonte, 31707 Blagnac AFM to include procedures for 2014–0273, which was superseded, but
Cedex, France; telephone: +33 5 61 93 deploying the ram air turbine manually correcting the information related to pre-
36 96; fax: +33 5 61 93 45 80; email: to provide sufficient hydraulic power mod/pre Service Bulletin (SB) or post-mod/
airworthiness.A330-A340@airbus.com; and avoid CSM/G shedding. AD 2015– post SB aeroplane configurations.
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![Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules 16249
Since EASA AD 2014–0281 was issued, in Related Service Information Under 1 AD because we evaluated all pertinent
order to improve the ‘‘ELEC EMER CONFIG’’ CFR Part 51 information and determined an unsafe
procedure, Airbus developed modifications
condition exists and is likely to exist or
to install improved Flight Warning Computer Airbus has issued Service Bulletin
(FWC), which is embodied in production develop on other products of these same
A330–31–3232, Revision 01, dated
through Airbus modification (mod) 205228, type designs.
February 14, 2017. The service
and to be embodied in service with Airbus
SB A330–31–3232 * * *. information describes procedures for Differences Between This Proposed AD
For the reasons described above, this replacement or modification of the and the MCAI or Service Information
[EASA] AD retains the requirements of EASA FWCs. This service information is
AD 2014–0281, which is superseded, and reasonably available because the The MCAI applies to all Airbus Model
requires installation of a software standard interested parties have access to it A330–200, A330–200 Freighter, and
upgrade [or replacement] of the two FWCs through their normal course of business A330–300 series airplanes. However,
and removal of the applicable AFM TR once or by the means identified in the this proposed AD excludes airplanes on
the aeroplane is modified.
Since EASA AD 2017–0105 was issued, it
ADDRESSES section. which Airbus modification 205228 has
was identified that there was no need to been embodied in production.
FAA’s Determination and Requirements
require removal of applicable AFM TR, nor of This Proposed AD Modification 205228 addresses the
incorporation of a later AFM revision, as the unsafe condition specified in this
contents are identical. This revised [EASA] This product has been approved by proposed AD. We have coordinated this
AD deletes the requirement of paragraph (3) the aviation authority of another difference with EASA.
[of EASA AD 2017–0105].
country, and is approved for operation
* * * * * in the United States. Pursuant to our Costs of Compliance
You may examine the MCAI in the bilateral agreement with the State of We estimate that this proposed AD
AD docket on the internet at http:// Design Authority, we have been notified affects 105 airplanes of U.S. registry.
www.regulations.gov by searching for of the unsafe condition described in the
and locating Docket No. FAA–2018– MCAI and service information We estimate the following costs to
0169. referenced above. We are proposing this comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
AFM revision (retained actions from AD 1 work-hour × $85 per hour = $85 ................. $0 $85 $8,925
2015-02-17).
FWC modification or replacement (new pro- 3 work-hours × $85 per hour = $255 ............. 0 255 26,775
posed action).
According to the manufacturer, some products identified in this rulemaking 2. Is not a ‘‘significant rule’’ under the
of the costs of this proposed AD may be action. DOT Regulatory Policies and Procedures
covered under warranty, thereby This proposed AD is issued in (44 FR 11034, February 26, 1979);
reducing the cost impact on affected accordance with authority delegated by 3. Will not affect intrastate aviation in
individuals. We do not control warranty the Executive Director, Aircraft Alaska; and
coverage for affected individuals. As a Certification Service, as authorized by 4. Will not have a significant
result, we have included all costs in our FAA Order 8000.51C. In accordance economic impact, positive or negative,
cost estimate. with that order, issuance of ADs is on a substantial number of small entities
normally a function of the Compliance under the criteria of the Regulatory
Authority for This Rulemaking Flexibility Act.
and Airworthiness Division, but during
Title 49 of the United States Code this transition period, the Executive List of Subjects in 14 CFR Part 39
specifies the FAA’s authority to issue Director has delegated the authority to
rules on aviation safety. Subtitle I, issue ADs applicable to transport Air transportation, Aircraft, Aviation
section 106, describes the authority of category airplanes to the Director of the safety, Incorporation by reference,
the FAA Administrator. ‘‘Subtitle VII: System Oversight Division. Safety.
Aviation Programs,’’ describes in more The Proposed Amendment
Regulatory Findings
detail the scope of the Agency’s
Accordingly, under the authority
authority. We determined that this proposed AD
delegated to me by the Administrator,
We are issuing this rulemaking under would not have federalism implications
the FAA proposes to amend 14 CFR part
the authority described in ‘‘Subtitle VII, under Executive Order 13132. This
39 as follows:
Part A, Subpart III, Section 44701: proposed AD would not have a
General requirements.’’ Under that substantial direct effect on the States, on PART 39—AIRWORTHINESS
section, Congress charges the FAA with the relationship between the national DIRECTIVES
daltland on DSKBBV9HB2PROD with PROPOSALS
promoting safe flight of civil aircraft in Government and the States, or on the
air commerce by prescribing regulations distribution of power and ■ 1. The authority citation for part 39
for practices, methods, and procedures responsibilities among the various continues to read as follows:
the Administrator finds necessary for levels of government. Authority: 49 U.S.C. 106(g), 40113, 44701.
safety in air commerce. This regulation For the reasons discussed above, I
is within the scope of that authority certify this proposed regulation: § 39.13 [Amended]
because it addresses an unsafe condition 1. Is not a ‘‘significant regulatory ■ 2. The FAA amends § 39.13 by
that is likely to exist or develop on action’’ under Executive Order 12866; removing Airworthiness Directive (AD)
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![Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules 16251
Issued in Des Moines, Washington, on p.m., Monday through Friday, except We will post all comments we
March 22, 2018. Federal holidays. receive, without change, to http://
Michael Kaszycki, For Airbus service information www.regulations.gov, including any
Acting Director, System Oversight Division, identified in this NPRM, contact Airbus, personal information you provide. We
Aircraft Certification Service. Airworthiness Office—EIAS, 1 Rond will also post a report summarizing each
[FR Doc. 2018–06591 Filed 4–13–18; 8:45 am] Point Maurice Bellonte, 31707 Blagnac substantive verbal contact we receive
BILLING CODE 4910–13–P Cedex, France; telephone +33 5 61 93 36 about this NPRM.
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; Discussion
DEPARTMENT OF TRANSPORTATION internet http://www.airbus.com. The European Aviation Safety Agency
For United Technologies Corporation (EASA), which is the Technical Agent
Federal Aviation Administration Aerospace Systems (UTAS) service for the Member States of the European
information identified in this AD, Union, has issued EASA Airworthiness
14 CFR Part 39 contact United Technologies Directive 2017–0237, dated December 4,
Corporation Aerospace Systems (UTAS): 2017 (referred to after this as the
[Docket No. FAA–2018–0298; Product
Identifier 2017–NM–179–AD] Goodrich Corporation, Actuation Mandatory Continuing Airworthiness
Systems, Stafford Road, Fordhouses, Information, or ‘‘the MCAI’’), to correct
RIN 2120–AA64 Wolverhampton WV10 7EH, England; an unsafe condition for all Airbus
phone: +44 (0) 1902 624938; fax: +44 (0) Model A318 and A319 series airplanes;
Airworthiness Directives; Airbus 1902 788100; email: Model A320–211, A320–212, A320–214,
Airplanes techpubs.wolverhampton@ A320–216, A320–231, A320–232, A320–
AGENCY: Federal Aviation goodrich.com; internet: http:// 233 airplanes; and Model A321–111,
Administration (FAA), DOT. www.goodrich.com/TechPubs. A321–112, A321–131, A321–211, A321–
You may view this service 212, A321–213, A321–231, and A321–
ACTION: Notice of proposed rulemaking
information at the FAA, Transport 232 airplanes. The MCAI states:
(NPRM). Standards Branch, 2200 South 216th The Trimmable Horizontal Stabilizer
SUMMARY: We propose to adopt a new Street, Des Moines, WA. For Actuator (THSA) of Airbus A320 Family
airworthiness directive (AD) for all information on the availability of this aeroplanes has been rig-tested to check
Airbus Model A318 and A319 series material at the FAA, call 206–231–3195. secondary load path behaviour in case of
airplanes; Model A320–211, A320–212, primary load path failure. In that
Examining the AD Docket configuration, the loads are transferred to the
A320–214, A320–216, A320–231, A320–
You may examine the AD docket on secondary load path, which should jam,
232, and A320–233 airplanes; and preventing any Trimmable Horizontal
the internet at http://
Model A321–111, A321–112, A321–131, Stabilizer motion. The test results showed
www.regulations.gov by searching for
A321–211, A321–212, A321–213, A321– that the secondary load path did not jam as
and locating Docket No. FAA–2018–
231, and A321–232 airplanes. This expected, preventing detection of the primary
0298; or in person at the Docket load path failure. To verify the integrity of
proposed AD was prompted by reports Management Facility between 9 a.m.
of missing assembly hardware on the the THSA primary load path and the correct
and 5 p.m., Monday through Friday, installation of the THSA, Airbus issued
trimmable horizontal stabilizer actuator except Federal holidays. The AD docket Service Bulletin (SB) A320–27–1164, later
(THSA). This proposed AD would contains this NPRM, the regulatory revised multiple times, and SB A320–
require repetitive inspections and evaluation, any comments received, and 27A1179, and EASA issued AD 2006–0223
checks of the lower and upper THSA other information. The street address for [which corresponds to FAA AD 2007–06–02,
attachments and applicable related the Docket Operations office (telephone Amendment 39–14983 (72 FR 12072, March
investigative and corrective actions; a 15, 2007) (‘‘AD 2007–06–02’’)], AD 2007–
800–647–5527) is in the ADDRESSES 0178 [which corresponds to FAA AD 2008–
one-time inspection of the THSA lower section. Comments will be available in
attachment and replacement as 09–16, Amendment 39–15497 (73 FR 24160,
the AD docket shortly after receipt. May 2, 2008)(‘‘AD 2008–09–16’’)], AD 2008–
applicable; and, for certain airplanes, 0150, and AD 2014–0147, each AD
FOR FURTHER INFORMATION CONTACT:
activation of the electrical load sensing superseding the previous one, requiring one-
Sanjay Ralhan, Aerospace Engineer,
device (ELSD) and concurrent time and repetitive inspections.
International Section, Transport
modifications. We are proposing this Since EASA AD 2014–0147 was issued,
Standards Branch, FAA, 2200 South Airbus designed a new device, called
AD to address the unsafe condition on
216th Street, Des Moines, WA 98198; Electrical Load Sensing Device (ELSD), to
these products.
phone and fax: 206–231–3223. introduce a new mean of THSA upper
DATES: We must receive comments on
SUPPLEMENTARY INFORMATION: secondary load path engagement detection.
this proposed AD by May 31, 2018. Consequently, Airbus issued several SBs
ADDRESSES: You may send comments, Comments Invited (Airbus SB A320–27–1245, A320–27–1246,
using the procedures found in 14 CFR We invite you to send any written and A320–27–1247, depending on aeroplane
11.43 and 11.45, by any of the following relevant data, views, or arguments about configuration) providing instructions to
install the wiring provision for ELSD
methods: this proposal. Send your comments to installation and to install ELSD on the THSA,
• Federal eRulemaking Portal: Go to an address listed under the ADDRESSES and SB A320–27–1248, providing
http://www.regulations.gov. Follow the section. Include ‘‘Docket No. FAA– instructions to activate the ELSD. Airbus also
instructions for submitting comments. 2018–0298; Product Identifier 2017– revised SB A320–27–1164, now at Revision
daltland on DSKBBV9HB2PROD with PROPOSALS
• Fax: 202–493–2251. NM–179–AD’’ at the beginning of your 13, including instructions applicable for
• Mail: U.S. Department of comments. We specifically invite aircraft equipped with ELSD.
Transportation, Docket Operations, M– comments on the overall regulatory, Furthermore, following a visual inspection
30, West Building Ground Floor, Room economic, environmental, and energy of the THSA, an operator reported that the
THSA was found with a bush missing,
W12–140, 1200 New Jersey Avenue SE, aspects of this NPRM. We will consider inducing torqueing of the THSA lower
Washington, DC 20590. all comments received by the closing attachment primary bolt against the THSA
• Hand Delivery: Deliver to Mail date and may amend this NPRM based lug, which resulted in the application of a
address above between 9 a.m. and 5 on those comments. transverse force on the lug.
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Document Created: 2018-04-14 02:19:04
Document Modified: 2018-04-14 02:19:04
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by May 31, 2018. | |
| 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. | |
| FR Citation | 83 FR 16248 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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