[Federal Register Volume 83, Number 73 (Monday, April 16, 2018)]
[Proposed Rules]
[Pages 16248-16251]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-06591]



[[Page 16248]]

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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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: [email protected]; internet: http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195.

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.
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    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: [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 
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: [email protected]; 
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