83 FR 55299 - Airworthiness Directives; Airbus SAS Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 214 (November 5, 2018)

We propose to supersede Airworthiness Directive (AD) 2016-19- 14, which applies to certain Airbus SAS Model A318 and A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2016-19-14 requires repetitive inspections for cracking of the 10VU rack fitting lugs, and repair of any cracking. Since we issued AD 2016-19-14, we have determined that the unsafe condition may exist on additional airplanes. This proposed AD continues to require repetitive inspections for cracking of the 10VU rack fitting lugs, and repair of any cracking. This proposed AD would also add airplanes to the applicability. We are proposing this AD to address the unsafe condition on these products.

[Federal Register Volume 83, Number 214 (Monday, November 5, 2018)]
[Proposed Rules]
[Pages 55299-55303]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-23689]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0903; Product Identifier 2018-NM-113-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS 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) 2016-19-
14, which applies to certain Airbus SAS Model A318 and A319 series 
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; 
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. AD 2016-19-14 requires repetitive inspections for cracking 
of the 10VU rack fitting lugs, and repair of any cracking. Since we 
issued AD 2016-19-14, we have determined that the unsafe condition may 
exist on additional airplanes. This proposed AD continues to require 
repetitive inspections for cracking of the 10VU rack fitting lugs, and 
repair of any cracking. This proposed AD would also add airplanes to 
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 December 20, 
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--EIAS, Rond-Point Emile Dewoitine No: 2, 
31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email [email protected]; internet http://www.airbus.com. You may view this referenced service

[[Page 55300]]

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-
0903; 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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0903; 
Product Identifier 2018-NM-113-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 2016-19-14, Amendment 39-18663 (81 FR 71602, October 
18, 2016) (``AD 2016-19-14''), for certain Airbus SAS Model A318 and 
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. AD 2016-19-14 requires repetitive inspections for 
cracking of the 10VU rack fitting lugs, and repair of any cracking. AD 
2016-19-14 resulted from a report of cracks found during maintenance 
inspections on certain 10VU rack fitting lugs. We issued AD 2016-19-14 
to address reading difficulties of flight-critical information 
displayed to the flightcrew during a critical phase of flight, such as 
an approach or takeoff, which could result in loss of airplane control 
at an altitude insufficient for recovery.

Actions Since AD 2016-19-14 Was Issued

    AD 2016-19-14 applies to the identified airplane models on which 
Airbus Modification 35869 has not been embodied in production. Since we 
issued AD 2016-19-14, we have determined that the unsafe condition may 
also exist on airplanes in a post-Airbus Modification 35869 
configuration.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0131, dated June 19, 2018 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus SAS Model A318 and A319 series 
airplanes; A320-211, -212, -214, -216, -231, -232, and -233 airplanes; 
and A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. 
The MCAI states:

    During an unscheduled maintenance operation on an A330 
aeroplane, the 10VU rack was removed for access and cracks were 
discovered on 10VU rack side fittings on lugs 1, 3 and 4. As a 
similar design is installed on A320 family aeroplanes, a sampling 
review was done to determine the possible fleet impact. The result 
showed that several aeroplanes had cracked or broken 10VU rack side 
fittings.
    This condition, if not detected and corrected, could lead to a 
high vibration level on the primary flight and navigation displays 
during critical flight phases (take-off and landing), possibly 
creating reading difficulties for the crew.
    Prompted by these findings, Airbus developed mod 35869 to 
reinforce the affected rack fitting lugs. For in-service aeroplanes, 
Airbus published SB [service bulletin] A320-92-1087 to provide 
detailed inspection (DET) and repair instructions. Consequently, 
EASA AD 2015-0170 [which corresponds to FAA AD 2016-19-14] was 
issued to require, for all pre mod 35869 aeroplanes, repetitive DET 
of the affected 10VU rack fitting lugs and, depending on findings, 
accomplishment of a repair.
    Since that [EASA] AD was issued, analysis confirmed the need to 
extend the inspection to post mod 35869 aeroplanes. Airbus issued SB 
A320-92-1119 providing instructions for DET and repair of those 
aeroplanes accordingly. Airbus developed mod 157335 to further 
reinforce and adjust the affected rack fitting lugs. Analysis is 
still ongoing to confirm mod 157335 as terminating action for the 
requirements of this [EASA] AD, and further AD action may follow.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0170, which is superseded, expanding 
the Applicability to include post mod 35869 aeroplanes, and 
requiring, for all aeroplanes, repetitive DET of the affected 10VU 
rack fitting lugs and, depending on findings, accomplishment of a 
repair [and reporting positive and negative findings to Airbus].

    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-
0903.

Model A320-216 Airplanes

    The Airbus SAS Model A320-216 was type certificated on December 19, 
2016. Before that date, any EASA ADs that affected Model A320-216 
airplanes were included on the Required Airworthiness Actions List 
(RAAL). One or more Model A320-216 airplanes have subsequently been 
placed on the U.S. Register, and will now be included in FAA AD 
actions. For Model A320-216 airplanes, the requirements that correspond 
to AD 2014-20-04 were mandated by the MCAI via the RAAL. Although that 
RAAL requirement is still in effect, for continuity and clarity we have 
identified Model A320-216 airplanes in paragraph (c) of this AD; the 
requirements of paragraphs (g) through (i) in this proposed AD would 
therefore apply to those airplanes.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A320-92-1087, Revision 03, 
dated July 31, 2017; and A320-92-1119, dated July 28, 2017. This 
service information describes procedures for repetitive inspections for 
cracking of the 10VU rack fitting lugs, and repair of any cracking. 
These documents are distinct since they apply to airplanes in different 
configurations. 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

    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 the relevant information and determined the unsafe 
condition described previously is likely to exist or develop

[[Page 55301]]

on other products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would retain all of the requirements of AD 2016-
19-14 and expand the applicability to include additional airplanes. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously except as discussed under 
``Differences Between this Proposed AD and the MCAI or Service 
Information.'' This proposed AD also would require sending the 
inspection results to Airbus SAS.

Differences Between This Proposed AD and the MCAI or Service 
Information

    This proposed AD would not permit further flight if cracks are 
detected in any 10VU rack fitting lug, but the MCAI permits flight for 
a limited time if cracking is detected in a single 10VU rack fitting 
lug. We have determined that, because of the safety implications and 
consequences associated with that cracking, any cracked 10VU rack 
fitting lug must be repaired before further flight. This difference has 
been coordinated with the EASA.

Costs of Compliance

    We estimate that this proposed AD affects 461 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $85 per hour = $170...........................              $0             $170          $78,370
----------------------------------------------------------------------------------------------------------------

    We estimate that it would take about 1 work-hour per product to 
comply with the reporting requirement in this proposed AD. The average 
labor rate is $85 per hour. Based on these figures, we estimate the 
cost of reporting the inspection results on U.S. operators to be $85 
per product.
    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
83 work-hours x $85 per hour = $7,055.          $9,140          $16,195
------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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 and associated appliances 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,

[[Page 55302]]

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) 
2016-19-14, Amendment 39-18663 (81 FR 71602, October 18, 2016), and 
adding the following new AD:

Airbus SAS: Docket No. FAA-2018-0903; Product Identifier 2018-NM-
113-AD.

(a) Comments Due Date

    We must receive comments by December 20, 2018.

(b) Affected ADs

    This AD replaces AD 2016-19-14, Amendment 39-18663 (81 FR 71602, 
October 18, 2016) (``AD 2016-19-14'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (c)(4) of this AD, certificated in any 
category, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 92, Electric and 
Electronic Common Installation.

(e) Reason

    This AD was prompted by a report of cracks found during 
maintenance inspections on certain 10VU rack fitting lugs. We are 
issuing this AD to address reading difficulties of flight-critical 
information displayed to the flightcrew during a critical phase of 
flight, such as an approach or takeoff, which could result in loss 
of airplane control at an altitude insufficient for recovery.

(f) Compliance

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

(g) Definitions

    For the purpose of this AD, Group 1 airplanes are in a pre-
Airbus Modification 35869 configuration, and Group 2 airplanes are 
in a post-Airbus Modification 35869 configuration.

(h) Repetitive Inspections

    (1) For Group 1 airplanes: At the later of the times specified 
in table 1 to paragraph (h)(1) of this AD, and thereafter at 
intervals not to exceed 20,000 flight cycles or 40,000 flight hours, 
whichever occurs first, do a detailed inspection for cracking of the 
10VU rack fitting lugs, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-92-1087, Revision 03, 
dated July 31, 2017.

  Table 1 to Paragraph (h)(1) of This AD--Initial Inspection Compliance
                       Time for Group 1 Airplanes
------------------------------------------------------------------------
 
------------------------------------------------------------------------
            Compliance time (whichever occurs later, A or B)
------------------------------------------------------------------------
A.................................  Prior to exceeding 30,000 total
                                     flight cycles or 60,000 total
                                     flight hours.
B.................................  Within 24 months after November 22,
                                     2016 (the effective date of AD
                                     2016[dash]19[dash]14).
------------------------------------------------------------------------

    (2) For Group 2 airplanes: At the later of the times specified 
in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD, and thereafter at 
intervals not to exceed 20,000 flight cycles or 40,000 flight hours, 
whichever occurs first, do a detailed inspection for cracking of the 
10VU rack fitting lugs, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-92-1119, dated July 28, 
2017.
    (i) Prior to exceeding 30,000 total flight cycles or 60,000 
total flight hours, whichever occurs first.
    (ii) Within 30 days after the effective date of this AD.

(i) Repair

    If any crack is found during any inspection required by 
paragraph (h)(1) or (h)(2) of this AD: Before further flight, do a 
repair in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-92-1087, Revision 03, dated July 31, 2017 (for 
Group 1 airplanes); or Service Bulletin A320-92-1119, dated July 28, 
2017 (for Group 2 airplanes); as applicable. Repair of a 10VU rack 
fitting lug does not terminate the repetitive inspections required 
by paragraphs (h)(1) and (h)(2) of this AD.

(j) Reporting

    At the applicable time specified in paragraph (j)(1) or (j)(2) 
of this AD: Submit a report of findings (positive and negative) of 
each inspection required by paragraph (h) of this AD to Airbus 
Service Bulletin Reporting Online Application on Airbus World 
(https://w3.airbus.com/), or submit the results to Airbus in 
accordance with the instructions of Airbus Service Bulletin A320-92-
1087, Revision 03, dated July 31, 2017 (for Group 1 airplanes); or 
Service Bulletin A320-92-1119, dated July 28, 2017 (for Group 2 
airplanes); as applicable. Where Figure A-FAAAA, Sheet 02, of 
Appendix 01, ``Inspection Report,'' of Airbus Service Bulletin A320-
92-1087, Revision 03, dated July 31, 2017; and Figure A-FAAAA, Sheet 
02, of Appendix 01, ``Inspection Report,'' of Service Bulletin A320-
92-1119, dated July 28, 2017; specifies sending removed lugs to 
Airbus for investigation, this AD does not include that requirement.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 90 days after the effective date of 
this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (h)(1) and (i) of this AD if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-92-1087, Revision 02, dated November 25, 2014.

(l) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 1 hour per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(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]. 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.

[[Page 55303]]

    (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 Airworthiness Directive 2018-0131, dated June 19, 2018, 
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-2018-0903.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; internet 
http://www.airbus.com. 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.


    Issued in Des Moines, Washington, on October 22, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-23689 Filed 11-2-18; 8:45 am]
 BILLING CODE 4910-13-P