81 FR 86975 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 232 (December 2, 2016)

Page Range		86975-86977
FR Document		2016-28621
We propose to adopt a new airworthiness directive (AD) for all Airbus Model A321 series airplanes. This proposed AD was prompted by a determination from fatigue testing on the Model A321 airframe that cracks could develop on holes at certain fuselage frame locations. This proposed AD would require repetitive inspections for cracking on holes at certain fuselage frame locations, and repairs if necessary. We are proposing this AD to prevent the unsafe condition on these products.
Federal Register, Volume 81 Issue 232 (Friday, December 2, 2016)
[Federal Register Volume 81, Number 232 (Friday, December 2, 2016)]
[Proposed Rules]
[Pages 86975-86977]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-28621]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 232 / Friday, December 2, 2016 / 
Proposed Rules

[[Page 86975]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9431; Directorate Identifier 2016-NM-104-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A321 series airplanes. This proposed AD was prompted by a 
determination from fatigue testing on the Model A321 airframe that 
cracks could develop on holes at certain fuselage frame locations. This 
proposed AD would require repetitive inspections for cracking on holes 
at certain fuselage frame locations, and repairs if necessary. We are 
proposing this AD to prevent the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 17, 
2017.

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, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
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 information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

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-2016-
9431; 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 proposed AD, 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

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-2016-9431; 
Directorate Identifier 2016-NM-104-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0106, dated June 6, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A321 
series airplanes. The MCAI states:

    Following a new full scale fatigue test campaign on the A321 
airframe, in the context of the A321 extended service goal, it was 
identified that cracks could develop on holes at frame (FR) 35.2A 
between stringers (STR) 22 and STR 23 on right hand (RH) and left 
hand (LH) sides, also on aeroplanes operated in the context of 
design service goal.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage.
    Prompted by these findings, Airbus developed an inspection 
programme, published in Service Bulletin (SB) A320-53-1315 and SB 
A320-53-1316, each containing instructions for a different location.
    For the reasons described above, this [EASA] AD requires 
repetitive special detailed (rototest) inspections (SDI) of the 
affected holes [for cracking] and, depending on findings, 
accomplishment of a repair.
    This [EASA] AD is considered an interim action, pending 
development of a permanent solution.

    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-2016-
9431.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1315, dated January 13, 
2016; and Service Bulletin A320-53-1316, dated January 13, 2016. This 
service information describes procedures for doing a special detailed 
inspection for cracking at the tooling holes on FR 35.2A between STR 22 
and STR 23 and repairs. These documents are distinct since they apply 
to different sides of the airplane. 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

[[Page 86976]]

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 the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 175 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  12 work-hours x $85 per              $0   $1,020 per          $178,500 per
                                  hour = $1,020 per                         inspection cycle.   inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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.

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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2016-9431; Directorate Identifier 2016-NM-
104-AD.

(a) Comments Due Date

    We must receive comments by January 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes, certificated in any category, 
all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a determination from fatigue testing on 
the Model A321 airframe that cracks could develop on holes at 
certain fuselage frame locations. We are issuing this AD to detect 
and correct cracking at certain hole locations in the fuselage 
frame, which could result in reduced structural integrity of the 
airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Do a special detailed (rototest) inspection for 
cracking of the affected holes at frame 35.2A on the left-hand side 
and right-hand side between stringer 22 and stringer 23, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1315, dated January 13, 2016 (right-hand side); and 
Airbus Service Bulletin A320-53-1316, dated January 13, 2016 (left-
hand side). Repeat the inspection of the affected holes thereafter 
at intervals not to exceed 21,500 flight cycles or 43,100 flight 
hours, whichever occurs first.
    (1) Before exceeding 25,400 total flight cycles or 50,900 total 
flight hours since first flight of the airplane, whichever occurs 
first.
    (2) Within 3,300 flight cycles after the effective date of this 
AD.

(h) Repair

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). 
Although the service information specified in paragraph (g) of this 
AD specifies to contact Airbus for repair instructions, and 
specifies that action as ``RC'' (Required for Compliance), this AD 
requires repair as specified in this paragraph. Repair of an 
airplane as required by this paragraph does not constitute 
terminating action for the repetitive actions required by paragraph 
(g) of this AD, unless specified otherwise in the instructions 
provided by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19.

[[Page 86977]]

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 Branch, send it 
to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, 
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. 
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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) of this AD: 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0106, dated June 6, 2016, 
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-2016-9431.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on November 16, 2016.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-28621 Filed 12-1-16; 8:45 am]
BILLING CODE 4910-13-P
86975

Proposed Rules Federal Register
Vol. 81, No. 232

Friday, December 2, 2016

This section of the FEDERAL REGISTER Point Maurice Bellonte, 31707 Blagnac Discussion
contains notices to the public of the proposed Cedex, France; telephone +33 5 61 93 36 The European Aviation Safety Agency
issuance of rules and regulations. The 96; fax +33 5 61 93 44 51; email
purpose of these notices is to give interested (EASA), which is the Technical Agent
account.airworth-eas@airbus.com; for the Member States of the European
persons an opportunity to participate in the
Internet http://www.airbus.com. You Union, has issued EASA Airworthiness
rule making prior to the adoption of the final
rules. may view this referenced service Directive 2016–0106, dated June 6, 2016
information at the FAA, Transport (referred to after this as the Mandatory
Airplane Directorate, 1601 Lind Avenue Continuing Airworthiness Information,
DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on or ‘‘the MCAI’’), to correct an unsafe
the availability of this material at the condition on all Airbus Model A321
Federal Aviation Administration FAA, call 425–227–1221. series airplanes. The MCAI states:
14 CFR Part 39 Examining the AD Docket Following a new full scale fatigue test
campaign on the A321 airframe, in the
[Docket No. FAA–2016–9431; Directorate You may examine the AD docket on context of the A321 extended service goal, it
Identifier 2016–NM–104–AD] the Internet at http:// was identified that cracks could develop on
www.regulations.gov by searching for holes at frame (FR) 35.2A between stringers
RIN 2120–AA64 and locating Docket No. FAA–2016– (STR) 22 and STR 23 on right hand (RH) and
left hand (LH) sides, also on aeroplanes
9431; or in person at the Docket
Airworthiness Directives; Airbus operated in the context of design service goal.
Management Facility between 9 a.m. This condition, if not detected and
Airplanes
and 5 p.m., Monday through Friday, corrected, could reduce the structural
AGENCY: Federal Aviation except Federal holidays. The AD docket integrity of the fuselage.
Administration (FAA), DOT. contains this proposed AD, the Prompted by these findings, Airbus
ACTION: Notice of proposed rulemaking regulatory evaluation, any comments developed an inspection programme,
received, and other information. The published in Service Bulletin (SB) A320–53–
(NPRM). 1315 and SB A320–53–1316, each containing
street address for the Docket Operations
office (telephone 800–647–5527) is in instructions for a different location.
SUMMARY: We propose to adopt a new
For the reasons described above, this
airworthiness directive (AD) for all the ADDRESSES section. Comments will [EASA] AD requires repetitive special
Airbus Model A321 series airplanes. be available in the AD docket shortly detailed (rototest) inspections (SDI) of the
This proposed AD was prompted by a after receipt. affected holes [for cracking] and, depending
determination from fatigue testing on on findings, accomplishment of a repair.
FOR FURTHER INFORMATION CONTACT:
the Model A321 airframe that cracks This [EASA] AD is considered an interim
Sanjay Ralhan, Aerospace Engineer, action, pending development of a permanent
could develop on holes at certain
International Branch, ANM–116, solution.
fuselage frame locations. This proposed
Transport Airplane Directorate, FAA,
AD would require repetitive inspections You may examine the MCAI in the
1601 Lind Avenue SW., Renton, WA
for cracking on holes at certain fuselage AD docket on the Internet at http://
98057–3356; telephone 425–227–1405;
frame locations, and repairs if www.regulations.gov by searching for
fax 425–227–1149.
necessary. We are proposing this AD to and locating Docket No. FAA–2016–
prevent the unsafe condition on these SUPPLEMENTARY INFORMATION: 9431.
products.
Comments Invited Related Service Information Under 1
DATES: We must receive comments on CFR Part 51
this proposed AD by January 17, 2017. We invite you to send any written
Airbus has issued Service Bulletin
ADDRESSES: You may send comments, relevant data, views, or arguments about
A320–53–1315, dated January 13, 2016;
using the procedures found in 14 CFR this proposed AD. Send your comments
and Service Bulletin A320–53–1316,
11.43 and 11.45, by any of the following to an address listed under the
dated January 13, 2016. This service
methods: ADDRESSES section. Include ‘‘Docket No.
information describes procedures for
• Federal eRulemaking Portal: Go to FAA–2016–9431; Directorate Identifier
doing a special detailed inspection for
http://www.regulations.gov. Follow the 2016–NM–104–AD’’ at the beginning of
cracking at the tooling holes on FR
instructions for submitting comments. your comments. We specifically invite
35.2A between STR 22 and STR 23 and
• Fax: 202–493–2251. comments on the overall regulatory,
repairs. These documents are distinct
• Mail: U.S. Department of economic, environmental, and energy
since they apply to different sides of the
Transportation, Docket Operations, M– aspects of this proposed AD. We will
airplane. This service information is
30, West Building Ground Floor, Room consider all comments received by the
reasonably available because the
W12–140, 1200 New Jersey Avenue SE., closing date and may amend this
interested parties have access to it
jstallworth on DSK7TPTVN1PROD with PROPOSALS

Washington, DC 20590. proposed AD based on those comments.
through their normal course of business
• Hand Delivery: Deliver to Mail We will post all comments we or by the means identified in the
address above between 9 a.m. and 5 receive, without change, to http:// ADDRESSES section.
p.m., Monday through Friday, except www.regulations.gov, including any
Federal holidays. personal information you provide. We FAA’s Determination and Requirements
For service information identified in will also post a report summarizing each of This Proposed AD
this NPRM, contact Airbus, substantive verbal contact we receive This product has been approved by
Airworthiness Office—EIAS, 1 Rond about this proposed AD. the aviation authority of another

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86976 Federal Register / Vol. 81, No. 232 / Friday, December 2, 2016 / Proposed Rules

country, and is approved for operation referenced above. We are proposing this Costs of Compliance
in the United States. Pursuant to our AD because we evaluated all pertinent
bilateral agreement with the State of information and determined an unsafe We estimate that this proposed AD
Design Authority, we have been notified condition exists and is likely to exist or affects 175 airplanes of U.S. registry.
of the unsafe condition described in the develop on other products of the same We estimate the following costs to
MCAI and service information type design. comply with this proposed AD:

ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection .... 12 work-hours × $85 per hour = $1,020 per inspec- $0 $1,020 per inspection $178,500 per inspection
tion cycle. cycle. cycle.

We have received no definitive data under the criteria of the Regulatory (f) Compliance
that would enable us to provide cost Flexibility Act. Comply with this AD within the
estimates for the on-condition actions compliance times specified, unless already
specified in this proposed AD. List of Subjects in 14 CFR Part 39 done.

Authority for This Rulemaking Air transportation, Aircraft, Aviation (g) Repetitive Inspections
safety, Incorporation by reference, At the later of the times specified in
Title 49 of the United States Code Safety. paragraphs (g)(1) and (g)(2) of this AD: Do a
specifies the FAA’s authority to issue special detailed (rototest) inspection for
rules on aviation safety. Subtitle I, The Proposed Amendment cracking of the affected holes at frame 35.2A
section 106, describes the authority of on the left-hand side and right-hand side
the FAA Administrator. ‘‘Subtitle VII: Accordingly, under the authority between stringer 22 and stringer 23, in
Aviation Programs,’’ describes in more delegated to me by the Administrator, accordance with the Accomplishment
detail the scope of the Agency’s the FAA proposes to amend 14 CFR part Instructions of Airbus Service Bulletin A320–
authority. 39 as follows: 53–1315, dated January 13, 2016 (right-hand
side); and Airbus Service Bulletin A320–53–
We are issuing this rulemaking under PART 39—AIRWORTHINESS 1316, dated January 13, 2016 (left-hand side).
the authority described in ‘‘Subtitle VII, DIRECTIVES Repeat the inspection of the affected holes
Part A, Subpart III, Section 44701: thereafter at intervals not to exceed 21,500
General requirements.’’ Under that flight cycles or 43,100 flight hours,
■ 1. The authority citation for part 39 whichever occurs first.
section, Congress charges the FAA with
continues to read as follows: (1) Before exceeding 25,400 total flight
promoting safe flight of civil aircraft in
Authority: 49 U.S.C. 106(g), 40113, 44701. cycles or 50,900 total flight hours since first
air commerce by prescribing regulations
flight of the airplane, whichever occurs first.
for practices, methods, and procedures (2) Within 3,300 flight cycles after the
§ 39.13 [Amended]
the Administrator finds necessary for effective date of this AD.
safety in air commerce. This regulation ■ 2. The FAA amends § 39.13 by adding
is within the scope of that authority the following new airworthiness (h) Repair
because it addresses an unsafe condition directive (AD): If any crack is found during any inspection
that is likely to exist or develop on required by paragraph (g) of this AD: Before
Airbus: Docket No. FAA–2016–9431; further flight, repair using a method
products identified in this rulemaking Directorate Identifier 2016–NM–104–AD. approved by the Manager, International
action. Branch, ANM–116, Transport Airplane
(a) Comments Due Date
Regulatory Findings Directorate, FAA; or the European Aviation
We must receive comments by January 17, Safety Agency (EASA); or Airbus’s EASA
We determined that this proposed AD 2017. Design Organization Approval (DOA).
would not have federalism implications Although the service information specified in
(b) Affected ADs paragraph (g) of this AD specifies to contact
under Executive Order 13132. This
proposed AD would not have a None. Airbus for repair instructions, and specifies
substantial direct effect on the States, on that action as ‘‘RC’’ (Required for
(c) Applicability Compliance), this AD requires repair as
the relationship between the national specified in this paragraph. Repair of an
This AD applies to Airbus Model A321–
Government and the States, or on the 111, –112, –131, –211, –212, –213, –231, and airplane as required by this paragraph does
distribution of power and –232 airplanes, certificated in any category, not constitute terminating action for the
responsibilities among the various all manufacturer serial numbers. repetitive actions required by paragraph (g) of
levels of government. this AD, unless specified otherwise in the
For the reasons discussed above, I (d) Subject instructions provided by the Manager,
certify this proposed regulation: Air Transport Association (ATA) of International Branch, ANM–116, Transport
America Code 53, Fuselage. Airplane Directorate, FAA; or EASA; or
1. Is not a ‘‘significant regulatory Airbus’s EASA DOA.
action’’ under Executive Order 12866; (e) Reason
jstallworth on DSK7TPTVN1PROD with PROPOSALS

2. Is not a ‘‘significant rule’’ under the (i) Other FAA AD Provisions
This AD was prompted by a determination
DOT Regulatory Policies and Procedures The following provisions also apply to this
from fatigue testing on the Model A321 AD:
(44 FR 11034, February 26, 1979); airframe that cracks could develop on holes (1) Alternative Methods of Compliance
3. Will not affect intrastate aviation in at certain fuselage frame locations. We are (AMOCs): The Manager, International
Alaska; and issuing this AD to detect and correct cracking Branch, ANM–116, Transport Airplane
4. Will not have a significant at certain hole locations in the fuselage Directorate, FAA, has the authority to
economic impact, positive or negative, frame, which could result in reduced approve AMOCs for this AD, if requested
on a substantial number of small entities structural integrity of the airplane. using the procedures found in 14 CFR 39.19.

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Federal Register / Vol. 81, No. 232 / Friday, December 2, 2016 / Proposed Rules 86977

In accordance with 14 CFR 39.19, send your DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
request to your principal inspector or local and locating Docket No. FAA–2016–
Flight Standards District Office, as Federal Aviation Administration 9394.
appropriate. If sending information directly
to the International Branch, send it to ATTN: 14 CFR Part 39 Examining the AD Docket
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport [Docket No. FAA–2016–9394; Directorate You may examine the AD docket on
Airplane Directorate, FAA, 1601 Lind Identifier 2016–NM–162–AD] the Internet at http://
Avenue SW., Renton, WA 98057–3356; RIN 2120–AA64
www.regulations.gov by searching for
telephone 425–227–1405; fax 425–227–1149. and locating Docket No. FAA–2016–
Information may be emailed to: 9-ANM-116- Airworthiness Directives; The Boeing 9394; or in person at the Docket
AMOC-REQUESTS@faa.gov. Before using Company Airplanes Management Facility between 9 a.m.
any approved AMOC, notify your appropriate and 5 p.m., Monday through Friday,
principal inspector, or lacking a principal AGENCY: Federal Aviation except Federal holidays. The AD docket
inspector, the manager of the local flight Administration (FAA), DOT. contains this proposed AD, the
standards district office/certificate holding ACTION: Notice of proposed rulemaking regulatory evaluation, any comments
district office. (NPRM). received, and other information. The
(2) Contacting the Manufacturer: For any street address for the Docket Office
requirement in this AD to obtain corrective SUMMARY: We propose to adopt a new (phone: 800–647–5527) is in the
actions from a manufacturer, the action must airworthiness directive (AD) for all The ADDRESSES section. Comments will be
be accomplished using a method approved Boeing Company Model 747–400, 747–
by the Manager, International Branch, ANM– available in the AD docket shortly after
400D, and 747–400F airplanes. This receipt.
116, Transport Airplane Directorate, FAA; or proposed AD was prompted by a report
EASA; or Airbus’s EASA DOA. If approved FOR FURTHER INFORMATION CONTACT:
of a 13.4-inch crack in the left wing
by the DOA, the approval must include the Nathan Weigand, Aerospace Engineer,
front spar web inboard of pylon number
DOA-authorized signature. Airframe Branch, ANM–120S, FAA,
(3) Required for Compliance (RC): Except
2 between front spar station inboard
(FSSI) 655.75 and FSSI 660, found Seattle Aircraft Certification Office
as required by paragraph (h) of this AD: If
any service information contains procedures following a fuel leak. This proposed AD (ACO), 1601 Lind Avenue SW., Renton,
or tests that are identified as RC, those would require repetitive detailed, WA 98057–3356; phone: 425–917–6428;
procedures and tests must be done to comply ultrasonic, and high frequency eddy fax: 425–917–6590; email:
with this AD; any procedures or tests that are current inspections for cracking of the nathan.p.weigand@faa.gov.
not identified as RC are recommended. Those front spar web between FSSI 628 and SUPPLEMENTARY INFORMATION:
procedures and tests that are not identified FSSI 713, and repairs if necessary. We
as RC may be deviated from using accepted are proposing this AD to address the Comments Invited
methods in accordance with the operator’s unsafe condition on these products.
maintenance or inspection program without We invite you to send any written
DATES: We must receive comments on
obtaining approval of an AMOC, provided relevant data, views, or arguments about
the procedures and tests identified as RC can this proposed AD by January 17, 2017.
this proposal. Send your comments to
be done and the airplane can be put back in ADDRESSES: You may send comments, an address listed under the ADDRESSES
an airworthy condition. Any substitutions or using the procedures found in 14 CFR section. Include ‘‘Docket No. FAA–
changes to procedures or tests identified as 11.43 and 11.45, by any of the following 2016–9394; Directorate Identifier 2016–
RC require approval of an AMOC. methods: NM–162–AD’’ at the beginning of your
(j) Related Information • Federal eRulemaking Portal: Go to comments. We specifically invite
http://www.regulations.gov. Follow the comments on the overall regulatory,
(1) Refer to Mandatory Continuing instructions for submitting comments.
Airworthiness Information (MCAI) EASA economic, environmental, and energy
• Fax: 202–493–2251. aspects of this proposed AD. We will
Airworthiness Directive 2016–0106, dated
June 6, 2016, for related information. This
• Mail: U.S. Department of consider all comments received by the
MCAI may be found in the AD docket on the Transportation, Docket Operations, closing date and may amend this
Internet at http://www.regulations.gov by M–30, West Building Ground Floor, proposed AD because of those
searching for and locating Docket No. FAA– Room W12–140, 1200 New Jersey comments.
2016–9431. Avenue SE., Washington, DC 20590.
(2) For service information identified in • Hand Delivery: Deliver to Mail We will post all comments we
this AD, contact Airbus, Airworthiness address above between 9 a.m. and 5 receive, without change, to http://
Office—EIAS, 1 Rond Point Maurice p.m., Monday through Friday, except www.regulations.gov, including any
Bellonte, 31707 Blagnac Cedex, France; Federal holidays. personal information you provide. We
telephone +33 5 61 93 36 96; fax +33 5 61 For service information identified in will also post a report summarizing each
93 44 51; email account.airworth-eas@ this NPRM, contact Boeing Commercial substantive verbal contact we receive
airbus.com; Internet http://www.airbus.com. Airplanes, Attention: Contractual & Data about this proposed AD.
You may view this service information at the Services (C&DS), 2600 Westminster
FAA, Transport Airplane Directorate, 1601 Discussion
Blvd., MC 110–SK57, Seal Beach, CA
Lind Avenue SW., Renton, WA. For
information on the availability of this
90740; telephone 562–797–1717; We have received a report indicating
Internet https:// that a fuel leak in one airplane led to the
jstallworth on DSK7TPTVN1PROD with PROPOSALS

material at the FAA, call 425–227–1221.
www.myboeingfleet.com. You may view discovery of a 13.4-inch crack in the left
Issued in Renton, Washington, on this referenced service information at wing front spar web inboard of pylon
November 16, 2016. the FAA, Transport Airplane number 2 between FSSI 655.75 and
Phil Forde, Directorate, 1601 Lind Avenue SW., FSSI 660. The airplane had accumulated
Acting Manager, Transport Airplane Renton, WA. For information on the 13,909 total flight cycles and 107,151
Directorate, Aircraft Certification Service. availability of this material at the FAA, total flight hours. This condition, if not
[FR Doc. 2016–28621 Filed 12–1–16; 8:45 am] call 425–227–1221. It is also available corrected, could result in fuel leaks and
BILLING CODE 4910–13–P on the internet at http:// a consequent fire.

VerDate Sep<11>2014 15:02 Dec 01, 2016 Jkt 241001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\02DEP1.SGM 02DEP1
Document Created: 2018-02-14 09:02:12
Document Modified: 2018-02-14 09:02:12
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 January 17, 2017.
Contact		Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149.
FR Citation		81 FR 86975
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 86975 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 232 (December 2, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
