[Federal Register Volume 81, Number 232 (Friday, December 2, 2016)]
[Proposed Rules]
[Pages 86975-86977]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28621]
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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.
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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).
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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
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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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]
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