[Federal Register Volume 82, Number 204 (Tuesday, October 24, 2017)]
[Proposed Rules]
[Pages 49146-49149]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-23014]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-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 A318-111 and -112 airplanes; Model A319-111, -112, -113, -
114, and -115 airplanes; Model A320-211, -212, -214, and -216
airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes.
This proposed AD was prompted by a review of maintenance instructions
for a blend repair of the snout diameter of the main beam assembly of
the forward engine mount that would create an excessive gap between the
bearing mono-ball and the snout. This proposed AD would require
modifying the main beam assembly of the forward engine mount. We are
proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by December 8,
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 service information at the FAA,
Transport Standards Branch, 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-2017-
1020; 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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, 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 proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-1020;
Product Identifier 2017-NM-114-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM 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 NPRM.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0132, dated July 27, 2017 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus Model A318-111 and -112 airplanes;
Model A319-111, -112,
[[Page 49147]]
-113, -114, and -115 airplanes; Model A320-211, -212, -214, and -216
airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes.
The MCAI states:
A review of maintenance instructions revealed that the Goodrich
Aerospace CFM56-5B, Forward Engine Mount Component Maintenance
Manual (CMM) 71-21-08, revision (rev.) 1 up to 46 (inclusive),
repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides
instructions to blend the wear on the forward engine mount assembly,
Part Number (P/N) 642-2000-9, 642-2000-13, or 642-2000-25, creating
an excessive gap between the bearing mono-ball and the snout of the
forward engine mount main beam assembly, P/N 642-2006-501, or P/N
642-2006-503.
This condition, if not detected and corrected, could lead to in-
flight failure of a forward engine mount and consequent detachment
of an engine, possibly resulting in reduced control of the aeroplane
and injury to persons on the ground.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-71-1065 and SB A320-71-1066, and Goodrich
Aerospace issued SB RA32071-159, providing instructions for an in-
shop inspection(s) for the main beam snout and, depending on
findings, applicable corrective action(s) and re-identification.
For the reason described above, this [EASA] AD requires
replacement of the affected forward engine mount main beam
assemblies. As the same main beam assemblies are certified for
CFM56-5A engine installation, this [EASA] AD also applies to
aeroplanes with that engine.
Required actions include modifying the main beam assembly of the
forward engine mount. The modification includes repairing, replacing,
or reworking the main beam assembly. 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-2017-1020.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-71-1065, Revision 01, dated
July 28, 2017. This service information describes procedures for
modifying the main beam assembly of the forward engine mount. The
modification includes, among other things, repair or replacement of the
main beam assembly.
Airbus has also issued Service Bulletin A320-71-1066, dated
December 1, 2016. This service information describes procedures for
modifying the main beam assembly of the forward engine mount. The
modification includes, among other things, rework of the main beam
assembly.
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.
Costs of Compliance
We estimate that this proposed AD affects 500 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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Modification..................... Up to 76 work-hours $778 Up to $7,238....... Up to $3,619,000.
x $85 per hour =
$6,460.
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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.
[[Page 49148]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD.
(a) Comments Due Date
We must receive comments by December 8, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318-111 and -112 airplanes;
Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-
211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211,
-212, and -213 airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by a review of maintenance instructions for
a blend repair of the diameter of the snout of the main beam
assembly of the forward engine mount that would create an excessive
gap between the bearing mono-ball and the snout. We are issuing this
AD to prevent in-flight failure of a forward engine mount, and
consequent detachment of an engine, which could result in reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definition of Affected Parts
For the purposes of this AD: An ``affected main beam'' is any
main beam assembly of the forward engine mount, part number (P/N)
642-2006-501 or P/N 642-2006-503, identified in paragraph (g)(1) or
(g)(2) of this AD.
(1) Any part for which no maintenance records are available to
confirm the part has never been repaired.
(2) Any part that was repaired as specified in the instructions
of Goodrich Aerospace component maintenance manual (CMM) 71-21-08,
Revision 1 through 46, repair 10, except for parts identified in
paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
(i) Any part on which a qualifying inspection identified in
paragraph (h) of this AD has been done and there were no findings
(the inspection was passed).
(ii) Any part on which a qualifying inspection identified in
paragraph (h) of this AD has been done and that part has been
repaired as specified in the instructions of Goodrich Aerospace
Service Bulletin RA32071-159.
(iii) Any part that has been repaired in accordance with other
instructions 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).
(h) Definition of Qualifying Inspection
For the purposes of this AD: ``A qualifying inspection'' is an
inspection done as specified in the instructions of Goodrich
Aerospace Service Bulletin RA32071-159; or for CFM56-5B engines, an
inspection done as specified in the instructions of Goodrich
Aerospace CMM 71-21-08, Revision 47, repair 10; or for CFM56-5A
engines, an inspection done as specified in the instructions of
Goodrich Aerospace CMM 71-21-06, Revision 59, repair 21.
(i) Definition of Airplane Groups
For the purposes of this AD: ``Group 1 airplanes'' are airplanes
on which an affected main beam has been installed as of the
effective date of this AD. ``Group 2 airplanes'' are airplanes on
which an affected main beam has not been installed as of the
effective date of this AD; this includes airplanes with an original
certificate of airworthiness or original export certificate of
airworthiness that was issued after the effective date of this AD.
(j) Modification of Affected Main Beam Assemblies
For Group 1 airplanes as identified in paragraph (i) of this AD:
At the earliest of the compliance times specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, modify each affected main
beam identified in paragraph (g) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-71-1065,
Revision 01, dated July 28, 2017; and Airbus Service Bulletin A320-
71-1066, dated December 1, 2016; as applicable, except as required
by paragraph (k) of this AD.
(1) Within 48 months after the effective date of this AD.
(2) Within 10,000 flight cycles after the effective date of this
AD.
(3) Within 15,000 flight hours after the effective date of this
AD.
(k) Exception to Service Information
Where Airbus Service Bulletin A320-71-1065, Revision 01, dated
July 28, 2017, specifies to contact a manufacturer for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (n)(2) of this
AD.
(l) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (j) of this AD involving Airbus Service Bulletin A320-71-
1065, Revision 01, dated July 28, 2017, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A320-71-1065, dated December 1, 2016.
(m) Parts Installation Prohibition
As of the effective date of this AD, no person may install an
affected main beam identified in paragraph (g) of this AD or a
forward engine mount assembly equipped with an affected main beam
identified in paragraph (g) of this AD, on any airplane.
(n) Other FAA AD Provisions
The following provisions also apply to this AD:
(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 manager of the International Section, send it to the
attention of the person identified in paragraph (o)(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.
(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
Section, Transport Standards Branch, 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 (k) 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.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0132, dated July 27, 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-2017-1020.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-1405; fax 425-227-1149.
(3) 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 Standards Branch, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
[[Page 49149]]
Issued in Renton, Washington, on October 17, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-23014 Filed 10-23-17; 8:45 am]
BILLING CODE 4910-13-P