80 FR 8575 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 32 (February 18, 2015)

Page Range		8575-8577
FR Document		2015-02683

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A310-203 airplanes. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD was prompted by reports that side link clevis bolts of the front engine mount do not meet the Design Service Goal (DSG) requirements on airplanes equipped with General Electric Company CF6-80A3 engines. This proposed AD would require repetitive replacement of all side link clevis engine mount bolts. We are proposing this AD to prevent failure of the front engine mount, and consequent possible departure of the engine.

Federal Register, Volume 80 Issue 32 (Wednesday, February 18, 2015)

[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Proposed Rules]
[Pages 8575-8577]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-02683]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0086; Directorate Identifier 2014-NM-191-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 A310-203 airplanes. This proposed AD is intended to 
complete certain mandated programs intended to support the airplane 
reaching its limit of validity (LOV) of the engineering data that 
support the established structural maintenance program. This proposed 
AD was prompted by reports that side link clevis bolts of the front 
engine mount do not meet the Design Service Goal (DSG) requirements on 
airplanes equipped with General Electric Company CF6-80A3 engines. This 
proposed AD would require repetitive replacement of all side link 
clevis engine mount bolts. We are proposing this AD to prevent failure 
of the front engine mount, and consequent possible departure of the 
engine.

DATES: We must receive comments on this proposed AD by April 6, 2015.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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-2015-
0086; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227-
2125; 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-2015-0086; 
Directorate Identifier 2014-NM-191-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

    As described in FAA Advisory Circular 120 104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a LOV of the 
engineering data that support the structural maintenance program under 
14 CFR 26.21. This proposed AD is the result of an assessment of the 
previously established programs by Airbus during the process of 
establishing the LOV for Airbus Model A310-203 airplanes. The actions 
specified in this proposed AD are necessary to complete certain 
programs to ensure the continued airworthiness of aging airplane 
structure and to support an airplane reaching its LOV.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0191, dated August 29, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A310-203 airplanes. The MCAI states:

    During fatigue analysis performed in the scope of the Extended 
Service Goal, taking into account the certification loads and the 
new lift-off loads, Airbus determined that side link clevis engine 
mount bolts do not meet the Design Service Goal (DSG) requirements 
on aeroplanes equipped with CF6-80A3 engines.
    This condition, if not corrected, could lead to failure of the 
front engine mount, possibly resulting in-flight separation of the 
engine from the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A310-71-2038 to introduce a life limit on the 
side link clevis engine mount bolts.
    For the reason described above, this [EASA] AD requires 
implementation of the new life limit and replacement of all side 
link clevis engine mount bolts that have exceeded the new limit.


[[Page 8576]]


    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-2015-
0086.

Relevant Service Information Under 1 CFR Part 51

    Airbus has issued Mandatory Service Bulletin A310-71-2038, 
including Appendices 01 and 02, dated April 8, 2014. The service 
information describes procedures for replacement of all side link 
clevis bolts on the CF6-80A3 front engine mount and subsequent re-
identification of the newly installed bolts with a cross (to 
differentiate them from the old ones). The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI. This service information is reasonably 
available; see ADDRESSES for ways to access this service information.

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 the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 13 airplanes of U.S. 
registry.
    We also estimate that it would take about 142 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $2,900 per product. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $194,610, or $14,970 per 
product.

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-2015-0086; Directorate Identifier 2014-NM-
191-AD.

(a) Comments Due Date

    We must receive comments by April 6, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A310-203 airplanes, certificated 
in any category, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by reports that side link clevis bolts of 
the front engine mount do not meet the Design Service Goal (DSG) 
requirements on airplanes equipped with General Electric Company 
CF6-80A3 engines. We are issuing this AD to prevent failure of the 
front engine mount, and consequent possible departure of the engine.

(f) Compliance

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

(g) Repetitive Bolt Replacement

    Within 18 months after the effective date of this AD, replace 
the side link clevis bolts, nuts, and bushings of the front engine 
mount on both engines, and re-identify the new installed bolts with 
a cross (to differentiate them from the old ones), in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A310-71-2038, including Appendices 01 and 02, dated April 
8, 2014. Repeat the replacement thereafter at intervals not to 
exceed 29 years.

(h) 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. 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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; 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. The 
AMOC approval letter must specifically reference this AD.
    (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 the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

[[Page 8577]]

(i) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0191, dated August 29, 
2014, 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-2015-0086.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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 January 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02683 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 8575

Aviation Safety Agency Airworthiness 11.43 and 11.45, by any of the following comments on the overall regulatory,
Directive 2014–0164, dated July 11, 2014, for methods: economic, environmental, and energy
related information. This MCAI may be • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
found in the AD docket on the Internet at http://www.regulations.gov. Follow the consider all comments received by the
http://www.regulations.gov by searching for
and locating Docket No. FAA–2015–0243.
instructions for submitting comments. closing date and may amend this
(2) For service information identified in • Fax: 202–493–2251. proposed AD based on those comments.
this AD, contact Airbus SAS, Airworthiness • Mail: U.S. Department of We will post all comments we
Office—EAW, 1 Rond Point Maurice Transportation, Docket Operations, M– receive, without change, to http://
Bellonte, 31707 Blagnac Cedex, France; 30, West Building Ground Floor, Room www.regulations.gov, including any
telephone +33 5 61 93 36 96; fax +33 5 61 W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
93 44 51; email account.airworth-eas@ Washington, DC 20590. will also post a report summarizing each
airbus.com; Internet http://www.airbus.com. • Hand Delivery: U.S. Department of substantive verbal contact we receive
You may view this service information at the Transportation, Docket Operations, M–
FAA, Transport Airplane Directorate, 1601 about this proposed AD.
Lind Avenue SW., Renton, WA. For
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE., Discussion
information on the availability of this
material at the FAA, call 425–227–1221. Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except As described in FAA Advisory
Issued in Renton, Washington, on February
Federal holidays. Circular 120 104 (http://www.faa.gov/
2, 2015. documentLibrary/media/Advisory_
For service information identified in
Dionne Palermo,
this proposed AD, contact Airbus SAS, Circular/120-104.pdf), several programs
Acting Manager, Transport Airplane Airworthiness Office—EAW, 1 Rond have been developed to support
Directorate, Aircraft Certification Service.
Point Maurice Bellonte, 31707 Blagnac initiatives that will ensure the
[FR Doc. 2015–02922 Filed 2–17–15; 8:45 am]
Cedex, France; telephone +33 5 61 93 36 continued airworthiness of aging
BILLING CODE 4910–13–P 96; fax +33 5 61 93 44 51; email airplane structure. The last element of
account.airworth-eas@airbus.com; those initiatives is the requirement to
Internet http://www.airbus.com. You establish a LOV of the engineering data
DEPARTMENT OF TRANSPORTATION
may view this referenced service that support the structural maintenance
information at the FAA, Transport program under 14 CFR 26.21. This
Federal Aviation Administration proposed AD is the result of an
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on assessment of the previously established
14 CFR Part 39 programs by Airbus during the process
the availability of this material at the
[Docket No. FAA–2015–0086; Directorate FAA, call 425–227–1221. of establishing the LOV for Airbus
Identifier 2014–NM–191–AD] Model A310–203 airplanes. The actions
Examining the AD Docket specified in this proposed AD are
RIN 2120–AA64
You may examine the AD docket on necessary to complete certain programs
the Internet at http:// to ensure the continued airworthiness of
Airworthiness Directives; Airbus aging airplane structure and to support
Airplanes www.regulations.gov by searching for
and locating Docket No. FAA–2015– an airplane reaching its LOV.
AGENCY: Federal Aviation 0086; or in person at the Docket The European Aviation Safety Agency
Administration (FAA), DOT. Management Facility between 9 a.m. (EASA), which is the Technical Agent
ACTION: Notice of proposed rulemaking and 5 p.m., Monday through Friday, for the Member States of the European
(NPRM). except Federal holidays. The AD docket Union, has issued EASA Airworthiness
contains this proposed AD, the Directive 2014–0191, dated August 29,
SUMMARY: We propose to adopt a new regulatory evaluation, any comments 2014 (referred to after this as the
airworthiness directive (AD) for all received, and other information. The Mandatory Continuing Airworthiness
Airbus Model A310–203 airplanes. This street address for the Docket Operations Information, or ‘‘the MCAI’’), to correct
proposed AD is intended to complete office (telephone 800–647–5527) is in an unsafe condition for all Airbus
certain mandated programs intended to the ADDRESSES section. Comments will Model A310–203 airplanes. The MCAI
support the airplane reaching its limit of be available in the AD docket shortly states:
validity (LOV) of the engineering data after receipt. During fatigue analysis performed in the
that support the established structural FOR FURTHER INFORMATION CONTACT: Dan scope of the Extended Service Goal, taking
maintenance program. This proposed Rodina, Aerospace Engineer, into account the certification loads and the
AD was prompted by reports that side International Branch, ANM–116, new lift-off loads, Airbus determined that
link clevis bolts of the front engine Transport Airplane Directorate, FAA, side link clevis engine mount bolts do not
mount do not meet the Design Service meet the Design Service Goal (DSG)
1601 Lind Avenue SW., Renton,
Goal (DSG) requirements on airplanes requirements on aeroplanes equipped with
Washington 98057–3356; telephone CF6–80A3 engines.
equipped with General Electric 425–227–2125; fax 425–227–1149.
Company CF6–80A3 engines. This This condition, if not corrected, could lead
SUPPLEMENTARY INFORMATION: to failure of the front engine mount, possibly
proposed AD would require repetitive resulting in-flight separation of the engine
replacement of all side link clevis Comments Invited from the aeroplane.
mstockstill on DSK4VPTVN1PROD with PROPOSALS

engine mount bolts. We are proposing We invite you to send any written To address this potential unsafe condition,
this AD to prevent failure of the front relevant data, views, or arguments about Airbus issued Service Bulletin (SB) A310–
engine mount, and consequent possible this proposed AD. Send your comments 71–2038 to introduce a life limit on the side
departure of the engine. link clevis engine mount bolts.
to an address listed under the For the reason described above, this
DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. [EASA] AD requires implementation of the
this proposed AD by April 6, 2015. FAA–2015–0086; Directorate Identifier new life limit and replacement of all side
ADDRESSES: You may send comments, 2014–NM–191–AD’’ at the beginning of link clevis engine mount bolts that have
using the procedures found in 14 CFR your comments. We specifically invite exceeded the new limit.

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8576 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules

You may examine the MCAI in the section, Congress charges the FAA with (c) Applicability
AD docket on the Internet at http:// promoting safe flight of civil aircraft in This AD applies to Airbus Model A310–
www.regulations.gov by searching for air commerce by prescribing regulations 203 airplanes, certificated in any category, all
and locating Docket No. FAA–2015– for practices, methods, and procedures manufacturer serial numbers.
0086. the Administrator finds necessary for (d) Subject
safety in air commerce. This regulation
Relevant Service Information Under 1 Air Transport Association (ATA) of
is within the scope of that authority
CFR Part 51 America Code 71, Powerplant.
because it addresses an unsafe condition
Airbus has issued Mandatory Service that is likely to exist or develop on (e) Reason
Bulletin A310–71–2038, including products identified in this rulemaking This AD was prompted by reports that side
Appendices 01 and 02, dated April 8, action. link clevis bolts of the front engine mount do
2014. The service information describes not meet the Design Service Goal (DSG)
procedures for replacement of all side Regulatory Findings requirements on airplanes equipped with
link clevis bolts on the CF6–80A3 front We determined that this proposed AD General Electric Company CF6–80A3
engine mount and subsequent re- would not have federalism implications engines. We are issuing this AD to prevent
identification of the newly installed under Executive Order 13132. This failure of the front engine mount, and
bolts with a cross (to differentiate them proposed AD would not have a consequent possible departure of the engine.
from the old ones). The actions substantial direct effect on the States, on (f) Compliance
described in this service information are the relationship between the national Comply with this AD within the
intended to correct the unsafe condition Government and the States, or on the compliance times specified, unless already
identified in the MCAI. This service distribution of power and done.
information is reasonably available; see responsibilities among the various
ADDRESSES for ways to access this (g) Repetitive Bolt Replacement
levels of government.
service information. For the reasons discussed above, I Within 18 months after the effective date
certify this proposed regulation: of this AD, replace the side link clevis bolts,
FAA’s Determination and Requirements nuts, and bushings of the front engine mount
of This Proposed AD 1. Is not a ‘‘significant regulatory on both engines, and re-identify the new
action’’ under Executive Order 12866; installed bolts with a cross (to differentiate
This product has been approved by 2. Is not a ‘‘significant rule’’ under the
the aviation authority of another them from the old ones), in accordance with
DOT Regulatory Policies and Procedures the Accomplishment Instructions of Airbus
country, and is approved for operation (44 FR 11034, February 26, 1979); Mandatory Service Bulletin A310–71–2038,
in the United States. Pursuant to our including Appendices 01 and 02, dated April
3. Will not affect intrastate aviation in
bilateral agreement with the State of 8, 2014. Repeat the replacement thereafter at
Alaska; and
Design Authority, we have been notified intervals not to exceed 29 years.
4. Will not have a significant
of the unsafe condition described in the
economic impact, positive or negative, (h) Other FAA AD Provisions
MCAI and service information
on a substantial number of small entities The following provisions also apply to this
referenced above. We are proposing this
under the criteria of the Regulatory AD:
AD because we evaluated all pertinent
Flexibility Act. (1) Alternative Methods of Compliance
information and determined an unsafe
(AMOCs): The Manager, International
condition exists and is likely to exist or List of Subjects in 14 CFR Part 39 Branch, ANM–116, Transport Airplane
develop on other products of the same Directorate, FAA, has the authority to
Air transportation, Aircraft, Aviation
type design. approve AMOCs for this AD, if requested
safety, Incorporation by reference,
Costs of Compliance Safety. using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
We estimate that this proposed AD The Proposed Amendment request to your principal inspector or local
affects 13 airplanes of U.S. registry. Flight Standards District Office, as
We also estimate that it would take Accordingly, under the authority appropriate. If sending information directly
about 142 work-hours per product to delegated to me by the Administrator, to the International Branch, send it to ATTN:
comply with the basic requirements of the FAA proposes to amend 14 CFR part Dan Rodina, Aerospace Engineer,
this proposed AD. The average labor 39 as follows: International Branch, ANM–116, Transport
rate is $85 per work-hour. Required Airplane Directorate, FAA, 1601 Lind
PART 39—AIRWORTHINESS Avenue SW., Renton, WA 98057–3356;
parts would cost about $2,900 per
DIRECTIVES telephone 425–227–2125; fax 425–227–1149.
product. Based on these figures, we Information may be emailed to: 9-ANM-116-
estimate the cost of this proposed AD on ■ 1. The authority citation for part 39 AMOC-REQUESTS@faa.gov. Before using
U.S. operators to be $194,610, or continues to read as follows: any approved AMOC, notify your appropriate
$14,970 per product. principal inspector, or lacking a principal
Authority: 49 U.S.C. 106(g), 40113, 44701. inspector, the manager of the local flight
Authority for This Rulemaking standards district office/certificate holding
§ 39.13 [Amended]
Title 49 of the United States Code district office. The AMOC approval letter
specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by adding must specifically reference this AD.
rules on aviation safety. Subtitle I, the following new airworthiness (2) Contacting the Manufacturer: For any
section 106, describes the authority of directive (AD): requirement in this AD to obtain corrective
mstockstill on DSK4VPTVN1PROD with PROPOSALS

the FAA Administrator. ‘‘Subtitle VII: Airbus: Docket No. FAA–2015–0086; actions from a manufacturer, the action must
Directorate Identifier 2014–NM–191–AD. be accomplished using a method approved
Aviation Programs,’’ describes in more
by the Manager, International Branch, ANM–
detail the scope of the Agency’s (a) Comments Due Date 116, Transport Airplane Directorate, FAA; or
authority. We must receive comments by April 6, the European Aviation Safety Agency
We are issuing this rulemaking under 2015. (EASA); or Airbus’s EASA Design
the authority described in ‘‘Subtitle VII, Organization Approval (DOA). If approved by
Part A, Subpart III, Section 44701: (b) Affected ADs the DOA, the approval must include the
General requirements.’’ Under that None. DOA-authorized signature.

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Document Created: 2018-02-16 11:10:39
Document Modified: 2018-02-16 11:10:39

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 April 6, 2015.
Contact		Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227- 2125; fax 425-227-1149.
FR Citation		80 FR 8575
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 8575 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 32 (February 18, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration