80 FR 42005 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 136 (July 16, 2015)

Page Range		42005-42007
FR Document		2015-17202

We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203 airplanes. This 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 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 AD requires repetitive replacement of all side link clevis engine mount bolts. We are issuing this AD to prevent failure of the front engine mount, and consequent possible departure of the engine.

Federal Register, Volume 80 Issue 136 (Thursday, July 16, 2015)

[Federal Register Volume 80, Number 136 (Thursday, July 16, 2015)]
[Rules and Regulations]
[Pages 42005-42007]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-17202]


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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; 
Amendment 39-18206; AD 2015-14-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A310-203 airplanes. This 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 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 AD requires 
repetitive replacement of all side link clevis engine mount bolts. We 
are issuing this AD to prevent failure of the front engine mount, and 
consequent possible departure of the engine.

DATES: This AD becomes effective August 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 20, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0086or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-0086.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A310-203 
airplanes. The NPRM published in the Federal Register on February 18, 
2015 (80 FR 8575). The NPRM 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. The NPRM was prompted by reports that 
side link clevis bolts of the front engine mount do not meet the DSG 
requirements on airplanes equipped with General Electric Company CF6-
80A3 engines. The NPRM proposed to require repetitive replacement of 
all side link clevis engine mount bolts. We are issuing this AD to 
prevent failure of the front engine mount, and consequent possible 
departure of the engine.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
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.

    You may examine the MCAI in the AD docket on the Internet at http:/
/www.regulations.gov/

[[Page 42006]]

#!documentDetail;D=FAA-2015-0086-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 8575, February 18, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 8575, February 18, 2015) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 8575, February 18, 2015).

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus 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). 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 of this 
AD.

Costs of Compliance

    We estimate that this AD affects 13 airplanes of U.S. registry.
    We also estimate that it will take about 142 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $2,900 per 
product. Based on these figures, we estimate the cost of this 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2015-14-08 Airbus: Amendment 39-18206. Docket No. FAA-2015-0086; 
Directorate Identifier 2014-NM-191-AD.

(a) Effective Date

    This AD becomes effective August 20, 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 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

[[Page 42007]]

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.

(i) Related Information

    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/#!documentDetail;D=FAA-2015-
0086-0003.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A310-71-2038, including Appendices 
01 and 02, dated April 8, 2014.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17202 Filed 7-15-15; 8:45 am]
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Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 42005

are consistent with the conservation DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2015–
plan during the last year of the contract. 0086.
* * * * * Federal Aviation Administration
FOR FURTHER INFORMATION CONTACT: Dan
(f) The eligible retired or retiring Rodina, Aerospace Engineer,
14 CFR Part 39
owner or operator and the eligible International Branch, ANM–116,
beginning, veteran, or socially [Docket No. FAA–2015–0086; Directorate Transport Airplane Directorate, FAA,
disadvantaged farmer or rancher must Identifier 2014–NM–191–AD; Amendment 1601 Lind Avenue SW., Renton, WA
39–18206; AD 2015–14–08] 98057–3356; telephone: 425–227–2125;
agree to be jointly and severally
responsible for complying with both the RIN 2120–AA64 fax: 425–227–1149.
provisions of the Transition Incentives SUPPLEMENTARY INFORMATION:
Program agreement and the provisions Airworthiness Directives; Airbus
Airplanes Discussion
of this part, and must also agree to be
jointly and severally responsible for any We issued a notice of proposed
AGENCY: Federal Aviation
payment adjustments that may result rulemaking (NPRM) to amend 14 CFR
Administration (FAA), Department of
from violations of the terms or part 39 by adding an AD that would
Transportation (DOT).
conditions of the Transition Incentives apply to all Airbus Model A310–203
ACTION: Final rule. airplanes. The NPRM published in the
Program agreement or this part.
SUMMARY: We are adopting a new Federal Register on February 18, 2015
§§ 1410.1, 1410.2, 1410.3, 1410.6, 1410.8, (80 FR 8575). The NPRM is intended to
1410.10, 1410.11, 1410.22, 1410.32, 1410.33, airworthiness directive (AD) for all
Airbus Model A310–203 airplanes. This complete certain mandated programs
1410.40, 1410.41, 1410.43, 1410.50, 1410.51,
1410.60, 1410.61, and 1410.62 [Amended] AD is intended to complete certain intended to support the airplane
mandated programs intended to support reaching its limit of validity (LOV) of
■ 54. In addition to the amendments set the airplane reaching its limit of validity the engineering data that support the
forth above, in 7 CFR part 1410, remove (LOV) of the engineering data that established structural maintenance
the word ‘‘CCC’’ each time it appears support the established structural program. The NPRM was prompted by
and add the words ‘‘the Deputy maintenance program. This AD was reports that side link clevis bolts of the
Administrator’’ in its place, in the prompted by reports that side link clevis front engine mount do not meet the DSG
following places: bolts of the front engine mount do not requirements on airplanes equipped
meet the design service goal (DSG) with General Electric Company CF6–
■ a. In § 1410.1(g), (h), and (i);
requirements on airplanes equipped 80A3 engines. The NPRM proposed to
■ b. In § 1410.2, in the definitions of require repetitive replacement of all side
with General Electric Company CF6–
‘‘Agricultural commodity’’, link clevis engine mount bolts. We are
80A3 engines. This AD requires
‘‘Commercial pond-raised aquaculture issuing this AD to prevent failure of the
repetitive replacement of all side link
facility’’, ‘‘Field’’, ‘‘Field windbreak, front engine mount, and consequent
clevis engine mount bolts. We are
shelterbelt, and/or living snowfence’’, possible departure of the engine.
issuing this AD to prevent failure of the
‘‘Offer’’, ‘‘Offeror’’, ‘‘Operator’’, The European Aviation Safety Agency
front engine mount, and consequent
‘‘Perennial crop’’, and ‘‘Technical (EASA), which is the Technical Agent
possible departure of the engine.
assistance’’; for the Member States of the European
DATES: This AD becomes effective
■ c. In § 1410.3(b) and (d); Union, has issued EASA AD 2014–0191,
August 20, 2015.
■ d. In § 1410.6(a)(2);
dated August 29, 2014 (referred to after
The Director of the Federal Register
this as the Mandatory Continuing
■ e. In § 1410.8(a); approved the incorporation by reference
Airworthiness Information, or ‘‘the
of a certain publication listed in this AD
■ f. In § 1410.10(b); MCAI’’), to correct an unsafe condition
as of August 20, 2015.
■ g. In § 1410.11(b) introductory text,
for all Airbus Model A310–203
ADDRESSES: You may examine the AD airplanes. The MCAI states:
(b)(1), (e), and (g); docket on the Internet at http://
During fatigue analysis performed in the
■ h. In § 1410.22(e); www.regulations.gov/
scope of the Extended Service Goal, taking
■ i. In § 1410.32(b)(3), (d) introductory #!docketDetail;D=FAA-2015-0086or in into account the certification loads and the
text, and (f)(2); person at the Docket Management new lift-off loads, Airbus determined that
Facility, U.S. Department of side link clevis engine mount bolts do not
■ j. In § 1410.33(d); Transportation, Docket Operations, M– meet the Design Service Goal (DSG)
■ k. In § 1410.40(b) and (g); 30, West Building Ground Floor, Room requirements on aeroplanes equipped with
■ l. In § 1410.41(b) and (c); W12–140, 1200 New Jersey Avenue SE., CF6–80A3 engines.
Washington, DC. This condition, if not corrected, could lead
■ m. In § 1410.43; to failure of the front engine mount, possibly
For service information identified in
■ n. In § 1410.50(a); this AD, contact Airbus SAS, resulting in-flight separation of the engine
from the aeroplane.
■ o. In § 1410.51(a)(1) and (c); Airworthiness Office—EAW, 1 Rond To address this potential unsafe condition,
Point Maurice Bellonte, 31707 Blagnac Airbus issued Service Bulletin (SB) A310–
■ p. In § 1410.60(a);
Cedex, France; telephone: +33 5 61 93 71–2038 to introduce a life limit on the side
■ q. In § 1410.61; and 36 96; fax: +33 5 61 93 44 51; email: link clevis engine mount bolts.
■ r. In § 1410.62(h). account.airworth-eas@airbus.com; For the reason described above, this
Internet http://www.airbus.com. You [EASA] AD requires implementation of the
tkelley on DSK3SPTVN1PROD with RULES

Val Dolcini, may view this referenced service new life limit and replacement of all side
Administrator, Farm Service Agency, and information at the FAA, Transport link clevis engine mount bolts that have
Executive Vice President, Commodity Credit Airplane Directorate, 1601 Lind Avenue exceeded the new limit.
Corporation. SW., Renton, WA. It is also available on You may examine the MCAI in the
[FR Doc. 2015–17317 Filed 7–15–15; 8:45 am] the Internet at http:// AD docket on the Internet at http://
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42006 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations

#!documentDetail;D=FAA-2015-0086- General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701.
0003. section, Congress charges the FAA with
§ 39.13 [Amended]
promoting safe flight of civil aircraft in
Comments ■ 2. The FAA amends § 39.13 by adding
air commerce by prescribing regulations
We gave the public the opportunity to for practices, methods, and procedures the following new airworthiness
participate in developing this AD. We the Administrator finds necessary for directive (AD):
received no comments on the NPRM (80 safety in air commerce. This regulation 2015–14–08 Airbus: Amendment 39–18206.
FR 8575, February 18, 2015) or on the is within the scope of that authority Docket No. FAA–2015–0086; Directorate
determination of the cost to the public. because it addresses an unsafe condition Identifier 2014–NM–191–AD.
that is likely to exist or develop on (a) Effective Date
Conclusion
products identified in this rulemaking
We reviewed the relevant data and This AD becomes effective August 20,
action. 2015.
determined that air safety and the
public interest require adopting this AD Regulatory Findings (b) Affected ADs
as proposed except for minor editorial We determined that this AD will not None.
changes. We have determined that these have federalism implications under
Executive Order 13132. This AD will (c) Applicability
minor changes:
• Are consistent with the intent that not have a substantial direct effect on This AD applies to Airbus Model A310–
was proposed in the NPRM (80 FR 8575, the States, on the relationship between 203 airplanes, certificated in any category, all
February 18, 2015) for correcting the manufacturer serial numbers.
the national government and the States,
unsafe condition; and or on the distribution of power and (d) Subject
• Do not add any additional burden responsibilities among the various Air Transport Association (ATA) of
upon the public than was already levels of government. America Code 71, Powerplant.
proposed in the NPRM (80 FR 8575, For the reasons discussed above, I
(e) Reason
February 18, 2015). certify that this AD:
1. Is not a ‘‘significant regulatory This AD was prompted by reports that side
Related Service Information Under 1 action’’ under Executive Order 12866; link clevis bolts of the front engine mount do
CFR Part 51 2. Is not a ‘‘significant rule’’ under the not meet the Design Service Goal (DSG)
requirements on airplanes equipped with
We reviewed Airbus Service Bulletin DOT Regulatory Policies and Procedures General Electric Company CF6–80A3
A310–71–2038, including Appendices (44 FR 11034, February 26, 1979); engines. We are issuing this AD to prevent
01 and 02, dated April 8, 2014. The 3. Will not affect intrastate aviation in failure of the front engine mount, and
service information describes Alaska; and consequent possible departure of the engine.
procedures for replacement of all side 4. Will not have a significant
economic impact, positive or negative, (f) Compliance
link clevis bolts on the CF6–80A3 front
engine mount and subsequent re- on a substantial number of small entities Comply with this AD within the
under the criteria of the Regulatory compliance times specified, unless already
identification of the newly installed
Flexibility Act. done.
bolts with a cross (to differentiate them
from the old ones). This service Examining the AD Docket (g) Repetitive Bolt Replacement
information is reasonably available Within 18 months after the effective date
because the interested parties have You may examine the AD docket on of this AD, replace the side link clevis bolts,
access to it through their normal course the Internet at http:// nuts, and bushings of the front engine mount
of business or by the means identified www.regulations.gov/ on both engines, and re-identify the new
in the ADDRESSES section of this AD. #!docketDetail;D=FAA-2015-0086; or in installed bolts with a cross (to differentiate
person at the Docket Management them from the old ones), in accordance with
Costs of Compliance Facility between 9 a.m. and 5 p.m., the Accomplishment Instructions of Airbus
Monday through Friday, except Federal Service Bulletin A310–71–2038, including
We estimate that this AD affects 13 Appendices 01 and 02, dated April 8, 2014.
airplanes of U.S. registry. holidays. The AD docket contains this
Repeat the replacement thereafter at intervals
We also estimate that it will take AD, the regulatory evaluation, any
not to exceed 29 years.
about 142 work-hours per product to comments received, and other
comply with the basic requirements of information. The street address for the (h) Other FAA AD Provisions
this AD. The average labor rate is $85 Docket Operations office (telephone: The following provisions also apply to this
per work-hour. Required parts will cost 800–647–5527) is in the ADDRESSES AD:
about $2,900 per product. Based on section. (1) Alternative Methods of Compliance
(AMOCs): The Manager, International
these figures, we estimate the cost of List of Subjects in 14 CFR Part 39 Branch, ANM–116, Transport Airplane
this AD on U.S. operators to be Directorate, FAA, has the authority to
Air transportation, Aircraft, Aviation
$194,610, or $14,970 per product. approve AMOCs for this AD, if requested
safety, Incorporation by reference,
Authority for This Rulemaking using the procedures found in 14 CFR 39.19.
Safety.
In accordance with 14 CFR 39.19, send your
Title 49 of the United States Code Adoption of the Amendment request to your principal inspector or local
specifies the FAA’s authority to issue Flight Standards District Office, as
Accordingly, under the authority appropriate. If sending information directly
rules on aviation safety. Subtitle I,
delegated to me by the Administrator, to the International Branch, send it to ATTN:
section 106, describes the authority of
the FAA amends 14 CFR part 39 as Dan Rodina, Aerospace Engineer,
the FAA Administrator. ‘‘Subtitle VII:
tkelley on DSK3SPTVN1PROD with RULES

follows: International Branch, ANM–116, Transport
Aviation Programs,’’ describes in more
Airplane Directorate, FAA, 1601 Lind
detail the scope of the Agency’s PART 39—AIRWORTHINESS Avenue SW., Renton, WA 98057–3356;
authority. DIRECTIVES telephone 425–227–2125; fax 425–227–1149.
We are issuing this rulemaking under Information may be emailed to: 9-ANM-116-
the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39 AMOC-REQUESTS@faa.gov. Before using
Part A, Subpart III, Section 44701: continues to read as follows: any approved AMOC, notify your appropriate

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Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 42007

principal inspector, or lacking a principal DEPARTMENT OF TRANSPORTATION FAA, Transport Airplane Directorate,
inspector, the manager of the local flight 3960 Paramount Blvd., Lakewood, CA
standards district office/certificate holding Federal Aviation Administration 90712–4137; phone: 562–627–5246; fax:
district office. The AMOC approval letter 562–627–5210; email: joseph.costa@
must specifically reference this AD. 14 CFR Part 39
(2) Contacting the Manufacturer: For any
faa.gov.
requirement in this AD to obtain corrective [Docket No. FAA–2006–23706; Directorate SUPPLEMENTARY INFORMATION: AD 2015–
actions from a manufacturer, the action must Identifier 2006–NE–03–AD; Amendment 39– 12–04, Amendment 39–18177, 80 FR
be accomplished using a method approved 18177; AD 2015–12–04] 34534, June 17, 2015), requires initial
by the Manager, International Branch, ANM– and repetitive dimensional inspections
116, Transport Airplane Directorate, FAA; or RIN 2120–AA64
of the affected fuel control drives and
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Airworthiness Directives; Honeywell insertion of certain airplane operating
Organization Approval (DOA). If approved by International Inc. Turboprop Engines procedures into the applicable flight
the DOA, the approval must include the manuals.
AGENCY: Federal Aviation As published, the AD number in the
DOA-authorized signature.
Administration (FAA), DOT. document headings is incorrect.
(i) Related Information ACTION: Final rule; correction. Additionally, the Amendment number
Refer to Mandatory Continuing in the regulatory text of AD 2015–12–04
Airworthiness Information (MCAI) EASA SUMMARY: The FAA is correcting an
is incorrect.
Airworthiness Directive 2014–0191, dated airworthiness directive (AD) that
No other part of the final rule has
August 29, 2014, for related information. published in the Federal Register. That
This MCAI may be found in the AD docket been changed.
AD applies to all Honeywell
on the Internet at http:// The effective date of AD 2015–12–04
International Inc. TPE331–1, –2, –2UA,
www.regulations.gov/ remains July 22, 2015.
–3U, –3UW, –5, –5A, –5AB, –5B, –6,
#!documentDetail;D=FAA-2015-0086-0003.
–6A, –10, –10AV, –10GP, –10GT, –10P, Correction of Non-Regulatory Text
(j) Material Incorporated by Reference –10R, –10T, –10U, –10UA, –10UF, In the Federal Register of June 17,
(1) The Director of the Federal Register –10UG, –10UGR, –10UR, –11U, –12JR, 2015, AD 2015–12–04; Amendment 39–
approved the incorporation by reference –12UA, –12UAR, and –12UHR 18177 (80 FR 34534) is corrected as
(IBR) of the service information listed in this turboprop engines with certain follows:
paragraph under 5 U.S.C. 552(a) and 1 CFR Honeywell part numbers (P/Ns) of
part 51. On page 34534, in the 2nd column, on
Woodward fuel control unit (FCU) line 6, change ‘‘2014–12–04’’ to ‘‘2015–
(2) You must use this service information assemblies, installed. The AD number in
as applicable to do the actions required by 12–04’’.
the document headings is incorrect.
this AD, unless this AD specifies otherwise.
Additionally, the Amendment number Correction of Regulatory Text
(i) Airbus Service Bulletin A310–71–2038,
including Appendices 01 and 02, dated April in the regulatory text is incorrect. This
§ 39.13 [Corrected]
8, 2014. document corrects these two errors. In
(ii) Reserved. all other respects, the original document ■ 2. The FAA amends § 39.13 by
(3) For service information identified in remains the same. removing airworthiness directive (AD)
this AD, contact Airbus SAS, Airworthiness DATES: This final rule is effective on July 2006–15–08, Amendment 39–14688 (71
Office—EAW, 1 Rond Point Maurice FR 41121, July 20, 2006), and adding the
22, 2015. The effective date of AD 2015–
Bellonte, 31707 Blagnac Cedex, France; following new AD:
telephone +33 5 61 93 36 96; fax +33 5 61 12–04, Amendment 39–18177 (80 FR
93 44 51; email account.airworth-eas@ 34534, June 17, 2015) remains July 22, 2015–12–04 Honeywell International Inc.:
airbus.com; Internet http://www.airbus.com. 2015. Amendment 39–18177; Docket No.
(4) You may view this service information FAA–2006–23706; Directorate Identifier
ADDRESSES: You may examine the AD
at the FAA, Transport Airplane Directorate, 2006–NE–03–AD.
docket on the Internet at http://
1601 Lind Avenue SW., Renton, WA. For www.regulations.gov; or in person at the (a) Effective Date
information on the availability of this
Docket Management Facility between 9 This AD is effective August 20, 2015.
material at the FAA, call 425–227–1221.
(5) You may view this service information a.m. and 5 p.m., Monday through
(b) Affected ADs
that is incorporated by reference at the Friday, except Federal holidays. The AD
docket contains this AD, the regulatory This AD replaces AD 2006–15–08,
National Archives and Records
evaluation, any comments received, and Amendment 39–14688 (71 FR 41121, July 20,
Administration (NARA). For information on
2006).
the availability of this material at NARA, call other information. The address for the
202–741–6030, or go to: http:// Docket Office (phone: 800–647–5527) is (c) Applicability
www.archives.gov/federal-register/cfr/ibr- Document Management Facility, U.S. This AD applies to all Honeywell
locations.html. Department of Transportation, Docket International Inc. TPE331–1, –2, –2UA, –3U,
Issued in Renton, Washington, on July 2, Operations, M–30, West Building –3UW, –5, –5A, –5AB, –5B, –6, –6A, –10,
2015. Ground Floor, Room W12–140, 1200 –10AV, –10GP, –10GT, –10P, –10R, –10T,
Jeffrey E. Duven, New Jersey Avenue SE., Washington, –10U, –10UA, –10UF, –10UG, –10UGR,
DC 20590. –10UR, –11U, –12JR, –12UA, –12UAR, and
Manager, Transport Airplane Directorate,
–12UHR turboprop engines with Honeywell
Aircraft Certification Service. FOR FURTHER INFORMATION CONTACT: part numbers (P/Ns) for Woodward fuel
[FR Doc. 2015–17202 Filed 7–15–15; 8:45 am] Joseph Costa, Aerospace Engineer, Los control unit (FCU) assemblies listed in Table
BILLING CODE 4910–13–P Angeles Aircraft Certification Office, 1 to paragraph (c) of this AD, installed.
tkelley on DSK3SPTVN1PROD with RULES

TABLE 1 TO PARAGRAPH (C)—AFFECTED FCU ASSEMBLY P/NS
Group No. Engine FCU Assembly P/Ns

1 ..................... TPE331–1, –2, and –2UA ........................ P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33,
–34, and –35.

VerDate Sep<11>2014 16:14 Jul 15, 2015 Jkt 235001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\16JYR1.SGM 16JYR1

Document Created: 2015-12-15 13:13:49
Document Modified: 2015-12-15 13:13:49

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		Rules and Regulations
Action		Final rule.
Dates		This AD becomes effective August 20, 2015.
Contact		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.
FR Citation		80 FR 42005
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 42005 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 136 (July 16, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration