73092 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 

V. Differences Between the Banks and 

the Enterprises 

Section 1313(f) of the Safety and 

Soundness Act requires the Director to 

consider the differences between the 

Banks and the Enterprises whenever 

promulgating regulations that affect the 

Banks. In developing the amendments 

to this rule, FHFA considered the 

differences between the Banks and the 

Enterprises, but also adhered to the 

statutory mandate that the regulation be 

‘‘consistent and comparable’’ with the 

regulations of the other agencies. In 

implementing the regulation, FHFA will 

define scenarios for the regulated 

entities, bearing in mind the key risk 

exposures at each regulated entity. 

In the final rule, FHFA requires 

different timeframes for reporting stress 

test results for the Enterprises versus the 

Banks. For the Enterprises, FHFA sets 

the dates for reporting stress test results 

to the regulator, the FRB, and the public 

in proximity to similar dates in the 

other agencies’ rules for institutions 

with over $50 billion in assets. 

Reporting dates for all the Banks, 

regardless of size, are set in proximity 

to similar dates for institutions with less 

than $50 billion in assets. As a result, 

the Banks have over three additional 

months to report results to FHFA, the 

FRB, and the public. 

VI. Paperwork Reduction Act 

The final rule does not contain any 

collections of information pursuant to 

the Paperwork Reduction Act of 1995 

(44 U.S.C. 3501, et seq.). Therefore, 

FHFA has not submitted any 

information to the Office of 

Management and Budget for review. 

VII. Regulatory Flexibility Act 

The final rule applies only to the 

regulated entities, which do not come 

within the meaning of small entities as 

defined in the Regulatory Flexibility Act 

(see 5 U.S.C. 601(6)). Therefore, in 

accordance with section 605(b) of the 

Regulatory Flexibility Act (5 U.S.C. 

605(b)), the General Counsel of FHFA 

certifies that this final rule will not have 

a significant economic impact on a 

substantial number of small entities. 

List of Subjects in 12 CFR Part 1238 

Administrative practice and 

procedure, Capital, Federal Home Loan 

Banks, Government-sponsored 

enterprises, Regulated entities, 

Reporting and recordkeeping 

requirements, Stress test. 

Authority and Issuance 

For the reasons stated in the 

preamble, and under the authority of 12 

U.S.C. 4513, 4526, and 5365(i), FHFA 

amends part 1238 of title 12 of the Code 

of Federal Regulations as follows: 

PART 1238—STRESS TESTING OF 

REGULATED ENTITIES 

■ 1. The authority citation for part 1238 

continues to read as follows: 

Authority: 12 U.S.C. 5365(i); 12 U.S.C. 

4513, 4526, 4612; and 12 U.S.C. 1426. 

■ 2. Amend § 1238.3 by revising 

paragraphs (a)(1) and (b) to read as 

follows: 

§ 1238.3 Annual stress test. 

(a) * * * 

(1) Shall complete an annual stress 

test of itself based on its data as of 

December 31 of the preceding calendar 

year; 

* * * * * 

(b) Scenarios provided by FHFA. In 

conducting its annual stress tests under 

this section, each regulated entity must 

use scenarios provided by FHFA, which 

shall be generally consistent with and 

comparable to those established by the 

FRB, that reflect a minimum of three 

sets of economic and financial 

conditions, including a baseline, 

adverse, and severely adverse scenario. 

Not later than 30 days after the FRB 

publishes its scenarios, FHFA will issue 

to all regulated entities a description of 

the baseline, adverse, and severely 

adverse scenarios that each regulated 

entity shall use to conduct its annual 

stress tests under this part. 

■ 3. Amend § 1238.5 by revising 

paragraph (a) to read as follows: 

§ 1238.5 Required report to FHFA and the 

FRB of stress test results and related 

information. 

(a) Report required for stress tests. On 

or before May 20 of each year, the 

Enterprises must report the results of 

the stress tests required under § 1238.3 

to FHFA, and to the FRB, in accordance 

with paragraph (b) of this section; and 

on or before August 31 of each year, the 

Banks must report the results of the 

stress tests required under § 1238.3 to 

FHFA, and to the FRB, in accordance 

with paragraph (b) of this section; 

* * * * * 

■ 4. Amend § 1238.7 by revising 

paragraph (a) to read as follows: 

§ 1238.7 Publication of results by 

regulated entities. 

(a) Public disclosure of results 

required for stress tests of regulated 

entities. The Enterprises must disclose 

publicly a summary of the stress test 

results for the severely adverse scenario 

not earlier than August 1 and not later 

than August 15 of each year. Each Bank 

must disclose publicly a summary of the 

stress test results for the severely 

adverse scenario not earlier than 

November 15 and not later than 

November 30 of each year. The 

summary may be published on the 

regulated entity’s Web site or in any 

other form that is reasonably accessible 

to the public; 

* * * * * 

Dated: November 11, 2015. 

Melvin L. Watt, 

Director, Federal Housing Finance Agency. 

[FR Doc. 2015–29861 Filed 11–23–15; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0490; Directorate 

Identifier 2014–NM–018–AD; Amendment 

39–18322; AD 2015–23–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–22– 

20 for certain Airbus Model A330–200, 

A330–300, and A340–300 series 

airplanes. AD 2008–22–20 required 

repetitive high frequency eddy current 

(HFEC) inspections for cracking, repair 

if necessary, and modification of the 

upper shell structure of the fuselage. 

This new AD shortens certain 

compliance times. This AD was 

prompted by a determination from a 

fatigue and damage tolerance evaluation 

that the compliance times must be 

reduced. We are issuing this AD to 

prevent fatigue cracking of the upper 

shell structure of the fuselage, which 

could result in reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

December 29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of December 17, 2008 (73 FR 

66747, November 12, 2008). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail; 

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Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73093 

D=FAA-2015-0490; or 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—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0490. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–22–20, 

Amendment 39–15717 (73 FR 66747, 

November 12, 2008). AD 2008–22–20 

applied to certain Airbus Model A330– 

200, A330–300, and A340–300 series 

airplanes. The NPRM published in the 

Federal Register on March 17, 2015 (80 

FR 13799). The NPRM was prompted by 

a determination from a fatigue and 

damage tolerance evaluation that the 

compliance times must be reduced. The 

NPRM also proposed to shorten certain 

compliance times. We are issuing this 

AD to prevent fatigue cracking of the 

upper shell structure of the fuselage, 

which could result in reduced structural 

integrity of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0012R1, dated January 

24, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Airbus 

Model A330–200, A330–300, and A340– 

300 series airplanes. The MCAI states: 

During fatigue tests (EF3) on the A340–600, 

damage was found in the longitudinal 

doubler at the Vertical Tail Plane (VTP) 

attachment cut out between Frame (FR) 80 

and FR86. This damage occurred between 

58,341 and 72,891 simulated flight cycles 

(FC). 

Due to the higher Design Service Goal and 

different design of the affected structural area 

(e.g. doubler thickness) for A330–200/–300 

and A340–300 airplane series, the damage 

assessment concluded that these airplanes 

may be also potentially affected. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the upper shell structure between FR80 

and FR86. 

Prompted by these findings, EASA issued 

AD 2007–0284 [(http://ad.easa.europa.eu/

blob/easa_ad_2007_0284_superseded.pdf/

AD_2007-0284_1)] to require implementation 

of an inspection programme of this structural 

area using a high frequency eddy current 

(HFEC) method and a modification to 

improve the upper shell structure. 

Since that [EASA] AD was issued, in the 

frame of a new fatigue and damage tolerance 

evaluation, taking into account the airplane 

utilisation, the inspection threshold and 

intervals have been reassessed and the 

conclusion was that the thresholds and 

intervals for inspection, as well as the 

threshold for modifying the airplane, must be 

reduced. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2007–0284, which is superseded and 

introduces redefined thresholds and 

intervals. 

This [EASA] AD is revised to clarify that, 

under some conditions, accomplishment of a 

repair constitutes terminating action for the 

repetitive inspections. One of the outcome of 

this clarification is the deletion of paragraph 

(5) of this [EASA] AD. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2015-0490-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 13799, 

March 17, 2015) and the FAA’s response 

to each comment. 

Support for the NPRM (80 FR 13799, 

March 17, 2015) 

An anonymous commenter agreed 

with the safety benefit provided by the 

NPRM (80 FR 13799, March 17, 2015). 

Request for Revise Cost 

Delta requested that we revise the 

NPRM (80 FR 13799, March 17, 2015) to 

relay the heavy impact of accomplishing 

Airbus Service Bulletin A330–53–3160, 

Revision 03, dated January 6, 2012. 

Delta explained that the modification 

specified in Airbus Service Bulletin 

A330–53–3160, Revision 03, dated 

January 6, 2012, requires removal of the 

vertical stabilizer and the aft galley, 

which can heavily impact the operation. 

Delta reasoned that it has consulted 

with its maintenance organization and it 

is estimated to take 400 work-hours 

instead of 208 work-hours. 

We disagree with the request to revise 

this AD. We made the cost estimate 

based on the information provided in 

Airbus Service Bulletin A330–53–3160, 

Revision 03, dated January 6, 2012. The 

required work-hours defined in Airbus 

Service Bulletin A330–53–3160, 

Revision 03, dated January 6, 2012, are 

based on the direct labor cost to do the 

work. The need to remove and reinstall 

the aft galley depends on the airplane 

interior configuration and may differ 

from operator to operator. We are unable 

to determine all possible interior 

configurations and thus determine the 

maximum work-hours which may be 

required for any specific configuration. 

This estimate assumes that the work 

will be done by experienced personnel, 

and may need to be revised upwards to 

suit an operator’s circumstances. The 

estimate does not include the time to 

prepare, plan, or inspect the work. We 

have made no changes to this AD in this 

regard. 

Conclusion 

We reviewed the available 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 

13799, March 17, 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 13799, 

March 17, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A330–53– 

3159, Revision 02, dated March 29, 

2010, describes procedures for a 

modification of the fuselage, which 

includes inspections (e.g., eddy current 

rotating probe test of fastener holes for 

cracking, high frequency eddy current 

(HFEC) inspections for cracking of the 

upper shell structure of the fuselage, 

and checks of the fastener position for 

clearance) and applicable corrective 

actions (e.g., repair and rework). 

• Airbus Service Bulletin A330–53– 

3160, Revision 03, dated January 6, 

2012, describes procedures for 

applicable actions, including an eddy 

current rotating probe test for cracking 

of the fastener holes and an HFEC 

inspection for cracks in the upper shell 

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73094 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 

of the fuselage (and including checks of 

the fastener position for clearance and 

applicable corrective actions (e.g., repair 

and rework)), and a modification of the 

airplane upper shell structure of the 

fuselage between FR80 and FR86. 

• Airbus Service Bulletin A330–53– 

3168, Revision 02, dated December 21, 

2011, describes procedures for a HFEC 

inspection for cracking of the upper 

shell structure of the fuselage between 

FR80 and FR86. 

• Airbus Service Bulletin A340–53– 

4165, Revision 02, dated March 29, 

2010, describes procedures for a 

modification of the fuselage, which 

includes inspections (e.g., eddy current 

rotating probe test of fastener holes for 

cracking, HFEC inspections for cracking 

of the upper shell structure of the 

fuselage, and checks of the fastener 

position for clearance) and applicable 

corrective actions (e.g., repair and 

rework). 

• Airbus Service Bulletin A340–53– 

4172, Revision 01, dated July 8, 2009, 

describes procedures for inspections 

(e.g., rototest inspections of fastener 

holes for cracking, HFEC inspections for 

cracking of the upper shell structure of 

the fuselage, and checks of the fastener 

position for clearance) and modification 

of the airplane upper shell structure 

between FR80 and FR86 (including 

applicable corrective actions (e.g., repair 

and rework). 

• Airbus Service Bulletin A340–53– 

4174, Revision 02, dated December 21, 

2011, describes procedures for a HFEC 

inspection for cracking of the upper 

shell structure of the fuselage between 

FR80 and FR86. 

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 26 

airplanes of U.S. registry. We also 

estimate that it will take about 208 

work-hours per product to comply with 

the basic requirements (inspection and 

modification) of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $28,360 

per product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $1,197,040, or $46,040 

per product. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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/#!docket

Detail;D=FAA-2015-0490; 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2008–22–20, Amendment 39–15717 (73 

FR 66747, November 12, 2008), and 

adding the following new AD: 

2015–23–06 Airbus: Amendment 39–18322. 

Docket No. FAA–2015–0490; Directorate 

Identifier 2014–NM–018–AD. 

(a) Effective Date 

This AD becomes effective December 29, 

2015. 

(b) Affected ADs 

This AD replaces AD 2008–22–20, 

Amendment 39–15717 (73 FR 66747, 

November 12, 2008). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–311, –312, and 

–313 airplanes; certificated in any category; 

all manufacturer serial numbers on which 

Airbus Modification 44205 has been 

embodied in production, except those on 

which Airbus Modification 52974 or 53223 

has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by the results of a 

fatigue and damage tolerance evaluation that 

concluded existing compliance times must be 

reduced. We are issuing this AD to prevent 

fatigue cracking of the upper shell structure 

of the fuselage, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

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Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73095 

(g) Inspection for Airbus Model A330–300 

and A340–300 Airplanes, Except Model 

A340–300 Weight Variant (WV) 027 

Airplanes 

For Model A330–300 and A340–300 

airplanes, except Model A340–300 WV 027 

airplanes: At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD, do a high 

frequency eddy current (HFEC) inspection for 

cracking of the upper shell structure between 

frame (FR) 80 and FR86, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3168, Revision 02, 

dated December 21, 2011; or Airbus Service 

Bulletin A340–53–4174, Revision 02, dated 

December 21, 2011; as applicable. Repeat the 

inspection thereafter at the applicable time 

specified in paragraph 1.E., ‘‘COMPLIANCE,’’ 

of Airbus Service Bulletin A330–53–3168, 

Revision 02, dated December 21, 2011; or 

Airbus Service Bulletin A340–53–4174, 

Revision 02, dated December 21, 2011; as 

applicable. 

(1) For airplanes that, as of the effective 

date of this AD, have not been inspected in 

accordance with Airbus Service Bulletin 

A330–53–3168; or Airbus Service Bulletin 

A340–53–4174; as applicable: Inspect at the 

later of the times specified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD. 

(i) Before reaching the applicable threshold 

specified in paragraph 1.E., ‘‘COMPLIANCE,’’ 

of Airbus Service Bulletin A330–53–3168, 

Revision 02, dated December 21, 2011; or 

Airbus Service Bulletin A340–53–4174, 

Revision 02, dated December 21, 2011; as 

applicable for airplane model, configuration, 

and utilization, since the airplane’s first 

flight. 

(ii) Within the threshold defined in 

paragraph 1.E, ‘‘COMPLIANCE,’’ of Airbus 

Service Bulletin A330–53–3168, Revision 01, 

dated February 15, 2008; or Airbus Service 

Bulletin A340–53–4174, Revision 01, dated 

February 15, 2008; as applicable for airplane 

model, configuration, and utilization since 

the airplane’s first flight; or within 12 months 

after the effective date of this AD; whichever 

occurs first. 

(2) For airplanes that, as of the effective 

date of this AD, have been inspected in 

accordance with Airbus Service Bulletin 

A330–53–3168; or Airbus Service Bulletin 

A340–53–4174; as applicable: Inspect at the 

later of the times specified in paragraphs 

(g)(2)(i) and (g)(2)(ii) of this AD. 

(i) Within the applicable interval specified 

in paragraph 1.E., ‘‘COMPLIANCE,’’ of 

Airbus Service Bulletin A330–53–3168, 

Revision 02, dated December 21, 2011; or 

Airbus Service Bulletin A340–53–4174, 

Revision 02, dated December 21, 2011; as 

applicable; to be counted from the last 

inspection. 

(ii) Within 12 months after the effective 

date of this AD without exceeding the 

intervals defined in paragraph 1.E, 

‘‘COMPLIANCE,’’ of Airbus Service Bulletin 

A330–53–3168, Revision 01, dated February 

15, 2008; or Airbus Service Bulletin A340– 

53–4174, Revision 01, dated February 15, 

2008; as applicable for airplane model, 

configuration, and utilization to be counted 

from the last inspection. 

(h) Corrective Action for Airbus Model 

A330–300 and A340–300 Airplanes, Except 

Model A340–300 WV 027 Airplanes 

If any crack is detected during any HFEC 

inspection required by the introductory text 

to 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). Accomplishment of a repair 

for a specific area, as required by this 

paragraph, is terminating action for the 

repetitive HFEC inspections required by the 

introductory text to paragraph (g) of this AD, 

as applicable, for that specific repaired area 

only. The need and definition of subsequent 

repetitive inspections (if any) for that specific 

repaired area will be defined in the 

applicable repair 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). 

(i) Optional Terminating Action 

For Airbus Model A330–300 and A340– 

300 airplanes, except Model A340–300 WV 

027 airplanes: Modification, which includes 

inspections and applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

53–3159, Revision 02, dated March 29, 2010; 

or Airbus Service Bulletin A340–53–4165, 

Revision 02, dated March 29, 2010; as 

applicable; terminates the repetitive HFEC 

inspections required by the introductory text 

to paragraph (g) of this AD, except where 

Airbus Service Bulletin A330–53–3159, 

Revision 02, dated March 29, 2010; or Airbus 

Service Bulletin A340–53–4165, Revision 02, 

dated March 29, 2010; as applicable; 

specifies to contact the manufacturer, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(j) Inspection and Modification for Airbus 

Model A330–200 Airplanes 

Within the compliance times specified in 

paragraph (j)(1) or (j)(2) of this AD, 

whichever occurs later: Do all applicable 

actions, including an eddy current rotating 

probe test and an HFEC inspection for cracks, 

and modify the airplane upper shell structure 

between FR80 and FR86; in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3160, Revision 03, 

dated January 6, 2012. 

(1) Within the compliance times identified 

in paragraph 1.E., ‘‘COMPLIANCE,’’ of 

Airbus Service Bulletin A330–53–3160, 

Revision 03, dated January 6, 2012, as 

applicable for airplane configuration and 

utilization since the airplane’s first flight. 

(2) Within 12 months after the effective 

date of this AD without exceeding the 

threshold defined in paragraph 1.E, 

‘‘COMPLIANCE,’’ of Airbus Service Bulletin 

A330–53–3160, Revision 02, dated March 29, 

2010, since the airplane’s first flight. 

(k) Inspection and Modification for Airbus 

Model A340–300 Airplanes, Only WV 027 

For Model A340–300 airplanes, WV 027 

only: Before the accumulation of 14,200 total 

flight cycles from the airplane’s first flight, 

do all applicable inspections and modify the 

airplane upper shell structure between FR80 

and FR86; in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–53–4172, Revision 01, 

dated July 8, 2009. 

(l) Corrective Action for Airbus Model A330– 

200 Airplanes; and Model A340–300 

Airplanes, only WV 027 

If any crack is detected during the 

inspection required by the introductory text 

to paragraph (j) of this AD, or paragraph (k) 

of this AD, before further flight, repair using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA; concurrently with 

modification required by paragraph the 

introductory text to paragraph (j) of this AD, 

or paragraph (k) of this AD. 

(m) Definition of ‘‘Threshold’’ and ‘‘Interval’’ 

(1) For the purposes of this AD, the term 

‘‘Threshold,’’ as used in paragraph 1.E., 

‘‘COMPLIANCE,’’ of the service information 

specified in paragraphs (m)(2)(i) through 

(m)(2)(vi) of this AD means the total flight 

cycles or flight hours accumulated since the 

airplane’s first flight. 

(2) For the purposes of this AD, the term 

‘‘Interval’’ as used in paragraph 1.E., 

‘‘COMPLIANCE,’’ of the service information 

specified in paragraphs (m)(2)(i) through 

(m)(2)(vi) of this AD means the total flight 

cycles or flight hours accumulated since the 

last inspection, as applicable. 

(i) Airbus Service Bulletin A330–53–3168, 

dated September 19, 2007. 

(ii) Airbus Service Bulletin A330–53–3168, 

Revision 01, dated February 15, 2008. 

(iii) Airbus Service Bulletin A330–53– 

3168, Revision 02, dated December 21, 2011. 

(iv) Airbus Service Bulletin A340–53– 

4174, dated September 19, 2007. 

(v) Airbus Service Bulletin A340–53–4174, 

Revision 01, dated February 15, 2008. 

(vi) Airbus Service Bulletin A340–53– 

4174, Revision 02, dated December 21, 2011. 

(n) Credit for Previous Actions 

(1) For Model A330–300 and A340–300 

airplanes, except Model A340–300 WV 027 

airplanes: This paragraph provides credit for 

the modification specified in paragraph (i) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information identified in paragraph 

(n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of 

this AD, as applicable. This service 

information is not incorporated by reference 

in this AD. 

(i) Airbus Service Bulletin A330–53–3159, 

dated September 19, 2007. 

(ii) Airbus Service Bulletin A330–53–3159, 

Revision 01, dated June 15, 2009. 

(iii) Airbus Service Bulletin A340–53– 

4165, dated September 19, 2007. 

(iv) Airbus Service Bulletin A340–53– 

4165, Revision 01, dated June 17, 2009. 

(2) For Model A330–200 airplanes: This 

paragraph provides credit for the inspection 

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and modification required by the 

introductory text to paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (n)(2)(i), 

(n)(2)(ii), or (n)(2)(iii) of this AD, as 

applicable. 

(i) Airbus Service Bulletin A330–53–3160, 

dated July 9, 2007, which was incorporated 

by reference in AD 2008–22–20, Amendment 

39–15717 (73 FR 66747, November 12, 2008). 

(ii) Airbus Service Bulletin A330–53–3160, 

Revision 01, dated April 28, 2009, which is 

not incorporated by reference in this AD. 

(iii) Airbus Service Bulletin A330–53– 

3160, Revision 02, dated March 29, 2010, 

which is not incorporated by reference in this 

AD. 

(3) For Model A340–300 airplanes, WV 027 

only: This paragraph provides credit for the 

inspection and modification required by 

paragraph (k) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Service Bulletin A340– 

53–4172, dated July 10, 2007, which is was 

incorporated by reference in AD 2008–22–20, 

Amendment 39–15717 (73 FR 66747, 

November 12, 2008). 

(o) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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: As of the 

effective date of this AD, 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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0012R1, dated 

January 24, 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–2015–0490. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(3) and (q)(4) of this AD. 

(q) 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. 

(3) The following service information was 

approved for IBR on December 29, 2015. 

(i) Airbus Service Bulletin A330–53–3159, 

Revision 02, dated March 29, 2010. 

(ii) Airbus Service Bulletin A330–53–3160, 

Revision 03, dated January 6, 2012. 

(iii) Airbus Service Bulletin A330–53– 

3168, Revision 02, dated December 21, 2011. 

(iv) Airbus Service Bulletin A340–53– 

4165, Revision 02, dated March 29, 2010. 

(v) Airbus Service Bulletin A340–53–4172, 

Revision 01, dated July 8, 2009. 

(vi) Airbus Service Bulletin A340–53– 

4174, Revision 02, dated December 21, 2011. 

(4) The following service information was 

approved for IBR on December 17, 2008 (73 

FR 66747, November 12, 2008). 

(i) Airbus Service Bulletin A330–53–3168, 

Revision 01, dated February 15, 2008. 

(ii) Airbus Service Bulletin A340–53–4174, 

Revision 01, dated February 15, 2008. 

(5) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(6) 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. 

(7) 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/ibrlocations.html. 

Issued in Renton, Washington, on October 

30, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28886 Filed 11–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0682; Directorate 

Identifier 2014–NM–074–AD; Amendment 

39–18329; AD 2015–23–12] 

RIN 2120–AA64 

Airworthiness Directives; ATR—GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

ATR—GIE Avions de Transport 

Re ́gional Model ATR42 and ATR72 

airplanes. This AD was prompted by 

new occurrences of certain cracked 

main landing gear (MLG) rear hinge 

pins. This AD requires identifying the 

serial number and part number of the 

MLG rear hinge pins, and replacing pins 

or the MLG if necessary. We are issuing 

this AD to detect and correct cracked 

rear hinge pins, which could lead to 

MLG structural failure, possibly 

resulting in collapse of the MLG and 

consequent injury to the occupants of 

the airplane. 

DATES: This AD becomes effective 

December 29, 2015. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

December 29, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2015-0682; or 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 ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre 

Nadot, 31712 Blagnac Cedex, France; 

telephone +33 (0) 5 62 21 62 21; fax +33 

(0) 5 62 21 67 18; email 

continued.airworthiness@atr.fr; Internet 

http://www.aerochain.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

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