78694 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 

establishes those dose rates, would be 

most appropriately addressed as a 

petition for rulemaking pursuant to 10 

CFR 2.802. Therefore, this rule will 

become effective as scheduled. 

Dated at Rockville, Maryland, this 20th day 

of December 2013. 

For the Nuclear Regulatory Commission. 

Helen Chang, 

Acting Chief, Rules, Announcements, and 

Directives Branch, Division of Administrative 

Services, Office of Administration. 

[FR Doc. 2013–31080 Filed 12–26–13; 8:45 am] 

BILLING CODE 7590–01–P 

FEDERAL HOUSING FINANCE 

AGENCY 

12 CFR Part 1238 

[No. 2013–N–19] 

Orders: Supplemental Orders on 

Reporting by Regulated Entities of 

Stress Testing Results as of 

September 30, 2013 

AGENCY: Federal Housing Finance 

Agency. 

ACTION: Orders. 

SUMMARY: In this document, the Federal 

Housing Finance Agency (FHFA) 

provides notice that it issued Orders to 

supplement its Orders dated November 

26, 2013, with respect to reporting 

under section 165(i)(2) of the DoddFrank Wall Street Reform and Consumer 

Protection Act (Dodd-Frank Act). 

DATES: Each Order is effective on the 

date signed. 

FOR FURTHER INFORMATION CONTACT: Naa 

Awaa Tagoe, Senior Associate Director, 

Office of Financial Analysis, Modeling 

and Simulations, (202) 649–3140, 

naaawaa.tagoe@fhfa.gov; Stefan 

Szilagyi, Examination Manager, 

FHLBank Modeling, FHLBank Risk 

Modeling Branch, (202) 649–3515, 

stefan.szilagy@fhfa.gov; or Mark D. 

Laponsky, Deputy General Counsel, 

Office of General Counsel, (202) 649– 

3054 (these are not toll-free numbers), 

mark.laponsky@fhfa.gov. The telephone 

number for the Telecommunications 

Device for the Hearing Impaired is (800) 

877–8339. 

SUPPLEMENTARY INFORMATION: 

I. Background 

FHFA is responsible for ensuring that 

the regulated entities operate in a safe 

and sound manner, including the 

maintenance of adequate capital and 

internal controls, that their operations 

and activities foster liquid, efficient, 

competitive, and resilient national 

housing finance markets, and that they 

carry out their public policy missions 

through authorized activities. See 12 

U.S.C. 4513. These Supplemental 

Orders are being issued under 12 U.S.C. 

4514(a), which authorizes the Director 

of FHFA to require by Order that the 

regulated entities submit regular or 

special reports to FHFA and establishes 

remedies and procedures for failing to 

make reports required by Order. The 

Supplemental Orders provide to the 

regulated entities two additional 

appendices of scenario assumptions to 

be used for stress testing. 

II. Orders 

For the convenience of the affected 

parties, the text of the Supplemental 

Orders, without appendices, follows 

below in its entirety. You may access 

these Orders with Appendices 11 and 

12 from FHFA’s Web site at http://

www.fhfa.gov/Default.aspx?Page=440. 

The Supplemental Orders and Summary 

Instructions and Guidance will be 

available for public inspection and 

copying at the Federal Housing Finance 

Agency, Eighth Floor, 400 Seventh St. 

SW., Washington, DC 20024. To make 

an appointment, call (202) 649–3804. 

The text of the Supplemental Orders 

is as follows: 

Federal Housing Finance Agency 

Order Nos. 2013–OR–B–3, 2013–OR–FNMA– 

3, and 2013–OR–FHLMC–3 

SUPPLEMENTAL ORDER ON REPORTING 

BY REGULATED ENTITIES OF STRESS 

TESTING RESULTS AS OF SEPTEMBER 30, 

2013 

Whereas, section 165(i)(2) of the DoddFrank Wall Street Reform and Consumer 

Protection Act (‘‘Dodd-Frank Act’’) requires 

certain financial companies with total 

consolidated assets of more than $10 billion, 

and which are regulated by a primary Federal 

financial regulatory agency, to conduct 

annual stress tests to determine whether the 

companies have the capital necessary to 

absorb losses as a result of adverse economic 

conditions; 

Whereas, FHFA’s rule implementing 

section 165(i)(2) of the Dodd-Frank Act is 

codified as 12 CFR part 1238 and requires 

that ‘‘[e]ach regulated entity must file a 

report in the manner and form established by 

FHFA.’’ 12 CFR § 1238.5(b); 

Whereas, on November 26, 2012, FHFA 

issued an Order to each regulated entity 

accompanied by appendices numbered 1 

through 10 and amended Summary 

Instructions and Guidance relating to the 

performance of stress tests as of September 

30, 2013, and the reporting of the results of 

such tests; 

Whereas, FHFA’s Acting Director has 

determined that it is appropriate to 

supplement the appendices to the November 

26, 2013 Orders with two additional 

appendices; 

Whereas, section 1314 of the Safety and 

Soundness Act, 12 U.S.C. § 4514(a) 

authorizes the Director of FHFA to require 

regulated entities, by general or specific 

order, to submit such reports on their 

management, activities, and operations as the 

Director considers appropriate. 

Now therefore, it is hereby ordered as 

follows: 

Each regulated entity shall report to FHFA 

and to the Board of Governors of the Federal 

Reserve System the results of stress testing as 

required by 12 CFR § 1238, in the form and 

with the content described therein and in the 

Summary Instructions and Guidance 

accompanying the November 26, 2013 

Orders, and using the scenarios provided in 

Appendices 1 through 10 to those Orders and 

Appendices 11 and 12 that accompany this 

Order. 

This Order is effective immediately. 

Signed at Washington DC, this 13th day of 

December, 2013. 

Edward J. DeMarco, 

Acting Director, Federal Housing Finance 

Agency. 

Dated: December 13, 2013. 

Edward J. DeMarco, 

Acting Director, Federal Housing Finance 

Agency. 

[FR Doc. 2013–30567 Filed 12–26–13; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0365; Directorate 

Identifier 2012–NM–223–AD; Amendment 

39–17704; AD 2013–25–08] 

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) 2009–24– 

09 for all Airbus Model A330–200 and 

–300 series airplanes, and Model A340– 

200 and –300 series airplanes. AD 2009– 

24–09 required a repetitive inspection 

program on certain check valves in the 

hydraulic systems that includes, among 

other things, inspections for lock wire 

presence and integrity, traces of seepage 

or black deposits, proper torque, 

alignment of the check valve and 

manifold, installing new lock wire, and 

corrective actions if needed. This new 

AD expands the applicability, reduces 

the compliance time, changes torque 

values of the check valve tightening, 

and requires a repetitive inspection 

program for certain check valves in the 


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Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 78695 

hydraulic systems on airplanes that 

have had a certain modification 

embodied during production or inservice. This AD was prompted by 

multiple reports of hydraulic line check 

valves loosening. We are issuing this AD 

to detect and correct such check valve 

loosening, which could result in 

hydraulic leaks, possibly leading to the 

loss of all three hydraulic systems and 

consequent loss of control of the 

airplane. 

DATES: This AD becomes effective 

January 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of December 14, 2009 (74 FR 

62208, November 27, 2009). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0365; or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

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 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on May 8, 2013 (78 FR 26716), 

and proposed to supersede AD 2009– 

24–09, Amendment 39–16068 (74 FR 

62208, November 27, 2009). The NPRM 

proposed to correct an unsafe condition 

for the specified products. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0244R1, 

dated January 25, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

An A330 operator experienced a yellow 

hydraulic circuit low level due to a loose 

check valve, Part Number (P/N) CAR401. 

During the inspection on the other two 

hydraulic systems, the other three check 

valves P/N CAR401 were also found to be 

loose with their lock wire broken in two 

instances. Airbus A340 aeroplanes are also 

equipped with P/N CAR401 high pressure 

manifold check valves. 

Additional cases of P/N CAR401 check 

valve loosening have been reported on 

aeroplanes having accumulated more than 

1,000 [total] flight cycles (FC). The check 

valve fitted on the Yellow hydraulic system 

is more affected, due to additional system 

cycles induced by cargo door operation. 

This condition, if not detected and 

corrected, could result in hydraulic leaks, 

possibly leading to the loss of all three 

hydraulic systems and consequent loss of 

control of the aeroplane. 

To address this unsafe condition, EASA 

issued Emergency AD 2009–0223–E (http://

ad.easa.europa.eu/blob/easa_ad_2009_

0223E_superseded.pdf/EAD_2009-0223-E_1) 

[which corresponds to FAA AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009)] to require an inspection 

programme to detect any check valve 

loosening and if necessary, to apply the 

applicable corrective actions. 

EASA AD 2010–0145 (http://

ad.easa.europa.eu/blob/easa_ad_2010_0145_

Superseded.pdf/AD_2010-0145_1), which 

superseded EASA EAD 2009–0223–E 

retaining its requirements, was issued to 

expand the applicability to the newly 

certified models A330–223F and A330–243F. 

Prompted by further reported in-service 

events of check valve P/N CAR401 loosening 

before reaching the threshold of 700 FC, 

EASA AD 2011–0139 (http://

ad.easa.europa.eu/blob/easa_ad_2011_0139_

superseded.pdf/AD_2011-0139_1), which 

superseded EASA AD 2010–0145, retaining 

its requirements, was issued to: 

—Extend the requirement to identify the P/ 

N CAR401 check valves to all aeroplanes, 

and to 

—reduce the inspection threshold for 

aeroplanes fitted with check valve P/N 

CAR401, either installed in production 

through Airbus modification 54491, or 

installed in service through Airbus Service 

Bulletin (SB) A330–29–3101 or Airbus SB 

A340–29–4078. 

EASA AD 2012–0070 (http://

ad.easa.europa.eu/blob/easa_ad_2012_0070_

Correction_superseded.pdf/AD_2012-0070_

1), which superseded EASA AD 2011–0139, 

retaining its requirements, was issued to 

require an increased torque value of the 

check valve tightening and High Pressure 

(HP) manifold re-identification. 

Since EASA AD 2012–0070 was issued, 

additional in-service events have been 

reported on aeroplanes fitted with check 

valves on which the increased torque value 

had been applied. Based on those events, it 

has been concluded that the action to retorque the check valves with an increased 

value is not a satisfactory terminating action 

for addressing the issue of those check 

valves. 

For the reasons described above, this new 

[EASA] AD partially retains the requirements 

of EASA AD 2012–0070, which is 

superseded. Additionally, for aeroplanes 

equipped with P/N CAR401 on which the 

increased torque value has been applied, this 

new [EASA] AD requires repetitive 

inspections of the check valves and HP 

manifolds. Finally, this [EASA] AD also 

requires application of a lower torque value 

when a check valve P/N CAR401 is installed 

on an aeroplane. 

This [EASA] AD is considered to be an 

interim action and further AD action may 

follow. 

Note: the reporting and the torque value 

increase requirements for check valves P/N 

CAR401 of EASA AD 2012–0070 are no 

longer part of this new [EASA] AD. 

You may obtain further information by 

examining the MCAI in the AD docket. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0365- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Change Compliance Time 

US Airways requested that we change 

the compliance time in paragraph (j) of 

the NPRM (78 FR 26716, May 8, 2013) 

to 1,000 flight hours after the effective 

date of the AD, or within 1,000 flight 

hours after the date of issuance of the 

original export certificate of 

airworthiness, whichever occurs later. 

US Airways stated that this will provide 

an inspection threshold for new 

airplane deliveries. 

We disagree with changing the 

compliance time to base it, in part, on 

the date of issuance of the original 

export certificate of airworthiness. In 

developing appropriate compliances 

time for this final rule, we considered 

the safety issue as well as the 

recommendations of the manufacturer, 

the availability of necessary repair parts, 

and the practical aspect of 

accomplishing the required inspection 

within an interval of time that 

corresponds to the normal maintenance 

schedules of most affected operators. In 

addition, the compliance time of 

‘‘Within 1,000 flight hours after the 

effective date of this AD’’ specified in 

paragraph (j) of this final rule 

corresponds with the compliance time 

given in the MCAI. We have not 

changed this final rule in this regard. 

Change Made to This Final Rule 

We reformatted paragraph (n) of this 

final rule, and removed an unnecessary 

sentence that appeared at the end of 

paragraph (n)(2) of the NPRM (78 FR 

26716, May 8, 2013). 


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78696 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

26716, May 8, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 26716, 

May 8, 2013). 

Costs of Compliance 

We estimate that this AD affects 67 

airplanes of U.S. registry. 

The actions that are required by AD 

2009–24–09, Amendment 39–16068 (74 

FR 62208, November 27, 2009), and 

retained in this AD take about 8 workhours per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $680 per 

product. 

We estimate that it will take about 2 

work-hours per product to comply with 

the new requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$11,390, or $170 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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-2013-0365; or in 

person at the Docket Operations office 

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) 

2009–24–09, Amendment 39–16068 (74 

FR 62208, November 27, 2009), and 

adding the following new AD: 

2013–25–08 Airbus: Amendment 39–17704. 

Docket No. FAA–2013–0365; Directorate 

Identifier 2012–NM–223–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 31, 2014. 

(b) Affected ADs 

This AD supersedes AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic power. 

(e) Reason 

This AD was prompted by multiple reports 

of hydraulic line check valves loosening. We 

are issuing this AD to detect and correct such 

check valve loosening, which could result in 

hydraulic leaks, possibly leading to the loss 

of all three hydraulic systems and 

consequent loss of control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Actions 

This paragraph restates the requirements of 

paragraph (g) of AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009). Except for Model A330– 

223F and A330–243F airplanes: Do the 

actions required by paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) For airplanes that do not have Airbus 

Modification 54491 embodied in production, 

or Airbus Service Bulletin A330–29–3101 or 

Airbus Service Bulletin A340–29–4078 

embodied in service: Within 100 flight cycles 

or 28 days after December 14, 2009 (the 

effective date of AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009)), whichever occurs first, 

inspect the check valves on the blue, green, 

and yellow hydraulic systems to identify 

their part numbers (P/Ns), in accordance 

with the instructions of Airbus All Operators 

Telex (AOT) A330–29A3111, Revision 1, 

dated October 8, 2009 (for Model A330–200 

and –300 series airplanes); or AOT A340– 

29A4086, Revision 1, dated October 8, 2009 

(for Model A340–200 and –300 series 

airplanes). Accomplishment of the inspection 

required by paragraph (h) of this AD 

terminates the requirements of this 

paragraph. 

(i) If check valves having P/N CAR401 are 

installed on all three hydraulic systems, 

before further flight, do the actions specified 

in paragraph (g)(2)(i) of this AD. After 

accomplishing the actions required by 

paragraph (g)(2)(i) of this AD, do the actions 

specified in paragraphs (g)(2)(ii) and 

(g)(2)(iii) of this AD at the applicable 

compliance times specified in those 

paragraphs. Accomplishment of the 

inspection required by paragraph (i) of this 

AD terminates the requirements of this 

paragraph. 


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(ii) If check valves having P/N CAR401 are 

not installed on all three hydraulic systems, 

no further action is required by this 

paragraph until any check valve having P/N 

CAR400 is replaced with a check valve 

having P/N CAR401. If any check valve 

having P/N CAR400 is replaced by a check 

valve having P/N CAR401, before further 

flight, do the inspection specified in 

paragraph (g)(1) of this AD to determine if all 

three hydraulic systems are equipped with 

check valves having P/N CAR401. 

Accomplishment of the inspection required 

by paragraph (h) of this AD terminates the 

requirements of this paragraph. 

(2) For airplanes on which Airbus 

Modification 54491 was embodied in 

production, or Airbus Service Bulletin A330– 

29–3101 or Airbus Service Bulletin A340– 

29–4078 was embodied in service, do the 

actions specified in paragraphs (g)(2)(i), 

(g)(2)(ii), and (g)(2)(iii) of this AD. 

(i) Except as required by paragraph (g)(1)(i) 

of this AD, at the applicable times specified 

in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of 

this AD, as applicable: Do the inspection 

program (detailed inspection of the lock wire 

for presence and integrity, a detailed 

inspection for traces of seepage or black 

deposits, and an inspection for proper 

torque) on yellow and blue high pressure 

manifolds, install new lock wires, and do all 

applicable corrective actions, in accordance 

with the instructions of paragraph 4.1.1 of 

Airbus AOT A330–29A3111, Revision 1, 

dated October 8, 2009 (for Model A330–200 

and –300 series airplanes); or AOT A340– 

29A4086, Revision 1, dated October 8, 2009 

(for Model A340–200 and –300 series 

airplanes). Do all applicable corrective 

actions before further flight. Accomplishment 

of the inspection required by paragraph (h)(1) 

of this AD terminates the requirements of this 

paragraph. 

(A) For airplanes on which Airbus 

Modification 54491 has been embodied in 

production: At the later of the times specified 

in paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) 

of this AD. 

(1) Before the accumulation of 1,000 total 

flight cycles since first flight but no earlier 

than the accumulation of 700 total flight 

cycles since first flight. 

(2) Within 100 flight cycles or 28 days after 

December 14, 2009 (the effective date of AD 

2009–24–09, Amendment 39–16068 (74 FR 

62208, November 27, 2009)), whichever 

occurs first. 

(B) For airplanes on which Airbus Service 

Bulletin A330–29–3101 or A340–29–4078 

was embodied in service: At the later of the 

times specified in paragraphs (g)(2)(i)(B)(1) 

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

(1) Within 1,000 flight cycles since the 

embodiment of Airbus Service Bulletin 

A330–29–3101 or A340–29–4078 but no 

earlier than 700 flight cycles after the 

embodiment of Airbus Service Bulletin 

A330–29–3101 or A340–29–4078. 

(2) Within 100 flight cycles or 28 days after 

December 14, 2009 (the effective date of AD 

2009–24–09, Amendment 39–16068 (74 FR 

62208, November 27, 2009)), whichever 

occurs first. 

(ii) Within 900 flight hours after 

accomplishment of paragraph (g)(2)(i) of this 

AD, do the inspection program (detailed 

inspection of the lock wire for presence and 

integrity, a detailed inspection for traces of 

seepage or black deposits, and an inspection 

for proper torque) and install a new lock wire 

on the green high pressure manifold; and do 

an inspection (detailed inspection for traces 

of seepage or black deposits, and detailed 

inspection to determine alignment of the 

check valve and manifold) on the yellow and 

blue high pressure manifolds, and do all 

applicable corrective actions; in accordance 

with the instructions of paragraph 4.1.2 of 

Airbus AOT A330–29A3111, Revision 1, 

dated October 8, 2009 (for Model A330–200 

and –300 series airplanes); or AOT A340– 

29A4086, Revision 1, dated October 8, 2009 

(for Model A340–200 and –300 series 

airplanes). Do all applicable corrective 

actions before further flight. Accomplishment 

of the inspection program required by 

paragraph (i) of this AD terminates the 

requirements of this paragraph. 

(iii) Within 900 flight hours after 

accomplishment of paragraph (g)(2)(ii) of this 

AD, and thereafter at intervals not to exceed 

900 flight hours, do the inspection program 

(detailed inspection for traces of seepage or 

black deposits, and detailed inspection to 

determine alignment of the check valve and 

manifold) on the green, yellow, and blue high 

pressure manifolds, and do all applicable 

corrective actions, in accordance with the 

instructions of paragraph 4.1.3 of Airbus 

AOT A330–29A3111, Revision 1, dated 

October 8, 2009 (for Model A330–200 and 

–300 series airplanes); or AOT A340– 

29A4086, Revision 1, dated October 8, 2009 

(for Model A340–200 and –300 series 

airplanes). Do all applicable corrective 

actions before further flight. Accomplishment 

of the inspection program required by 

paragraph (i) of this AD terminates the 

requirements of this paragraph. 

(h) New Inspection and Actions 

For airplanes equipped with check valves 

having P/N CAR400; and for airplanes 

equipped with check valves having P/N 

CAR401, except for airplanes on which 

Airbus Modification 201384 has been 

embodied during production, or on which 

Airbus Service Bulletin A330–29–3119 (for 

Model A330–200, –200F, and –300 series 

airplanes) or Airbus Service Bulletin A340– 

29–4091 (for Model A340–200 and –300 

series airplanes) has been embodied in 

service: Within 900 flight hours after the 

effective date of this AD, inspect the check 

valves on the blue, green, and yellow 

hydraulic systems to identify their part 

numbers, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–29–3111, 

Revision 02, dated June 23, 2011 (for Model 

A330–200, –200F and –300 series airplanes); 

or Airbus Mandatory Service Bulletin A340– 

29–4086, Revision 02, dated June 23, 2011 

(for Model A340–200 and –300 series 

airplanes). Accomplishment of the actions 

required by this paragraph terminates the 

requirements specified in paragraphs (g)(1) 

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

(1) If check valves having P/N CAR401 are 

installed on all three hydraulic systems: 

Before further flight, do the inspection 

program (detailed inspection for red mark 

presence and alignment integrity of the check 

valve and manifold, a detailed inspection for 

traces of seepage or black deposits, and an 

inspection for proper torque) on yellow and 

blue high pressure manifolds, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–29– 

3111, Revision 02, dated June 23, 2011 (for 

Model A330–200, –200F, and –300 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–29–4086, Revision 02, dated 

June 23, 2011 (for Model A340–200 and –300 

series airplanes). Accomplishment of the 

actions required by this paragraph terminates 

the requirements specified in paragraph 

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

(2) If check valves having P/N CAR401 are 

not installed on all three hydraulic systems, 

no further action is required by this 

paragraph until any check valve having P/N 

CAR400 is replaced with a check valve 

having P/N CAR401. If any check valve 

having P/N CAR400 is replaced by a check 

valve having P/N CAR401: Before further 

flight after such replacement, do the actions 

specified in paragraph (h) of this AD, to 

determine if all three hydraulic systems are 

equipped with check valves having P/N 

CAR401. If check valves having P/N CAR401 

are installed on all three hydraulic systems: 

Before further flight, do the actions specified 

in paragraphs (h)(1) and (i) of this AD. 

(i) New Repetitive Inspection Program and 

Corrective Actions 

Within 900 flight hours after 

accomplishment of paragraph (h)(1) of this 

AD, do the inspection program (detailed 

inspection for red mark presence and 

alignment integrity of the check valve and 

manifold, a detailed inspection for traces of 

seepage or black deposits, and an inspection 

for proper torque) on the green, yellow, and 

blue system check valves, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–29– 

3111, Revision 02, dated June 23, 2011 (for 

Model A330–200, –200F, and –300 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–29–4086, Revision 02, dated 

June 23, 2011 (for Model A340–200 and –300 

series airplanes). Repeat the inspection 

program thereafter at intervals not to exceed 

900 flight hours. Do all applicable corrective 

actions before further flight. Accomplishment 

of the actions required by this paragraph 

terminates the requirements specified in 

paragraphs (g)(1)(i), (g)(2)(ii), and (g)(2)(iii) of 

this AD. 

(j) New Repetitive Inspection for Certain 

Airplanes 

For airplanes equipped with check valves 

having P/N CAR401 and on which Airbus 

Modification 201384 has been embodied 

during production, or on which Airbus 

Service Bulletin A330–29–3119 (for Model 

A330–200, –200F, and –300 series airplanes); 

or Airbus Service Bulletin A340–29–4091 

(for Model A340–200 and –300 series 

airplanes) has been embodied in service: 

Within 1,000 flight hours after the effective 

date of this AD, do a general visual 


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78698 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 

inspection of the green, yellow, and blue 

high pressure manifolds and check valves 

having P/N CAR401 for any sign of rotation 

of the check valve head, and for any signs of 

hydraulic fluid leakage or seepage (including 

black deposits), in accordance with the 

instructions of Airbus Alert Operators 

Transmission A29L001–12, dated October 11, 

2012. Repeat the inspection thereafter at 

interval not to exceed 900 flight hours. 

(k) New Corrective Action for Certain 

Airplanes 

If, during any inspection required by 

paragraph (j) of this AD, any sign of rotation 

of the check valve head is found, or any sign 

of hydraulic fluid leakage or seepage 

(including black deposits) is found: Before 

further flight, do all applicable corrective 

actions, in accordance with the instructions 

of Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(l) No Terminating Action 

Accomplishment of the corrective actions 

required by this AD does not constitute 

terminating action for the repetitive 

inspections required by this AD. 

(m) Replacement Check Valve Torque Value 

As of the effective date of this AD, at each 

replacement of a check valve with a check 

valve having P/N CAR401, apply a torque of 

141 to 143 newton metre (N.m) (103.98 to 

105.45 pounds-foot (lbf.ft)) during 

installation. 

(n) Credit for Previous Actions 

(1) This paragraph restates the credit 

specified in paragraph (g)(2)(iv) of AD 2009– 

24–09, Amendment 39–16068 (74 FR 62208, 

November 27, 2009). This paragraph provides 

credit for actions required by paragraph 

(g)(2)(i) of this AD, if those actions were 

performed before December 14, 2009 (the 

effective date of AD 2009–24–09), using the 

applicable service information specified in 

paragraphs (n)(1)(i) and (n)(1)(ii) of this AD. 

(i) Airbus AOT A330–29A3111, dated 

September 2, 2009 (for Model A330–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(ii) Airbus AOT A340–29A4086, dated 

September 2, 2009 (for Model A340–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service information specified in paragraphs 

(n)(2)(i) through (n)(2)(iv) of this AD. 

(i) Airbus AOT A330–29A3111, dated 

September 2, 2009 (for Model A330–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(ii) Airbus AOT A330–29A3111, Revision 

1, dated October 8, 2009 (for Model A330– 

200 and –300 series airplanes). 

(iii) Airbus AOT A340–29A4086, dated 

September 2, 2009, (for Model A340–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(iv) Airbus AOT A340–29A4086, Revision 

1, dated October 8, 2009 (for Model A340– 

200 and –300 series airplanes). 

(o) No Reporting 

Although the service information specified 

in paragraphs (o)(1) through (o)(5) of this AD 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(1) Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(2) Airbus Mandatory Service Bulletin 

A330–29–3111, Revision 02, dated June 23, 

2011. 

(3) Airbus Mandatory Service Bulletin 

A340–29–4086, Revision 02, dated June 23, 

2011. 

(4) Airbus AOT A330–29A3111, Revision 

1, dated October 8, 2009. 

(5) Airbus AOT A340–29A4086, Revision 

1, dated October 8, 2009. 

(p) 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. AMOCs 

approved for AD 2009–24–09, Amendment 

39–16068 (74 FR 62208, November 27, 2009), 

are approved as AMOCs for the 

corresponding provisions of this AD, except 

AMOC ANM–116–11–172 is not approved as 

an AMOC for the corresponding provisions of 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0244R1, dated January 25, 

2013, for related information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/ 

#!documentDetail;D=FAA-2013-0365-0003. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (r)(5) and (r)(6) of this AD. 

(r) 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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on January 31, 2014. 

(i) Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A330–29–3111, Revision 02, dated June 23, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A340–29–4086, Revision 02, dated June 23, 

2011. 

(4) The following service information was 

approved for IBR on December 14, 2009 (74 

FR 62208, November 27, 2009). 

(i) Airbus Alert Operators Telex A330– 

29A3111, Revision 1, dated October 8, 2009. 

Only the first page of this document contains 

the document number, revision level, and 

date; no other pages of this document contain 

this information. 

(ii) Airbus Alert Operators Telex A340– 

29A4086, Revision 1, dated October 8, 2009. 

Only the first page of this document contains 

the document number, revision level, and 

date; no other pages of this document contain 

this information. 

(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 review copies of the 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 

November 26, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–29998 Filed 12–26–13; 8:45 am] 

BILLING CODE 4910–13–P 


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