9374 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 

(m) Terminating Action 

Accomplishment of the actions required by 

paragraphs (k) and (l) of this AD terminate 

the requirements of paragraphs (g) and (i) of 

this AD. 

(n) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install or reinstall any barrel nut 

P/N SL4081C14SP1 at the forward engine 

mount assembly on any airplane, and only P/ 

N SL4750NA may be installed. 

(o) New Exceptions to Service Information 

Specifications 

(1) Where Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated May 

28, 2015, specifies a compliance time ‘‘after 

the original issue date of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 747–71–2332, Revision 1, dated May 

28, 2015, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(p) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (l) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (r) of this 

AD. 

(q) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (k) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 747–71–2332, 

dated May 30, 2014, which is not 

incorporated by reference in this AD. 

(r) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (s)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2013–24–12 

are approved as AMOCs for the 

corresponding provisions of this AD. 

(5) Except as required by paragraph (o)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (r)(5)(i) and (r)(5)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(s) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6428; fax: 425–917–6590; email: 

Nathan.p.weigand@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone: 206– 

544–5000, extension 1; fax: 206–766–5680; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on February 

15, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03690 Filed 2–24–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3701; Directorate 

Identifier 2015–NM–015–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–25– 

08, for all Airbus Model A330–200, 

–200 Freighter, and –300 series 

airplanes; and Model A340–200 and 

–300 series airplanes. AD 2013–25–08 

currently requires 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, 

installation of new lock wire, and 

corrective actions if needed. Since we 

issued AD 2013–25–08, Airbus has 

developed an improved check valve. 

This proposed AD would add airplanes 

to the applicability, and require 

modifying the green, blue and yellow 

high pressure hydraulic manifolds by 

replacing certain check valves with 

improved check valves, which would 

terminate the repetitive inspections 

required by this proposed AD. We are 

proposing this AD to detect and correct 

hydraulic check valve loosening; 

loosened valves could result in 

hydraulic leaks, possibly leading to the 

loss of all three hydraulic systems and 

consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by April 11, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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 


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the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3701; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2016–3701; Directorate Identifier 

2015–NM–015–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On November 26, 2013, we issued AD 

2013–25–08, Amendment 39–17704 (78 

FR 78694, December 27, 2013) (‘‘AD 

2013–25–08’’). AD 2013–25–08 requires 

actions intended to address an unsafe 

condition on all Airbus Model A330– 

200 and –300 series airplanes; and 

Model A340–200 and –300 series 

airplanes. 

Since we issued AD 2013–25–08, 

which superseded AD 2009–24–09 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union, has 

issued EASA Airworthiness Directive 

2015–0009, dated January 16, 2015 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition. 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 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 

—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. 

To address that, EASA issued AD 2012–0244, 

which partially retained the requirements of 

EASA AD 2012–0070, which was 

superseded. Additionally, for aeroplanes 

equipped with P/N CAR401 on which the 

increased torque value had been applied, 

EASA AD 2012–0244 required repetitive 

inspections of the check valves and HP 

manifolds. Finally, EASA AD 2012–0244 also 

required application of a lower torque value 

when a check valve P/N CAR401 is installed 

on an aeroplane. 

Note: The reporting and the torque value 

increase requirements for check valves P/N 

CAR401 of EASA AD 2012–0070 were no 

longer part of EASA AD 2012–0244. 

EASA AD was revised to clarify which 

actions are required for P/N CAR401 check 

valves, depending on applied (or not) torque 

value. 

Since EASA AD 2012–0244R1 (http:// 

ad.easa.europa.eu/blob/easa_ad_

2012_0244_R1_superseded.pdf/AD_2012- 

0244R1_1) was issued, Airbus developed an 

improved check valve P/N CAR402, which is 

embodied in production through Airbus 

modification 203972, and in service through 

associated Airbus SB A330–29–3125, or 

Airbus SB A340–29–4096, as applicable to 

aeroplane type. In addition, these SBs 

provide instructions about the torque value 

(between 230 and 250 Nm) and reidentification of HP manifolds after check 

valve P/N CAR402 installation. 

For the reasons described above, this [EASA] 

AD retains the requirements of EASA AD 

2012–0244R1, which is superseded, and 

requires the installation of check valves P/N 

CAR402 as terminating action to the 

repetitive inspections [and adds airplanes to 

the applicability]. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3701. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A330–29–3125, Revision 01, including 

Appendixes 01 and 02, dated July 30, 

2015; and Service Bulletin A340–29– 

4096, Revision 01, including 

Appendixes 01 and 02, dated July 30, 

2015. This service information describes 

procedures for modifying the green, 

blue, and yellow high pressure 

hydraulic manifolds by replacing each 

check valve having part number (P/N) 

CAR401 with an improved check valve 

having P/N CAR402. 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. 


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FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Explanation of a Certain Alternative 

Method of Compliance (AMOC) 

Paragraph (t)(1)(iii) of this proposed 

AD states that AMOC ANM–116–14– 

429 is not approved as an AMOC for the 

corresponding provisions of this AD. 

This AMOC defines a terminating action 

when Airbus Modification 203972 is 

introduced in production or when the 

Airbus Service Bulletin A330–29–3125, 

dated August 8, 2014, is embodied in 

service. This proposed AD will exclude 

from the applicability airplanes with 

Airbus Modification 203972 and will 

mandate actions in accordance with 

Airbus Service Bulletin A330–29–3125, 

Revision 01, including Appendixes 01 

and 02, dated July 30, 2015. 

Costs of Compliance 

We estimate that this proposed AD 

affects 88 airplanes of U.S. registry. 

The actions required by AD 2013–25– 

08, and retained in this proposed AD 

take about 10 work-hours per product, 

at an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2013–25–08 is $850 per 

product. 

We also estimate that it would take 

about 32 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $239,360, or $2,720 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

aircraft that might need these actions. 

According to the manufacturer, some 

of the costs of this proposed 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 available 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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) 

2013–25–08, Amendment 39–17704 (78 

FR 78694, December 27, 2013), and 

adding the following new AD: 

Airbus: Docket No. FAA–2016–3701; 

Directorate Identifier 2015–NM–015–AD. 

(a) Comments Due Date 

We must receive comments by April 11, 

2016. 

(b) Affected ADs 

This AD replaces AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013). 

(c) Applicability 

This AD applies to Airbus airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes; 

all manufacturer serial numbers except those 

on which Airbus modification 203972 has 

been embodied in production. 

(2) Model A340–211, –212, –213, –311, 

–312, and –313 airplanes; 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 

hydraulic 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 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013), with no changes. 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 


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(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. 

(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 Airbus 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) Retained Inspection, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013, with no changes. 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 January 31, 

2014 (the effective date of AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013)), 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 

Service Bulletin A330–29–3111, Revision 02, 

dated June 23, 2011 (for Model A330–200, 

–200F and –300 series airplanes); or Airbus 

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 Service Bulletin A330–29–3111, 

Revision 02, dated June 23, 2011 (for Model 

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

or Airbus 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) Retained Repetitive Inspection Program 

and Corrective Actions, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2013–25–08, Amendment 

39–17704 (78 FR 78694, December 27, 2013), 

with no changes. 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 Service Bulletin A330–29–3111, 

Revision 02, dated June 23, 2011 (for Model 

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


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or Airbus Service Bulletin A340–29–4086, 

Revision 02, dated June 23, 2011 (for Model 

A340–200 and –300 series airplanes). Do all 

applicable corrective actions before further 

flight. Repeat the inspection program 

thereafter at intervals not to exceed 900 flight 

hours. 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) Retained Repetitive Inspection for Certain 

Airplanes, With No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2013–25–08, Amendment 

39–17704 (78 FR 78694, December 27, 2013), 

with no changes. 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 

January 31, 2014 (the effective date of AD 

2013–25–08, Amendment 39–17704 (78 FR 

78694, December 27, 2013)), do a general 

visual 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) Retained Corrective Action for Certain 

Airplanes, With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013), with no changes. 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) Retained Provisions Regarding 

Terminating Action, With No Changes 

This paragraph restates the provisions of 

paragraph (l) of AD 2013–25–08, Amendment 

39–17704 (78 FR 78694, December 27, 2013), 

with no changes. Accomplishment of the 

corrective actions required by this AD does 

not constitute terminating action for the 

repetitive inspections required by this AD. 

(m) Retained Replacement Check Valve 

Torque Value, With No Changes 

This paragraph restates the requirements of 

paragraph (m) of AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013), with no changes. As of 

January 31, 2014 (the effective date of AD 

2013–25–08, Amendment 39–17704 (78 FR 

78694, December 27, 2013)), at each 

replacement of a check valve with a check 

valve having P/N CAR401, apply a torque of 

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

105.45 pounds-foot (lbf.ft)) during 

installation. 

(n) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the provisions of 

paragraph (n) of AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013), with no changes. 

(1) 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, Amendment 39–16068 (74 FR 

62208, November 27, 2009)), 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 

January 31, 2014 (the effective date of AD 

2013–25–08, Amendment 39–17704 (78 FR 

78694, December 27, 2013)) 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) Retained Provisions for Reporting, With 

No Changes 

This paragraph restates the provisions of 

paragraph (o) of AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013), with no changes. 

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) New Requirement of This AD: Modify 

Hydraulic Systems 

Within 36 months after the effective date 

of this AD, modify the green, blue, and 

yellow high pressure hydraulic manifolds by 

replacing each check valve having P/N 

CAR401 with an improved check valve 

having P/N CAR402, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–29–3125, Revision 01, 

including Appendixes 01 and 02, dated July 

30, 2015; or Airbus Service Bulletin A340– 

29–4096, Revision 01, including Appendixes 

01 and 02, dated July 30, 2015; as applicable. 

(q) New Requirement of This AD: Repetitive 

Inspection Terminating Action 

Modification of an airplane, as required by 

paragraph (p) of this AD, constitutes 

terminating action for the repetitive 

inspections required by this AD. 

(r) New Requirement of This AD: Parts 

Installation Limitations 

(1) For an airplane that, as of the effective 

date of this AD, has a check valve having P/ 

N CAR401 installed, after modification of an 

airplane as required by paragraph (p) of this 

AD, no person may install a check valve 

having P/N CAR401, on that airplane. 

(2) For an airplane that does not have a 

check valve having P/N CAR401 installed, as 

of the effective date of this AD, no person 

may install a check valve having P/N 

CAR401, on that airplane. 

(s) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (p) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A330–29–3125, dated August 8, 2014; or 

Airbus Service Bulletin A340–29–4096, 

dated August 8, 2014; as applicable; which 

are not incorporated by reference in this AD. 

(t) 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. 

(i) 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. 

(ii) AMOC ANM–116–14–180 R1, dated 

February 21, 2014, is approved as an AMOC 

for the corresponding provisions of this AD. 


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Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules 9379 

(iii) AMOC ANM–116–14–429, dated 

September 25, 2014, is not approved as an 

AMOC for the corresponding provisions of 

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 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. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(u) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0009, dated 

January 16, 2015, 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–2016–3701. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at 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. 

(3) 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 service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

15, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03699 Filed 2–24–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[REG–150349–12] 

RIN 1545–BL39 

Amendments to the Low-Income 

Housing Credit Compliance-Monitoring 

Regulations 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Notice of proposed rulemaking 

by cross-reference to temporary 

regulations. 

SUMMARY: In the Rules and Regulations 

section of this issue of the Federal 

Register, the IRS is issuing final and 

temporary regulations concerning the 

compliance-monitoring duties of a State 

or local housing credit agency (Agency) 

for purposes of the low-income housing 

credit. The final and temporary 

regulations revise and clarify certain 

rules relating to the requirements to 

conduct physical inspections and 

review low-income certifications and 

other documentation. The text of the 

temporary regulations also serves as the 

text of these proposed regulations. 

DATES: Comments and requests for a 

public hearing must be received by May 

25, 2016. 

ADDRESSES: Send submissions to: 

CC:PA:LPD:PR (REG–150349–12), room 

5203, Internal Revenue Service, P.O. 

Box 7604, Ben Franklin Station, 

Washington, DC 20044. Submissions 

may be hand delivered Monday through 

Friday between the hours of 8 a.m. and 

4 p.m. to: CC:PA:LPD:PR (REG–150349– 

12), Courier’s Desk, Internal Revenue 

Service, 1111 Constitution Avenue NW., 

Washington, DC. Submissions may also 

be sent electronically via the Federal 

eRulemaking Portal at 

www.regulations.gov (IRS REG–150349– 

12). 

FOR FURTHER INFORMATION CONTACT: 

Concerning the regulations, Jian H. 

Grant, (202) 317–4137, and Martha M. 

Garcia, (202) 317–6853 (not toll-free 

numbers); concerning submission of 

comments, the hearing, and/or to be 

placed on the building access list to 

attend the hearing, Oluwafunmilayo 

Taylor at (202) 317–6901 (not a toll-free 

number). 

SUPPLEMENTARY INFORMATION: 

Background 

Final and temporary regulations in 

the Rules and Regulations section of this 

issue of the Federal Register amend the 

Income Tax Regulations (26 CFR part 1) 

relating to section 42 and serve as the 

text for these proposed regulations. 

Special Analyses 

Certain IRS regulations, including this 

one, are exempt from the requirements 

of Executive Order 12866, as 

supplemented and reaffirmed by 

Executive Order 13563. Therefore, a 

regulatory assessment is not required. It 

also has been determined that section 

553(b) of the Administrative Procedure 

Act (5 U.S.C. chapter 5) does not apply 

to these regulations, and because the 

regulations do not impose a collection 

of information on small entities, the 

Regulatory Flexibility Act (5 U.S.C. 

chapter 6) does not apply. Pursuant to 

section 7805(f) of the Internal Revenue 

Code, this notice of proposed 

rulemaking will be submitted to the 

Chief Counsel for Advocacy of the Small 

Business Administration for comment 

on their impact on small business. 

Comments and Requests for Public 

Hearing 

Before these proposed regulations are 

adopted as final regulations, 

consideration will be given to any 

comments that are submitted timely to 

the IRS as prescribed in this preamble 

under the ‘‘ADDRESSES’’ heading. The 

Treasury Department and the IRS 

request comments on all aspects of the 

proposed rules. All comments will be 

available at www.regulations.gov or 

upon request. A public hearing will be 

scheduled if requested in writing by any 

person that timely submits written 

comments. If a public hearing is 

scheduled, notice of the date, time, and 

place for the public hearing will be 

published in the Federal Register. 

Drafting Information 

The principal authors of these 

regulations are Jian H. Grant and Martha 

M. Garcia, Office of the Associate Chief 

Counsel (Passthroughs and Special 

Industries). However, other personnel 

from the IRS and the Treasury 

Department participated in their 

development. 

List of Subjects in 26 CFR Part 1 

Income taxes, Reporting and 

recordkeeping requirements. 

Proposed Amendments to the 

Regulations 

Accordingly, 26 CFR part 1 is 

proposed to be amended as follows: 

PART 1—INCOME TAXES 

■ Paragraph 1. The authority citation 

continues to read in part as follows: 

Authority: 26 U.S.C. 7805 * * * 


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