## 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


## 9375 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules

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.


## 9376 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules

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


## 9377 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules

(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);


## 9378 Federal Register / Vol. 81, No. 37 / Thursday, February 25, 2016 / Proposed Rules

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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(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 * * *