## 72398 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules

the inspection at the later of the times specified in paragraphs (h)(2)(ii)(A) and (h)(2)(ii)(B) of this AD.

(A) Within 20,600 flight cycles or 30,900 flight hours after first flight of the airplane,
whichever occurs first.

(B) Within 1,600 flight cycles or 2,400 flight hours after the effective date of this AD,
whichever occurs first.

(3) For ‘‘normal range operations’’ airplanes having an average flight time of 1.5 flight hours or more: Repeat the inspection at the applicable time required in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.

(i) For Model A300 F4–605R and F4–622R airplanes: Repeat the inspection thereafter at intervals not to exceed 9,000 flight cycles or 19,400 flight hours, whichever occurs first.

(ii) For Model A300 B4–600, B4–600R, and Model A300 C4–605R Variant F airplanes: Repeat the inspection thereafter at intervals not to exceed 7,100 flight cycles or 15,300 flight hours, whichever occurs first.

(4) For ‘‘short range operations’’ airplanes having an average flight time of less than 1.5 flight hours: Repeat the inspection at the applicable time required in paragraphs (h)(4)(i) and (h)(4)(ii) of this AD.

(i) For Model A300 F4–605R and F4–622R airplanes: Repeat the inspection thereafter at intervals not to exceed 9,700 flight cycles or 14,500 flight hours, whichever occurs first.

(ii) For Model A300 B4–600, B4–600R, and Model A300 C4–605R Variant F airplanes: Repeat the inspection thereafter at intervals not to exceed 7,600 flight cycles or 11,500 flight hours, whichever occurs first.

(i) Definition of Average Flight Time for Paragraph (h) of This AD

For the purpose of paragraph (h) of this AD, the Average Flight Time must be
established as follows:

(1) For the initial inspection, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles
at the effective date of this AD.

(2) For the first repeated inspection interval, the average flight time is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold.

(3) For all inspection intervals onwards, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections.

(j) New Requirement of This AD: Corrective Action for Any Cracking Found

If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. Accomplishing a repair does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD.

(k) Credit for Previous Actions

This paragraph provides credit for inspections required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using any of the service information identified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, which are not incorporated by reference in this AD.

(1) Airbus Service Bulletin A300–57–6028, Revision 04, dated October 25, 1999.

(2) Airbus Service Bulletin A300–57–6028, Revision 05, dated January 11, 2002.

(3) Airbus Service Bulletin A300–57–6028, Revision 06, dated May 17, 2006.

(l) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 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) AMOCs approved previously for AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995), are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

(m) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2014–0119, dated May 13, 2014, for related information. This MCAI may be
found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–4817.

(2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ 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 November 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–29443 Filed 11–18–15; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–4815; Directorate Identifier 2015–NM–112–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) 2015–03– 06, for all Airbus Model A330–200, A330–200 Freighter, A330–300, A340– 200, A340–300, A340–500, and A340– 600 series airplanes. AD 2015–03–06 currently requires repetitive inspections of the left-hand and right-hand wing main landing gear (MLG) rib 6 aft bearing lugs (forward and aft) to detect any cracks on the two lugs, and replacement if necessary. Since we issued AD 2015–03–06, we have received reports of additional cracking of the MLG rib 6 aft bearing lugs. This proposed AD would reduce certain compliance times. We are proposing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing.

**DATES** 

### : We must receive comments on this proposed AD by January 4, 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 proposed AD, contact Airbus SAS,


## 72399 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules

Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;

Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

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–2015– 4815; 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–2015–4815; Directorate Identifier 2015–NM–112–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 February 2, 2015, we issued AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015). AD 2015– 03–06 requires actions intended to
address an unsafe condition on all Airbus Model A330–200, A330–200 Freighter, A330–300, A340–200, A340– 300, A340–500, and A340–600 series airplanes.

Since we issued AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015), we have determined that it is necessary to introduce a more restrictive initial inspection threshold and a grace period for airplanes that have already exceeded the new
threshold.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0120, dated June 26, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus Model A330–200, A330–200 Freighter, A330–300, A340–200, A340–300, A340– 500, and A340–600 series airplanes. The

MCAI states:

During Main Landing Gear (MLG) lubrication, a crack was visually found in the MLG rib 6 aft bearing forward lug on one A330 in-service aeroplane. The crack had extended through the entire thickness of the forward lug at approximately the 4 o’clock position (when looking forward). It has been determined that a similar type of crack can develop on other aeroplane types that are listed in the Applicability paragraph.

This condition, if not detected and corrected, could affect the structural integrity
of the MLG attachment.

To address this situation, Airbus issued inspection Service Bulletin (SB) A330–57– 3096, SB A340–57–4104 and SB A340–57– 5009 to provide instructions for repetitive inspections of the gear rib lugs.

Prompted by these findings, EASA issued Emergency AD 2006–0364–E to require repetitive detailed visual inspections of the Left Hand (LH) and Right Hand (RH) wing MLG rib 6 aft bearing lugs.

Later, EASA issued AD 2007–0247–E, which superseded [EASA] AD 2006–0364–E,

to:

—expand the Applicability to all A330 and A340 aeroplanes, because the interference fit bushes cannot be considered as a terminating action, owing to unknown root cause; and

—add a second parameter quoted in flight hours (FH) to the inspection interval in order to reflect the aeroplane utilisation in service.

EASA AD 2007–0247–E was revised to correct a typographical error.

Since the first crack finding and issuance of the inspection SBs and related ADs, six further cracks were reported.

Consequently, EASA issued AD 2013–0271 [which corresponds to FAA AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015)], which retained the requirements of [EASA] AD 2007–0247R1–E, which was superseded, and expanded the Applicability of the [EASA] AD to the newly certified
models A330–223F and A330–243F. That AD also reduced the inspection threshold(s) toreflect the updated risk assessment and inservice experience. Since this [EASA] AD was issued, a new occurrence of crack finding was reported. Further analysis resulted in the need to reduce the threshold of the initial inspection.

Prompted by this finding, Airbus issued SB
A330–57–3096 Revision 06 to introduce a more restrictive initial inspection threshold and a grace period for aeroplanes which have already passed the new threshold.

For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2013–0271, which is superseded, and introduces reduced initial inspection thresholds.



### 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–2015–

4815.

Related Service Information Under 1

CFR Part 51

Airbus has issued Service Bulletin A330–57–3096, Revision 06, dated May 29, 2015. The service information describes procedures for detailed inspections to detect any cracking on the forward and aft lugs of the Left Hand (LH) and Right Hand (RH) wing MLG
Rib 6. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the

**ADDRESSES** 

### section of this NPRM.

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 the same type design.

Explanation of ‘‘RC’’ Procedures and
Tests in Service Information

The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and
tests from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD


## 72400 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules

compliance. The procedures and tests identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified
unsafe condition.

As specified in a Note under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and 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 alternative method of compliance (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 will require approval of

an AMOC.

Costs of Compliance

We estimate that this proposed AD affects 101 airplanes of U.S. registry.

The actions required by AD 2015–03– 06, Amendment 39–18102 (80 FR 8511, February 18, 2015), and retained in this proposed AD take about 2 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2015–03–06 is $170 per product.

This proposed AD reduces the initial compliance time but adds no new

actions.

We have received no definitive data that would enable us to provide cost
estimates for the on-condition actions specified in this proposed AD.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking

action.

Regulatory Findings

We determined that this 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) 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015), and adding the following new AD:

Airbus: Docket No. FAA–2015–4815;
Directorate Identifier 2015–NM–112–AD.

(a) Comments Due Date

We must receive comments by January 4,

2016.

(b) Affected ADs

This AD replaces AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015).

(c) Applicability

This AD applies to Airbus Model A330–
201, –202, –203, –223, –223F, –243, –243F
–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340– 211, –212, –213 –311, –312, –313, –541, and –642 airplanes; certificated in any category;
all manufacturer serial numbers.

(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

This AD was prompted by reports of cracking of the main landing gear (MLG) rib 6 aft bearing forward lug. We are issuing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Inspections

At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do adetailed inspection for cracking of the lefthand and right-hand wing MLG rib 6 aft bearing lugs (forward and aft), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3096, Revision 06, dated May 29, 2015 (for Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes); A340–57– 4104, Revision 04, dated October 17, 2013 (for Model A340–211, –212, –213, –311, –312, –313 airplanes); or A340–57–5009, Revision 03, dated October 17, 2013 (for Model A340–541 and –642 airplanes); as applicable.

(1) Within 24 months or 2,000 flight cycles, whichever occurs first since airplane first flight or since the last MLG support rib replacement, as applicable.

(2) Within 30 days after the effective date
of this AD.

(h) Repetitive Inspections

Repeat the inspection required by paragraph (g) of this AD thereafter at the time specified in paragraphs (h)(1) through (h)(7) of this AD, as applicable.

(1) For Model A330–201, –202, –203, –223, and –243 airplanes: Repeat the inspections at intervals not to exceed 300 flight cycles or 1,500 flight hours, whichever occurs first.

(2) For Model A330–223F and –243F airplanes: Repeat the inspections at intervals not to exceed 300 flight cycles or 900 flight hours, whichever occurs first.

(3) For Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes: Repeat the inspections at intervals not to exceed 300 flight cycles or 900 flight hours,
whichever occurs first.

(4) For Model A340–211, –212, and –213 airplanes: Repeat the inspections at intervals not to exceed 200 flight cycles or 800 flight hours, whichever occurs first.

(5) For Model A340–311 and –312 airplanes; and Model A340–313 airplanes (except weight variant (WV) 27): Repeat the inspections at intervals not to exceed 200 flight cycles or 800 flight hours, whichever
occurs first.

(6) For Model A340–313 (only WV27) airplanes: Repeat the inspections at intervals


## 72401 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules

not to exceed 200 flight cycles or 400 flight hours, whichever occurs first.

(7) For Model A340–541 and –642 airplanes: Repeat the inspections at intervals not to exceed 100 flight cycles or 500 flight hours, whichever occurs first.

(i) Corrective Action

If any crack is found during any inspection required by paragraphs (g) or (h) of this AD: Before further flight, replace the cracked MLG support rib 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). Replacement of an MLG support rib does not terminate the repetitive inspections required by paragraph (h) of this AD.

(j) Credit for Previous Actions

This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (j)(1) through (j)(15) of this AD.

(1) Airbus Service Bulletin A330–57A3096, dated December 5, 2006, which was incorporated by reference in AD 2007–03–04, Amendment 39–14915 (74 FR 4416, January 31, 2007).

(2) Airbus Service Bulletin A330–57A3096, Revision 01, dated April 18, 2007, which is not incorporated by reference by this AD.

(3) Airbus Service Bulletin A330–57–3096, Revision 02, dated August 13, 2007, which was incorporated by reference in AD 2007– 22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)).

(4) Airbus Service Bulletin A330–57–3096, Revision 03, dated October 24, 2012, which is not incorporated by reference by this AD.

(5) Airbus Service Bulletin A330–57–3096, Revision 04, dated February 6, 2013, which is not incorporated by reference in this AD.

(6) Airbus Service Bulletin A330–57–3096, Revision 05, dated October 17, 2013, which was incorporated by reference in AD 2015– 03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015).

(7) Airbus Service Bulletin A340–57A4104, dated December 5, 2006, which was incorporated by reference in AD 2007–03–04, Amendment 39–14915 (72 FR 4416, January 31, 2007).

(8) Airbus Service Bulletin A340–57–4104, Revision 01, dated August 13, 2007, which is not incorporated by reference in this AD.

(9) Airbus Service Bulletin A340–57–4104, Revision 02, dated September 5, 2007, which was incorporated by reference in AD 2007– 22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)).

(10) Airbus Service Bulletin A340–57– 4104, Revision 03, dated October 24, 2012, which is not incorporated by reference in this

AD.

(11) Airbus Service Bulletin A340– 57A5009, dated December 5, 2006, which was incorporated by reference in AD 2007– 03–04, Amendment 39–14915 (72 FR 4416, January 31, 2007). (12) Airbus Service Bulletin A340–57– 5009, Revision 01, dated August 13, 2007, which was incorporated by reference in AD 2007–22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)).

(13) Airbus Service Bulletin A340–57– 5009, Revision 02, dated October 24, 2012, which is not incorporated by reference in this

AD.

(14) Airbus Alert Operators Transmission A57L005–14, dated July 15, 2014, which is not incorporated by reference in this AD.

(15) Airbus Alert Operators Transmission A57L005–14, Revision 01, dated August 15, 2014, which is not incorporated by reference
in this AD.

(k) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement
in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

(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.

(l) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0120, dated June 26, 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–

2015–4815.

(2) 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 November 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–29442 Filed 11–18–15; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–4816; Directorate Identifier 2014–NM–238–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY**

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY**

### : We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This proposed AD was prompted by investigations that
revealed that the cover seal of the brake dual distribution valve (BDDV) was damaged and did not ensure efficient sealing. This proposed AD would require modifying the BDDV having certain part numbers; modifying the drain hose of the BDDV; checking for the presence of water, ice, and hydraulic fluid; and re-identifying the BDDV; and related investigative and corrective actions if necessary. We are proposing this AD to prevent damage to the BDDV, which could lead to water ingestion in the BDDV and freezing of the BDDV in flight, possibly resulting in loss of braking system function after landing.

**DATES** 

### : We must receive comments on this proposed AD by January 4, 2016.

**ADDRESSES** 

### : You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following
methods: