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, 


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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) to 

reflect 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 


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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 a 

detailed 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 


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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: 


rmajette on DSK2TPTVN1PROD with PROPOSALS