34098 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 

no market agencies selling livestock 

through privately negotiated sales. The 

stockyards in which privately 

negotiated sales occurred now sell 

livestock in public auctions. While 

some employees may have retained a 

‘‘salesman’’ job title, these employees no 

longer perform those functions that 

made them key employees. 

GIPSA is requesting comments from 

livestock industry representatives that 

address the following: 

(1) Which of the following should be 

included as a key employee, and why: 

(a) Auctioneer 

(b) Clerk of Sale 

(c) Ringmen 

(d) Salesmen 

(e) Weighmaster/Weigher 

(f) Manager or Owner 

(2) If weighers are otherwise 

considered key employees, should a 

weigher be allowed to bid on livestock 

when: 

(a) The market scale is equipped with a 

digital indicator 

(b) Livestock are not sold by weight 

(3) If livestock scale operators remain 

on the list of key employees would you 

object to GIPSA referring to the 

livestock scale operator as the 

‘‘weigher’’ rather than the 

‘‘weighmaster’’ in 201.56(c)? 

GIPSA is also interested to hear 

comments on whether key employees 

may purchase livestock during a sale 

under specific circumstances, or for 

specific purposes, such as: 

(4) If a key employee would step 

down from the auctioneer’s booth or 

scale during a sale: 

(a) Could the key employee then bid 

on livestock for their own account from 

the bleachers with the other buyers as 

long as the employee provided no key 

services while doing so: 

(i) Should this be limited to a specific 

species; 

(ii) Should their time spent bidding or 

serving in a key capacity be 

documented, and if so, how; 

(iii) Should a key employee be 

allowed to return to the auctioneer’s 

booth or scale, to perform key employee 

duties, after bidding on livestock from 

the bleachers? 

(5) Should GIPSA allow a key 

employee to buy livestock for market 

support or to fill orders held by their 

employer, the market agency? 

(6) What is perceived to be the 

greatest impediment or barrier to 

effective competition at a market agency 

selling livestock on a commission basis? 

GIPSA welcomes any comments 

addressing these issues and any other 

aspects of the general subject of 

permitting key employees to purchase 

livestock from consignments to a market 

agency. 

Susan B. Keith, 

Acting Administrator, Grain Inspection, 

Packers and Stockyards Administration. 

[FR Doc. 2015–14538 Filed 6–12–15; 8:45 am] 

BILLING CODE 3410–KD–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1981; Directorate 

Identifier 2014–NM–204–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 A330–200 Freighter, 

A330–200, A330–300, A340–200, and 

A340–300 series airplanes. This 

proposed AD was prompted by reports 

that the inner bore of some main 

landing gear (MLG) unit bogie beams 

were insufficiently re-protected against 

corrosion after inspection or 

maintenance actions were 

accomplished. This proposed AD would 

require, for certain MLG units, 

determining which revision of the 

component maintenance manual (CMM) 

was used to accomplish the most recent 

MLG unit overhaul; a detailed 

inspection for missing or damaged 

paint, and if necessary, a detailed 

inspection of the cadmium plating for 

discrepancies, measurement of the 

depth of the cadmium plating, a general 

visual inspection of the base metal for 

corrosion or damage, a detailed 

inspection of repaired areas for cracking 

or corrosion; and corrective actions if 

necessary. We are proposing this AD to 

detect and correct corrosion in the bore 

of each MLG unit bogie beam, which 

could result in collapse of a MLG unit, 

and subsequent damage to the airplane 

and injury to occupants. 

DATES: We must receive comments on 

this proposed AD by July 30, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 Airbus service information 

identified in this proposed 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. For Messier-Dowty 

service information contact MessierDowty Limited, Cheltenham Road, 

Cloucester, GL2 9QH, England; 

telephone +44(0) 1452 712424; fax+ 

44(0) 1452 713821; Internet http://

www.messier-dowtycom). 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– 

1981; 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–2015–1981; Directorate Identifier 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 34099 

2014–NM–204–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0222, dated October 6, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Airbus 

Model A330–200 Freighter, A330–200, 

A330–300, A340–200, and A340–300 

series airplanes. The MCAI states: 

From in-service experience, it was found 

that the inner bore of some bogie beams had 

been insufficiently re-protected against 

corrosion after inspection and/or possible 

maintenance actions accomplished in this 

area (absence of corrosion inhibitor and 

damage to paint have been found in some 

specific areas). 

This condition, if not detected and 

corrected, could lead to corrosion on the bore 

of the bogie beam, potentially resulting in 

Main Landing Gear (MLG) collapse, 

ultimately resulting in damage to the 

aeroplane and injury to the occupants. 

To address this potential unsafe condition, 

Airbus issued Alert Operators Transmission 

(AOT) A32L004–14, providing inspection 

instructions for some aeroplane 

configurations. 

For the reasons described above, this 

[EASA] AD requires identification of the 

MLG units that are possibly affected, [a 

detailed] inspection [for missing or damaged 

paint] of the MLG Bogie Beam bore and, 

depending on findings, accomplishment of 

the applicable corrective actions. 

This [EASA] AD also prohibits the 

installation of MLG units that have been 

overhauled by using instructions from an 

earlier Components Maintenance Manual 

(CMM) revision. 

Required actions also include a detailed 

inspection of the cadmium plating for 

discrepancies (gray in color), 

measurement of the depth of the 

cadmium plating if necessary, and a 

general visual inspection of the base 

metal for corrosion or damage, and a 

detailed inspection of repaired areas for 

cracking or corrosion. Corrective actions 

include removing cadmium plating and 

repairing any cracked, corroded, or 

damaged areas; re-applying cadmium 

plating and paint; and re-applying 

temporary corrosion protection to the 

bores of the MLG bogie beams. 

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– 

1981. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Alert Operators 

Transmission A32L004–14, dated July 

28, 2014, including Appendices 1, 2, 3, 

and 4, which are not dated. This service 

information describes procedures for 

inspections of the bogie beam bore of 

the MLG. 

Messier-Dowty has issued the 

following service information, which 

describes procedures for inspections of 

the internal diameter of the bogie beam 

for corrosion. 

• Service Bulletin A33/34–32–272, 

including Appendices A, B, C, and D, 

dated November 16, 2007. 

• Service Bulletin A33/34–32–272, 

Revision 1, including Appendices A, B, 

C, and D, dated September 22, 2008. 

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 these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 89 airplanes of U.S. registry. 

We also estimate that it would take 

about 12 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 $90,780, or $1,020 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for any necessary follow-on 

actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed AD has been 

detailed in the Costs of Compliance 

section of this document and includes 

time for reviewing instructions, as well 

as completing and reviewing the 

collection of information. Therefore, all 

reporting associated with this proposed 

AD is mandatory. Comments concerning 

the accuracy of this burden and 

suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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; 


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34100 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 

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 adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–1981; 

Directorate Identifier 2014–NM–204–AD. 

(a) Comments Due Date 

We must receive comments by July 30, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus airplanes, 

certificated in any category, identified in 

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

(1) Model A330–201, A330–202, A330– 

203, A330–223, A330–223F, A330–243, 

A330–243F, A330–301, A330–302, A330– 

303, A330–321, A330–322, A330–323, A330– 

341, A330–342, and A330–343 airplanes; all 

manufacturer serial numbers; except those on 

which Airbus Modification 58896 has been 

embodied in production or embodied 

through Airbus Service Bulletin A330–32– 

3237. 

(2) Model A340–211, A340–212, A340– 

213, A340–311, A340–312, and A340–313 

airplanes; all manufacturer serial numbers; 

except those on which Airbus Modification 

58896 has been embodied in production or 

embodied through Airbus Service Bulletin 

A340–32–4279. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports that the 

inner bore of some main landing gear (MLG) 

unit bogie beams were insufficiently reprotected against corrosion after inspection 

or maintenance actions were accomplished. 

We are issuing this AD to detect and correct 

corrosion in the bore of each MLG unit bogie 

beam, which could result in collapse of a 

MLG unit, and subsequent damage to the 

airplane and injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Identification of Affected MLG Units 

Within 12 months after the effective date 

of this AD: For MLG units having a 201252 

series or 201490 series part number, 

determine the revision of the Airbus 

component maintenance manual (CMM) used 

to do the most recent MLG unit overhaul. If 

it is determined that the Airbus CMM 

revision specified in paragraph (g)(1) or (g)(2) 

of this AD was used to accomplish the most 

recent MLG unit overhaul: Within 12 months 

after the effective date of this AD, clean the 

area between the bogie pivot pin and the 

bogie beam bore of each MLG unit and do a 

detailed inspection for missing or damaged 

paint, in accordance with the instructions of 

Airbus Alert Operators Transmission 

A32L004–14 dated July 28, 2014. 

(1) For MLG units having a part number in 

the 201252 series: Airbus CMM 32–11–74, 

Revision 25 or earlier. 

(2) For MLG units having a part number in 

the 201490 series: Airbus CMM 32–12–05, 

Revision 20 or earlier. 

(h) Inspection of Cadmium Plating 

If, during the inspection required by 

paragraph (g) of this AD, any missing or 

damaged paint is found: Before further flight, 

do a detailed inspection of the cadmium 

plating for discrepancies, measure the depth 

of the plating as applicable, and do a general 

visual inspection of the base metal for 

corrosion or damage. If any discrepancy, 

damage, or corrosion is found, before further 

flight, do all applicable corrective actions, 

and do a detailed inspection of repaired areas 

for cracking or corrosion, in accordance with 

Airbus Alert Operators Transmission 

A32L004–14, dated July 28, 2014, except 

where Airbus Alert Operators Transmission 

A32L004–14, dated July 28, 2014, specifies to 

contact Messier-Dowty if cracking or 

corrosion is found in a repaired area, before 

further flight, repair 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). 

(i) Reporting Requirement 

At the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD, report the 

findings of the inspection required by 

paragraph (g) of this AD to Airbus, Customer 

Services Engineering—SEEL1, Attn: Philippe 

Kerangueven, Product Leader A330/A340, 

ATA–32, Landing Gear Systems, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; phone +33 (0) 5 67 19 18 42; 

fax +33 0 5 67 19 12–05; email 

philippe.kerangueven@airbus.com. The 

report must include the information specified 

in Appendix 2 of Airbus Alert Operators 

Transmission A32L004–14, dated July 28, 

2014. 

(1) If the inspection was done on or after 

the effective date of this AD: Within 90 days 

after that inspection. 

(2) If the inspection was done before the 

effective date of this AD: Within 90 days after 

the effective date of this AD. 

(j) Optional Method of Compliance 

Accomplishment of the boroscope 

inspection of the internal diameter of the 

bogie beam for corrosion or damage to the 

protective treatments, measurement of the 

depth of the protective treatments as 

applicable, and accomplishment of all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Messier-Dowty Service Bulletin A33/34–32– 

272, dated November 16, 2007; or Revision 

1, including Appendices A, B, C, and D, 

dated September 22, 2008; are acceptable for 

the corresponding actions required by 

paragraphs (g) and (h) of this AD for that 

MLG unit, provided the actions in the 

Messier-Dowty Service Bulletins identified in 

paragraphs (j)(1) through (j)(5) of this AD 

have not been accomplished on that MLG 

unit. Where Messier-Dowty Service Bulletin 

A33/34–32–272, dated November 16, 2007; 

or Revision 1, including Appendices A, B, C, 

and D, dated September 22, 2008; specify to 

contact Messier-Dowty for repair 

information, the repair must be accomplished 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(1) Messier-Dowty Service Bulletin A33/

34–32–285, dated July 9, 2010. 

(2) Messier-Dowty Service Bulletin A33/

34–32–285, Revision 1, dated October 4, 

2011. 

(3) Messier-Dowty Service Bulletin A33/

34–32–285, Revision 2, dated October 4, 

2012. 

(4) Messier-Dowty Service Bulletin A33/

34–32–285, Revision 3, dated September 11, 

2013. 

(5) Messier-Dowty Service Bulletin A33/

34–32–285, Revision 4, dated January 23, 

2014. 

Note 1 to paragraph (j) of this AD: 

Inspections done using the instructions in 

Messier-Dowty Service Bulletin A33/34–32– 

285, Revision 5, dated August 14, 2014, do 

not affect the optional method of compliance 

provided by this paragraph. 

(k) Parts Installation Limitation 

As of the effective date of this AD, any 

overhauled MLG unit having a 201252 series 

or 201490 series part number may be 

installed on an airplane, provided the most 

recent MLG overhaul was done using an 

Airbus CMM that is not specified in 

paragraph (g)(1) or (g)(2) of this AD, or, prior 

to installation, the MLG unit passes the 

inspection required by paragraph (g) of this 

AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
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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: 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0222, dated 

October 6, 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– 

2015–1981. 

(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 June 3, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14229 Filed 6–12–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1429; Directorate 

Identifier 2014–NM–246–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 A319–113, A319–114, 

A320–211, and A320–212 airplanes. 

This proposed AD was prompted by a 

report that the aft mount pylon bolts of 

the CFM56–5 engines may have been 

installed using the wrong torque values. 

This proposed AD would require 

identification of engines that were 

installed using the wrong torque values 

and re-torque of the four aft mount 

pylon bolts of those engines. We are 

proposing this AD to detect and correct 

improper torque of the aft mount pylon 

bolts, which, if combined with any 

maintenance damage, could lead to aft 

engine mount failure, possibly resulting 

in engine detachment and consequent 

reduced control of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 30, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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, 

Airworthiness Office—EIAS, 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 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– 

1429; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1405; 

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–2015–1429; Directorate Identifier 

2014–NM–246–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 


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