3510 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2004–13–02, 

Amendment 39–13682 (69 FR 35237, June 

24, 2004), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

and (h) of this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: Bill.Ashforth@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on January 

14, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00955 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1043; Directorate 

Identifier 2013–NM–079–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 all 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and Model A340–200 and 

A340–300 series airplanes. This 

proposed AD was prompted by reports 

of cracked support strut body ends at a 

certain frame location of the trimmable 

horizontal stabilizer (THS). This 

proposed AD would require repetitive 

inspections for cracking of the strut 

ends of the THS support located at a 

certain frame in the tail cone, and 

replacement if necessary; and 

reinstallation or installation of 

reinforcing clamps on certain strut ends. 

We are proposing this AD to detect and 

correct cracked support strut body ends 

of the THS, which could lead to the loss 

of all four THS support struts and which 

would make the remaining structure 

unable to carry limit loads, resulting in 

the loss of the horizontal tail plane. 

DATES: We must receive comments on 

this proposed AD by March 9, 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 SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

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–2014– 

1043; 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–2014–1043; Directorate Identifier 

2013–NM–079–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 2014–0068, dated March 18, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Airbus Model 

A330–200, A330–200 Freighter, and 

A330–300 series airplanes; and Model 

A340–200 and A340–300 series 

airplanes. The MCAI states: 

During scheduled maintenance on A330 

aeroplanes, several Trimmable Horizontal 

Stabilizer (THS) support struts at frame (FR) 

91 were found cracked at strut body ends. 

The THS is supported and articulated at FR 

91 by four struts to fix the hinges (Y-bolts) 

and keep the structural integrity in lateral 

direction. 

Analysis revealed that cracks can reduce 

ability of the support struts to carry specified 

tension loads. 

This condition, if not detected and 

corrected, could lead to the loss of all four 

THS support struts at FR91, which would 

make the remaining structure unable to carry 

limit loads, resulting in the loss of Horizontal 

Tail Plane. 

A340–500/600 aeroplanes are not affected 

by this [EASA] AD as different material is 

used on THS support struts. 

To address this potentially unsafe 

condition, EASA issued AD 2013–0076 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0076_superseded.pdf/AD-2013-0076_1] 

to require repetitive special detailed 

inspections [high frequency eddy current 

(HFEC) inspections for cracking] of all 8 strut 

ends of the THS support located at FR91 in 

the tail cone and, depending on findings, 

replacement of THS support struts. That 


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[EASA] AD also required, for aeroplanes on 

which Airbus Modification 203493 had not 

been embodied in production, or Airbus 

Service Bulletin (SB) A330–53–3204 or SB 

A340–53–4199, as applicable, has not been 

embodied in service, the installation of a 

clamping device on each support strut end to 

stop growth of possible cracks (crack stopper 

function) in order to secure integrity of the 

struts. 

Since issuance of EASA AD 2013–0076, it 

has been discovered that several aeroplanes 

are fitted with another strut configuration 

(SARMA Strut) [Societe ́ Anonyme de 

Recherche Me ́canique Applique ́e] than the 

TAC (Technical Airborne Components 

Industries) strut, which caused the other strut 

not to be considered. Consequently, Airbus 

revised Airbus SB A330–53–3206 and SB 

A340–53–4208, accordingly in order to add 

a one-time [HFEC] inspection [for cracking] 

for SARMA struts and in case of finding to 

replace it with a TAC strut and thereafter to 

accomplish repetitive inspections and EASA 

issued AD 2013–0219 [http://

ad.easa.europa.eu/blob/easa_ad_2013_0219_

superseded.pdf/AD-2013-0219_1], which is 

superseded, and required accomplishment of 

the instructions as specified in the latest 

revision of each SB, as applicable. 

Since issuance of EASA AD 2013–0219, 

based on the reporting received from 

operators, it has been determined that 

repetitive inspections are also to be 

accomplished for aeroplanes equipped with 

SARMA strut. Airbus introduced that 

inspection in the applicable SB at revision 3. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2013–0219, which is superseded, and 

requires accomplishment of repetitive 

[HFEC] inspective inspection [for cracking] 

for aeroplanes equipped with SARMA strut. 

This [EASA] AD is considered as an 

interim action, pending the development of 

a terminating action. 

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–2014– 

1043. 

Related Service Information 

Airbus has issued the following 

service information: 

• Airbus Service Bulletin A330–53– 

3206, Revision 03, dated February 28, 

2014. This service information describes 

procedures for inspections for cracking 

of the strut ends of the THS support 

located in the airplane tail cone for 

Model A330 airplanes. 

• Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 

2014. This service information describes 

procedures for inspections for cracking 

of the strut ends of the THS support 

located in the airplane tail cone for 

Model A340 airplanes. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Although EASA Airworthiness 

Directive 2014–0068, dated March 18, 

2014, Airbus Service Bulletin A330–53– 

3206, Revision 03, dated February 28, 

2014, and Airbus Service Bulletin 

A340–53–4208, Revision 03, dated 

February 28, 2014, allow further flight 

after certain cracks are found during 

compliance with the proposed action, 

paragraph (j)(2) of this proposed AD 

would require that any cracked THS 

support strut be replaced with a new or 

serviceable TAC strut before further 

flight. 

Interim Action 

We consider this proposed AD 

interim action. If final action is later 

identified, we might consider further 

rulemaking then. 

Costs of Compliance 

We estimate that this proposed AD 

affects 84 airplanes of U.S. registry. 

We also estimate that it would take 

about 9 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 $64,260, or $765 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition 

replacement specified in this proposed 

AD. 

We estimate that any necessary 

follow-on strut reinforcements would 

take about 2 work-hours and require 

parts costing $5,680, for a cost of $5,850 

per product. We have no way of 

determining the number of aircraft that 

might need this action. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
3512 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 

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–2014–1043; 

Directorate Identifier 2013–NM–079–AD. 

(a) Comments Due Date 

We must receive comments by March 9, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category, all 

manufacturer serial numbers. 

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

–223, –223F, –243, and –243F airplanes. 

(2) Airbus Model A330–301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(3) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

cracked support strut body ends at a certain 

frame location of the trimmable horizontal 

stabilizer (THS). We are issuing this AD to 

detect and correct cracked support strut body 

ends of the THS, which could lead to the loss 

of all four THS support struts and which 

would make the remaining structure unable 

to carry limit loads, resulting in the loss of 

the horizontal tail plane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Strut Types 

For the purpose of this AD, a Societe ́

Anonyme de Recherche Me ́canique 

Applique ́e (SARMA) strut is a strut on which 

the diameter of the strut end is lower than 

43 millimeters. All other struts are Technical 

Airborne Components Industries (TAC) 

struts. 

(h) Repetitive Inspections of TAC Strut Ends 

At the applicable time specified in 

paragraph (i) of this AD, do a high frequency 

eddy current (HFEC) inspection for cracking 

of all TAC strut ends of the THS support 

located at frame (FR) 91 in the tail cone, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

53–3206, Revision 03, dated February 28, 

2014; or Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 2014; 

as applicable. Repeat the inspection 

thereafter at intervals not to exceed 42 

months or 20,000 flight hours, whichever 

occurs first. For airplanes on which Airbus 

Modification 203493 has been embodied in 

production, or Airbus Service Bulletin A330– 

53–3204 or Airbus Service Bulletin A340– 

53–4199, as applicable, has been embodied 

in service, remove the clamp from each strut 

end before accomplishing the inspections 

required by this paragraph. 

(i) Compliance Times for Paragraphs (h) and 

(k) of This AD 

Do the inspections required by paragraphs 

(h) and (k) of this AD at the applicable times 

specified in paragraphs (i)(1), (i)(2), and (i)(3) 

of this AD. 

(1) For Model A330 series airplanes having 

manufacturer serial numbers 012 through 209 

inclusive, and Model A340 series airplanes 

having manufacturer serial numbers 002 

through 210 inclusive: Within 6 months after 

the effective date of this AD. 

(2) For Model A330 series airplanes having 

manufacturer serial numbers 211 through 422 

inclusive, and Model A340 series airplanes 

having manufacturer serial numbers 212 

through 447 inclusive: Within 24 months 

after the effective date of this AD. 

(3) For Model A330 series airplanes having 

manufacturer serial numbers 423 and 

subsequent, and Model A340 series airplanes 

having manufacturer serial numbers 450 

through 955 inclusive: Within 36 months 

after the effective date of this AD or since the 

first flight of the airplane, whichever occurs 

later. 

(j) Corrective Action for TAC Strut Ends and 

Installation of Reinforcing Clamps 

(1) If, during any inspection required by 

paragraph (h) of this AD, no cracks are found: 

Before further flight, reinstall or install, as 

applicable, reinforcing clamps on the strut 

ends, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3206, Revision 03, 

dated February 28, 2014; or Airbus Service 

Bulletin A340–53–4208, Revision 03, dated 

February 28, 2014. 

(2) If, during any inspection required by 

paragraph (h) of this AD, any crack is found: 

Before further flight, replace any affected 

strut with a new or serviceable TAC strut and 

install reinforcing clamps on the strut end, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

53–3206, Revision 03, dated February 28, 

2014; or Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 2014; 

as applicable. 

(k) Repetitive Inspections of SARMA Strut 

Ends 

At the applicable time specified in 

paragraph (i) of this AD, do an HFEC 

inspection for cracking of all SARMA strut 

ends of the THS support located at FR 91 in 

the tail cone, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3206, Revision 03, 

dated February 28, 2014; or Airbus Service 

Bulletin A340–53–4208, Revision 03, dated 

February 28, 2014; as applicable. Repeat the 

inspection thereafter at intervals not to 

exceed 12 months. 

(l) Corrective Action for SARMA Strut Ends 

If any crack is found on a strut end during 

the inspection required by paragraph (k) of 

this AD: Before further flight, replace any 

affected SARMA strut with a new or 

serviceable TAC strut and install reinforcing 

clamps on the strut end, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3206, Revision 03, 

dated February 28, 2014; or Airbus Service 

Bulletin A340–53–4208, Revision 03, dated 

February 28, 2014; as applicable. 

(m) No Terminating Action 

Replacement of THS struts on an airplane 

does not constitute terminating action for the 

repetitive inspections required by this AD. 

(n) No Reporting 

Although Airbus Service Bulletin A330– 

53–3206, Revision 03, dated February 28, 

2014, and Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 2014, 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(o) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) through (k) of this 

AD, if those actions were performed before 

the effective date of this AD using any of the 

service information identified in paragraphs 

(n)(1) through (n)(6) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(1) Airbus Service Bulletin A330–53–3206, 

dated February 7, 2013. 

(2) Airbus Service Bulletin A330–53–3206, 

Revision 01, dated June 10, 2013. 

(3) Airbus Service Bulletin A330–53–3206, 

Revision 02, dated August 8, 2013. 

(4) Airbus Service Bulletin A340–53–4208, 

dated February 7, 2013. 

(5) Airbus Service Bulletin A340–53–4208, 

Revision 01, dated June 10, 2013. 

(6) Airbus Service Bulletin A340–53–4208, 

Revision 02, dated August 8, 2013. 

(p) 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: 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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0068, dated 

March 18, 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– 

2014–1043. 

(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 January 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–00993 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0076; Directorate 

Identifier 2013–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 all 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and Airbus Model A340–200, 

A340–300, A340–500, and A340–600 

series airplanes. This proposed AD was 

prompted by a report that, during a 

production flight test, the ram air 

turbine (RAT) did not pressurize the 

green hydraulic system. For certain 

airplanes, this proposed AD would 

require identification of the part 

number, serial number, and standard of 

the RAT pump, RAT module, RAT 

actuator, and RAT lower gearbox 

assembly; replacement of the balance 

weight screw, modification of the 

actuator coil spring, modification of the 

actuator, an inspection of the anti-stall 

valve for correct installation in the RAT 

pump housing; and corrective actions if 

necessary. For certain other airplanes, 

this proposed AD would require reidentification or replacement of the RAT 

module. We are proposing this AD to 

prevent loss of the impeller function 

and RAT pump pressurization 

capability, which, if preceded by a total 

engine flame-out, could result in the 

loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 9, 2015. 

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 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.A330A–340@

airbus.com; Internet http://

www.airbus.com. For Hamilton 

Sundstrand service information 

identified in this proposed AD, contact 

Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 

Harrison Avenue, P.O. Box 7002, 

Rockford, IL 61125–7002; telephone 

860–654–3575; fax 860–998–4564; email 

tech.solutions@hs.utc.com; Internet 

http://www.hamiltonsundstrand.com. 

You may view the 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– 

0076; 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–2015–0076; Directorate Identifier 

2013–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 

Directive 2013–0274, dated November 

15, 2013 (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, 

and A330–300 series airplanes; and 

Airbus Model A340–200, A340–300, 

A340–500, and A340–600 series 

airplanes. The MCAI states: 

During a production flight test of an A330– 

300 aeroplane, the Ram Air Turbine (RAT) 

did not pressurize the green hydraulic 

system. Investigation revealed that the 

impeller drive (hex) shaft had a reduced 

length of engagement with the pump drive 

shaft. This caused the impeller drive shaft to 

disengage from the pump and disconnect the 

impeller. It was determined that the 

disconnection was the result of internal hex 

dimensions on the pump impeller shaft, 

which had been changed in a manufacturing 

drawing. From the investigation analysis, it 

was possible to identify a list of affected 

parts. 


emcdonald on DSK67QTVN1PROD with PROPOSALS