25664 Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed and High Frequency Eddy 

Current (HFEC) Inspections 

Within 24 months after the effective date 

of this AD: Do a detailed inspection for 

cracking and corrosion of the left and right 

side chords of the fin closure rib, and do a 

HFEC inspection of the left- and right-side 

chords for cracking, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 727–55– 

0095, dated September 24, 2012. If any 

cracking or corrosion is found, before further 

flight, repair or replace the affected right or 

left-side chord using a method approved in 

accordance with the procedures specified in 

paragraph (h) of this AD. Repeat the detailed 

inspection and HFEC inspection thereafter at 

intervals not to exceed 26 months. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: berhane.alazar@faa.gov. 

(2) For Boeing 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 also 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on April 23, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–10367 Filed 5–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0335; Directorate 

Identifier 2012–NM–187–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 A330–300, A340–200, 

and A340–300 series airplanes. This 

proposed AD was prompted by a 

determination that ballscrew rupture 

could occur on certain trimmable 

horizontal stabilizer actuators (THSAs). 

This proposed AD would require 

repetitive THSA ballscrew shaft 

integrity tests, and replacement if 

necessary. We are proposing this AD to 

detect and correct ballscrew rupture, 

which, along with corrosion on the 

ballscrew lower splines, may lead to 

loss of transmission of THSA torque 

loads from the ballscrew to the tie-bar 

and consequent THSA blowback, which 

could result in loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by June 17, 2013. 

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— 

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 review copies of 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; or in person at the 

Docket Operations office 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, 

Washington 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–2013–0335; Directorate Identifier 

2012–NM–187–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 

Community, has issued EASA 

Airworthiness Directive 2012–0210, 

dated October 11, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules 25665 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Since the issuance of EASA AD 2012–0061 

which addresses the corrosion identified in 

service on THSA [part number] P/N 47147– 

500 and P/N 47147–700 at the level of the 

ballscrew lower splines, further analyses 

have been conducted to determine the need 

for any additional action. 

The ballscrew lower splines are not loaded 

in normal operation, only in case of 

ballscrew rupture. Analysis results have 

shown that such rupture could happen 

during the current inspection interval 

imposed by the Maintenance Review Board 

Report (MRBR), task 274000–12. 

Corrosion on the lower splines, in case of 

ballscrew rupture, may lead to loss of 

transmission of THSA torque loads from the 

ballscrew to the tie-bar and consequent 

THSA blowback, which could result in loss 

of control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires reduction of the check 

interval of MRBR task 274000–12. 

Required actions include repetitive 

THSA ballscrew shaft integrity tests. 

Corrective actions include replacement 

of the THSA. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service bulletins. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

• Airbus Mandatory Service Bulletin 

A330–27–3191, dated June 7, 2012. 

• Airbus Mandatory Service Bulletin 

A340–27–4186, dated June 7, 2012. 

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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 30 products of U.S. registry. 

We also estimate that it would take 

about 7 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 the 

proposed AD on U.S. operators to be 

$17,850, or $595 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 8 work-hours and require parts 

costing up to $722,556, for a cost of up 

to $723,236 per product. We have no 

way of determining the number of 

products that may need these actions. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Airbus: Docket No. FAA–2013–0335; 

Directorate Identifier 2012–NM–187–AD. 

(a) Comments Due Date 

We must receive comments by June 17, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers; if fitted with a 

trimmable horizontal stabilizer actuator 

(THSA) having part number (P/N) 47147–500 

or P/N 47147–700. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that ballscrew rupture could occur on certain 

THSAs. We are issuing this AD to detect and 

correct ballscrew rupture, which, along with 

corrosion on the ballscrew lower splines, 

may lead to loss of transmission of THSA 

torque loads from the ballscrew to the tie-bar 

and consequent THSA blowback, which 

could result in loss of control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Integrity Tests 

At the later of the times specified in 

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

applicable, do a THSA ballscrew shaft 

integrity test, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3191, 

dated June 7, 2012; or Airbus Mandatory 

Service Bulletin A340–27–4186, dated June 

7, 2012; as applicable. Repeat the integrity 

test thereafter at intervals not to exceed 

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25666 Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules 

12,000 flight hours or 4,400 flight cycles, 

whichever occurs first. 

(1) At the latest of the times specified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. 

(i) Within 12,000 flight hours since the 

airplane’s first flight; or 

(ii) Within 12,000 flight hours since the 

most recent THSA ballscrew shaft integrity 

test was done as specified in maintenance 

review board report (MRBR) Task 274000–12; 

or 

(iii) Within 12,000 flight hours since the 

most recent THSA ballscrew shaft integrity 

test was done, as specified in Airbus 

Mandatory Service Bulletin A330–27–3179 

or Airbus Mandatory Service Bulletin A340– 

27–4175, as applicable. (These service 

bulletins specify testing in case of type II or 

type III findings). 

(2) Within 1,000 flight hours after the 

effective date of this AD, but without 

exceeding the latest of the times specified in 

paragraphs (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of 

this AD. 

(i) 16,000 flight hours since the airplane’s 

first flight. 

(ii) 16,000 flight hours since the most 

recent THSA ballscrew shaft integrity test 

was done, as specified in MRBR task 274000– 

12. 

(iii) 16,000 flight hours since the most 

recent THSA ballscrew shaft integrity test 

was done, as specified in Airbus Mandatory 

Service Bulletin A330–27–3179, or Airbus 

Mandatory Service Bulletin A340–27–4175, 

as applicable. (These service bulletins specify 

testing in case of type II or type III findings). 

(h) Replacement 

If the result from any test required by 

paragraph (g) of this AD is not correct, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3191, dated June 7, 2012; 

or Airbus Mandatory Service Bulletin A340– 

27–4186, dated June 7, 2012; as applicable: 

Before further flight, replace the THSA with 

a serviceable THSA, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3191, 

dated June 7, 2012; or Airbus Mandatory 

Service Bulletin A340–27–4186, dated June 

7, 2012; as applicable. Replacement of a 

THSA, as required by this paragraph, with a 

THSA having P/N 47147–500 or P/N 47147– 

700, is not terminating action for the 

repetitive tests required by paragraph (g) of 

this AD. 

(i) 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, Washington 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0210, dated October 11, 2012, 

and the service bulletins specified in 

paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, 

for related information. 

(i) Airbus Mandatory Service Bulletin 

A330–27–3191, dated June 7, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A340–27–4186, dated June 7, 2012. 

(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 

review copies of 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. 

Issued in Renton, Washington, on April 23, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–10366 Filed 5–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0360; Directorate 

Identifier 2013–NM–033–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 an 

existing airworthiness directive (AD) 

that applies to all Airbus Model A318, 

A319, A320, and A321 series airplanes. 

The existing AD currently requires 

revising the airplane flight manual 

(AFM) to advise the flightcrew of 

emergency procedures for addressing 

angle of attack (AoA) sensor blockage. 

The existing AD also provides for 

optional terminating action for the AFM 

revision, which involves replacing AoA 

sensor conic plates with AoA sensor flat 

plates. Since we issued that AD, we 

have determined that the replacement of 

AoA sensor conic plates is necessary to 

address the identified unsafe condition. 

This proposed AD would mandate the 

installation of AoA sensor flat plates 

and removal of the AFM revision. We 

are proposing this AD to prevent 

reduced control of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 17, 2013. 

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, 

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 review copies of 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; or in person at the 

Docket Operations office 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 

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