Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules 59295 

(a) Comments Due Date 

We must receive comments by November 

12, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

–777F series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracking in the fuselage skin underneath the 

satellite communication (SATCOM) antenna 

adapter. We are issuing this AD to detect and 

correct cracking and corrosion in the fuselage 

skin, which could lead to rapid 

decompression and loss of structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

(1) For Group 1–4 airplanes and Group 5, 

Configuration 3 and 4 airplanes identified in 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013: Except as required by 

paragraphs (h)(1) and (h)(2) of this AD, 

within the applicable compliance times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013, do internal detailed and 

surface high frequency eddy current (HFEC) 

inspections of the visible fuselage skin, and 

doubler if installed, for cracking; do external 

detailed and surface HFEC inspections of the 

visible fuselage skin, and doubler if installed, 

for cracking, corrosion, and any indication 

that shows a contact of a certain fastener to 

a bonding jumper; and do all applicable 

repairs; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013, except as required by paragraph 

(h)(3) of this AD. Thereafter, repeat the 

inspections at the applicable intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013. Do all applicable repairs 

before further flight. 

(2) For Group 5, Configuration 1, 2, and 5 

airplanes identified in Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 2013: 

No action is required by this AD. 

(h) Exceptions to the Service Information 

(1) The ‘‘Condition Questionnaire’’ column 

in Tables 1, 5, and 9 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 2013, 

refers to airplanes with certain conditions ‘‘at 

the time of the original issue date of this 

service bulletin.’’ For this AD, use ‘‘as of the 

effective date of this AD’’ instead of ‘‘at the 

time of the original issue date of this service 

bulletin.’’ 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(3) If any crack, corrosion, or indication 

that shows a contact of the fastener attaching 

the SATCOM lug adapter plate to the 

bonding plate is found during any inspection 

required by this AD, and Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(i) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Melanie Violette, Aerospace 

Engineer, Airframe Branch, ANM 120S, FAA, 

Seattle Aircraft Certification Office, 1601 

Lind Avenue SW., Renton, WA 98057 3356; 

phone: (425) 917–6422; fax: (425) 917–6590; 

email: melanie.violette@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 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 

September 18, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23456 Filed 9–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0829; Directorate 

Identifier 2013–NM–085–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) 2010–23– 

12, which applies to certain Airbus 

Model A330–201, –202, –203, –223, 

–223F, –243, and –243F Airplanes, 

Model A330–300 series airplanes, and 

Model A340–200, A340–300, A340–500, 

and A340–600 series airplanes. AD 

2010–23–12 requires inspecting to 

determine the part number for Thales 

Avionics Angle of Attack (AoA) probes, 

and replacing any affected probe with a 

serviceable probe. Since we issued AD 

2010–23–12 we received reports that the 

AoA sensors on certain airplanes were 

modified and re-identified without 

performing the inspection to determine 

the part number; therefore, the affected 

probes were not replaced with 

serviceable probes. This proposed AD 

would add airplanes to the applicability 

and, for certain airplanes, require those 

affected probes be replaced. We are 

proposing this AD to prevent erroneous 

AoA information and consequent 

delayed activation or non-activation of 

the AoA protection systems, which, in 

combination with flight at a high angle 

of attack, could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

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 


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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 Thales Avionics service 

information identified in this proposed 

AD, contact Thales—Aerospace 

Division, 105, avenue du General 

Eisenhower—BP 63647, 31036 Toulouse 

Cedex 1, France; telephone +33 (0)5 61 

19 65 00; fax +33 (0)5 61 19 66 00; 

Internet http://www.thalesgroup.com/

aerospace. You may 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. 

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–2013–0829; Directorate Identifier 

2013–NM–085–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 October 22, 2010, we issued AD 

2010–23–12, Amendment 39–16501 (75 

FR 68698, November 9, 2010). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010), we received reports 

that the AoA sensors on certain 

airplanes were modified and reidentified without performing the 

inspection to determine the part 

number; therefore, the affected probes 

were not replaced with serviceable 

probes. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2013–0068, 

dated March 15, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During Airbus Final Assembly Line 

reception flight tests, Angle of Attack (AoA) 

data from two different aeroplanes were 

found inaccurate, which was confirmed by 

flight data analysis. 

The results of the investigation conducted 

by Airbus and Thales on the removed sensors 

revealed oil residue between the stator and 

the rotor parts of the AoA vane position 

resolvers. This oil residue was the result of 

incorrect removal of machining oil during the 

manufacturing process of the AoA resolvers. 

At low temperatures, this oil residue 

becomes viscous (typically in cruise) causing 

delayed and/or reduced AoA vane 

movement. Multiple AoA sensors could be 

simultaneously affected, providing incorrect 

indications of the AoA of the aeroplane. 

This condition, if not corrected, could lead 

to erroneous AoA information and 

consequent delayed activation or nonactivation of the AoA protection systems 

which, if during flight at a high angle of 

attack, could result in reduced control of the 

aeroplane. 

To address this unsafe condition, EASA 

issued AD 2010–0016R1 [(http://

ad.easa.europa.eu/blob/easa_ad_2013_

0068.pdf/AD_2011-0007R1_1)] [which 

corresponds to FAA AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010)] to require the 

identification of the serial number (S/N) of 

each installed Thales Avionics (formerly 

SEXTANT), Part Number (P/N) C16291AA 

AoA sensor and the replacement of all 

suspect units with serviceable one. EASA AD 

2010–0016R1 also prohibited the (re) 

installation of these same S/N AoA sensors 

on any aeroplane, unless corrective measures 

had been accomplished. 

Since that [EASA] AD was issued, it was 

discovered that a part of the affected 

population of AoA sensors may have been 

modified and re-identified from P/N 

C16291AA to P/N C16291AB, in accordance 

with the instructions of Airbus Service 

Bulletin (SB) A330–34–3228 or SB A340–34– 

5070, as applicable to aeroplane type, 

without having passed the inspection in 

accordance with the instructions of Thales 

Avionics SB C16291A–34–007, Revision 01. 

For the reasons described above, this new 

[EASA] AD retains the requirements of EASA 

AD 2010–0016R1, which is superseded, 

[adds airplanes to the applicability, and 

requires, for the affected population that was 

not addressed by EASA AD 2010–0016R1, 

the replacement of the suspect units with 

serviceable ones. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Thales Avionics has issued Service 

Bulletin C16291A–34–007, Revision 04, 

dated October 11, 2012. 

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 the same 

type design. 

Change to AD 2010–23–12, Amendment 

39–16501 (75 FR 68698, November 9, 

2010) 

We have changed paragraph (h) in 

this proposed AD to clarify the 

procedures for replacing the probes. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 70 products of U.S. registry. 

The actions that are required by AD 

2010–23–12, Amendment 39–16501 (75 


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FR 68698, November 9, 2010), and 

retained in this proposed AD take about 

3 work-hours per product, at an average 

labor rate of $85 per work hour. Based 

on these figures, the estimated cost of 

the currently required actions is $255 

per product. 

We estimate that it would take about 

9 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $0 per product. Where 

the service information lists required 

parts costs that are covered under 

warranty, we have assumed that there 

will be no charge for these parts. As we 

do not control warranty coverage for 

affected parties, some parties may incur 

costs higher than estimated here. Based 

on these figures, we estimate the cost of 

the proposed AD on U.S. operators to be 

$53,550, or $765 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the optional terminating 

action 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. 

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 

removing airworthiness directive (AD) 

2010–23–12, Amendment 39–16501 (75 

FR 68698, November 9, 2010), and 

adding the following new AD: 

Airbus: Docket No. FAA–2013–0829; 

Directorate Identifier 2013–NM–085–AD. 

(a) Comments Due Date 

We must receive comments by November 

12, 2013. 

(b) Affected ADs 

This AD supersedes AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010). 

(c) Applicability 

(c) This AD applies to Airbus airplanes, 

certificated in any category, as 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. 

(2) Model A340–211, A340–212, A340– 

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

541, and A340–642 airplanes; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34: Navigation. 

(e) Reason 

This AD was prompted by reports that the 

AoA sensors on certain airplanes were 

modified and re-identified without 

performing an inspection to determine the 

part number; therefore, probes having certain 

part numbers were not replaced with 

serviceable probes. We are issuing this AD to 

prevent erroneous AoA information and 

consequent delayed activation or nonactivation of the AoA protection systems, 

which, in combination with flight at a high 

angle of attack, could result in reduced 

controllability 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) Retained Inspection of AoA Probes 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010). For airplanes on which 

an AoA sensor having part number (P/N) 

C16291AA is installed, except as provided by 

paragraph (k) of this AD: Within 3 months 

after December 14, 2010 (the effective date of 

AD 2010–23–12), perform a detailed 

inspection of the Thales Avionics AoA 

probes having P/N C16291AA for a serial 

number identification, in accordance with 

the Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

A review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

serial number of the AoA probe can be 

conclusively determined from that review. If 

no AoA probe having P/N C16291AA and a 

serial number identified in Thales Service 

Bulletin C16291A–34–007, Revision 01, 

dated December 3, 2009, is identified during 

the inspection required by this paragraph of 

this AD, no further action is required by this 

AD, except for paragraph (l) of this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–34–3232, dated January 20, 2010 (for 

Model A330–200 and A330–300 series 

airplanes). 

(2) Airbus Mandatory Service Bulletin 

A340–34–4239, dated January 20, 2010 (for 

Model A340–200 and A340–300 series 

airplanes). 

(3) Airbus Mandatory Service Bulletin 

A340–34–5072, dated January 20, 2010 (for 

Model A340–500, and A340–600 series 

airplanes). 

(h) Retained Replacement of Identified AoA 

Probes 

This paragraph restates the requirements of 

paragraph (h) of AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010), with clarified 

procedures. If the serial number of the AoA 

probe identified during the inspection 

required by paragraph (g) of this AD 

corresponds to a suspect AoA probe specified 

in Thales Service Bulletin C16291A–34–007, 

Revision 01, dated December 3, 2009: At the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD, replace the affected AoA 

probe with a serviceable AoA probe, in 

accordance with one of the four options and 

associated Accomplishment Instructions 

specified in the applicable service bulletin 


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identified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD. 

(1) For airplanes on which Airbus 

Modification 53368 (back-up speed scale) has 

been embodied in production or Airbus 

Service Bulletin A330–34–3213, Airbus 

Service Bulletin A340–34–4213, or Airbus 

Service Bulletin A340–34–5060, as 

applicable, has been embodied in service: 

Within 3 months after December 14, 2010 

(the effective date of AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010)). 

(2) For airplanes on which Airbus 

Modification 53368 (back-up speed scale) has 

not been embodied in production and Airbus 

Service Bulletin A330–34–3213, Airbus 

Service Bulletin A340–34–4213, or Airbus 

Service Bulletin A340–34–5060, as 

applicable, has not been embodied in service: 

Within 15 months after December 14, 2010 

(the effective date of AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010)). 

(i) New Replacement of AoA Probes 

For airplanes on which an AoA probe 

having P/N C16291AA or C16291AB, with a 

serial number identified in Thales Service 

Bulletin C16291A–34–007, Revision 04, 

dated October 11, 2012, is installed, except 

as provided by paragraph (k) of this AD: 

Within 6 months after the effective date of 

this AD, replace any AoA probe having P/N 

C16291AA or C16291AB with a serviceable 

AoA probe, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

A review of airplane maintenance records 

that demonstrates that the affected AoA 

probe has passed the inspection, in 

accordance with the Accomplishment 

Instructions of Thales Service Bulletin 

C16291A–34–007, Revision 04, dated 

October 11, 2012, is acceptable for 

compliance with the requirements of this 

paragraph. 

(j) Exception to AD Requirements 

Airplanes on which Airbus Modification 

58555 (installation of AoA sensors with P/N 

C16291AB) or Airbus Modification 46921 

(installation of AoA sensors with P/N 

0861ED) has been embodied in production 

are not affected by the requirements in 

paragraphs (g), (h) and (i) of this AD, 

provided that no AoA sensor has been 

replaced since first flight. 

(k) Parts Installation Limitations 

(1) For airplanes on which an AoA sensor 

having part number (P/N) C16291AA is 

installed: As of December 14, 2010 (the 

effective date of AD 2010–23–12, 

Amendment 39–16501 (75 FR 68698, 

November 9, 2010)) and until the effective 

date of this AD, no person may install, on 

any airplane, a Thales Avionics AoA probe 

having P/N C16291AA and a serial number 

identified in Thales Service Bulletin 

C16291A–34–007, Revision 01, dated 

December 3, 2009, unless the AoA is fitted 

with an inspection label stating that Thales 

Service Bulletin C16291A–34–007, has been 

accomplished. 

(2) As of the effective date of this AD, no 

person may install, on any airplane, a Thales 

Avionics AoA probe having P/N C16291AA 

or P/N C16291AB and a serial number 

identified in Thales Service Bulletin 

C16291A–34–007, Revision 04, dated 

October 11, 2012, unless the AoA is fitted 

with an inspection label stating that Thales 

Service Bulletin C16291A–34–007, has been 

accomplished. 

(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: 

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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information Airworthiness 

Directive 2013–0068, dated March 15, 2013, 

for related information, which can be found 

in the AD docket on the internet at http://

www.regulations.gov. 

(2) 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. 

(3) For Thales Avionics service information 

identified in this proposed AD, contact 

Thales—Aerospace Division, 105, avenue du 

General Eisenhower—BP 63647, 31036 

Toulouse Cedex 1, France; telephone +33 

(0)5 61 19 65 00; fax +33 (0)5 61 19 66 00; 

Internet http://www.thalesgroup.com/

aerospace. 

(4) You may 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 

September 17, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23443 Filed 9–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1158; Directorate 

Identifier 2010–SW–018–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise 

airworthiness directive (AD) 2011–22– 

05 for Eurocopter France (Eurocopter) 

Model AS350B, B1, B2, B3, BA, C, D, 

D1, AS355E, F, F1, F2, N, and NP 

helicopters with certain tail rotor pitch 

control rods installed. AD 2011–22–05 

currently requires, before the first flight 

of each day, checking the tail rotor (T/ 

R) pitch control rod (control rod) 

outboard spherical bearing (bearing) for 

play. If play exists, AD 2011–22–05 

requires measuring the bearing’s radial 

and axial play. Since we issued AD 

2011–22–05, we have determined that 

we can safely extend the compliance 

time to perform the initial and recurring 

checks for bearing play. The proposed 

actions are intended to prevent failure 

of a control rod, loss of T/R control, and 

subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by November 25, 

2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 


emcdonald on DSK67QTVN1PROD with PROPOSALS