Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Proposed Rules 69899 

parts would cost about $1,577 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $190,848, or $7,952 

per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus Defense and Space S.A. (formerly 

known as Construcciones Aeronauticas, 

S.A.): Docket No. FAA–2015–4809; 

Directorate Identifier 2015–NM–012–AD. 

(a) Comments Due Date 

We must receive comments by December 

28, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus Defense and 

Space S.A. (formerly known as 

Construcciones Aeronauticas, S.A.) Model 

CN–235–200 and CN–235–300 airplanes, 

certificated in any category, manufacturer 

serial numbers C–018 through C–211 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 26, Fire Protection. 

(e) Reason 

This AD was prompted by reports of false 

engine fire warning events, which 

consequently led to engine in-flight shut 

down. We are issuing this AD to prevent 

unnecessary in-flight-shutdown of an engine, 

which could result in reduced controllability 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification of Engine Fire 

Extinguishing/Detection System 

Within 18 months after the effective date 

of this AD: Modify the location and routing 

of the engine fire detection system, in 

accordance with the Accomplishment 

Instructions of EADS CASA Service Bulletin 

SB–235–26–0006, dated July 8, 2014. 

(h) 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1112; 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 

the European Aviation Safety Agency 

(EASA); or EADS CASA’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0011, dated 

January 20, 2015, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–4809. 

(2) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net.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 October 

30, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28560 Filed 11–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4810; Directorate 

Identifier 2015–NM–090–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 

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69900 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Proposed Rules 

Airbus Model A330–200, –200 

Freighter, and –300 series airplanes; and 

all Airbus Model A340–200, –300, –500, 

and –600 series airplanes. This 

proposed AD was prompted by a report 

of blockage of Angle of Attack (AOA) 

probes during climb, leading to 

activation of the Alpha Protection 

(Alpha Prot) while the Mach number 

increased. This activation could cause a 

continuous nose-down pitch rate that 

cannot be stopped with backward 

sidestick input, even in the full 

backward position. For certain 

airplanes, this proposed AD would 

require replacing certain AOA sensors 

(probes) with certain new AOA sensors. 

For certain other airplanes, this 

proposed AD would also require 

inspections and functional heat testing 

of certain AOA sensors for 

discrepancies, and replacement if 

necessary. We are proposing this AD to 

prevent erroneous AOA information and 

Alpha Prot activation due to blocked 

AOA probes, which could result in a 

continuous nose-down command and 

consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by December 28, 

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–2015– 

4810; 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–2015–4810; Directorate Identifier 

2015–NM–090–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 2015–0134, dated July 8, 2015 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A330– 

200, –200 Freighter, and –300 series 

airplanes; and Model A340–200, –300, 

–500, and –600 series airplanes. The 

MCAI states: 

An occurrence was reported where an 

Airbus A321 aeroplane encountered a 

blockage of two Angle of Attack (AOA) 

probes during climb, leading to activation of 

the Alpha Protection (Alpha Prot) while the 

Mach number increased. The flight crew 

managed to regain full control and the flight 

landed uneventfully. It was determined that 

the affected AOA probes are also fitted on 

A330 and A340 aeroplanes. 

When Alpha Prot is activated due to 

blocked AOA probes, the flight control laws 

order a continuous nose down pitch rate that, 

in a worst case scenario, cannot be stopped 

with backward sidestick inputs, even in the 

full backward position. If the Mach number 

increases during a nose down order, the AOA 

value of the Alpha Prot will continue to 

decrease. As a result, the flight control laws 

will continue to order a nose down pitch 

rate, even if the speed is above minimum 

selectable speed, known as VLS. 

This condition, if not corrected, could 

result in loss of control of the aeroplane. 

Investigation results indicated that 

aeroplanes equipped with certain UTC 

Aerospace (UTAS, formerly known as 

Goodrich) AOA sensors, or equipped with 

certain SEXTANT/THOMSON AOA sensors, 

appear to have a greater susceptibility to 

adverse environmental conditions than 

aeroplanes equipped with the latest Thales 

AOA sensor, Part Number (P/N) C16291AB, 

which was designed to improve AOA 

indication behaviour in heavy rain 

conditions. 

Having determined that replacement of 

these AOA sensors is necessary to achieve 

and maintain the required safety level of the 

aeroplane, EASA issued AD 2015–0089, to 

require modification of the aeroplanes by 

replacement of the affected P/N sensors, and, 

after modification, prohibits (re-) installation 

of those P/N AOA sensors. That [EASA] AD 

also required repetitive detailed visual 

inspections (DET) and functional heating 

tests of certain Thales AOA sensors and 

provided an optional terminating action for 

those inspections. 

Since EASA AD 2015–0089 was issued, 

based on further analysis results, Airbus 

issued Operators Information Transmission 

(OIT) Ref. 999.0017/15 Revision 1, 

instructing operators to speed up the removal 

from service of UTAS P/N 0861ED2 AOA 

sensors. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2015–0089, which is superseded, but 

reduces the compliance times for aeroplanes 

with UTAS P/N 0861ED2 AOA sensors 

installed. 

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– 

4810. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information: 

• Service Bulletin A330–34–3215, 

Revision 02, dated March 29, 2010. 

• Service Bulletin A330–34–3228, 

dated October 7, 2009. 

• Service Bulletin A330–34–3315, 

dated March 26, 2015. 

• Service Bulletin A340–34–4215, 

Revision 02, dated March 29, 2010. 

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• Service Bulletin A340–34–4234, 

dated October 7, 2009. 

• Service Bulletin A340–34–4294, 

dated March 26, 2015. 

• Service Bulletin A340–34–5062, 

Revision 01, dated March 29, 2010. 

• Service Bulletin A340–34–5070, 

dated October 9, 2009. 

• Service Bulletin A340–34–5105, 

dated March 26, 2015. 

The service information describes 

procedures for replacing certain pitot 

probes with certain new pitot probes. 

The service information also describes 

procedures for inspections and 

functional heat testing of certain pitot 

probes, and replacement if necessary. 

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 55 airplanes of U.S. registry. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Replacement ................ 5 work-hours × $85 per hour = $425 ............... $0 $425 ............................................... $23,375 

Inspection/test .............. 3 work-hours × $85 per hour = $255 ............... 0 $255 per inspection/test cycle ....... 14,025 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–4810; 

Directorate Identifier 2015–NM–090–AD. 

(a) Comments Due Date 

We must receive comments by December 

28, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD, all 

manufacturer serial numbers. 

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

–223, –223F, –243, –243F, –301, –302, –303, 

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

airplanes. 

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

–311, –312, –313, –541, and –642 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34, Navigation. 

(e) Reason 

This AD was prompted by a report of 

blockage of two Angle of Attack (AOA) 

probes during climb, leading to activation of 

the Alpha Protection (Alpha Prot) while the 

Mach number increased. This activation 

could cause a continuous nose-down pitch 

rate that cannot be stopped with backward 

sidestick input, even in the full backward 

position. We are issuing this AD to prevent 

erroneous AOA information and Alpha Prot 

activation due to blocked AOA probes, which 

could result in a continuous nose-down 

command and consequent loss of control of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Certain UTAS AOA 

Sensors 

For airplanes on which any UTAS AOA 

sensor having part number (P/N) 0861ED or 

P/N 0861ED2 is installed: At the applicable 

time specified in paragraph (h) of this AD, 

replace all Captain and First Officer AOA 

sensors (probes) having P/N 0861ED or 

0861ED2 with AOA sensors having Thales P/ 

N C16291AB, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

(1) Airbus Service Bulletin A330–34–3315, 

dated March 26, 2015 (for Model A330 

airplanes). 

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(2) Airbus Service Bulletin A340–34–4294, 

dated March 26, 2015 (for Model A340–200 

and –300 airplanes). 

(3) Airbus Service Bulletin A340–34–5105, 

dated March 26, 2015 (for Model A340–500 

and –600 airplanes). 

(h) Compliance Times for the Requirements 

of Paragraph (g) of This AD 

Do the actions required by paragraph (g) of 

this AD at the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD. 

(1) For airplanes with AOA sensors having 

P/N 0861ED: Within 22 months after the 

effective date of this AD. 

(2) For airplanes with AOA sensors having 

P/N 0861ED2: Within 7 months after the 

effective date of this AD. 

(i) Replacement of Certain SEXTANT/

THOMSON AOA Sensors 

For airplanes on which any SEXTANT/

THOMSON AOA sensor having P/N 

45150320 is installed: Within 22 months after 

the effective date of this AD, replace all 

SEXTANT/THOMSON AOA sensors (probes) 

having P/N 45150320 with AOA sensors 

having Thales P/N C16291AB, in accordance 

with the Accomplishment Instructions of the 

applicable service information identified in 

paragraph (i)(1) or (i)(2) of this AD. 

(1) Airbus Service Bulletin A330–34–3228, 

dated October 7, 2009 (for Model A330–200 

and –300 airplanes). 

(2) Airbus Service Bulletin A340–34–4234, 

dated October 7, 2009 (for Model A340–200 

and –300 airplanes). 

(j) Repetitive Inspections/Tests of Certain 

Thales AOA Sensors 

For airplanes on which one or more Thales 

AOA sensor having P/N C16291AA is 

installed: Before the accumulation of 17,000 

total flight hours on the AOA sensor since 

first installation on an airplane, or within 6 

months after the effective date of this AD, 

whichever occurs later; and thereafter at 

intervals not to exceed 3,800 flight hours; do 

a detailed inspection of the three AOA 

sensors at FINs 3FP1, 3FP2, and 3FP3 for 

discrepancies (e.g., the vane of the sensor 

does not deice properly), and a functional 

heating test of each AOA sensor having P/N 

C16291AA, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (j)(1), (j)(2), or (j)(3) of this AD. 

(1) Airbus Service Bulletin A330–34–3215, 

Revision 02, dated March 29, 2010 (for Model 

A330–200 and –300 airplanes). 

(2) Airbus Service Bulletin A340–34–4215, 

Revision 02, dated March 29, 2010 (for Model 

A340–200 and –300 airplanes). 

(3) Airbus Service Bulletin A340–34–5062, 

Revision 01, dated March 29, 2010 (for Model 

A340–500 and –600 airplanes). 

(k) Corrective Actions 

If any discrepancy is found during any 

inspection required by paragraph (j) of this 

AD, or if any test is failed during the heating 

test required by paragraph (j) of this AD: 

Before further flight, replace all affected AOA 

sensors with sensors identified in paragraph 

(k)(1) or (k)(2) of this AD, in accordance with 

the Accomplishment Instructions of the 

applicable service information identified in 

paragraph (j)(1), (j)(2), or (j)(3) of this AD. 

(1) Replace with AOA sensors having 

Thales P/N C16291AA, on which the 

inspection and test required by paragraph (j) 

of this AD were passed. 

(2) Replace with AOA sensors having 

Thales P/N C16291AB. 

(l) Airplanes Excluded From Certain 

Requirements 

(1) The actions specified in paragraphs (g), 

(i), (j), and (k) of this AD are not required, 

provided that the conditions specified in 

paragraphs (l)(1)(i), (l)(1)(ii), and (l)(1)(iii) of 

this AD are met. 

(i) Airbus Modification 58555 (installation 

of Thales P/N C16291AB AOA sensors) has 

been embodied in production. 

(ii) Airbus Modification 46921 (installation 

of UTAS AOA sensors) has not been 

embodied in production. 

(iii) No AOA sensor having SEXTANT/

THOMSON P/N 45150320 or UTAS P/N 

0861ED or P/N 0861ED2 has been installed 

on the airplane since date of issuance of the 

original airworthiness certificate or date of 

issuance of the original export certificate of 

airworthiness. 

(2) The actions specified in paragraphs (g) 

and (i) of this AD are not required, provided 

that all conditions specified in paragraphs 

(l)(2)(i), (l)(2)(ii), and (l)(2)(iii) of this AD are 

met. 

(i) Only AOA sensors with P/Ns approved 

after the effective date of this AD have been 

installed. 

(ii) The AOA sensor P/N is approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). 

(iii) The installation is accomplished in 

accordance with airplane modification 

instructions approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; the EASA; or 

Airbus’s EASA DOA. 

(m) Optional Terminating Modification 

Replacement of all Thales AOA sensors 

having P/N C16291AA with Thales AOA 

sensors having P/N C16291AB, in accordance 

with the Accomplishment Instructions of the 

applicable service information identified in 

paragraph (m)(1), (m)(2), or (m)(3) of this AD, 

terminates the repetitive inspections and 

functional heating tests required by 

paragraph (j) of this AD. 

(1) Airbus Service Bulletin A330–34–3228, 

dated October 7, 2009 (for Model A330–200 

and –300 airplanes). 

(2) Airbus Service Bulletin A340–34–4234, 

dated October 7, 2009 (for Model A340–200 

and –300 airplanes). 

(3) Airbus Service Bulletin A340–34–5070, 

dated October 9, 2009 (for Model A340–500 

and –600 airplanes). 

(n) Parts Installation Prohibitions 

(1) For airplanes on which only Thales P/ 

N C16291AB AOA sensors are installed as of 

the effective date of this AD: No person may 

install, on any airplane, a Thales AOA sensor 

having P/N C16291AA as of the effective date 

of this AD. 

(2) For airplanes on which the 

modification specified in paragraph (m) of 

this AD has been done: No person may 

install, on any airplane, a Thales AOA sensor 

having P/N C16291AA after accomplishing 

the specified modification. 

(3) For airplanes on which Thales P/N 

C16291AA or P/N C16291AB AOA sensors 

are installed as of the effective date of this 

AD: No person may install, on any airplane, 

a UTAS AOA sensor having P/N 0861ED or 

P/N 0861ED2, or a SEXTANT/THOMSON 

AOA sensor having P/N 45150320, as of the 

effective date of this AD. 

(4) For airplanes on which the replacement 

required by paragraph (i) of this AD has been 

done: No person may install, on any airplane, 

a UTAS AOA sensor having P/N 0861ED or 

P/N 0861ED2, or a SEXTANT/THOMSON 

AOA sensor having P/N 45150320, after 

accomplishing the replacement. 

(5) For airplanes on which the replacement 

required by paragraph (g) of this AD has been 

done: No person may install, on any airplane, 

a UTAS AOA sensor having P/N 0861ED or 

P/N 0861ED2, or a SEXTANT/THOMSON 

AOA sensor having P/N 45150320, after 

accomplishing the replacement, except that a 

UTAS AOA sensor having P/N 0861ED may 

be installed in the standby position of that 

airplane. 

(o) 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 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0134, dated 

July 8, 2015, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Proposed Rules 69903 

searching for and locating Docket No. FAA– 

2015–4810. 

(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 October 

30, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28559 Filed 11–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4212; Directorate 

Identifier 2015–NM–010–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

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 BAE 

Systems (Operations) Limited Model 

BAe 146 series airplanes and Model 

Avro 146–RJ series airplanes. This 

proposed AD was prompted by reports 

of cracking of the main fitting of the 

nose landing gear (NLG) and a 

determination that a new safe-life 

limitation for affected NLG main fittings 

has not been mandated. This proposed 

AD would require replacing affected 

NLG main fittings that have exceeded 

the safe-life limitation with a new or 

serviceable fitting. We are proposing 

this AD to prevent collapse of the NLG, 

which if not corrected, could lead to 

degradation of direction control on the 

ground or an un-commanded turn to the 

left, and a consequent loss of control of 

the airplane on the ground, possibly 

resulting in damage to the airplane and 

injury to occupants. 

DATES: We must receive comments on 

this proposed AD by December 28, 

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 BAE Systems 

(Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 

1292 675704; email RApublications@

baesystems.com; Internet http://

www.baesystems.com/Businesses/

RegionalAircraft/index.htm. 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– 

4212; 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1175; 

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–2015–4212; Directorate Identifier 

2015–NM–010–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 2012–0191R1, dated 

November 6, 2012 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all BAE Systems (Operations) 

Limited Model BAe 146 series airplanes 

and Model Avro 146–RJ series airplanes. 

The MCAI states: 

Several occurrences of the aeroplane‘s 

Nose Landing Gear (NLG) Main Fitting 

cracking have been reported. Subsequently in 

different cases, NLG Main Fitting crack lead 

to collapsed NLG, locked NLG steering and 

an aeroplane‘s un-commanded steering to the 

left. 

Cracks in the NLG Bell Housing are not 

detectable with the NLG fitted to the 

aeroplane and are difficult to detect during 

overhaul without substantial disassembly of 

the gear. 

This condition, if not corrected, could lead 

to degradation of directional control on the 

ground or an un-commanded turn to the left 

and a consequent loss of control of the 

aeroplane on the ground, possibly resulting 

in damage to the aeroplane and injury to 

occupants. 

Prompted by these findings, BAE Systems 

(Operations) Ltd issued Inspection Service 

Bulletin (ISB) 32–186 (hereafter referred to as 

the ISB) to introduce a new safe life of 16,000 

flight cycles (FC) for certain NLG main 

fittings, having a Part Number (P/N) as 

identified in Paragraph 1A, tables 1, 2 and 3 

of the ISB. 

To correct this unsafe condition, EASA 

issued [EASA] AD 2012–0191 to require 

implementation of the new safe-life 

limitation for the affected NLG main fittings 

and replacement of fittings that have already 

exceeded the new limit. 

* * * * * 

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– 

4212. 

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