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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 


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p.m., Monday through Friday, except 

Federal holidays. 

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 

foreign authority’s AD, the economic 

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 service information identified in 

this proposed AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.eurocopter.com/techpub. You may 

review service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On October 12, 2011, we issued AD 

2011–22–05, Amendment 39–16847 (76 

FR 70046, November 10, 2011) for 

Eurocopter Model AS350B, B1, B2, B3, 

BA, C, D, D1, AS355E, F, F1, F2, N, and 

NP helicopters with certain T/R control 

rods installed. AD 2011–22–05 requires 

the following actions: 

• Before the first flight of each day, 

checking the control rod bearing for 

play on the helicopter, by observation 

and feel, by slightly moving the TR 

blade in the flapping axis while 

monitoring the bearing for movement. 

• If the Teflon cloth is coming out of 

its position within the bearing or if there 

is discoloration or scoring, replacing the 

control rod assembly before further 

flight. 

• If play is detected, having a 

mechanic remove the control rod from 

the helicopter, and using a dial 

indicator, measuring the control rod 

bearing wear. If the radial play exceeds 

0.008 inch or axial play exceeds 0.016 

inch, replacing the control rod with an 

airworthy control rod before further 

flight. 

• Thereafter, at intervals not to 

exceed 30 hours time-in-service (TIS), 

repeating the requirement to remove the 

control rod and measuring the bearing 

for wear using a dial indicator. 

AD 2011–22–05 was prompted by the 

issuance of AD No. 2010–0006, dated 

January 7, 2010, by the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union. The 

EASA AD was issued to correct an 

unsafe condition for certain Eurocopter 

helicopters. EASA advised that a pilot 

of a Eurocopter Model AS350 helicopter 

felt slight vibrations in the pedal unit in 

flight. A few minutes later, the vibration 

level increased and the pilot carried out 

a precautionary autorotation landing. 

After landing, it was discovered that one 

TR pitch-change link was damaged, the 

tailboom cone was missing, and there 

was an impact mark on the tailboom. 

Further investigation revealed the 

affected TR pitch-change link showed 

extensive wear on the ball-joint. EASA 

advised that this condition, if not 

detected and corrected, could lead to 

loss of the anti-torque function and 

possible loss of control of the helicopter. 

Actions Since AD 2011–22–05 Was 

Issued 

Since we issued AD 2011–22–05 (76 

FR 70046, November 10, 2011), we have 

determined that we can safely extend 

the compliance time for the initial 

bearing play check and the interval for 

recurring checks to 30 hours TIS. We 

also received several requests for 

alternative methods of compliance 

regarding the bearing play check, and as 

a result this proposed AD would clarify 

the requirements of that check. We 

removed a previous requirement that if 

the Teflon cloth is coming out of its 

normal position within the bearing, or if 

there is discoloration or scoring on the 

bearing, that the control rod be replaced 

with an airworthy rod before further 

flight. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin (ASB) No. 05.00.60 for the 

Model AS350 series helicopters, and 

ASB No. 05.00.56 for the Model AS355 

series helicopters, both dated December 

9, 2009. These ASBs specify performing 

an initial and recurring check for play 

in the pitch-change links. If axial play 

in the ball-joint is detectable, the ASBs 

specify removing the pitch-change link 

and measuring the bearing wear using a 

dial indicator. EASA classified these 

ASBs as mandatory and issued EASA 

AD No. 2010–0006 to ensure the 

continued airworthiness of these 

helicopters. 

Proposed AD Requirements 

This proposed AD would clarify the 

requirements of AD 2011–22–05, extend 

the compliance time for the bearing play 

checks to 30 hours TIS, and remove the 

requirement to replace the control rod if 

the Teflon cloth is out of position or if 

there is discoloration or scoring on the 

bearing. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 936 helicopters of U.S. 

Registry and that labor costs will 

average $85 a work-hour. We estimate, 

per helicopter, it will take minimal 

work-hours to do the check, 1 workhour to measure the bearing play, and 

1 work-hour to replace 1 control rod. 

The average labor rate is $85 per workhour. Required parts will cost about 


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$1,724 to replace a control rod per 

helicopter. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators is minimal for the check. 

Measuring the bearing play, if needed, 

would cost $85 per helicopter, and 

replacing 1 control rod would cost 

$1,809 per helicopter. 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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 an economic 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) 

2011–22–05, Amendment 39l16847 

(76 FR 70046, November 10, 2011), and 

adding the following new AD: 

Eurocopter France: Docket No. FAA–2011– 

1158; Directorate Identifier 2010–SW– 

018–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model AS350B, B1, B2, B3, BA, 

C, D, D1; and Model AS355E, F, F1, F2, N, 

and NP helicopters; with tail rotor (T/R) 

pitch control rod (control rod), part number 

(P/N) 350A33–2100–00, –01, –02, –03, –04; 

P/N 350A33–2121–00, –01, –02; P/N 

350A33–2143–00; or P/N 350A33–2145–00 

or –01, installed; certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

excessive play in the control rod. This 

condition could result in failure of a T/R 

control rod, loss of T/R control, and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD revises AD 2011–22–05 (76 FR 

70046, November 10, 2011), Amendment 39– 

16847, Docket No. FAA–2011–1158, 

Directorate Identifier 2010–SW–018–AD. 

(d) Comments Due Date 

We must receive comments by November 

25, 2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Within 30 hours time-in-service (TIS) 

and, if no bearing play is detected, thereafter 

at intervals not to exceed 30 hours TIS, place 

the T/R pedals in the neutral position. If the 

helicopter is fitted with a T/R load 

compensator, discharge the accumulator as 

described in the rotorcraft flight manual. 

Check the control rod bearing (bearing) for 

play on the helicopter, by observation and 

feel, by slightly moving the T/R blade in the 

flapping axis while monitoring the bearing 

for movement. See the following Figure 1 to 

Paragraph (f) of this AD. The actions required 

by this paragraph of may be performed by the 

owner/operator (pilot) holding at least a 

private pilot certificate, and must be entered 

into the helicopter maintenance records 

showing compliance with this AD in 

accordance with 14 CFR 43.9(a)(1)–(4) and 14 

CFR 91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

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(2) If a pilot or mechanic detects play in 

the bearing, before the next flight, a mechanic 

must remove the control rod from the 

helicopter, and using a dial indicator, 

measure the bearing wear according to the 

following and as shown in Figures 2 and 3 

to Paragraph (f) of this AD: 


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BILLING CODE 4910–13–C 

(i) Remove the control rod from the 

helicopter. 

(ii) Mount the control rod in a vise as 

shown in Figure 2 to Paragraph (f) of this AD. 

(iii) Using a dial indicator, take axial play 

readings by moving the spherical bearing in 

the direction F (up and down) as shown in 

Figure 2 to Paragraph (f) of this AD. 

(iv) Install a bolt through the bearing and 

secure it with a washer and nut to provide 

a clamping surface when the bearing is 

clamped in a vise. 

(v) Mount the control rod and bearing in 

a vise as shown in Figure 3 to Paragraph (f) 

of this AD. 

(vi) Using a dial indicator, take radial play 

measurements by moving the control rod in 

the direction F as shown in Figure 3 to 

Paragraph (f) of this AD. 

(vii) Record the hours of operation on each 

control rod. 

(viii) If the radial play exceeds 0.008 inch 

or axial play exceeds 0.016 inch, replace the 

control rod with an airworthy control rod 

before further flight. 

(ix) If the radial and axial play are within 

limits, reinstall the control rod. 

(x) Thereafter, at intervals not to exceed 30 

hours TIS, remove the control rod and 

measure the bearing play with a dial 

indicator in accordance with paragraph (f)(2) 

of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(3) An AMOC approved previously in 

accordance with Airworthiness Directive No. 

2011–22–05, Amendment 39–16847 (76 FR 

70046, November 10, 2011), is approved as 

an AMOC for the corresponding 

requirements in paragraph (f)(2) of this AD. 

(h) Additional Information 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. 05.00.60 and ASB No. 05.00.56, both 

dated December 9, 2009, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

service information identified in this AD, 

contact American Eurocopter Corporation, 

2701 N. Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or (800) 

232–0323; fax (972) 641–3775; or at http:// 

www.eurocopter.com/techpub. You may 

review a copy of the service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

the European Aviation Safety Agency (EASA) 

AD No. 2010–0006, dated January 7, 2010. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2011–1158. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail rotor control system. 

Issued in Fort Worth, Texas, on September 

17, 2013. 

Gwendolynne O’Connell, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23434 Filed 9–25–13; 8:45 am] 

BILLING CODE 4910–13–P 


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