57086 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–23539 Filed 9–21–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0753; Directorate 

Identifier 2014–NM–128–AD; Amendment 

39–18270; AD 2015–19–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–19– 

04, for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 

2011–19–04 required repetitive 

inspections for cracking of the left-hand 

and right-hand inboard and outboard 

elevator servo-control rod eye-ends, and 

corrective actions if necessary. This new 

AD requires an inspection to determine 

if certain elevator servo-control parts are 

installed, and replacement if necessary. 

This AD was prompted by a 

determination that certain elevator 

servo-control parts that do not conform 

to the approved type design have been 

installed and may have the potential of 

cracks in the rod eye-end. We are 

issuing this AD to detect and correct rod 

eye-end cracking, which could result in 

uncontrolled elevator surface and 

consequent reduced control of the 

airplane. 

DATES: This AD becomes effective 

October 27, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 27, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 21, 2011 (76 FR 

57630, September 16, 2011). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 22, 2009 (74 FR 

41611 August 18, 2009). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0753; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

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

UTC service information identified in 

this AD, contact UTC Aerospace 

Systems; Roger Dangremont; telephone 

+01 34 32 63 28; email 

roger.dangrement@goodrich.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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0753. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011). AD 2011–19–04 

applied to all Model A318, A319, A320, 

and A321 series airplanes. The NPRM 

published in the Federal Register on 

October 21, 2014 (79 FR 62928). The 

NPRM was prompted by a 

determination that certain elevator 

servo-control parts that do not conform 

to the approved type design have been 

installed and may have the potential of 

cracks in the rod eye-end. The NPRM 

proposed to continue to require 

repetitive inspections of the left-hand 

and right-hand inboard and outboard 

elevator servo-control rod eye-ends for 

cracking, and corrective actions if 

necessary. The NPRM also proposed to 

require an inspection to determine if 

certain elevator servo-control parts are 

installed, and replacement if necessary. 

We are issuing this AD to detect and 

correct rod eye-end cracking, which 

could result in uncontrolled elevator 

surface and consequent reduced control 

of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0137, dated May 28, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition. The MCAI states: 

One case of elevator servo-control 

disconnection was reported on an A320 

family aeroplane. Investigation results 

revealed that the failure occurred at the 

servo-control rod eye-end. Prompted by this 

finding, additional inspections revealed 

cracking at the same location on a number of 

other servo-control rod eye-ends. In several 

cases, both actuators of the same elevator 

surface were affected. 

It was determined that the detected rod 

end cracks are caused by fatigue, induced by 

a bending effect which is linked to the 

spherical bearing rotational torque. As the 

elevator surface is neither actuated nor 

damped, a dual servo-control disconnection 

on the same elevator would result in an 

uncontrolled surface. 

This condition, if not corrected, could 

result in reduced control of the aeroplane. 

To address this potential unsafe condition, 

EASA issued [an airworthiness directive 

(later revised)] [which corresponds to FAA 

AD 2009–17–04, Amendment 39–15995 (74 

FR 41611, August 18, 2009)] to require a onetime inspection of the elevator servo-control 

rod eye-ends for aeroplanes which had 

accumulated more than 10,000 flight cycles 

(FC) since aeroplane first flight and, in case 

of findings, accomplishment of corrective 

actions. 

As a result of EASA AD 2008–0149, a 

significant number of rod eye-ends were 

found cracked. In addition, some cracks were 

reported on rod eye-ends that had not yet 

accumulated the 10,000 FC of the established 

threshold. 

Prompted by these findings, EASA issued 

[an airworthiness directive (later revised)] 

[which corresponds to FAA AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011)], which partially 

retained the initial inspection requirement of 

EASA AD 2008–0149, which was 

superseded, reduced the compliance time of 

the initial inspection and introduced a 

repetitive inspection programme. 

After EASA AD 2010–0046R1 (http://

ad.easa.europa.eu/blob/easa_ad_2010_0046_

R1_superseded.pdf/AD_2010-0046R1_1) was 

issued, a new elevator servo-control rod eyeend was developed, incorporating a regreasable roller bearing. 

Consequently, EASA issued [EASA] AD 

2013–0309 (later corrected) (http://

ad.easa.europa.eu/blob/easa_ad_2013_0309_

superseded.pdf/AD_2013-0309_1), retaining 

the requirements of EASA AD 2010–0046R1, 

which was superseded, and introduced an 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations 57087 

optional terminating action for the repetitive 

inspections by replacing the existing elevator 

servo-control rod eye-ends with the new 

elevator servo-control rod eye-end. In 

addition, that [EASA] AD prohibited, for 

aeroplanes that incorporate this optional 

modification, (re)installation of unmodified 

elevator servo-controls. 

At the time that EASA AD 2013–0309 was 

issued, it was planned that Airbus would 

proceed with the certification of certain 

elevator servo-controls, Part Number (P/N) 

31075–0xx, P/N 31075–1xx and P/N 31075– 

3xx (originally certified only for installation 

on Model A320–111 aeroplanes, which are 

no longer in service), to allow installation of 

those parts on other A320 family aeroplane 

Models. 

Since that [EASA] AD was issued, Airbus 

decided not to progress with certification of 

the affected elevator servo-controls for 

installation on other Models. 

For the reason described above, and 

because of evidence that such parts remain 

available as spares in the field, this [EASA] 

AD retains the requirements of EASA AD 

2013–0309, which is superseded, and adds a 

prohibition to install the affected elevator 

servo-controls that were only intended for 

A320–111 aeroplanes. 

This AD requires an inspection to 

determine whether any elevator control 

part having P/N 31075–0xx, 31075–1xx, 

or 31075–3xx is installed, and 

replacement if necessary. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0753- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 62928, 

October 21, 2014) and the FAA’s 

response to each comment. 

Request To Clarify Affected Airplanes 

for Certain Proposed Requirements 

United Airlines (UAL) requested that, 

for clarity reasons, we revise the 

identity of affected airplanes in 

paragraphs (g) through (j) of the 

proposed AD (79 FR 62928, October 21, 

2014) to pertain only to elevator servocontrols having part number (P/N) 

341203 or P/N 341203–xxx rod eyeends. UAL stated that per Airbus 

Service Bulletin A320–27A1186, 

Revision 07, dated March 2, 2011; and 

Goodrich Service Bulletin 31075–27–22, 

dated July 2, 2013, it understands that 

only the rod eye-ends fitted with selflubricating spherical bearings are 

required to have initial and repetitive 

inspections for cracks. 

We partially agree with the 

commenter’s request. We agree that only 

certain elevator servo-controls and rod 

eye-ends are affected. However, 

paragraph (n) of this AD addresses the 

commenter’s concern. Paragraph (n) of 

this AD identifies airplanes that are not 

affected by the requirements of 

paragraphs (g), (h), (k) and (l) of this AD. 

We have not changed this AD as 

requested by the commenter, but we 

have revised the heading of paragraph 

(n) of this AD to more accurately reflect 

the content of that paragraph. 

Request To Permit the Use of 

Serviceable Parts, and Relocate the 

Definition of Serviceable Parts 

UAL requested that we permit the use 

of serviceable parts in paragraph (l)(1) of 

the proposed AD (79 FR 62928, October 

21, 2014), and move the definition of a 

serviceable part from paragraph (l)(2) of 

the proposed AD to paragraph (l)(1) of 

the proposed AD. 

We agree with the commenter’s 

requests. We have determined that the 

use of serviceable parts is acceptable as 

replacement parts in paragraph (l)(1) of 

this AD. We have changed the wording 

of paragraph (l)(1) of this AD to specify 

that serviceable parts may be used as 

replacement parts. We have also moved 

the definition of serviceable parts from 

paragraph (l)(2) of this AD to paragraph 

(l)(1) of this AD since both paragraphs 

(l)(1) and (l)(2) of this AD specify the 

use of serviceable parts. 

Request To Revise Service Information 

Title 

UAL requested that we revise 

paragraph (l)(2) of the proposed AD (79 

FR 62928, October 21, 2014) to replace 

the service information nomenclature 

from Goodrich Service Bulletin 31075– 

27–22, dated July 2, 2013, to UTC 

Aerospace Systems Service Bulletin 

31075–27–22, dated July 2, 2013. 

We agree with the commenter’s 

request. The requested service bulletin 

title change is correct. We have revised 

paragraph (l)(2) of this AD accordingly. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

62928, October 21, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 62928, 

October 21, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–27–1223, dated September 3, 

2013; and UTC Aerospace Systems 

Service Bulletin 31075–27–22, dated 

July 2, 2013. The service information 

describes procedures for modifying and 

replacing the elevator servo-control eyeend. 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 AD. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

The actions that are required by AD 

2011–19–04, Amendment 39–16809 (76 

FR 57630, September 16, 2011), and 

retained in this AD take about 25 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that are required by AD 2011– 

19–04 is $2,125 per product. 

We also estimate that it would take 

about 14 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $1,012,690, or $1,190 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 2 work-hours and require parts 

costing $4,000, for a cost of $4,170 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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 


Lhorne on DSK5TPTVN1PROD with RULES
57088 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0753; 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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

2011–19–04, Amendment 39–16809 (76 

FR 57630, September 16, 2011), and 

adding the following new AD: 

2015–19–08 Airbus: Amendment 39–18270; 

Docket No. FAA–2014–0753; Directorate 

Identifier 2014–NM–128–AD. 

(a) Effective Date 

This AD becomes effective October 27, 

2015. 

(b) Affected ADs 

This AD replaces AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(4) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that certain elevator servo-control parts that 

do not conform to the approved type design 

have been installed and may have the 

potential of cracks in the rod eye-end. We are 

issuing this AD to detect and correct rod eyeend cracking, which could result in 

uncontrolled elevator surface and consequent 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011), with no changes. 

(1) At the applicable times specified in 

paragraphs (g)(1)(i) and (g)(1)(ii) of this AD: 

Inspect both the left-hand and right-hand 

inboard elevator servo-control rod eye-ends 

for cracking, in accordance with the 

instructions of Airbus All Operators Telex 

(AOT) A320–27A1186, Revision 04, dated 

April 3, 2009; or the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27A1186, Revision 07, dated March 2, 2011. 

As of October 21, 2011 (the effective date of 

AD 2011–19–04, Amendment 39–16809 (76 

FR 57630, September 16, 2011)), use Airbus 

Service Bulletin A320–27A1186, Revision 07, 

dated March 2, 2011. 

(i) For airplanes that have accumulated 

10,000 total flight cycles or more as of 

September 22, 2009 (the effective date of AD 

2009–17–04, Amendment 39–15995 (74 FR 

41611, August 18, 2009)): At the later of the 

times specified in paragraphs (g)(1)(i)(A) and 

(g)(1)(i)(B) of this AD. 

(A) Within 1,500 flight cycles after 

September 22, 2009 (the effective date of AD 

2009–17–04, Amendment 39–15995 (74 FR 

41611, August 18, 2009)). 

(B) Within 1,500 flight cycles after 

accumulating 10,000 total flight cycles since 

first flight of the airplane. 

(ii) For airplanes that have accumulated 

less than 10,000 total flight cycles as of 

September 22, 2009 (the effective date of AD 

2009–17–04, Amendment 39–15995 (74 FR 

41611, August 18, 2009)): At the later of the 

times specified in paragraphs (g)(1)(ii)(A) and 

(g)(1)(ii)(B) of this AD. 

(A) Before the accumulation of 5,000 total 

flight cycles. 

(B) Within 20 months after October 21, 

2011 (the effective date of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011)) but no later than before 

the accumulation of 11,500 total flight cycles. 

(2) At the applicable time specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: 

Inspect both the left-hand and right-hand 

outboard elevator servo-control rod eye-ends 

for cracking, in accordance with the 

instructions of Airbus AOT A320–27A1186, 

Revision 04, dated April 3, 2009; or the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27A1186, Revision 07, 

dated March 2, 2011. As of October 21, 2011 

(the effective date of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011)), use Airbus Service 

Bulletin A320–27A1186, Revision 07, dated 

March 2, 2011. 

(i) For airplanes that have accumulated 

10,000 total flight cycles or more as of 

September 22, 2009 (the effective date of AD 

2009–17–04, Amendment 39–15995 (74 FR 

41611, August 18, 2009)): At the later of the 

times specified in paragraphs (g)(2)(i)(A) and 

(g)(2)(i)(B) of this AD. 

(A) Within 3,000 flight cycles after 

September 22, 2009 (the effective date of AD 

2009–17–04, Amendment 39–15995 (74 FR 

41611, August 18, 2009)). 

(B) Within 3,000 flight cycles after 

accumulating 10,000 total flight cycles since 

first flight of the airplane. 

(ii) For airplanes that have accumulated 

less than 10,000 total flight cycles as of 

September 22, 2009 (the effective date of AD 

2009–17–04, Amendment 39–15995 (74 FR 

41611, August 18, 2009)): At the later of the 

times specified in paragraphs (g)(2)(ii)(A) and 

(g)(2)(ii)(B) of this AD. 

(A) Before the accumulation of 7,500 total 

flight cycles. 

(B) Within 40 months after October 21, 

2011 (the effective date of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011)), but no later than before 

the accumulation of 13,000 total flight cycles. 

(h) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011), with no changes. 

Repeat the inspections of the left-hand and 

right-hand inboard and outboard elevator 

servo-control rod eye-ends for cracking as 

required by paragraphs (g)(1) and (g)(2) of 

this AD at the later of the times specified in 

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

the inspections thereafter at intervals not to 

exceed 5,000 flight cycles. 

(1) Within 5,000 flight cycles after the last 

inspection required by paragraph (g)(1) or 

(g)(2) of this AD as applicable. 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations 57089 

(2) Within 6 months after October 21, 2011 

(the effective date of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011)). 

(i) Retained Corrective Actions 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–19–04, Amendment 

39–16809 (76 FR 57630, September 16, 2011), 

with no changes. If any cracking is found 

during any inspection required by paragraph 

(g) or (h) of this AD, before further flight, 

accomplish all applicable corrective actions, 

in accordance with the Accomplishment 

Instructions and figures of Airbus Service 

Bulletin A320–27A1186, Revision 07, dated 

March 2, 2011. 

(j) Retained Parts Installation Limitation for 

Elevator Servo-Control Rod Eye-Ends 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–19–04, Amendment 

39–16809 (76 FR 57630, September 16, 2011), 

with a new exception. As of October 21, 2011 

(the effective date of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57360, 

September 16, 2011)), and except as required 

by paragraph (p) of this AD, no person may 

install on any airplane an elevator servocontrol rod eye-end unless it is new or has 

been inspected in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27A1186, Revision 07, 

dated March 2, 2011, with no crack findings. 

(k) New Requirement of This AD: Inspection 

To Determine Part Numbers 

As of the effective date of this AD: At the 

later of the times specified in paragraphs 

(k)(1) and (k)(2) of this AD, do an inspection 

to determine whether any elevator control 

part having part number (P/N) 31075–0xx, 

31075–1xx, or 31075–3xx is installed. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part numbers of the elevator control parts can 

be conclusively determined from that review. 

(1) Concurrently with the accomplishment 

of the next inspection required by paragraph 

(g) or (h) of this AD. 

(2) Within 30 days after the effective date 

of this AD. 

(l) New Requirement of This AD: 

Replacement of Certain Parts 

If the inspection required by paragraph (k) 

of this AD reveals that any elevator servocontrols having P/Ns 31075–0xx, 31075–1xx, 

or 31075–3xx are installed: Before further 

flight, do the actions specified in paragraph 

(l)(1) or (l)(2) of this AD. 

(1) Replace all elevator servo-controls 

having P/N 31075–0xx, 31075–1xx, or 

31075–3xx with serviceable parts having P/ 

N 31075–2xx or 31075–4xx, as applicable, 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

Serviceable parts are those that have been 

inspected for cracks in the rod eye-ends 

without any crack findings, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–27A1186, 

Revision 07, dated March 2, 2011. 

(2) Replace all elevator servo-controls 

having P/N 31075–0xx, 31075–1xx, or 

31075–3xx with serviceable parts having P/ 

N 31075–6xx or 31075–8xx, as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1223, dated September 3, 2013; or UTC 

Aerospace Systems Service Bulletin 31075– 

27–22, dated July 2, 2013. 

(m) New Optional Terminating Action for 

Certain Inspections 

Modification of an airplane by replacing all 

4 elevator servo-control rod eye-ends with 

modified (i.e. re-greasable) parts, and reidentification of those elevator servo-controls 

to P/N 31075–6xx or P/N 31075–8xx, as 

applicable, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1223, dated 

September 3, 2013; constitutes terminating 

action for the requirements of paragraphs (g), 

(h), (k), and (l) of this AD. 

Note 1 to paragraph (m) of this AD: 

Maintenance Review Board Report task 

reference 27.34.00/06, Lubrication of Elevator 

Servo-control Rod Eye End Bearing, is 

applicable to elevator servo-controls having 

P/N 31075–6xx or P/N 31075–8xx. 

(n) Airplanes Excluded From Certain 

Inspection Requirements 

Airplanes on which Airbus Modification 

154554 (installation of servo-controls having 

P/N 31075–6xx or P/N 31075–8xx, fitted with 

modified rod eye-end roller bearing) has been 

embodied in production are not affected by 

the requirements of paragraphs (g), (h), (k), 

and (l) of this AD, provided that no elevator 

servo-control having P/N 31075–0xx, or P/N 

31075–1xx, or P/N 31075–2xx, or P/N 31075– 

3xx, or P/N 31075–4xx, fitted with rod eyeend assembly P/N 341203-xxx, has been 

reinstalled since first flight. 

(o) Credit for Previous Actions 

(1) This paragraph restates the credit 

specified in paragraph (k) of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011). 

(i) This paragraph provides credit for 

actions required by paragraphs (g)(1) and 

(g)(2) of this AD, if those actions were 

performed before October 21, 2011 (the 

effective date of AD 2011–19–04, 

Amendment 39–16809 (76 FR 57630, 

September 16, 2011)), using the service 

information specified in paragraphs 

(o)(1)(i)(A) through (o)(1)(i)(E) of this AD. 

(A) Airbus AOT A320–27A1186, dated 

June 23, 2008, which is not incorporated by 

reference in this AD. 

(B) Airbus AOT A320–7A1186, Revision 

01, dated August 11, 2008, which is not 

incorporated by reference in this AD. 

(C) Airbus AOT A320–7A1186, Revision 

02, dated March 30, 2009, which is not 

incorporated by reference in this AD. 

(D) Airbus AOT 320–7A1186, Revision 03, 

dated April 1, 2009, which is not 

incorporated by reference in this AD. 

(E) Airbus AOT A320–27A1186, Revision 

04, dated April 3, 2009, which was 

incorporated by reference in AD 2009–17–04, 

Amendment 39–15995 (74 FR 41611, August 

18, 2009), which continues to be 

incorporated by reference in this AD. 

(ii) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before 

October 21, 2011 (the effective date of AD 

2011–19–04, Amendment 39–16809 (76 FR 

57630, September 16, 2011)), using Airbus 

Service Bulletin A320–27A1186, Revision 05, 

dated March 10, 2010; or Airbus Service 

Bulletin A320–27A1186, Revision 06, dated 

December 14, 2010; which are not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (i) of this AD, 

if those actions were performed before 

October 21, 2011 (the effective date of AD 

2011–19–04, Amendment 39–16809 (76 FR 

57630, September 16, 2011)), using Airbus 

Service Bulletin A320–27A1186, Revision 06, 

dated December 14, 2010, which is not 

incorporated by reference in this AD. 

(p) New Parts Installation Prohibition 

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

person may install on any airplane an 

elevator servo-control having P/N 31075–0xx, 

31075–1xx, or 31075–3xx. 

(2) No person may install on any airplane 

an elevator servo-control having P/N 31075– 

2xx or P/N 31075–4xx, or an elevator servocontrol rod eye-end having P/N 341203 or P/ 

N 341203–XXX, as required by paragraphs 

(p)(2)(i) and (p)(2)(ii) of this AD, as 

applicable. 

(i) For airplanes that do not have Airbus 

Modification 154554 embodied in 

production: After optional modification of 

the airplane as specified in paragraph (m) of 

this AD. 

(ii) For airplanes on which Airbus 

Modification 154554 has been embodied in 

production: As of the effective date of this 

AD. 

(q) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2011–19–04, Amendment 39–16809 (76 FR 

57630, September 16, 2011), are approved as 

AMOCs for the corresponding provisions of 

this AD. 


Lhorne on DSK5TPTVN1PROD with RULES
57090 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations 

(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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(r) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0137, dated 

May 28, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2014–0753. 

(2) Airbus Service information identified in 

this AD that is not incorporated by reference 

is available at the addresses specified in 

paragraphs (s)(6) and (s)(8) of this AD. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 27, 2015. 

(i) Airbus Service Bulletin A320–27–1223, 

dated September 3, 2013. 

(ii) UTC Aerospace Systems Service 

Bulletin 31075–27–22, dated July 2, 2013. 

(4) The following service information was 

approved for IBR on October 21, 2011 (76 FR 

57630, September 16, 2011). 

(i) Airbus Service Bulletin A320–27A1186, 

Revision 07, including Appendices 1, 2, 3, 4, 

5, and 6, dated March 2, 2011. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on September 22, 2009 (74 

FR 41611, August 18, 2009). 

(i) Airbus All Operators Telex A320– 

27A1186, Revision 04, dated April 3, 2009. 

The document number and issue date of 

Airbus AOT A320–27A1186, Revision 04, 

dated April 3, 2009, are specified only on the 

first page of the AOT. 

(ii) Reserved. 

(6) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airworth-eas@

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

(7) For UTC service information identified 

in this AD, contact UTC Aerospace Systems; 

Roger Dangremont; telephone +01 34 32 63 

28; email roger.dangrement@goodrich.com. 

(8) 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. 

(9) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–23541 Filed 9–21–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 886 

[Docket No. FDA–2015–N–3044] 

Medical Devices; Ophthalmic Devices; 

Classification of the Oral Electronic 

Vision Aid 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Final order. 

SUMMARY: The Food and Drug 

Administration (FDA) is classifying the 

oral electronic vision aid into class II 

(special controls). The special controls 

that will apply to the device are 

identified in this order and will be part 

of the codified language for the oral 

electronic vision aid’s classification. 

The Agency is classifying the device 

into class II (special controls) in order 

to provide a reasonable assurance of 

safety and effectiveness of the device. 

DATES: This order is effective September 

22, 2015. The classification was 

applicable on June 18, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Dexiu Shi, Center for Devices and 

Radiological Health, Food and Drug 

Administration, 10903 New Hampshire 

Ave., Bldg. 66, Rm. 2246, Silver Spring, 

MD, 20993–0002, 301–796–6470, 

dexiu.shi@fda.hhs.gov. 

SUPPLEMENTARY INFORMATION: 

I. Background 

In accordance with section 513(f)(1) of 

the Federal Food, Drug, and Cosmetic 

Act (the FD&C Act) (21 U.S.C. 

360c(f)(1)), devices that were not in 

commercial distribution before May 28, 

1976 (the date of enactment of the 

Medical Device Amendments of 1976), 

generally referred to as postamendments 

devices, are classified automatically by 

statute into class III without any FDA 

rulemaking process. These devices 

remain in class III and require 

premarket approval, unless and until 

the device is classified or reclassified 

into class I or II, or FDA issues an order 

finding the device to be substantially 

equivalent, in accordance with section 

513(i), to a predicate device that does 

not require premarket approval. The 

Agency determines whether new 

devices are substantially equivalent to 

predicate devices by means of 

premarket notification procedures in 

section 510(k) of the FD&C Act (21 

U.S.C. 360(k)) and part 807 (21 CFR part 

807) of the regulations. 

Section 513(f)(2) of the FD&C Act (21 

U.S.C. 360c(f)(2)), as amended by 

section 607 of the Food and Drug 

Administration Safety and Innovation 

Act (Pub. L. 112–144), provides two 

procedures by which a person may 

request FDA to classify a device under 

the criteria set forth in section 513(a)(1). 

Under the first procedure, the person 

submits a premarket notification under 

section 510(k) of the FD&C Act for a 

device that has not previously been 

classified and, within 30 days of 

receiving an order classifying the device 

into class III under section 513(f)(1), the 

person requests a classification under 

section 513(f)(2). Under the second 

procedure, rather than first submitting a 

premarket notification under section 

510(k) and then a request for 

classification under the first procedure, 

the person determines that there is no 

legally marketed device upon which to 

base a determination of substantial 

equivalence and requests a classification 

under section 513(f)(2) of the FD&C Act. 

If the person submits a request to 

classify the device under this second 

procedure, FDA may decline to 

undertake the classification request if 

FDA identifies a legally marketed device 

that could provide a reasonable basis for 

review of substantial equivalence with 

the device or if FDA determines that the 

device submitted is not of ‘‘lowmoderate risk’’ or that general controls 

would be inadequate to control the risks 

and special controls to mitigate the risks 

cannot be developed. 

In response to a request to classify a 

device under either procedure provided 

by section 513(f)(2) of the FD&C Act, 

FDA will classify the device by written 

order within 120 days. This 

classification will be the initial 

classification of the device. 

On August 7, 2013, Wicab Inc., 

submitted a request for classification of 

the BrainPort V100 under section 

513(f)(2) of the FD&C Act. The 

manufacturer recommended that the 

device be classified into class II (Ref. 1). 

In accordance with section 513(f)(2) of 

the FD&C Act, FDA reviewed the 

request in order to classify the device 

under the criteria for classification set 

forth in section 513(a)(1). FDA classifies 


Lhorne on DSK5TPTVN1PROD with RULES