Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73099 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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 ATR—GIE Avions de Transport 

Re ́gional’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0074, dated 

March 21, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

!documentDetail;D=FAA-2015-0682-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(3) and (o)(4) of this AD. 

(o) 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. 

(i) Messier-Bugatti-Dowty Service Bulletin 

631–32–213, dated December 16, 2013. 

(ii) Messier-Bugatti-Dowty Service Bulletin 

631–32–214, dated January 13, 2014. 

(iii) Messier-Bugatti-Dowty Service 

Bulletin 631–32–215, dated January 13, 2014. 

(iv) Messier-Bugatti-Dowty Service Bulletin 

631–32–216, Revision 1, dated December 17, 

2013. Pages 4, 5, and 8 of this service bulletin 

are the original issue and are dated October 

30, 2013. 

(v) Messier-Bugatti-Dowty Service Bulletin 

631–32–219, dated March 3, 2014. 

(vi) Messier-Bugatti-Dowty Service Bulletin 

631–32–220, dated March 3, 2014. 

(3) For service information identified in 

this AD, contact ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. 

(4) 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. 

(5) 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/ibr-locations.html. 

Issued in Renton, Washington, on 

November 12, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–29682 Filed 11–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0251; Directorate 

Identifier 2014–NM–200–AD; Amendment 

39–18330; AD 2015–23–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by a determination that, in 

specific flight conditions, the allowable 

load limits on the vertical tail plane 

could be reached and possibly 

exceeded. Exceeding allowable load 

could result in detachment of the 

vertical tail plane. This AD requires 

modification of the pin programming 

flight warning computer (FWC) to 

activate the stop rudder input warning 

(SRIW) logic; and an inspection to 

determine the part numbers of the FWC 

and the flight augmentation computer 

(FAC), and replacement of the FWC and 

FAC if necessary. We are issuing this 

AD to prevent detachment of the 

vertical tail plane and consequent loss 

of control of the airplane. 

DATES: This AD becomes effective 

December 29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 29, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2015-0251; 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 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.airwortheas@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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–0251. 

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 by adding an AD that would 

apply to all Airbus Model A318, A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on March 5, 2015 (80 FR 

11960). The NPRM was prompted by a 

determination that, in specific flight 

conditions, the allowable load limits on 

the vertical tail plane could be reached 

and possibly exceeded. Exceeding 

allowable load could result in 

detachment of the vertical tail plane. 

The NPRM proposed to require 

modification of the pin programming of 

the FWC to activate the SRIW logic; and 

an inspection to determine the part 

numbers of the FWC and the FAC, and 

replacement of the FWC and FAC if 

necessary. We are issuing this AD to 

prevent detachment of the vertical tail 

plane and consequent loss of 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 2014–0217R1, dated February 

26, 2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition. The MCAI states: 

During design reviews that were conducted 

following safety recommendations related to 

in-service incidents and one accident on 

another aircraft type, it has been determined 

that, in specific flight conditions, the 

allowable load limits on the vertical tail 

plane could be reached and possibly 

exceeded. 

This condition, if not corrected, could lead, 

in the worst case, to detachment of the 

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73100 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 

vertical tail plane in flight and consequent 

loss of the aeroplane. 

To prevent such a possibility, Airbus has 

developed modifications within the flight 

augmentation computer (FAC) to reduce the 

vertical tail plane stress and to activate a 

conditional aural warning within the flight 

warning computer (FWC) to further protect 

against pilot induced rudder doublets. 

Consequently, EASA issued AD 2014–0217 

(ad.easa.europa.eu/blob/easa_ad_2014_

0217.pdf/AD_2014–0217_1) to require 

installation and activation of the stop rudder 

input warning (SRIW) logic. In addition, that 

[EASA] AD required, prior to or concurrent 

with modification of an aeroplane with the 

activation of the SRIW, upgrades of the FAC 

and FWC, to introduce the SRIW logic and 

SRIW aural capability, respectively. After 

modification, the [EASA] AD prohibited 

installation of certain Part Number (P/N) 

FWC and FAC. 

Since that [EASA] AD was issued, an 

additional previously-published Airbus 

Service Bulletin (SB) was identified, and a 

new SB was published, for the concurrent 

requirement to replace the FAC with a unit 

having a P/N as listed in Table 3 of Appendix 

1 of the AD. 

For the reasons described above, this 

[EASA] AD is revised to amend paragraph 

(2), adding references to additional Airbus 

SBs. 

In addition, this AD requires, prior to 

or concurrent with modification of an 

airplane with the activation of the 

SRIW, upgrades of the FAC and FWC to 

introduce the SRIW logic and SRIW 

aural capability, respectively. After 

modification, this AD prohibits 

installation of FWCs and FACs having 

certain part numbers. You may examine 

the MCAI in the AD docket on the 

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

!documentDetail;D=FAA-2015-0251- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 11960, 

March 5, 2015) and the FAA’s response 

to each comment. 

Request To Refer to Revised Service 

Information 

Airbus requested that we refer to 

revised service information. 

We agree with the Airbus request to 

refer to revised service information. No 

additional work is required by the 

revised service information. We have 

revised paragraph (g) of this AD to refer 

to Airbus Service Bulletin A320–22– 

1480, Revision 02, dated March 30, 

2015. We have added new paragraph 

(m)(1) of this AD to provide credit for 

the actions required by paragraph (g) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–22–1480, 

dated July 9, 2014; or Airbus Service 

Bulletin A320–22–1480, Revision 01, 

dated February 6, 2015. 

We have revised paragraph (i) of this 

AD to refer in part to the following 

service information. 

• Airbus Service Bulletin A320–22– 

1427, Revision 05, including Appendix 

01, dated November 24, 2014 (FAC 622 

hard B). 

• Airbus Service Bulletin A320–22– 

1447, Revision 03, dated April 21, 2015 

(FAC CAA02 hard C). 

• Airbus Service Bulletin A320–22– 

1454, dated February 12, 2014 (FAC 

CAA02). 

• Airbus Service Bulletin A320–22– 

1461, Revision 07, including Appendix 

01, dated March 23, 2015 (FAC B623 

hard B). 

• Airbus Service Bulletin A320–22– 

1502, dated November 14, 2014 (FAC 

CAA02). 

We have redesignated paragraph (m) 

of the proposed AD (80 FR 11960, 

March 5, 2015) as new paragraph (m)(2) 

of this AD to provide credit for the 

actions required by paragraph (i) of this 

AD, if those actions were performed 

before the effective date of this AD using 

the following additional service 

information. 

• Airbus Service Bulletin A320–22– 

1427, Revision 04, dated February 11, 

2014. 

• Airbus Service Bulletin A320–22– 

1447, Revision 01, dated September 18, 

2014. 

• Airbus Service Bulletin A320–22– 

1447, Revision 02, dated December 2, 

2014. 

• Airbus Service Bulletin A320–22– 

1461, Revision 04, dated September 15, 

2014. 

• Airbus Service Bulletin A320–22– 

1461, Revision 05, dated November 13, 

2014. 

• Airbus Service Bulletin A320–22– 

1461, Revision 06, dated January 21, 

2015. 

Request To Clarify Approved Parts 

United Airlines (UAL) requested that 

we split paragraph (h)(3)(iv) of the 

proposed AD (80 FR 11960, March 5, 

2015) into two paragraphs to clarify the 

approved parts. UAL stated that 

paragraphs (h)(3)(i), (h)(3)(ii), and 

(h)(3)(iii) of the proposed AD clearly 

denote three of the four possible 

standards of FAC, but paragraph 

(h)(3)(iv) of the proposed AD leads one 

to believe that a FAC CAA02 hard C is 

required regardless of the airplane 

configuration. 

We agree with UAL’s request to 

clarify the FWCs and FACs having the 

part numbers that are compatible with 

SRIW activation required by paragraph 

(g) of this AD. We have revised 

paragraph (h)(3)(iv) of the AD to state 

that for all airplanes configured with an 

FAC standard CAA01, an FAC having 

soft P/N G2856AAA02 installed on hard 

P/N C13206AA00 (CAA02 hard C) are 

compatible with SRIW activation 

required by paragraph (g) of this AD. We 

have added new paragraph (h)(3)(v) of 

this AD to state that for all airplane 

configurations, an FWC having P/N 

350E053021212 (H2–F7) are compatible 

with SRIW activation required by 

paragraph (g) of this AD. 

Request for Additional Details and 

Clarification Regarding SRIW Changes 

The National Transportation Safety 

Board (NTSB) stated that there are 

differences between the Airbus Model 

A300/A310 series airplane SRIW system 

and the Airbus Model A320 series 

airplane SRIW system. The NTSB 

explained that the Model A300/A310 

series airplane SRIW contains a red 

warning light on the glareshield, which 

lights when the SRIW is activated; 

however, the NPRM (80 FR 11960, 

March 5, 2015) did not mention the 

warning light as part of the Model A320 

series airplane SRIW. The NTSB also 

stated that details associated with the 

modifications of the FAC and FWC are 

not stated in the NPRM (80 FR 11960, 

March 5, 2015). The NTSB stated that 

without details regarding the changes 

associated with the Model A320 series 

airplane SRIW it cannot fully assess the 

FAA response for the Model A320 series 

airplanes to NTSB safety 

recommendations A–04–56 (http://

www.ntsb.gov/safety/safety-recs/

recletters/A04_56_62.pdf) and A–04–57 

(http://www.ntsb.gov/safety/safety-recs/

recletters/A04_56_62.pdf). The NTSB 

also wanted the FAA to clarify whether 

the Model A320 series airplane SRIW 

has more comprehensive protections 

compared with the Model A300 series 

airplane SRIW. 

We agree with the NTSB that there are 

differences between the Airbus Model 

A300/A310 series airplane and Model 

A318/A319/A320/A321 series airplane 

SRIW systems, such as, the latter does 

not include a light on the glareshield in 

front of each pilot; instead it includes a 

red master caution warning in addition 

to the aural synthetic voice warning to 

prevent pilots from making any further 

reversals. In addition, the Model Airbus 

A318/A319/A320/A321 series airplane 

SRIW modification includes a rudder 

travel limiter unit (RTLU) modification 

in the FAC that minimizes the available 

deflections for all the possible 

combinations of altitude and speed. 

This will ensure that after one full 

rudder pedal reversal, the vertical tail 

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plane (VTP) loads remain within the 

safe limits. After reviewing the design, 

analyses, and simulator demonstrations, 

the FAA has concluded that these 

warnings will prevent the flightcrew 

from continuing the inappropriate 

rudder inputs prior to exceeding the 

ultimate design loads that could result 

in failure of the vertical tail plane. We 

have determined that details associated 

with our disposition to NTSB safety 

recommendations A–04–56 and A–04– 

57 are outside the context of this AD. 

We will provide those details directly to 

the NTSB in our response to the safety 

recommendations. We have not changed 

this final rule in this regard. 

Conclusion 

We reviewed the relevant data, 

considered 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 minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

11960, March 5, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 11960, 

March 5, 2015). 

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 

A320–22–1480, Revision 02, dated 

March 30, 2015. This service 

information describes procedures for 

modifying the pin programming to 

activate the SRIW logic. 

Airbus has also issued the following 

service information. The service 

information describes procedures for 

replacing FWCs and FACs. 

• Airbus Service Bulletin A320–22– 

1375, dated January 15, 2014. 

• Airbus Service Bulletin A320–22– 

1427, Revision 05, dated November 24, 

2014. 

• Airbus Service Bulletin A320–22– 

1447, Revision 03, dated April 21, 2015. 

• Airbus Service Bulletin A320–22– 

1454, dated February 12, 2014. 

• Airbus Service Bulletin A320–22– 

1461, Revision 07, dated March 23, 

2015. 

• Airbus Service Bulletin A320–22– 

1502, dated November 14, 2014. 

• Airbus Service Bulletin A320–31– 

1414, Revision 03, dated September 15, 

2014. 

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 953 

airplanes of U.S. registry. 

We also estimate that it will take 

about 3 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 $243,015, or $255 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 6 work-hours (3 work-hours for an 

FWC and 3 work-hours for an FAC), for 

a cost of up to $510 per product. We 

have received no definitive data that 

will enable us to provide part cost 

estimates for the on-condition actions 

specified in this AD. We have no way 

of determining the number of aircraft 

that might need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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-2015-0251; 

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 adding 

the following new airworthiness 

directive (AD): 

2015–23–13 Airbus: Amendment 39–18330. 

Docket No. FAA–2015–0251; Directorate 

Identifier 2014–NM–200–AD. 

(a) Effective Date 

This AD becomes effective December 29, 

2015. 

(b) Affected ADs 

None. 

(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. 

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73102 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 

(d) Subject 

Air Transport Association (ATA) of 

America Code 22, Auto Flight; 31, 

Instruments. 

(e) Reason 

This AD was prompted by a determination 

that, in specific flight conditions, the 

allowable load limits on the vertical tail 

plane could be reached and possibly 

exceeded. Exceeding allowable load could 

result in detachment of the vertical tail plane. 

We are issuing this AD to prevent 

detachment of the vertical tail plane and 

consequent loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Pin Programming Modification 

Within 48 months after the effective date 

of this AD, modify the pin programming to 

activate the stop rudder input warning 

(SRIW) logic, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–22–1480, Revision 02, 

dated March 30, 2015. 

(h) Inspection To Determine Part Numbers 

(P/Ns), Flight Warning Computer (FWC) and 

Flight Augmentation Computer (FAC) 

Replacement 

Prior to or concurrently with the actions 

required by paragraph (g) of this AD: Inspect 

the part numbers of the FWC and the FAC 

installed on the airplane. If any FWC or FAC 

having a part number identified in paragraph 

(h)(1) or (h)(2) of this AD, as applicable, is 

installed on an airplane, prior to or 

concurrently with the actions required by 

paragraph (g) of this AD, replace all affected 

FWCs and FACs with a unit having a part 

number identified in paragraph (h)(3) of this 

AD, in accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraph (i) of this 

AD. 

(1) Paragraphs (h)(1)(i) through (h)(1)(xvii) 

of this AD identify FWCs having part 

numbers that are non-compatible with the 

SRIW activation required by paragraph (g) of 

this AD. 

(i) 350E017238484 (H1D1). 

(ii) 350E053020303 (H2E3). 

(iii) 350E016187171 (C5). 

(iv) 350E053020404 (H2E4). 

(v) 350E017248685 (H1D2). 

(vi) 350E053020606 (H2F2). 

(vii) 350E017251414 (H1E1). 

(viii) 350E053020707 (H2F3). 

(ix) 350E017271616 (H1E2). 

(x) 350E053021010 (H2F3P). 

(xi) 350E018291818 (H1E3CJ). 

(xii) 350E053020808 (H2F4). 

(xiii) 350E018301919 (H1E3P). 

(xiv) 350E053020909 (H2–F5). 

(xv) 350E018312020 (H1E3Q). 

(xvi) 350E053021111 (H2–F6). 

(xvii) 350E053020202 (H2E2). 

(2) Paragraphs (h)(2)(i) through 

(h)(2)(xxxiv) of this AD identify FACs having 

part numbers that are non-compatible with 

the SRIW activation required by paragraph 

(g) of this AD. 

(i) B397AAM0202. 

(ii) B397BAM0101. 

(iii) B397BAM0512. 

(iv) B397AAM0301. 

(v) B397BAM0202. 

(vi) B397BAM0513. 

(vii) B397AAM0302. 

(viii) B397BAM0203. 

(ix) B397BAM0514. 

(x) B397AAM0303. 

(xi) B397BAM0305. 

(xii) B397BAM0515. 

(xiii) B397AAM0404. 

(xiv) B397BAM0406. 

(xv) B397BAM0616. 

(xvi) B397AAM0405. 

(xvii) B397BAM0407. 

(xviii) B397BAM0617. 

(xix) B397AAM0506. 

(xx) B397BAM0507. 

(xxi) B397BAM0618. 

(xxii) B397AAM0507. 

(xxiii) B397BAM0508. 

(xxiv) B397BAM0619. 

(xxv) B397AAM0508. 

(xxvi) B397BAM0509. 

(xxvii) B397BAM0620. 

(xxviii) B397AAM0509. 

(xxix) B397BAM0510. 

(xxx) B397CAM0101. 

(xxxi) B397AAM0510. 

(xxxii) B397BAM0511. 

(xxxiii) B397CAM0102. 

(xxxiv) Soft P/N G2856AAA01 installed on 

hard P/N C13206AA00. 

(3) Paragraphs (h)(3)(i) through (h)(3)(v) of 

this AD identify the FWCs and FACs having 

the part numbers that are compatible with 

SRIW activation required by paragraph (g) of 

this AD. 

(i) For airplane configurations with no 

sharklet, an FAC having P/N B397BAM0621 

(621 hard B). 

(ii) For airplanes configured with sharklet 

A320 and A319, an FAC having P/N 

B397BAM0622 (622 hard B). 

(iii) For airplanes configured with sharklet 

A321, an FAC having P/N B397BAM0623 

(623 hard B). 

(iv) For all airplanes configured with an 

FAC standard CAA01, an FAC having soft P/ 

N G2856AAA02 installed on hard P/N 

C13206AA00 (CAA02 hard C). 

(v) For all airplane configurations, an FWC 

having P/N 350E053021212 (H2–F7). 

(i) Service Information for Actions Required 

by Paragraph (h) of This AD 

Do the actions required by paragraph (h) of 

this AD in accordance with the 

Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraphs (i)(1) through (i)(7) of 

this AD. 

(1) Airbus Service Bulletin A320–22–1375, 

dated January 15, 2014 (FAC 621 hard B). 

(2) Airbus Service Bulletin A320–22–1427, 

Revision 05, including Appendix 01, dated 

November 24, 2014 (FAC 622 hard B). 

(3) Airbus Service Bulletin A320–22–1447, 

Revision 03, dated April 21, 2015 (FAC 

CAA02 hard C). 

(4) Airbus Service Bulletin A320–22–1454, 

dated February 12, 2014 (FAC CAA02). 

(5) Airbus Service Bulletin A320–22–1461, 

Revision 07, including Appendix 01, dated 

March 23, 2015 (FAC 623 hard B). 

(6) Airbus Service Bulletin A320–22–1502, 

dated November 14, 2014 (FAC CAA02). 

(7) Airbus Service Bulletin A320–31–1414, 

Revision 03, dated September 15, 2014 (FWC 

H–F7). 

(j) Exclusion From Actions Required by 

Paragraphs (g) and (h) of This AD 

An airplane on which Airbus Modification 

154473 has been embodied in production is 

excluded from the requirements of 

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

that within 30 days after the effective date of 

this AD, an inspection of the part numbers 

of the FWC and the FAC installed on the 

airplane is done to determine that no FWC 

having a part number listed in paragraph 

(h)(1) of this AD, and no FAC having a part 

number listed in paragraph (h)(2) of this AD, 

has been installed on that airplane since date 

of manufacture. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part numbers of the 

FWC and FAC can be conclusively 

determined from that review. If any FWC or 

FAC having a part number identified in 

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

applicable, is installed on a post-Airbus 

Modification 154473 airplane: Within 30 

days after the effective date of this AD, do the 

replacement required by paragraph (h) of this 

AD. 

(k) Parts Installation Prohibitions 

After modification of an airplane as 

required by paragraphs (g), (h), and (j) of this 

AD: Do not install on that airplane any FWC 

having a part number listed in paragraph 

(h)(1) of this AD or any FAC having a part 

number listed in paragraph (h)(2) of this AD. 

(l) Later Approved Parts 

Installation of a version (part number) of 

the FWC or FAC approved after the effective 

date of this AD is an approved method of 

compliance with the requirements of 

paragraph (h) or (j) of this AD, provided the 

requirements specified in paragraphs (l)(1) 

and (l)(2) of this AD are met. 

(1) The version (part number) must be 

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). 

(2) The installation 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. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–22–1480, dated July 9, 2014; 

or Airbus Service Bulletin A320–22–1480, 

Revision 01, dated February 6, 2015. This 

service information is 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 the 

effective date of this AD using the applicable 

Airbus service information identified in 

paragraphs (m)(2)(i) through (m)(2)(xviii) of 

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Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73103 

this AD. This service information is not 

incorporated by reference in this AD. 

(i) Airbus Service Bulletin A320–22–1427, 

dated January 25, 2013. 

(ii) Airbus Service Bulletin A320–22–1427, 

Revision 01, dated July 30, 2013. 

(iii) Airbus Service Bulletin A320–22– 

1427, Revision 02, dated October 14, 2013. 

(iv) Airbus Service Bulletin A320–22– 

1427, Revision 03, dated November 8, 2013. 

(v) Airbus Service Bulletin A320–22–1427, 

Revision 04, dated February 11, 2014. 

(vi) Airbus Service Bulletin A320–22– 

1447, dated October 18, 2013. 

(vii) Airbus Service Bulletin A320–22– 

1447, Revision 01, dated September 18, 2014. 

(viii) Airbus Service Bulletin A320–22– 

1447, Revision 02, dated December 2, 2014. 

(ix) Airbus Service Bulletin A320–22– 

1461, dated October 31, 2013. 

(x) Airbus Service Bulletin A320–22–1461, 

Revision 01, dated February 25, 2014. 

(xi) Airbus Service Bulletin A320–22– 

1461, Revision 02, dated April 30, 2014. 

(xii) Airbus Service Bulletin A320–22– 

1461, Revision 03, dated July 17, 2014. 

(xiii) Airbus Service Bulletin A320–22– 

1461, Revision 04, dated September 15, 2014. 

(xiv) Airbus Service Bulletin A320–22– 

1461, Revision 05, dated November 13, 2014. 

(xv) Airbus Service Bulletin A320–22– 

1461, Revision 06, dated January 21, 2015. 

(xvi) Airbus Service Bulletin A320–31– 

1414, dated December 19, 2012. 

(xvii) Airbus Service Bulletin A320–31– 

1414, Revision 01, dated March 21, 2013. 

(xviii) Airbus Service Bulletin A320–31– 

1414, Revision 02, dated July 30, 2013. 

(n) 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. 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) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(3) 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. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0217R1, dated 

February 26, 2015, for related information. 

This MCAI may be found in the AD docket 

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

gov/#!documentDetail;D=FAA-2015-0251- 

0003. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(3) and (p(4) of this AD. 

(p) 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. 

(i) Airbus Service Bulletin A320–22–1375, 

dated January 15, 2014. 

(ii) Airbus Service Bulletin A320–22–1427, 

Revision 05, including Appendix 01, dated 

November 24, 2014. 

(iii) Airbus Service Bulletin A320–22– 

1447, Revision 03, dated April 21, 2015. 

(iv) Airbus Service Bulletin A320–22– 

1454, dated February 12, 2014. 

(v) Airbus Service Bulletin A320–22–1461, 

Revision 07, including Appendix 01, dated 

March 23, 2015. 

(vi) Airbus Service Bulletin A320–22– 

1480, Revision 02, dated March 30, 2015. 

(vii) Airbus Service Bulletin A320–22– 

1502, dated November 14, 2014. 

(viii) Airbus Service Bulletin A320–31– 

1414, Revision 03, dated September 15, 2014. 

(3) For 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. 

(4) 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. 

(5) 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/ibr-locations.html. 

Issued in Renton, Washington, on 

November 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–29702 Filed 11–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–1869; Airspace 

Docket No. 15–AGL–9] 

Establishment of Class E Airspace; 

Newberry, MI 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: This action corrects an error 

in the legal description of a final rule 

published in the Federal Register of 

September 24, 2015, that establishes 

Class E airspace at the Newberry VHF 

Omni-Directional Range/Distance 

Measuring Equipment (VOR/DME), 

Newberry, MI. The legal description 

noted exclusionary language for Federal 

airways and Canadian airspace not 

required for this airspace. 

DATES: Effective date: 0901 UTC, 

December 10, 2015. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 Code of Federal Regulations, Part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: Raul 

Garza, Jr., Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 10101 Hillwood Parkway., Fort 

Worth, TX 76177; telephone 817–222– 

5874. 

SUPPLEMENTARY INFORMATION: 

History 

On September 24, 2015, a final rule 

was published in the Federal Register 

establishing Class E airspace at the 

Newberry VOR/DME, Newberry, MI (80 

FR 57522) Docket No. FAA–2015–1869. 

Subsequent to publication, the FAA 

found that the exclusionary language for 

Federal airways and Canadian airspace 

noted in the airspace description is not 

required and, therefore, is removed. 

Final Rule Correction 

Accordingly, pursuant to the 

authority delegated to me, in the 

Federal Register of September 24, 2015, 

(80 FR 57522) FR Doc. 2015–23987, on 

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