73096 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 

and modification required by the 

introductory text to paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (n)(2)(i), 

(n)(2)(ii), or (n)(2)(iii) of this AD, as 

applicable. 

(i) Airbus Service Bulletin A330–53–3160, 

dated July 9, 2007, which was incorporated 

by reference in AD 2008–22–20, Amendment 

39–15717 (73 FR 66747, November 12, 2008). 

(ii) Airbus Service Bulletin A330–53–3160, 

Revision 01, dated April 28, 2009, which is 

not incorporated by reference in this AD. 

(iii) Airbus Service Bulletin A330–53– 

3160, Revision 02, dated March 29, 2010, 

which is not incorporated by reference in this 

AD. 

(3) For Model A340–300 airplanes, WV 027 

only: This paragraph provides credit for the 

inspection and modification required by 

paragraph (k) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Service Bulletin A340– 

53–4172, dated July 10, 2007, which is was 

incorporated by reference in AD 2008–22–20, 

Amendment 39–15717 (73 FR 66747, 

November 12, 2008). 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

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

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0012R1, dated 

January 24, 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–2015–0490. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(q) 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 December 29, 2015. 

(i) Airbus Service Bulletin A330–53–3159, 

Revision 02, dated March 29, 2010. 

(ii) Airbus Service Bulletin A330–53–3160, 

Revision 03, dated January 6, 2012. 

(iii) Airbus Service Bulletin A330–53– 

3168, Revision 02, dated December 21, 2011. 

(iv) Airbus Service Bulletin A340–53– 

4165, Revision 02, dated March 29, 2010. 

(v) Airbus Service Bulletin A340–53–4172, 

Revision 01, dated July 8, 2009. 

(vi) Airbus Service Bulletin A340–53– 

4174, Revision 02, dated December 21, 2011. 

(4) The following service information was 

approved for IBR on December 17, 2008 (73 

FR 66747, November 12, 2008). 

(i) Airbus Service Bulletin A330–53–3168, 

Revision 01, dated February 15, 2008. 

(ii) Airbus Service Bulletin A340–53–4174, 

Revision 01, dated February 15, 2008. 

(5) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(6) 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. 

(7) 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 October 

30, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28886 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–2015–0682; Directorate 

Identifier 2014–NM–074–AD; Amendment 

39–18329; AD 2015–23–12] 

RIN 2120–AA64 

Airworthiness Directives; ATR—GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

ATR—GIE Avions de Transport 

Re ́gional Model ATR42 and ATR72 

airplanes. This AD was prompted by 

new occurrences of certain cracked 

main landing gear (MLG) rear hinge 

pins. This AD requires identifying the 

serial number and part number of the 

MLG rear hinge pins, and replacing pins 

or the MLG if necessary. We are issuing 

this AD to detect and correct cracked 

rear hinge pins, which could lead to 

MLG structural failure, possibly 

resulting in collapse of the MLG and 

consequent injury to the occupants 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=FAA2015-0682; 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 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. 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 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73097 

and locating Docket No. FAA–2015– 

0682. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

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 ATR—GIE Avions de 

Transport Re ́gional Model ATR42 and 

ATR72 airplanes. The NPRM published 

in the Federal Register on April 10, 

2015 (80 FR 19246). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0074, dated March 21, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all ATR—GIE 

Avions de Transport Re ́gional Model 

ATR42 and ATR72 airplanes. The MCAI 

states: 

Prompted by cases of rupture of Main 

Landing Gear (MLG) rear hinge pin part 

number (P/N) D61000 encountered in service 

in 1994 and 1996, DGAC France issued [an] 

AD * * * for ATR 42 aeroplanes and 

[another]AD * * * for ATR 72 aeroplanes to 

require inspection and, depending on 

findings, corrective action. 

Since those [French] ADs were issued, new 

occurrences of cracked rear hinge pin P/N 

D61000 were reported on ATR72 MLG. 

The result of subsequent investigation 

revealed that the affected pins were subjected 

to a non-detected thermal abuse done in 

production during grinding process. Analysis 

also showed that other MLG pin P/N’s could 

be affected by the same nonconformity. 

This condition, if not detected and 

corrected, could lead to MLG structural 

failure, possibly resulting in collapse of the 

MLG and consequently injury to the 

occupants of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires inspection and, 

depending on findings, replacement of 

affected pins. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2015-0682-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 19246, April 10, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

19246, April 10, 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 19246, 

April 10, 2015). 

Related Service Information Under 1 

CFR Part 51 

Messier-Bugatti-Dowty has issued the 

following service information, which 

describes procedures for inspecting the 

MLG hinge pin. 

• Service Bulletin 631–32–213, dated 

December 16, 2013. 

• Service Bulletin 631–32–214, dated 

January 13, 2014. 

• Service Bulletin 631–32–215, dated 

January 13, 2014. 

• Service Bulletin 631–32–216, 

Revision 1, dated December 17, 2013. 

• Service Bulletin 631–32–219, dated 

March 3, 2014. 

• Service Bulletin 631–32–220, dated 

March 3, 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 81 

airplanes of U.S. registry. 

We also estimate that it will take 

about 8 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $16,000 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$1,351,080, or $16,680 per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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-2015-0682; 

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: 

mstockstill on DSK4VPTVN1PROD with RULES

73098 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 

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): 

2015–23–12 ATR—GIE Avions de 

Transport Re ́gional: Amendment 39– 

18329. Docket No. FAA–2015–0682; 

Directorate Identifier 2014–NM–074–AD. 

(a) Effective Date 

This AD becomes effective December 29, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to ATR—GIE Avions de 

Transport Re ́gional Model ATR42–200, –300, 

–320, and –500 airplanes; and Model 

ATR72–101, –201, –102, –202, –211, –212, 

and –212A airplanes; certificated in any 

category; all certified models; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by new 

occurrences of certain cracked main landing 

gear (MLG) rear hinge pins. We are issuing 

this AD to detect and correct cracked rear 

hinge pins, which could lead to MLG 

structural failure, possibly resulting in 

collapse of the MLG and consequent injury 

to the occupants of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Hinge Pin Identification and Replacement 

for Model ATR72 Airplanes 

For Model ATR72 airplanes: Within 12 

months after the effective date of this AD, 

inspect for the serial number of the left-hand 

(LH) and right-hand (RH) MLG rear hinge 

pins having part number (P/N) D61000. A 

review of airplane maintenance records is 

acceptable in lieu of this identification if the 

part number and serial number of the LH and 

RH MLG rear hinge pins can be conclusively 

determined from that review. If a rear hinge 

pin having P/N D61000 has a serial number 

listed in Messier-Bugatti-Dowty Service 

Bulletin 631–32–213, dated December 16, 

2013; or Messier-Bugatti-Dowty Service 

Bulletin 631–32–216, Revision 1, dated 

December 17, 2013; as applicable: Within 12 

months after the effective date of this AD, 

replace the pin with a serviceable part as 

identified in paragraph (h) of this AD, in 

accordance with the Accomplishment 

Instructions of Messier-Bugatti-Dowty 

Service Bulletin 631–32–213, dated 

December 16, 2013; or Messier-Bugatti-Dowty 

Service Bulletin 631–32–216, Revision 1, 

dated December 17, 2013; as applicable. 

(h) Definition of Serviceable Hinge Pin for 

Model ATR72 Airplanes 

For Model ATR72 airplanes: For purposes 

of paragraph (g) of this AD, a serviceable 

MLG rear hinge pin is a pin that is specified 

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

(1) A hinge pin that is not identified in 

Messier-Bugatti-Dowty Service Bulletin 631– 

32–213, dated December 16, 2013; or 

Messier-Bugatti-Dowty Service Bulletin 631– 

32–216, Revision 1, dated December 17, 

2013; as applicable. 

(2) A hinge pin that has been inspected and 

reconditioned, in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–213, 

dated December 16, 2013; or Messier-BugattiDowty Service Bulletin 631–32–216, 

Revision 1, dated December 17, 2013; as 

applicable. 

(i) MLG Pin Identification and Replacement 

for Model ATR72 Airplanes 

For Model ATR72 airplanes: At the earlier 

of the times specified in paragraphs (i)(1) and 

(i)(2) of this AD, inspect all LH and RH MLG 

pins for a part number and serial number 

listed in Messier-Bugatti-Dowty Service 

Bulletin 631–32–214, dated January 13, 2014; 

or Messier-Bugatti-Dowty Service Bulletin 

631–32–219, dated March 3, 2014; as 

applicable. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number and serial 

number of the LH and RH MLG pin can be 

conclusively determined from that review. If 

any affected MLG pin is found: At the earlier 

of the compliance times specified in 

paragraphs (i)(1) and (i)(2) of this AD, replace 

the MLG with a serviceable MLG as 

identified in paragraph (j) of this AD, using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or ATR— 

GIE Avions de Transport Re ́gional’s EASA 

Design Organization Approval (DOA). 

(1) No later than the next MLG overhaul 

scheduled after the effective date of this AD. 

(2) Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

installation of the MLG on an airplane since 

new or since last overhaul, as applicable. 

(j) Definition of Serviceable MLG for Model 

ATR72 Airplanes 

For Model ATR72 airplanes: For purposes 

of paragraph (i) of this AD, a serviceable MLG 

is one that incorporates pins specified in 

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

(1) Pins that are not identified in MessierBugatti-Dowty Service Bulletin 631–32–214, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–219, dated 

March 3, 2014; as applicable. 

(2) Pins that have been inspected and 

reconditioned in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–214, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–219, dated 

March 3, 2014; as applicable. 

(k) MLG Pin Identification and Replacement 

for Model ATR42 Airplanes 

(1) For Model ATR42 airplanes: Within the 

compliance time identified in paragraph 

(k)(1)(i) or (k)(1)(ii) of this AD, whichever 

occurs first, inspect for any LH and RH MLG 

pins having a part number and serial number 

listed in Messier-Bugatti-Dowty Service 

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

or Messier-Bugatti-Dowty Service Bulletin 

631–32–220, dated March 3, 2014; as 

applicable. A review of airplane maintenance 

records is acceptable in lieu of this 

identification if the part number and serial 

number of the LH and RH MLG pin can be 

conclusively determined from that review. 

(i) No later than the next MLG overhaul 

scheduled after the effective date of this AD. 

(ii) Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

installation of the MLG on an airplane since 

new or since last overhaul, as applicable. 

(2) If the MLG pin having a part number 

and serial number listed in Messier-BugattiDowty Service Bulletin 631–32–215, dated 

January 13, 2014; or Messier-Bugatti-Dowty 

Service Bulletin 631–32–220, dated March 3, 

2014; as applicable; is found to be installed 

during the identification required by 

paragraph (k)(1) of this AD, within the 

compliance time identified in paragraph 

(k)(1) of this AD, replace the MLG with a 

serviceable MLG, 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. A serviceable MLG is 

a part that has pins as identified in paragraph 

(k)(2)(i) or (k)(2)(ii) of this AD. 

(i) Pins that are not listed in MessierBugatti-Dowty Service Bulletin 631–32–215, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–220, dated 

March 3, 2014; as applicable. 

(ii) Pins that have been inspected and 

reconditioned, in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–215, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–220, dated 

March 3, 2014; as applicable. 

(l) Credit for Previous Actions 

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 Messier-Bugatti-Dowty 

Service Bulletin 631–32–216, dated October 

30, 2013, which is not incorporated by 

reference in this AD. 

(m) 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: 

Tom Rodriguez, Aerospace Engineer, 

mstockstill on DSK4VPTVN1PROD with RULES

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 

mstockstill on DSK4VPTVN1PROD with RULES