## 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


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

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:


## 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 theAccomplishment 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 theAccomplishment 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 numberand 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 theAccomplishment 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,


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

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 theDOA, 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