### 21242 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations

Transport Aircraft Division (MTAD), Integrated Customer Services (ICS), Technical Services, Avenida de Arago  ́ n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; email MTA.TechnicalService@casa.eads.net; Internet http://www.eads.net.

(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/ibrlocations.html.

Issued in Renton, Washington, on March 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–07572 Filed 4–8–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–5813; Directorate Identifier 2014–NM–111–AD; Amendment**  **39–18460; AD 2016–07–15]**

**RIN 2120–AA64**

**Airworthiness Directives; Dassault Aviation Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a fuel leak that occurred in the baggage compartment during fuel system pressurization. This AD requires opening the fuel boxes and restoring the sealing. We are issuing this AD to prevent failure of a connector or coupling on a fuel line, which, in combination with a leak in the corresponding enclosure (i.e., fuel box), could result in a fire in the baggage compartment and affect the safe flight of the airplane.

**DATES :**  This AD is effective May 16,
2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 16, 2016.

**ADDRESSES :**  For service information identified in this final rule, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201– 440–6700; Internet http:// www.dassaultfalcon.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–
5813. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 5813; 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 Office (telephone 800–647– 5527) is 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 20590.

**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 certain Dassault Aviation Model FALCON 7X airplanes. The NPRM published in the Federal Register on November 27, 2015 (80 FR 74056) (‘‘the NPRM’’). The NPRM was prompted by a fuel leak that occurred in the baggage compartment during fuel system pressurization. The NPRM proposed to require opening the fuel boxes and restoring the sealing. We are issuing this AD to detect and correct failure of a connector or coupling on a fuel line, which, in combination with a leak in the corresponding enclosure (i.e., fuel box), could result in a fire in the baggage compartment and affect the safe flight 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 2014–0116, dated May 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Dassault Aviation Model FALCON 7X airplanes. The MCAI states:

During the fuel system pressurization of a production line Falcon 7X aeroplane, a fuel leak occurred in the baggage compartment. The technical investigations concluded that a double failure of a connector (or coupling) on a fuel line, in combination with a defective fuel tightness of the corresponding enclosure (fuel box), caused the leak.

Failure of the second barrier (fuel box) is a dormant failure, as this will only manifest itself in case of connector (or fuel pipe coupling) failure in flight.

This condition, if not corrected, could result in a fire in the baggage compartment, which would affect the aeroplane safe flight.

To address this potential unsafe condition, Dassault Aviation issued Service Bulletin (SB) F7X–284, which provides instructions to restore the sealing of the Left Hand (LH) and Right Hand (RH) fuel boxes.

For the reasons described above, this [EASA] AD requires opening of the fuel boxes and restoration of the sealing of the fuel boxes to meet the initial design specifications.

You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–
5813.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM 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 for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

We reviewed Dassault Service Bulletin 7X–284, Revision 1, dated April 8, 2014. The service information describes procedures for opening the fuel boxes and restoring the sealing. This service information is reasonably available because the interested parties have access to it through their normal


### 21243 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations

course of business or by the means identified in the **ADDRESSES** section. Costs of Compliance

We estimate that this AD affects 39 airplanes of U.S. registry.

We also estimate that it will take about 16 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts are negligible. Based on these figures, we estimate the cost of this AD on U.S. operators to be $53,040, or $1,360 per product.

According to the manufacturer, all 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. 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):

2016–07–15 Dassault Aviation: Amendment 39–18460. Docket No. FAA–2015–5813; Directorate Identifier 2014–NM–111–AD.
(a) Effective Date

This AD is effective May 16, 2016.
(b) Affected ADs

None. (c) Applicability

This AD applies to Dassault Aviation Model FALCON 7X airplanes, certificated in any category, serial numbers (S/Ns) 1 through 140 inclusive, S/Ns 142 through 156 inclusive, S/Ns 158 through 176 inclusive, S/ Ns 178 through 181 inclusive, and S/N 183, 184, 187, 188, 190, 194, and 200.
(d) Subject

Air Transport Association (ATA) of America Code 28, Fuel.
(e) Reason

This AD was prompted by a fuel leak that occurred in the baggage compartment during fuel system pressurization. We are issuing this AD to prevent failure of a connector or coupling on a fuel line, which, in combination with a leak in the corresponding enclosure (i.e., fuel box), could result in a fire in the baggage compartment and affect the safe flight of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Open the Fuel Box and Restore the Sealing

Within 98 months after the effective date of this AD, open the left-hand and right-hand fuel boxes and restore the sealing, in accordance with the Accomplishment Instructions of Dassault Service Bulletin 7X– 284, Revision 1, dated April 8, 2014.

(h) 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, 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 European Aviation Safety Agency (EASA); or Dassault Aviation’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(i) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0116, dated May 13, 1014, 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–
2015–5813. (j) 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) Dassault Service Bulletin 7X–284, Revision 1, dated April 8, 2014.

(ii) Reserved. (3) For service information identified in this AD, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http:// www.dassaultfalcon.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.


### 21244 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations

(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/ibrlocations.html.

Issued in Renton, Washington, on March 25, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–07571 Filed 4–8–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1277; Directorate Identifier 2014–NM–155–AD; Amendment**  **39–18459; AD 2016–07–14]**

**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 certain Airbus Model A319, A320, and A321 series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This AD requires replacing the clips, shear webs, and angles, including doing all applicable related investigative actions, and repair if necessary. We are issuing this AD to prevent fatigue damage on the clips, shear webs, and angles; such damage could affect the structural integrity of the airplane.

**DATES :**  This AD becomes effective May 16, 2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 16, 2016.

**ADDRESSES :**  For service information identified in this final rule, 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. 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–
1277. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1277; 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.

**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 certain Airbus Model A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on May 8, 2015 (80 FR 26487) (‘‘the NPRM’’).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0177, dated July 25, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A319, A320, and A321 series airplanes. The MCAI states:

During the A320 fatigue test campaign for Extended Service Goal (ESG), it was determined that fatigue damage could appear on the clips, shear webs and angles at rear fuselage section 19, on Frame (FR) 72 and FR74.

This condition, if not detected and corrected, could affect the structural integrity of the aeroplane.

To address this potential unsafe condition, Airbus developed a modification, which has been published through Airbus Service Bulletin (SB) A320–53–1266 for in-service application to allow aeroplanes to operate up to the new ESG limit.

For the reasons described above, this [EASA] AD requires replacement of the affected clips, shear webs and angles at rear fuselage section 19, FR72 and FR74 [including all applicable related investigative actions and repair if any cracking is found].

Related investigative actions include rotating probe testing for cracking of the fastener holes and high frequency eddy current inspections for cracking of the stringers. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–
1277.

Actions Since NPRM was Issued

Since the NPRM was issued, Airbus has issued Airbus Service Bulletin A320–53–1266, Revision 03, dated May 7, 2015. We have revised paragraph (g) of this AD to reference this revised service information. We have revised paragraph (i) of this AD to give credit for actions done before the effective date of this AD using the following service information.

• Airbus Service Bulletin A320–53– 1266, dated January 11, 2013.

• Airbus Service Bulletin A320–53– 1266, Revision 01, dated June 20, 2013.

• Airbus Service Bulletin A320–53– 1266, Revision 02, dated August 13,
2014.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM

An anonymous commenter provided support for the NPRM. Request To Omit Part Replacement Requirement

United Airlines requested that we revise paragraph (h) of the proposed AD to omit the additional part replacement. United Airlines noted that paragraph (h) of the proposed AD states that the replacement of clips, shear webs, and angles must be accomplished again before 30,000 flight cycles or 60,000 flight hours, whichever occurs first, if the replacement was accomplished before 30,000 flight cycles or 60,000 flight hours, whichever occurred first from airplane’s first flight. The commenter stated that this paragraph suggests that the installation of new parts does not constitute terminating action. The commenter expressed that paragraph (g) of the proposed AD has no repetitive requirement for replacement