### 10537 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules

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 this proposed regulation:

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. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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):

Dassault Aviation: Docket No. FAA–2016– 3987; Directorate Identifier 2015–NM– 165–AD.
(a) Comments Due Date

We must receive comments by April 15,
2016.
(b) Affected ADs

None. (c) Applicability

This AD applies to Dassault Aviation Model FALCON 7X airplanes, certificated in any category, manufacturer serial numbers 1 through 221 inclusive, except serial numbers 182 and 220.
(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

This AD was prompted by a report of improperly drilled bores, located on upper and lower stiffener joints to the web at a certain frame. We are issuing this AD to detect and correct an unsatisfactory bore that can adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done.
(g) Inspect Bores

Within 4,000 flight cycles or 98 months, whichever occurs first since date of issuance of the original airworthiness certificate or date of issuance of the original export certificate of airworthiness, do a detailed visual and rototest inspection of the bores, located on upper and lower stiffener joints to the web at pylon Frame 41, to determine if the bores are not satisfactory, in accordance with the Accomplishment Instructions of Dassault Service Bulletin 7X–346, dated April 24, 2015.
(h) Repair

If, during the inspection required by paragraph (g) of this AD, it is determined that any bore is not satisfactory: Before further flight, repair affected bores, in accordance with the Accomplishment Instructions of Dassault Service Bulletin 7X–346, dated April 24, 2015, except as required by paragraph (i) of this AD.
(i) Exceptions

Where the Dassault Service Bulletin 7X– 346, dated April 24, 2015, specifies to contact Dassault Aviation: Before further flight, repair 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).
(j) 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 EASA; or Dassault Aviation’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0204, dated October 8, 2015, for related information. This MCAI may be found on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–
2016–3987.

(2) 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. 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.

Issued in Renton, Washington, on February 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–04295 Filed 2–29–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–3986; Directorate Identifier 2015–NM–147–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–400, 747–400D, and 747–400F series airplanes. This proposed AD was prompted by a determination that a certain fastener type in the fuel tank walls has insufficient bond to the structure, and an electrical wiring short could cause arcing to occur at the ends of fasteners in the fuel tanks. This proposed AD would require the installation of new clamps and polytetrafluoroethylene (TFE) sleeves on the wire bundles of the front spars and rear spars of the wings. This proposed AD would also require inspecting the existing TFE sleeves under the wire bundle clamps for correct installation, and replacement if necessary. We are proposing this AD to prevent potential ignition sources in the fuel tank in theevent of a lightning strike or highpowered short circuit, and consequent fire or explosion.


### 10538 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules

**DATES :**  We must receive comments on this proposed AD by April 15, 2016.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206– 766–5680; Internet https:// www.myboeingfleet.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–2016–
3986. 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–2016– 3986; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Tung Tran, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6505; fax: 425–917–6590; email: Tung.Tran@ faa.gov.

**SUPPLEMENTARY INFORMATION :**  Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2016–3986; Directorate Identifier 2015– NM–147–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

The manufacturer has determined that a certain fastener type in the fuel tank walls has insufficient bond to the structure, and an electrical wiring short could cause arcing to occur at the ends of fasteners in the fuel tanks. Potential ignition sources in the fuel tank in theevent of a lightning strike or highpowered short circuit, if not corrected, could result in a fire or explosion. Related Rulemaking

On September 17, 2007, we issued AD 2007–20–01, Amendment 39–15211 (72 FR 54533, September 26, 2007), applicable to certain The Boeing Company Model 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, and 747SP series airplanes. That AD requires reconfiguring the clamps of certain wire bundles and applying insulating sealant to certain fasteners inside the fuel tanks using Boeing Special Attention Service Bulletin 747– 57–2327, Revision 1, dated July 10, 2006, on airplane line numbers 696 through 1363. Airplane line numbers 1364 through 1419 were changed during production. The actions required by AD 2007–20–01 are intended to prevent arcing inside the fuel tanks in the event of a lightning strike or high-powered short circuit, which could result in a fuel tank explosion or fire.

Since we issued AD 2007–20–01, Amendment 39–15211 (72 FR 54533, September 26, 2007), the FAA has determined that for certain The Boeing Company Model 747–400, 747–400D, and 747–400F series airplanes, a certain fastener type in the fuel tank walls has insufficient bond to the structure and that an electrical wiring short could cause arcing to occur at the ends of fasteners in the fuel tanks. We determined that certain clamp locations need to be changed to prevent possible ignition sources in the fuel tanks. These clamps were not installed at these locations during production and were not identified in Boeing Special Attention Service Bulletin 747–57– 2327, Revision 1, dated July 10, 2006. Therefore, it is necessary to install new clamps and TFE sleeves at these additional locations on the wire bundles of the front spars and rear spars of the left and right wings.

Related Service Information Under 1 CFR Part 51

We reviewed Boeing Special Attention Service Bulletin 747–28– 2324, Revision 1, dated July 27, 2015. The service information describes procedures for installing new clamps and TFE sleeves on the wire bundles of the front spars and rear spars of the wings. The service information also describes procedures for inspecting TFE sleeves under the wire bundle clamps that were installed using the procedures specified in Boeing Special Attention Service Bulletin 747–28–2324, dated November 4, 2014, for correct installation, and replacing them if necessary. 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.

FAA’s Determination

We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements

This proposed AD would require accomplishing the actions specified in the service information described previously. Costs of Compliance

We estimate that this proposed AD affects 135 airplanes of U.S. registry.

We estimate the following costs to comply with this proposed AD:


### 10539 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules

E STIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Installation of wire bundle clamps Up to 7 work-hours × $85 per hour = $595 .............. $138 Up to $733 ....... Up to $98,955. Inspection ...................................... Up to 5 work-hours × $85 per hour = $425 .............. $0 Up to $425 ....... Up to $57,375.

We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

(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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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):
The Boeing Company: Docket No. FAA– 2016–3986; Directorate Identifier 2015– NM–147–AD.
(a) Comments Due Date

We must receive comments by April 15,
2016.
(b) Affected ADs

None. (c) Applicability

This AD applies to The Boeing Company Model 747–400, 747–400D, and 747–400F series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 747–28–2324, Revision 1, dated July 27, 2015.
(d) Subject

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

This AD was prompted by a determination that a certain fastener type in the fuel tank walls has insufficient bond to the structure, and an electrical wiring short could cause arcing to occur at the ends of fasteners in the fuel tanks. We are issuing this AD to prevent potential ignition sources in the fuel tank inthe event of a lightning strike or highpowered short circuit, and consequent fire or explosion.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Installation/Inspection

Within 60 months after the effective date of this AD, do the actions specified in paragraph (g)(1) or (g)(2) of this AD, as applicable.

(1) For airplanes on which the modification specified in Boeing Special Attention Service Bulletin 747–28–2324, dated November 3, 2014, has not been done as of the effective date of this AD: Install new clamps and polytetrafluoroethylene (TFE) sleeves on the wire bundles of the front spars and rear spars of the wings, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–28–2324, Revision 1, dated July 27,
2015.

(2) For airplanes on which the modification specified in Boeing Special Attention Service Bulletin 747–28–2324, dated November 3, 2014, has been done as of the effective date of this AD: Do a detailed inspection of the TFE sleeves under the wire bundle clamps for correct installation, and replace the sleeves if not correctly installed, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–28–2324, Revision 1, dated July 27, 2015.
(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (i)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.

(2) 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair, alteration, or modification required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD.
(i) Related Information

(1) For more information about this AD, contact Tung Tran, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6505; fax: 425–917–6590; email: Tung.Tran@faa.gov.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services


### 10540 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules

Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on February 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–04292 Filed 2–29–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–3984; Directorate Identifier 2014–NM–119–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to supersede Airworthiness Directive (AD) 2013–10– 03, for all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. AD 2013–10–03 currently requires one-time inspections for deformation and damage of the bogie beams of the main landing gear (MLG); repetitive inspections for damage and corrosion of the sliding piston sub-assembly on certain airplanes; and related investigative and corrective actions if necessary. Since we issued AD 2013–10–03, we have determined that certain one-time inspections are no longer necessary, certain compliance times may be extended, and an optional terminating action should be provided. This proposed AD would remove Model A340–500, and –600 series airplanes from the applicability, remove certain one-time inspections of the MLG bogiebeams and the sliding piston subassembly; revise certain compliance times and provide, for certain airplanes, an optional terminating action for the repetitive actions. We are proposing this AD to detect and correct damage or corrosion under the bogie stop pad of both MLG bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane, or collapse of the MLG and departure of the airplane from the runway.

**DATES :**  We must receive comments on this proposed AD by April 15, 2016.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, 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. 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. 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–2016– 3984; 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 proposed 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. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  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.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2016–3984; Directorate Identifier 2014–NM–119–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On May 13, 2013, we issued AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013). AD 2013–10– 03 requires actions intended to address an unsafe condition on all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. (AD 2013–10–03 superseded AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)).

Since we issued AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013), we have determined that certain one-time inspections are no longer necessary, certain compliance times may be extended, and an optional terminating action should be provided.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014– 0120R1, dated August 31, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330– 200, –200 Freighter, and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. The MCAI states:

During a scheduled maintenance inspection on the Main Landing Gear (MLG), the bogie stop pad was found deformed and cracked. Upon removal of the bogie stop pad for replacement, the bogie beam was also found cracked.

The results of a laboratory investigation indicated that an overload event had occurred and no fatigue propagation of the crack was evident.

A second bogie beam crack was subsequently found on another aeroplane, located under a bogie stop pad which only had superficial paint damage.

This condition, if not detected and corrected, could lead to landing gear bogie detachment from the aeroplane, or landing gear collapse, or a runway excursion,