## 10535 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules

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– 2016–3700; Directorate Identifier 2015– NM–171–AD.
(a) Comments Due Date

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

None. (c) Applicability

This AD applies to all The Boeing Company Model 757–200 and –200CB, series airplanes, certificated in any category.
(d) Subject

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

(e) Unsafe Condition

This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices at stringer (S)–14R, lower fastener row, are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct cracking of the fuselage skin lap splice. Such cracking could result in reduced structural integrity of the airplane.
(f) Compliance

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

At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0102, dated October 8, 2015, except as required by paragraph (h) of this AD: Do an external dual frequency eddy current inspection or internal high frequency eddy current inspection for cracking of the lap splice, inner skin lower fastener row, at S–14R, station (STA) 440 through STA 540, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0102, dated October 8, 2015. Repeat either inspection thereafter at the time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0102, dated October 8,
2015. (h) Service Information Exceptions

(1) Where Boeing Alert Service Bulletin 757–53A0102, dated October 8, 2015, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) The Condition column of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0102, dated October 8, 2015, refers to total flight cycles and total flight hours ‘‘as of the original issue date of this service bulletin.’’ This AD, however, applies to the airplanes with the specified total flight cycles or total flight hours as of the effective date of this AD.
(i) Repair

If any crack is found during any inspection required by this AD, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(j) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Los Angeles 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 (k) of this AD. Information may be emailed to: 9-ANM-LAACO-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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes ODA that has been authorized by the Manager, Los Angeles ACO, to make those findings. 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.

(4) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply.

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.
(k) Related Information

(1) For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: 562–627–5348; fax: 562–627–5210; email: eric.schrieber@faa.gov.

(2) For service information identified in this AD, 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.

Issued in Renton, Washington, on February 15, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–03695 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–2016–3987; Directorate Identifier 2015–NM–165–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Dassault **Aviation 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 Dassault Aviation Model FALCON 7X airplanes. This proposed AD was prompted by a report of improperly drilled bores, located on upper and lower stiffener joints to the web at a certain frame. This proposed AD would require a one-time inspection of the bores, and repair if necessary. We are proposing this AD to detect and correct an unsatisfactory bore that can adversely affect the structural integrity of the airplane.

**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.


## 10536 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules

• 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 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. 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– 3987; 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**

### : 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** 

### :
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–2016–3987; Directorate Identifier 2015–NM–165–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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued Airworthiness Directive 2015–0204, dated October 8, 2015, (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Dassault Aviation FALCON 7X airplanes. The MCAI states:

On the assembly line of Falcon 7X airplanes, defects were detected on left hand and right hand engine pylons. A quality review revealed that bores located on upper and lower stiffener joints to the web at pylon Frame 41 were improperly drilled. Fettlings of borings, for fixing diameter 4 mm and 5 mm, were found ovalized, too deep and having irregular surface qualities under the head of fixing. Dassault Aviation identified the individual airplanes that are potentially affected by this production deficiency.

This condition, if not detected and corrected, would adversely affect the structural integrity of the airplane.

To address this potential unsafe condition Dassault Aviation published Service Bulletin (SB) 7X–346 to provide corrective action instructions.

For the reasons described above, this [EASA] AD requires a one-time [detailed] visual [and rototest] inspection for unsatisfactory bores and, depending on findings, repair of affected stiffener bores.



### A bore is not satisfactory if it has any surface defects greater than or equal to 0.5 mm or if any chamfer dimension or edge distance value is not within the dimensions specified in Dassault Aviation Service Bulletin 7X–346, dated April 24, 2015. 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–2016–3987.

Related Service Information Under 1 CFR Part 51

Dassault Aviation has issued Dassault Service Bulletin 7X–346 dated April 24, 2015. The service information describes procedures for a one-time inspection of the bores on stiffeners at Frame 41 on the engine pylons, and repair 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 and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance

We estimate that this proposed AD affects 55 airplanes of U.S. registry.

We also estimate that it would take about 66 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $308,550, or $5,610 per product.

In addition, we estimate that any necessary follow-on actions would take about 20 work-hours and require parts costing $149, for a cost of $1,849 per product. We have no way of determining the number of aircraft that might need this action.

According to the manufacturer, some of the costs of this proposed 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 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


## 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.