This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510.

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# Rules and Regulations Federal Register 

### 73687

Vol. 78, No. 236

Monday, December 9, 2013

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0979; Directorate Identifier 2013–NM–223–AD; Amendment**  **39–17697; AD 2013–25–01]**

**RIN 2120–AA64**

**Airworthiness Directives; DASSAULT AVIATION Airplanes** 

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all DASSAULT AVIATION Model Falcon10 airplanes. This AD requires a onetime inspection for cracking of the righthand (RH) and left-hand (LH) inboard flaps, and replacement if necessary. This AD was prompted by reports of cracking found on the inboard end plate (rib) of the RH inboard flap. We are issuing this AD to detect and correct such cracking, which could lead to complete fracture of the rib and loss of integrity of the flap structure, resulting in loss of control of the airplane.

**DATES :**  This AD becomes effective December 24, 2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 24, 2013.

We must receive comments on this AD by January 23, 2014.

**ADDRESSES :**  You may send comments 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 AD, contact Dassault Falcon Jet, 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; or in person at the Docket Operations office 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. 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 :** 

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0262, dated October 30, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI
states:

Cracks were found on two Falcon 10 aeroplanes on the inboard end plate (rib) of the Right Hand (RH) inboard flap. On both aeroplanes the crack had initiated in the same area of the rib. This condition, if not detected and corrected, could lead to complete fracture of the rib and loss of integrity of the flap

structure.

To address this potential unsafe condition, Dassault Aviation published Service Bulletin (SB) F10–318, which provides instructions for inspection of the affected area.

For reasons described above, this [EASA] AD requires a one-time [detailed] inspection of the RH and Left Hand (LH) inboard flaps and, depending on findings, replacement of the cracked part.

You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0979.

Relevant Service Information

Dassault Aviation has issued Mandatory Service Bulletin F10–318, dated October 30, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
FAA’s Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

FAA’s Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because cracking of the inboard end plate (rib) of the inboard flap could lead to complete fracture of the rib and loss of integrity of the flap structure, resulting in loss of control of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.


### 73688 Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Rules and Regulations

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA–2013–0979; Directorate Identifier 2013–NM–223– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. Costs of Compliance

We estimate that this AD affects 81 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

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

Inspection ................... 1 work-hour × $85 per hour = $85 .................................................... $0 $85 $6,885

We estimate the following costs to do any necessary replacement that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need this replacement:



### O N 

### -CONDITION 

### COSTS

Action Labor cost Parts cost Cost per product

Replacement ..................... 2 work-hours × $85 per hour = $170 ....................................................................... $41,600 $41,770

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):

2013–25–01 DASSAULT AVIATION: Amendment 39–17697. Docket No. FAA–2013–0979; Directorate Identifier 2013–NM–223–AD. (a) Effective Date This AD becomes effective December 24,
2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to DASSAULT AVIATION Model Falcon 10 airplanes, certificated in any category, all serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 27, Flight controls.
(e) Reason

This AD was prompted by reports of cracking found on the inboard end plate (rib) of the right-hand inboard flap. We are issuing this AD to detect and correct such cracking, which could lead to complete fracture of the rib and loss of integrity of the flap structure, resulting in loss of control of the airplane.
(f) Compliance

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

Within 65 days after the effective date of this AD, do a detailed inspection for cracking of ribs 1 and 3 of the left- and right-hand inboard flaps, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin F10–318, dated October 30, 2013. If any cracking is found, before further flight, replace the inboard flap with a crack-free serviceable flap, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin F10–318, dated October 30, 2013.


### 73689 Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Rules and Regulations

(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, 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the DAH with a State of Design Authority’s design organization approval). For a repair method to be approved, the repair approval must specifically refer to this AD. You are required to ensure the product is airworthy before it is returned to service.
(i) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0262, dated October 30, 2013, for related information. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0979.
(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 Mandatory Service Bulletin F10–318, dated October 30, 2013.

(ii) Reserved. (3) For service information identified in this AD, contact Dassault Falcon Jet, 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.

(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 November 26, 2013. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–29122 Filed 12–6–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0753; Directorate Identifier 2013–CE–025–AD; Amendment**  **39–17677; AD 2013–24–03]**

**RIN 2120–AA64**

**Airworthiness Directives; Beechcraft Corporation Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation (type certificate previously held by Hawker Beechcraft Corporation) Models 1900, 1900C, and 1900D airplanes. This AD was prompted by reports of cracking in the front spar cap angles and hat section structure of the vertical stabilizer. This AD requires inspections of the vertical stabilizer spar angles and hat section for cracks with corrective actions as necessary. We are issuing this AD to correct the unsafe condition on these products.

**DATES :**  This AD is effective January 13,
2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 13, 2014.

**ADDRESSES :**  For service information identified in this AD, contact Beechcraft Corporation at address: 10511 E. Central, Wichita, Kansas 67206; phone: (800) 429–5372 or (316) 676–3140; Internet: http://www.beechcraft.com/
customer

_support/contact

_ us/. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 address for the Docket Office (phone: 800–647–5527) is Document 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 :**  Paul Chapman, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4152; fax: (316) 946–4107; email: paul.chapman@faa.gov.

**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 the specified products. The NPRM published in the Federal Register on August 27, 2013 (78 FR 52870). The NPRM proposed to require doing visual inspections of the vertical stabilizer spar angles and hat section for cracks and taking corrective actions as
necessary.

Comments

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

Scott Lewis suggested that the number of cracks reported may not be accurate. The commenter stated that his fleet had 53 cracks, which is a much higher percentage of airplanes cracked than the 56 cracks reported in the 140 airplanes that Beechcraft reported to the FAA. The commenter proposed no changes to the AD.

We agree that the percentage of cracks reported may be low. This further justifies the need for the AD action and therefore, no changes to the final rule
are necessary. Costs of Compliance Too Low

Scott Lewis stated the costs supplied by Beechcraft are too low and that the actual costs are running $5,983 per side for the spar cap angles plus $9,212 for engineer support for a total of $15,195. This is compared to the $3,150 cited in the NPRM. This does not include the cost of the hat section if it requires repair.