### 50810 Federal Register / Vol. 80, No. 162 / Friday, August 21, 2015 / Proposed Rules

control, such as heading select or vertical speed, must be plainly indicated on, or adjacent to, each control if necessary to prevent inappropriate use or confusion.

(g) Under any condition of flight appropriate to its use, the flight guidance system may not produce hazardous loads on the airplane, nor create hazardous deviations in the flight path. This applies to both fault-free operation and in the event of a malfunction, and assumes that the pilot begins corrective action within a reasonable period of time.

(h) When the flight guidance system is in use, a means must be provided to avoid excursions beyond an acceptable margin from the speed range of the normal flight envelope. If the airplane experiences an excursion outside this range, a means must be provided to prevent the flight guidance system from providing guidance or control to an unsafe speed.

(i) The flight guidance system functions, controls, indications, and alerts must be designed to minimize flight crew errors and confusion concerning the behavior and operation of the flight guidance system. Means must be provided to indicate the current mode of operation, including any armed modes, transitions, and reversions. Selector switch position is not an acceptable means of indication. The controls and indications must be grouped and presented in a logical and consistent manner. The indications must be visible to each pilot under all expected lighting conditions.

(j) Following disengagement of the auto thrust function, a caution (visual and auditory) must be provided to each pilot.

(k) During auto thrust operation, it must be possible for the flight crew to move the thrust levers without requiring excessive force. The auto thrust may not create a potential hazard when the flight crew applies an override force to the thrust levers.

(l) For purposes of this section, a transient is a disturbance in the control or flight path of the airplane that is not consistent with response to flight crew inputs or environmental conditions.

(1) A minor transient would not significantly reduce safety margins and would involve flight crew actions that are well within their capabilities. A minor transient may involve a slight increase in flight crew workload or some physical discomfort to passengers or cabin crew.

(2) A significant transient may lead to a significant reduction in safety margins, an increase in flight crew workload, discomfort to the flight crew, or physical distress to the passengers or cabin crew, possibly including non-fatal injuries. Significant transients do not require, in order to remain within or recover to the normal flight envelope, any of the following:

i. Exceptional piloting skill, alertness, or strength.

ii. Forces applied by the pilot which are greater than those specified in § 23.143(c).

iii. Accelerations or attitudes in the airplane that might result in further hazard to secured or non-secured occupants.

Cirrus must also demonstrate, through tests and analysis, that no single failure or malfunction or probable combinations of failures of the auto thrust system components results in the probability for LOTC, or un-commanded thrust changes and transients that result in an LOTC event, to exceed the following:

1. Average Events per Million Hours: 10 (1X10

¥ 05 per hour)

2. Maximum Events per Million Hours: 100 (1X10

¥ 04 per hour)

Note: The term ‘‘probable’’ in the context of ‘‘probable combination of failures’’ does not have the same meaning as used for a safety assessment process. The term ‘‘probable’’ in ‘‘probable combination of failures’’ means ‘‘foreseeable,’’ or those failure conditions anticipated to occur one or more times during the operational life of each airplane.

Issued in Kansas City, Missouri, on August 13, 2015. Earl Lawrence, Manger, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–20756 Filed 8–20–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3144; Directorate Identifier 2014–NM–110–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Dassault Aviation** 

**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 900EX airplanes and FALCON 2000EX airplanes. This proposed AD was prompted by a report of significant fuel leakage at the middle position of the left outboard slat. This proposed AD would require modifying the assembly of the slat extension mechanical stop. We are proposing this AD to prevent failure of the assembly of the slat extension mechanical stop, which if not corrected, could lead to a significant fuel leak and result in an uncontained fire.

**DATES :**  We must receive comments on this proposed AD by October 5, 2015.

**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 proposed 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 by searching for and locating Docket No. FAA–2015– 3144; 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.


### 50811 Federal Register / Vol. 80, No. 162 / Friday, August 21, 2015 / Proposed Rules

**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–2015–3144; Directorate Identifier 2014–NM–110–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 EASA Airworthiness Directive 2014–0115, 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 900EX airplanes and FALCON 2000EX airplanes. The MCAI states:

After landing, an aeroplane experienced a significant fuel leakage at the middle position of the left outboard slat. Investigations showed that the fuel spillage originated in a structural cap, which had been punctured by a broken locking pin of the slat extension mechanical stop.

A design review revealed that the locking pin could become loose due to an incorrectinstallation combined with a non-faulttolerant design.

This condition, if not corrected, may lead to a significant fuel leak, possibly resulting in an uncontained fire.

To address this potential unsafe condition, Dassault Aviation developed a modification of the slat extension mechanical stop assembly (Mod M3678 for F2000EX aeroplanes and Mod M5870 for F900EX aeroplanes) with the purpose to increase its robustness with regards to possible mishandling on production or during maintenance. Dassault Aviation also published Service Bulletin (SB) F2000EX– 344 and SB F900EX–450, for embodiment in service of that modification.

For the reasons described above, this [EASA AD] requires modification of the slat extension mechanical stop assembly.

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–
3144.

Related Service Information Under 1 CFR Part 51

We reviewed Dassault Service Bulletin F900EX–450, dated March 10, 2014; and Service Bulletin F2000EX– 344, dated March 10, 2014. This service information describes procedures for modifying the assembly of the slat extension mechanical stop. 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 NPRM. 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 these same type designs. Costs of Compliance

We estimate that this proposed AD affects 67 airplanes of U.S. registry.

We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $3,510 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $280,730, or $4,190 per product. 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):

Dassault Aviation: Docket No. FAA–2015– 3144; Directorate Identifier 2014–NM– 110–AD.
(a) Comments Due Date

We must receive comments by October 5,
2015.
(b) Affected ADs

None. (c) Applicability

This AD applies to Dassault Aviation airplanes specified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.

(1) Dassault Aviation Model FALCON 900EX airplanes, all serial numbers on which Dassault Aviation Modification M5281 has


### 50812 Federal Register / Vol. 80, No. 162 / Friday, August 21, 2015 / Proposed Rules

been embodied, except those on which Dassault Aviation Modification M5870 has been embodied in production.

(2) Dassault Aviation Model FALCON 2000EX airplanes, all serial numbers on which Dassault Aviation Modification M2846 has been embodied, except those on which Dassault Aviation Modification M3678 has been embodied in production.
(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason

This AD was prompted by a report of significant fuel leakage at the middle position of the left outboard slat. We are issuing this AD to prevent failure of the assembly of the slat extension mechanical stop, which if not corrected, could lead to a significant fuel leak and result in an uncontained fire.
(f) Compliance

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

Within 9 months or 440 flight hours, whichever occurs first after the effective date of this AD: Modify the assembly of the slat extension mechanical stop, in accordance with Accomplishment Instructions of Dassault Service Bulletin F900EX–450, dated March 10, 2014; or Dassault Service Bulletin F2000EX–344, dated March 10, 2014, as applicable.
(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 (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0115, dated May 13, 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–
2015–3144.

(2) 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 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 August 11, 2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–20586 Filed 8–20–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3143; Directorate Identifier 2015–NM–047–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Empresa Brasileira de Aeronautica S.A.**  **(Embraer) 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 Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB–135 airplanes and Model EMB–145, –145ER, –145MR, –145LR, –145MP, and –145EP airplanes. This proposed AD was prompted by a report of chafing between the fuel pump electrical harness and the fuel pump tubing during scheduled maintenance. This proposed AD would require a detailed inspection for chafing on the electrical harness of each electrical fuel pump in the fuel tanks, replacing the affected electrical fuel pump with a new or serviceable pump if necessary, and installing clamps on the fuel pump electrical harnesses. We are proposing this AD to detect and correct chafing of the fuel pump harnesses with other parts inside the fuel tank, which could present a potential ignition source that could result in a fire or fuel tank explosion. **DATES :**  We must receive comments on this proposed AD by October 5, 2015.

**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 proposed AD, contact Empresa Brasileira de Aeronautica S.A. (Embraer), Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170–Putim–12227–901 Sa  ̃ o Jose dos Campos–SP–Brasil; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927–7546; email distrib@ embraer.com.br; Internet http:// www.flyembraer.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–2015– 3143; 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 :**  Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1175; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about