### 68688 Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations

operated as before the change under VMC, safety in relation to lightning effects is not diminished by installing a ‘‘glass cockpit’’. An operation in IMC, which would to our mind require a lightning protection system in accordance with FAR 23.867(c), is not considered and not permitted (reference AFM). For these reasons AQUILA proposes to remove the added requirement 14 CFR 23.867 from the Airworthiness Design Standards as listed in the NPRM.

The FAA agrees with the commenter and has removed the added design criteria of 14 CFR part 23.867 at amendment 23–49. The final applicable design criteria for the installation of advanced avionic displays on the Aquila AT01–100 are the addition four 14 CFR part 23 regulations as shown above.
Applicability

As discussed above, these airworthiness design standards under the special class, JAR–VLA rule are applicable to the Aquila AT01–100 model and future JAR–VLA (CS–VLA) models on FAA TCDS A51CE.

Conclusion

This action affects only certain airworthiness design standards on Aquila AT01–100 model and future JAR–VLA model airplanes shown on FAA TCDS A51CE. It is not a standard of general applicability and it affects only the applicant who applied to the FAA for approval of these features on the airplane.

Citation

The authority citation for these airworthiness standards is as follows:

Authority: 49 U.S.C. 106(g), 40113 and

44701.

Issued in Kansas City, Missouri on October
28, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–26910 Filed 11–14–13; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0870; Directorate Identifier 2013–NM– 166–AD; Amendment**  **39–17657; AD 2013–23–02]**

**RIN 2120–AA64**

**Airworthiness Directives; EADS CASA (Type Certificate Previously Held by**  **Construcciones Aeronauticas, S.A.) 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 EADS CASA (Type Certificate previously held by Construcciones Aeronauticas, S.A.) Model CN–235, CN– 235–100, CN–235–200, CN–235–300, and C–295 airplanes. This AD requires inspection of the feeder cables of certain fuel booster pumps for damage (including, but not limited to, signs of electrical arcing and fuel leaks), and replacement if necessary. This AD was prompted by a report of an in-flight problem with the fuel transfer system. We are issuing this AD to detect and correct damage to certain fuel booster pumps, which could create an ignition source in the fuel tank vapor space, and result in a fuel tank explosion and consequent loss of the airplane.

**DATES :**  This AD becomes effective December 2, 2013.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 2, 2013.

We must receive comments on this AD by December 30, 2013.

**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 EADS CASA, Military 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. 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 Management Facility 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 :**  Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227– 1112; 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 2013–0186, dated August 16, 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:

An occurrence with a CN–235 aeroplane has been reported, involving an in-flight problem with the fuel transfer system.

The results of the subsequent investigation revealed damage on the fuel booster pump electrical feeding cable and some burn marks on the pump body and plate (fairing) at the external side of the fuel tank; confirmed electrical arcing between the wire and pump body; and revealed as well fuel leakage onto the affected wire.

This condition, if not detected and corrected, could create an ignition source in the fuel tank vapour space, possibly resulting in a fuel tank explosion and loss of the aeroplane.

To address this potential unsafe condition, EADS CASA (Airbus Military) issued All Operators Letter (AOL) 235–025 and AOL


### 68689 Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations

295–025, providing inspection instructions for the affected fuel booster pumps, Part Number (P/N) 1C12–34 and P/N 1C12–46.

For the reasons described above, this [EASA] AD requires a one-time [detail visual] inspection of the affected fuel booster pumps to detect damage [including, but not limited, to signs of electrical arcing and fuel leaks] and, depending on findings, replacement of the fuel booster pump. This [EASA] AD also requires the reporting of all findings to EADS CASA for evaluation.

This [EASA] AD is considered to be an interim action and further AD action may follow.
You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0870.

Relevant Service Information

Airbus Military (EADS CASA) has issued the following service information.

• For Model CN–235 airplanes: Airbus Military All Operator Letter 235– 025, dated July 29, 2013.

• For Model C–295 airplanes: Airbus Military All Operator Letter 295–025, Revision 01, dated August 1, 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 damage to the fuel booster pump could create an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss 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. 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–2013–0870; Directorate Identifier 2013–NM–166– 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 35 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

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

Inspection of fuel boost

pump. 2 work-hours × $85 per hour = $170 per fuel boost
pump. $0 $170 per fuel boost pump $11,900

We estimate the following costs to do any necessary replacements 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 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Replacement of fuel boost pump .............................. 3 work-hours × $85 per hour = $255 per pump ...... $16,080 $16,335 per pump.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. 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


### 68690 Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations

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):
2013–23–02 EADS CASA (Type Certificate Previously Held by Construcciones Aeronauticas, S.A.): Amendment 39– 17657. Docket No. FAA–2013–0870; Directorate Identifier 2013–NM–166–AD.

(a) Effective Date

This AD becomes effective December 2,
2013.
(b) Affected ADs

None. (c) Applicability This AD applies to EADS CASA (Type Certificate previously held by Construcciones Aeronauticas, S.A.) Model CN–235, CN–235– 100, CN–235–200, CN–235–300, and C–295 airplanes, certificated in any category, all manufacturer serial numbers.
(d) Subject

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

(e) Reason

This AD was prompted by a report of an in-flight problem with the fuel transfer system. We are issuing this AD to detect and correct damage to certain fuel booster pumps, which could create an ignition source in the fuel tank vapor space, and result in a fuel tank explosion and consequent loss of the airplane.
(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(g) Inspection of the Feeder Cables of Certain Fuel Booster Pumps

Within the times specified in paragraph (g)(1) or (g)(2) of this AD, as applicable: Perform a detailed visual inspection for damage (including, but not limited to, signs of electrical arcing and fuel leaks) of the electrical feeder cables of each fuel booster pump having part number (P/N) 1C12–34 or 1C12–46, in accordance with the instructions of Airbus Military All Operator Letter 235– 025, dated July 29, 2013 (for Model CN–235 airplanes); or Airbus Military All Operator Letter 295–025, Revision 01, dated August 1, 2013 (for Model C–295 airplanes).

(1) For each fuel booster pump that has not been replaced as of the effective date of this AD: Prior to the accumulation of 300 total flight hours or within 5 cycles after the effective date of this AD, whichever occurs later.

(2) For each fuel booster pump that has been replaced as of the effective date of this AD: Within 300 flight hours since the most recent fuel booster pump replacement, or within 5 flight cycles after the effective date of this AD, whichever occurs later.
(h) Replacement of Affected Fuel Boost Pumps

If any damage (including, but not limited to, signs of electrical arcing and fuel leaks) is found during the inspection required by paragraph (g) of this AD: Within the time specified in paragraph (h)(1) or (h)(2) of this AD, replace the affected fuel booster pump with a serviceable pump, in accordance with Airbus Military All Operator Letter 235–025, dated July 29, 2013 (for Model CN–235 airplanes); or Airbus Military All Operator Letter 295–025, Revision 01, dated August 1, 2013 (for Model C–295 airplanes).

(1) Before further flight. (2) Within 10 days following the inspection, provided that the airplane is operated under the conditions specified in Airbus Military All Operator Letter 235–025, dated July 29, 2013 (for Model CN–235 airplanes); or Airbus Military All Operator Letter 295–025, Revision 01, dated August 1, 2013 (for Model C–295 airplanes).
(i) Report of Inspection Findings

At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, submit an inspection report to EADS CASA (Airbus Military), in accordance with Airbus Military All Operator Letter 235–025, dated July 29, 2013 (for Model CN–235 airplanes); or Airbus Military All Operator Letter 295–025, Revision 01, dated August 1, 2013 (for Model C–295 airplanes).

(1) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection.

(2) If the inspection was done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD. (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: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 227–1112; 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 by the Design Approval Holder (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.

(3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response,


### 68691 Federal Register / Vol. 78, No. 221 / Friday, November 15, 2013 / Rules and Regulations

including the time for reviewing instructions, completing, and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer,
AES–200.

(k) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0186, dated August 16, 2013, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2013–

0870.
(l) 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) Airbus Military All Operator Letter 235– 025, dated July 29, 2013.

(ii) Airbus Military All Operator Letter 295–025, Revision 01, dated August 1, 2013.

(3) For service information identified in this AD, contact EADS–CASA, Military 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 October
31, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–27017 Filed 11–14–13; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0630; Directorate Identifier 2012–NM–213–AD; Amendment**  **39–17660; AD 2013–23–05]**

**RIN 2120–AA64**

**Airworthiness Directives; Fokker Services B.V. Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by a design review, which revealed that, under certain failure conditions, wiring in the main fuel tank could develop a short circuit that might cause a hot spot on the wiring conduit or puncture the wiring conduit wall. This AD requires installing fuses in the power supply wiring and/or return wiring for various components in the fuel system; and revising the airplane maintenance program by incorporating critical design configuration control limitations. We are issuing this AD to prevent an ignition source in the main fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.

**DATES :**  This AD becomes effective December 20, 2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 20, 2013.

**ADDRESSES :**  You may examine the AD on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0630; or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280– 350; fax +31 (0)88–6280–111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.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. **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 the specified products. The NPRM published in the Federal Register on July 31, 2013 (78 FR 46303). The NPRM proposed to correct an unsafe condition for the specified products.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0241, dated November 12, 2012 (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:

Prompted by an accident * * *, the FAA published Special Federal Aviation Regulation (SFAR) 88 [66 FR 23086, May 7, 2001], and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/25/

12.

The design review conducted by Fokker Services on the Fokker 70 and Fokker 100 in response to these regulations revealed that under certain failure conditions of the wiring of the Overflow Valve Reed Switch, or the solenoid of the Level Control Pilot Valve (LCPV), or the solenoid of the Re/De-fueling Shut- Off Valve, or the Collector-Tank Low Level Float-Switch, a short circuit may develop that causes a hot spot on the wiring conduit, or puncturing of the wiring conduit wall in the main fuel tank.

This condition, if not corrected, could create an ignition source in the main fuel tank vapour space, possibly resulting in a fuel tank explosion and consequent loss of the aeroplane.

For the reasons described above, this [EASA]AD requires the installation of fuses in the power supply wiring and/or returnwiring for the main tank overflow valve reedswitches, the LCPV solenoid, the Re/De-fuel shut-off valve solenoid and the collector-tank Low Level float switch and subsequently, the implementation of the associated Critical Design Configuration Control Limitations (CDCCL[s]) [and revising the maintenance program to incorporate the CDCCLs].
You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0630-
0002.