## 25254 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules

(iii) Airbus Service Bulletin A340–57– 4106, Revision 01, dated June 31, 2009.

(iv) Airbus Service Bulletin A340–57– 4106, Revision 02, dated June 15, 2011.

(2) For airplanes that have been modified as of the effective date of this AD in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: No action is required by this paragraph, except as otherwise required by paragraph (l) of this AD and, provided that if any crack was found during any modification specified in this paragraph and the service information specified to contact Airbus, repair was done before further flight using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(o) Optional Terminating Actions

(1) Modification of an airplane in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (o)(1)(i), (o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or (o)(1)(vi) of this AD; as applicable to airplane type and depending on airplane configuration; terminates the requirements of this AD, provided that in case of any crack finding during any modification specified in this paragraph, and the service information specifies to contact Airbus, repair is done before further flight, using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature

(i) Airbus Service Bulletin A330–57–3090, dated March 27, 2006.

(ii) Airbus Service Bulletin A330–57–3090, Revision 01, dated June 15, 2011.

(iii) Airbus Service Bulletin A330–57– 3098, Revision 03, including Appendix 01, dated September 24, 2012.

(iv) Airbus Service Bulletin A340–57– 4098, dated March 27, 2006.

(v) Airbus Service Bulletin A340–57–4098, Revision 01, dated June 15, 2011.

(vi) Airbus Service Bulletin A340–57– 4106, Revision 03, including Appendix 01, dated September 24, 2012.

(2) Accomplishment of the ultrasonic inspection required by paragraph (l) of this AD and all applicable corrective actions required by paragraph (m) of this AD terminates the requirements of this AD for those airplanes.
(p) 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: 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. 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) AMOCs approved previously for AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011), are approved as AMOCs for the corresponding provisions of this AD.

(3) Contacting the Manufacturer: As of the effective date of this AD, 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 Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(q) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0010R1, dated May 5, 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–
2015–0937.

(2) For service information identified in this AD, 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 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 April 13,
2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–10177 Filed 5–1–15; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0934; Directorate Identifier 2014–NM–030–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 all Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE–FALCON 200 airplanes; and Model MYSTERE–FALCON 20–C5, 20– D5, 20–E5, and 20–F5 airplanes. This proposed AD was prompted by reports of defective fire extinguisher tubes. It was determined the defects were caused by corrosion. This proposed AD would require repetitive general visual inspections of the fire extinguisher tubes for cracking and corrosion, and replacement of any cracked tube with a serviceable tube, if necessary. We are proposing this AD to detect and correct cracking and corrosion in the fire extinguisher tubes, which could impact the capability to extinguish an engine fire, and possibly result in damage to the airplane and injury to the
passengers.

**DATES** 

### : We must receive comments on this proposed AD by June 18, 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. 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– 0934; 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,


## 25255 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules

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–2015–0934; Directorate Identifier 2014–NM–030–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 2013–0299, dated December 19, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE– FALCON 200 airplanes; and Model MYSTERE–FALCON 20–C5, 20–D5, 20– E5, and 20–F5 airplanes. The MCAI
states:

Several defective extinguisher tubes have been reported on certain Dassault Aviation Fan Jet Falcon aeroplanes. The results of the investigations concluded that these occurrences were caused by corrosion.

This condition, if not detected and corrected, could impact the capability to extinguish an engine fire, possibly resulting in damage to the aeroplane and injury to the occupants.

For the reason described above, this [EASA] AD requires repetitive [general visual] inspections [for cracking and corrosion] of the fire extinguisher tubes and, depending on findings, the replacement of an affected part with a serviceable part (improved fire extinguisher tube). It also proposes the replacement of those tubes with the ‘‘old Part Number’’ (P/N) with a serviceable part with the new P/N as a terminating action. In addition, this [EASA] AD prohibits installation of an affected tube on an aeroplane. 

### 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–
0934. 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 170 airplanes of U.S. registry.

We also estimate that it would take about 4 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 $57,800, or $340 per product.

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):

Dassault Aviation: Docket No. FAA–2015– 0934; Directorate Identifier 2014–NM– 030–AD.
(a) Comments Due Date

We must receive comments by June 18,
2015.
(b) Affected ADs

None. (c) Applicability

This AD applies to Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE–FALCON 200 airplanes; and Model MYSTERE–FALCON 20–C5, 20–D5, 20–E5, and 20–F5 airplanes, certificated in any category, all manufacturer serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 26, Fire protection.

(e) Reason

This AD was prompted by reports of defective fire extinguisher tubes. It was determined the defects were caused by


## 25256 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules

corrosion. We are issuing this AD to detect and correct cracking and corrosion in the fire extinguisher tubes, which could impact the capability to extinguish an engine fire, and possibly result in damage to the airplane and injury to the passengers.
(f) Compliance

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

For airplanes identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Within 13 months or 450 flight hours, whichever occurs first after the effective date of this AD, do a general visual inspection of the fire extinguisher tubes for cracking and corrosion, in accordance with 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). Repeat the inspection thereafter at intervals not to exceed 13 months.

(1) Model FAN JET FALCON airplanes and Model FAN JET FALCON SERIES C, D, E, F, and G airplanes, equipped with any fire extinguisher tubes having part numbers MY20791–101, MY20791–101–1, MY20791– 102, MY20791–102–1, MY20791–117, and MY20791–112. (2) Model MYSTERE–FALCON 200 airplanes equipped with any fire extinguisher tubes having part numbers M20H791000210B1 and M20H791000240B1.

(3) Model MYSTERE–FALCON 20–C5, 20– D5, 20–E5, and 20–F5 airplanes equipped with any fire extinguisher tubes having part numbers M20R791101, M20R791101A1, and M20R791102.
(h) Corrective Action

If, during any inspection required by paragraph (g) of this AD, any cracking or corrosion is found, before further flight, replace the tube with a serviceable tube having a part number specified in Table 1 of paragraph (h) of this AD, as applicable.



### TABLE 

### 1 OF 

### PARAGRAPH 

### (h) OF THIS 

### AD—S ERVICEABLE 

### F IRE 

### EXTINGUISHER 

### TUBES

For model— Equipped with affected pin— Replace with serviceable pin—

FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes ................................. MY20791–101 MY20791-101–2 FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes ................................. MY20791–101–1 MY20791–101–2 FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes ................................. MY20791–102 MY20791–102–2 FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes ................................. MY20791-102–1 MY20791–102–2 FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes ................................. MY20791–117 MY20791–117–1 FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes ................................. MY20791–112 MY20791–112–1 MYSTERE–FALCON 200 airplanes ................................................................................................... . M20H791000210B1 M20H791000210B2 MYSTERE–FALCON 200 airplanes ................................................................................................... . M20H791000240B1 M20H791000240B2 MYSTERE–FALCON 20-C5, 20–D5, 20–E5, and 20–F5 airplanes ................................................... M20R791101 M20R791101 A2 MYSTERE–FALCON 20–C5, 20–D5, 20–E5, and 20–F5 airplanes .................................................. M20R791101A1 M20R79110 1A3 MYSTERE–FALCON 20–C5, 20–D5, 20–E5, and 20–F5 airplanes .................................................. M20R791102 M20R791102A2

(i) Terminating Action for the Repetitive Inspections

Replacement of an affected tube with a serviceable tube, as required by paragraph (h) of this AD, constitutes a terminating action for the repetitive inspections required by paragraph (g) of this AD.
(j) Parts Installation Prohibition

As of the effective date of this AD, no person may install a tube having a part number identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, on any airplane.
(k) 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) 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.

(l) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0299, dated December 19, 2013, 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–2015–0934.

Issued in Renton, Washington, on April 17,

2015. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–10179 Filed 5–1–15; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF HOMELAND **SECURITY**

**Coast Guard**

**33 CFR Part 147**

**[Docket No. USCG–2015–0248]**

**RIN 1625–AA00**



### Safety Zone; NOBLE DISCOVERER, **Outer Continental Shelf Drillship, Chukchi Sea, Alaska** 

**AGENCY** 

### : Coast Guard, DHS.

**ACTION** 

### : Notice of proposed rulemaking.

**SUMMARY** 

### : The Coast Guard proposes a safety zone that extends 500 meters from the outer edge of the DRILLSHIP NOBLE DISCOVERER, as well as 500 meters from those points, suitably marked by a buoy, where the DRILLSHIP NOBLE DISCOVERER’s mooring spread meets the ocean’s surface. This safety zone would be in effect both when the DRILLSHIP NOBLE DISCOVERER is anchored and when deploying and recovering moorings. As a result, the size and shape of the safety zone will vary, depending on how far from the vessel the mooring spread is deployed, which is expected to be no more than 1,000 meters. This safety zone would be in effect when the DRILLSHIP NOBLE DISCOVERER is on