### 69989 Federal Register / Vol. 78, No. 226 / Friday, November 22, 2013 / Rules and Regulations

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 90–26–12, Amendment 39–6841 (55 FR 51406, December 14, 1990), and adding the following new AD:

2013–23–07 Erickson Air-Crane Incorporated (Type Certificate Previously Held By Sikorsky Aircraft Corporation): Amendment 39–17662; Docket No. FAA–2013–0556; Directorate Identifier 2007–SW–30–AD.
(a) Applicability

This AD applies to Erickson Air-Crane Incorporated (Erickson) Model S–64E and S– 64F helicopters, with rotary wing blade assembly (main rotor blade), part number 6415–20201–043, –045, –047, –048, –049, –050, or –051; or 6415–20601–041, –042, –043, –044, –045, –046, –047, –048, –049, –050, –051, or –052, installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as a crack in the main rotor blade (blade), which could result in blade separation and subsequent loss of control of the helicopter.
(c) Affected ADs

This AD supersedes AD 90–26–12, Docket No. 90–ASW–27, Amendment 39–6841 (55 FR 51406, December 14, 1990).
(d) Effective Date

This AD becomes effective December 27,
2013. (e) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(f) Required Actions

(1) Before further flight, visually check the Blade Inspection Method (BIM) pressure indicators of the main rotor blades for a black or red color indication.

(2) Before further flight, replace any blade with a black or red color indication in a BIM pressure indicator with an airworthy part of the same part number unless the black or red color indication is determined to be the result of BIM system malfunction.

Note 1 to paragraph (f)(2) of this AD: Paragraphs (f)(4)(i–iv) of this AD specify how to determine if a BIM system is functioning correctly.

(3) Repeat the visual BIM pressure indicator check required by paragraph (f)(1) of this AD prior to the first flight of each day and thereafter at intervals not to exceed:

(i) Three hours time-in-service (TIS) from the last check for helicopters engaged in seven or more external lifts per hour; or

(ii) Five hours TIS from the last check for helicopters engaged in either less than seven external lifts per hour or operation without external cargo.

(4) Prior to the first flight of each day, check the BIM pressure indicator for proper function as follows:

(i) Press in and hold the manual test lever (grenade-type handle) on the raised area of the handle over the pin-type actuation plunger. Do not handle the indicator glass bulb since the heat of the hand may change the internal reference pressure and result in an erroneous indicator reading.

(ii) Depress the actuation plunger fully to shut off the pressure completely from the blade into the indicator. If necessary, press with the thumbs of both hands to overcome the plunger spring force.

Note 2 to paragraph (f)(4)(ii) of this AD: If pressure is applied to the end of the lever on the flat area, the actuation plunger will not fully depress.

(iii) Verify proper operation of the indicator by observing that a full-black or full-red (unsafe) indication appears in not less than 10 or more than 30 seconds after depressing the plunger for a temperature of 20 degrees F (

¥ 6.7 degrees C) or above. At lower temperatures, extend the upper limit to the corresponding time as follows:

(A) 19 to 0 degrees F (

¥ 7.2 to

¥ 17.8 degrees C); upper limit of 35 seconds.

(B)

¥ 1 to

¥ 20 degrees F (

¥ 18.3 to

¥ 28.9 degrees C); upper limit of 40 seconds.

(C)

¥ 21 to

¥ 40 degrees F (

¥ 29.4 to

¥ 40.0 degrees C); upper limit of 50 seconds.

(D)

¥ 41 to

¥ 60 degrees F (

¥ 40.5 to

¥ 51.1 degrees C); upper limit of 60 seconds.

(iv) Release the lever and observe that the black or red indication snaps backimmediately, leaving an all-white or allyellow (safe) indication.

(v) If the indicator does not meet the specified requirements, then either identify and correct the BIM indicator malfunction or replace the suspect main rotor blade with an airworthy blade of the same part number prior to further flight.

(5) The checks required by paragraphs (f)(1) and (f)(4)(i–iv) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR §§ 43.9(a)(1)–(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR §§ 91.417, 121.380, or 135.439. (g) Special Flight Permits

Special flight permits will not be issued.
(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170; email 7-AVS-ASW-170@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(i) Additional Information

Erickson Air-Crane Incorporated Service Bulletins No. 64B15–4, Revision 5, dated September 17, 2013 for the Model S–64E and No. 64F15–2, Revision A, dated July 14, 1999 for the Model S–64F, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Erickson Air-Crane Incorporated, ATTN: Chris Erickson, Director of Regulatory Compliance, 3100 Willow Springs Rd, P.O. Box 3247, Central Point, OR 97502; telephone (541) 664–5544; fax (541) 664– 2312; email cerickson@ericksonaircrane.com. You may review a copy of this information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(j) Subject

Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades.

Issued in Fort Worth, Texas, on October 30,
2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013–27635 Filed 11–21–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0523; Directorate Identifier 2012–SW–091–AD; Amendment**  **39–17664; AD 2013–23–09]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with sliding doors, except those with modification AL.4262. This AD requires removing from service certain part-numbered nuts and washers from the lower ball-joint bolt. This AD was prompted by a report of a sliding door detaching from the helicopter in flight. These actions are intended to prevent loss of the lower ball-joint nut, which could lead to loss of the sliding door and damage to the helicopter.

**DATES :**  This AD is effective December 27, 2013.

**ADDRESSES :**  For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052;


### 69990 Federal Register / Vol. 78, No. 226 / Friday, November 22, 2013 / Rules and Regulations

telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. 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 foreign authority’s AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone 817–222–5110; email robert.grant@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On June 20, 2013 at 78 FR 37154, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to add an AD that would apply to Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with sliding doors installed, except those with modification AL.4262. The NPRM proposed to require removing from service each nut, part number (P/N) ASN52320BH060N, and each washer, P/N 23111AG0LE, within 165 hours timein-service (TIS) and replacing them with an airworthy nut and washer. The proposed requirements were intended to prevent loss of the lower ball-joint nut, which could lead to loss of the sliding door and damage to the helicopter.

The NPRM was prompted by AD No. 2012–0205, dated October 1, 2012, issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. EASA issued AD 2012–0205 to correct an unsafe condition for Eurocopter Model AS350B, AS350BA, AS350BB, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with a sliding door installed, except those with modification AL. 4262. EASA advises that during a patrol flight with the doors open, the right-hand (RH) sliding door became detached and was lost in-flight. EASA states it was discovered that the nut of the ball-joint bolt was missing, which allowed the ball-joint bolt to detach from the door and the door to ‘‘fall off’’ the aircraft.According to EASA, a check of the lefthand (LH) sliding door revealed that the nut of the ball-joint bolt was not tightened, and could be unscrewed byhand. EASA advises that the selflocking characteristics of the nut were lost, possibly due to a defective assembly of the ball-joint bolt. This failure of the self-locking characteristics of the nut could lead to loss of the sliding door in-flight, potentially resulting in damage of the surrounding helicopter structure and possible injury to persons on the ground. For these reasons, EASA issued AD 2012–0205 to require modification AL.4262, which specifies replacing each nut, P/N ASN52320BH060N, and washer, P/N 23111AG0LE, with nut, P/N 22542K060, and lock-washer, P/N 23351AC060LE, on the lower ball-joint bolt.

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (78 FR 37154, June 20, 2013).

FAA’s Determination

These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed.

Differences Between This AD and the EASA AD

The EASA AD requires replacing the lower ball-joint nut and washer within 165 flight hours or 13 calendar months, while this AD requires replacing the affected lower ball joint nut and washer within 165 hours TIS. In addition, this AD does not apply to the ModelAS350BB as that helicopter is not typecertificated in the U.S., but it applies to Models AS350C and AS350D1 because those models have a similar lower ball joint nut and washer.

Related Service Information

Eurocopter has issued Alert Service Bulletin (ASB) No. AS350–52.00.34 for Model AS350 B, B1, B2, B3, BA, BB, D, and L1 helicopters and ASB No. AS355– 52.00.26 for Model AS355 E, F, F1, F2, N, and NP helicopters, both Revision 0 and both dated July 9, 2012. The ASBs describe procedures to replace the nuts and lock-washers on the LH and RH sliding door lower ball-joint bolts withdifferent part numbered nuts and lockwashers, to ‘‘double lock’’ the lower ball-joint bolts. Eurocopter designates the maintenance procedure and design change in its ASBs as modification AL.4262. Costs of Compliance

We estimate that this AD will affect 900 helicopters of U.S. Registry.

We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per hour, replacing the nuts and washers on the sliding doors will require about 1 work-hour, and required parts costs will be minimal, for a cost per helicopter of $85 and a total cost to U.S. operators of $76,500. 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 helicopters identified in this rulemaking action. Regulatory Findings

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.


### 69991 Federal Register / Vol. 78, No. 226 / Friday, November 22, 2013 / Rules and Regulations

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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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.

We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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):
2013–23–09 Eurocopter France: Amendment 39–17664; Docket No. FAA–2013–0523; Directorate Identifier 2012–SW–091–AD.
(a) Applicability

This AD applies to Eurocopter France (Eurocopter) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with sliding doors installed, except those with modification AL.4262, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as loss of the self-locking feature of the sliding door lower ball-joint nut. This conditioncould result in detachment of the lower balljoint bolt from the sliding door and subsequent loss of the sliding door from the helicopter in flight.

(c) Effective Date

This AD becomes effective December 27,
2013. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

(1) Within 165 hours time-in-service, remove each nut, part number (P/N) ASN52320BH060N, and each washer, P/N23111AG0LE, from the left-hand and righthand sliding door lower ball-joint bolts and replace them with an airworthy nut and washer.

(2) Do not install a nut, P/N ASN52320BH060N, or washer, P/N23111AG0LE, on any sliding door lower balljoint bolt.
(f) Special Flight Permits

Special flight permits are prohibited.
(g) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone 817–222– 5110; email robert.grant@faa.gov

.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.

(h) Additional Information

(1) Eurocopter Alert Service Bulletin (ASB) No. AS350–52.00.34 for Model AS350B, B1, B2, B3, BA, BB and D and L1 helicopters and ASB No. AS355–52.00.26 for Model AS355E, F, F1, F2, N, and NP helicopters, both Revision 0 and both dated July 9, 2012, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http://www.eurocopter.com/ techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2012–0205, dated October 1, 2012. You may view the EASA AD on the internet in AD Docket No. FAA–2013–0523 at http:// www.regulations.gov.
(i) Subject

Joint Aircraft Service Component (JASC) Code: 5200: Doors.

Issued in Fort Worth, Texas, on November 5, 2013. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013–27636 Filed 11–21–13; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND**  **HUMAN SERVICES**

**Food and Drug Administration**

**21 CFR Part 14**

**[Docket No. FDA–2013–N–1380]**

**Advisory Committee; Veterinary Medicine Advisory Committee;**  **Termination**

**AGENCY :**  Food and Drug Administration, HHS.

**ACTION :**  Final rule.

**SUMMARY :**  The Food and Drug Administration (FDA) is announcing the termination of the Veterinary Medicine Advisory Committee. This document removes the Veterinary Advisory Committee from the Agency’s list of standing advisory committees.

**DATES :**  This rule is effective November 22, 2013.

**FOR FURTHER INFORMATION CONTACT :**  Michael Ortwerth, Advisory Committee Oversight and Management Staff, Food and Drugs Administration, 10903 New Hampshire Ave., Bldg. 32, Rm. 5129, Silver Spring MD 20993–0002, FAX: 301–847–8640, or email at Michael.Ortwerth@fda.hhs.gov.

**SUPPLEMENTARY INFORMATION :**  The Veterinary Medicine Committee was established on April 24, 1984 (49 FR 20809; May 17, 1984). The purpose of the Committee was to review and evaluate available data concerning safety and effectiveness of marketed and investigational new animal drugs, feeds, and devices for use in the treatment and prevention of animal diseases and increased animal production. The Committee is no longer needed and was terminated on September 24, 2013.

Under 5 U.S.C. 553(b)(3)(B) and (d) and 21 CFR 10.40 (d) and (e), the Agency finds good cause to dispense with notice and public comment procedures and to proceed to an immediate effective date on this rule. Notice and public comment and a delayed effective date are unnecessary and are not in the public interest as this final rule merely removes the name of the Veterinary Medicine Advisory Committee from the list of FDA’s standing advisory committees in 21 CFR
14.100.

Therefore, the Agency is amending 21 CFR 14.100(f) as set forth in the regulatory text of this document. List of Subjects in 21 CFR Part 14

Administrative practice and procedure, Advisory committees, Color additives, Drugs, Radiation protection.