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

§ 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 back 

immediately, 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; 


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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 by 

hand. 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 Model 

AS350BB 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 with 

different 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. 


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

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 condition 

could 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/N 

23111AG0LE, 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/N 

23111AG0LE, 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. 


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