Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57047 

TABLE XII—INTERIOR CONTAINER DEFECTS

Defects 

Categories 

Major Minor 

De-tinning in metal container materially affecting usability ..................................................................................... 101 ........................

De-tinning in metal container not materially affecting usability ............................................................................... ........................ 201 

Black spots in metal container ................................................................................................................................ ........................ 202 

Enamel missing (when required) in metal container ............................................................................................... 102 ........................

Enamel breakdown in metal container material affecting usability ......................................................................... 103 ........................

Enamel breakdown in metal container material not affecting usability ................................................................... ........................ 203 

Other defect(s) of the interior of the container (metal, plastic, paper, rigid, etc.) e.g., interior damage, tear, 

delamination, missing layer, off-odor, interior blisters, etc. that materially affects usability ............................... 104 ........................

Defect(s) of the interior of the container (metal, plastic, paper, rigid, etc.) e.g., interior damage, tear, 

delamination, missing layer, off-odor, interior blisters, etc. that materially affects appearance but not usability ........................ 204 

TABLE XIII—ACCEPTANCE NUMBERS FOR INTERNAL CONTAINER DEFECTS

Sample Size (n = number of containers) 

Major Total 

Interior Defects Interior Defects 

Ac Re Ac Re 

n—13 ............................................................................................................... 0 1 2 3 

n—21 ............................................................................................................... 1 2 3 4 

n—29 ............................................................................................................... 1 2 4 5 

n—38 ............................................................................................................... 2 3 5 6 

n—48 ............................................................................................................... 2 3 6 7 

n—60 ............................................................................................................... 2 3 7 8 

Dated: September 11, 2013. 

Rex A. Barnes, 

Associate Administrator, Agricultural 

Marketing Service. 

[FR Doc. 2013–22574 Filed 9–16–13; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0119; Directorate 

Identifier 2011–SW–034–AD; Amendment 

39–17541; AD 2013–16–03] 

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 

AS350 and AS355 helicopters, to 

require inspecting for a crack in the 

control lever attachment yokes, and if 

needed, replacing the tail rotor gearbox 

(TGB). This AD is prompted by 

improper casting of TGB casing 

assemblies, which may lead to cracking. 

A crack in the control lever attachment 

yokes could cause a loss of tail rotor 

pitch control, and consequently, loss of 

control of the helicopter. 

DATES: This AD is effective October 22, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of October 22, 2013. 

ADDRESSES: 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. 

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, any incorporated-byreference service information, 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 February 11, 2013, at 78 FR 9634, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 to include an AD that would apply 

to Eurocopter Model AS350 and AS355 

helicopters. The NPRM proposed to 

require inspecting for a crack in the 

control lever attachment yokes, and if 

needed, replacing the TGB. The 

proposed requirements were intended to 

prevent a crack in the control lever 

attachment yokes, which could cause a 

loss of tail rotor pitch control, and 

consequently, loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

2011–0104, dated May 27, 2011, issued 

by the European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for the Eurocopter Model AS 350 and 

AS 355 helicopters. EASA advises that 

cracks were found on some TGB casing 

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57048 Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 

assemblies when a dye-penetrant 

inspection was performed after the 

machining of the control lever 

attachment yokes. The inspection 

followed the repair of the manufacturing 

mold. EASA reports that cracks in the 

TGB casing assemblies, if not detected 

and corrected, could lead to a crack on 

the control lever attachment yokes, 

which could cause the loss of tail rotor 

pitch control and subsequent loss of 

control of the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(78 FR 9634, February 11, 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 except the reference to the 

Aerospace Material Specification 2647 

or equivalent has been removed and we 

are now incorporating by reference 

procedures for the Fluorescent 

Penetrant Inspection. These changes are 

consistent with the intent of the 

proposals in the NPRM (78 FR 9634, 

February 11, 2013) and will not increase 

the economic burden on any operator 

nor increase the scope of the AD. 

Differences Between This AD and the 

EASA AD 

We require inspecting for a crack in 

the attachment yokes of the TGB casing 

assemblies within 100 hours time-inservice (TIS). EASA requires that the 

inspection be conducted within 26 

months or 660 flight hours if the TGB 

casing assemblies have less than 550 

flight hours and within 110 flight hours 

or 13 months if the TGB casing 

assemblies have 550 or more flight 

hours. We do not include the Model 

AS350BB helicopter because it is not 

type certificated in the United States, 

but we do include models AS350C and 

AS350D1. 

Related Service Information 

Eurocopter issued Alert Service 

Bulletin (ASB) No. AS350–65.00.46 for 

Model AS350 helicopters and ASB 

AS355–65.00.22 for AS355 helicopters. 

Both ASBs are Revision 0 and dated 

May 18, 2011. The ASBs call for nondestructive inspections, such as a dyepenetrant inspection, to check for cracks 

in the attachment yokes of the TGB 

casing assemblies. If there is a crack, the 

ASBs call for replacing the TGB with an 

airworthy TGB and returning the 

replaced TGB to Eurocopter. 

Costs of Compliance 

We estimate that this AD affects 693 

helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 

We estimate that it takes two workhours to inspect TGB casing assemblies 

for a cost of $170 per helicopter, and 

$117,810 for the U.S. fleet. No parts are 

needed. Replacing the TGB requires five 

work hours for a labor cost of $425. 

Parts cost $37,825 for a total cost of 

$38,250 per helicopter. 

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. 

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): 

2013–16–03 EUROCOPTER FRANCE 

HELICOPTERS (EUROCOPTER): 

Amendment 39–17541; Docket No. 

FAA–2013–0119; Directorate Identifier 

2011–SW–034–AD. 

(a) Applicability 

This AD applies to Eurocopter AS350C, D, 

D1, B, BA, B1, B2, and B3; and AS355E, F, 

F1, F2, N, and NP helicopters, with a tailrotor 

gearbox (TGB) casing assembly, part number 

(P/N) 350A33–1090–02 and serial number (S/ 

N) MA47577, MA47585, MA47587 through 

MA47593, MA47597 through MA47600, 

MA47602, MA47604, MA47606, MA47610, 

MA47613, MA47615, MA47617, MA47619 

through MA47624, MA47626, MA47628, or 

MA47631 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the control lever attachment yoke of 

the TGB casing assembly, which could result 

in loss of tail rotor pitch control and loss of 

helicopter control. 

(c) Effective Date 

This AD becomes effective October 22, 

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 

Within 100 hours time-in-service: 

(1) Remove the control lever, as depicted 

in Figure 1, item (b), of Eurocopter Alert 

Service Bulletin (ASB) No. AS350–65.00.46 

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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57049 

or No. AS355–65.00.22, both Revision 0 and 

both dated May 18, 2011, as applicable for 

your model helicopter. 

(2) Strip the paint from the TGB control 

lever attachment yokes, as depicted in Figure 

2, item (z), of the ASB No. AS350–65.00.46 

or No. AS355–65.00.22, as applicable to your 

model helicopter. 

(3) Perform a Fluorescent Penetrant 

Inspection (FPI) in accordance with 

paragraph 3.B.2 of ASB No. AS350–65.00.46 

or No. AS355–65.00.22, as applicable to your 

model helicopter, on the TGB control lever 

attachment yokes for a crack. You are only 

required to follow the actions defined in this 

ASB paragraph pertaining to the FPI. 

(4) If a crack exists, before further flight, 

replace the TGB with an airworthy TGB. 

(5) If there is no crack, clean the inspected 

area and apply chemical conversion coating 

(Alodine 1200 or equivalent), Epoxy primer, 

and top coat paint. 

(f) 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– 

5328; 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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0104, dated May 27, 2011. You may 

view the EASA AD at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0119. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail Rotor Gearbox. 

(i) 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 the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin No. 

AS350–65.00.46, Revision 0, dated May 18, 

2011. 

(ii) Eurocopter Alert Service Bulletin No. 

AS355–65.00.22, Revision 0, May 18, 2011. 

(3) For Eurocopter 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. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on July 26, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–22295 Filed 9–16–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0301; Directorate 

Identifier 2013–NM–025–AD; Amendment 

39–17575; AD 2013–18–02] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200, 

–300, –300F, and –400ER series 

airplanes. This AD was prompted by 

reports of cracked and corroded nuts on 

an outboard flap support rib. This AD 

requires, for certain airplanes, repetitive 

inspections of the cap seal for damaged 

sealant on nuts common to certain 

outboard flap support ribs, and related 

investigative and corrective actions if 

necessary. For certain other airplanes, 

this AD also requires repetitive 

inspections of the cap seal for damaged 

sealant on nuts common to certain 

outboard flap support ribs, related 

investigative and corrective actions if 

necessary, and if necessary, a detailed 

inspection to determine the nut type 

installed in the outboard flap support 

rib and corrective actions. This AD also 

provides terminating action for the 

repetitive inspections under certain 

conditions. We are issuing this AD to 

detect and correct cracked and corroded 

nuts and bolts and the installation of 

incorrect nuts on certain outboard flap 

support ribs, which could lead to 

additional nut and bolt damage in the 

joint, result in loss of an outboard flap, 

and adversely affect continued safe 

flight and landing of the airplane. 

DATES: This AD is effective October 22, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 22, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. 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 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on April 10, 2013 (78 FR 

21276). The NPRM proposed to require, 

for certain airplanes, repetitive 

inspections of the cap seal for damaged 

sealant on nuts common to certain 

outboard flap support ribs, related 

investigative and corrective actions if 

necessary, and replacement of all 

fasteners in the support ribs, which 

terminates the repetitive inspections. 

For certain other airplanes, the NPRM 

proposed to require repetitive 

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