Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 42409 

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): 

2013–10–51 Eurocopter France: 

Amendment 39–17487; Docket No. 

FAA–2013–0522; Directorate Identifier 

2013–SW–018–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, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

excessive play that could cause the 

distributor slide valve to jam in its sleeve. 

This condition could result in jamming of the 

hydraulic flight controls, necessitating that 

the pilot cut off hydraulic power. This action 

would increase the pilot’s workload, 

resulting in possible loss of helicopter 

control. 

(c) Effective Date 

This AD becomes effective July 31, 2013 to 

all persons except those persons to whom it 

was made immediately effective by 

Emergency AD No. 2013–10–51, issued on 

May 9, 2013, which contains the 

requirements of this AD. 

(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) Before further flight, inspect the single 

hydraulic main and tail servo-control’s 

(servo-control) component history card or 

equivalent record to determine if it has a part 

number (P/N) and serial number (S/N) listed 

in the Appendix, paragraph 4.A, of 

Eurocopter Emergency Alert Service Bulletin 

No. 67.00.60 (EASB No. 67.00.60) or No. 

67.00.41 (EASB No. 67.00.41), both dated 

April 15, 2013, as appropriate for your model 

helicopter; or was repaired or overhauled 

from September 27, 2012, through January 

30, 2013, by UTC Aerospace Systems or 

Goodrich Corporation in Monroe, North 

Carolina. 

(2) If the servo-control does have a P/N and 

S/N listed in paragraph 4.A of EASB No. 

67.00.60 or EASB No. 67.00.41, as 

appropriate for your model helicopter, or if 

the servo-control was repaired or installed 

from September 27, 2012, through January 

30, 2013, by UTC Aerospace Systems or 

Goodrich Corporation in Monroe, North 

Carolina, inspect the servo-control to 

determine whether the identification plate is 

marked with a ‘‘B’’ as shown in the 

Appendix, paragraph 4.B, of EASB No. 

67.00.60 or EASB No. 67.00.41, as 

appropriate for your model helicopter. If it is 

marked with a ‘‘B,’’ no further action is 

required. 

(3) If the identification plate is not marked 

with a ‘‘B,’’ inspect all sides of the external 

race of the servo-control’s bearing to 

determine if it has any marking shown as (b) 

in Detail A of Figure 1 of EASB No. 67.00.60 

or EASB No. 67.00.41, as appropriate for your 

model helicopter. If there is any marking, 

before further flight, replace the servo-control 

with an airworthy servo-control. 

(4) If there is no marking on the sides of 

the external race, inspect each bearing 

sealing flange to determine if it is marked 

with ‘‘RWG Germany 60–5593’’ as shown as 

(d) in Detail C of Figure 2 of EASB No. 

67.00.60 or EASB No. 67.00.41, as 

appropriate for your model helicopter. If 

there is ‘‘RWG Germany 60–5593’’ marking at 

least partially visible on a flange of the 

bearing, no further action is required. 

(5) If there is no ‘‘RWG Germany 60–5593’’ 

marking at least partially visible on a flange 

of the bearing, before further flight, replace 

the servo-control with an airworthy servocontrol. 

(f) Special Flight Permits 

Special flight permits may be permitted 

only for taking a helicopter to a repair station 

to meet the requirements of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Hemann, 

Transportation Safety Analyst, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email michael.hemann@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 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) AD 

No. 2013–0095–E, dated April 16, 2013. You 

may view the EASA AD at http:// 

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0522. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6730, Rotorcraft Servo System. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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 EASB No. 67.00.60, dated 

April 15, 2013. 

(ii) Eurocopter EASB No. 67.00.41, dated 

April 15, 2013. 

Note 1 to paragraph (j)(2): Eurocopter 

EASB No. 67.00.60, dated April 15, 2013, and 

Eurocopter EASB No. 67.00.41, dated April 

15, 2013, are co-published as one document 

along with Eurocopter EASB No. 67.00.36, 

dated April 15, 2013, and Eurocopter EASB 

No. 67.00.27, dated April 15, 2013, which are 

not incorporated by reference in this AD. 

(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 June 13, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–16682 Filed 7–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0018; Directorate 

Identifier 2010–SW–060–AD; Amendment 

39–17483; AD 2013–12–05] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

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42410 Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH 

(Eurocopter) Model MBB–BK 117 C–2 

helicopters. This AD requires 

determining if a certain serial-numbered 

bevel gear is installed in the tailrotor 

intermediate gear box (IGB). If such a 

bevel gear is installed in the IGB, this 

AD requires recording the bevel gear’s 

reduced life limit in the Airworthiness 

Limitations section of the maintenance 

manual and on the component history 

card or equivalent IGB record. If the 

bevel gear’s life limit has been reached 

or exceeded, this AD requires, before 

further flight, replacing the bevel gear 

with an airworthy bevel gear. This AD 

is prompted by the discovery that the 

tooth foot fillets in certain bevel gears 

fall below the minimum dimensions 

required in the design documents to 

ensure safe functioning of the bevel gear 

until it reaches its approved life limit. 

This AD’s actions are intended to 

prevent failure of a bevel gear before it 

reaches its currently approved life limit, 

failure of the IGB, and subsequent loss 

of helicopter control. 

DATES: This AD is effective August 20, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of August 20, 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 European 

Aviation Safety Agency (EASA) AD, any 

incorporated-by-reference 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: 

Chinh Vuong, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email 

chinh.vuong@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, issued EASA AD No. 2010–0096 

on May 25, 2010, to correct an unsafe 

condition for Eurocopter Model MBB– 

BK 117 C–2 helicopters. EASA advised 

that during a recent review of the 

production documents for the bevel 

gears of the IGB, it was discovered that 

certain production batch numbers have 

tooth foot fillets below the required 

minimum values that would ensure the 

approved life limits for this part. 

On January 18, 2013, at 78 FR 4090, 

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 MBB–BK 117 C–2 

helicopters. The NPRM proposed to 

require determining if a certain serialnumbered bevel gear was installed in 

the IGB. If such a bevel gear was 

installed in the IGB, the NPRM 

proposed to require recording the bevel 

gear’s reduced life limit in the 

Airworthiness Limitations section of the 

maintenance manual and on the 

component history card or equivalent 

IGB record. If the bevel gear’s life limit 

was reached or exceeded, the NPRM 

proposed to require, before further 

flight, replacing the bevel gear with an 

airworthy bevel gear. The proposed 

requirements were intended to prevent 

failure of a bevel gear before it reached 

its currently approved life limit, failure 

of the IGB, and subsequent loss of 

helicopter control. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(78 FR 4090, January 18, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, 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 

This AD does not require sending a 

copy of the form in Eurocopter’s Alert 

Service Bulletin No. MBB BK117 C–2– 

04A–005, Revision 2, dated April 28, 

2010 (ASB), to the manufacturer. This 

AD does not require sending the IGB to 

an overhaul facility. Also, this AD does 

not specify a single ferry flight not to 

exceed 20 hours time-in-service to a 

maintenance facility if the bevel gear 

has exceeded the reduced life limit. 

Related Service Information 

Eurocopter’s ASB specifies 

determining whether certain serialnumbered bevel gears are installed in 

the IGB. The ASB specifies recording 

the reduced life limit for each affected 

bevel gear on the log card of the IGB and 

on the list of life-limited parts. If a bevel 

gear has one of the serial numbers listed 

in Table 1 of the ASB, the ASB specifies 

filling out a reply form and copying and 

sending it to Eurocopter. The ASB also 

specifies sending the IGB to a certified 

overhaul facility for replacing the bevel 

gear if it has reached or exceeded its life 

limit. EASA classified this ASB as 

mandatory and issued AD No. 2010– 

0096, dated May 25, 2010, to ensure the 

continued airworthiness of these 

helicopters. 

Costs of Compliance 

We estimate that this AD affects 107 

helicopters of U.S. registry and that the 

labor rate averages $85 per work-hour. 

We also estimate that it takes about a 

half hour to determine whether the IGB 

is affected and to enter the reduced life 

limit on the component history card or 

the equivalent record and to revise the 

Airworthiness Limitations section of the 

maintenance manual. Based on these 

figures, we estimate that the cost per 

helicopter totals about $43, about $4,601 

for the U.S. fleet. 

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 

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Federal Register / Vol. 78, No. 136 / Tuesday, July 16, 2013 / Rules and Regulations 42411 

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): 

2013–12–05 Eurocopter Deutschland GmbH 

Helicopters: Amendment 39–17483; 

Docket No. FAA–2013–0018; Directorate 

Identifier 2010–SW–060–AD. 

(a) Applicability 

This AD applies to Model MBB–BK 117 C– 

2 helicopters with a bevel gear, part number 

(P/N) 4639 310 065, installed in the tail rotor 

intermediate gear box (IGB), P/N 4639 002 

007, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a bevel gear, failure of the tail rotor 

IGB, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective August 20, 

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 30 days, do the following: 

(1) Determine if a bevel gear with a serial 

number (S/N) listed in Table 1 of Eurocopter 

Alert Service Bulletin MBB BK117 C–2–04A– 

005, Revision 2, dated April 28, 2010 (ASB), 

is installed in the IGB. 

(i) If a bevel gear listed in Table 1 of the 

ASB is installed in the IGB, record the 

reduced life limit of the bevel gear onto the 

component history card or equivalent record 

of the IGB. 

(ii) If the bevel gear life limit has been 

reached or is exceeded, before further flight, 

replace the bevel gear with an airworthy 

bevel gear. 

(2) Revise the Airworthiness Limitations 

section of the maintenance manual by 

reducing the retirement life for each IGB 

bevel gear, P/N 4639 310 065, that has a S/ 

N listed in Table 1 of the ASB to the life limit 

corresponding to that S/N. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Chinh Vuong, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

chinh.vuong@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 (EASA) AD 

No. 2010–0096, dated May 25, 2010. You 

may view the EASA AD at http:// 

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0018. 

(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 MBB 

BK117 C–2–04A–005, Revision 2, dated April 

28, 2010. 

(ii) Reserved. 

(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 June 13, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–14848 Filed 7–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0864; Directorate 

Identifier 2011–NM–023–AD; Amendment 

39–17496; AD 2013–13–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 767 

airplanes. That AD currently requires 

sealing certain fasteners and stiffeners 

in the fuel tank, changing certain wire 

bundle clamp configurations on the fuel 

tank walls, inspecting certain fasteners 

in the fuel tanks and determining the 

method of attachment of the vortex 

generators; and performing corrective 

actions if necessary. This new AD adds 

a general visual inspection for the 

presence of a polytetrafluoroethylene 

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