Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 21233 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on March 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08068 Filed 4–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0630; Directorate 

Identifier 2011–SW–010–AD; Amendment 

39–17409; AD 2013–07–05] 

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 EC130B4 helicopters. 

This AD requires visually checking the 

center windscreen panel (center 

windscreen) for a crack and replacing 

the center windscreen if there is a crack, 

if the windscreen distorts during flight, 

or within 12 months. This AD was 

prompted by in-flight cracking and 

failure of a center windscreen. The 

actions of this AD are intended to detect 

a crack in the blending radii of the 

center windscreen to prevent failure of 

the windscreen, injury to the flight 

crew, and subsequent loss of control of 

the helicopter. 

DATES: This AD is effective May 15, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of May 15, 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, 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: Jim 

Grigg, Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 

76137; telephone (817) 222–5110; email 

jim.grigg@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 18, 2012, at 77 FR 36213, 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 France EC130B4 helicopters 

with a center windscreen, part number 

(P/N) 350A25–9004–00, 350A25–9025– 

00, or 350A25–9041–20. That NPRM 

proposed to require, before each flight, 

visually checking the center windscreen 

and replacing the center windscreen 

panel before further flight if there is a 

crack in the center windscreen panel or 

if the windscreen distorts during flight. 

The NPRM also proposed to require, 

within 12 months, replacing the center 

windscreen with a certain partnumbered windscreen, which would 

terminate the repetitive inspection 

requirements. The NPRM specified that 

an owner/operator (pilot) may perform 

the visual check and must enter 

compliance with the applicable 

paragraph into the helicopter 

maintenance records in accordance with 

14 CFR 43.9(a)(1)–(4) and 

91.417(a)(2)(v). A pilot may perform this 

check because it involves only a visual 

check for a crack in the center 

windscreen and can be performed 

equally well by a pilot or a mechanic. 

This authorization is an exception to 

our standard maintenance regulations. 

The proposed requirements were 

intended to detect a crack in the 

blending radii of the center windscreen 

to prevent failure of the windscreen, 

injury to the flight crew, and subsequent 

loss of control of the helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, issued EASA AD No. 2010–0258, 

dated December 6, 2010 (AD 2010– 

0258), to correct an unsafe condition for 

the Eurocopter France EC130B4 

helicopters. EASA received reports that 

center windscreen panels failed during 

flights due to a crack that started in the 

blending radius between the lower and 

upper sections of the windscreen. EASA 

stated that this condition, if not detected 

and corrected, could result in serious 

injury of the helicopter occupants, and 

therefore, issued Emergency AD 2007– 

0219–E, dated August 24, 2007, (AD 

2007–0219–E), requiring a pre-flight 

inspection of the center windscreen, 

repair or replacement of a cracked 

windscreen, and an airspeed limitation. 

In AD 2010–0258, EASA notes that it 

approved a modification (MOD 073590) 

for the EC130B4 helicopters that 

incorporates a newly designed center 

windscreen panel, part number (P/N) 

350A25–9045–20, to ‘‘eliminate the 

possibility of centre windshield cracks 

thus providing an alternative 

terminating action for the preflight 

inspections.’’ 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(77 FR 36213, June 18, 2012). 

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 imposes flight 

restrictions and replacing the 

windscreen within 50 flight hours or 15 

days, whichever occurs first, if 

distortion of the windscreen is detected 

in-flight. This AD mandates replacing 

the windscreen before further flight if 

distortion occurs during flight. In 

addition, this AD mandates MOD 

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21234 Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 

073590 and replacing the affected 

windscreen with an airworthy 

windscreen, P/N 350A25–9045–20, 

within 12 months. 

Related Service Information 

We reviewed Eurocopter Emergency 

Alert Service Bulletin (ASB) No. 

05A005 Revision 2, dated November 22, 

2010. The ASB specifies: 

• Performing a visual check of the 

center windscreen before each flight. 

• Replacing any center windscreen 

before resuming flight if a crack is 

detected. 

• If in-flight distortion is found, 

immediately restricting airspeed to 70 

knots or below, and 

Æ If a crack is found, before next 

flight, replacing the windscreen per 

Eurocopter Service Bulletin 56–003, 

dated November 16, 2010, (SB 56–003), 

which describes procedures to perform 

MOD 073590, and 

Æ If no crack is found, affixing an 

airspeed limitation label and within 50 

flying hours or 15 days, whichever is 

earlier, replacing the windscreen per 

MOD 073590. 

• That incorporation of MOD 073590 

is an alternative to the bulletin, 

relieving users of the inspection 

requirements. 

EASA has classified this ASB as 

mandatory and issued AD 2010–0258 to 

ensure the continued airworthiness of 

these helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

87 helicopters of U.S. registry and that 

labor costs will average $85 per workhour. Therefore, we estimate the 

following costs to comply with this AD: 

• The check of the center windscreen 

before each flight will take about 15 

minutes for a labor cost of $21.25 per 

inspection. No parts will be needed, so 

the total cost for the U.S. 87-helicopter 

fleet is about $1,849 per inspection. 

• Replacing the center windscreen 

will require about 20 work-hours for a 

labor cost of $1,700 per helicopter. Parts 

will cost $6,037 for a total cost per 

helicopter of $7,737. 

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): 

2013–07–05 Eurocopter France: 

Amendment 39–17409; Docket No. 

FAA–2012–0630; Directorate Identifier 

2011–SW–010–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

EC130B4 helicopters with center windscreen 

panel (center windscreen), part number (P/N) 

350A25–9004–00, 350A25–9025–00, or 

350A25–9041–20, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the blending radii of the center 

windscreen, which could lead to failure of 

the center windscreen, injury to the flight 

crew, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective May 15, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

(1) Until the center windscreen is replaced 

with center windscreen P/N 350A25–9045– 

20, before each flight, visually check the 

center windscreen for a crack in the area of 

the blending radii where the front-lower part 

of the center windscreen joins the front 

fuselage as depicted in Figure 1 to paragraph 

(e)(1) of this AD. This visual check 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 Title 14 Code of Federal 

Regulations (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. 

BILLING CODE 4910–13–P 

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Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 21235 

BILLING CODE 4910–13–C 

(2) If there is a crack or if a pilot indicates 

that the center windscreen distorted during 

flight, before further flight, replace the center 

windscreen with an airworthy center 

windscreen, P/N 350A25–9045–20, in 

accordance with the Accomplishment 

Instructions, paragraphs 2.B.2.b. through 

2.B.2.b.4., of Eurocopter Service Bulletin No. 

56–003, Revision 0, dated November 16, 

2010. 

(3) Within 12 months, replace the center 

windscreen with an airworthy center 

windscreen, P/N 350A25–9045–20, in 

accordance with the instructions contained 

in paragraph (e)(2) of this AD. 

(4) Replacing the center windscreen with 

center windscreen, P/N 350A25–9045–20, 

constitutes terminating action for the 

requirements of this AD. 

(f) Special Flight Permits 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the requirements of this AD can be 

accomplished, provided that: 

(1) No passengers are onboard; 

(2) The time to fly to the location does not 

exceed 10 hours time-in-service; and 

(3) The airspeed does not exceed 70 knots 

indicated air speed (KIAS). 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Jim Grigg, 

Manager, Safety Management Group, 

Rotorcraft Directorate, FAA, 2601 Meacham 

Blvd., Fort Worth, TX 76137; telephone (817) 

222–5110; email jim.grigg@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 

European Aviation Safety Agency AD No. 

2010–0258, dated December 6, 2010. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5600, Window/Windshield System. 

(j) 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 Service Bulletin No. 56–003, 

Revision 0, dated November 16, 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. 


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21236 Federal Register / Vol. 78, No. 69 / Wednesday, April 10, 2013 / Rules and Regulations 

Issued in Fort Worth, Texas, on January 22, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–07932 Filed 4–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0809; Directorate 

Identifier 2011–NM–135–AD; Amendment 

39–17361; AD 2013–04–04] 

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 757 

airplanes equipped with Rolls-Royce 

RB211–535E engines. That AD currently 

requires repetitive inspections for signs 

of damage of the aft hinge fittings and 

attachment bolts of the thrust reversers, 

and related investigative and corrective 

actions if necessary. The existing AD 

also provides for an optional 

terminating modification for the 

repetitive inspections. For certain 

airplanes, this new AD adds a one-time 

inspection of the washers installed 

under the attachment bolts of the aft 

hinge fittings for correct installation 

sequence, and reinstallation if 

necessary. This new AD also adds an 

option for installing a redesigned aft 

hinge fitting with the trim already done, 

instead of trimming an existing or new 

hinge fitting, which is included in the 

existing optional terminating 

modification. This AD was prompted by 

reports of incorrectly installed washers 

under the attachment bolts of the aft 

hinge fittings of the thrust reversers. We 

are issuing this AD to prevent failure of 

the attachment bolts and consequent 

separation of a thrust reverser from the 

airplane during flight, which could 

result in structural damage to the 

airplane. 

DATES: This AD is effective May 15, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 15, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 6, 2008 (73 FR 

37786, July 2, 2008). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, Washington 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6440; fax: 425–917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–13–20, 

Amendment 39–15583 (73 FR 37786, 

July 2, 2008). That AD applies to the 

specified products. The NPRM 

published in the Federal Register 

August 16, 2012 (77 FR 49396). That 

NPRM proposed to continue to require 

repetitive inspections for signs of 

damage of the aft hinge fittings and 

attachment bolts of the thrust reversers, 

and related investigative and corrective 

actions if necessary. That NPRM also 

proposed to continue to provide for an 

optional terminating modification for 

the repetitive inspections. For certain 

airplanes, that NPRM proposed to add a 

one-time inspection of the washers 

installed under the attachment bolts of 

the aft hinge fittings for correct 

installation sequence, and reinstallation 

if necessary. That NPRM also proposed 

to add an option for installing a 

redesigned aft hinge fitting with the trim 

already done, instead of trimming an 

existing or new hinge fitting, which is 

included in the existing optional 

terminating modification. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 49396, 

August 16, 2012) and the FAA’s 

response to each comment. 

Support for the NPRM (77 FR 49396, 

August 16, 2012) 

Boeing concurred with the content of 

the NPRM (77 FR 49396, August 16, 

2012). 

FedEx Express stated that it is 

accomplishing the actions specified in 

the NPRM (77 FR 49396, August 16, 

2012), and determined that its regular 

maintenance check schedule is not 

adversely affected by the specified 

actions. 

Request To Address Effects of NPRM 

(77 FR 49396, August 16, 2012) on 

Winglets 

Aviation Partners Boeing (APB) stated 

that it has reviewed the NPRM (77 FR 

49396, August 16, 2012), and Boeing 

Special Attention Service Bulletin 757– 

54–0049, Revision 1, dated September 

23, 2009, and Revision 2, dated July 27, 

2011; and Boeing Special Attention 

Service Bulletin 757–54–0050, Revision 

1, dated October 7, 2009, and Revision 

2, dated July 27, 2011; and has 

determined that the installation of 

winglets, per Supplemental Type 

Certificate (STC) ST01518SE, ‘‘does not 

affect them.’’ 

We infer that APB means the 

installation of these winglets does not 

affect accomplishing the NPRM (77 FR 

49396, August 16, 2012). We agree with 

the commenter and have determined 

that this AD should clarify the 

procedures to address these APB 

winglets. We have added a new 

paragraph (c)(2) to this AD to state that 

the installation of STC ST01518SE 

(http://rgl.faa.gov/Regulatory_and

_Guidance_Library/rgstc.nsf/0/48E13

CDFBBC32CF4862576A4005

D308B?OpenDocument&High

light=st01518se) does not affect the 

ability to accomplish the actions 

required by this AD. For airplanes on 

which STC ST01518SE is installed, a 

‘‘change in product’’ alternative method 

of compliance (AMOC) approval request 

is not necessary to comply with the 

requirements of section 39.17 of the 

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