Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 70205 

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 November 

5, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27637 Filed 11–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0487; Directorate 

Identifier 2010–SW–056–AD; Amendment 

39–17666; AD 2013–23–11] 

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 

AS332L2 and EC225LP helicopters. This 

AD requires inspecting the torque value 

of the bolts that secure the front and rear 

main gearbox (MGB) suspension bar 

attaching fittings, and re-torqueing the 

bolts to the proper value if the torque 

value is out of tolerance. This AD also 

requires, if the torque value is out of 

tolerance by more than 20 percent, 

inspecting the bolts, frames, and related 

equipment for a crack and repairing or 

replacing them if cracked. This AD was 

prompted by reports of cracks on Frame 

5295 of Model AS332L2 helicopters. 

The actions of this AD are intended to 

detect the torque loss of the bolts that 

secure the MGB bar attaching fittings 

and to prevent cracks that could lead to 

failure of the MGB supporting structure, 

detachment of the MGB, and loss of 

helicopter control. 

DATES: This AD is effective December 

30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 30, 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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 7, 2013, at 78 FR 34288, 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 AS332L2 and 

EC225LP helicopters. The NPRM 

proposed to require inspecting the 

torque value of the bolts that secure the 

front and rear MGB suspension bar 

attaching fittings, and re-torqueing the 

bolts to the proper value if the torque 

value is out of tolerance. The NPRM 

also proposed to require that if the 

torque value is out of tolerance by more 

than 20 percent, inspecting the bolts, 

frames, and related equipment for a 

crack and repairing or replacing them if 

cracked. The proposed requirements 

were intended to detect the torque loss 

of the bolts that secure the MGB bar 

attaching fittings and to prevent cracks 

that could lead to failure of the MGB 

supporting structure, detachment of the 

MGB, and loss of helicopter control. 

The NPRM was prompted by AD No. 

2006–0163 R1, dated December 13, 2007 

(AD No. 2006–0163R1), issued by the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, to correct an unsafe 

condition in Model AS 332 L2 and 

Model EC 225 LP helicopters. According 

to EASA, analysis of tightening torques 

revealed some cases of tightening torque 

loss, which can lead to the formation of 

a crack at the MGB bar attaching fittings. 

As a result, EASA AD No. 2006–0163R1 

requires checking the bolts securing the 

front and rear of the MGB bar attaching 

fittings for tightening torque loss and, if 

the loss is equal to or greater than 20 

percent, readjusting the torque and 

checking the four bolts securing the 

MGB bar attaching fitting mounting 

plate, as well as the frame 3855, for a 

crack. If there is a crack in at least one 

of the bolts, AD No. 2006–0163R1 

requires replacing all four bolts. If there 

is a crack in frame 3855, AD No. 2006– 

0163R1 requires suspending all flights 

and contacting the manufacturer for 

corrective action. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(78 FR 34288, June 7, 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 

This AD differs from the EASA AD in 

that we use the word ‘‘inspect’’ to 

describe actions required by a mechanic 

versus the word ‘‘check,’’ which is how 

we describe actions allowed by a pilot. 

We also require that if you find a crack 

in a frame or fitting, you repair or 

replace the cracked part instead of 

contacting the manufacturer. Also, we 

have different compliance times for the 

initial inspection for the tightening 


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70206 Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 

torque of the bolts that secure the MGB 

attaching fitting. 

Related Service Information 

We reviewed Eurocopter Alert Service 

Bulletin (ASB) No. 05.00.65, Revision 0, 

dated March 28, 2006, for Model 

AS332L2 helicopters, and ASB No. 

05A002, Revision 1, dated December 6, 

2007, for Model EC225LP helicopters. 

The ASBs specify inspecting the 

tightening torque of the bolts that secure 

the front and rear of the MGB bar 

attaching fittings. If more than a 20 

percent tightening torque load loss is 

discovered, the ASBs require inspecting 

the frames 3855 and 5295 for a crack in 

the area of the MGB bar attaching 

fittings. EASA classified these ASBs as 

mandatory and issued EASA AD No. 

2006–0163 R1 to ensure the continued 

airworthiness of these helicopters. 

Costs of Compliance 

We estimate that this AD affects 4 

helicopters of U.S. Registry and that 

labor costs average $85 a work-hour. 

Based on these estimates, we expect the 

following costs: 

• Inspecting the torque of each bolt 

that secures the front and rear MGB 

attaching fitting requires 1 work-hour 

and no parts for a total cost of $85 per 

helicopter, and $340 for the U.S. fleet. 

• Readjusting the torque adds another 

0.25 work-hour for a total cost of about 

$21 per helicopter. 

• Replacing all four nuts and bolts of 

an attachment fitting requires 4 workhours. Parts cost $1,000 for a total cost 

of $1,340 per helicopter. 

• Replacing the attachment fitting or 

plate requires 16 work-hours 

respectively. Parts cost $2,000 

respectively for a total cost of $3,360 to 

replace each part per helicopter. 

• Replacing frames 3855 and 5295 

require 40 work-hours respectively. 

Parts cost $5,000 to replace each frame 

for a total cost of $8,400 per frame 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): 

2013–23–11 Eurocopter France: 

Amendment 39–17666; Docket No. 

FAA–2013–0487; Directorate Identifier 

2010–SW–056–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model AS332L2 and EC225LP 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loss of tightening torque of a bolt that secures 

the front and rear main gearbox (MGB) 

suspension bar attaching fittings, which can 

change the loads on the frames and cause 

cracking. This condition could lead to failure 

of the MGB supporting structure, detachment 

of the MGB, and subsequent loss of control 

of the helicopter. 

(c) Effective Date 

This AD becomes effective December 30, 

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 500 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 825 

hours TIS, inspect the tightening torque of 

each bolt that secures the front and rear MGB 

attaching fitting by using as reference Figure 

1 of Eurocopter Alert Service Bulletin (ASB) 

No. 05.00.65, Revision 0, dated March 28, 

2006, for the Model AS332L2 helicopters; 

and ASB No. 05A002, Revision 1, dated 

December 6, 2007, for the Model EC225LP 

helicopters. 

(2) If the loss of tightening torque of a nut 

is less than or equal to 20 percent of the 

minimum tightening torque, before further 

flight, readjust the tightening torque. 

(3) If the loss of tightening torque of any 

nut (front or rear) is greater than 20 percent 

of the minimum tightening torque, before 

further flight: 

(i) Inspect each bolt and nut that secures 

the attachment fitting for a crack, and 

(ii) Inspect for a crack in the attachment 

area of the attachment fitting, the attachment 

plate, and Frame 3855 for the front fitting 

and Frame 5295 for the rear fitting. 

(A) If no crack exists, readjust the 

tightening torque. 

(B) If there is a crack in any nut or bolt, 

before further flight, replace all four nuts and 

bolts of the affected attachment fitting. 

(C) If there is a crack in the attachment area 

of the attachment fitting or the attachment 

plate, before further flight, replace the 

cracked attachment fitting or plate with an 

airworthy fitting or plate. 

(D) If there is a crack in Frame 3855 for the 

front fitting or Frame 5295 for the rear fitting, 

before further flight, repair or replace the 

frame. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 70207 

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 the 

European Aviation Safety Agency (EASA) AD 

No. 2006–0163 R1, dated December 13, 2007. 

You may view the EASA AD at http://

www.regulations.gov in Docket No. FAA– 

2013–0487. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6330, Main Rotor Transmission Mount. 

(i) 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 Alert Service Bulletin No. 

05.00.65, Revision 0, dated March 28, 2006. 

(ii) Eurocopter Alert Service Bulletin No. 

05A002, Revision 1, dated December 6, 2007. 

(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 November 

5, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27638 Filed 11–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0418; Directorate 

Identifier 2012–NM–200–AD; Amendment 

39–17668; AD 2013–23–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A300 series airplanes; 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes; and Model A300 

C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). This AD was prompted 

by a report that cracking was found in 

area 2 of the frame base fittings between 

frame 41 and frame 46. This AD requires 

a check of maintenance records to 

determine if certain repairs were done 

in area 1 of the frame base fittings, and, 

for affected airplanes, a detailed 

inspection for cracking in area 2 of the 

frame base fittings between frame 41 

and frame 46, and repair if necessary. 

We are issuing this AD to detect and 

correct cracking in area 2 of the frame 

base fittings between frame 41 and 

frame 46, which could adversely affect 

the structural integrity of the airplane. 

DATES: This AD becomes effective 

December 30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 30, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0418 or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: (425) 227–2125; 

fax: (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on May 14, 2013 (78 FR 28159). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2012–0229, 

dated October 31, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During accomplishment of Airbus SB 

[service bulletin] A300–53–6111, which 

addresses detailed visual inspections of the 

lower frame fittings between Frame (FR) 41 

and FR 46, on one A300–600 aeroplane a 

crack was detected in the area 2 of the foot 

of frame FR 46 at junction radius level. 

This frame, that was previously repaired 

due to a crack finding in the area 1, was not 

due to be inspected before reaching the postrepair inspection threshold, i.e., 45,400 FC 

[flight cycles], from repair embodiment. 

It has been determined that the current 

repairs proposed in Airbus SB A300–53– 

6111 and Airbus [SB] A300–53–0337 are of 

limited effect to prevent cracking in the area 

2 of the lower frame fittings. 

Consequently, as a temporary action and 

until an improvement of the existing repairs 

is made available, this [EASA] AD requires 

a one-time detailed visual inspection [for 

cracking] of [the] frame base fittings that were 

repaired in accordance with Airbus SB 

A300–53–0337, original issue or Rev. 1, or 

Airbus SB A300–53–6111 original issue up to 

Rev. 4 * * *. 

The unsafe condition is cracking in the 

frame base fittings, which could 

adversely affect the structural integrity 

of the airplane. The required actions 

include repairing any cracking found. 

You may obtain further information by 

examining the MCAI in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0418- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Request To Correct Typographical 

Error in SUMMARY Section 

UPS noted there is a typographical 

error in the SUMMARY section of the 

NPRM (78 FR 28159, May 14, 2013). 

UPS stated that the third line includes 

the phrase ‘‘frame brace fittings,’’ but 

throughout the rest of the document the 

terminology used is ‘‘frame base 

fittings.’’ UPS suggested that for 


emcdonald on DSK67QTVN1PROD with RULES