70202 Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 

(d) Subject 

Air Transport Association of America 

(ATA) Code 28: Fuel. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as a defective 

sealing of a tapped through bore hole at the 

inside of the fuel tank openings in 

combination with prolonged periods at 

maximum fuel level. We are issuing this AD 

to detect and correct a defective sealing of a 

tapped through bore hole at the inside of the 

fuel tank openings, which if not detected and 

corrected, could cause long-term structural 

degradation of the wing structure. 

(f) Actions and Compliance 

Unless already done, do the following 

actions, as specified in paragraphs (f)(1) 

through (f)(6), including subparagraphs, of 

this AD: 

Note 1 to paragraph (f) of this AD: The 

service information referenced in this AD 

contains German to English translation. The 

MCAI cites the English translation. The 

following is the English to German 

translation of the service information 

entitled: AQUILA Aviation GmbH 

Vorgeschrieben Technische Mitteilung SB– 

AT01–027, dated August 15, 2013 (English 

translation: AQUILA Aviation GmbH 

Mandatory Service Bulletin SB–AT01–027, 

Issue A.02, dated August 15, 2013). For 

paragraphs (f)(1) through (f)(6), the service 

information will be cited using the English 

translation. 

(1) Within 100 hours time-in-service (TIS) 

after December 30, 2013 (the effective date of 

this AD) or 3 months after December 30, 2013 

(the effective date of this AD), whichever 

occurs first, and repetitively thereafter at 

intervals not to exceed 12 months, visually 

inspect the left hand (LH) and right hand 

(RH) wing tank areas following paragraph (1) 

of the Actions section of AQUILA Aviation 

GmbH Mandatory Service Bulletin SB– 

AT01–027, Issue A.02, dated August 15, 

2013. 

(2) Concurrent with the initial inspection 

required in paragraph (f)(1) of this AD, seal 

the tapped through bore holes inside the LH 

and RH fuel tank openings following 

paragraph (2) of the Actions section of 

AQUILA Aviation GmbH Mandatory Service 

Bulletin SB–AT01–027, Issue A.02, dated 

August 15, 2013. 

(3) If, during any subsequent inspection 

required in paragraph (f)(1) of this AD, a 

tapped through bore hole inside the LH or 

RH fuel tank opening is found to be 

improperly sealed, within the next 100 hours 

TIS after detecting the improper seal or 3 

months after detecting the improper seal, 

whichever occurs first, renew the sealing of 

the affected bore hole following paragraph (2) 

of the Actions section of AQUILA Aviation 

GmbH Mandatory Service Bulletin SB– 

AT01–027, Issue A.02, dated August 15, 

2013. 

(4) If, during any inspection required in 

paragraph (f)(1) of this AD, the upper wing 

shells show damaged finishing in the tank 

areas, before further flight, contact AQUILA 

Aviation GmbH following paragraph (3) of 

the Actions section of AQUILA Aviation 

GmbH Mandatory Service Bulletin SB– 

AT01–027, Issue A.02, dated August 15, 

2013, at the address identified in paragraph 

(i)(3) of this AD for an approved repair 

scheme and, accomplish the repair scheme 

before further flight. 

(5) Accomplishment of corrective actions 

required in paragraph (f)(3) or (f)(4) of this 

AD does not constitute terminating action for 

the repetitive inspections required by 

paragraph (f)(1) of this AD. 

(6) After accomplishment of the required 

initial inspection and sealing in paragraphs 

(f)(1) and (f)(2) of this AD, compliance with 

the requirements of this AD can be 

demonstrated by: 

(i) Revising the approved Aircraft 

Maintenance Program (AMP) and standard 

practices (Instructions for Continued 

Airworthiness) on the basis of which the 

operator or the owner ensures the continuing 

airworthiness of each airplane: Incorporate 

the repetitive 12 calendar month visual 

inspection of the LH and RH wing tank areas 

required in paragraph (f)(1) of this AD, 

Actions section of AQUILA Aviation GmbH 

Mandatory Service Bulletin SB–AT01–027, 

Issue A.02, dated August 15, 2013; and 

(ii) Complying with the approved AMP 

described in paragraph (f)(6)(i) of this AD. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2013–0236, dated 

September 25, 2013, for related information. 

You may examine the MCAI on the Internet 

at http://www.regulations.gov by searching 

for and locating it in Docket No. FAA–2013– 

0963. 

(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) AQUILA Aviation GmbH 

Vorgeschrieben Technische Mitteilung SB– 

AT01–027, dated August 15, 2013 (English 

translation: AQUILA Aviation GmbH 

Mandatory Service Bulletin SB–AT01–027, 

Issue A.02, dated August 15, 2013). 

Note 2 to paragraph (i)(2)(i) of this AD: 

This service information contains German to 

English translation. EASA used the English 

translation in referencing the documents 

from AQUILA Aviation GmbH. For 

enforceability purposes, we will refer to the 

AQUILA Aviation GmbH service information 

as the titles appear on the documents. 

(ii) Reserved. 

(3) For AQUILA—Aviation by Excellence 

AG service information identified in this AD, 

contact AQUILA Aviation GmbH, OT 

Schoenhagen, Flugplatz, D–14959 Trebbin, 

Germany; phone: +49-(0) 33731–707–0; fax: 

+49 (0) 33731–707–11; Internet: http://

www.aquila-aviation.de/; email: 

maintenance@aquila-aviation.de. 

(4) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on 

November 5, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–27914 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–2013–0354; Directorate 

Identifier 2011–SW–072–AD; Amendment 

39–17665; AD 2013–23–10] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010– 

21–01 for Eurocopter France 

(Eurocopter) Model AS350B, BA, B1, 

B2, B3, D, AS355E, F, F1, F2, and N 


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Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 70203 

helicopters. AD 2010–21–01 required an 

inspection to determine whether a 

cross-member is installed at station X 

2165 and doublers at X 2325 and Y 269, 

and installing them if they are missing. 

This new AD retains the requirements of 

AD 2010–21–01 but clarifies the 

inspection procedures and limits the 

applicability to only those helicopters 

with collective-to-yaw control coupling. 

This AD is prompted by a crack 

discovered in the area of the center 

cross-member at station X 2325, at the 

attachment point of the yaw channel 

ball-type control sheath stop, of a Model 

AS355N helicopter fitted with the 

collective-to-yaw control coupling. The 

actions of this AD are intended to 

prevent reduced yaw control and 

subsequent 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 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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–21–01, 

Amendment 39–16461 (75 FR 63050, 

October 14, 2010), which applied to 

Eurocopter Model AS350B, BA, B1, B2, 

B3, D, AS355E, F, F1, F2, and N 

helicopters. The NPRM was published 

in the Federal Register on July 3, 2013 

(78 FR 40045). AD No. 2010–21–01 

required within 10 hours time-in-service 

(TIS) or 1 month, inspecting the 

helicopters to determine whether a 

cross-member is installed at station X 

2165 and doublers at X 2325 and Y 269. 

If the cross-member and doublers are 

not installed, AD No. 2010–21–01 

required inspecting for a crack in the 

center cross-member, and replacing the 

center cross-member if there is a crack 

before further flight. If a crack does not 

exist, AD No. 2010–21–01 required 

inspecting the tail rotor control rigging 

before further flight. Lastly, if needed, 

AD 2010–21–01 required installing a 

cross-member and two doublers within 

55 hours TIS. AD 2010–21–01 was 

prompted by AD No. 2007–0139–E, 

dated May 15, 2007 (corrected May 23, 

2007), issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union. EASA advised 

that a crack was discovered in the area 

of the center cross-member at station X 

2325, at the attachment point of the yaw 

channel ball-type control sheath stop, of 

a Model AS355N helicopter fitted with 

the collective-to-yaw control coupling. 

Since we issued AD No. 2010–21–01, 

we discovered that we included all 

helicopters in the AD applicability 

rather than limiting it to only those 

helicopters with collective-to-yaw 

control coupling. Therefore, this new 

AD retains the requirements in AD No. 

2010–21–01 with some revisions for the 

inspection of the tail rotor control 

rigging to clarify those procedures. This 

AD also reduces the applicability to 

only those Model AS350 and AS355 

helicopters with collective-to-yaw 

control coupling installed. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(78 FR 40045, July 3, 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 as 

follows: 

• We require the installation of the 

cross-member at station X 2165 and the 

two doublers at stations X 2325 and Y 

269 within 55 hours time-in-service. 

The EASA AD requires that this action 

be accomplished within 12 months. 

• We do not require repetitive 

inspections if no crack exists in the 

center cross-member, whereas the EASA 

AD does. 

• We do not include military model 

helicopters in the applicability. 

Related Service Information 

We reviewed Eurocopter Emergency 

Alert Service Bulletin (EASB), Revision 

0, dated April 11, 2007, that contains 

three different numbers (Nos. 53.00.37, 

53.00.11, and 53.00.23) for Eurocopter 

Model 350, 355, 550, and 555 

helicopters. EASB No. 53.00.37 relates 

to two Model 350 (350 BB and 350 L1) 

helicopters that are not type certificated 

in the United States. EASB No. 53.00.11 

relates to four Model 550 and six Model 

555 military helicopters that are not 

type-certificated in the United States. 

The EASB describes procedures for 

checking the conformity for the cross 

member at X 2325 under the cabin floor. 

The actions in the EASA AD are 

intended to correct the same unsafe 

condition as that identified in the 

service bulletin. 

Costs of Compliance 

We estimate that this AD affects 72 

helicopters of U.S. Registry and that 

labor costs average $85 a work-hour. It 

takes about one work-hour to perform 

the inspections, and if needed, to install 

the cross-member, two doublers and an 

airworthy center-cross member. 

Required parts cost about $161 per 

helicopter. Based on these figures, we 

estimate the cost of the AD to be $246 

per helicopter and $17,712 for the fleet 

if all repairs are needed. 

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: 


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70204 Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 

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 

removing Airworthiness Directive (AD) 

2010–21–01, Amendment 39–16461 (75 

FR 63050, October 14, 2010), and 

adding the following new AD: 

2013–23–10 Eurocopter France: 

Amendment 39–17665; Docket No. 

FAA–2013–0354; Directorate Identifier 

2011–SW–072–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

Model AS350B, BA, B1, B2, B3, D, AS355E, 

F, F1, F2, and N helicopters with collectiveto-yaw control coupling, part number 

350A27–2178–04, 350A27–2178–06, or 

350A27–2178–0601, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

reduced yaw control travel, which could 

result in loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2010–21–01, 

Amendment 39–16461 (75 FR 63050, October 

14, 2010). 

(d) Effective Date 

This AD becomes effective December 30, 

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) Within 10 hours time-in-service (TIS) or 

within one month, whichever occurs first, 

determine whether the cross-member 

(numbered ‘‘1’’) at station X 2165 and the two 

doublers (numbered ‘‘2’’ and ‘‘3’’) at stations 

X 2325 and Y 269 are installed as shown in 

Figure 1 of Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 53.00.37, 

Revision 0, dated April 11, 2007 (EASB 

53.00.37), for Model AS350 helicopters and 

EASB No. 53.00.23, Revision 0, dated April 

11, 2007 (EASB 53.00.23), for Model AS355 

helicopters. 

(2) If the cross-member (numbered ‘‘1’’) 

and doublers (numbered ‘‘2’’ and ‘‘3’’) are not 

installed, before further flight, inspect for a 

crack in the center cross-member (numbered 

‘‘4’’) in the area around the attachment point 

of the tail rotor directional ball-type control 

as shown in Figure 1 of EASB 53.00.37 for 

Model AS350 helicopters or EASB 53.00.23 

for Model AS355 helicopters. 

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

replace the unairworthy center cross-member 

(Numbered ‘‘4’’) with an airworthy center 

cross-member as described in paragraph (f)(3) 

of this AD. 

(ii) If a crack does not exist, before further 

flight, inspect the tail rotor control rigging to 

determine whether it meets conformity 

limits. 

(A) If all items of the tail rotor control 

rigging are found within conformity limits, 

install the cross-member and doublers as 

described in paragraph (f)(3) of this AD. 

(B) For any items of the tail rotor control 

rigging found outside of conformity limits, 

perform appropriate corrective action in 

accordance with FAA-accepted procedures, 

and install the cross-member and doublers as 

described in paragraph (f)(3) of this AD. 

(3) Within 55 hours TIS, if the cross 

member (Numbered ‘‘1’’) is not installed, 

install the cross-member at station X 2165 

and the 2 doublers (Numbered ‘‘2’’ and ‘‘3’’) 

at stations X 2325 and Y 269 by following the 

Appendix, the referenced figures 2 and 3 of 

EASB 53.00.37 for Model AS350 helicopters 

or EASB 53.00.23 for Model AS355 

helicopters. 

(g) 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, TX 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 

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. 2007–0139–E, dated May 15, 2007 

(corrected May 23, 2007). You may view the 

EASA AD at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2013–0354. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5320, Fuselage Miscellaneous 

Structure. 

(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 Emergency Alert Service 

Bulletin No. 53.00.37, Revision 0, dated April 

11, 2007. 

(ii) Eurocopter Emergency Alert Service 

Bulletin No. 53.00.23, Revision 0, dated April 

11, 2007. 

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

Emergency Alert Service Bulletin (EASB) No. 

53.00.37, Revision 0, dated April 11, 2007, 

and Eurocopter EASB No. 53.00.23, Revision 

0, dated April 11, 2007, are co-published as 

one document along with Eurocopter EASB 

No. 53.00.11, Revision 0, dated April 11, 

2007, which is 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) 


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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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