7288 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 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 January 

21, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–01663 Filed 2–9–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0133; Directorate 

Identifier 2014–SW–066–AD; Amendment 

39–18088; AD 2014–22–51] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Formerly Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are publishing a new 

airworthiness directive (AD) for Airbus 

Helicopters (formerly Eurocopter 

France) Model EC130T2 helicopters, 

which was sent previously to all known 

U.S. owners and operators of these 

helicopters. This AD requires 

repetitively inspecting the attachment 

points where the fan attaches to the 

main gearbox (MGB) oil cooler hopper 

(hopper) and replacing any cracked 

hopper with an airworthy hopper. This 

AD is prompted by several cases of a 

cracked hopper. The cracks were found 

on the hopper at the fan attachment 

points. These actions are intended to 

detect a crack in the hopper at a fan 

attachment point to prevent failure of 

the fan attachment, interference of the 

fan with the control rod of the front 

servo-control or with the flight control 

bellcrank, and subsequent loss of 

control of the helicopter. 

DATES: This AD becomes effective 

February 25, 2015 to all persons except 

those persons to whom it was made 

immediately effective by Emergency AD 

(EAD) 2014–22–51, issued on October 

29, 2014, which contained the 

requirements of this AD. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of February 25, 2015. 

We must receive comments on this 

AD by April 13, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this AD, contact Airbus Helicopters, 

Inc., 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641– 

0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0133. 

FOR FURTHER INFORMATION CONTACT: Eric 

Haight, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

eric.haight@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

On October 29, 2014, we issued EAD 

2014–22–51, which requires, before 

further flight and thereafter at intervals 

not to exceed 10 hours time-in-service 

(TIS), visually inspecting the hopper for 

a crack at the four attachment points. If 

there is a crack, EAD 2014–22–51 

requires replacing the hopper with an 

airworthy hopper, which is not 

terminating action for the repetitive 

visual inspections. EAD 2014–22–51 

was sent previously to all known U.S. 

owners and operators of these 

helicopters and resulted from several 

cases of a cracked MGB oil cooler 

hopper. 

EAD 2014–22–51 was prompted by 

EAD No. 2014–0229–E, dated October 

20, 2014, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for the Airbus 

Helicopters Model EC130T2 helicopters. 

EASA advises of several cases of 

cracked MGB oil cooler fan attachments 

to the hopper. EASA EAD No. 2014– 

0229–E requires repetitive visual 

inspections of the MGB oil cooler fan 

attachment to the hopper and, 

depending on findings, replacement of 

cracked parts. 

FAA’s Determination 

This helicopter has been approved by 

the aviation authority of France and is 


rljohnson on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations 7289 

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 EAD. 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 

the same type design. 

Related Service Information Under 1 

CFR Part 51 

Airbus Helicopters issued Emergency 

Alert Service Bulletin No. 05A020 

Revision 0, dated October 20, 2014 

(EASB), specifying periodic visual 

checks for cracks in the engine MGB oil 

fan hopper. The EASB states that a crack 

could lead to the total failure of the fan 

attachment and that this condition, if 

not detected and corrected, could lead 

to interference of the fan with the 

control rod of the front servo-control or 

with the flight control bellcrank, 

possibly resulting in reduced control of 

the helicopter. Also, the EASB states 

that pending modification, the periodic 

visual check of the hopper is necessary. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

AD Requirements 

This AD requires, before further flight 

and thereafter at intervals not to exceed 

10 hours TIS, visually inspecting the 

hopper for a crack at the four fan 

attachment points. If there is a crack in 

the hopper, this AD requires replacing 

the hopper with an airworthy hopper. 

Replacing the hopper does not 

constitute terminating action for the 

repetitive visual inspections required by 

this AD. 

Differences Between This AD and the 

EASA AD 

We do not use the compliance time 

option of every 7 days. 

Interim Action 

We consider this AD to be an interim 

action. The design approval holder is 

currently developing a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, we might consider 

additional rulemaking. 

Costs of Compliance 

We estimate that this AD will affect 

60 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. Labor costs are estimated 

at $85 per hour. We estimate 0.2 work 

hour to inspect the hopper at an 

estimated $17 per helicopter and a total 

cost of $1,020 for the fleet. If a hopper 

is replaced, we estimate 6 hours to 

replace it and $1,000 for required parts 

for a total of $1,510. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we found and continue to 

find that the risk to the flying public 

justifies waiving notice and comment 

prior to the adoption of this rule 

because the previously described unsafe 

condition can adversely affect the 

controllability of the helicopter and the 

required corrective actions must be 

accomplished before further flight and 

in 10-hour intervals. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment before issuing this AD were 

impracticable and contrary to the public 

interest and good cause existed to make 

the AD effective immediately by EAD 

2014–22–51, issued on October 9, 2014, 

to all known U.S. owners and operators 

of these helicopters. These conditions 

still exist and the AD is hereby 

published in the Federal Register as an 

amendment to section 39.13 of the 

Federal Aviation Regulations (14 CFR 

39.13) to make it effective to all persons. 

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 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that 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, 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): 

2014–22–51 Airbus Helicopters 

(Formerly Eurocopter France): Amendment 

39–18088; Docket No. FAA–2015–0133; 

Directorate Identifier 2014–SW–066–AD. 

(a) Applicability 

This AD applies to Model EC130T2 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the main gearbox oil cooler fan 

hopper. This condition could result in failure 

of the fan attachment, interference of the fan 

with the control rod of the front servo-control 

or with the flight control bellcrank, and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 25, 

2015 to all persons except those persons to 

whom it was made immediately effective by 

Emergency AD 2014–22–51, issued on 

October 29, 2014, which contains the 

requirements of this AD. 


rljohnson on DSK3VPTVN1PROD with RULES
7290 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations 

(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 

Before further flight and thereafter at 

intervals not to exceed 10 hours time-inservice, using a light and a mirror, visually 

inspect the hopper for a crack at the four fan 

attachment points. The hopper is depicted as 

item ‘‘a’’ and the fan as item ‘‘b’’ in Figure 

1 of Airbus Helicopters Emergency Alert 

Service Bulletin No. 05A020, Revision 0, 

dated October 20, 2014 (EASB). If there is a 

crack in the hopper, replace the hopper with 

an airworthy hopper. Examples of a crack are 

shown in Figure 2 of the EASB. Replacing the 

hopper does not constitute terminating action 

for the repetitive visual inspections required 

by this AD. 

(f) Special Flight Permits 

Special flight permits may be issued 

provided that the fan is removed. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

EAD. Send your proposal to: Eric Haight, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

eric.haight@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 

EAD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD No. 2014–0229–E, dated 

October 20, 2014. You may view the EASA 

AD on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2015–0133. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Tracking Code: 6322 Main Rotor Drive 

Rotorcraft Cooling Fan 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) Airbus Helicopters Emergency Alert 

Service Bulletin No. 05A020, Revision 0, 

dated October 20, 2014. 

(ii) Reserved. 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://

www.airbushelicopters.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 January 16, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01803 Filed 2–9–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0142; Directorate 

Identifier 2012–NM–161–AD; Amendment 

39–18093; AD 2015–02–24] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2007–03– 

18, AD 2008–17–02, AD 2012–08–03, 

and AD 2012–15–14, for certain Airbus 

Model A300 B4–2C, B4–103, and B4– 

203 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); and Model 

A310 series airplanes. AD 2007–03–18, 

AD 2008–17–02, AD 2012–08–03, and 

AD 2012–15–14 required repetitive 

inspections of the forward lugs of the aft 

bearing at rib 5 of the main landing gear 

(MLG) on the left-hand (LH) and righthand (RH) wings, and repair if 

necessary; and installation of new 

bushes with increased interference fit in 

the forward lug of the aft bearing at rib 

5 of the MLG on the LH and RH wings. 

This new AD adds airplanes to the 

applicability; and adds, for certain 

airplanes, repetitive inspections of the 

MLG rib 5 aft bearing forward lugs, and 

repair if necessary. This AD was 

prompted by reports of cracking in the 

forward lug of the MLG rib 5 aft bearing 

attachment. We are issuing this AD to 

detect and correct cracking of the 

forward lugs of the aft bearing at rib 5 

of the MLG on the LH and RH wings, 

which could affect the structural 

integrity of the MLG attachment, 

resulting in possible MLG collapse 

during landing or rollout. 

DATES: This AD becomes effective 

March 17, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 17, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of September 11, 2012 (77 FR 

46937, August 7, 2012). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 29, 2012 (77 FR 

24367, April 24, 2012). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of September 17, 2008 (73 FR 

47032, August 13, 2008). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of February 6, 2007 (72 FR 

2612, January 22, 2007). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0142; or in 

person at the Docket 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. 

For service information identified in 

this AD, contact Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0142. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 


rljohnson on DSK3VPTVN1PROD with RULES