Federal Register / Vol. 75, No. 143 / Tuesday, July 27, 2010 / Rules and Regulations 43801 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0721; Directorate 

Identifier 2009–SW–56–AD; Amendment 39– 

16370; AD 2010–15–04] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (ECF) Model EC225LP 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

specified ECF Model EC225LP 

helicopters. This AD results from a 

mandatory continuing airworthiness 

information (MCAI) AD issued by the 

aviation authority of the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community. The 

MCAI AD states there have been a ‘‘few’’ 

reports of cracks and failure of the main 

rotor hub (MRH) cone restrainer support 

lugs at their attachment points on the 

reinforcement ring where the dome 

fairing is secured. Also, cracks on the 

dome fairing support have been 

reported. Failure of the cone restrainer 

support or the dome fairing support 

attachment lugs may lead to loss of the 

dome fairing, damage to the rotor 

blades, and subsequent loss of control of 

the helicopter. 

DATES: This AD becomes effective on 

August 11, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 11, 

2010. 

We must receive comments on this 

AD by September 27, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting your 

comments electronically. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from American 

Eurocopter Corporation, 2701 Forum 

Drive, Grand Prairie, TX 75053–4005, 

telephone (800) 232–0323, fax (972) 

641–3710, or at http:// 

www.eurocopter.com. 

Examining the 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 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is 

stated in the ADDRESSES section of this 

AD. Comments will be available in the 

AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Gary 

Roach, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5130, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2009– 

0024, dated February 20, 2009, to 

correct an unsafe condition for the 

Eurocopter Model EC225LP helicopters. 

The MCAI AD states there have been 

a ‘‘few’’ reports of cracks and failure of 

the MRH cone restrainer support lugs in 

the area of their attachment points on 

the reinforcement ring where the dome 

fairing is secured. Also, cracks on the 

dome fairing support have been 

reported. Failure of the cone restrainer 

support or the dome fairing support 

attachment lugs may lead to loss of the 

dome fairing, damage to the rotor 

blades, and subsequent loss of control of 

the helicopter or injury to persons on 

the ground. 

You may obtain further information 

by examining the MCAI AD and any 

related service information in the AD 

docket. 

Related Service Information 

Eurocopter has issued one Emergency 

Alert Service Bulletin (EASB) No. 

05A003, Revision 2, dated February 3, 

2009 (EASB No. 05A003) for two 

different helicopters: the Model 

EC225LP and the military Model 

EC725AP, a non-FAA type certificated 

helicopter. Eurocopter has also issued 

EASB No. 62–007, dated July 10, 2009 

(SB 62–007), which corresponds to 

MOD 0743718. EASB 05A003 specifies 

checking the MRH in the area of the 

cone restrainer support attachment lugs 

and the dome fairing support 

attachment lugs for a crack. If a crack is 

found in one of the five lugs of the cone 

restrainer support or the dome fairing 

support, the EASB specifies complying 

with SB 62–007 before further flight. SB 

62–007 specifies modifying the MRH by 

replacing the cone restrainer support 

and the dome fairing support, 

reidentifying those parts and balancing 

the main rotor blades if they were 

removed. The actions described in the 

MCAI AD are intended to correct the 

unsafe condition identified in the 

service information. 

FAA’s Evaluation and Unsafe Condition 

Determination 

This helicopter has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, their 

Technical Agent, has notified us of the 

unsafe condition described in the MCAI 

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 this 

same type design. 

Differences Between This AD and the 

MCAI AD 

We do not specify dates because the 

dates have already passed nor do we 

specify the compliance time in days but 

rather only in hours time-in-service 

(TIS). We also use a different 

compliance time. Also, we use inspect 

rather than check when referring to an 

action required by a mechanic as 

opposed to a pilot. 

Costs of Compliance 

We estimate that this AD will affect 

about 4 helicopters of U.S. registry. We 

also estimate that it will take about 30 

work-hours per helicopter to inspect 

and modify the MRH. The average labor 

rate is $85 per work-hour. Required 

parts will cost about $18,981 per 

helicopter. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators will be $86,124, assuming a 

crack is found in each MRH cone 

restrainer support or dome fairing 

support attachment lugs. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 


jdjones on DSK8KYBLC1PROD with RULES
43802 Federal Register / Vol. 75, No. 143 / Tuesday, July 27, 2010 / Rules and Regulations 

AD. We find that the risk to the flying 

public justifies waiving notice and 

comment prior to adoption of this rule 

because of the short compliance time of 

15 hours TIS to conduct the inspection 

for a crack in the attachment lugs. 

Failure of these lugs could result in loss 

of control of the helicopter. Therefore, 

we have determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in fewer than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. 

However, we invite you to send us any 

written data, views, or arguments 

concerning this AD. Send your 

comments to an address listed under the 

ADDRESSES section of this AD. Include 

‘‘Docket No. FAA–2010–0721; 

Directorate Identifier 2009–SW–56–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 

product(s) 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. 

Therefore, I certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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): 

2010–15–04 EUROCOPTER FRANCE: 

Amendment 39–16370. Docket No. 

FAA–2010–0721; Directorate Identifier 

2009–SW–57–AD. 

Effective Date 

(a) This AD becomes effective on August 

11, 2010. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model EC225LP 

helicopters, except those that have been 

modified with MOD 0743718, certificated in 

any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD states 

there have been a ‘‘few’’ reports of cracks and 

failure of the main rotor hub (MRH) cone 

restrainer support lugs at their attachment 

points on the reinforcement ring where the 

dome fairing is secured. Also, cracks on the 

dome fairing support have been reported. 

Failure of the cone restrainer support or the 

dome fairing support attachment lugs may 

lead to loss of the dome fairing, damage to 

the rotor blades, and subsequent loss of 

control of the helicopter. 

Actions and Compliance 

(e) Required as indicated: 

(1) Within 15 hours time-in-service (TIS), 

unless already done, and thereafter at 

intervals not to exceed 15 hours TIS, visually 

inspect for a crack in the area of the 

attachment points on the MRH reinforcement 

ring of the lugs securing the cone restrainer 

support and also of the lugs securing the 

dome fairing support as depicted in Figures 

1 and 2 of Eurocopter Emergency Alert 

Service Bulletin No. 05A003, Revision 2, 

dated February 3, 2009 (EASB No. 05A003) 

and by following the Accomplishment 

Instructions, paragraph 2.B.1, of EASB No. 

05A003. 

Note: The one EASB No. 05A003 applies 

to two different model helicopters: 

Eurocopter Model EC225LP helicopters that 

are type-certificated in the United States and 

Eurocopter Model EC725AP military 

helicopters that are not type-certificated in 

the United States. 

(2) If a crack is found in the area of any 

of the lugs of the cone restrainer support or 

the dome fairing support, as depicted in 

Figures 1 and 2 of EASB No. 05A003, before 

further flight, modify the MRH by replacing 

both the cone restrainer support and the 

dome fairing support assembly by following 

the Accomplishment Instructions, paragraphs 

2.B.1. and 2.B.2., reidentify the cone 

restrainer support and dome fairing assembly 

by following paragraph 2.D., and if removed, 

track and balance the main rotor blades by 

following paragraph 3.B.3. of Eurocopter 

Service Bulletin No. 62–007, Revision 1, 

dated July 10, 2009. 

(f) Replacing and reidentifying both the 

cone restrainer support and the dome fairing 

support assembly in accordance with 

paragraph (e)(2) of this AD constitutes 

terminating action for the requirements of 

this AD. 

Differences Between this AD and the MCAI 

AD 

(g) We do not specify dates because the 

dates are already passed nor do we specify 

the time in days but rather only in hours TIS. 

We also use a different initial compliance 

time. Also, we use inspect rather than check 

when referring to an action required by a 

mechanic as opposed to a pilot. 

Other Information 

(h) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, ATTN: DOT/FAA Southwest Region, 

Gary Roach, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, Regulations 

and Guidance Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone (817) 

222–5130, fax (817) 222–5961, has the 

authority to approve AMOCs for this AD, if 

requested, using the procedures found in 14 

CFR 39.19. 


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Federal Register / Vol. 75, No. 143 / Tuesday, July 27, 2010 / Rules and Regulations 43803 

(i) A special flight permit may be issued to 

ferry the helicopter to a location where the 

modification can be done, provided the dome 

fairing and its attachment screws are 

removed. When allowing flight with the 

dome fairing removed, the special flight 

permit must contain information that alerts 

the flight crew that when flying without the 

dome fairing, the lateral vibrations of the 

helicopter significantly increase at speeds of 

70 to 120 knots. These lateral vibrations do 

not affect flight safety. 

Related Information 

(j) European Aviation Safety Agency 

(EASA) Airworthiness Directive No. 2009– 

0024, dated February 20, 2009, contains 

related information. 

Joint Aircraft System/Component (JASC) 

Code 

(k) The JASC Code is 6220: Main Rotor 

Head. 

Material Incorporated by Reference 

(l) You must use the specified portions of 

Eurocopter Emergency Alert Service Bulletin 

No. 05A003, Revision 2, dated February 3, 

2009, and Eurocopter Service Bulletin No. 

62–007, Revision 1, dated July 10, 2009, to 

do the actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Fort Worth, 

Texas, 76137; or 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/ibr-locations.html. 

Issued in Fort Worth, Texas, on July 13, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–17757 Filed 7–26–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0173; Directorate 

Identifier 2009–NM–076–AD; Amendment 

39–16374; AD 2010–15–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. That AD currently 

requires repetitive inspections to find 

cracks, fractures, or corrosion of each 

carriage spindle of the left and right 

outboard mid-flaps, and corrective 

action if necessary. That AD also 

currently requires repetitive gap checks 

of the inboard and outboard carriage of 

the outboard mid-flaps to detect 

fractured carriage spindles, and 

corrective actions if necessary. This new 

AD requires any new or serviceable 

carriage spindle installed per the 

requirements of the existing AD to meet 

minimum allowable diameter 

measurements taken at three locations. 

This AD also requires new repetitive 

inspections, measurements, and 

overhaul of the carriage spindles, and 

applicable corrective actions. In 

addition, this AD requires replacing any 

carriage spindle when it has reached its 

maximum life limit. This AD results 

from reports of fractures that resulted 

from stress corrosion and pitting along 

the length of the spindle and spindle 

diameter, and additional reports of 

corrosion on the outboard flap carriage 

spindles. We are issuing this AD to 

detect and correct cracked, corroded, or 

fractured carriage spindles, and to 

prevent severe flap asymmetry, which 

could result in reduced control or loss 

of controllability of the airplane. 

DATES: This AD becomes effective 

August 31, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 31, 2010. 

On December 4, 2003 (68 FR 67027, 

December 1, 2003), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in the AD. 

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; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 (telephone 800–647–5527) 

is the 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; telephone 

(425) 917–6440; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2003–24–08, 

Amendment 39–13377 (68 FR 67027, 

December 1, 2003). The existing AD 

applies to all Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. That NPRM was published in 

the Federal Register on March 1, 2010 

(75 FR 9137). That NPRM proposed to 

continue to require repetitive gap 

checks of the inboard and outboard 

carriage of the outboard mid-flaps to 

detect fractured carriage spindles, and 

corrective actions if necessary, and 

continue to require repetitive 

inspections to find cracks, factures, or 

corrosion of each carriage spindle of the 

left and right outboard mid-flaps. That 

NPRM also proposed to require any new 

or serviceable carriage spindle installed 

per the requirements of the existing AD 

to meet minimum allowable diameter 

measurements taken at three locations. 

That NPRM proposed to require new 

repetitive inspections, measurements, 

and overhaul of the carriage spindles, 

and applicable corrective actions. In 

addition, that NPRM also proposed to 

require replacing any carriage spindle 


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