22510 Federal Register / Vol. 75, No. 82 / Thursday, April 29, 2010 / Rules and Regulations 

Actions and Compliance 

(e) Before the next hoist operation, unless 

already accomplished, disconnect the ground 

wire for the hoist squib wiring and test the 

hoist system to assure that the squib can be 

electrically fired (MOD 073318) by following 

the Accomplishment Instructions, Paragraph 

2.B.1. through 2.B.4., of Eurocopter Alert 

Service Bulletin (ASB) No. 25.00.95, for the 

AS350 model helicopters or ASB No. 

25.00.85, for the AS355 model helicopters, 

both dated November 16, 2005, as 

appropriate for your model helicopter. 

Differences Between This AD and the MCAI 

AD 

(f) This AD differs from the MCAI AD in 

that it: 

(1) Does not include the Model BB 

helicopters but does include the Model 

AS350C and D1 and Model AS355NP 

helicopters; 

(2) Does not require the actions specified 

in the Compliance section, paragraph 1 of the 

MCAI AD; 

(3) Does not address spares; and 

(4) Requires compliance before the next 

hoist operation instead of within 30 days. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, FAA, ATTN: George Schwab, 

Aerospace Engineer, Rotorcraft Directorate, 

Fort Worth, Texas 76193–0112, telephone 

(817) 222–5114, fax (817) 222–5961, has the 

authority to approve AMOCs for this AD, if 

requested, using the procedures found in 14 

CFR 39.19. 

(h) Special Flight Permits: Special flight 

permits may be issued under 14 CFR 21.197 

and 21.199 to operate the helicopter to a 

location where the requirements of this AD 

can be done provided that the hoist is not 

used. 

Related Information 

(i) Mandatory Continuing Airworthiness 

Information (EASA) Airworthiness Directive 

No. 2006–0164, dated June 9, 2006, contains 

related information. 

Joint Aircraft System/Component (JASC) 

Code 

(j) The JASC Code is 25: Equipment/ 

Furnishings. 

Material Incorporated by Reference 

(k) You must use the specified portions of 

Eurocopter Alert Service Bulletin No. 

25.00.95 or No. 25.00.85, both dated 

November 16, 2005, 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 the service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (972) 

641–3460, fax (972) 641–3527. 

(3) You may review copies of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas, 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 March 15, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–9006 Filed 4–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0410; Directorate 

Identifier 2010–SW–024–AD; Amendment 

39–16265; AD 2010–05–51] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (ECF) Model EC120B 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting Airworthiness Directive (AD) 

2010–05–51, which was sent previously 

to all known U.S. owners and operators 

of ECF Model EC120B helicopters by 

individual letters. This AD requires, at 

specified intervals, inspecting the main 

rotor head rotor hub (rotor hub) for a 

crack. If you find scoring, paint flaking 

or left-over identification plate 

adhesive, the AD requires sanding the 

area until the primer coat becomes 

visible and inspecting the rotor hub for 

a crack. If you find a crack, the AD 

requires, before further flight, replacing 

the rotor hub with an airworthy rotor 

hub. This amendment is prompted by a 

mandatory continuing airworthiness 

information (MCAI) AD issued by the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community. The MCAI AD states that 

ECF has been informed of an emergency 

landing due to excessive vibrations 

originating from the main rotor. After an 

investigation, it was determined that the 

main rotor head rotor hub (rotor hub) 

had failed in the attachment area of one 

of the three drag damper fittings. The 

actions specified by the AD are intended 

to prevent failure of a hub, excessive 

vibrations, loss of a main rotor blade, 

and subsequent loss of control of the 

helicopter. 

DATES: Effective May 14, 2010, to all 

persons except those persons to whom 

it was made immediately effective by 

Emergency AD (EAD) 2010–05–51, 

issued on February 24, 2010, which 

contained the requirements of this 

amendment. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of May 14, 

2010. 

Comments for inclusion in the Rules 

Docket must be received on or before 

June 28, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• 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 docket that contains the 

AD, any comments, and other 

information 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 Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. 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: On 

February 24, 2010, the FAA issued EAD 

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Federal Register / Vol. 75, No. 82 / Thursday, April 29, 2010 / Rules and Regulations 22511 

2010–05–51 for the ECF Model EC120B 

helicopters. This AD requires, within 

specified intervals, inspecting the rotor 

hub for a crack and removing the 

identification plate and cleaning the 

area. If you find scoring, paint flaking or 

left-over identification plate adhesive, 

the AD requires sanding the area until 

the primer coat becomes visible and 

inspecting the rotor hub for a crack. If 

you find a crack, the AD requires, before 

further flight, replacing the rotor hub 

with an airworthy rotor hub. This 

amendment is prompted by an 

emergency landing due to excessive 

vibrations originating from the main 

rotor. After an investigation, it was 

determined the rotor hub had failed in 

the attachment area of one of the three 

drag damper fittings. This condition, if 

not corrected, could result in failure of 

a hub, excessive vibrations, loss of a 

main rotor blade, and subsequent loss of 

control of the helicopter. 

EASA, the airworthiness authority for 

France, notified the FAA that an unsafe 

condition may exist on these helicopter 

models. EASA advises of an emergency 

landing due to a set of amplitude 

vibrations originating from the main 

rotor. 

ECF has issued Emergency Alert 

Service Bulletin No. 05A012, Revision 

1, dated February 19, 2010 (EASB), 

which specifies inspecting the rotor hub 

for a crack. Also, if you find local 

deterioration (scoring or paint spalling), 

the EASB specifies sanding the area, 

removing the finish paint until the 

primer coat becomes visible, and 

inspecting the area for a crack. If you 

find a crack, the EASB specifies 

replacing the affected rotor hub with a 

new rotor hub. 

EASA classified this service bulletin 

as mandatory and issued AD No. 2010– 

0026–E, dated February 19, 2010, to 

ensure the continued airworthiness of 

these helicopters in France. 

This AD differs from the MCAI AD in 

that we refer to flight hours as time-inservice (TIS). Also, we do not require 

you to contact the manufacturer. 

This helicopter model is 

manufactured in France and is type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement with France, EASA, 

their technical agent, has kept the FAA 

informed of the situation described 

above. The FAA has examined the 

findings of EASA, reviewed all available 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

Since the unsafe condition described 

is likely to exist or develop on other 

ECF Model EC120B helicopters of the 

same type design, the FAA issued EAD 

2010–05–51. The AD requires, at 

specified intervals, inspecting the rotor 

hub for a crack. If you find scoring, 

paint flaking or left-over identification 

plate adhesive, the AD requires sanding 

the area and inspecting the specified 

areas of the rotor hub for a crack. If you 

find a crack, the AD requires, before 

further flight, replacing the rotor hub 

with an airworthy rotor hub. The 

actions must be done by following 

specified portions of the EASB. The 

short compliance time involved is 

required because the previously 

described critical unsafe condition can 

adversely affect the controllability and 

structural integrity of the helicopter. 

Therefore, inspecting the rotor hub for 

a crack is required within 15 hours TIS, 

and if you find a crack, replacing the 

rotor hub with an airworthy rotor hub 

is required before further flight, and this 

AD must be issued immediately. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately by individual 

letters issued on February 24, 2010, to 

all known U.S. owners and operators of 

ECF Model EC120B helicopters. These 

conditions still exist, and the AD is 

hereby published in the Federal 

Register as an amendment to 14 CFR 

39.13 to make it effective to all persons. 

However, we made a minor editorial 

change in paragraph (a) of this AD. We 

added the word, ‘‘Eurocopter’’ in front of 

the words, ‘‘Emergency Alert Service 

Bulletin,’’ which we inadvertently 

omitted in the EAD. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

The FAA estimates that this AD will 

affect 114 helicopters of U.S. registry, 

and inspecting the rotor hub for a crack 

will take a minimal amount of time. It 

will take about 1 hour to do the sanding, 

assuming 37 rotor hubs require sanding. 

It will take about 6 hours to replace a 

rotor hub, assuming 2 helicopters will 

require replacement of a rotor hub. The 

average labor rate is $85 per hour. 

Required parts will cost about $61,685 

per helicopter. Based on these figures, 

we estimate the total cost impact of the 

AD on U.S. operators to be $127,535. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2010–0410; 

Directorate Identifier 2010–SW–024– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light 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 with FAA 

personnel concerning this AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Regulatory Findings 

We have 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 above, I 

certify that the regulation: 

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. See the AD docket to examine 

the economic evaluation. 

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. 

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22512 Federal Register / Vol. 75, No. 82 / Thursday, April 29, 2010 / Rules and Regulations 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2010–05–51 Eurocopter France: 

Amendment 39–16265. Docket No. 

FAA–2010–0410; Directorate Identifier 

2010–SW–024–AD. 

Applicability 

Model EC120B helicopters, with a main 

rotor head with a rotor hub, part number (P/ 

N) C622A1002103, C622A1002104, or 

C622A1002105, installed, certificated in any 

category. 

Compliance 

Required as indicated. 

To prevent failure of a main rotor hub, 

excessive vibrations, loss of a main rotor 

blade, and subsequent loss of control of the 

helicopter, do the following: 

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

unless done previously, and thereafter at 

intervals not to exceed 15 hours TIS, inspect 

the rotor hub for a crack in the areas depicted 

in Figures 1 and 2, areas ‘‘A1’’ and ‘‘A2,’’ of 

Eurocopter Emergency Alert Service Bulletin 

No. 05A012, Revision 1, dated February 19, 

2010 (EASB). If the identification plate ‘‘b’’ 

depicted in Figure 2 of the EASB is in the 

inspection areas ‘‘A1’’ or ‘‘A2,’’ remove the 

plate and clean the area where the 

identification plate information will be 

marked ‘‘B,’’ by following the 

Accomplishment Instructions, paragraph 

2.B.2.a., of the EASB. 

(1) If you find scoring, paint flaking, or leftover identification plate adhesive, sand the 

area using No. 600-grit (fine grit) abrasive 

paper until the primer coat becomes visible 

and inspect the rotor hub for a crack. 

(2) If you find a crack, before further flight, 

replace the rotor hub with an airworthy rotor 

hub. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact 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, for information about 

previously approved alternative methods of 

compliance. 

(c) Special flight permits will not be 

issued. 

(d) The Joint Aircraft System/Component 

(JASC) Code is 6220: Main Rotor Head. 

(e) The inspections shall be done by 

following the specified portions of 

Eurocopter Emergency Alert Service Bulletin 

No. 05A012, Revision 1, dated February 19, 

2010. The Director of the Federal Register 

approved this incorporation by reference in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Copies may be obtained 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. 

Copies may be inspected at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

(f) This amendment becomes effective on 

May 14, 2010, to all persons except those 

persons to whom it was made immediately 

effective by EAD 2010–05–51, issued 

February 24, 2010, which contained the 

requirements of this amendment. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2010–0026–E, dated February 19, 2010. 

Issued in Fort Worth, Texas, on April 12, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–9007 Filed 4–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0124 Directorate 

Identifier 2010–CE–002–AD; Amendment 

39–16274; AD 2010–09–09] 

RIN 2120–AA64 

Airworthiness Directives; Piaggio Aero 

Industries S.p.A. Model PIAGGIO P– 

180 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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 failure of fuel pump sealing, due to 

possible incorrect maintenance procedures 

and subsequent testing, caused a fuel leakage 

into the main landing gear bay. Presence of 

fuel vapours in that zone creates a risk of fire 

due to presence of potential ignition sources 

such as electrical equipment and connectors. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

3, 2010. 

On June 3, 2010, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

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: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4145; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

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