Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12659 

Software Installation for the Autopilot Flight 

Director Computers 

(g) Within 90 days after the effective date 

of this AD, install new operational program 

software in the left, center, and right 

autopilot flight director computers, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–22A0024, dated January 22, 2010. 

Special Flight Permit 

(h) Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: Frank 

van Leynseele, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130S, FAA, 

Seattle Aircraft Certification Office, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6492; fax 

(425) 917–6590. Information may be e-mailed 

to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 777–22A0024, dated January 22, 

2010, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(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 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. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 3, 

2010. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5290 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0663; Directorate 

Identifier 2007–SW–25–AD; Amendment 39– 

16231; AD 2010–06–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS 332 C, L, L1, and L2; 

AS 350 B3; AS355 F, F1, F2, and N; SA 

365N and N1; AS 365 N2 and N3; SA 

366G1; EC 130 B4; and EC 155B and 

B1 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

specified model helicopters. This AD 

results from 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 the AD is issued following a 

manufacturing nonconformity found on 

one batch of the servo-control caps. 

With a defective servo-control, rotation 

of the distributor might not be stopped 

mechanically since only friction of 

inner seals holds the distributor sleeve 

in its position. The AD actions are 

intended to address the unsafe 

condition created by a manufacturing 

nonconformity found on one batch of 

servo-control caps. If not corrected this 

condition could cause untimely 

movements of servo-controls, which are 

used on main and anti-torque rotors, 

and lead to the loss of control of the 

helicopter. 

DATES: This AD becomes effective on 

April 21, 2010. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

April 21, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

regulations.gov or in person at the 

Docket Operations office, U.S. 

Department of Transportation, M–30, 

West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 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 (972) 641–3460, fax (972) 

641–3527, or at http:// 

www.eurocopter.com. 

EXAMINING THE AD DOCKET: The AD 

docket contains the Notice of proposed 

rulemaking (NPRM), the economic 

evaluation, any comments received, and 

other information. The street address 

and operating hours for the Docket 

Operations office (telephone (800) 647– 

5527) are in the ADDRESSES section of 

this AD. Comments will be available in 

the AD docket shortly after they are 

received. 

FOR FURTHER INFORMATION CONTACT: 

Uday Garadi, Aviation Safety Engineer, 

Regulations and Policy Group, FAA, 

Rotorcraft Directorate, Fort Worth, 

Texas 76137, telephone (817) 222–5123, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to the Eurocopter France Model 

AS 332 C, L, L1, and L2; AS 350 B3; 

AS355 F, F1, F2, and N; SA 365N and 

N1; AS 365 N2 and N3; SA 366G1; EC 

130 B4; and EC 155B and B1 helicopters 

on July 14, 2009. That NPRM was 

published in the Federal Register on 

August 3, 2009 (74 FR 38381). That 

NPRM proposed to address the unsafe 

condition created by a manufacturing 

nonconformity found on one batch of 

servo-control caps. If not corrected this 

condition could cause untimely 

movements of servo-controls, which are 

used on main and anti-torque rotors, 

and lead to the loss of control of the 

helicopter. You may obtain further 

information by examining the MCAI AD 

and any related service information in 

the AD docket. 

Comments 

By publishing the NPRM, we gave the 

public an opportunity to participate in 

developing this AD. However, we 

received no comment on the NPRM or 

on our determination of the cost to the 

public. Therefore, based on our review 

and evaluation of the available data, we 

have determined that air safety and the 

public interest require adopting the AD 

as proposed. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
12660 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 

Relevant Service Information 

Eurocopter has issued Alert Service 

Bulletin (ASB) No. 67.00.37 for Model 

AS 332 helicopters, ASB No. 67.00.40 

for Model AS 350 helicopters, ASB No. 

67.00.28 for Model AS 355 helicopters, 

ASB No. 67.00.13 for Model AS 365 and 

SA 365 helicopters, ASB No. 67.08 for 

Model SA 366 helicopters, ASB No. 

67A010 for Model EC 130 helicopters, 

and ASB No. 67A010 for Model EC 155 

helicopters, all Revision 0 and all dated 

February 19, 2007. Two of the ASBs 

have identical numbers and dates. There 

is a separate ASB No. 67A010 with the 

same date for the Model EC130 

helicopter and the Model EC 155 

helicopter. The actions described in the 

MCAI AD are intended to correct the 

same unsafe condition as that identified 

in the service information. 

Differences Between This AD and the 

MCAI AD 

We have reviewed the MCAI AD and 

related service information and, in 

general, agree with their substance. 

However, our AD differs from the MCAI 

AD in that it: 

• Is not applicable to the Model AS 

332 C1 helicopters because they are not 

type certificated in the United States; 

• Does not require returning the 

servo-controls to the manufacturer; 

• Does not address servo-control 

‘‘spares’’ (parts not installed on a 

helicopter); 

• Uses the term ‘‘inspect’’ rather than 

‘‘check’’; and 

• Includes information explaining 

that there are 2 ASBs with the same 

number and date—ASB No. 67A010 for 

the Model EC130 B4 helicopters and 

ASB No. 67A010 for the Model EC 155B 

and B1 helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

about 318 helicopters with 33 nonconforming control cap assemblies of 

U.S. registry. Also, we estimate that it 

would take about 1 work-hour to inspect 

each helicopter in the fleet and 4 workhours per helicopter to remove and 

replace an unairworthy servo-control. 

The average labor rate is $85 per workhour. A replacement cap assembly 

would cost $15,605. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators to be $553,215, or 

$1,740 per helicopter. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

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 AD: 

2010–06–07 Eurocopter France: 

Amendment 39–16231; Docket No. 

FAA–2009–0663; Directorate Identifier 

2007–SW–25–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on April 21, 2010. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Eurocopter France 

(Eurocopter) Model AS 332 C, L, L1, and L2; 

AS 350 B3; AS355 F, F1, F2, and N; SA 365N 

and N1; AS 365 N2 and N3; SA 366G1; EC 

130 B4; and EC 155B and B1 helicopters, 

certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD states 

that the AD is issued following a 

manufacturing nonconformity found on one 

batch of the servo-control cap, part number 

(P/N) 800137. With a defective servo-control, 

rotation of the distributor might not be 

stopped mechanically since only friction of 

inner seals holds the distributor sleeve in its 

position. If not corrected this condition could 

cause untimely movements of servo-controls, 

which are used on main and anti-torque 

rotors, and lead to the loss of control of the 

helicopter. 

Actions and Compliance 

(e) Within 2 months after the effective date 

of this AD, unless already done, do the 

following actions. 

(1) For each servo-control with a P/N and 

a serial number (S/N) listed in paragraph 

1.A.1. of the applicable Eurocopter Alert 

Service Bulletin (ASB) stated in Table 1 of 

this AD, determine whether there is a letter 

‘‘R’’ marked in the inspection box of the 

servo-control identification plate. 

(2) If there is no letter ‘‘R’’ marked in the 

inspection box of a servo-control 

identification plate, on the next removal of 

the servo-control, or not later than 2 years 

after the effective date of this AD, whichever 

occurs first, replace the servo-control with an 

airworthy servo-control that has an ‘‘R’’ 

marked in the inspection box of the servocontrol identification plate or one with a 

serial number not listed in paragraph 1.A.1 

of the ASB applicable to your model 

helicopter. 

Note 1: The letter ‘‘R’’ marked in the 

inspection box of the servo-control 

identification plate indicates that the servocontrol cap assembly has been brought into 

conformity with design data and has been 

installed properly. 

(3) There are 2 identically numbered and 

dated ASBs. There is an ASB No. 67A010, 

dated February 19, 2007, that applies to the 

Model EC130B4 helicopters and an ASB No. 

67A010, dated February 19, 2007, that 

applies to the Model EC 155B and B1 

helicopters. You must use the ASB that 

applies to your model helicopter. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12661 

TABLE 1 

For helicopter model: Refer to paragraph 1.A.1 of ASB: 

AS 332 C, L, L1, and L2 ................................................................................................................. No. 67.00.37, dated February 19, 2007. 

AS 350 B3 ....................................................................................................................................... No. 67.00.40, dated February 19, 2007. 

AS 355 F, F1, F2, and N ................................................................................................................ No. 67.00.28, dated February 19, 2007. 

AS 365 N and N1 ............................................................................................................................ No. 67.00.13, dated February 19, 2007. 

SA 366 G1 ...................................................................................................................................... No. 67.08, dated February 19, 2007. 

EC 130 B4 ....................................................................................................................................... No. 67A010, dated February 19, 2007. 

EC 155B and B1 ............................................................................................................................. No. 67A010, dated February 19, 2007. 

Differences Between This AD and the MCAI 

AD 

(f) This AD differs from the MCAI AD in 

that it: 

(1) Is not applicable to the Model AS 332 

C1 helicopters because they are not type 

certificated in the United States; 

(2) Does not require returning the servocontrols to the manufacturer; 

(3) Does not address servo-control ‘‘spares’’ 

(parts not installed on a helicopter); 

(4) Uses the term ‘‘inspect’’ rather than 

‘‘check’’; and 

(5) Includes information explaining that 

there are 2 ASBs with the same number and 

date. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, 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: Uday Garadi, Aviation 

Safety Engineer, Regulations and Policy 

Group, Rotorcraft Directorate, FAA, Fort 

Worth, Texas 76137, telephone (817) 222– 

5123, fax (817) 222–5961. 

Related Information 

(h) MCAI EASA Airworthiness Directive 

2007–0099, dated April 11, 2007, contains 

related information. 

Joint Aircraft System/Component (JASC) 

Code 

(i) JASC Code 6700: Rotorcraft Flight 

Control. 

Material Incorporated by Reference 

(j) You must use the portions of the service 

information specified in Table 2 to do the 

actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information specified in Table 2 

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 (972) 

641–3460, fax (972) 641–3527, or at http:// 

www.eurocopter.com. 

(3) You may review copies 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. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Eurocopter Alert Service Bulletin Date For helicopter model 

No. 67.00.37 ............................................................................... February 19, 2007 ................................................. AS 332 C, L, L1, and L2. 

No. 67.00.40 ............................................................................... February 19, 2007 ................................................. AS 350 B3. 

No. 67.00.28 ............................................................................... February 19, 2007 ................................................. AS 355 F, F1, F2, and N. 

No. 67.00.13 ............................................................................... February 19, 2007 ................................................. AS 365 N and N1. 

No. 67.08 .................................................................................... February 19, 2007 ................................................. SA 366 G1. 

No. 67A010 ................................................................................ February 19, 2007 ................................................. EC 130 B4. 

No. 67A010 ................................................................................ February 19, 2007 ................................................. EC 155B and B1. 

Issued in Fort Worth, Texas, on February 

18, 2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–5288 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0068; Directorate 

Identifier 2010–NE–05–AD; Amendment 39– 

16240; AD 2010–06–15] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF6–45 and CF6–50 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF6–45 and 

CF6–50 series turbofan engines with 

certain low-pressure turbine (LPT) stage 

3 disks installed. This AD requires 

fluorescent penetrant inspection (FPI) of 

the LPT stage 3 disk under certain 

conditions and removal of the disk from 

service before further flight if found 

cracked. This AD also requires initial 

and repetitive borescope inspections of 

the high-pressure turbine (HPT) rotor 

stage 1 and stage 2 blades for wear and 

damage, including excessive airfoil 

material loss. This AD results from three 

reports of uncontained failures of LPT 

stage 3 disks and eight reports of 

cracked LPT stage 3 disks found during 

shop visit inspections. We are issuing 

this AD to prevent critical life-limited 

rotating engine part failure, which could 

result in an uncontained engine failure 

and damage to the airplane. 

DATES: This AD becomes effective April 

1, 2010. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1