Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Rules and Regulations 61341 

accordance with the procedures specified in 

paragraph (o) of this AD. 

Post-Repair Inspections 

(m) Except as required by paragraph (n) of 

this AD, for airplanes on which the forward 

edge frame of the number 5 main entry door 

cutouts, at station 2231, between stringers 16 

and 31, is repaired in accordance with 

Boeing Alert Service Bulletin 747–53A2450: 

Within 3,000 flight cycles after doing the 

repair or within 1,500 flight cycles after the 

effective date of this AD, whichever occurs 

later, do the detailed, LFEC, and HFEC 

inspections of the repaired area for cracks in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2450, Revision 5, dated January 29, 

2009. If no cracking is found, repeat the 

inspections thereafter at intervals not to 

exceed 3,000 flight cycles. If any crack is 

found, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. Doing the inspections specified in 

paragraph (m) of this AD terminates the 

repetitive inspections required by paragraphs 

(g), (h), (i), (j), and (k) of this AD for the 

repaired area. 

(n) For any frame that is repaired in 

accordance with a method other than the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009, do the inspection in 

accordance with a method approved in 

accordance with the procedures specified in 

paragraph (o) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(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: Ivan Li, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6437; fax (425) 917–6590; Or, e-mail 

information 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2001–16–02, 

amendment 39–12370, are approved as 

AMOCs for the corresponding provisions of 

paragraphs (g), (h), (i), and (l) of this AD. 

Material Incorporated by Reference 

(p) You must use Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009, 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. 

(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 

September 15, 2010. 

Robert D. Breneman, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–23840 Filed 10–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0449; Directorate 

Identifier 2009–SW–38–AD; Amendment 39– 

16456; AD 2010–20–21] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. (Agusta) Model A109E 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Agusta Model A109E 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 after a report of an electrical 

failure, an investigation revealed 

inadequate functioning of the 35 

amperes (Amps) battery bus (BATT 

BUS) circuit breaker that was not within 

design requirements. The actions 

specified in this AD are intended to 

replace the 35 Amps circuit breaker 

with a 50 Amps circuit breaker and 

replace the wires with oversized ones to 

prevent an electrical failure, loss of 

electrical power, and subsequent loss of 

control of the helicopter. 

DATES: This AD becomes effective on 

November 9, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

9, 2010. 

ADDRESSES: You may get the service 

information identified in this AD from 

Agusta, Via Giovanni Agusta, 520 21017 

Cascina Costa di Samarate (VA), Italy, 

telephone 39 0331–229111, fax 39 

0331–229605/222595, or at http:// 

customersupport.agusta.com/ 

technical_advice.php. 

Examining the Docket: You may 

examine the docket that contains this 

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 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, Mark 

Wiley, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Policy Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5114, fax 

(817) 222–5961. 

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 Agusta Model A109E 

helicopters on April 7, 2010. That 

NPRM was published in the Federal 

Register on April 27, 2010 (75 FR 

22043). That NPRM proposed to require 

modifying the fuselage electrical 

installation and the overhead panel 

electrical installation. 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2009– 

0137, dated June 23, 2009, to correct an 


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61342 Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Rules and Regulations 

unsafe condition for the Agusta Model 

A109E helicopters. 

Following a report of an electrical 

failure, Agusta investigated the 

electrical power generation system and 

identified inadequate functioning of the 

35 Amps BATT BUS circuit breaker. To 

prevent an electrical failure, the 

manufacturer has developed a BATT 

BUS circuit breaker modification kit for 

replacing the 35 Amps circuit breaker 

with a 50 Amps circuit breaker and 

replacing the wires with oversized ones. 

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. 

Related Service Information 

Agusta has issued Mandatory 

Bollettino Tecnico No. 109EP–98, dated 

June 22, 2009, that specifies modifying 

the BATT BUS circuit breaker 

installation. The service information 

specifies modifying the fuselage 

electrical installation, part number (P/N) 

109–0741–49, and the overhead panel 

electrical installation, P/N 109–0741– 

55, with a BATT BUS circuit breaker 

modification kit, P/N 109–0824–73–101. 

The actions described in the MCAI AD 

are intended to correct the same unsafe 

condition as that identified in the 

service information. 

FAA’s Evaluation and Unsafe Condition 

Determination 

This model helicopter has been 

approved by the aviation authority of 

Italy and is approved for operation in 

the United States Pursuant to our 

bilateral agreement with Italy, 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 

the same type design. 

Differences Between This AD and the 

MCAI AD 

We refer to flight hours as hours timein-service. Also, we do not refer to a 

calendar compliance date of December 

31, 2009, because the effective date of 

this AD would be later than that date. 

Costs of Compliance 

We estimate that this AD will affect 

about 73 helicopters of U.S. registry. We 

also estimate that it will take about 5 

work-hours per helicopter to modify the 

BAT BUS circuit breaker installation. 

The average labor rate is $85 per workhour. Required parts will cost about 

$700 for the BAT BUS circuit breaker 

kit. Based on these figures, we estimate 

that the cost of this AD on U.S. 

operators is $82,125, assuming the 

entire fleet is modified. 

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 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. 

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. The FAA amends § 39.13 by adding 

the following new AD: 

2020–20–21 Agusta S.p.A.: Amendment 39– 

16456; Docket No. FAA–2010–0449; 

Directorate Identifier 2009–SW–38–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on November 9, 2010. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Agusta Model 

A109E helicopters, all serial numbers up to 

and including serial number (S/N) 11758 

(except S/N 11741, 11754, and 11757) 

modified with a circuit breaker modification 

kit, part number (P/N) 109–0812–04–101, 

–103, –107, or –109; certificated in any 

category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD states 

after a report of an electrical failure, an 

investigation revealed inadequate 

functioning of the 35 amperes (Amps) battery 

bus (BATT BUS) circuit breaker. 

Actions and Compliance 

(e) Within 50 hours time-in-service, unless 

already done, modify the fuselage electrical 

installation, P/N 109–0741–49, and the 

overhead panel electrical installation, P/N 

109–0741–55 with a BATT BUS circuit 

breaker modification kit, P/N 109–0824–73– 

101, as depicted in Figures 1 and 2 and by 

following the Compliance Instructions, 

paragraphs 2 through 20.7, of Agusta 

Mandatory Bollettino Tecnico No. 109EP–98, 

dated June 22, 2009. 

Differences Between This AD and the MCAI 

AD 

(f) We refer to flight hours as hours timein-service. Also, we do not refer to a calendar 

compliance date of December 31, 2009, 

because the effective date of this AD would 

be later than that date. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 


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Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Rules and Regulations 61343 

Group, ATTN: DOT/FAA Southwest Region, 

Mark Wiley, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, 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. 

Related Information 

(h) EASA MCAI AD No. 2009–0137, dated 

June 23, 2009, contains related information. 

Joint Aircraft System/Component (JASC) 

Code 

(i) The JASC Code is 2460: Electrical Power 

Systems. 

Material Incorporated by Reference 

(j) You must use the specified portions of 

Agusta Mandatory Bollettino Tecnico No. 

109EP–98, dated June 22, 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 Agusta, Via Giovanni 

Agusta, 520 21017 Cascina Costa di Samarate 

(VA), Italy, telephone 39 0331–229111, fax 39 

0331–229605/222595, or at http:// 

customersupport.agusta.com/ 

technical_advice.php. 

(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 September 

22, 2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–24723 Filed 10–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0301; Directorate 

Identifier 2009–NE–22–AD; Amendment 39– 

16457; AD 2010–20–22] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (RRD) 

Models Tay 620–15, Tay 650–15, and 

Tay 651–54 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), 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: 

Following a review of operational data of 

the Tay 651–54 engine, it has been found that 

the actual stress levels in the Tay 651–54 

engine High Pressure Compressor (HPC) 

stages 1, 3, 6, 7 and 12 discs were higher than 

those originally assumed and therefore the 

approved lives needed to be reduced. 

We are issuing this AD to prevent HPC 

stages 1, 3, 6, 7, and 12 discs from 

exceeding the approved reduced life 

limits, which could result in an 

uncontained failure of a disc and 

damage to the airplane. 

DATES: This AD becomes effective 

November 9, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

November 9, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: Tara 

Chaidez, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: tara.chaidez@faa.gov; telephone 

(781) 238–7773; fax (781) 238–7199. 

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 

Register on March 25, 2010 (75 FR 

14379). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

Following a review of operational data of 

the Tay 651–54 engine, it has been found that 

the actual stress levels in the Tay 651–54 

engine High Pressure Compressor (HPC) 

stages 1, 3, 6, 7 and 12 discs were higher than 

those originally assumed and therefore the 

approved lives needed to be reduced. 

As Tay 651–54 service run HPC discs may 

be installed on Tay 620–15 and Tay 650–15 

engine models, it is necessary to reduce the 

maximum approved lives of the affected HPC 

disc serial numbers installed on Tay 620–15 

and Tay 650–15 engines as well. 

The approved lives of the affected HPC 

stages 1, 3, 6, 7 and 12 discs specified in this 

Airworthiness Directive supersede the 

approved lives given in the Time Limits 

Manuals, Chapter 05–10–01. 

Exceeding of the approved life limits could 

potentially result in non-contained disc 

failure. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD would affect about 

10 products of U.S. registry. We also 

estimate that it would take about 1 

work-hours per product to comply with 

this AD. The average labor rate is $85 

per work-hour. Required parts would 

cost about $100,000 per product. Based 

on these figures, we estimate the cost of 

the AD on U.S. operators to be 

$1,000,850. 

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 above, I 

certify this AD: 


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