11004 Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 

on any operator nor increase the scope 

of the AD. 

The FAA estimates that this AD will 

affect 259 2101 I/O Approach Plus 

systems installed on aircraft of U.S. 

registry, and the required actions will 

take approximately 2 work hours per 

aircraft to accomplish at an average 

labor rate of $80 per work hour. 

Required parts will cost approximately 

$300 per aircraft. Based on these figures, 

we estimate the total cost impact of the 

AD on U.S. operators to be $72,520, 

assuming one 2101 I/O Approach Plus 

system is installed on each aircraft, the 

manufacturer will provide all $300 in 

parts at no cost, and the only costs for 

these parts will be $120 for shipping 

costs for each unit. 

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. 

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, 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: 

2009–05–08 Trimble or Freeflight Systems: 

Amendment 39–15832. Docket No. 

FAA–2007–28689; Directorate Identifier 

2006–SW–17–AD. 

Applicability 

All aircraft with a Trimble or FreeFlight 

Systems 2101 I/O Approach Plus global 

positioning system (GPS) navigation system 

(2101 I/O Approach Plus system), part 

number 81440–xx–241E, 81440–xx–241F, or 

81440–xx–241G (xx indicates either the 

numbers 02, 03, or 12), with software 

revision –241E, –241F, or 241G, installed, 

certificated in any category. 

Compliance 

Required within 180 days after the 

effective date of this AD for aircraft approved 

for instrument flight rule (IFR) flight, or 270 

days after the effective date of this AD for 

aircraft approved for visual flight rule (VFR) 

flight, unless accomplished previously. 

To prevent a pilot from making an unsafe 

decision based on erroneous information 

provided by the 2101 I/O Approach Plus 

system, which could result in loss of control 

of the aircraft, accomplish the following: 

(a) Upgrade the system software of any 

Trimble or FreeFlight Systems 2101 I/O 

Approach Plus GPS navigation system, part 

number (P/N) 81440–xx–241E, 81440–XX– 

241F, or 81440–xx–241G (xx indicates the 

numbers 02, 03, or 12), that currently has 

software revision –241E, –241F, or –241G, to 

system software revision, P/N 81440–XX– 

241J. 

Note: Sections II and III of FreeFlight 

Systems Service Bulletin No. SB 81440–XX– 

00–19, dated December 12, 2006, pertains to 

the requirements of this AD. 

(b) Upgrading the Trimble or FreeFlight 

Systems 2101 I/O Approach Plus GPS 

Navigation System’s software, to system 

software revision, P/N 81440–xx–241J, is 

considered a terminating action for the 

requirements of this AD. 

(c) 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, Special 

Certification Office, FAA, ATTN: Sung-Hui 

Cavazos, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Special Certification 

Office, Fort Worth, Texas 76193–0190, 

telephone (817) 222–5142, fax (817) 222– 

5785, for information about previously 

approved alternative methods of compliance. 

(d) Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the aircraft to a location where the 

requirements of this AD can be accomplished 

provided that the aircraft is operated under 

VFR only. 

(e) This amendment becomes effective on 

April 20, 2009. 

Issued in Fort Worth, Texas, on February 

19, 2009. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4942 Filed 3–13–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0195; Directorate 

Identifier 2007–SW–34–AD; Amendment 39– 

15837; AD 2009–06–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model EC 155B and EC155B1 

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 

Eurocopter France (Eurocopter) Model 

EC 155B and EC155B1 helicopters. This 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community. The MCAI states 

that ‘‘the Airworthiness Directive (AD) 

is prompted by the discovery of a short 

circuit evidence in hoist connector ‘‘24 

Delta’’ even though the hoist was 

removed from the rotorcraft. The short 

circuit generated sufficient heat to ignite 

the paint on the cooler support cowling 

near the hoist cut-off connector ‘‘24 

Delta.’’ This condition, if not corrected, 

could result in a fire in this area which 

could propagate to surrounding zones.’’ 

This AD requires actions that are 

intended to address this unsafe 

condition. 

Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 11005 

DATES: This AD becomes effective on 

March 31, 2009. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

March 31, 2009. 

We must receive comments on this 

AD by May 15, 2009. 

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 (972) 641–3460, fax (972) 

641–3527, 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: 

George Schwab, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Regulations and Policy Group, Fort 

Worth, Texas 76193–0111, telephone 

(817) 222–5114, fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Emergency AD No. 2007–0159–E, dated 

June 6, 2007, to correct an unsafe 

condition for Eurocopter Model EC 

155B and EC155B1 helicopters. 

This AD requires actions that are 

intended to detect a short circuit in a 

hoist connector and prevent a fire in the 

aircraft. You may obtain further 

information by examining the MCAI and 

any related service information in the 

AD docket. 

Related Service Information 

Eurocopter has issued Emergency 

Alert Service Bulletin No. 25A085, 

dated June 1, 2007. The actions 

described in the MCAI are intended to 

correct the same unsafe condition as 

that identified in the service 

information. 

FAA’s Evaluation and Unsafe Condition 

Determination 

This product 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, their Technical 

Agent has notified us of the unsafe 

condition described in the MCAI. We 

are issuing this AD because we 

evaluated all information provided by 

EASA on behalf of France 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 

We have used a compliance time of 1 

month rather than 3 months because of 

the serious consequences of an 

undetected short circuit and potential 

aircraft fire. 

Costs of Compliance 

We estimate that this AD will affect 1 

helicopter of U.S. registry. We also 

estimate that it will take about 3 workhours to comply with the basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $500 per 

helicopter. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators will be $740. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. We find that the risk to the flying 

public justifies waiving notice and 

comment prior to adoption of this rule 

because a wiring short circuit near the 

hoist cut-off connector caused the paint 

on the cooler support cowling to catch 

on fire. 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–2009–0195; 

Directorate Identifier 2007–SW–34–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 

11006 Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 

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: 

2009–06–01 Eurocopter France: 

Amendment 39–15837. Docket No. 

FAA–2009–0195; Directorate Identifier 

2007–SW–34–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on March 31, 2009. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model EC 155B and 

EC155B1 helicopters with a serial number (S/ 

N) less than 6763, and with optional 

equipment OP 45C07 (OP 45C07), installed, 

certificated in any category. OP 45C07 is the 

helicopter provision kit (electrical and 

structural mount modifications) used to 

support installation and operation of a hoist. 

(1) To determine if your helicopter has OP 

45C07 installed, review aircraft 

documentation, which should state if OP 

45C07 equipment is installed, or 

(2) Perform a physical inspection for the 

existence of the 24 Delta hoist electrical 

female connector (MIL–C–5015 type 

connector), which is installed, just forward of 

the right-hand engine cowling and just below 

the right engine inlet. Figures 1 and 6 of 

Eurocopter Emergency Alert Service Bulletin 

No. 25A085, dated June 1, 2007 (ASB), depict 

where the connector is located. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

‘‘the Airworthiness Directive (AD) is 

prompted by the discovery of a short circuit 

evidence in hoist connector ‘‘24 Delta’’ even 

though the hoist was removed from the 

rotorcraft. The short circuit generated 

sufficient heat to ignite the paint on the 

cooler support cowling near the hoist cut-off 

connector ‘‘24 Delta.’’ This condition, if not 

corrected, could result in a fire in this area 

which could propagate to surrounding 

zones.’’ This AD requires actions that are 

intended to address this unsafe condition. 

Actions and Compliance 

(e) Within 7 days, unless already 

accomplished, do the following: 

(1) Determine the orientation of the fixed 

connector ‘‘24 Delta’’ and if the large contacts 

are not oriented ‘‘aft,’’ re-orient the fixed 

connector so that they are facing ‘‘aft’’ by 

following the Accomplishment Instructions, 

paragraphs 2.B.1. and 2.B.2.a., of the ASB. 

(2) Immediately after each hoist removal 

until the electrical bonding braid for the 

fixed hoist connector ‘‘24 Delta’’ is installed, 

disconnect the hoist power cable by 

following the Accomplishment Instructions, 

paragraph 2.B.2.b., of the ASB. 

(f) Within 1 month, install an electrical 

bonding braid for connector ‘‘24 Delta’’ by 

following the Accomplishment Instructions, 

paragraph 2.B.2.c., of the ASB. 

(g) Factory-implemented modification 

MOD 0745C82 is acceptable terminating 

action for the requirements of this AD. 

Differences Between This AD and the MCAI 

(h) We have used a compliance time of 1 

month rather than 3 months because of the 

serious consequences of an undetected short 

circuit and potential aircraft fire. 

Other Information 

(i) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, FAA, ATTN: George Schwab, 

Aerospace Engineer, Rotorcraft Directorate, 

Regulations and Policy Group, Fort Worth, 

Texas 76193–0111, 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 

(j) Mandatory Continuing Airworthiness 

Information (MCAI) Emergency 

Airworthiness Directive No. 2007–0159–E, 

dated June 6, 2007, contains related 

information. 

Air Transport Association of America (ATA) 

Tracking Code 

(k) ATA Code 25: 2500–Hoist box; 1420– 

Hoist cut-off connector. 

Material Incorporated by Reference 

(l) You must use the specified portions of 

Eurocopter Emergency Alert Service Bulletin 

No. 25A085, dated June 1, 2007, 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 (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. 

Issued in Fort Worth, Texas on February 

19, 2009. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4953 Filed 3–13–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0215; Directorate 

Identifier 2007–NM–278–AD; Amendment 

39–15850; AD 2009–06–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A321–131 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A321–131 airplanes. This 

AD requires repetitive ultrasonic 

inspections to detect cracks in the wing 

inner rear spars at the attachment holes 

of the Main Landing Gear (MLG) 

forward pintle fitting, the actuator 

cylinder anchorage fitting, and rib 5 

fitting; and repair of the sealant or repair 

of any crack. This AD results from a 

finding that certain A321–131 airplanes 

may not reach the design life goal due 

to differences in thickness of the inner 

rear spars and that fatigue cracks may 

develop on inner rear spars starting 

from the fastener holes for the 

attachment of gear rib 5, the forward 

pintle fitting, and the actuating cylinder 

anchorage on these airplanes. We are 

issuing this AD to detect and correct 

such fatigue cracks, which could result 

in reduced structural integrity of the 

airplane. 

DATES: This AD becomes effective 

March 31, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 31, 2009. 

We must receive comments on this 

AD by April 15, 2009. 

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 comments.