Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations 11003 

Compliance: Within 10 hours time-inservice (TIS), unless accomplished 

previously: 

To prevent fatigue cracking of a yoke, 

failure of the yoke, and subsequent loss of 

control of the helicopter, do the following: 

(a) Review the helicopter records to 

determine all of the helicopter models on 

which the affected yoke has been installed 

since its production and the hours TIS of 

each affected yoke. 

(b) If an affected part-numbered yoke is 

installed or has ever been installed on a 

Model 412CF helicopter or on a Model 412 

or 412EP helicopter with a (BHT–412–SI–62) 

slope landing kit, P/N 412–704–012–101, 

installed, do the following: 

(1) Reidentify the P/N on the existing yoke 

data plate by using a vibrating stylus and 

etching two lines through the last three digits 

of the existing P/N and etching ‘‘137FM’’ 

adjacent to where you etched through the last 

three digits of the original P/N. This converts 

each affected yoke P/N to a new yoke P/N 

412–010–101–137FM. The serial number 

remains the same. 

Note 1: The ‘‘FM’’ P/N suffix denotes a 

field modified part. 

(2) Record the reidentified P/N on the 

applicable component history card or 

equivalent record. 

(c) If you cannot determine all the model 

helicopters on which an affected yoke has 

been installed since its production or 

whether it has ever been installed on a Model 

412 or 412EP helicopter with a (BHT–412– 

SI–62) slope landing kit, P/N 412–704–012– 

101, installed, reidentify the yoke P/N as 

P/N 412–010–101–137FM using a vibrating 

stylus in accordance with paragraph (b)(1) of 

this AD. Record the reidentified P/N on the 

applicable component history card or 

equivalent record. 

(d) For each reidentified yoke, P/N 412– 

010–101–137FM, reduce the retirement life 

from 5,000 hours TIS to 4,500 hours TIS. 

Record the revised life limit on the 

applicable component history card or 

equivalent record. 

Note 2: Bell Helicopter Textron, Inc. Alert 

Service Bulletins No. 412–08–128 and No. 

412CF–08–35, both dated March 4, 2008, 

pertain to the subject of this AD. 

(e) This AD revises the Airworthiness 

Limitations section of the applicable 

maintenance manual or the Instructions for 

Continued Airworthiness (ICAs) by reducing 

the retirement life from 5,000 hours TIS to 

4,500 hours TIS for each reidentified yoke, 

P/N 412–010–101–137FM. 

(f) 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, Rotorcraft 

Directorate, FAA, ATTN: Michael Kohner, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Fort Worth, Texas 

76193–0170, telephone (817) 222–5170, fax 

(817) 222–5783, for information about 

previously approved alternative methods of 

compliance. 

(g) Special flight permits will not be 

issued. 

(h) This amendment becomes effective on 

March 31, 2009. 

Issued in Fort Worth, Texas, on February 

12, 2009. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4950 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–2007–28689; Directorate 

Identifier 2006–SW–17–AD; Amendment 39– 

15832; AD 2009–05–08] 

RIN 2120–AA64 

Airworthiness Directives; Trimble or 

FreeFlight Systems 2101 I/O Approach 

Plus Global Positioning System (GPS) 

Navigation Systems 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Trimble or FreeFlight Systems 2101 I/O 

Approach Plus global positioning 

system (GPS) navigation system (2101 

I/O Approach Plus system) that requires 

a software upgrade for this system. This 

amendment is prompted by an incident 

that led to the discovery of several 

annunciation errors with the 2101 I/O 

Approach Plus system. The actions 

specified by this AD are intended 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. 

DATES: Effective April 20, 2009. 

ADDRESSES: You may get the service 

information identified in this AD from 

FreeFlight Systems, 3700 IH 35, Waco, 

Texas, USA, 76706, or by calling (254) 

662–0000 or on the Internet at http:// 

www.freeflightsystems.com. 

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 at the Docket 

Operations office, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

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. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified 

navigation system was published in the 

Federal Register on July 13, 2007 (72 FR 

38532). That action proposed to require, 

within 180 days after the effective date 

of the AD for aircraft approved for 

instrument flight rule (IFR) flight, or 270 

days after the effective date of the AD 

for aircraft approved for visual flight 

rule (VFR) flight, upgrading the 2101 

I/O Approach Plus system software to 

correct several software errors. 

Freeflight Systems issued Service 

Information Letter (SIL) 81440–XX–00– 

17, dated November 7, 2005, when the 

manufacturer believed that software 

version 241H would correct the 

erroneous information displays. 

However, version 241H did not correct 

all the errors. Therefore, FreeFlight 

Systems issued SIL 81440–XX–00–19, 

dated May 10, 2006, which describes 

the release of new operating system 

software, version 241J, ‘‘that makes 

communication between the Host and 

the GPS processors more robust.’’ 

Freeflight Systems subsequently issued 

Service Bulletin No. SB 81440–XX–00– 

19, dated December 12, 2006, that 

contains the instructions for obtaining 

and upgrading the software to version 

241J. Although the proposed AD 

included a Note referencing SIL 81440– 

XX–00–17, this AD references the most 

recently available service information, 

Service Bulletin No. SB 81440–XX–00– 

19, dated December 12, 2006. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

The commenter, FreeFlight Systems, 

states that ‘‘the proposed AD specifies 

81440–13–XXXX as being applicable for 

this upgrade. The 81440–13–XXXX is a 

number assigned for an NVG (night 

vision goggles) version of the 81440 that 

was never put into production so no 

units exist that would require this 

upgrade. The 81440–13–XXXX was 

included in error in the AD Worksheet 

identifying applicable systems provided 

to the FAA by FreeFlight Systems.’’ 

Therefore, part number (P/N) 81440–13– 

XXXX (where XXXX is –241E, –241F, or 

241G) should be removed from the AD. 

The FAA concurs and has removed 

those P/Ns from the AD. 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. The FAA has 

determined that these changes will 

neither increase the economic burden 

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.