Federal Register / Vol. 73, No. 2 / Thursday, January 3, 2008 / Rules and Regulations 395 

per engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $2,269,168. 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

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 airworthiness 

directive: 

2007–26–20 Pratt & Whitney: Amendment 

39–15322. Docket No. FAA–2007–27230; 

Directorate Identifier 2007–NE–04–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 7, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Pratt & Whitney 

PW4164, PW4168, and PW4168A turbofan 

engines with certain low pressure turbine 

(LPT) stage 4 disks, part number (P/N) 

51N404, that have a serial number (S/N) 

listed in the following Table 1, installed. 

These engines are installed on, but not 

limited to, Airbus A330–200 and A330–300 

series airplanes. 

TABLE 1.—AFFECTED LPT STAGE 4 

DISKS BY SERIAL NUMBER

LPT Stage 4 Disk Serial Nos. 

CLDLC01142 

CLDLC01143 

CLDLC01144 

CLDLC01145 

CLDLC01146 

CLDLC01148 

CLDLC01149 

CLDLC01150 

CLDLC01151 

CLDLC01152 

CLDLC01181 

CLDLC01182 

CLDLC01183 

CLDLC01185 

CLDLC01186 

CLDLC01187 

Unsafe Condition 

(d) This AD results from a report of 

improperly manufactured LPT stage 4 disks. 

We are issuing this AD to prevent an 

uncontained engine failure due to low-cycle 

fatigue, which could result in damage to the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed at the 

next piece-part exposure after the effective 

date of this AD or within 7,500 cycles-sincenew, unless the actions have already been 

done. 

Removing the LPT Stage 4 Disk 

(f) Remove from service any LPT stage 4 

disk that has an S/N listed in Table 1 of this 

AD. 

Prohibition Against Installing an Affected 

Disk 

(g) After the effective date of this AD, do 

not install any disk, P/N 51N404, that has an 

S/N listed in Table 1 of this AD or any disk 

removed as specified in paragraph (f) of this 

AD except as allowed by paragraph (h) of this 

AD. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Special Flight Permits 

(i) Under 14 CFR part 39.23, we are 

prohibiting the special flight permits for this 

AD. 

Related Information 

(j) Contact V. Rose Len, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7772; fax (781) 

238–7199, for more information about this 

AD. 

Material Incorporated by Reference 

(k) None. 

Issued in Burlington, Massachusetts, on 

December 20, 2007. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–25505 Filed 1–2–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0379; Directorate 

Identifier 2007–NM–331–AD; Amendment 

39–15318; AD 2007–26–16] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Model 680 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Model 680 airplanes. This AD 

requires inspecting the routing of the aft 

fairing wire bundle assembly for 

adequate separation between the wiring 

and the hydraulic line; inspecting for 

chafing or damage of the wire bundle 


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396 Federal Register / Vol. 73, No. 2 / Thursday, January 3, 2008 / Rules and Regulations 

assembly and for damage to the 

hydraulic line, and doing corrective 

actions if necessary. This AD results 

from an incident report which indicated 

that a hydraulic leak and wire chafing, 

including signs of heat damage, were 

found within the lower tail cone fairing 

area. Similar wire chafing has also been 

found on other airplanes. We are issuing 

this AD to detect and correct wire 

chafing, and inadequate separation of 

the wiring and hydraulic line, which 

could lead to electrical arcing and a 

hydraulic leak and could result in a 

potential source of ignition and 

consequent fire. 

DATES: This AD is effective January 18, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 7, 2008. 

We must receive comments on this 

AD by March 3, 2008. 

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. 

• 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. 

For service information identified in 

this AD, contact Cessna Aircraft Co., 

P.O. Box 7706, Wichita, Kansas 67277. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647–

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Jarrett Larrow, Aerospace Engineer, 

Electrical Systems and Avionics, ACE–

119W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; telephone (316) 

946–4128; fax (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received an incident report which 

indicated that a hydraulic leak and wire 

chafing, including signs of heat damage, 

were found within the lower tail cone 

fairing area on a Cessna Model 680 

airplane. The incident occurred while 

the airplane was on the ground. Wire 

chafing has also been found on other 

airplanes. Chafing of the wiring, and 

inadequate separation of the wiring and 

hydraulic line, could lead to electrical 

arcing and a hydraulic leak and could 

result in a potential source of ignition 

and consequent fire. 

Relevant Service Information 

We reviewed Cessna Alert Service 

Letter ASL680–24–02, dated October 1, 

2007. The service letter describes 

procedures for inspecting the routing of 

the aft fairing wire bundle assembly for 

adequate separation between the wiring 

and the hydraulic line; inspecting for 

chafing or damage of the wire bundle 

assembly and for damage to the 

hydraulic line; and corrective actions if 

necessary. The corrective actions 

include repairing the wiring if any 

damage to the wire bundle is found, 

replacing the hydraulic line if any 

damage is found, and re-routing the 

wire bundle so there is a minimum of 

two inches from the hydraulic line. The 

service letter refers to the Model 680 

wiring diagram and maintenance 

manuals, which contain the procedures 

for doing the corrective actions. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the AD and the 

Service Information.’’

Differences Between the AD and the 

Service Information 

The service information refers only to 

an ‘‘inspection’’ for routing and chafing 

or damage of the wire bundles and 

hydraulic line. We have determined that 

the procedures in the service 

information should be described as a 

‘‘general visual inspection.’’ Note 1 has 

been included in this AD to define this 

type of inspection. 

The Accomplishment Instructions of 

the service information describe 

procedures for completing a 

maintenance transaction report and 

submitting a copy to the manufacturer. 

This AD would not require that action. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA–

2007–0379; Directorate Identifier 2007–

NM–331–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 


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Federal Register / Vol. 73, No. 2 / Thursday, January 3, 2008 / Rules and Regulations 397 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance 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: 

2007–26–16 Cessna Aircraft Company: 

Amendment 39–15318. Docket No. 

FAA–2007–0379; Directorate Identifier 

2007–NM–331–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective January 18, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Cessna Model 680 

airplanes, certificated in any category, serial 

numbers –0001 through –0152 inclusive, 

–0157, and –0158. 

Unsafe Condition 

(d) This AD results from an incident report 

which indicated that a hydraulic leak and 

wire chafing, including signs of heat damage, 

were found within the lower tail cone fairing 

area. Similar wire chafing has also been 

found on other airplanes. We are issuing this 

AD to detect and correct wire chafing, and 

inadequate separation of the wiring and 

hydraulic line, which could lead to electrical 

arcing and a hydraulic leak and could result 

in a potential source of ignition and 

consequent fire. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections/Corrective Actions 

(f) Within 10 days after the effective date 

of this AD: Do a general visual inspection of 

the routing of the aft fairing wire bundle 

assembly for adequate separation between 

the wiring and the hydraulic line, and do a 

general visual inspection for chafing or 

damage of the wire bundle assembly and for 

damage to the hydraulic line; by doing all of 

the actions, including all applicable 

corrective actions, specified in the 

Accomplishment Instructions of Cessna Alert 

Service Letter ASL680–24–02, dated October 

1, 2007; except as provided by paragraph (g) 

of this AD. Do all applicable corrective 

actions before further flight. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Exception to Alert Service Letter 

(g) Although the Accomplishment 

Instructions of Cessna Alert Service Letter 

ASL680–24–02, dated October 1, 2007, 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Electrical Systems and 

Avionics, ACE–119W, FAA, ATTN: Jarrett 

Larrow, Aerospace Engineer, Electrical 

Systems and Avionics, ACE–119W, FAA, 

Wichita Aircraft Certification Office, 1801 

Airport Road, room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; telephone 

(316) 946–4128; fax (316) 946–4107; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Material Incorporated by Reference 

(i) You must use Cessna Alert Service 

Letter ASL680–24–02, dated October 1, 2007, 

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 Cessna Aircraft Co., P.O. Box 

7706, Wichita, Kansas 67277. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington; 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. 

Issued in Renton, Washington, on 

December 20, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 07–6265 Filed 1–2–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0378; Directorate 

Identifier 2007–SW–04–AD; Amendment 39–

15314; AD 2007–26–12] 

RIN 2120–AA64 

Airworthiness Directives; Robinson 

Helicopter Company Models R22, R22 

Alpha, R22 Beta, R22 Mariner, R44 and 

R44 II Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Robinson Helicopter Company 

(Robinson) helicopters. This action 

requires a one-time visual inspection for 

skin separation along the leading edge 

of blade skin aft of the skin-to-spar bond 

line on the lower surface of each blade 

and in the tip cap area. This action also 

requires a ‘‘tap test’’ for detecting a 

separation or void in both bonded areas. 

This action also requires repainting any 

exposed area of the blades. If any 

separation or void is detected, replacing 

the blade before further flight is 


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