10052 Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 

Actions Compliance Procedures 

For each crew seat (pilot and copilot), install 

Modification Kit MK172–25–10C or fabricate 

and install a steel lock rod/bar.

For airplanes that have over 1,000 hours 

time-in-service (TIS) on the effective date of 

this AD: do the action within the next 4 

months after April 11, 2007 (the effective 

date of this AD).

For airplanes that have from 501 to 1,000 

hours TIS on the effective date of this AD: 

do the action within the next 8 months after 

April 11, 2007 (the effective date of this AD).

For airplanes that have from 0 to 500 hours 

TIS on the effective date of this AD: do the 

action within the next 12 months after April 

11, 2007 (the effective date of this AD).

Follow Cessna Single Engine Service Bulletin 

SB04–25–01, Revision 4, dated December 

26, 2006, for installing Modification Kit 

MK172–25–10C. Follow Cessna Single Engine Service Bulletin SB04–25–02, Revision 

1, dated October 17, 2005, or Revision 2, 

dated June 5, 2006, for fabricating and installing a steel lock rod/bar. 

(2) Airplanes that have Modification Kit 

MK172–25–10A or Modification Kit MK172–

25–10B installed: 

Action Compliance Procedures 

(i) For each crew seat (pilot and copilot), do an 

installation inspection.

Within the next 30 days after April 11, 2007 

(the effective date of this AD).

Follow Cessna Single Engine Service Bulletin 

SB04–25–01, Revision 4, dated December 

26, 2006. 

(ii) If you do not find any discrepancies during 

the inspection required in paragraph (e)(2)(i) 

of this AD, make a log book entry showing 

compliance with this AD and no further action 

is required.

Before further flight after the inspection required in paragraph (e)(2)(i) of this AD.Follow Cessna Single Engine Service Bulletin 

SB04–25–01, Revision 4, dated December 

26, 2006. 

(iii) If you find discrepancies during the inspection required in paragraph (e)(2)(i) of this AD, 

make all necessary corrective actions.

Before further flight after the inspection required in paragraph (e)(2)(i) of this AD.Follow Cessna Single Engine Service Bulletin 

SB04–25–01, Revision 4, dated December 

26, 2006. 

Note: Although not required for the 

airplanes affected by this AD, you may 

replace the steel lock rod/bar with 

Modification Kit MK172–25–10C. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office, FAA, ATTN: Gary Park, 

Aerospace Engineer, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209; 

telephone: (316) 946–4123; facsimile: (316) 

946–4107, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Material Incorporated by Reference 

(g) You must use Cessna Single Engine 

Service Bulletin SB04–25–01, Revision 4, 

dated December 26, 2006; and Cessna Single 

Engine Service Bulletin SB04–25–02, 

Revision 1, dated October 17, 2005, or 

Revision 2, dated June 5, 2006, 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 Company, 

Product Support, P.O. Box 7706, Wichita, KS 

67277; telephone: (316) 517–5800; fax: (316) 

942–9006. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; 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 Kansas City, Missouri, on 

February 26, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–3834 Filed 3–6–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26693 Directorate 

Identifier 2006–CE–90–AD; Amendment 39–

14970; AD 2007–05–09] 

RIN 2120–AA64 

Airworthiness Directives; REIMS 

AVIATION S.A. Model F406 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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: 

This AD is issued following a nose landing 

gear collapse during takeoff roll. Several 

expertises proved that the locking device of 

the Nose Landing Gear (NLG) actuator rod 

was on several F406 airplanes not 

conforming with the installation approved by 

the manufacturer. 

There were two different landing gear 

actuator designs installed on the Model 

F406 airplanes (Teijin Seiki and 

Cessna). The actuators used different 

locking devices to retain the spherical 

rod-end to the actuator rod. Use of the 

incorrect locking device could allow the 

spherical rod-end to disconnect from 

the actuator rod. We are issuing this AD 

to require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective April 

11, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 11, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 


sroberts on PROD1PC70 with RULES
Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 10053 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

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 January 8, 2007 (72 FR 672). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

This AD is issued following a nose landing 

gear collapse during takeoff roll. Several 

expertises proved that the locking device of 

the Nose Landing Gear (NLG) actuator rod 

was on several F406 airplanes not 

conforming with the installation approved by 

the manufacturer. 

The MCAI requires: 

As Main Landing Gear (MLG) actuator rod 

locking devices are similar to the NLG ones, 

then MLG actuator locking devices shall also 

be inspected. 

This AD requires inspection of the NLG 

and MLG locking devices and as requested 

their replacement to comply with the 

manufacturer’s approved design. 

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. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are described in a 

separate paragraph of the AD, and take 

precedence over the actions copied from 

the MCAI. 

Costs of Compliance 

We estimate that this AD will affect 7 

products of U.S. registry. We also 

estimate that it will take about 5 workhours per product to comply with this 

AD. The average labor rate is $80 per 

work-hour. Required parts will cost 

about $20 per product. Where the 

service information lists required parts 

costs that are covered under warranty, 

we have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$2,940, or $420 per product. 

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: 

(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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD Docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 the 

NPRM, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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: 

2007–05–09 REIMS AVIATION S.A.: 

Amendment 39–14970; Docket No. 

FAA–2006–26693; Directorate Identifier 

2006–CE–90–AD. 


sroberts on PROD1PC70 with RULES
10054 Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 11, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model F406 

airplanes, all serial numbers, certificated in 

any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states: 

This AD is issued following a nose landing 

gear collapse during takeoff roll. Several 

expertises proved that the locking device of 

the Nose Landing Gear (NLG) actuator rod 

was on several F406 airplanes not 

conforming with the installation approved by 

the manufacturer. 

There were two different landing gear 

actuator designs installed on the Model F406 

airplanes (Teijin Seiki and Cessna). The 

actuators used different locking devices to 

retain the spherical rod-end to the actuator 

rod. Use of the incorrect locking device could 

allow the spherical rod-end to disconnect 

from the actuator rod, and consequently the 

landing gear could collapse. 

Actions and Compliance 

(e) Unless already done, do the following 

actions: 

(1) Within 3 months or 100 hours time-inservice (TIS) after April 11, 2007 (the 

effective date of this AD), whichever occurs 

first: 

(i) For airplanes with Teijin Seiki Nose 

Landing Gear (NLG) P/N 9910139–9: inspect 

the NLG for conformity with the key lock 

system installation description in Figure 1 of 

the REIMS AVIATION INDUSTRIES Service 

Bulletin No. F406–56, dated April 12, 2005; 

(ii) For airplanes with Cessna NLG P/N 

9910139–9: inspect the NLG for conformity 

with the key lock system installation 

description in Figure 2 of the REIMS 

AVIATION INDUSTRIES Service Bulletin 

No. F406–56, dated April 12, 2005; 

(iii) For airplanes with Teijin Seiki Main 

Landing Gear (MLG) P/N 9910136–8: inspect 

the MLG for conformity with the key lock 

system installation description in Figure 3 of 

the REIMS AVIATION INDUSTRIES Service 

Bulletin No. F406–56, dated April 12, 2005; 

and 

(iv) For airplanes with Cessna MLG P/N 

9910136–8: inspect the MLG for conformity 

with the key lock system installation 

description in Figure 4 of the REIMS 

AVIATION INDUSTRIES Service Bulletin 

No. F406–56, dated April 12, 2005. 

(2) Before further flight after any inspection 

from (e)(1) of this AD where the key lock 

system does not conform to the appropriate 

installation description, install a key lock 

system that conforms to the appropriate 

installation description. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Mike Kiesov, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4144; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et. seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to MCAI Direction ge ́ne ́rale de 

l’aviation civile AD No. F–2005–065, dated 

April 27, 2005, for related information. 

Material Incorporated by Reference 

(h) You must use REIMS AVIATION 

INDUSTRIES Service Bulletin No. F406–56, 

dated April 12, 2005, 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 REIMS AVIATION 

INDUSTRIES, Ae ́rodrome de Reims Prunay, 

51360 Prunay, France, A l’attention du 

Support Client; telephone: 03.26.48.46.53; 

fax: 03.26.49.18.57. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; 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 Kansas City, Missouri, on 

February 23, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–3835 Filed 3–6–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27308; Directorate 

Identifier 2007–NE–06–AD; Amendment 39–

14977; AD 2007–05–16] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Aircraft Engines (GE) CF34–

3A1/–3B/–3B1 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: This action supersedes 

emergency airworthiness directive (AD) 

2007–04–51 that was sent previously to 

all known U.S. owners and operators of 

GE CF34–3A1/–3B/–3B1 turbofan 

engines. That action required a onetime 

visual and tactile inspection of certain 

areas of certain serial number (SN) fan 

disks for an arc-out defect, within 20 

engine flight hours after the effective 

date of that AD. This AD supersedes AD 

2007–04–51 and adds eight SNs to the 

list of suspect fan disks. This AD results 

from GE discovering eight additional 

SNs of fan disks suspected of having an 

arc-out defect, and from the original 

report that a GE CF34–3B1 turbofan 

engine experienced an uncontained fan 

disk failure during flight operation. We 

are issuing this AD to prevent an 

uncontained fan disk failure and 

airplane damage. 

DATES: This AD becomes effective 

March 12, 2007. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of March 12, 2007. 

We must receive any comments on 

this AD by May 7, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 


sroberts on PROD1PC70 with RULES