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
Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 10055 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact General Electric Company via 

Lockheed Martin Technology Services, 

10525 Chester Road, Suite C, Cincinnati, 

Ohio 45215, telephone (513) 672–8400, 

fax (513) 672–8422 for the service 

information identified in this AD. 

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: On 

February 16, 2007, the FAA issued 

emergency AD 2007–04–51, that applies 

to GE CF34–3A1/–3B/–3B1 turbofan 

engines. That AD requires a onetime 

visual and tactile inspection of certain 

areas of certain SN fan disks, within 20 

engine flight hours after the effective 

date of that AD. That AD resulted from 

a report that a GE CF34–3B1 turbofan 

engine experienced an uncontained fan 

disk failure during flight operation. 

After landing the airplane, an inspection 

of the GE CF34–3B1 engine showed the 

front section of the engine failed, 

resulting in the fan, forward cowlings, 

and fan reverser departing from the 

engine. The airplane sustained minor 

fuselage damage. A subsequent 

inspection of the recovered segments of 

the fan disk found an electrical arc-out 

defect at the fracture origin site. The fan 

disk was marked using the electrochemical etch marking (ECM) procedure 

during engine assembly. If the ECM 

procedure is performed incorrectly, an 

arc-out defect can occur. This arc-out 

defect, caused during part marking, 

resulted in the uncontained failure. 

This condition, if not corrected, could 

result in an uncontained fan disk failure 

and airplane damage. Since emergency 

AD 2007–04–51 was issued, GE 

discovered eight additional SNs of fan 

disks suspected of having an arc-out 

defect. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of GE Alert Service 

Bulletin (ASB) No. CF34–BJ S/B 72–

A0213, dated February 15, 2007, and 

Revision 1, dated February 27, 2007, 

and GE ASB No. CF34–AL S/B 72–

A0232, dated February 15, 2007, and 

Revision 1, dated February 27, 2007, 

that describe procedures for visual and 

tactile inspection of certain areas of 

certain SN fan disks suspected of having 

an arc-out defect. 

FAA’s Determination and Requirements 

of This AD 

Since the unsafe condition described 

is likely to exist or develop on other 

engines of the same type design, we are 

issuing this AD to supersede emergency 

AD 2007–04–51 and to prevent an 

uncontained fan disk failure and 

airplane damage. This AD requires a 

onetime visual and tactile inspection of 

certain areas of certain SN fan disks for 

an arc-out defect, within 20 engine 

flight hours after the effective date of 

this AD. You must use the service 

information described previously to 

perform the actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists to make the AD 

effective immediately to all known U.S. 

owners and operators of GE CF34–3A1/ 

–3B/–3B1 turbofan engines. We are 

publishing the AD in the Federal 

Register as an amendment to Section 

39.13 of part 39 of the Code of Federal 

Regulations (14 CFR part 39) to make it 

effective to all persons. 

Interim Action 

These actions are interim actions and 

we may take further rulemaking actions 

in the future. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2007–27308; Directorate Identifier 

2007–NE–06–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the DMS Web site, 

anyone can find and read the comments 

in any of our dockets, including the 

name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78) or you may visit 

http://dms.dot.gov. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

(800) 647–5227) is located on the plaza 

level of the Department of 

Transportation Nassif Building at the 

street address stated in ADDRESSES. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

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. 


sroberts on PROD1PC70 with RULES
10056 Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 

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, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Under 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 airworthiness 

directive: 

2007–05–16 General Electric Aircraft 

Engines: Amendment 39–14977. Docket 

No. FAA–2007–27308; Directorate 

Identifier 2007–NE–06–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 12, 2007. 

Affected ADs 

(b) This AD supersedes emergency AD 

2007–04–51. 

Applicability 

(c) This AD applies to General Electric 

Aircraft Engines (GE) CF34–3A1/-3B/-3B1 

turbofan engines that have fan disks with 

serial numbers (SNs) listed in Table 1 of this 

AD. 

TABLE 1.—FAN DISK SNS AND LAST

KNOWN ASSOCIATED ENGINE SERIAL

NUMBER (ESN) 

SN 

(Fan Disk) 

ESN 

(current) 

GEE148JH ................................ 872787 

GEE01629 ................................ 807168 

GEE01888 ................................ 807188 

GEE147MF ............................... 807620 

GEE147NA ............................... 807622 

GEE147V5 ................................ 807624 

GEE147VC ............................... 807625 

GEE148JG ................................ 807633 

GEE145LL ................................ 872526 

GEE145NK ............................... 872545 

GEE1466F ................................ 872563 

GEE1466L ................................ 872568 

GEE146H3 ................................ 872599 

GEE146KD ............................... 872604 

GEE146N7 ................................ 872634 

GEE147N7 ................................ 872705 

GEE147N8 ................................ 872709 

TABLE 1.—FAN DISK SNS AND LAST

KNOWN ASSOCIATED ENGINE SERIAL

NUMBER (ESN)—Continued 

SN 

(Fan Disk) 

ESN 

(current) 

GEE14818 ................................ 872727 

GEE14815 ................................ 872730 

GEE1480J ................................ 872731 

GEE1485J ................................ 872745 

GEE1480F ................................ 872750 

GEE14885 ................................ 872763 

GEE148EJ ................................ 872780 

GEE148FT ................................ 872785 

GEE148ER ............................... 872790 

GEE148PN ............................... 872804 

GEE148RN ............................... 872811 

GEE148TW ............................... 872817 

GEE03675 ................................ SPARE 

GEE148R0 ................................ SPARE 

GEE148VT ................................ 872830 

GEE148WC .............................. 872837 

GEE1F9G6 ............................... 872841 

GEE1F9G8 ............................... 872846 

GEE1F9GA ............................... 872849 

GEE1F9WN .............................. 872857 

GEE1FA22 ................................ 872866 

GEE1FA6H ............................... 872886 

(d) For reference, affected regional jet fan 

disk part numbers (P/Ns) are 5922T01G04, 

5922T01G05, 6078T57G01, 6078T57G02, 

6078T57G03, 6078T57G04, 6078T57G05, and 

6078T57G06. 

(e) For reference, affected business jet fan 

disk P/Ns are 5921T18G01, 5921T18G09, 

5921T18G10, 5921T54G01, 5922T01G02, 

5922T01G04, 5922T01G05, 6020T62G04, 

6020T62G05, 6078T00G01, 6078T57G01, 

6078T57G02, 6078T57G03, 6078T57G04, 

6078T57G05, and 6078T57G06. 

(f) These engines are installed on, but not 

limited to, Bombardier, Inc. CL–600–2B16 

(CL–601–3R Variant), CL–600–2B16 (CL–604 

Variant), and CL–600–2B19 (Regional Jet 

Series 100 and 440) model airplanes. 

Unsafe Condition 

(g) 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. 

Compliance 

(h) You are responsible for having the 

actions required by this AD performed within 

20 engine flight hours after the effective date 

of this AD, unless the actions have already 

been done. 

Inspection of the Fan Disk 

(i) Perform a onetime visual and tactile 

inspection of the bore area on the 39 fan 

disks listed in Table 1 of this AD, that have 

not had a shop-level inspection. 

(j) For regional jet engine models CF34–

3A1/–3B1, use paragraphs 3.A through 

3.B.(2)(h) of the Accomplishment 

Instructions of GE Alert Service Bulletin 

(ASB) No. CF34–AL S/B 72–A0232, Revision 

1, dated February 27, 2007, to do the 

inspections. 

(k) For business jet engine models CF34–

3A1/–3B, use paragraphs 3.A through 

3.B.(2)(h) of the Accomplishment 

Instructions of GE ASB No. CF34–BJ S/B 72–

A0213, Revision 1, dated February 27, 2007, 

to do the inspections. 

Previous Inspection Credit 

(l) Previous inspection credit is allowed: 

(1) For regional jet engine models CF34–

3A1/–3B1, inspected using paragraphs 3.A 

through 3.B.(2)(g) of the Accomplishment 

Instructions of GE ASB No. CF34–AL S/B 72–

A0232, dated February 15, 2007, for the fan 

disk SNs listed in emergency AD 2007–04–

51. 

(2) For business jet engine models CF34–

3A1/–3B, inspected using paragraphs 3.A 

through 3.B.(2)(g) of the Accomplishment 

Instructions of GE ASB No. CF34–BJ S/B 72–

A0213, dated February 15, 2007, for the fan 

disk SNs listed in emergency AD 2007–04–

51. 

(m) Fan disks listed in Table 1 of this AD 

that have already had a full visual inspection, 

eddy current inspection, and fluorescent 

penetrant inspection using GE CF34–3 (BJ) 

Heavy Maintenance Manual SEI–782, Section 

72–21–00, or using GE CF34–3 (RJ) Engine 

Manual SEI–756, Section 72–21–00, are 

considered in compliance with this AD. 

Alternative Methods of Compliance 

(n) 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. 

Related Information 

(o) AD 2006–05–04, dated March 3, 2006, 

also addresses the subject of this AD. GE ASB 

No. CF34–BJ S/B 72–A0088, dated August 

21, 2000, and GE ASB No. CF34–AL S/B 72–

A0103, dated August 4, 2000, pertain to the 

subject of this AD. 

(p) 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. 

Material Incorporated by Reference 

(q) You must use the service information 

specified in Table 2 of this AD to perform the 

actions required by this AD. The Director of 

the Federal Register approved the 

incorporation by reference of the documents 

listed in Table 2 of this AD in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. You 

can get a copy from General Electric 

Company via Lockheed Martin Technology 

Services, 10525 Chester Road, Suite C, 

Cincinnati, Ohio 45215, telephone (513) 672–

8400, fax (513) 672–8422. You may review 

copies at the FAA, New England Region, 

Office of the Regional Counsel, 12 New 

England Executive Park, Burlington, MA; 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:// 


sroberts on PROD1PC70 with RULES
Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 10057 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

TABLE 2.—INCORPORATION BY REFERENCE

GE Aircraft Engines Alert Service Bulletin No. Page Revision Date 

CF34–BJ S/B 72–A0213 ................................................................................. All ......................... Original ................ February 15, 2007. 

Total Pages: 12 

CF34–BJ S/B 72–A0213 ................................................................................. All ......................... 1 ........................... February 27, 2007. 

Total Pages: 13 

CF34–AL S/B 72–A0232 ................................................................................ All ......................... Original ................ February 15, 2007. 

Total Pages: 12 

CF34–AL S/B 72–A0232 ................................................................................ All ......................... 1 ........................... February 27, 2007. 

Total Pages: 13 

Issued in Burlington, Massachusetts, on 

February 28, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–3833 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–2006–26707; Directorate 

Identifier 2006–NM–157–AD; Amendment 

39–14973; AD 2007–05–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 Airplanes and Model A340–200 

and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330 airplanes and 

Model A340–200 and –300 series 

airplanes. This AD requires inspecting 

to determine the part number of certain 

S4- and MZ-type spoiler servo controls 

(SSCs). For certain other airplanes, this 

AD requires inspecting to determine the 

part number of all SSCs. This AD also 

requires replacing any affected SSC with 

a new SSC. This AD results from a new 

load duty cycle defined by the 

manufacturer. Additional fatigue tests 

and calculations done on this basis 

indicated that the spoiler valve 

manifold of the S4-type SSCs, and, on 

certain airplanes, the maintenance cover 

of the MZ-type SSCs, may crack during 

its service life due to pressure impulse 

fatigue. We are issuing this AD to 

prevent fatigue cracking of certain SSCs, 

which could result in hydraulic leakage 

and consequent loss of SSC function 

and loss of the associated hydraulic 

system. These conditions could affect 

all three hydraulic systems, which 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective April 

11, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 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 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Airbus Model A330 

airplanes and Model A340–200 and 

–300 series airplanes. That NPRM was 

published in the Federal Register on 

December 28, 2006 (71 FR 78102). That 

NPRM proposed to require inspecting to 

determine the part number of certain 

S4- and MZ-type spoiler servo-controls 

(SSCs). For certain other airplanes, that 

NPRM proposed to require inspecting to 

determine the part number of all SSCs. 

That NPRM also proposed to require 

replacing any affected SSC with a new 

SSC. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

This AD affects about 27 airplanes of 

U.S. registry. 

It takes about 1 work hour per 

airplane to accomplish the inspection to 

determine the part number, at an 

average labor rate of $80 per work hour. 

Based on these figures, the estimated 

cost of the inspection required by this 

AD for U.S. operators is $2,160, or $80 

per airplane. 

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 


sroberts on PROD1PC70 with RULES