57660 Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 

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 

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: 

2010–19–05 Eurocopter France: 

Amendment 39–16433 ; Docket No. 

FAA–2010–0426; Directorate Identifier 

2009–SW–34–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on October 27, 2010. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model SA–365N1, 

AS–365N2, AS 365 N3, EC 155B, and 

EC155B1 helicopters, with a fenestron tail 

rotor blade (blade), part number 365A12– 

0060–01 or 365A12–0070–00, installed, 

certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD reports 

the separation and loss of a stainless steel 

ring (75 mm in diameter) from a blade sleeve 

resulting in severe, high-frequency 

vibrations, which can lead to damage to the 

fenestron blades, loss of yaw control, and 

subsequent loss of control of the helicopter. 

Actions and Compliance 

(e) Required as indicated: 

(1) For the Model SA–365N1, AS–365N2, 

and AS 365 N3 helicopters, within 50 hours 

time-in-service (TIS), unless done previously, 

and thereafter at intervals not to exceed 10 

hours TIS, inspect each blade of the fenestron 

tail rotor to determine whether there has 

been any outward slippage (toward the 

shroud) of the stainless steel ring that is 

around the sleeve of each blade where the 

blade enters the fenestron hub as depicted in 

Appendix 1 and by following the 

Accomplishment Instructions, paragraph 

2.B.1., of Eurocopter Alert Service Bulletin 

No. 05.00.49, dated March 1, 2006. 

(2) For the Model EC 155B or B1 

helicopters, within 50 hours time-in-service 

(TIS), unless done previously, and thereafter 

at intervals not to exceed 15 hours TIS, 

inspect each blade of the fenestron tail rotor 

to determine whether there has been any 

outward slippage (toward the shroud) of the 

stainless steel ring that is around the sleeve 

of each blade where the blade enters the 

fenestron hub as depicted in Appendix 1 and 

by following paragraph 2.B.1., of Eurocopter 

Alert Service Bulletin No. 05A011, dated 

March 1, 2006. 

(3) If the stainless steel ring has slipped 

outward, before further flight, replace the 

blade with an airworthy blade. 

Differences Between This AD and the MCAI 

AD 

(f) We refer to flying hours as hours timein-service. Also, we use ‘‘inspect’’ rather than 

‘‘check’’ to describe the action to be taken in 

the AD. We use a different initial compliance 

time. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Rotorcraft 

Directorate, Safety Management Group, Attn: 

DOT/FAA Southwest Region, Gary Roach, 

ASW–111, Aviation Safety Engineer, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5130, 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 

(h) European Aviation Safety Agency 

MCAI Airworthiness Directive No. 2006– 

0099, dated April 24, 2006, contains related 

information. 

Joint Aircraft System/Component (JASC) 

Code 

(i) The JASC Code is 6400: Tail Rotor. 

Material Incorporated by Reference 

(j) You must use the specified portions of 

Eurocopter Alert Service Bulletins No. 

05A011 and No. 05.00.49, both dated March 

1, 2006, 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 (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; 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 September 

3, 2010. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–23098 Filed 9–21–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0811; Directorate 

Identifier 2008–NE–41–AD; Amendment 39– 

16429; AD 2010–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation (RRC) AE 3007A Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

RRC AE 3007A series turbofan engines. 

That AD currently requires performing 

an eddy current inspection (ECI) or 

surface wave ultrasonic test (SWUT) 

inspection on each affected highpressure turbine (HPT) wheel. This AD 

requires removing or performing initial 

and repetitive ECIs or SWUT 

inspections on HPT stage 2 wheels for 

cracks. This AD also reduces the 

approved life limits of certain HPT stage 

2 wheels. This AD results from reports 

of cracked HPT stage 2 wheels. We are 

issuing this AD to prevent uncontained 

failure of the HPT stage 2 wheel and 

damage to the airplane. 

DATES: This AD becomes effective 

October 27, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 


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Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 57661 

publications listed in the regulations as 

of October 27, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce Corporation, P.O. Box 420, 

Speed Code U15, Indianapolis, IN 

46206–0420, e-mail: 

indy.pubs.services@rolls-royce.com. 

The Docket Operations office is 

located at Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

FOR FURTHER INFORMATION CONTACT: Kyri 

Zaroyiannis, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

Small Airplane Directorate, FAA, 2300 

E. Devon Ave., Des Plaines, IL 60018; 

e-mail: kyri.zaroyiannis@faa.gov; 

telephone (847) 294–7836; fax (847) 

294–7834. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 by 

superseding AD 2009–08–51, 

Amendment 39–15905 (74 FR 22091, 

May 12, 2009), with a proposed AD. The 

proposed AD applies to RRC AE 3007A 

series turbofan engines. We published 

the proposed AD in the Federal Register 

on February 18, 2010 (75 FR 7209). That 

action proposed to require: 

• Removing from service, any engine 

with certain part number (P/N) HPT 

stage 2 wheels that have a cycles-sincenew (CSN) specified in Table 1 of this 

AD, by the compliance time specified in 

Table 1 of this AD; or 

• Performing an ECI or SWUT 

inspection on certain P/N HPT stage 2 

wheels that have a CSN specified in 

Table 1 of this AD by the compliance 

time specified in Table 1 of this AD; and 

• Performing repetitive ECI or SWUT 

inspections of the HPT stage 2 wheels 

within 3,000 cycles-since-last 

inspection. 

Examining the AD 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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request To Clarify Repetitive 

Inspection Paragraph 

One commenter asks us to clarify 

paragraph (i) of the proposed AD, which 

states ‘‘Thereafter, within 3,000 cycles 

since last inspection, remove the engine 

from service * * *’’ The commenter 

asks if the last inspection means those 

inspections performed to comply with 

ADs 2008–19–51, 2008–26–06 and 

2009–08–51. The commenter feels 

paragraph (i) of the proposed AD is not 

clear. 

We agree. We changed paragraph (i) of 

this AD to ‘‘Thereafter, within 3,000 

cycles-since-last inspection performed 

as a result of this AD or its predecessor 

ADs (Emergency ADs 2008–19–51, AD 

2008–26–06, and 2009–08–51), remove 

the engine from service * * * 

Request To Credit for Work Done to 

Previous Revisions of the Service 

Bulletins 

Four commenters ask us to allow 

credit for initial and repetitive 

inspections performed using previous 

versions of RRC Alert Service Bulletin 

(ASB) AE 3007A–A–72–367, Revision 2, 

dated June 22, 2009, Service Bulletin 

(SB) AE 3007A–72–176, Revision 5, 

dated September 2, 2008; SB AE 3007A– 

72–215, Revision 2, dated September 28, 

2009; SB AE 3007A–72–368, Revision 3, 

dated May 24, 2010; and SB AE 3007A– 

72–369, Revision 2, dated November 5, 

2009. 

We agree. We added paragraph (g)(6) 

to allow credit for initial and repetitive 

inspections performed using earlier 

versions of RRC ASB AE 3007A–A–72– 

367, Revision 2, dated June 22, 2009; SB 

AE 3007A–72–368, Revision 3, dated 

May 24, 2010; and SB AE 3007A–72– 

369, Revision 2, dated November 5, 

2009. We also changed paragraph (l) of 

this AD to state ‘‘For wheels, P/N 

23069438 * * * RRC SB AE 3007A–72– 

176, Revision 5, dated September 2, 

2008, or earlier version; or SB AE 

3007A–72–215, Revision 2, dated 

September 28, 2009, or earlier version, 

remove the wheel before exceeding the 

new, reduced ECLL of 10,000 CSN.’’ 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

1402 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 2 work-hours per engine 

to perform both the ECI and SWUT. The 

average labor rate is $85 per work-hour. 

No parts are required for the inspection. 

We estimate the prorated life lost per 

stage 2 wheel is about $13,177. Based on 

these figures, we estimate the total cost 

of the AD to U.S. operators to be 

$18,712,494. This estimate is exclusive 

of any warranty coverage. 

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, Incorporation by reference, 

Safety. 


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57662 Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 

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 

removing Amendment 39–15905 (74 FR 

22091, May 12, 2009), and by adding a 

new airworthiness directive, 

Amendment 39–16429, to read as 

follows: 

2010–19–01 Rolls-Royce Corporation 

(Formerly Allison Engine Company): 

Amendment 39–16429. Docket No. 

FAA–2009–0811; Directorate Identifier 

2008–NE–41–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 27, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–08–51, 

Amendment 39–15905. 

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (RRC) AE 3007A series turbofan 

engines with high-pressure turbine (HPT) 

stage 2 wheels, part numbers (P/Ns) 

23069438, 23069592, 23074462, 23074644, 

23075345, or 23084520 installed. These 

engines are installed on, but not limited to, 

Empresa Brasileira de Aeronautica S. A. 

(EMBRAER) EMB–135 and EMB–145 

airplanes. 

Unsafe Condition 

(d) This AD results from reports of cracked 

HPT stage 2 wheels. We are issuing this AD 

to prevent uncontained failure of the HPT 

stage 2 wheel and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

HPT Stage 2 Wheels Exempted From the 

Inspection Requirements of This AD 

(f) The following engines are exempt from 

the inspection requirements of this AD: 

(1) All engines with an HPT stage 2 wheel, 

P/N 23084520. 

(2) All engines with an HPT stage 2 wheel, 

P/N 23075345, that has a serial number (S/ 

N) specified in Table 1 of this AD, and 

(3) All engines with an HPT stage 2 wheel, 

P/N 23074462, that has a S/N specified in 

Table 2 of this AD. 

TABLE 1—HPT STAGE 2 WHEEL, P/N 

23075345 BY S/N EXCLUDED FROM

INSPECTION REQUIREMENTS (g) 

THROUGH (i) OF THIS AD 

MM507646 MM508211 MM508319 

MM508144 MM508221 MM508320 

MM508153 MM508241 MM508322 

MM508176 MM508248 MM508337 

MM508186 MM508251 MM508338 

MM508188 MM508264 MM508382 

MM508205 MM508305 MM508387 

MM508208 MM508311 

TABLE 2—HPT STAGE 2 WHEEL, P/N 

23074462 BY S/N EXCLUDED FROM

INSPECTION REQUIREMENTS (g) 

THROUGH (i) OF THIS AD 

MM504890 MM505025 MM505054 

MM504963 MM505034 MM505055 

MM504990 MM505041 MM505056 

MM504995 MM505045 MM505061 

MM505007 MM505046 All ‘MM’ prefix S/Ns 

higher than 

MM505061 

MM505017 MM505048 All S/Ns with 

‘MW’ prefix 

Initial Eddy Current Inspection (ECI) or 

Surface Wave Ultrasonic Testing (SWUT) 

Inspection 

(g) For engines with an HPT stage 2 wheel, 

P/Ns 23069438, 23069592, 23074462, 

23074644, or 23075345, remove the engine 

from service or perform an initial inspection 

of the wheel by the cycle limit specified in 

Table 3 of this AD. Use one of the following 

methods for the inspection: 

(1) For HPT stage 2 wheels that have S/Ns 

listed in Table 4 of this AD, use paragraphs 

2.A. through 2.C.(4) of RRC Alert Service 

Bulletin (ASB) AE 3007A–A–72–367, 

Revision 2 dated June 22, 2009, to inspect the 

wheel. 

(2) For HPT stage 2 wheels that have S/Ns 

not listed in Table 4 of this AD, use 

paragraphs 2.A. through 2.C.(4) of RRC ASB 

AE 3007A–A–72–367, Revision 2, dated June 

22, 2009, or use paragraphs 2.A. through 2.N. 

of RRC Service Bulletin (SB) AE 3007A–72– 

368, Revision 3, dated May 24, 2010; or use 

2.A. through 2.V.(4) of RRC SB AE 3007A– 

72–369, Revision 2, dated November 5, 2009, 

to perform the inspections. 

TABLE 3—COMPLIANCE TIMES FOR ENGINE REMOVAL OR ECI OR SWUT INSPECTION OF THE HPT STAGE 2 WHEELS BY

CYCLES-SINCE-NEW

[CSN] 

For HPT stage 2 wheels with the following CSN on the effective date of 

this AD: 

Remove engine from service or inspect wheel within the following cycles-in-service (CIS) after the effective date of this AD: 

(3) 17,500 or more CSN ........................................................................... Remove engine from service or inspect before next flight. 

(4) 10,000 to 17,499 CSN ........................................................................ 15 CIS. 

(5) 9,999 or fewer CSN ............................................................................ Before accumulating 10,015 CSN. 

Credit for Previous Inspections 

(6) Inspections performed before the 

effective date of this AD using earlier 

versions of RRC ASB AE 3007A–A–72–367 or 

RRC SB AE 3007A–72–368 or RRC SB AE 

3007A–72–369 comply with the 

requirements of paragraphs (g)(1) and (g)(2) 

of this AD. 

TABLE 4—S/NS OF HPT STAGE 2 

WHEELS TO BE INSPECTED BY SB 

AE 3007A–72–367 

[ECI Method Only] 

HPT stage 2 wheels requiring ECI method 

only 

MM119400 MM183796 

MM119480 MM183808 

MM119508 MM183831 

MM155847 MM228730 

MM155907 MM228951 

MM155908 MM503748 

MM183236 MM504004 

MM183362 MM57188 

MM183754 MM57440 

TABLE 4—S/NS OF HPT STAGE 2 

WHEELS TO BE INSPECTED BY SB 

AE 3007A–72–367—Continued 

[ECI Method Only] 

MM183762 MM57480 

Installation Prohibition 

(h) After the effective date of this AD, don’t 

return to service, any HPT stage 2 wheel that 

was installed in any RRC AE 3007A series 

engine that has been removed as a result of 

the inspection requirements of this AD, 

unless the HPT stage 2 wheel was inspected 

as specified in RRC ASB AE 3007A–A–72– 

367, Revision 2, dated June 22, 2009; or RRC 


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SB AE 3007A–72–368, Revision 3, dated May 

24, 2010; or RRC SB AE 3007A–72–369, 

Revision 2, dated November 5, 2009. 

Repetitive Inspection 

(i) Thereafter, within 3,000 cycles-sincelast inspection performed as a result of this 

AD or its predecessor ADs (Emergency ADs 

2008–19–51, AD 2008–26–06, and 2009–08– 

51), remove the engine from service until an 

ECI or SWUT inspection is performed on the 

HPT stage 2 wheel. Use paragraphs 2.A. 

through 2.C.(4) of RRC ASB AE 3007A–A– 

72–367, Revision 2, dated June 22, 2009, or 

use paragraphs 2.A. through 2.N. of RRC SB 

AE 3007A–72–368, Revision 3, dated May 24, 

2010; or use 2.A. through 2.V.(4) of RRC SB 

AE 3007A–72–369, Revision 2, dated 

November 5, 2009, to inspect the wheel. 

New, Reduced Engine Cycle Life Limit and 

Removal From Service 

(j) For HPT stage 2 wheels, P/N 23084520, 

do the following: 

(1) For wheels that have 22,985 CSN or 

more on the effective date of this AD, remove 

the wheel from service within 15 CIS after 

the effective date of this AD. 

(2) Thereafter, remove HPT stage 2 wheels, 

P/N 23084520, before exceeding the new, 

reduced engine cycle life limit (ECLL) of 

23,000 CSN. 

(k) For HPT stage 2 wheels, P/N 23075345 

and 23074644, do the following: 

(1) For wheels that have 19,985 CSN or 

more on the effective date of this AD, remove 

the wheel from service within 15 CIS after 

the effective date of this AD unless paragraph 

(k)(3) of this AD applies. 

(2) Thereafter, remove HPT stage 2 wheels, 

P/N 23075345 and 23074644, before 

exceeding the new, reduced ECLL of 20,000 

CSN. 

(3) For HPT stage 2 wheels, P/N 23075345, 

that have a S/N listed in Table 5 of this AD 

and that have 22,985 CSN or more on the 

effective date of this AD, remove the wheel 

from service within 15 CIS after the effective 

date of this AD. 

(4) Thereafter, for HPT stage 2 wheels, 

P/N 23075345, that have a S/N listed in Table 

5 of this AD, remove the wheel from service 

before exceeding the new, reduced ECLL of 

23,000 CSN. 

TABLE 5—S/NS OF HPT STAGE 2 WHEEL, P/N 23075345, ELIGIBLE TO REMAIN IN SERVICE UNTIL 23,000 CSN 

MM507646 MM508205 MM508251 MM508322 

MM508144 MM508208 MM508264 MM508337 

MM508153 MM508211 MM508305 MM508338 

MM508176 MM508221 MM508311 MM508382 

MM508186 MM508241 MM508319 MM508387 

MM508188 MM508248 MM508320 

(l) For wheels, P/N 23069438, in engines 

that have not complied with RRC SB AE 

3007A–72–176, Revision 5, dated September 

2, 2008, or earlier version; or SB AE 3007A– 

72–215, Revision 2, dated September 28, 

2009, or earlier version, remove the wheel 

before exceeding the new, reduced ECLL of 

10,000 CSN. 

(m) For wheels, P/N 23069438, in engines 

that have complied with RRC SB AE 3007A– 

72–176, Revision 5, dated September 2, 2008, 

or earlier version; or SB AE 3007A–72–215, 

Revision 2, dated September 28, 2009, or 

earlier version; do the following: 

(1) For wheels that have 19,985 CSN or 

more on the effective date of this AD, remove 

the wheel from service within 15 CIS after 

the effective date of this AD. 

(2) Thereafter, remove the wheel from 

service before exceeding the new, reduced 

ECLL of 20,000 CSN. 

Alternative Methods of Compliance 

(n) The Manager, Chicago Aircraft 

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 

(o) Under 14 CFR 39.23, we are limiting the 

special flight permits for this AD by 

restricting the flight to essential flight crew 

only. 

Related Information 

(p) Contact Kyri Zaroyiannis, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, Small Airplane Directorate, FAA, 

2300 E. Devon Ave., Des Plaines, IL 60018; 

e-mail: kyri.zaroyiannis@faa.gov; telephone 

(847) 294–7836; fax (847) 294–7834, for more 

information about this AD. 

Material Incorporated by Reference 

(q) You must use the service information 

specified in Table 6 of this AD to perform the 

inspections required by this AD. The Director 

of the Federal Register approved the 

incorporation by reference of the documents 

listed in Table 6 of this AD in accordance 

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

can get a copy from Rolls-Royce Corporation, 

P.O. Box 420, Indianapolis, IN 46206; 

telephone (317) 230–3774; fax (317) 230– 

8084; e-mail: indy.pubs.services@rollsroyce.com. You may review copies at the 

FAA, New England Region, 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:// 

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

TABLE 6—INCORPORATION BY REFERENCE

Rolls-Royce Corporation Service Information No. Page Revision Date 

Alert Service Bulletin AE 3007A–A–72–367, Total Pages: 8 ........................................ ALL .......................... 2 June 22, 2009. 

Service Bulletin AE 3007A–72–368, Total Pages: 23 ................................................... ALL .......................... 3 May 24, 2010. 

Service Bulletin AE 3007A–72–369, Total Pages: 22 ................................................... ALL .......................... 2 November 5, 2009. 


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57664 Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 

(Only the transmittal letter for Alert 

Service Bulletin (ASB) AE 3007A–A–72–367, 

Revision 2, dated June 22, 2009, identifies 

this service bulletin as an ASB; no other page 

of this document contains this information.) 

Issued in Burlington, Massachusetts, on 

September 1, 2010. 

Robert G. Mann, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–22370 Filed 9–21–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0926; Directorate 

Identifier 2010–CE–024–AD; Amendment 

39–16435; AD 2010–20–01] 

RIN 2120–AA64 

Airworthiness Directives; G ROB– 

WERKE Model G120A Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

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 the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

GROB Aircraft AG has been informed that 

flap ribs P/N 120A–1053 and 120A–1054 

have been found cracked during regular 

maintenance. Structural failure of the ribs 

may cause failure of the middle flap support 

which may lead to flap asymmetry due to 

excessive flap deformation and ultimately 

could result in reducing the controllability of 

the aeroplane. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

October 12, 2010. 

On October 12, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive comments on this 

AD by November 8, 2010. 

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. 

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: Greg 

Davison, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Emergency AD 

No.: 2010–0140, dated July 2, 2010 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

GROB Aircraft AG has been informed that 

flap ribs P/N 120A–1053 and 120A–1054 

have been found cracked during regular 

maintenance. Structural failure of the ribs 

may cause failure of the middle flap support 

which may lead to flap asymmetry due to 

excessive flap deformation and ultimately 

could result in reducing the controllability of 

the aeroplane. 

Pending further investigation on the root 

source for the cracks, including review of the 

original proofs of compliance, temporary 

limitations for flap operations were 

established until terminating action 

development. 

EASA AD 2010–0065–E required a 

repetitive inspection of the RH and LH flap 

ribs. EASA AD 2010–0065–E is superseded 

as a terminating action has been developed 

by Grob Aircraft AG. 

This AD, which supersedes EASA AD 

2010–0065–E retaining its requirements, 

additionally requires accomplishment of 

repair N° 1121–017 and modification N° 

1121–018 for aeroplanes on which cracks 

have been found or accomplishment of 

modification N° 1121–018 only for 

aeroplanes on which no crack has been 

found. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

GROB Aircraft AG has issued Service 

Bulletin No. ASB1121–113/1, dated 

May 18, 2010; Repair Instruction No. 

RI–1121–017, dated April 1, 2010; and 

Repair Instruction No. RI–1121–018, 

dated May 18, 2010. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

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 have also 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. These 

requirements take precedence over 

those copied from the MCAI. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because during regular 

maintenance, cracks have been found in 

the flap ribs. If not corrected, structural 

failure of the ribs may cause failure of 

the middle flap support, which could 

lead to flap asymmetry, due to excessive 


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