### 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


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

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) HPTstage 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.


### 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 S TAGE 

### 2 W HEEL 

### , P/N

23075345 BY 

### S/N E XCLUDED 

### F ROM 

### I NSPECTION 

### R EQUIREMENTS 

### (g) T HROUGH 

### (i) OF 

### T HIS 

### 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 S TAGE 

### 2 W HEEL 

### , P/N 23074462 BY 

### S/N E XCLUDED 

### F ROM 

### I NSPECTION 

### R EQUIREMENTS 

### (g) T HROUGH 

### (i) OF 

### T HIS 

### AD

MM504890 MM505025 MM505054 MM504963 MM505034 MM505055 MM504990 MM505041 MM505056 MM504995 MM505045 MM505061MM505007 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—C OMPLIANCE 

### T IMES FOR 

### E NGINE 

### R EMOVAL OR 

### ECI OR 

### SWUT I NSPECTION OF THE 

### HPT S TAGE 

### 2 W HEELS BY 

### C YCLES 

### -S INCE 

### -N EW [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 CS N.

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/N S OF 

### HPT S TAGE 

### 2 W HEELS TO BE 

### I NSPECTED 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/N S OF 

### HPT S TAGE 

### 2 W HEELS TO BE 

### I NSPECTED 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


### 57663 Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations

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/N S OF 

### HPT S TAGE 

### 2 W HEEL 

### , P/N 23075345, E LIGIBLE 

### T O 

### R EMAIN IN 

### S ERVICE 

### U NTIL 

### 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—I NCORPORATION BY 

### R EFERENCE

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.


### 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