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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Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 57665 

flap deformation, and ultimately reduce 

the controllability of the airplane. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–0926; 

Directorate Identifier 2010–CE–024–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify 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 regulatory 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: 

2010–20–01 GROB-WERKE: Amendment 

39–16435; Docket No. FAA–2010–0926; 

Directorate Identifier 2010–CE–024–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 12, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model G120A 

airplanes, all serial numbers, certificated in 

any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 57: Wings. 

Reason 

(e) 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 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. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Before further flight after October 12, 

2010 (the effective date of this AD), and 

repetitively thereafter before the first flight of 

each day, inspect the right hand (RH) and left 

hand (LH) flap ribs for cracks following 

GROB Aircraft AG Service Bulletin No.: 

ASB1121–113/1, Accomplishment 

Instructions, PART A, dated May 18, 2010. 

(2) If no crack is found during any 

inspection required in paragraph (f)(1) of this 

AD, before further flight, you must comply 

with the following conditions until the 

Repair Instructions in GROB Aircraft AG 

Repair Instruction No. RI–1121–018, dated 

May 18, 2010, are done: 

(i) Reduction of the airplane’s maximum 

flap deflection to the ‘‘TAKE-OFF’’ position 

and reduction of the maximum flaps 

extended speed VFE to 114 knots indicated 

airspeed (KIAS); 

(ii) Modification of the placard part 

number (P/N) 120A–7000.113E to show 

reduced flap deflection of ‘‘TAKE-OFF’’ 

position and maximum flaps extended speed 

VFE of 114 KIAS, and 

(iii) Insertion into the limitations section of 

the airplane flight manual and/or pilots 

operating handbook an amendment showing 

that the Temporary Maximum Flap Position 

is TAKE-OFF and the Maximum Flap 

Extended Speed is 114 KIAS. 

(3) If no crack is found during any 

inspection required in paragraph (f)(1) of this 

AD, within the next 12 months after the 

effective date of this AD, modify the LH and 

RH flap ribs following GROB Aircraft AG 

Repair Instruction No. RI–1121–018, dated 

May 18, 2010 and GROB Aircraft AG Service 

Bulletin No.: ASB1121–113/1, 

Accomplishment Instructions, PART B, dated 

May 18, 2010. 

(4) If a crack is found during any 

inspection required in paragraph (f)(1) of this 

AD, before further flight, repair the 

applicable flap rib(s) following GROB 

Aircraft AG Repair Instruction No. RI–1121– 

017, dated April 1, 2010; GROB Aircraft AG 

Repair Instruction No. RI–1121–018, dated 

May 18, 2010; and GROB Aircraft AG Service 

Bulletin No.: ASB1121–113/1, 

Accomplishment Instructions, PART B, dated 

May 18, 2010. 

(g) You may at any time complete GROB 

Aircraft AG Repair Instruction No. RI–1121– 

017, dated April 1, 2010, and GROB Aircraft 

AG Service Bulletin No. ASB1121–113/1, 


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57666 Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 

Accomplishment Instructions, PART B, dated 

May 18, 2010, to terminate the repetitive 

inspection required in paragraph (f)(1) of this 

AD, and to terminate the conditions required 

by paragraphs (f)(2) of this AD. This repair 

must be done before further flight if cracks 

are found as required in paragraph (f)(4) of 

this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: The MCAI 

allows flight with known cracks for up to 100 

hours time-in-service. FAA policy is to not 

allow further flight with known cracks in 

critical structure. We require that if any 

cracks are found, before further flight, the 

crack must be repaired following the 

applicable GROB service information. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

Attn: Greg Davison, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

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

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

(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 

(i) Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2010–0140, dated 

July 2, 2010; GROB Aircraft AG Repair 

Instruction No. RI–1121–017, dated April 1, 

2010; GROB Aircraft AG Repair Instruction 

No. RI–1121–018, dated May 18, 2010; and 

GROB Aircraft AG Service Bulletin No.: 

ASB1121–113/1, dated May 18, 2010, for 

related information. 

Material Incorporated by Reference 

(j) You must use GROB Aircraft AG Repair 

Instruction No. RI–1121–017, dated April 1, 

2010; GROB Aircraft AG Repair Instruction 

No. RI–1121–018, dated May 18, 2010; and 

GROB Aircraft AG Service Bulletin No.: 

ASB1121–113/1, dated May 18, 2010, 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 GROB Aircraft AG, 

Lettenbachstrasse 9, 86874 TussenhausenMattsies, Germany; telephone: +49 (0) 8268– 

998–0; fax: +49 (0) 8268–998–200; e-mail 

productsupport@grob-aircraft.com; Internet: 

http://www.grob-aircraft.eu/service-andsupport/g-120/documentation/servicebulletins.html. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on 

September 14, 2010. 

William J. Timberlake, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–23377 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–2009–0715; Directorate 

Identifier 2008–NM–211–AD; Amendment 

39–16432; AD 2010–19–04] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–120, –120ER, 

–120FC, –120QC, and –120RT 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

It has been found the occurrence of 

corrosion on the Auxiliary Power Unit (APU) 

mounting rods that could cause the APU rod 

to break, affecting the APU support structure 

integrity. 

* * * * * 

APU support structure failure could 

result in loss of power of the APU and 

possible loss of control of the airplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 27, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 27, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on August 19, 2009 (74 FR 

41805). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

It has been found the occurrence of 

corrosion on the Auxiliary Power Unit (APU) 

mounting rods that could cause the APU rod 

to break, affecting the APU support structure 

integrity. 

* * * * * 

APU support structure failure could 

result in loss of power of the APU and 

possible loss of control of the airplane. 

The required action is doing an external 

detailed inspection for corrosion of the 

APU auxiliary and center mounting rods 

and rod ends, and corrective actions if 

necessary. Corrective actions include 

removing corrosion, applying 

anticorrosive treatment, and replacing 

mounting rods. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 


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