Document ID: FAA-2010-0926-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: GROB-WERKE Model G120A Airplanes
Posted Date: 2010-09-22T04:00Z

[Federal Register: September 22, 2010 (Volume 75, Number 183)]
[Rules and Regulations]               
[Page 57664-57666]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22se10-5]                         

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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.

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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[deg] 
1121-017 and modification N[deg] 1121-018 for aeroplanes on which 
cracks have been found or accomplishment of modification N[deg] 
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

[[Page 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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[deg] 
1121-017 and modification N[deg] 1121-018 for aeroplanes on which 
cracks have been found or accomplishment of modification N[deg] 
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,

[[Page 57666]]

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 Tussenhausen-Mattsies, 
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-and-support/g-120/documentation/service-
bulletins.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]
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