[Federal Register Volume 69, Number 213 (Thursday, November 4, 2004)]
[Rules and Regulations]
[Pages 64251-64253]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-24522]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18030; Directorate Identifier 2004-CE-13-AD; 
Amendment 39-13849; AD 2004-22-21]
RIN 2120-AA64


Airworthiness Directives; GROB-WERKE Model G120A Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts a new airworthiness directive (AD) for all 
GROB-WERKE (GROB) Model G120A airplanes. This AD requires you to 
repetitively inspect visually the area between the vertical stabilizer 
main spar and the nearby vertical stabilizer skin for any disbonding/
crack; repair any disbonding/crack found; and calculate weight and 
balance after any repair. This AD is the result of mandatory continuing 
airworthiness information (MCAI) issued by the airworthiness authority 
for Germany. We are issuing this AD to detect and correct any 
disbonding/crack in the area between the vertical stabilizer main spar 
and nearby stabilizer skin, which could result in possible structural 
failure. This failure could lead to difficulty in airplane flight 
control.

DATES: This AD becomes effective on December 27, 2004.
    As of December 27, 2004, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: To get the service information identified in this AD, 
contact GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 
Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 
8268 998139; facsimile: 011 49 8268 998200. To review this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at NARA, 
go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030.
    To view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-18030.

FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION: 

Discussion

    What events have caused this AD? The Luftfahrt-Bundesamt (LBA), 
which

[[Page 64252]]

is the airworthiness authority for Germany, recently notified FAA that 
an unsafe condition may exist on all GROB Model G120A airplanes. The 
LBA reports that a routine inspection of a Model G120A-I airplane found 
disbonding/cracking in the area between the vertical stabilizer main 
spar and nearby vertical stabilizer skin near the VOR (very high 
frequency omni directional range) antenna. A fleet-wide inspection of 
the Model G120A-I airplane fleet found one other Model G120A-I airplane 
with disbonding/cracking in the same area. The most likely reason for 
the disbonding/cracking was an incorrectly installed antenna support 
bracket, which caused permanent tension on the bonding seam. This 
resulted in disbonding/cracking in the area near the VOR antenna.
    What is the potential impact if FAA took no action? Any disbonding/
crack in the area between the vertical stabilizer main spar and nearby 
stabilizer skin could result in possible structural failure. This 
failure could lead to difficulty in airplane flight control.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to all GROB Model G120A airplanes. This 
proposal was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on July 15, 2004 (69 FR 42360). The NPRM proposed to 
require you to repetitively inspect visually the area between the 
vertical stabilizer main spar and the nearby vertical stabilizer skin 
for any disbonding/crack; repair any disbonding/crack found; and 
calculate weight and balance after any repair.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. We received no 
comments on the proposal or on the determination of the cost to the 
public.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for minor 
editorial corrections. We have determined that these minor corrections:

--Are consistent with the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 6 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to do the 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                   Total cost per
              Labor cost                       Parts cost             airplane      Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.......  Not applicable..........             $65   6 x $65 = $390
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of this proposed inspection. We 
have no way of determining the number of airplanes that may need this 
repair:

------------------------------------------------------------------------
                                                          Total cost per
           Labor cost                  Parts cost            airplane
------------------------------------------------------------------------
20 workhours x $65 per hour =    The manufacturer                $1,300
 $1,300.                          covers under warranty
                                  and will supply any
                                  parts for the new U-
                                  profile assembly
                                  (antenna support
                                  bracket) consisting
                                  of part numbers: 120A-
                                  2363.02; 120A-2364;
                                  and 120A-2365.
------------------------------------------------------------------------

Regulatory Findings

    Will this AD impact various entities? 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.
    Will this AD involve a significant rule or regulatory action? 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 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 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 by 
sending a request to us at the address listed under ADDRESSES. Include 
``Docket No. FAA-2004-18030; Directorate Identifier 2004-CE-13-AD'' in 
your request.

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 Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (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. FAA amends Sec.  39.13 by adding a new AD to read as follows:


[[Page 64253]]


2004-22-21 Grob-Werke: Amendment 39-13849; Docket No. FAA-2004-
18030; Directorate Identifier 2004-CE-13-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on December 27, 2004.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects Model G120A airplanes, all serial numbers, 
that are certificated in any category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Germany. The actions specified in this AD are intended to detect and 
correct any disbonding/crack in the area between the vertical 
stabilizer main spar and nearby stabilizer skin, which could result 
in possible structural failure. This failure could lead to 
difficulty in airplane flight control.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Inspect the area between the  Within the next 50  Follow GROB Luft-
 vertical stabilizer main spar     hours time-in-      und Raumfahrt
 and the nearby vertical           service (TIS)       Service Bulletin
 stabilizer skin for any           after December      No. MSB 1121-049,
 disbonding/crack along the spar/  27, 2004 (the       dated April 20,
 skin contact (both sides of the   effective date of   2004. The
 vertical stabilizer).             this AD), unless    applicable
                                   already done.       airplane
                                   Repetitively        maintenance
                                   inspect             manual also
                                   thereafter at       addresses this
                                   every 50 hours      issue.
                                   TIS.
(2) If any disbonding/crack is    Before further      Follow GROB Luft-
 found during any inspection       flight after any    und Raumfahrt
 required by paragraph (e)(1) of   inspection          Service Bulletin
 this AD:                          required by         No. MSB1121-049,
(i) Get a repair instruction       paragraph (e)(1)    dated April 20,
 from the manufacturer; and.       of this AD where    2004; and any
(ii) Follow this repair            any disbonding/     repair
 instruction..                     crack is found.     instruction
(iii) The repetitive inspections                       obtained from
 of paragraph (e)(1) of this AD                        GROB Luft-und
 are still required after any                          Raumfahrt,
 repair..                                              Lettenbachstrasse
                                                       9, D-86874
                                                       Tussenhausen-
                                                       Mattsies, Federal
                                                       Republic of
                                                       Germany;
                                                       telephone: 011 49
                                                       8268 998139;
                                                       facsimile: 011 49
                                                       8268 998200.
                                                       Obtain approval
                                                       of this repair
                                                       instruction
                                                       through the FAA
                                                       at the address
                                                       specified in
                                                       paragraph (f) of
                                                       this AD. The
                                                       applicable
                                                       airplane
                                                       maintenance
                                                       manual also
                                                       addresses this
                                                       issue.
(3) Calculate weight and balance  Before further      Follow GROB Luft-
 after any repair required by      flight after any    und Raumfahrt
 paragraph (e)(2) of this AD.      repair required     Service Bulletin
                                   by paragraph        No. MSB1121-049,
                                   (e0(2) of this AD.  dated April 20,
                                                       2004. The
                                                       applicable
                                                       airplane
                                                       maintenance
                                                       manual also
                                                       addresses this
                                                       issue.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Standards Office, Small 
Airplane Directorate, FAA. For information on any already approved 
alternative methods of compliance, contact Karl Schletzbaum, 
Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, 
Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; 
facsimile: (816) 329-4090.

Is There Other Information That Relates to This Subject?

    (g) German AD Number D-2004-204, dated April 23, 2004, also 
addresses the subject of this AD.

Does This AD Incorporate Any Material by Reference?

    (h) You must do the actions required by this AD following the 
instructions in GROB Luft-und Raumfahrt Service Bulletin No. 
MSB1121-049, dated April 20, 2004. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To 
get a copy of this service information, contact GROB Luft-und 
Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, 
Federal Republic of Germany; telephone: 011 49 8268 998139; 
facsimile: 011 49 8268 998200. To review copies of this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To 
view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif 
Building, Room PL-401, Washington, DC 20590-001 or on the Internet 
at http://dms.dot.gov. The docket number is FAA-2004-18030.

    Issued in Kansas City, Missouri, on October 27, 2004.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-24522 Filed 11-3-04; 8:45 am]
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