[Federal Register Volume 69, Number 198 (Thursday, October 14, 2004)]
[Rules and Regulations]
[Pages 60949-60952]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-22715]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-56-AD; Amendment 39-13815; AD 2004-20-10]
RIN 2120-AA64


Airworthiness Directives; Valentin GmbH & Co. Taifun 17E 
Sailplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts a new airworthiness directive (AD) for all 
Valentin GmbH & Co. Taifun 17E sailplanes. This AD requires you to do 
an operational check of the front wing-locking mechanism left and 
right, inspect stop key movement, inspect wing and fuselage side root 
ribs, inspect the wing side shear force fittings, and take any 
corrective actions that may be required. 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 malfunction of wing-locking mechanism, which could result 
in failure of the wing-locking mechanism disengagement. This failure 
could lead to unlocking of wing in flight and consequent loss of 
control of the sailplane.

DATES: This AD becomes effective on November 24, 2004.
    As of November 24, 2004, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: You may get the service information identified in this AD 
from KORFF + CO.KG, Dieselstrasse 5, D-63128 Dietzenbach, Germany.
    You may view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2003-CE-56-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Gregory M. Davison, Aerospace 
Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: 816-329-4130; facsimile: 816-
329-4090.

SUPPLEMENTARY INFORMATION:

Discussion

    What events have caused this AD? The Luftfahrt-Bundesamt (LBA), 
which is the airworthiness authority for Germany, recently notified FAA 
that an unsafe condition may exist on all Valentin GmbH & Co. Taifun 
17E sailplanes. The LBA reports that during an investigation, an 
incorrect locked shear force fitting was found.
    What is the potential impact if FAA took no action? Malfunction of 
wing-locking mechanism could result in failure of the wing attachment 
assembly. This failure could lead to unlocking of wing in flight and 
consequent loss of control of the sailplane.
    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 Valentin GmbH & Co. Taifun 17E 
sailplanes. This proposal was published in the Federal Register as a 
notice of proposed

[[Page 60950]]

rulemaking (NPRM) on April 22, 2004 (69 FR 21771). The NPRM proposed to 
require you to do an operational check of the front wing-locking 
mechanism left and right, inspect stop key movement, inspect wing and 
fuselage side root ribs, inspect the wing side shear force fittings, 
and take any corrective actions that may be required.

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 sailplanes does this AD impact? We estimate that this AD 
affects 25 sailplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected sailplanes? We estimate the following costs to accomplish the 
inspections:

----------------------------------------------------------------------------------------------------------------
                                                                                                  Total cost  on
                  Labor cost                               Parts cost             Total cost per       U.S.
                                                                                     sailplane       operators
----------------------------------------------------------------------------------------------------------------
2 work hours x $65 per hour = $130............  No parts needed for inspection..            $130          $3,250
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    We estimate the following costs to accomplish replacement of the 
stop key F1-1300 that will be required based on the results of the 
inspections. We have no way of determining the number of sailplanes 
that may need the stop key F1-1300 replaced or the number of sailplanes 
that may need additional repair because of abrasion. We also do not 
know the cost that will be associated with any abrasion repair:

------------------------------------------------------------------------
                                                            Total cost
           Labor cost                   Parts cost         per sailplane
------------------------------------------------------------------------
3 workhours x $65 per hour =     $16 each x 2 (2 are                $227
 $195.                            required) = $32.
------------------------------------------------------------------------

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 
``AD Docket No. 2003-CE-56-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:

2004-20-10 Valentin GmbH & Co.: Amendment 39-13815; Docket No. 2003-
CE-56-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on November 24, 2004.

What Other ADs Are Affected by This Action?

    (b) None.

What Sailplanes Are Affected by This AD?

    (c) This AD affects the following sailplane models and serial 
numbers that are certificated in any category: Valentin GmbH & Co. 
Taifun 17E, all serial numbers are affected except those where 
Service Bulletin 23-818 has been complied with.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of an incorrectly locked shear force 
fitting, which may have caused wing-locking mechanism disengagement. 
The actions specified in this AD are intended to detect and correct 
malfunction of the wing-locking mechanism, which could result in 
failure of the wing attachment assembly. This failure could lead to 
unlocking of wing in flight and subsequent loss of control of the 
sailplane.

What Must I Do To Address This Problem?

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

[[Page 60951]]



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                 Actions                               Compliance                        Procedures
---------------------------------------------------------------------------------------------------------------
(1) Perform the following actions with     Inspect within 25 hours time-in-   Inspect following the Korff +
 the motor glider rigged..                  service (TIS) after November 24,   CO.KG Service Bulletin SB-KOCO
(i) An operational check of the front       2004 (the effective date of this   03/818, dated December 12, 2002
 wing locking mechanism left and right      AD). Repetitively inspect every    (German LBA approved December
 for damage, deformation, and smooth        25 hours TIS thereafter.           20, 2002).
 operation over full travel range..
(ii) A visual inspection through the
 operation hole on the bottom side of the
 wings, ensure the bolt (item 3 of
 drawing F1-1340) is in the fully locked
 front position. Confirm a fully locked
 position by withdrawal of the signal pin
 (Item 15 and Item 11 of drawing F1-1340)
 into the wing's upper surface and ensure
 the pin is level with that surface.
 While in this full front stop position,
 measure the potential movement of the
 bolt. If residual movement of 2mm or
 greater exists, replace the stop key
 (Item 25 of drawing F1-1340)..
(2) Perform the following actions with     Inspect within 25 hours TIS after  Inspect following the Korff +
 the motor glider derigged.                 November 24, 2004 (the effective   CO.KG Service Bulletin SB-KOCO
(i) An operational check of the front       date of this AD). Repetitively     03/818, dated December 12, 2002
 wing locking mechanism left and right      inspect every 25 hours TIS         (German LBA approved December
 for damage, deformation, and smooth        thereafter.                        20, 2002).
 operation over full travel range..
(ii) A visual inspection of the motor
 glider for stop key movement. You should
 not be able to move the stop key by hand
 more than 2mm backwards in the full
 locked front position..
(3) If deficiencies are found during the   Do corrective actions prior to     Correct, repair, or replace
 inspections required in paragraphs         further flight.                    defective parts following the
 (e)(1) and (e)(2), correct, repair, or                                        Korff + CO.KG Service Bulletin
 replace the defective parts.                                                  SB-KOCO 03/818, dated December
                                                                               12, 2002 (German LBA approved
                                                                               December 20, 2002).
(4) Perform the following inspections,     Inspect within 25 hours TIS after  Inspect following the Korff +
 and if any of the following conditions     November 24, 2004 (the effective   CO.KG Service Bulletin SB-KOCO
 are found, contact the manufacturer at     date of this AD). Repetitively     03/818, dated December 12, 2002
 the address specified in paragraph (g)     inspect every 25 hours TIS         (German LBA approved December
 of this AD for FAA-approved corrective     thereafter. Perform corrective     20, 2002).
 action and perform the corrective          action prior to further flight.
 action. You must send a copy of
 correspondence you send to the
 manufacturer to the FAA at the address
 in paragraph (f).
(i) Inspect the wing side shear force
 fittings for abrasion, deformation, and
 correct screwing to the root rib..
(ii) Inspect the wing and fuselage side
 root ribs for damage (delamination) and
 around all fittings (shear force
 fittings, wing connection studs, wing
 connection bushings, connection to the
 telescopic rods, rear center studs and
 bushings). Inspect for defective bonding
 to the shells as well as defective
 connections to the spar or the wing spar
 box..
(5) When corrective action or maintenance  After corrective action or         Do the operational check
 is done, do an operational check of the    maintenance is done, you must do   following the Korff + CO.KG
 motor glider in the rigged and derigged    the operational check prior to     Service Bulletin SB-KOCO 03/
 configuration.                             further flight.                    818, dated December 12, 2002
                                                                               (German LBA approved December
                                                                               20, 2002).
----------------------------------------------------------------------------------------------------------------


    Note: We recommend that you make the ``Flight Manual'' and 
``Instructions for Continued Airworthiness'' changes that are listed 
under Actions: 5. of Korff + CO.KG Service Bulletin SB-KOCO 03/818, 
dated December 12, 2002 (German LBA approved December 20, 2002).

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, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106. For information on any already approved alternative 
methods of compliance, contact Gregory M. Davison, Aerospace 
Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: 816-329-4130; facsimile: 
816-329-4090.

[[Page 60952]]

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated 
December 12, 2002 (German LBA approved December 20, 2002). 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. You may get a copy from KORFF + CO.KG, 
Dieselstrasse 5, D-63128 Dietzenbach, Germany. You may review copies 
at FAA, Central Region, Office of the Regional Counsel, 901 Locust, 
Room 506, Kansas City, Missouri 64106; 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/code_of_federal_regulations/ibr_locations.html.

Is There Other Information That Relates to This Subject?

    (h) LBA airworthiness directive 2003-051, dated January 29, 
2003; and
    Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated December 
20, 2002, also address the subject of this AD.

    Issued in Kansas City, Missouri, on September 29, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-22715 Filed 10-13-04; 8:45 am]
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