Airworthiness Directives; DG Flugzeugbau GmbH Models DG-800B and DG-500MB Sailplanes, 76681-76683 [05-24481]

Download as PDF Federal Register / Vol. 70, No. 248 / Wednesday, December 28, 2005 / Rules and Regulations What Is the Unsafe Condition Presented in This AD? MODELS (1) (2) (3) (3) (4) G103 TWIN ASTIR G103 TWIN II G103A TWIN II ACRO G103C TWIN III ACRO G 103 C Twin III SL (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions of this AD are intended to prevent abnormal or 76681 uncontrolled sailplane release due to cracked center of gravity (CG) release hook attachment brackets. This condition could result in reduced or loss of sailplane control. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Replace the center of gravity (CG) release hook attachment brackets with improved design brackets as follows: (i) For Models G103 TWIN ASTIR, G103 TWIN II, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes: install new part number (P/N) 103B–2360.01/1 or 103B–2360.01/2 and P/N 103B– 2360.02/1 or 103B–2360–02/2. (ii) For Models G103 TWIN ASTIR sailplanes: install an additional plate, P/N 103–2360.02 below each attachment bracket. (iii) For Models G103 C TWIN III SL sailplanes: install new P/N 103B–2360.01/2 and P/N 103B–2360.02/2. (2) Do not install any CG release hook attachment bracket that is not a part number referenced in paragraphs (e)(1)(i) and (e)(1)(iii) of this AD, as applicable. For sailplanes previously affected by AD 2004–08–13: Within the next 25 hours timein-service (TIS) after June 4, 2004 (the effective date of AD 2004–08–13), unless already done. For sailplanes not previously affected by AD 2004–08–13: Within the next 25 hours time-in-service (TIS) after February 6, 2006 (the effective date of this AD), unless already done. For Models G103 TWIN ASTIR, G103 TWIN II, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes: Follow Grob Service Bulletin No. MSB315–62, dated January 21, 2002, or Grob Service Bulletin No. MSB315–62/2, dated March 9, 2005. For Model G103 C Twin III SL sailplanes: Follow Grob Service Bulletin No. MSB869– 22, dated January 22, 2002. As of the effective date of this AD ................... Not Applicable. 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 Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; facsimile: (816) 329–4090. rwilkins on PROD1PC63 with RULES Is There Other Information That Relates to This Subject? (g) German AD No. 2002–066, effective date: March 21, 2002, and German AD No. 2002–067, effective date: March 21, 2002, 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 Service Bulletin No. MSB315–62, dated January 21, 2002, Grob Service Bulletin No. MSB315–62/2, dated March 9, 2005, and Grob Service Bulletin No. MSB869–22, dated January 22, 2002, as applicable. (1) On June 4, 2004 (69 FR 21402, April 21, 2004), and in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, the Director of the Federal Register approved the incorporation by reference of Grob Service Bulletin No. MSB315–62, dated January 21, 2002, and Grob Service Bulletin No. MSB869–22, dated January 22, 2002. VerDate Aug<31>2005 16:43 Dec 27, 2005 Jkt 205001 (2) As of February 6, 2006, and in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, the Director of the Federal Register approved the incorporation by reference of Grob Service Bulletin No. MSB315–62/2, dated March 9, 2005. (3) To get a copy of this service information, contact BURKHARDT GROB LUFT–UND RAUMFAHRT GmbH & CO KG, Letenbachstrasse 9, D–86874 TussenhausenMattsies, 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: https://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 https:// dms.dot.gov. The docket number is FAA– 2005–20803; Directorate Identifier 2005–CE– 19–AD. Issued in Kansas City, Missouri, on December 16, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–24480 Filed 12–27–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22206; Directorate Identifier 2005–CE–45–AD; Amendment 39– 14432; AD 2005–26–11] RIN 2120–AA64 Airworthiness Directives; DG Flugzeugbau GmbH Models DG–800B and DG–500MB Sailplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain DG Flugzeugbau GmbH Models DG– 800B and DG–500MB sailplanes. This AD requires you to modify the connection of the starter ring gear to the lower drive belt pulley adapter. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the bolts currently used to connect the starter ring gear to the drive belt pulley adapter from shearing off and the bolt heads falling into the engine compartment. Failure of this connection could render the engine inoperative. Consequently, this failure could lead to loss of control of the sailplane. E:\FR\FM\28DER1.SGM 28DER1 76682 Federal Register / Vol. 70, No. 248 / Wednesday, December 28, 2005 / Rules and Regulations This AD becomes effective on February 7, 2006. As of February 7, 2006, 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 DG-Flugzeugbau, Postbox 41 20, D–76625 Bruchsal, Federal Republic of Germany; telephone: ++49 7257 890; facsimile: ++45 7257 8922; Internet: www.dg-flugzeugbau.de. 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– 0001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2005–22206; Directorate Identifier 2005–CE–45–AD. FOR FURTHER INFORMATION CONTACT: Gregory Davison, Glider Project Manager, ACE–112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; facsimile: (816) 329– 4090. DATES: 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 certain DG Flugzeugbau GmbH Models DG– 800B and DG–500MB sailplanes. The LBA reports that sheared off bolt heads have been found in the engine compartment of approximately 20 of the specified sailplanes. These bolts connect the starter ring gear to the lower drive belt pulley adapter. Failure of this connection could render the engine inoperative. What is the potential impact if FAA took no action? The bolts currently used to connect the starter ring gear to the drive belt pulley adapter may shear off and the bolt heads could fall into the engine compartment. Failure of this connection could render the engine inoperative. Consequently, this failure could lead to 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 certain DG Flugzeugbau GmbH Models DG–800B and DG–500MB sailplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on October 9, 2005 (70 FR 58107). The NPRM proposed to require the modification of the connection of the starter ring gear to the lower drive belt pulley adapter. 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 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. Labor cost How many sailplanes does this AD impact? We estimate that this AD affects 7 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 do this modification: Parts cost 3 work hours × $65 = $195 ......................................................................................................... rwilkins on PROD1PC63 with RULES Authority for This Rulemaking What authority does FAA have for issuing this rulemaking action? 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 VerDate Aug<31>2005 16:43 Dec 27, 2005 Jkt 205001 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 AD. 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; PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 $21 Total cost per sailplane Total cost on U.S. operators $216 $1,512 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 other information as included in the Regulatory Evaluation) 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–2005–22206; Directorate Identifier 2005–CE–45–AD’’ in your request. E:\FR\FM\28DER1.SGM 28DER1 Federal Register / Vol. 70, No. 248 / Wednesday, December 28, 2005 / Rules and Regulations 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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 2005–26–11 DG Flugzeugbau GmbH: Amendment 39–14432; Docket No. FAA–2005–22206; Directorate Identifier 2005–CE–45–AD. 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: 1. The authority citation for part 39 continues to read as follows: I Model Serial Nos. (1) DG–800B .. All serial numbers up to and including 8–260, with the exception of 8–247 and 8– 258; and Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] Model Serial Nos. (2) DG–500MB All serial numbers up to and including 5E220B15, with the exception of 5E190B5. When Does This AD Become Effective? (a) This AD becomes effective on February 7, 2006. 2. FAA amends § 39.13 by adding a new AD to read as follows: I 76683 What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of bolt failure in the connection of the starter ring gear to the drive belt pulley adapter. The bolt heads may shear off and the bolt heads could fall into the engine compartment. The actions specified in this AD are intended to prevent the bolts currently used to connect the starter ring gear to the drive belt pulley adapter from shearing off and the bolt heads falling into the engine compartment. Failure of this connection could render the engine inoperative. Consequently, this failure could lead to loss of control of the sailplane. What Must I Do to Address This Problem? (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Remove the starter ring gear assembly with adapter and lower drive belt pulley. Within 30 days after February 7, 2006 (the effective date of this AD). (2) Modify the connection area where the bolts connect the starter ring gear to the lower drive belt pulley adapter. Within 30 days after February 7, 2006 (the effective date of this AD). (3) Reinstall the starter ring gear assembly with the adapter and lower pulley. Within 30 days after February 7, 2006 (the effective date of this AD). Follow DG-Flugzeugbau GmbH Working Instruction No. 1 for TN 873/30, dated June 9, 2004; and Technical Note No. 873/30 and No. 843/22, approved by LuftfahrtBundesamt (LBA) on June 29, 2004, and approved by European Aviation Safety Agency (EASA) on July 9, 2004. Follow DG-Flugzeugbau GmbH Working Instruction No. 1 for TN 873/30, dated June 9, 2004; and Technical Note No. 873/30 and No. 843/22, approved by LBA on June 29, 2004, and approved by EASA on July 9, 2004. Follow DG-Flugzeugbau GmbH Working Instruction No. 1 for TN 873/30, dated June 9, 2004; and Technical Note No. 873/30 and No. 843/22, approved by LBA on June 29, 2004, and approved by EASA on July 9, 2004. May I Request an Alternative Method of Compliance? rwilkins on PROD1PC63 with RULES (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 Gregory Davison, Glider Project Manager, ACE–112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4130; facsimile: (816) 329–4090. Is There Other Information That Relates to This Subject? (g) LBA Airworthiness Directive D–2004– 347, dated July 2, 2004; DG-Flugzeugbau GmbH Working Instruction No. 1 for TN 873/ 30, dated June 9, 2004; and Technical Note No. 873/30 and No. 843/22, approved by LBA VerDate Aug<31>2005 16:43 Dec 27, 2005 Jkt 205001 on June 29, 2004, and approved by the EASA on July 9, 2004, also address 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 DGFlugzeugbau GmbH Working Instruction No. 1 for TN 873/30, dated June 9, 2004; and Technical Note No. 873/30 and No. 843/22, approved by LBA on June 29, 2004, and approved by the EASA on July 9, 2004. The Director of the Federal Register approved the incorporation by reference of this service information in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact DGFlugzeugbau, Postbox 41 20, D–76625 Bruchsal, Federal Republic of Germany; telephone: ++49 7257 890; facsimile: ++45 7257 8922; e-mail: www.dg-flugzeugbau.de. 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 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 to: https://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 20590–0001 or on the Internet at https:// dms.dot.gov. The docket number is FAA– 2005–22206; Directorate Identifier 2005–CE– 45–AD. Issued in Kansas City, Missouri, on December 16, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–24481 Filed 12–27–05; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\28DER1.SGM 28DER1

Agencies

[Federal Register Volume 70, Number 248 (Wednesday, December 28, 2005)]
[Rules and Regulations]
[Pages 76681-76683]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-24481]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22206; Directorate Identifier 2005-CE-45-AD; 
Amendment 39-14432; AD 2005-26-11]
RIN 2120-AA64


Airworthiness Directives; DG Flugzeugbau GmbH Models DG-800B and 
DG-500MB Sailplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
DG Flugzeugbau GmbH Models DG-800B and DG-500MB sailplanes. This AD 
requires you to modify the connection of the starter ring gear to the 
lower drive belt pulley adapter. This AD results from mandatory 
continuing airworthiness information (MCAI) issued by the airworthiness 
authority for Germany. We are issuing this AD to prevent the bolts 
currently used to connect the starter ring gear to the drive belt 
pulley adapter from shearing off and the bolt heads falling into the 
engine compartment. Failure of this connection could render the engine 
inoperative. Consequently, this failure could lead to loss of control 
of the sailplane.

[[Page 76682]]


DATES: This AD becomes effective on February 7, 2006.
    As of February 7, 2006, 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 DG-Flugzeugbau, Postbox 41 20, D-76625 Bruchsal, Federal 
Republic of Germany; telephone: ++49 7257 890; facsimile: ++45 7257 
8922; Internet: www.dg-flugzeugbau.de.
    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 20590-0001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2005-22206; Directorate 
Identifier 2005-CE-45-AD.

FOR FURTHER INFORMATION CONTACT: Gregory Davison, Glider Project 
Manager, ACE-112, Small Airplane Directorate, 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 certain DG Flugzeugbau GmbH 
Models DG-800B and DG-500MB sailplanes. The LBA reports that sheared 
off bolt heads have been found in the engine compartment of 
approximately 20 of the specified sailplanes. These bolts connect the 
starter ring gear to the lower drive belt pulley adapter. Failure of 
this connection could render the engine inoperative.
    What is the potential impact if FAA took no action? The bolts 
currently used to connect the starter ring gear to the drive belt 
pulley adapter may shear off and the bolt heads could fall into the 
engine compartment. Failure of this connection could render the engine 
inoperative. Consequently, this failure could lead to 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 certain DG Flugzeugbau GmbH Models 
DG-800B and DG-500MB sailplanes. This proposal was published in the 
Federal Register as a notice of proposed rulemaking (NPRM) on October 
9, 2005 (70 FR 58107). The NPRM proposed to require the modification of 
the connection of the starter ring gear to the lower drive belt pulley 
adapter.

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 7 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 do this 
modification:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                           Labor cost                               Parts cost       sailplane    U.S. operators
----------------------------------------------------------------------------------------------------------------
3 work hours x $65 = $195.......................................             $21            $216          $1,512
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
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 AD.

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 
other information as included in the Regulatory Evaluation) 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-2005-22206; Directorate Identifier 2005-CE-45-AD'' in your 
request.

[[Page 76683]]

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:

2005-26-11 DG Flugzeugbau GmbH: Amendment 39-14432; Docket No. FAA-
2005-22206; Directorate Identifier 2005-CE-45-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on February 7, 2006.

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:

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
(1) DG-800B............................  All serial numbers up to and
                                          including 8-260, with the
                                          exception of 8-247 and 8-258;
                                          and
(2) DG-500MB...........................  All serial numbers up to and
                                          including 5E220B15, with the
                                          exception of 5E190B5.
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of bolt failure in the connection of 
the starter ring gear to the drive belt pulley adapter. The bolt 
heads may shear off and the bolt heads could fall into the engine 
compartment. The actions specified in this AD are intended to 
prevent the bolts currently used to connect the starter ring gear to 
the drive belt pulley adapter from shearing off and the bolt heads 
falling into the engine compartment. Failure of this connection 
could render the engine inoperative. Consequently, this failure 
could lead to loss of control of the sailplane.

What Must I Do to Address This Problem?

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Remove the starter ring   Within 30 days after  Follow DG-
 gear assembly with adapter    February 7, 2006      Flugzeugbau GmbH
 and lower drive belt pulley.  (the effective date   Working Instruction
                               of this AD).          No. 1 for TN 873/
                                                     30, dated June 9,
                                                     2004; and Technical
                                                     Note No. 873/30 and
                                                     No. 843/22,
                                                     approved by
                                                     Luftfahrt-Bundesamt
                                                     (LBA) on June 29,
                                                     2004, and approved
                                                     by European
                                                     Aviation Safety
                                                     Agency (EASA) on
                                                     July 9, 2004.
(2) Modify the connection     Within 30 days after  Follow DG-
 area where the bolts          February 7, 2006      Flugzeugbau GmbH
 connect the starter ring      (the effective date   Working Instruction
 gear to the lower drive       of this AD).          No. 1 for TN 873/
 belt pulley adapter.                                30, dated June 9,
                                                     2004; and Technical
                                                     Note No. 873/30 and
                                                     No. 843/22,
                                                     approved by LBA on
                                                     June 29, 2004, and
                                                     approved by EASA on
                                                     July 9, 2004.
(3) Reinstall the starter     Within 30 days after  Follow DG-
 ring gear assembly with the   February 7, 2006      Flugzeugbau GmbH
 adapter and lower pulley.     (the effective date   Working Instruction
                               of this AD).          No. 1 for TN 873/
                                                     30, dated June 9,
                                                     2004; and Technical
                                                     Note No. 873/30 and
                                                     No. 843/22,
                                                     approved by LBA on
                                                     June 29, 2004, and
                                                     approved by EASA on
                                                     July 9, 2004.
------------------------------------------------------------------------

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 Gregory Davison, Glider 
Project Manager, ACE-112, Small Airplane Directorate, 901 Locust, 
Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; 
facsimile: (816) 329-4090.

Is There Other Information That Relates to This Subject?

    (g) LBA Airworthiness Directive D-2004-347, dated July 2, 2004; 
DG-Flugzeugbau GmbH Working Instruction No. 1 for TN 873/30, dated 
June 9, 2004; and Technical Note No. 873/30 and No. 843/22, approved 
by LBA on June 29, 2004, and approved by the EASA on July 9, 2004, 
also address 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 DG-Flugzeugbau GmbH Working Instruction No. 1 for TN 
873/30, dated June 9, 2004; and Technical Note No. 873/30 and No. 
843/22, approved by LBA on June 29, 2004, and approved by the EASA 
on July 9, 2004. The Director of the Federal Register approved the 
incorporation by reference of this service information in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this 
service information, contact DG-Flugzeugbau, Postbox 41 20, D-76625 
Bruchsal, Federal Republic of Germany; telephone: ++49 7257 890; 
facsimile: ++45 7257 8922; e-mail: www.dg-flugzeugbau.de. 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: https://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 20590-0001 or on 
the Internet at https://dms.dot.gov. The docket number is FAA-2005-
22206; Directorate Identifier 2005-CE-45-AD.

    Issued in Kansas City, Missouri, on December 16, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-24481 Filed 12-27-05; 8:45 am]
BILLING CODE 4910-13-P
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