Airworthiness Directives; GROB-WERKE GMBH & CO KG Model G102 ASTIR CS Sailplanes, 32484-32487 [E6-8712]

Download as PDF 32484 Federal Register / Vol. 71, No. 108 / Tuesday, June 6, 2006 / Proposed Rules recipients of Departmental financial assistance; * * * * * 7 CFR part 3407—CSREES procedures to implement the National Environmental Policy Act; * * * * * Dated: May 31, 2006. Colien Hefferan, Administrator, Cooperative State Research, Education, and Extension Service. [FR Doc. E6–8704 Filed 6–5–06; 8:45 am] BILLING CODE 3410–22–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24253; Directorate Identifier 2006–CE–23–AD] RIN 2120–AA64 Airworthiness Directives; GROB– WERKE GMBH & CO KG Model G102 ASTIR CS Sailplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 84–09–05, which applies to certain GROB–WERKE GMBH & CO KG (previously identified as BURKHART–GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS sailplanes. AD 84–09–05 requires you to install a modified spherical locking bolt and nut in the forward horizontal stabilizer connection to the vertical stabilizer and install new locking pins in the aft connecting plate for the horizontal stabilizer. Since we issued AD 84–09–05, fatigue cracks were found in the modified spherical locking bolt. Consequently, this proposed AD would require you to replace the modified spherical locking bolt, the retaining pins (collar bolts), and associated hardware; add a life limit on the spherical locking bolt and the retaining pins; and repetitively inspect the front and rear horizontal stabilizer attachment. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are proposing this AD to prevent cracks in the spherical locking bolt, which could result in failure of the horizontal stabilizer connection. This failure could lead to loss of control. DATES: We must receive comments on this proposed AD by June 29, 2006. rwilkins on PROD1PC63 with PROPOSAL SUMMARY: VerDate Aug<31>2005 16:48 Jun 05, 2006 Jkt 208001 Use one of the following addresses to comment on this proposed AD: • DOT Docket Web site: Go to http:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact GROB Luftund Raumfahrt, Lettenbachstrasse 9, D– 86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; fax: 011 49 8268 998200; e-mail: productsupport@grobaerospace.de. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Gregory A. Davison, Aerospace Engineer, ACE–112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; facsimile: (816) 329– 4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2006–24253; Directorate Identifier 2006–CE–23–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion A broken spherical locking bolt in the horizontal stabilizer attachment on a GROB–WERKE GMBH & CO KG (GROB) (previously identified as BURKHART– PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS sailplane caused us to issue AD 84–09–05, Amendment 39–4849. AD 84–09–05 requires the following for certain Model G102 ASTIR CS sailplanes: • Installing a modified spherical locking bolt and nut in the forward horizontal stabilizer connection to the vertical stabilizer; and • Installing new locking pins in the aft connecting plate for the horizontal stabilizer. The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, notified the FAA of the need to supersede AD 84–09–05 to address an unsafe condition that may exist or could develop on GROB Model G102 ASTIR CS sailplanes. The LBA reports an incident of the modified spherical locking bolt found broken on one of the affected sailplanes after landing. Investigation revealed that fatigue, resulting from alternating stress on the stabilizer during unsymmetrical loading, caused the spherical locking bolt to crack. This condition, if not corrected, could result in failure of the horizontal stabilizer connection. This failure could lead to loss of control. Relevant Service Information We have reviewed GROB Service Bulletin MSB306–38/1, dated November 28, 2005, and GROB Service Bulletin MSB306–38, dated February 12, 2004. These service bulletins specify doing the following: • Removing and replacing the spherical locking bolt with a new bolt, part number (P/N) 102–3500.21; • Removing and replacing all retaining pins (collar bolts) on the Tplate with new retaining pins, P/N 102– 2142.46; • Incorporating Revision 9 into the Maintenance Manual (which may be downloaded at http://www.GrobAerospace.de/); • Adding a life limit to the new spherical locking bolt and retaining pins; and • Inspecting (repetitively) the front and rear horizontal stabilizer attachment assembly after the initial replacements. Foreign Airworthiness Authority Information The LBA classified this service bulletin as mandatory and issued German AD Number D–2004–168, dated March 23, 2004, to ensure the continued airworthiness of these sailplanes in Germany. These GROB Model G102 ASTIR CS sailplanes are manufactured in Germany E:\FR\FM\06JNP1.SGM 06JNP1 32485 Federal Register / Vol. 71, No. 108 / Tuesday, June 6, 2006 / Proposed Rules and are type-certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the LBA has kept us informed of the situation described above. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we have examined the LBA’s findings, evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design that are certificated for operation in the United States. This proposed AD would supersede AD 84–09–05 with a new AD that would require you to do the following: • Remove the existing spherical locking bolt, nut, retaining pins (collar bolts), self-locking nut, and the lock washer; and replace with a new spherical locking bolt, P/N 102–3500.21, that has revision letter ‘‘b’’ permanently marked on the bottom of the bolt, a new nut, P/N 102–3510.21, new retaining pins (collar bolts), P/N 102–2142.46, a new self-locking nut, P/N LN9348–M8, and a new lock washer, P/N DIN 6797– 10,5PHR. • Add a life limit on the new spherical locking bolt and the retaining pins; and • Inspect (repetitively) the front and rear horizontal stabilizer attachment assembly after the initial replacements. Labor cost Differences Between This Proposed AD and the Service Information The service information specifies using a 20X magnifying glass for doing the inspections. This proposed AD specifies using a dye penetrant method and a 10X magnifying glass for doing the inspections. This difference is because 20X magnifiers are not readily available in the field. The requirements of this proposed AD, if adopted as a final rule, would take precedence over the provisions in the service information. Costs of Compliance We estimate that this proposed AD would affect 56 sailplanes in the U.S. registry. We estimate the following costs to do the proposed replacements: Parts cost 2 workhours × $80 per hour = $160 ............................................................................................ Total cost for each sailplane Total cost on U.S. operators $413 $23,128 Total cost for each sailplane Total cost on U.S. operators $160 $8,960 $253 We estimate the following costs to do each proposed inspection: Labor cost Parts cost 2 workhours × $80 per hour = $160 ............................................................................................ Not Applicable Authority for This Rulemaking rwilkins on PROD1PC63 with PROPOSAL 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 have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the VerDate Aug<31>2005 16:48 Jun 05, 2006 Jkt 208001 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 the proposed regulation: 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. (800) 647–5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Examining the AD Docket You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone § 39.13 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 84–09–05, Amendment 39–4849, and adding the following new AD: GROB–WERKE GMBH & CO KG (previously identified as BURKHART–GROB FLUGZEUGBAU INDUSTRIESTRABE): Docket No. FAA–2006–24253; Directorate Identifier 2006–CE–23–AD. E:\FR\FM\06JNP1.SGM 06JNP1 32486 Federal Register / Vol. 71, No. 108 / Tuesday, June 6, 2006 / Proposed Rules Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by June 29, 2006. Applicability (c) This AD affects Model G102 ASTIR CS sailplanes, serial numbers 1001 through 1536, that are certificated in any category. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Affected ADs (b) This AD supersedes AD 84–09–05, Amendment 39–4849. Germany. We are issuing this AD to prevent cracks in the spherical locking bolt, which could result in failure of the horizontal stabilizer connection. This failure could lead to loss of control. Compliance (e) To address this problem, you must do the following: rwilkins on PROD1PC63 with PROPOSAL Actions Compliance Procedures (1) Remove and replace as follows: (i) Remove the existing retaining pins (collar bolts) and the self-locking nut and replace with new retaining pins, part numbers (P/N) 102–2142.46, and self-locking nut, P/N LN9348–M8 (or FAA-approved equivalent part numbers), on the T-plate; (ii) Remove the existing spherical locking bolt and replace with a new spherical locking bolt, P/N 102–3500.21, that has revision letter ‘‘b’’ permanently marked on the bottom of the bolt (or FAA-approved equivalent part number ). Return all replaced spherical locking bolts to Grob Systems, Inc., Aircraft Division, 1070 Navajo Drive, Bluffton, Ohio 45817; (iii) Remove the existing nut and replace with a new nut, P/N 102–3510.21 (or FAA-approved equivalent part number); and (iv) Remove the existing lock washer and replace with a new lock washer, P/N DIN 6796–10,5PHR (or FAA-approved equivalent part number). (2) Repetitively inspect the front and rear horizontal stabilizer attachment assembly using a dye-penetrant method along with a minimum 10X magnifying glass for excessive movement, cracks, and/or damage in the spherical locking bolt. This inspection method takes precedence over the procedures outlined in GROB Service Bulletin MSB306–38, dated February 12, 2004. (3) If, during any inspection required in paragraph (e)(2) of this AD, you find excessive movement: (i) In the front horizontal stabilizer attachment, you must replace the spherical locking bolt with a new part. (ii) In the rear horizontal stabilizer attachment, you must replace the retaining pins with new parts. (iii) In the front and rear horizontal stabilizer attachment after doing the replacement(s) required in paragraph (e)(3)(i) and (e)(3)(ii) of this AD, you must replace the bearing in the stabilizer spar web. (4) If, during any inspection required in paragraph (e)(2) of this AD, you do not find excessive movement in the front and rear horizontal stabilizer attachment: (i) Inspect the spherical locking bolt for cracks and damage using a dye-penetrant method along with a minimum 10X magnifying glass. (ii) If you find cracks or damage on the spherical locking bolt, during the inspection required in paragraph (e)(4)(i) of this AD, you must replace the bolt with a new bolt. Within the next 90 days after the effective date of this AD, unless already done. After doing the replacements, the spherical locking bolt and retaining pins have a life limit of 10 years and must be replaced at that time. As specified in GROB Service Bulletin MSB306–38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306–38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005. Initially inspect within the next 100 hours timein-service (TIS) or at the next annual inspection after the replacement required in paragraph (e)(1) of this AD, whichever occurs first. Repetitively inspect thereafter at 12-month intervals or at intervals not to exceed 100 hours TIS, whichever occurs first. As specified in GROB Service Bulletin MSB306–38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306–38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005. Before further flight after each inspection required in paragraph (e)(2) of this AD. After each replacement, the spherical locking bolt and the retaining pins have a life limit of 10 years and must be replaced at that time. As specified in GROB Service Bulletin MSB306–38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306–38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005. Before further flight after each inspection required in paragraph (e)(2) of this AD. After each replacement, the spherical locking bolt and the retaining pins have a life limit of 10 year and must be replaced at that time. As specified in GROB Service Bulletin MSB306–38/1, dated November 28, 2005, following the Accomplishment Instructions in GROB Service Bulletin MSB306–38, dated February 12, 2004, and the Annual Inspection procedures on pages 7 and 8 of the Astir CS Maintenance Manual, Rev. 9, dated Nov. 2005. VerDate Aug<31>2005 17:59 Jun 05, 2006 Jkt 208001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\06JNP1.SGM 06JNP1 Federal Register / Vol. 71, No. 108 / Tuesday, June 6, 2006 / Proposed Rules Actions Compliance (5) Do not install any spherical locking bolt, P/N 102–3500.21 (or FAA-approved equivalent part number), that does not have revision letter ‘‘b’’ permanently marked on the bottom of the bolt. (6) 14 CFR 21.303 allows for replacement parts through parts manufacturer approval (PMA). The phrase ‘‘or FAA-approved equivalent part number’’ in this AD is intended to signify those parts that are PMA parts approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD. As of the effective date of this AD ................... Not applicable. Not Applicable .................................................. Procedures Not Applicable. Note: During ground handling, it has been noted that a tendency exists for the ground crew to move these gliders by using the horizontal stabilizer as a lifting point. This practice may facilitate damage to the stabilizer assembly and should be avoided. See Caution note in GROB Service Bulletin MSB306–38, dated February 12, 2004. DEPARTMENT OF TRANSPORTATION Alternative Methods of Compliance (AMOCs) RIN 2120–AA64 (f) The Manager, Standards Office, Small Airplane Directorate, FAA, ATTN: Gregory A. Davison, Aerospace Engineer, ACE–112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; facsimile: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 84–09–05 are not approved for this AD. Related Information (h) German AD Number D–2004–168, dated March 23, 2004, also addresses the subject of this AD. To get copies of the documents referenced in this AD, contact GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D–86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; fax: 011 49 8268 998200; e-mail: productsupport@grob-aerospace.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, or on the Internet at http://dms.dot.gov. The docket number is Docket No. FAA–2006–24253; Directorate Identifier 2006–CE–23–AD. rwilkins on PROD1PC63 with PROPOSAL 32487 Issued in Kansas City, Missouri, on May 30, 2006. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–8712 Filed 6–5–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 16:48 Jun 05, 2006 Jkt 208001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24951; Directorate Identifier 2005–NM–184–AD] Airworthiness Directives; Gulfstream Model GV and GV–SP Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Gulfstream Model GV and GV– SP series airplanes. This proposed AD would require repairing the force link assembly wire harness. This proposed AD results from a report indicating that the wiring harness outer shield and insulation on the primary conductors may have been inadvertently cut due to an improper method used to remove the wiring outer jacket. We are proposing this AD to prevent the loss of the hardover prevention system (HOPS) in the roll axis due to a short circuit in the wiring harness, which could result in reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by July 21, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, Georgia 31402–2206, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Darby Mirocha, Aerospace Engineer, Systems and Equipment Branch, ACE– 119A, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone (770) 703–6095; fax (770) 703–6097. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–24951; Directorate Identifier 2005–NM–184–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date E:\FR\FM\06JNP1.SGM 06JNP1

Agencies

[Federal Register Volume 71, Number 108 (Tuesday, June 6, 2006)]
[Proposed Rules]
[Pages 32484-32487]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-8712]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24253; Directorate Identifier 2006-CE-23-AD]
RIN 2120-AA64


Airworthiness Directives; GROB-WERKE GMBH & CO KG Model G102 
ASTIR CS Sailplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 84-09-05, 
which applies to certain GROB-WERKE GMBH & CO KG (previously identified 
as BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS 
sailplanes. AD 84-09-05 requires you to install a modified spherical 
locking bolt and nut in the forward horizontal stabilizer connection to 
the vertical stabilizer and install new locking pins in the aft 
connecting plate for the horizontal stabilizer. Since we issued AD 84-
09-05, fatigue cracks were found in the modified spherical locking 
bolt. Consequently, this proposed AD would require you to replace the 
modified spherical locking bolt, the retaining pins (collar bolts), and 
associated hardware; add a life limit on the spherical locking bolt and 
the retaining pins; and repetitively inspect the front and rear 
horizontal stabilizer attachment. This proposed AD results from 
mandatory continuing airworthiness information (MCAI) issued by the 
airworthiness authority for Germany. We are proposing this AD to 
prevent cracks in the spherical locking bolt, which could result in 
failure of the horizontal stabilizer connection. This failure could 
lead to loss of control.

DATES: We must receive comments on this proposed AD by June 29, 2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-
Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; 
fax: 011 49 8268 998200; e-mail: productsupport@grob-aerospace.de.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-24253; Directorate Identifier 2006-CE-23-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    A broken spherical locking bolt in the horizontal stabilizer 
attachment on a GROB-WERKE GMBH & CO KG (GROB) (previously identified 
as BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE) Model G102 ASTIR CS 
sailplane caused us to issue AD 84-09-05, Amendment 39-4849. AD 84-09-
05 requires the following for certain Model G102 ASTIR CS sailplanes:
     Installing a modified spherical locking bolt and nut in 
the forward horizontal stabilizer connection to the vertical 
stabilizer; and
     Installing new locking pins in the aft connecting plate 
for the horizontal stabilizer.
    The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority 
for Germany, notified the FAA of the need to supersede AD 84-09-05 to 
address an unsafe condition that may exist or could develop on GROB 
Model G102 ASTIR CS sailplanes.
    The LBA reports an incident of the modified spherical locking bolt 
found broken on one of the affected sailplanes after landing.
    Investigation revealed that fatigue, resulting from alternating 
stress on the stabilizer during unsymmetrical loading, caused the 
spherical locking bolt to crack.
    This condition, if not corrected, could result in failure of the 
horizontal stabilizer connection. This failure could lead to loss of 
control.

Relevant Service Information

    We have reviewed GROB Service Bulletin MSB306-38/1, dated November 
28, 2005, and GROB Service Bulletin MSB306-38, dated February 12, 2004. 
These service bulletins specify doing the following:
     Removing and replacing the spherical locking bolt with a 
new bolt, part number (P/N) 102-3500.21;
     Removing and replacing all retaining pins (collar bolts) 
on the T-plate with new retaining pins, P/N 102-2142.46;
     Incorporating Revision 9 into the Maintenance Manual 
(which may be downloaded at http://www.Grob-Aerospace.de/);
     Adding a life limit to the new spherical locking bolt and 
retaining pins; and
     Inspecting (repetitively) the front and rear horizontal 
stabilizer attachment assembly after the initial replacements.

Foreign Airworthiness Authority Information

    The LBA classified this service bulletin as mandatory and issued 
German AD Number D-2004-168, dated March 23, 2004, to ensure the 
continued airworthiness of these sailplanes in Germany.
    These GROB Model G102 ASTIR CS sailplanes are manufactured in 
Germany

[[Page 32485]]

and are type-certificated for operation in the United States under the 
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 
21.29) and the applicable bilateral airworthiness agreement.
    Under this bilateral airworthiness agreement, the LBA has kept us 
informed of the situation described above.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we have examined the LBA's 
findings, evaluated all information and determined the unsafe condition 
described previously is likely to exist or develop on other products of 
the same type design that are certificated for operation in the United 
States.
    This proposed AD would supersede AD 84-09-05 with a new AD that 
would require you to do the following:
     Remove the existing spherical locking bolt, nut, retaining 
pins (collar bolts), self-locking nut, and the lock washer; and replace 
with a new spherical locking bolt, P/N 102-3500.21, that has revision 
letter ``b'' permanently marked on the bottom of the bolt, a new nut, 
P/N 102-3510.21, new retaining pins (collar bolts), P/N 102-2142.46, a 
new self-locking nut, P/N LN9348-M8, and a new lock washer, P/N DIN 
6797-10,5PHR.
     Add a life limit on the new spherical locking bolt and the 
retaining pins; and
     Inspect (repetitively) the front and rear horizontal 
stabilizer attachment assembly after the initial replacements.

Differences Between This Proposed AD and the Service Information

    The service information specifies using a 20X magnifying glass for 
doing the inspections. This proposed AD specifies using a dye penetrant 
method and a 10X magnifying glass for doing the inspections. This 
difference is because 20X magnifiers are not readily available in the 
field.
    The requirements of this proposed AD, if adopted as a final rule, 
would take precedence over the provisions in the service information.

Costs of Compliance

    We estimate that this proposed AD would affect 56 sailplanes in the 
U.S. registry.
    We estimate the following costs to do the proposed replacements:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost for   Total cost on
                           Labor cost                               Parts cost    each sailplane  U.S. operators
----------------------------------------------------------------------------------------------------------------
2 workhours x $80 per hour = $160...............................            $253            $413         $23,128
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do each proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost for   Total cost on
                           Labor cost                               Parts cost    each sailplane  U.S. operators
----------------------------------------------------------------------------------------------------------------
2 workhours x $80 per hour = $160...............................  Not Applicable            $160          $8,960
----------------------------------------------------------------------------------------------------------------

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 have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at http://dms.dot.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5227) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 84-09-05, Amendment 39-4849, and adding the following new AD:

GROB-WERKE GMBH & CO KG (previously identified as BURKHART-GROB 
FLUGZEUGBAU INDUSTRIESTRABE): Docket No. FAA-2006-24253; Directorate 
Identifier 2006-CE-23-AD.

[[Page 32486]]

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by June 29, 2006.

Affected ADs

    (b) This AD supersedes AD 84-09-05, Amendment 39-4849.

Applicability

    (c) This AD affects Model G102 ASTIR CS sailplanes, serial 
numbers 1001 through 1536, that are certificated in any category.

Unsafe Condition

    (d) This AD results from mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Germany. We are issuing this AD to prevent cracks in the spherical 
locking bolt, which could result in failure of the horizontal 
stabilizer connection. This failure could lead to loss of control.

Compliance

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Remove and replace as     Within the next 90    As specified in GROB
 follows:                      days after the        Service Bulletin
 (i) Remove the existing       effective date of     MSB306-38/1, dated
 retaining pins (collar        this AD, unless       November 28, 2005,
 bolts) and the self-locking   already done. After   following the
 nut and replace with new      doing the             Accomplishment
 retaining pins, part          replacements, the     Instructions in
 numbers (P/N) 102-2142.46,    spherical locking     GROB Service
 and self-locking nut, P/N     bolt and retaining    Bulletin MSB306-38,
 LN9348-M8 (or FAA-approved    pins have a life      dated February 12,
 equivalent part numbers),     limit of 10 years     2004, and the
 on the T-plate;               and must be           Annual Inspection
 (ii) Remove the existing      replaced at that      procedures on pages
 spherical locking bolt and    time.                 7 and 8 of the
 replace with a new                                  Astir CS
 spherical locking bolt, P/N                         Maintenance Manual,
 102-3500.21, that has                               Rev. 9, dated Nov.
 revision letter ``b''                               2005.
 permanently marked on the
 bottom of the bolt (or FAA-
 approved equivalent part
 number ). Return all
 replaced spherical locking
 bolts to Grob Systems,
 Inc., Aircraft Division,
 1070 Navajo Drive,
 Bluffton, Ohio 45817;
     (iii) Remove the
     existing nut and
     replace with a new nut,
     P/N 102-3510.21 (or FAA-
     approved equivalent
     part number); and
     (iv) Remove the
     existing lock washer
     and replace with a new
     lock washer, P/N DIN
     6796-10,5PHR (or FAA-
     approved equivalent
     part number).
(2) Repetitively inspect the  Initially inspect     As specified in GROB
 front and rear horizontal     within the next 100   Service Bulletin
 stabilizer attachment         hours time-in-        MSB306-38/1, dated
 assembly using a dye-         service (TIS) or at   November 28, 2005,
 penetrant method along with   the next annual       following the
 a minimum 10X magnifying      inspection after      Accomplishment
 glass for excessive           the replacement       Instructions in
 movement, cracks, and/or      required in           GROB Service
 damage in the spherical       paragraph (e)(1) of   Bulletin MSB306-38,
 locking bolt. This            this AD, whichever    dated February 12,
 inspection method takes       occurs first.         2004, and the
 precedence over the           Repetitively          Annual Inspection
 procedures outlined in GROB   inspect thereafter    procedures on pages
 Service Bulletin MSB306-38,   at 12-month           7 and 8 of the
 dated February 12, 2004.      intervals or at       Astir CS
                               intervals not to      Maintenance Manual,
                               exceed 100 hours      Rev. 9, dated Nov.
                               TIS, whichever        2005.
                               occurs first.
(3) If, during any            Before further        As specified in GROB
 inspection required in        flight after each     Service Bulletin
 paragraph (e)(2) of this      inspection required   MSB306-38/1, dated
 AD, you find excessive        in paragraph (e)(2)   November 28, 2005,
 movement:                     of this AD. After     following the
 (i) In the front horizontal   each replacement,     Accomplishment
 stabilizer attachment, you    the spherical         Instructions in
 must replace the spherical    locking bolt and      GROB Service
 locking bolt with a new       the retaining pins    Bulletin MSB306-38,
 part.                         have a life limit     dated February 12,
 (ii) In the rear horizontal   of 10 years and       2004, and the
 stabilizer attachment, you    must be replaced at   Annual Inspection
 must replace the retaining    that time.            procedures on pages
 pins with new parts.                                7 and 8 of the
 (iii) In the front and rear                         Astir CS
 horizontal stabilizer                               Maintenance Manual,
 attachment after doing the                          Rev. 9, dated Nov.
 replacement(s) required in                          2005.
 paragraph (e)(3)(i) and
 (e)(3)(ii) of this AD, you
 must replace the bearing in
 the stabilizer spar web.
(4) If, during any            Before further        As specified in GROB
 inspection required in        flight after each     Service Bulletin
 paragraph (e)(2) of this      inspection required   MSB306-38/1, dated
 AD, you do not find           in paragraph (e)(2)   November 28, 2005,
 excessive movement in the     of this AD. After     following the
 front and rear horizontal     each replacement,     Accomplishment
 stabilizer attachment:        the spherical         Instructions in
 (i) Inspect the spherical     locking bolt and      GROB Service
 locking bolt for cracks and   the retaining pins    Bulletin MSB306-38,
 damage using a dye-           have a life limit     dated February 12,
 penetrant method along with   of 10 year and must   2004, and the
 a minimum 10X magnifying      be replaced at that   Annual Inspection
 glass.                        time.                 procedures on pages
 (ii) If you find cracks or                          7 and 8 of the
 damage on the spherical                             Astir CS
 locking bolt, during the                            Maintenance Manual,
 inspection required in                              Rev. 9, dated Nov.
 paragraph (e)(4)(i) of this                         2005.
 AD, you must replace the
 bolt with a new bolt.

[[Page 32487]]

 
(5) Do not install any        As of the effective   Not applicable.
 spherical locking bolt, P/N   date of this AD.
 102-3500.21 (or FAA-
 approved equivalent part
 number), that does not have
 revision letter ``b''
 permanently marked on the
 bottom of the bolt.
(6) 14 CFR 21.303 allows for  Not Applicable......  Not Applicable.
 replacement parts through
 parts manufacturer approval
 (PMA). The phrase ``or FAA-
 approved equivalent part
 number'' in this AD is
 intended to signify those
 parts that are PMA parts
 approved through
 identicality to the design
 of the part under the type
 certificate and replacement
 parts to correct the unsafe
 condition under PMA (other
 than identicality). If
 parts are installed that
 are identical to the unsafe
 parts, then the corrective
 actions of the AD affect
 these parts also. In
 addition, equivalent
 replacement parts to
 correct the unsafe
 condition under PMA (other
 than identicality) may also
 be installed provided they
 meet current airworthiness
 standards, which include
 those actions cited in this
 AD.
------------------------------------------------------------------------


    Note:  During ground handling, it has been noted that a tendency 
exists for the ground crew to move these gliders by using the 
horizontal stabilizer as a lifting point. This practice may 
facilitate damage to the stabilizer assembly and should be avoided. 
See Caution note in GROB Service Bulletin MSB306-38, dated February 
12, 2004.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Standards Office, Small Airplane Directorate, 
FAA, ATTN: Gregory A. Davison, Aerospace Engineer, ACE-112, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4130; facsimile: (816) 329-4090, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.
    (g) AMOCs approved for AD 84-09-05 are not approved for this AD.

Related Information

    (h) German AD Number D-2004-168, dated March 23, 2004, also 
addresses the subject of this AD. To get copies of the documents 
referenced in this AD, contact GROB Luft-und Raumfahrt, 
Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Federal Republic 
of Germany; telephone: 011 49 8268 998139; fax: 011 49 8268 998200; 
e-mail: productsupport@grob-aerospace.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, or on the Internet at http://dms.dot.gov. The 
docket number is Docket No. FAA-2006-24253; Directorate Identifier 
2006-CE-23-AD.

    Issued in Kansas City, Missouri, on May 30, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-8712 Filed 6-5-06; 8:45 am]
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