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 https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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 https:// 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 https://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 https://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 https://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 https://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 https://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 https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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 https://
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 https://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 https://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 https://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]
BILLING CODE 4910-13-P

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