| preamble attached >>> |
ADs updated daily at www.Tdata.com
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| PROPOSED AD |
GROB-WERKE GMBH & CO KG (PREVIOUSLY IDENTIFIED AS BURKHART-GROB
FLUGZEUGBAU INDUSTRIESTRABE): Docket No. FAA-2006-24253; Directorate Identifier 2006-CE-23-AD. |
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:
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ACTIONS COMPLIANCE PROCEDURES
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(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.
(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.
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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.
DATES: We must receive comments on this proposed AD by June 29, 2006.
| PREAMBLE |
|
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 Transportat-
ion (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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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 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:
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TOTAL COST FOR TOTAL COST ON
LABOR COST PARTS COST EACH SAILPLANE U.S. OPERATORS
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2 workhours x
$80 per hour = $160.. $253 $413 $23,128
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We estimate the following costs to do each proposed inspection:
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TOTAL COST FOR TOTAL COST ON
LABOR COST PARTS COST EACH SAILPLANE U.S. OPERATORS
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2 workhours x
$80 per hour = $160... Not Applicable $160 $8,960
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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: