[Federal Register Volume 63, Number 176 (Friday, September 11, 1998)]
[Proposed Rules]
[Pages 48653-48655]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-24383]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-68-AD]
RIN 2120-AA64
Airworthiness Directives; Burkhart Grob Luft-und Raumfahrt Models
G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to all Burkhart Grob Luft-und Raumfahrt (Grob)
Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes.
The proposed AD would require inspecting the area of the elevator trim
tab hinges for cracks and a secure fit, and repairing any elevator trim
tab hinges with cracks or where a proper secure fit is not found. The
proposed AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for Germany.
The actions specified by the proposed AD are intended to prevent
structural damage of the trim tab hinges caused by cracks, which could
result in trim tab failure with consequent loss of control of the
airplane.
DATES: Comments must be received on or before October 15, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-68-
[[Page 48654]]
AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
Comments may be inspected at this location between 8 a.m. and 4 p.m.,
Monday through Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from Burkhart Grob Luft-und Raumfahrt, D-8939 Mattsies, Federal
Republic of Germany. This information also may be examined at the Rules
Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Karl M. Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate, 1201 Walnut, suite 900,
Kansas City, Missouri 64106; telephone: (816) 426-6932; facsimile:
(816) 426-2169.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 98-CE-68-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 98-CE-68-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority
for Germany, recently notified the FAA that an unsafe condition may
exist on all Grob Models G115, G115A, G115B, G115C, G115C2, G115D, and
G115D2 airplanes. The LBA reports incidents of cracks found in the area
of the trim tab hinges on the affected airplanes. The LBA states that
the cracks could be forming due to the trim tab end touching the upper
elevator shell at full deflection. This would indicate a loose or non-
secure fit of the trim tab hinges.
This condition, if not detected and corrected, could result in trim
tab failure with consequent loss of control of the airplane.
Relevant Service Information
Grob has issued Service Bulletin 1078-75, dated May 15, 1998, which
specifies procedures for inspecting the area of the elevator trim tab
hinges for cracks and a secure fit. Included with this service bulletin
are Installation Instructions No. 1078-75, dated May 15, 1998, which
specify procedures for repairing any elevator trim tab hinges with
cracks or where a proper secure fit is not found.
The LBA of Germany classified this service bulletin as mandatory
and issued German AD 1998-299, dated June 4, 1998, in order to assure
the continued airworthiness of these airplanes in Germany.
The FAA's Determination
These airplane models 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. Pursuant to this
bilateral airworthiness agreement, the LBA of Germany has kept the FAA
informed of the situation described above.
The FAA has examined the findings of the LBA; reviewed all
available information, including the service information referenced
above; and determined that AD action is necessary for products of this
type design that are certificated for operation in the United States.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Grob Models G115, G115A, G115B, G115C,
G115C2, G115D, and G115D2 airplanes of the same type design registered
in the United States, the FAA is proposing AD action. The proposed AD
would require inspecting the area of the elevator trim tab hinges for
cracks and a secure fit, and repairing any elevator trim tab hinges
with cracks or where a proper secure fit is not found. Accomplishment
of the proposed inspection would be in accordance with Grob Service
Bulletin 1078-75, dated May 15, 1998. Accomplishment of the proposed
repairs, if necessary, would be accomplished in accordance with Grob
Installation Instructions No. 1078-75, dated May 15, 1998.
Cost Impact
The FAA estimates that 26 airplanes in the U.S. registry would be
affected by the proposed inspection, that it would take approximately 1
workhour per airplane to accomplish the proposed inspection, and that
the average labor rate is approximately $60 an hour. Based on these
figures, the total cost impact of the proposed inspection on U.S.
operators is estimated to be $1,560, or $60 per airplane.
If any of the affected airplanes would have trim tab hinges that
were found cracked or where a proper secure fit was not found, the
proposed repair would take approximately 5 workhours per airplane at an
average labor rate of $60 per hour. Parts would cost approximately $25
per airplane. Based on these figures, the cost to repair any trim tab
hinges found cracked, or where a proper secure fit was not found, would
be approximately $325 per airplane.
Regulatory Impact
The regulations proposed herein would not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated,
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. A copy of the draft regulatory evaluation
prepared for this action has been placed in the Rules Docket. A copy of
it may be obtained by contacting the Rules Docket at the
[[Page 48655]]
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Burkhart Grob Luft-und Raumfahrt: Docket No. 98-CE-68-AD.
Applicability: Model G115, G115A, G115B, G115C, G115C2, G115D,
and G115D2 airplanes, all serial numbers, certificated in any
category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (d) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent structural damage of the trim tab hinges caused by
cracks, which could result in trim tab failure with consequent loss
of control of the airplane, accomplish the following:
(a) Within the next 50 hours time-in-service (TIS) after the
effective date of this AD, inspect the area of the elevator trim tab
hinges for cracks and a secure fit. Accomplish this inspection in
accordance with the Action section of Grob Service Bulletin No.
1078-75, dated May 15, 1998.
(b) Prior to further flight, repair any elevator trim tab hinges
with cracks or where a proper secure fit is not found. Accomplish
these repairs in accordance with the Procedure section of Grob
Installation Instructions No. 1078-75, dated May 15, 1998.
(c) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(d) An alternative method of compliance or adjustment of the
compliance times that provides an equivalent level of safety may be
approved by the Manager, Small Airplane Directorate, 1201 Walnut,
suite 900, Kansas City, Missouri 64106. The request shall be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, Small Airplane
Directorate.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(e) Questions or technical information related to Grob Service
Bulletin 1078-75, dated May 15, 1998, should be directed to Burkhart
Grob Luft-und Raumfahrt, D-8939 Mattsies, Federal Republic of
Germany. This service information may be examined at the FAA,
Central Region, Office of the Regional Counsel, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106.
Note 3: The subject of this AD is addressed in German AD 1998-
299, dated June 4, 1998.
Issued in Kansas City, Missouri, on September 3, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-24383 Filed 9-10-98; 8:45 am]
BILLING CODE 4910-13-P
