[Federal Register Volume 60, Number 198 (Friday, October 13, 1995)]
[Proposed Rules]
[Pages 53310-53312]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25439]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-30-AD]
Airworthiness Directives; HB Flugtechnik GmbH Model HB-23/2400
Sailplanes
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 HB Flugtechnik GmbH (Flugtechnik) Model HB-23/
2400 sailplanes. The proposed action would require inspecting (one
time) the elevator control system for incorrect rigging and
repetitively inspecting the threaded adjustable extension joints in the
push rod to control lever connection for cracks, and, if cracked,
replacing the threaded adjustable joints at both ends of the push rod.
Cracking of the threaded adjustable extension joints and incorrect
rigging of the elevator control system prompted the proposed action.
The actions specified by the proposed AD are intended to prevent
failure of the elevator control system, which, if not detected and
corrected, could result in possible loss of elevator control and loss
of the sailplane.
DATES: Comments must be received on or before December 14, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region,
[[Page 53311]]
Office of the Assistant Chief Counsel, Attention: Rules Docket No. 95-
CE-30-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 HB Flugtechnik GmbH, Dr. Adolf Scharfstr, 42, PF 74, A-4053 Haid,
Austria, telephone 43.7229.80904. This information also may be examined
at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Herman Belderok, Sailplane Program
Officer, Small Airplane Directorate, Airplane Certification Service,
FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64105; 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. 95-CE-30-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 Assistant Chief Counsel,
Attention: Rules Docket No. 95-CE-30-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The Austro Control GmbH (ACG), which is the airworthiness authority
for Austria, recently notified the FAA that an unsafe condition may
exist on certain Flugtechnik Model HB-23/2400 sailplanes. The ACG
advises that failure of the elevator control system has resulted in
several incidents and two fatal accidents. Specifically, a fatal
accident investigation revealed fatigue cracks in the threaded
adjustable extension joint of the elevator control push rod, thereby
causing loss of elevator control while in flight.
In addition, the ACG has received several reports of deformation
marks on the push rod tubes, bent adjustable extension joints, and
jamming between the elevator control lever and the elevator push rod
when the pilot pushes the control lever completely forward. Damage of
this nature is possibly caused by incorrect rigging or having less than
specified clearances between the elevator control lever and the
elevator push rod. HB Flugtechnik GmbH has issued service bulletins
(SB) HB-23/17/91 and HB-23/18/91, both dated October 28, 1991,
specifying the following:
--Inspecting (one time) for bending, and dents on the elevator control
push rod tube and replacing the elevator control push rod tube, if
damaged,
--Inspecting the clearance between the elevator control lever and the
elevator control push rod, ensuring the clearance remains at least 3
mm,
--Inspecting the threaded portion of the adjustable push rod joints
(located at each end of the push rod), for fatigue cracks and
deformation, and if cracked or damaged, (based on the fatigue
evaluation), replace the joints on both ends of the push rod.
--Repetitively inspecting, at intervals not to exceed 500 hours, the
threaded portion of the adjustable push rod joints for cracks or
deformation, and if cracked or damaged replacing the joints as
necessary.
The ACG classified these service bulletins as mandatory and issued
ACG AD numbers 66 and 67 in order to assure the continued airworthiness
of these sailplanes in Austria.
This sailplane model is manufactured in Austria and is 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 between Austria and
the United States. Pursuant to this bilateral airworthiness agreement,
the ACG has kept the FAA informed of the situation described above. The
FAA has examined the findings of the ACG, reviewed all available
information, and determined that AD action is necessary for products of
this type design that are certificated for operation in the United
States.
Since an unsafe condition has been identified that is likely to
exist or develop in other Flugtechnik HB-23/2400 sailplanes of the same
type design, the proposed AD would require inspecting (one time) the
elevator control system for incorrect rigging, inspecting the threaded
extension joints for cracks, if cracks are found, replacing the joints,
and repetitively inspecting the extension joints at intervals not to
exceed 500 hours time-in-service (TIS) thereafter for cracks or
deformation, and if cracked or damaged replacing the joints as
necessary.
The FAA estimates that one sailplane in the U.S. registry would be
affected by the proposed AD, that it would take approximately 3 hours
to accomplish the proposed action, and that the average labor rate is
approximately $60 an hour. Parts cost approximately $70 per sailplane.
Based on these figures, the total cost impact of the proposed AD on
U.S. operators is estimated to be $250. This figure is based on the
assumption that the affected owner/operator of the affected sailplane
has not incorporated the proposed modification or accomplished the
proposed inspections. The FAA has no way of determining the number of
repetitive inspections completed.
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
[[Page 53312]]
contacting the Rules Docket at the 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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
HB Flugtechnik GMBH: Docket No. 95-CE-30-AD.
Applicability: Model HB-23/2400 Sailplanes (serial numbers 23001
through 23048), certificated in any category.
Note 1: This AD applies to each sailplane 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 sailplanes 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 (f) 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 initially within the next 50 hours time-in-
service (TIS) after the effective date of this AD and as indicated
in the body of this AD thereafter, unless already accomplished.
To prevent failure of the elevator control system, which, if not
detected and corrected, could result in possible loss of elevator
control and loss of the sailplane, accomplish the following:
(a) Inspect (one time) for bending, and dents on the elevator
control push rod tube. Prior to further flight, replace the elevator
control push rod tube in accordance with Flugtechnick Service
Bulletin (SB) HB-23/18/91, dated October 28, 1991.
(b) Inspect the clearance between the elevator control lever and
the elevator control push rod, ensuring the clearance remains at
least 3 mm. If clearance is not 3 mm, prior to further flight,
adjust in accordance with the maintenance manual.
(c) Inspect the threaded portion of the adjustable push rod
joints (located at each end of the push rod) for fatigue cracks and
deformation, and if cracked or damaged, (based on the fatigue
evaluation), prior to further flight, replace the joints on both
ends of the push rod, in accordance with Flugtechnick SB HB-23/17/
91, dated October 28, 1991.
(d) Repetitively inspect the threaded portion of the adjustable
push rod joints, at intervals not to exceed 500 hours time-in-
service (TIS) thereafter for cracks or deformation, and if cracked
or damaged, prior to further flight, replace the joints as
necessary, in accordance with Flugtechnick SB HB-23/17/91, dated
October 28, 1991.
(e) 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 sailplane to a location where
the requirements of this AD can be accomplished.
(f) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Small Airplane
Directorate, FAA, 1201 Walnut, Kansas City, Missouri, 64106. The
request for the alternative method 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.
(g) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to HB Flugtechnik
GmbH, Dr. Adolf Scharfstr. 42, PF 74, A-4053 Haid, Austria,
telephone 43.7229.80904, or may examine these documents at the FAA,
Central Region, Office of the Assistant Chief Counsel, Room 1558,
601 E. 12th Street, Kansas City, Missouri 64106.
Issued in Kansas City, Missouri, on October 6, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-25439 Filed 10-12-95; 8:45 am]
BILLING CODE 4910-13-U
