Federal Register, Volume 72 Issue 161 (Tuesday, August 21, 2007)

[Federal Register Volume 72, Number 161 (Tuesday, August 21, 2007)]
[Rules and Regulations]
[Pages 46551-46553]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 07-4090]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28610; Directorate Identifier 2007-CE-058-AD;
Amendment 39-15166; AD 2007-17-08]
RIN 2120-AA64

Airworthiness Directives; DG Flugzeugbau GmbH Model DG-500MB
Gliders and Glaser-Dirks Flugzeugbau GmbH Model DG-800B Gliders

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued by the aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:

This AD requires actions that are intended to address the unsafe
condition described in the MCAI.

DATES: This AD becomes effective September 10, 2007.
On September 10, 2007, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in this AD.
We must receive comments on this AD by September 20, 2007.

ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: http://www.regulations.gov.
Follow the instructions for submitting comments.

Examining the AD Docket

You may examine the AD docket 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 AD
docket contains this AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone (800) 647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Gregory Davison, Aerospace Engineer,
FAA, Small Airplanes Directorate, 901 Locust St., Room 301, Kansas
City, Missouri 64016; telephone: (816) 329-4130; fax: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Discussion

The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued
Emergency AD No. 2007-0001R1-E, dated January 10, 2007, (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

Instead of the hub normally used which carries the starter ring
gear and the hub for

[[Page 46552]]

the tooth belt a slip-clutch can be mounted. The unit contains the
hub for the tooth belt and the starter ring gear. Occurrences during
service have shown that under bad conditions excessive wear on
several parts of the clutch can occur. In order to avoid further
damages the affected parts of the slip clutch on the engines SOLO 2
625 01 and SOLO 2 652 02 have to be inspected and replaced, if
necessary. In order to check the condition of the clutch on all
engines SOLO 2 625 in future, additional procedures are installed
and additional inspection terms are introduced. The cover place in
front of the slip clutch has to be replaced by a stronger plate with
the No. 2042888.
The original Emergency AD has now been revised to indicate that
the initial inspection of the installed slip-clutch is required when
12.5 hours in operation have been accumulated.
You may obtain further information by examining the MCAI in the
AD docket.

Relevant Service Information

SOLO Kleinmotoren GmbH has issued Service Bulletin Nr. 4600-2-2,
dated December 27, 2006. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.

FAA's Determination and Requirements of the AD

This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are issuing this AD because we
evaluated all information provided by the State of Design Authority and
determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might have also required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
described in a separate paragraph of the AD. These requirements take
precedence over those copied from the MCAI.

FAA's Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
occurrences during service have shown that under certain conditions,
excessive wear on several parts of the clutch can occur. Excessive wear
could cause the slip clutch to disengage at an undesired torque, which
could result in reduced power during critical phases of flight.
Therefore, we determined that notice and opportunity for public comment
before issuing this AD are impracticable and that good cause exists for
making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2007-28610; Directorate
Identifier 2007-CE-058-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because 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 about this AD.

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 determined that this AD will not have federalism implications
under Executive Order 13132. This AD will 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 this AD:
(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) 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 AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec. 39.13 by adding the following new AD:

2007-17-08 DG Flugzeugbau GmbH and Glaser-Dirks Flugzeugbau GmbH:
Amendment 39-15166; Docket No. FAA-2007-28610; Directorate
Identifier 2007-CE-058-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective
September 10, 2007.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Models DG-500MB and DG-800B gliders, all
serial numbers, that:
(1) Have SOLO engine 2 625 01 equipped with optional slip-clutch
sets, SOLO part number (P/N) 29 00 202, installed; or

[[Page 46553]]

(2) Have SOLO engine 2 625 02 equipped with optional slip-clutch
sets, SOLO P/N 29 00 202, installed; and
(3) Are certificated in any category.

Subject

(d) Air Transport Association of America (ATA) Code 61:
Propellers.

Reason

(e) The mandatory continuing airworthiness information (MCAI)
states:

Instead of the hub normally used which carries the starter ring
gear and the hub for the tooth belt a slip-clutch can be mounted.
The unit contains the hub for the tooth belt and the starter ring
gear. Occurrences during service have shown that under bad
conditions excessive wear on several parts of the clutch can occur.
In order to avoid further damages the affected parts of the slip
clutch on the engines SOLO 2 625 01 and SOLO 2 652 02 have to be
inspected and replaced, if necessary. In order to check the
condition of the clutch on all engines SOLO 2 625 in future,
additional procedures are installed and additional inspection terms
are introduced. The cover place in front of the slip clutch has to
be replaced by a stronger plate with the No. 2042888.
The original Emergency AD has now been revised to indicate that
the initial inspection of the installed slip-clutch is required when
12.5 hours in operation have been accumulated.

Actions and Compliance

(f) Unless already done, do the following actions.
(1) Before further flight after September 10, 2007 (the
effective date of this AD):
(i) Remove the cover plate of the slip-clutch;
(ii) Inspect the friction pads for wear. Dimension in new
condition is .335 inches (8.5 mm), the wear limit is .256 inches
(6.5 mm);
(iii) Inspect the slip-clutch shoes on the contact surface to
the hub for wear. The wear limit is .039 inches (1 mm);
(iv) Replace any parts found to be outside the wear limit; and
(v) Assemble the slip-clutch with a new cover plate, P/N
2042888.
(2) Every 12.5 hours time-in-service (TIS) after doing the
actions required by paragraph (f)(1) of this AD, repetitively
inspect the slip-clutch and replace any parts found to be outside
the wear limit before further flight after the inspection in which
the part(s) exceeds the specified limit.
(3) Every 25 hours TIS after September 10, 2007 (the effective
date of this AD), inspect the tiltplay of the clutch drum on the hub
for excessive play.
(i) With the tooth belt released, measure the play in the axial
direction on the starter gear. The play limit is .024 inches (0.6
mm); and
(ii) Before further flight after any inspection in which
excessive play is found, replace with an FAA-approved part that is
new or overhauled by the manufacturer.
(4) Every 50 hours TIS after September 10, 2007 (the effective
date of this AD), replace the slip-clutch with an FAA-approved part
that is new or overhauled by the manufacturer.
(5) As of September 10, 2007 (the effective date of this AD),
only install slip-clutch cover plate P/N 2042888.
(6) Each time before the slip-clutch is mounted, degrease the
taper of the crankshaft and the hub of the clutch with thinner
following the instructions in the service bulletin specified in
paragraph (f)(7) of this AD. The pound inches equivalent to 120 Nm
is 1062.1.
(7) Do all actions required by this AD following SOLO
Kleinmotoren GmbH Service Bulletin Nr. 4600-2-2, dated December 27,
2006.

FAA AD Differences

Note: This AD differs from the MCAI and/or service information
as follows: No differences.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Staff, FAA, ATTN: Gregory Davison, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4130; fax: (816) 329-4090, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Before using any approved AMOC on
any airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et.seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120[pi]0056.

Related Information

(h) Refer to MCAI European Aviation Safety Agency (EASA)
Emergency AD No. 2007-0001R1-E, dated January 10, 2007, and SOLO
Kleinmotoren GmbH Service Bulletin Nr. 4600-2-2, dated December 27,
2006, for related information.

Material Incorporated by Reference

(i) You must use SOLO Kleinmotoren GmbH Service Bulletin Nr.
4600-2-2, dated December 27, 2006, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact SOLO
Kleinmotoren GmbH, Customer Support, 71050 Sindelfingen, Germany;
telephone: +49-(0) 7031-301-210; fax: +49-(0) 7031-301-136; e-mail:
germany.com">wolfgang.emmerich@solo-germany.com.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust St., Room 506, Kansas City,
Missouri 64016; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal[pi]register/cfr/ibr-locations.html.

Issued in Kansas City, Missouri on August 14, 2007.
Terry L. Chasteen,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 07-4090 Filed 8-20-07; 8:45 am]
BILLING CODE 4910-13-P