Airworthiness Directives; DG Flugzeugbau GmbH Model DG-500 Elan Series, DG-500M, and DG-500MB Gliders, 56891-56894 [E7-19682]
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Federal Register / Vol. 72, No. 193 / Friday, October 5, 2007 / Rules and Regulations
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 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.
Examining the AD Docket
You may examine the AD docket 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 AD docket contains the
NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
yshivers on PROD1PC62 with RULES
2007–20–08 Alpha Aviation Design Limited
(Type Certificate No. A48EU previously
held by Apex Aircraft and Avions Pierre
Robin): Amendment 39–15218; Docket
No. FAA–2006–26491; Directorate
Identifier 2006–CE–076–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective November 9, 2007.
Affected ADs
(b) None.
VerDate Aug<31>2005
15:23 Oct 04, 2007
Jkt 214001
Applicability
(c) This AD applies to Model R2160
airplanes, serial numbers 001 through 191,
certificated in any category.
Subject
(d) Air Transport Association of America
(ATA) Code 28: Fuel.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
To prevent fuel system leaks inspect the
bronze/brass hollow threaded fuel line
fittings for type and leaks, per Avions Pierre
Robin Service Bulletin (SB) No. 86.
Actions and Compliance
(f) Unless already done, within the next 25
hours time-in-service after November 9, 2007
(the effective date of this AD) replace the
Type 1 fuel line fittings with Type 2 fittings
following Avions Pierre Robin Service
Bulletin No. 86, dated July, 1980.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: This AD
requires the replacement of the Type 1 fuel
line fittings with Type 2 fittings following
Avions Pierre Robin Service Bulletin No. 86,
dated July, 1980. The MCAI required a onetime inspection for leaks and replacement if
leaks were found. There was no MCAI action
to determine whether leaks developed in the
future. The FAA believes that mandatory
replacement of the fittings will eliminate
current leaking fittings as well as preventing
the problem from developing in the future.
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4146; fax: (816)
329–4090. 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 2120–0056.
Frm 00009
Fmt 4700
Sfmt 4700
Related Information
(h) Refer to MCAI Airworthiness Authority
of New Zealand AD DCA/R2000/12, dated
June 29, 2006, and Avions Pierre Robin
Service Bulletin No. 86, dated July, 1980, for
related information.
Material Incorporated by Reference
(i) You must use Avions Pierre Robin
Service Bulletin No. 86, dated July, 1980, 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 Alpha Aviation Design Ltd.,
Ingram Road, Hamilton Airport, R.D.2.
Hamilton 3282, New Zealand.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; 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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on
September 27, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–19501 Filed 10–4–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Other FAA AD Provisions
PO 00000
56891
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28709; Directorate
Identifier 2007–CE–062–AD; Amendment
39–15219; AD 2007–21–01]
RIN 2120–AA64
Airworthiness Directives; DG
Flugzeugbau GmbH Model DG–500
Elan Series, DG–500M, and DG–500MB
Gliders
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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:
During a recent flight with a DG–500 ELAN
Trainer, the bolt of bearing stand 5RU61,
which is the pivot for bell crank 5St19, failed
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Federal Register / Vol. 72, No. 193 / Friday, October 5, 2007 / Rules and Regulations
in-flight, leading to loss of control of the
aircraft. Although the occupants managed to
exit the aircraft safely, the aircraft crashed
and was damaged beyond repair. While the
investigation continues, the most likely cause
is suspected to be insufficient tightening of
the nut on the bolt of bearing stand 5RU61.
This condition, if not corrected, may cause
excessive bending loads, leading to
premature failure of the bolt and loss of
control of the aircraft.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
October 25, 2007.
On October 25, 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 November 5, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• 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.
yshivers on PROD1PC62 with RULES
Examining the AD Docket
You may examine the AD docket on
the Internet at https://www.regulations.
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: Greg
Davison, Glider Program Manager, 901
Locust, Room 301, Kansas City,
Missouri 64106; 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 AD No. 2007–
0176–E, dated June 22, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
VerDate Aug<31>2005
15:23 Oct 04, 2007
Jkt 214001
unsafe condition for the specified
products. The MCAI states:
During a recent flight with a DG–500 ELAN
Trainer, the bolt of bearing stand 5RU61,
which is the pivot for bell crank 5St19, failed
in-flight, leading to loss of control of the
aircraft. Although the occupants managed to
exit the aircraft safely, the aircraft crashed
and was damaged beyond repair. While the
investigation continues, the most likely cause
is suspected to be insufficient tightening of
the nut on the bolt of bearing stand 5RU61.
This condition, if not corrected, may cause
excessive bending loads, leading to
premature failure of the bolt and loss of
control of the aircraft. As a precautionary
measure, for the reasons described above,
this Emergency Airworthiness Directive
(EAD) requires a check of the torque on the
affected nut, immediate replacement of any
bolts where the torque is found to be
insufficient and introduces a life limit for the
affected bolts. Any bolts that have already
exceeded this limit in service must be
replaced, as indicated.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
DG Flugzeugbau GmbH has issued
Technical Note 348/19 and 843/26
(same document), dated June 20, 2007,
which references Working Instructions
DG Flugzeugbau GmbH No. 1 and 2,
dated June 20, 2007; and Working
Instruction DG Flugzeugbau GmbH No.
3, dated June 25, 2007. 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
PO 00000
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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 during a recent flight with
a DG–500 ELAN Trainer, the bolt of
bearing stand 5RU61, which is the pivot
for bell crank 5St19, failed in flight with
consequent loss of control of the
aircraft. The most likely cause is
insufficient tightening of the nut on the
bolt of bearing stand 5RU61. This
condition, if not corrected, may cause
excessive bending loads that could
result in premature failure of the bolt
with consequent loss of control of the
aircraft. 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–2007–28709;
Directorate Identifier 2007–CE–062–
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 https://
www.regulations.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
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Federal Register / Vol. 72, No. 193 / Friday, October 5, 2007 / Rules and Regulations
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
yshivers on PROD1PC62 with RULES
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–21–01 DG Flugzeugbau GMBH:
Amendment 39–15219; Docket No.
VerDate Aug<31>2005
15:23 Oct 04, 2007
Jkt 214001
FAA–2007–28709; Directorate Identifier
2007–CE–062–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 25, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models DG–500 Elan
Series, DG–500M, and DG–500MB gliders, all
serial numbers, certificated in any category.
Subject
(d) Air Transport Association of America
(ATA) Code 27: Flight Controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During a recent flight with a DG–500 ELAN
Trainer, the bolt of bearing stand 5RU61,
which is the pivot for bell crank 5St19, failed
in-flight, leading to loss of control of the
aircraft. Although the occupants managed to
exit the aircraft safely, the aircraft crashed
and was damaged beyond repair. While the
investigation continues, the most likely cause
is suspected to be insufficient tightening of
the nut on the bolt of bearing stand 5RU61.
This condition, if not corrected, may cause
excessive bending loads, leading to
premature failure of the bolt and loss of
control of the aircraft.
As a precautionary measure, for the
reasons described above, this Emergency
Airworthiness Directive (EAD) requires a
check of the torque on the affected nut,
immediate replacement of any bolts where
the torque is found to be insufficient and
introduces a life limit for the affected bolts.
Any bolts that have already exceeded this
limit in service must be replaced, as
indicated.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Before the next flight after October 25,
2007 (the effective date of this AD) and
thereafter at intervals not to exceed 12
months, inspect the actual torque of the nut
that attaches bell crank 5St19 to the bolt
following Working Instruction No. 1, dated
June 20, 2007, as referenced in DG
Flugzeugbau GmbH Technical Note 348/19
and 843/26 (same document), dated June 20,
2007, as applicable to type.
(i) If the torque is found to be less than 2.2
ft. lb. (3 Nm), before further flight, replace the
affected bolt with a serviceable bolt following
Working Instruction No. 2, dated June 20,
2007, as referenced in DG Flugzeugbau
GmbH Technical Note 348/19 and 843/26
(same document), dated June 20, 2007, as
applicable to type.
(ii) Report any findings of insufficient
torque you find within 7 days after
insufficient torque is found. Include in your
report the glider serial number, glider hours
time-in-service (TIS), the torque that was
found, and a point of contact name and
phone number. Send your report to DG
Flugzeugbau GmbH, Otto-Lilienthal-Weg 2,
D–76646 Bruchsal, Germany; telephone: +49
PO 00000
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Fmt 4700
Sfmt 4700
56893
7251 3020140; facsimile: +49 7251 3020149;
e-mail: dirks@dg-flugzeugbau.de.
(iii) If the torque is found to be 2.2 ft. lb.
(3 Nm) or more, before further flight, increase
the torque of the nut to 9 ft. lb. (12 Nm);
(2) Unless already replaced as required by
paragraph (f)(1)(i) of this AD, within the next
6 months after October 25, 2007 (the effective
date of this AD) or when the glider reaches
a total of 1,000 hours TIS, whichever occurs
later, and repetitively thereafter at intervals
not to exceed 1,000 hours TIS, replace the
affected bolt with a serviceable bolt following
Working Instruction No. 2, dated June 20,
2007, as referenced in DG Flugzeugbau
GmbH Technical Note 348/19 and 843/26
(same document), dated June 20, 2007, as
applicable to type.
(3) Installation of an additional bracket
following Working Instruction No. 3, dated
June 25, 2007, as referenced in DG
Flugzeugbau GmbH Technical Note 348/19
and 843/26 (same document), dated June 20,
2007, as applicable to type, terminates the
repetitive requirement in paragraph (f)(2) of
this AD.
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 Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Greg Davison, Glider Program
Manager, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4130; fax: (816)
329–4090. 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 2120–0056.
Related Information
(h) Refer to MCAI EASA AD No. 2007–
0176–E, dated June 22, 2007, and DG
Flugzeugbau GmbH Technical Note 348/19
and 843/26 (same document), dated June 20,
2007; Working Instructions No. 1 and No. 2,
dated June 20, 2007, as referenced in DG
Flugzeugbau GmbH Technical Note 348/19
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Federal Register / Vol. 72, No. 193 / Friday, October 5, 2007 / Rules and Regulations
and 843/26 (same document), dated June 20,
2007; and Working Instruction No. 3, dated
June 25, 2007, as referenced in DG
Flugzeugbau GmbH Technical Note 348/19
and 843/26 (same document), dated June 20,
2007, for related information.
Material Incorporated by Reference
(i) You must use DG Flugzeugbau GmbH
Technical Note 348/19 and 843/26 (same
document), dated June 20, 2007; Working
Instructions No. 1 and 2 dated June 20, 2007,
and Working Instruction No. 3 dated June 25,
2007, as referenced in DG Flugzeugbau
GmbH Technical Note 348/19 and 843/26
(same document), dated June 20, 2007, 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 AMS-Flight d.o.o.,
Kavciceva 4, 1000 Ljubljana, Slovenia.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; 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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri on
September 28, 2007.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–19682 Filed 10–4–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30571; Amdt. No. 3237]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
yshivers on PROD1PC62 with RULES
AGENCY:
15:23 Oct 04, 2007
Jkt 214001
This rule is effective October 5,
2007. The compliance date for each
SIAP, associated Takeoff Minimums,
and ODP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of October 5,
2007.
ADDRESSES: Availability of matters
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591;
2. The FAA Regional Office of the
region in which the affected airport is
located;
3. The National Flight Procedures
Office, 6500 South MacArthur Blvd.,
Oklahoma City, OK 73169 or,
4. The National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
Availability—All SIAPs and Takeoff
Minimums and ODPs are available
online free of charge. Visit nfdc.faa.gov
to register. Additionally, individual
SIAP and Takeoff Minimums and ODP
copies may be obtained from:
1. FAA Public Inquiry Center (APA–
200), FAA Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591; or
2. The FAA Regional Office of the
region in which the affected airport is
located.
DATES:
FOR FURTHER INFORMATION CONTACT:
SUMMARY: This Rule establishes,
amends, suspends, or revokes Standard
Instrument Approach Procedures
(SIAPs) and associated Takeoff
Minimums and Obstacle Departure
Procedures for operations at certain
airports. These regulatory actions are
needed because of the adoption of new
or revised criteria, or because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, adding new
obstacles, or changing air traffic
VerDate Aug<31>2005
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
Harry. J. Hodges, Flight Procedure
Standards Branch (AFS–420), Flight
Technologies and Programs Division,
Flight Standards Service, Federal
Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd., Oklahoma City,
OK 73169 (Mail Address: P.O. Box
25082, Oklahoma City, OK 73125)
telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This rule
amends Title 14 of the Code of Federal
Regulations, Part 97 (14 CFR part 97), by
establishing, amending, suspending, or
revoking SIAPs, Takeoff Minimums
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Sfmt 4700
and/or ODPs. The complete regulatory
description of each SIAP and its
associated Takeoff Minimums or ODP
for an identified airport is listed on FAA
form documents which are incorporated
by reference in this amendment under 5
U.S.C. 552(a), 1 CFR part 51, and 14
CFR part 97.20. The applicable FAA
Forms are FAA Forms 8260–3, 8260–4,
8260–5, 8260–15A, and 8260–15B when
required by an entry on 8260–15A.
The large number of SIAPs, Takeoff
Minimums and ODPs, in addition to
their complex nature and the need for
a special format make publication in the
Federal Register expensive and
impractical. Furthermore, airmen do not
use the regulatory text of the SIAPs,
Takeoff Minimums or ODPs, but instead
refer to their depiction on charts printed
by publishers of aeronautical materials.
Thus, the advantages of incorporation
by reference are realized and
publication of the complete description
of each SIAP, Takeoff Minimums and
ODP listed on FAA forms is
unnecessary. This amendment provides
the affected CFR sections and specifies
the types of SIAPs and the effective
dates of the SIAPs, the associated
Takeoff Minimums, and ODPs. This
amendment also identifies the airport
and its location, the procedure, and the
amendment number.
The Rule
This amendment to 14 CFR part 97 is
effective upon publication of each
separate SIAP, Takeoff Minimums and
ODP as contained in the transmittal.
Some SIAP and Takeoff Minimums and
textual ODP amendments may have
been issued previously by the FAA in a
Flight Data Center (FDC) Notice to
Airmen (NOTAM) as an emergency
action of immediate flight safety relating
directly to published aeronautical
charts. The circumstances which
created the need for some SIAP and
Takeoff Minimums and ODP
amendments may require making them
effective in less than 30 days. For the
remaining SIAPs and Takeoff
Minimums and ODPs, an effective date
at least 30 days after publication is
provided.
Further, the SIAPs and Takeoff
Minimums and ODPs contained in this
amendment are based on the criteria
contained in the U.S. Standard for
Terminal Instrument Procedures
(TERPS). In developing these SIAPs and
Takeoff Minimums and ODPs, the
TERPS criteria were applied to the
conditions existing or anticipated at the
affected airports. Because of the close
and immediate relationship between
these SIAPs, Takeoff Minimums and
ODPs, and safety in air commerce, I find
E:\FR\FM\05OCR1.SGM
05OCR1
]]>Agencies
[Federal Register Volume 72, Number 193 (Friday, October 5, 2007)]
[Rules and Regulations]
[Pages 56891-56894]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-19682]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28709; Directorate Identifier 2007-CE-062-AD;
Amendment 39-15219; AD 2007-21-01]
RIN 2120-AA64
Airworthiness Directives; DG Flugzeugbau GmbH Model DG-500 Elan
Series, DG-500M, and DG-500MB Gliders
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
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:
During a recent flight with a DG-500 ELAN Trainer, the bolt of
bearing stand 5RU61, which is the pivot for bell crank 5St19, failed
[[Page 56892]]
in-flight, leading to loss of control of the aircraft. Although the
occupants managed to exit the aircraft safely, the aircraft crashed
and was damaged beyond repair. While the investigation continues,
the most likely cause is suspected to be insufficient tightening of
the nut on the bolt of bearing stand 5RU61.
This condition, if not corrected, may cause excessive bending
loads, leading to premature failure of the bolt and loss of control
of the aircraft.
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective October 25, 2007.
On October 25, 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 November 5, 2007.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations. 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: Greg Davison, Glider Program Manager,
901 Locust, Room 301, Kansas City, Missouri 64106; 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 AD
No. 2007-0176-E, dated June 22, 2007 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
During a recent flight with a DG-500 ELAN Trainer, the bolt of
bearing stand 5RU61, which is the pivot for bell crank 5St19, failed
in-flight, leading to loss of control of the aircraft. Although the
occupants managed to exit the aircraft safely, the aircraft crashed
and was damaged beyond repair. While the investigation continues,
the most likely cause is suspected to be insufficient tightening of
the nut on the bolt of bearing stand 5RU61.
This condition, if not corrected, may cause excessive bending
loads, leading to premature failure of the bolt and loss of control
of the aircraft. As a precautionary measure, for the reasons
described above, this Emergency Airworthiness Directive (EAD)
requires a check of the torque on the affected nut, immediate
replacement of any bolts where the torque is found to be
insufficient and introduces a life limit for the affected bolts. Any
bolts that have already exceeded this limit in service must be
replaced, as indicated.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
DG Flugzeugbau GmbH has issued Technical Note 348/19 and 843/26
(same document), dated June 20, 2007, which references Working
Instructions DG Flugzeugbau GmbH No. 1 and 2, dated June 20, 2007; and
Working Instruction DG Flugzeugbau GmbH No. 3, dated June 25, 2007. 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
during a recent flight with a DG-500 ELAN Trainer, the bolt of bearing
stand 5RU61, which is the pivot for bell crank 5St19, failed in flight
with consequent loss of control of the aircraft. The most likely cause
is insufficient tightening of the nut on the bolt of bearing stand
5RU61. This condition, if not corrected, may cause excessive bending
loads that could result in premature failure of the bolt with
consequent loss of control of the aircraft. 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-2007-28709; Directorate
Identifier 2007-CE-062-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 https://
www.regulations.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
[[Page 56893]]
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:
2007-21-01 DG Flugzeugbau GMBH: Amendment 39-15219; Docket No. FAA-
2007-28709; Directorate Identifier 2007-CE-062-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
25, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models DG-500 Elan Series, DG-500M, and
DG-500MB gliders, all serial numbers, certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 27: Flight
Controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During a recent flight with a DG-500 ELAN Trainer, the bolt of
bearing stand 5RU61, which is the pivot for bell crank 5St19, failed
in-flight, leading to loss of control of the aircraft. Although the
occupants managed to exit the aircraft safely, the aircraft crashed
and was damaged beyond repair. While the investigation continues,
the most likely cause is suspected to be insufficient tightening of
the nut on the bolt of bearing stand 5RU61.
This condition, if not corrected, may cause excessive bending
loads, leading to premature failure of the bolt and loss of control
of the aircraft.
As a precautionary measure, for the reasons described above,
this Emergency Airworthiness Directive (EAD) requires a check of the
torque on the affected nut, immediate replacement of any bolts where
the torque is found to be insufficient and introduces a life limit
for the affected bolts. Any bolts that have already exceeded this
limit in service must be replaced, as indicated.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Before the next flight after October 25, 2007 (the effective
date of this AD) and thereafter at intervals not to exceed 12
months, inspect the actual torque of the nut that attaches bell
crank 5St19 to the bolt following Working Instruction No. 1, dated
June 20, 2007, as referenced in DG Flugzeugbau GmbH Technical Note
348/19 and 843/26 (same document), dated June 20, 2007, as
applicable to type.
(i) If the torque is found to be less than 2.2 ft. lb. (3 Nm),
before further flight, replace the affected bolt with a serviceable
bolt following Working Instruction No. 2, dated June 20, 2007, as
referenced in DG Flugzeugbau GmbH Technical Note 348/19 and 843/26
(same document), dated June 20, 2007, as applicable to type.
(ii) Report any findings of insufficient torque you find within
7 days after insufficient torque is found. Include in your report
the glider serial number, glider hours time-in-service (TIS), the
torque that was found, and a point of contact name and phone number.
Send your report to DG Flugzeugbau GmbH, Otto-Lilienthal-Weg 2, D-
76646 Bruchsal, Germany; telephone: +49 7251 3020140; facsimile: +49
7251 3020149; e-mail: dirks@dg-flugzeugbau.de.
(iii) If the torque is found to be 2.2 ft. lb. (3 Nm) or more,
before further flight, increase the torque of the nut to 9 ft. lb.
(12 Nm);
(2) Unless already replaced as required by paragraph (f)(1)(i)
of this AD, within the next 6 months after October 25, 2007 (the
effective date of this AD) or when the glider reaches a total of
1,000 hours TIS, whichever occurs later, and repetitively thereafter
at intervals not to exceed 1,000 hours TIS, replace the affected
bolt with a serviceable bolt following Working Instruction No. 2,
dated June 20, 2007, as referenced in DG Flugzeugbau GmbH Technical
Note 348/19 and 843/26 (same document), dated June 20, 2007, as
applicable to type.
(3) Installation of an additional bracket following Working
Instruction No. 3, dated June 25, 2007, as referenced in DG
Flugzeugbau GmbH Technical Note 348/19 and 843/26 (same document),
dated June 20, 2007, as applicable to type, terminates the
repetitive requirement in paragraph (f)(2) of this AD.
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 Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Greg Davison, Glider Program Manager, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4130; fax: (816) 329-4090.
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 2120-0056.
Related Information
(h) Refer to MCAI EASA AD No. 2007-0176-E, dated June 22, 2007,
and DG Flugzeugbau GmbH Technical Note 348/19 and 843/26 (same
document), dated June 20, 2007; Working Instructions No. 1 and No.
2, dated June 20, 2007, as referenced in DG Flugzeugbau GmbH
Technical Note 348/19
[[Page 56894]]
and 843/26 (same document), dated June 20, 2007; and Working
Instruction No. 3, dated June 25, 2007, as referenced in DG
Flugzeugbau GmbH Technical Note 348/19 and 843/26 (same document),
dated June 20, 2007, for related information.
Material Incorporated by Reference
(i) You must use DG Flugzeugbau GmbH Technical Note 348/19 and
843/26 (same document), dated June 20, 2007; Working Instructions
No. 1 and 2 dated June 20, 2007, and Working Instruction No. 3 dated
June 25, 2007, as referenced in DG Flugzeugbau GmbH Technical Note
348/19 and 843/26 (same document), dated June 20, 2007, 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 AMS-
Flight d.o.o., Kavciceva 4, 1000 Ljubljana, Slovenia.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; 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: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri on September 28, 2007.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-19682 Filed 10-4-07; 8:45 am]
BILLING CODE 4910-13-P
