Airworthiness Directives; DG Flugzeugbau GmbH Model DG-500MB Sailplanes and Glaser-Dirks Flugzeugbau GmbH Model DG-800B Sailplanes, 29440-29442 [05-9975]
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29440
Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and Regulations
Actions
Compliance
Procedures
(5) Do not install a new lever shaft side plate
that is less than 0.050 inches in thickness.
As of June 30, 2005 (the effective date of this
AD).
As specified in Nomad Alert Service Bulletin
ANMD–27–51, Rev. 2, dated April 29,
2004; and Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary
Revision 26, Fatigue Critical Areas, dated
May 27, 2004.
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19.
(1) Unless FAA authorizes otherwise, send
your request to your principal inspector. The
principal inspector may add comments and
will send your request to the Manager,
Standards Office, Small Airplane Directorate,
FAA. For information on any already
approved alternative methods of compliance,
contact Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, ACE–112, 901
Locust, Rm 301, Kansas City, Missouri,
64106; telephone: (816) 329–4059; facsimile:
(816) 329–4090.
(2) Alternative methods of compliance
approved for AD 2003–14–20 are not
considered approved as alternative methods
of compliance for this AD.
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 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2005–20439; Directorate Identifier 2005–CE–
04–AD.
Issued in Kansas City, Missouri, on May
13, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–9976 Filed 5–20–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
As of June 30, 2005, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
ADDRESSES: To get the service
information identified in this AD,
contact DG Flugzeugbau, Postbox 41 20,
76625 Bruchsal, Germany; telephone, 49
7257 890; fax, 49 7257 8922.
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 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2004–19959; Directorate Identifier
2004–CE–46–AD.
FOR FURTHER INFORMATION CONTACT:
Gregory Davison, Aerospace Engineer,
FAA, Small Airplane Directorate, ACE–
112, Room 301, 901 Locust, Kansas City,
Missouri 64106; telephone: 816–329–
4130; facsimile: 816–329–4090.
SUPPLEMENTARY INFORMATION:
Is There Other Information That Relates to
This Subject?
(g) Australian AD GAF–N22/44,
Amendment 2, dated November 2004, also
addresses the subject of this AD.
14 CFR Part 39
Does This AD Incorporate Any Material By
Reference?
(h) You must do the actions required by
this AD following the instructions in
Nomad—Series N22 & N24 Inspection
Requirements Manual, Temporary Revision
26, Fatigue Critical Areas, dated May 27,
2004, and Nomad Alert Service Bulletin
ANMD–27–51, Rev. 2, dated April 29, 2004,
which incorporates the following pages:
RIN 2120–AA64
Discussion
Airworthiness Directives; DG
Flugzeugbau GmbH Model DG–500MB
Sailplanes and Glaser-Dirks
Flugzeugbau GmbH Model DG–800B
Sailplanes
What events have caused this AD?
The Luftfahrt-Bundesamt (LBA), which
is the airworthiness authority for
Germany, recently notified FAA that an
unsafe condition may exist on all DG
Flugzeugbau GmbH Model DG–500MB
sailplanes equipped with a Solo engine
and all Glaser-Dirks Flugzeugbau GmbH
Model DG–800B sailplanes equipped
with a Solo engine. The LBA reports
that a damaged propeller was found on
a Model DG–800B sailplane.
The foam core inside the propeller
separated and caused one blade to be
thicker than the other. The propeller
became overheated after the engine was
retracted. This was possibly due to
limited ventilation. The LBA reports
three occurrences of this condition.
The propeller on Model DG–500MB
sailplanes equipped with a Solo engine
is of a similar design to Model DG–800B
sailplanes equipped with a Solo engine.
What is the potential impact if FAA
took no action? If not detected and
corrected, damage to the propeller,
specifically foam core separation, could
cause the propeller to fail to perform
properly. This failure could lead to
reduced or loss of control of the
sailplane.
Revision
level
Pages
1 and 3 ..........
2 .....................
4 .....................
1 Original
2
2
1
Date
April 29, 2004.
Jan. 29, 2004.
Sept. 13, 2002.
issue.
(1) The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) To get a copy of this service
information, contact Nomad Operations,
Aerospace Support Division, Boeing
Australia, PO Box 767, Brisbane, QLD 4001
Australia; telephone 61 7 3306 3366;
facsimile 61 7 3306 3111. To review copies
of this service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
VerDate jul<14>2003
14:30 May 20, 2005
Jkt 205001
[Docket No. FAA–2004–19959; Directorate
Identifier 2004–CE–46–AD; Amendment 39–
14101; AD 2005–10–23]
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for all DG
Flugzeugbau GmbH Model DG–500MB
sailplanes equipped with a Solo engine
and Glaser-Dirks Flugzeugbau GmbH
Model DG–800B sailplanes equipped
with a Solo engine. This AD requires
you to inspect the propeller for damage,
specifically foam core separation, and
replace any damaged propeller. This AD
results from mandatory continuing
airworthiness information (MCAI)
issued by the airworthiness authority for
Germany. We are issuing this AD to
detect and correct damage to the
propeller, which could result in failure
of the propeller to perform properly.
This failure could lead to reduced or
loss of control of the sailplane.
DATES: This AD becomes effective on
June 30, 2005.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
E:\FR\FM\23MYR1.SGM
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29441
Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and Regulations
Has FAA taken any action to this
point? We issued a proposal to amend
part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include
an AD that would apply to all DG
Flugzeugbau GmbH Model DG–500MB
sailplanes equipped with a Solo engine
and Glaser-Dirks Flugzeugbau GmbH
Model DG–800B sailplanes equipped
with a Solo engine. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on February 14, 2005 (70 FR 7443). The
NPRM proposed to require you to
inspect the propeller for damage,
specifically foam core separation, and
replace any damaged propeller.
Comments
Was the public invited to comment?
We provided the public the opportunity
to participate in developing this AD. We
received no comments on the proposal
or on the determination of the cost to
the public.
Conclusion
What is FAA’s final determination on
this issue? We have carefully reviewed
the available data and determined that
air safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Changes to 14 CFR Part 39—Effect on
the AD
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, the
FAA published a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
which governs the FAA’s AD system.
This regulation now includes material
that relates to altered products, special
flight permits, and alternative methods
of compliance. This material previously
was included in each individual AD.
Since this material is included in 14
CFR part 39, we will not include it in
future AD actions.
Costs of Compliance
How many sailplanes does this AD
impact? We estimate that this AD affects
31 sailplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
sailplanes? We estimate the following
costs to accomplish the inspection:
Labor cost
Parts cost
Total cost
per
sailplane
1 work hour × $65 per hour = $65 ........................................................................
Not applicable ...........
$65
We estimate the following costs to do
any necessary replacements that will be
required based on the results of the
inspection. We have no way of
Total cost on
U.S. operators
$65 × 31 = $2,015.
determining the number of sailplanes
that may need this replacement:
Labor cost
Parts cost
Total cost per sailplane
1 work hour × $65 per hour = $65 ........................................................................................................
$4,000
$4,065.
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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 AD.
Regulatory Findings
Will this AD impact various entities?
We have determined that this AD will
not have federalism implications under
VerDate jul<14>2003
14:30 May 20, 2005
Jkt 205001
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.
Will this AD involve a significant rule
or regulatory action? 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 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 summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2004–19959;
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
Directorate Identifier 2004–CE–46–AD’’
in your request.
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 Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (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]
I 2. FAA amends § 39.13 by adding a
new AD to read as follows:
2005–10–23 DG Flugzeugbau GmbH and
Glaser-Dirks Flugzeugbau GmbH:
Amendment 39–14101; Docket No.
FAA–2004–19959; Directorate Identifier
2004–CE–46–AD.
E:\FR\FM\23MYR1.SGM
23MYR1
29442
Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and Regulations
When Does This AD Become Effective?
What Sailplanes Are Affected By This AD?
(a) This AD becomes effective on June 30,
2005.
(c) This AD affects all Model DG–500MB
and DG–800B sailplanes that are:
(1) Certificated in any category; and
(2) Equipped with a Solo engine.
What Other ADs Are Affected By This
Action?
What Is the Unsafe Condition Presented in
This AD?
(b) None.
(d) This AD is the result of mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Germany. The actions specified in this AD
are intended to detect and correct damage to
the propeller, which could result in failure of
the propeller to perform properly. This
failure could lead to reduced or loss of
control of the sailplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect the propeller for any signs of damage.
Within 25 hours time-in-service (TIS) after
June 30, 2005 (the effective date of this
AD).
(2) If any damage is found during the inspection required in paragraph (e)(1) of this AD,
replace the propeller.
Before further flight after the inspection required in paragraph (e)(1) approved on this
AD.
(3) Insert the following language in the Limitations Section of the AFM:.
‘‘Caution: With high temperatures (temperature
on ground above 25 °C/77 °F) there is the
risk of overheating the propeller after engine
retraction. To avoid damage, extend the engine again via the manual switch (approx. 1
second) to open the engine doors. Retract
again after 5 minutes.’’
Within 25 hours TIS after June 30, 2005 (the
effective date of this AD).
Follow DG Flugzeugbau Technical Note No.
843/19 (LBA approved on April 7, 2004;
EASA approved on April 26, 2004); and DG
Flugzeugbau Technical Note 873/29 (LBA
approved on April 7, 2004; EASA approved
April 26, 2004), as applicable.
Follow DG Flugzeugbau Technical Note No.
843/19 (LBA approved on April 7, 2004;
EASA approved on April 26, 2004); and DG
Flugzeugbau Technical Note 873/29 (LBA
approved on April 7, 2004; EASA approved
April 26, 2004), as applicable.
The owner/operator holding at least a private
pilot certificate as authorized by section
43.7 of the Federal Aviation Regulations
(14 CFR 43.7) may do the flight manual
changes requirement of this AD. Make an
entry in the aircraft records showing compliance with this portion of the AD following
section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
Note: For Model DG–500MB sailplanes,
FAA recommends you install a polyurethane
shock absorber at the retaining cable
mounting in the fuselage. This is specified in
DG Flugzeugbau Technical Note No. 843/19
(LBA approved on April 7, 2004; EASA
approved on April 26, 2004). The
approximate cost to install the shock
absorber is $520 (4 work hours × $65 per
hour for labor = $260 + $260 for parts).
Starting with serial number 5E243B20 and
on, this shock absorber is being installed at
production.
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Standards Office, Small Airplane
Directorate, FAA. For information on any
already approved alternative methods of
compliance, contact Gregory Davison,
Aerospace Engineer, FAA, Small Airplane
Directorate, ACE–112, Room 301, 901 Locust,
Kansas City, Missouri 64106; telephone: 816–
329–4130; facsimile: 816–329–4090.
Is There Other Information That Relates to
This Subject?
Does This AD Incorporate Any Material by
Reference?
(h) You must do the actions required by
this AD following the DG Flugzeugbau
Technical Note No. 843/19 (LBA approved
on April 7, 2004; EASA approved on April
26, 2004); and DG Flugzeugbau Technical
Note 873/29 (LBA approved on April 7, 2004;
EASA approved April 26, 2004). The Director
of the Federal Register approved the
incorporation by reference of these service
bulletins in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. To get a copy of this
service information, contact DG Flugzeugbau,
Postbox 41 20, 76625 Bruchsal, Germany;
telephone, 49 7257 890; fax, 49 7257 8922.
To review copies of this service information,
go to the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. 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 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2004–19959; Directorate Identifier 2004–CE–
46–AD.
(g) German AD Number D–2004–195 and
AD Number D–2004–196, both dated April
23, 2004, also address the subject of this AD.
VerDate jul<14>2003
14:30 May 20, 2005
Jkt 205001
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Issued in Kansas City, Missouri, on May
13, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–9975 Filed 5–20–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20024; Directorate
Identifier 2004–NM–66–AD; Amendment 39–
14100; AD 2005–10–22]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–200C and 747–200F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Boeing Model 747–200C and 747–200F
series airplanes. This AD requires
repetitive inspections for cracking of the
left and right C–3 frame upper closure
fittings of the nose cargo door, and
E:\FR\FM\23MYR1.SGM
23MYR1
]]>Agencies
[Federal Register Volume 70, Number 98 (Monday, May 23, 2005)]
[Rules and Regulations]
[Pages 29440-29442]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-9975]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19959; Directorate Identifier 2004-CE-46-AD;
Amendment 39-14101; AD 2005-10-23]
RIN 2120-AA64
Airworthiness Directives; DG Flugzeugbau GmbH Model DG-500MB
Sailplanes and Glaser-Dirks Flugzeugbau GmbH Model DG-800B Sailplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for all DG
Flugzeugbau GmbH Model DG-500MB sailplanes equipped with a Solo engine
and Glaser-Dirks Flugzeugbau GmbH Model DG-800B sailplanes equipped
with a Solo engine. This AD requires you to inspect the propeller for
damage, specifically foam core separation, and replace any damaged
propeller. This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for Germany.
We are issuing this AD to detect and correct damage to the propeller,
which could result in failure of the propeller to perform properly.
This failure could lead to reduced or loss of control of the sailplane.
DATES: This AD becomes effective on June 30, 2005.
As of June 30, 2005, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
ADDRESSES: To get the service information identified in this AD,
contact DG Flugzeugbau, Postbox 41 20, 76625 Bruchsal, Germany;
telephone, 49 7257 890; fax, 49 7257 8922.
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 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2004-19959; Directorate
Identifier 2004-CE-46-AD.
FOR FURTHER INFORMATION CONTACT: Gregory Davison, Aerospace Engineer,
FAA, Small Airplane Directorate, ACE-112, Room 301, 901 Locust, Kansas
City, Missouri 64106; telephone: 816-329-4130; facsimile: 816-329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The Luftfahrt-Bundesamt (LBA),
which is the airworthiness authority for Germany, recently notified FAA
that an unsafe condition may exist on all DG Flugzeugbau GmbH Model DG-
500MB sailplanes equipped with a Solo engine and all Glaser-Dirks
Flugzeugbau GmbH Model DG-800B sailplanes equipped with a Solo engine.
The LBA reports that a damaged propeller was found on a Model DG-800B
sailplane.
The foam core inside the propeller separated and caused one blade
to be thicker than the other. The propeller became overheated after the
engine was retracted. This was possibly due to limited ventilation. The
LBA reports three occurrences of this condition.
The propeller on Model DG-500MB sailplanes equipped with a Solo
engine is of a similar design to Model DG-800B sailplanes equipped with
a Solo engine.
What is the potential impact if FAA took no action? If not detected
and corrected, damage to the propeller, specifically foam core
separation, could cause the propeller to fail to perform properly. This
failure could lead to reduced or loss of control of the sailplane.
[[Page 29441]]
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to all DG Flugzeugbau GmbH Model DG-
500MB sailplanes equipped with a Solo engine and Glaser-Dirks
Flugzeugbau GmbH Model DG-800B sailplanes equipped with a Solo engine.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on February 14, 2005 (70 FR 7443). The NPRM
proposed to require you to inspect the propeller for damage,
specifically foam core separation, and replace any damaged propeller.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. We received no
comments on the proposal or on the determination of the cost to the
public.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for minor
editorial corrections. We have determined that these minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many sailplanes does this AD impact? We estimate that this AD
affects 31 sailplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected sailplanes? We estimate the following costs to accomplish the
inspection:
----------------------------------------------------------------------------------------------------------------
Total cost
Labor cost Parts cost per Total cost on U.S. operators
sailplane
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour = $65 Not applicable................ $65 $65 x 31 = $2,015.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspection. We have
no way of determining the number of sailplanes that may need this
replacement:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost sailplane
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour = $65..................................... $4,000 $4,065.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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 AD.
Regulatory Findings
Will this AD impact various entities? We have 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.
Will this AD involve a significant rule or regulatory action? 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 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 summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2004-19959; Directorate Identifier 2004-CE-46-AD'' in your
request.
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 Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (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. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2005-10-23 DG Flugzeugbau GmbH and Glaser-Dirks Flugzeugbau GmbH:
Amendment 39-14101; Docket No. FAA-2004-19959; Directorate
Identifier 2004-CE-46-AD.
[[Page 29442]]
When Does This AD Become Effective?
(a) This AD becomes effective on June 30, 2005.
What Other ADs Are Affected By This Action?
(b) None.
What Sailplanes Are Affected By This AD?
(c) This AD affects all Model DG-500MB and DG-800B sailplanes
that are:
(1) Certificated in any category; and
(2) Equipped with a Solo engine.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Germany. The actions specified in this AD are intended to detect and
correct damage to the propeller, which could result in failure of
the propeller to perform properly. This failure could lead to
reduced or loss of control of the sailplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the propeller Within 25 hours time- Follow DG
for any signs of damage. in-service (TIS) Flugzeugbau
after June 30, 2005 Technical Note No.
(the effective date 843/19 (LBA
of this AD). approved on April
7, 2004; EASA
approved on April
26, 2004); and DG
Flugzeugbau
Technical Note 873/
29 (LBA approved on
April 7, 2004; EASA
approved April 26,
2004), as
applicable.
(2) If any damage is found Before further Follow DG
during the inspection flight after the Flugzeugbau
required in paragraph inspection required Technical Note No.
(e)(1) of this AD, replace in paragraph (e)(1) 843/19 (LBA
the propeller. approved on this AD. approved on April
7, 2004; EASA
approved on April
26, 2004); and DG
Flugzeugbau
Technical Note 873/
29 (LBA approved on
April 7, 2004; EASA
approved April 26,
2004), as
applicable.
(3) Insert the following Within 25 hours TIS The owner/operator
language in the Limitations after June 30, 2005 holding at least a
Section of the AFM:. (the effective date private pilot
``Caution: With high of this AD). certificate as
temperatures (temperature authorized by
on ground above 25 [deg]C/ section 43.7 of the
77 [deg]F) there is the Federal Aviation
risk of overheating the Regulations (14 CFR
propeller after engine 43.7) may do the
retraction. To avoid flight manual
damage, extend the engine changes requirement
again via the manual switch of this AD. Make an
(approx. 1 second) to open entry in the
the engine doors. Retract aircraft records
again after 5 minutes.''. showing compliance
with this portion
of the AD following
section 43.9 of the
Federal Aviation
Regulations (14 CFR
43.9).
------------------------------------------------------------------------
Note: For Model DG-500MB sailplanes, FAA recommends you install
a polyurethane shock absorber at the retaining cable mounting in the
fuselage. This is specified in DG Flugzeugbau Technical Note No.
843/19 (LBA approved on April 7, 2004; EASA approved on April 26,
2004). The approximate cost to install the shock absorber is $520 (4
work hours x $65 per hour for labor = $260 + $260 for parts).
Starting with serial number 5E243B20 and on, this shock absorber
is being installed at production.
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, contact Gregory Davison,
Aerospace Engineer, FAA, Small Airplane Directorate, ACE-112, Room
301, 901 Locust, Kansas City, Missouri 64106; telephone: 816-329-
4130; facsimile: 816-329-4090.
Is There Other Information That Relates to This Subject?
(g) German AD Number D-2004-195 and AD Number D-2004-196, both
dated April 23, 2004, also address the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the DG
Flugzeugbau Technical Note No. 843/19 (LBA approved on April 7,
2004; EASA approved on April 26, 2004); and DG Flugzeugbau Technical
Note 873/29 (LBA approved on April 7, 2004; EASA approved April 26,
2004). The Director of the Federal Register approved the
incorporation by reference of these service bulletins in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this
service information, contact DG Flugzeugbau, Postbox 41 20, 76625
Bruchsal, Germany; telephone, 49 7257 890; fax, 49 7257 8922. To
review copies of this service information, go to the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, go to: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html or call (202) 741-6030. 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 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2004-19959; Directorate
Identifier 2004-CE-46-AD.
Issued in Kansas City, Missouri, on May 13, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-9975 Filed 5-20-05; 8:45 am]
BILLING CODE 4910-13-P
