Airworthiness Directives; Stemme GmbH & Co. KG Models STEMME S10-V and STEMME S10-VT Powered Sailplanes, 20072-20075 [E7-7642]
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20072
Federal Register / Vol. 72, No. 77 / Monday, April 23, 2007 / Proposed Rules
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
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 regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Alpha Aviation Design Limited (Type
Certificate No. A48EU previously held
by APEX Aircraft and AVIONS PIERRE
ROBIN): Docket No. FAA–2006–26494;
Directorate Identifier 2006–CE–79–AD.
Comments Due Date
(a) We must receive comments by May 23,
2007.
pwalker on PROD1PC71 with PROPOSALS
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model R2160
airplanes, serial numbers 001 through 378,
certificated in any category.
Subject
(d) Air Transport Association of America
(ATA) Code 57: Wings.
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16:49 Apr 20, 2007
Jkt 211001
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
To prevent unchecked corrosion
developing on the wing spars due to access
for inspections being difficult under normal
maintenance practices, which could lead to
an unsafe condition and possibly a
catastrophic failure of the wing accomplish
the following:
The MCAI requires inspecting the visible
parts of the spar web and the upper and
lower boom angles (top and bottom spar
caps) for corrosion and correcting as
necessary.
Actions and Compliance
(f) Unless already done, do the following
actions. Accomplishment of European
Aviation Safety Agency (EASA) AD 2005–
0028 satisfies the requirement of this AD:
(1) Within 66 months after aircraft date of
manufacture or within 6 months after the
effective date of this AD, whichever occurs
later, unless already done within the last 24
months, and thereafter at intervals not to
exceed 24 months, remove the main landing
gear legs and all the wing inspection panels
following the instructions in the aircraft
maintenance manual and inspect the visible
parts of the spar web and the upper and
lower boom angles (top and bottom spar
caps), following Avions Pierre Robin Service
Letter No. 19, dated October 1980; and
Avions Pierre Robin Service Bulletin No. 99,
dated June 24, 1983. If the spars are replaced,
the inspections at intervals of 24 months
must be resumed within 60 months from the
date of replacement.
(2) Before further flight, if corrosion is
found on the rear face of the spar web or the
upper and lower boom angles, then inspect
the front face of the spar for corrosion
following Avions Pierre Robin Service Letter
No. 19, dated October 1980; and Avions
Pierre Robin Service Bulletin No. 99, dated
June 24, 1983. It may be necessary to cut
inspection holes or remove the wings to
inspect the front face of the spar. Inspection
holes must be prepared to a manufacturerapproved repair scheme.
(3) Before further flight, treat corrosion
following Avions Pierre Robin Service Letter
No. 19, dated October 1980; and Avions
Pierre Robin Service Bulletin No. 99, dated
June 24, 1983.
(4) Before further flight, if corrosion is
found which exceeds the limits specified in
Avions Pierre Robin Service Letter No. 19,
dated October 1980, repair following an
approved repair scheme.
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 2120–0056.
Related Information
(h) Refer to MCAI Civil Aviation Authority
of New Zealand AD DCA/R2000/37A, dated
December 21, 2006; Avions Pierre Robin
Service Letter No. 19, dated October 1980;
and Avions Pierre Robin Service Bulletin No.
99, dated June 24, 1983, for related
information.
Issued in Kansas City, Missouri, on April
17, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–7644 Filed 4–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27431; Directorate
Identifier 2007–CE–016–AD]
RIN 2120–AA64
Airworthiness Directives; Stemme
GmbH & Co. KG Models STEMME S10–
V and STEMME S10–VT Powered
Sailplanes
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
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: Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4146; fax: (816)
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
FAA AD Differences
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AGENCY:
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Federal Register / Vol. 72, No. 77 / Monday, April 23, 2007 / Proposed Rules
product. The MCAI describes the unsafe
condition as:
Service experience showed that the
connection screw of the propeller blade
follower type 10AP–VM may break and the
main part of the blade follower can be lost
in flight. This condition, if not corrected,
could lead to high vibration during powered
flight and consequently result in decreased
control of the aircraft.
Stemme has developed a new blade
follower, Model 10AP–VP, which is
reinforced on the shaft and has an Allen head
screw installed instead of a slotted screw. For
the reason stated above, this Emergency
Airworthiness Directive (EAD) requires the
replacement of the blade follower type
10AP–VM with the new type 10AP–VP.
This EAD has been revised to correct the
TCDS reference and the applicability
statement. No separate TC was issued for the
affected propellers. These propellers are part
of the aircraft type design.
Paragraph (4) of the ‘‘Compliance’’ section
of this EAD has been corrected.
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by May 23, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
pwalker on PROD1PC71 with PROPOSALS
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 this
proposed AD, the regulatory evaluation,
any comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) 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 Airplane Directorate, 901
Locust, Room 301, Kansas City,
VerDate Aug<31>2005
16:49 Apr 20, 2007
Jkt 211001
Missouri 64106; telephone: (816) 329–
4130; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–27431; Directorate Identifier
2007–CE–016–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Emergency AD No. 2006–0373R1–E,
dated December 15, 2006, corrected
January 5, 2007 (referred to after this as
‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Service experience showed that the
connection screw of the propeller blade
follower type 10AP–VM may break and the
main part of the blade follower can be lost
in flight. This condition, if not corrected,
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20073
could lead to high vibration during powered
flight and consequently result in decreased
control of the aircraft.
Stemme has developed a new blade
follower, Model 10AP–VP, which is
reinforced on the shaft and has an Allen head
screw installed instead of a slotted screw. For
the reason stated above, this Emergency
Airworthiness Directive (EAD) requires the
replacement of the blade follower type
10AP–VM with the new type 10AP–VP.
This EAD has been revised to correct the
TCDS reference and the applicability
statement. No separate TC was issued for the
affected propellers. These propellers are part
of the aircraft type design.
Paragraph (4) of the ‘‘Compliance’’ section
of this EAD has been corrected.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Stemme GmbH & Co. KG has issued
STEMME F & D Service Bulletin (SB)
A31–10–078, Am.-Index: 01.a, dated
November 6, 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 Proposed 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 proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed 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 also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a note within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
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20074
Federal Register / Vol. 72, No. 77 / Monday, April 23, 2007 / Proposed Rules
affect about 53 products of U.S. registry.
We also estimate that it would take
about 3 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Required
parts would cost about $117 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these costs. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here.
Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators to be $18,921, or $357 per
product.
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.
pwalker on PROD1PC71 with PROPOSALS
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
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.
16:49 Apr 20, 2007
Jkt 211001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Authority for This Rulemaking
VerDate Aug<31>2005
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Stemme GmbH & Co. KG Models STEMME
S10–V and STEMME S10–VT Powered
Sailplanes: Docket No. FAA–2007–
27431; Directorate Identifier 2007–CE–
016–AD.
Comments Due Date
(a) We must receive comments by May 23,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models STEMME
S10–V and STEMME S10–VT powered
sailplanes, all serial numbers, certificated in
any category.
Subject
(d) Air Transport Association of America
(ATA) Code 61: Propellers.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Service experience showed that the
connection screw of the propeller blade
follower type 10AP–VM may break and the
main part of the blade follower can be lost
in flight. This condition, if not corrected,
could lead to high vibration during powered
flight and consequently result in decreased
control of the aircraft.
Stemme has developed a new blade
follower, Model 10AP–VP, which is
reinforced on the shaft and has an Allen head
screw installed instead of a slotted screw. For
the reason stated above, this Emergency
Airworthiness Directive (EAD) requires the
replacement of the blade follower type
10AP–VM with the new type 10AP–VP.
This EAD has been revised to correct the
TCDS reference and the applicability
statement. No separate TC was issued for the
affected propellers. These propellers are part
of the aircraft type design.
Paragraph (4) of the ‘‘Compliance’’ section
of this EAD has been corrected.
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Fmt 4702
Sfmt 4702
Actions and Compliance
(f) Unless already done, within 25 engine
operating hours or 90 days after the effective
date of this AD, whichever occurs first, do
the following actions:
(1) Replace the blade follower type 10AP–
VM with the new type 10AP–VP following
the instructions contained in STEMME F &
D SB A31–10–078, Am.-index: 01.a, dated
November 6, 2006.
(2) As of 25 engine operating hours or 90
days after the effective date of this AD, do not
install a propeller type 10AP–F, 10AP–V or
11AP–V on any aircraft, unless that propeller
has the new type 10AP–VP blade follower
installed following the instructions contained
in STEMME F & D SB A31–10–078, Am.index: 01.a, dated November 6, 2006.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: The MCAI
requires an amendment to the aircraft flight
manual before further flight as an interim
requirement to the replacement. We consider
before flight as an urgent safety of flight
compliance time, and we do not consider this
unsafe condition to be an urgent safety of
flight condition. We feel that 25 engine
operating hours or 90 days, whichever occurs
first, for the replacement is an adequate
compliance for this AD action and meets the
FAA requirements of a notice of proposed
rulemaking (NPRM). We do encourage you to
incorporate these flight manual amendments
referenced in the MCAI and service
information until you replace the propeller
blade follower.
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 2120–0056.
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Federal Register / Vol. 72, No. 77 / Monday, April 23, 2007 / Proposed Rules
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Emergency AD No.:
2006–0373R1–E, dated December 15, 2006,
corrected January 5, 2007; and STEMME F &
D SB A31–10–078, Am.-index: 01.a, dated
November 6, 2006, for related information.
Issued in Kansas City, Missouri, on April
17, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–7642 Filed 4–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27229; Directorate
Identifier 2007–NE–03–AD]
RIN 2120–AA64
Comments Invited
Airworthiness Directives; CFM
International, S.A. CFM56–7B Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
pwalker on PROD1PC71 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
CFM International, S.A. CFM56–7B
Series Turbofan Engines. This proposed
AD would require revising the
Airworthiness Limitations Section
(ALS) in the Engine Shop Manual (ESM)
and the air carrier’s approved
continuous airworthiness maintenance
program (CAMP) to add mandatory
inspections of certain low pressure
turbine rear frames (TRFs) to the ALS or
CAMP. This proposed AD results from
a refined lifing analysis by the engine
manufacturer that shows the need to
identify an initial threshold for
inspecting certain TRFs. We are
proposing this AD to prevent failure of
the TRF from low-cycle fatigue cracks.
Failure of the TRF could result in
engine separation from the airplane,
which could lead to loss of control of
the airplane.
DATES: We must receive any comments
on this proposed AD by June 22, 2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
VerDate Aug<31>2005
16:49 Apr 20, 2007
Jkt 211001
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You may examine the comments on
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
Colleen M. D’Alessandro, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803; telephone (781)
238–7133; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2007–27229; Directorate Identifier
2007–NE–03–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the DOT
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78) or you may visit https://
dms.dot.gov.
Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received and, any final disposition in
person at the DOT Docket Offices
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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20075
The Docket Office (telephone (800) 647–
5227) is located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the
Docket Management Facility receives
them.
Discussion
This AD is required because TRFs,
part numbers 340–166–205–0, 340–166–
206–0, 340–166–207–0, 340–166–208–0,
340–166–209–0, 340–166–210–0, now
require an initial inspection threshold of
25,000 cycles-in-service (CIS) on the
commercial (air carrier) models engines
and 19,000 CIS on the business jet
models. This proposed AD would not
affect any other CFM56–7B part number
TRFs. We have been monitoring CFM’s
revised life analysis progress since
February 2005. CFM International
provided to us the November 15, 2006
revision to the ESM to introduce
mandatory inspections of the TRF. CFM
International has been using a damage
tolerant lifing approach, based on an
FAA approved methodology for
structural lifed components, to prepare
life extensions for all CFM56 TRFs
using on-condition life management.
This improved life management process
defines a first inspection threshold and
reinspection intervals accounting for
crack initiation and propagation. The
previous life management process was
based on crack initiation only. This
condition, if not corrected, could result
in failure of the TRF from low-cycle
fatigue cracks. Failure of the TRF could
result in engine separation from the
airplane, which could lead to loss of
control of the airplane.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require revising the
Airworthiness Limitations Section in
the ESM and the air carrier’s approved
continuing airworthiness maintenance
program to incorporate life reductions
for certain TRFs.
Costs of Compliance
We estimate that this proposed AD
would affect 1,228 engines installed on
airplanes of U.S. registry. Since life
extensions are possible on condition,
the cost of the proposed AD will be
limited to performing TRF inspections.
We also estimate that it would take
about 3.0 work-hours per engine to
perform the proposed actions, including
E:\FR\FM\23APP1.SGM
23APP1
]]>Agencies
[Federal Register Volume 72, Number 77 (Monday, April 23, 2007)]
[Proposed Rules]
[Pages 20072-20075]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-7642]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27431; Directorate Identifier 2007-CE-016-AD]
RIN 2120-AA64
Airworthiness Directives; Stemme GmbH & Co. KG Models STEMME S10-
V and STEMME S10-VT Powered Sailplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation
[[Page 20073]]
product. The MCAI describes the unsafe condition as:
Service experience showed that the connection screw of the
propeller blade follower type 10AP-VM may break and the main part of
the blade follower can be lost in flight. This condition, if not
corrected, could lead to high vibration during powered flight and
consequently result in decreased control of the aircraft.
Stemme has developed a new blade follower, Model 10AP-VP, which
is reinforced on the shaft and has an Allen head screw installed
instead of a slotted screw. For the reason stated above, this
Emergency Airworthiness Directive (EAD) requires the replacement of
the blade follower type 10AP-VM with the new type 10AP-VP.
This EAD has been revised to correct the TCDS reference and the
applicability statement. No separate TC was issued for the affected
propellers. These propellers are part of the aircraft type design.
Paragraph (4) of the ``Compliance'' section of this EAD has been
corrected.
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by May 23, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
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 this proposed AD, the regulatory evaluation, any
comments received, and other information. The street address for the
Docket Office (telephone (800) 647-5227) 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 Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4130; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
27431; Directorate Identifier 2007-CE-016-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Emergency AD No. 2006-0373R1-E, dated December 15, 2006, corrected
January 5, 2007 (referred to after this as ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
Service experience showed that the connection screw of the
propeller blade follower type 10AP-VM may break and the main part of
the blade follower can be lost in flight. This condition, if not
corrected, could lead to high vibration during powered flight and
consequently result in decreased control of the aircraft.
Stemme has developed a new blade follower, Model 10AP-VP, which
is reinforced on the shaft and has an Allen head screw installed
instead of a slotted screw. For the reason stated above, this
Emergency Airworthiness Directive (EAD) requires the replacement of
the blade follower type 10AP-VM with the new type 10AP-VP.
This EAD has been revised to correct the TCDS reference and the
applicability statement. No separate TC was issued for the affected
propellers. These propellers are part of the aircraft type design.
Paragraph (4) of the ``Compliance'' section of this EAD has been
corrected.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Stemme GmbH & Co. KG has issued STEMME F & D Service Bulletin (SB)
A31-10-078, Am.-Index: 01.a, dated November 6, 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 Proposed 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 proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed 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 also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would
[[Page 20074]]
affect about 53 products of U.S. registry. We also estimate that it
would take about 3 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $117 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these costs.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $18,921, or $357 per product.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Stemme GmbH & Co. KG Models STEMME S10-V and STEMME S10-VT Powered
Sailplanes: Docket No. FAA-2007-27431; Directorate Identifier 2007-
CE-016-AD.
Comments Due Date
(a) We must receive comments by May 23, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models STEMME S10-V and STEMME S10-VT
powered sailplanes, all serial numbers, certificated in any
category.
Subject
(d) Air Transport Association of America (ATA) Code 61:
Propellers.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states: Service experience showed that the connection screw of the
propeller blade follower type 10AP-VM may break and the main part of
the blade follower can be lost in flight. This condition, if not
corrected, could lead to high vibration during powered flight and
consequently result in decreased control of the aircraft.
Stemme has developed a new blade follower, Model 10AP-VP, which
is reinforced on the shaft and has an Allen head screw installed
instead of a slotted screw. For the reason stated above, this
Emergency Airworthiness Directive (EAD) requires the replacement of
the blade follower type 10AP-VM with the new type 10AP-VP.
This EAD has been revised to correct the TCDS reference and the
applicability statement. No separate TC was issued for the affected
propellers. These propellers are part of the aircraft type design.
Paragraph (4) of the ``Compliance'' section of this EAD has been
corrected.
Actions and Compliance
(f) Unless already done, within 25 engine operating hours or 90
days after the effective date of this AD, whichever occurs first, do
the following actions:
(1) Replace the blade follower type 10AP-VM with the new type
10AP-VP following the instructions contained in STEMME F & D SB A31-
10-078, Am.-index: 01.a, dated November 6, 2006.
(2) As of 25 engine operating hours or 90 days after the
effective date of this AD, do not install a propeller type 10AP-F,
10AP-V or 11AP-V on any aircraft, unless that propeller has the new
type 10AP-VP blade follower installed following the instructions
contained in STEMME F & D SB A31-10-078, Am.-index: 01.a, dated
November 6, 2006.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: The MCAI requires an amendment to the aircraft flight
manual before further flight as an interim requirement to the
replacement. We consider before flight as an urgent safety of flight
compliance time, and we do not consider this unsafe condition to be
an urgent safety of flight condition. We feel that 25 engine
operating hours or 90 days, whichever occurs first, for the
replacement is an adequate compliance for this AD action and meets
the FAA requirements of a notice of proposed rulemaking (NPRM). We
do encourage you to incorporate these flight manual amendments
referenced in the MCAI and service information until you replace the
propeller blade follower.
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 2120-0056.
[[Page 20075]]
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA)
Emergency AD No.: 2006-0373R1-E, dated December 15, 2006, corrected
January 5, 2007; and STEMME F & D SB A31-10-078, Am.-index: 01.a,
dated November 6, 2006, for related information.
Issued in Kansas City, Missouri, on April 17, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-7642 Filed 4-20-07; 8:45 am]
BILLING CODE 4910-13-P
