Airworthiness Directives; APEX Aircraft (Type Certificate No. A36EU Formerly Held by AVIONS MUDRY et CIE) Model CAP 10 B Airplanes, 21077-21079 [E7-7980]
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21077
Rules and Regulations
Federal Register
Vol. 72, No. 82
Monday, April 30, 2007
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27529; Directorate
Identifier 2007–CE–018–AD; Amendment
39–15038; AD 2007–09–06]
RIN 2120–AA64
Airworthiness Directives; APEX
Aircraft (Type Certificate No. A36EU
Formerly Held by AVIONS MUDRY et
CIE) Model CAP 10 B Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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
SUMMARY:
pwalker on PROD1PC71 with RULES
Several recent inspections have revealed
that some spar wooden centre blocks have
shown cracks. Investigation revealed that
cracks are generated by the wood drying.
Actions specified in this AD are intended to
detect and correct any defects on the central
wing spar block.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective May
21, 2007.
On May 21, 2007 the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
We must receive any comments on
this AD by June 4, 2007.
ADDRESSES: You may send comments by
any of the following methods:
VerDate Aug<31>2005
16:27 Apr 27, 2007
Jkt 211001
• 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: 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
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: Mr.
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; 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. The 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 AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
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Frm 00001
Fmt 4700
Sfmt 4700
MCAI and for this reason might not
follow our plain language principles.
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–
0015, dated January 12, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products.
The MCAI states:
Several recent inspections have revealed
that some spar wooden centre blocks have
shown cracks. Investigation revealed that
cracks are generated by the wood drying.
Actions specified in this AD are intended to
detect and correct any defects on the central
wing spar block.
This AD is requiring the installation of two
reinforcement plates on the wing spar to
counter the shear loading, implementation of
corrective actions to slow down the wood
drying and is also introducing new repetitive
inspections.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
APEX Aircraft has issued Service
Bulletin No. 060307 R1, Amendment
date November 2, 2006; Apex Aircraft
CAP10C—Main Spar Wooden Center
Block—Reinforcement Instructions No.
1001766, dated October 6, 2006; and
Apex Aircraft Document No. 1001133–
A, DR400 Spar Consolidation, Applying
Araldite 2015 Adhesive, dated February
4, 2003. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This 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.
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21078
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations
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 of cracks found on the
central wing spar block. 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.
pwalker on PROD1PC71 with RULES
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–2007–27529;
Directorate Identifier 2007–CE–018–
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://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
VerDate Aug<31>2005
16:27 Apr 27, 2007
Jkt 211001
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 amends14 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
2007–09–06 APEX Aircraft (Type
Certificate No. A36EU formerly held by
AVIONS MUDRY et CIE): Amendment
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
39–15038; Docket No. FAA–2007–27529;
Directorate Identifier 2007–CE–018–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 21, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model CAP 10 B
airplanes, all serial numbers, that are:
(1) Certificated in any category; and
(2) fitted with major change 000302, wood/
carbon-made wings, part-number
11.56.00.010, serial numbers 001 to 084
inclusive.
Subject
(d) Air Transport Association of America
(ATA) Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Several recent inspections have revealed
that some spar wooden center blocks have
shown cracks. Investigation revealed that
cracks are generated by the wood drying.
Actions specified in this AD are intended to
detect and correct any defects on the central
wing spar block.
This AD is requiring the installation of two
reinforcement plates on the wing spar to
counter the shear loading, implementation of
corrective actions to slow down the wood
drying and is also introducing new repetitive
inspections.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Before further flight after May 21, 2007
(the effective date of this AD):
(i) Fabricate a placard that incorporates the
following words (using at least 1⁄8-inch
letters) and install this placard on the
instrument panel within the pilot’s clear
view: ‘‘FLICK MANEUVERS ARE
PROHIBITED’’; and
(ii) Insert a copy of this AD into the
Limitations section of the Pilot’s Operating
Handbook (POH).
(iii) 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 fabricate the
placard required in paragraph (f)(1)(i) of this
AD and may insert the information into the
POH as required in paragraph (f)(1)(ii) of this
AD. Make an entry into the aircraft records
showing compliance with these portions of
the AD in accordance with section 43.9 of the
Federal Aviation Regulations (14 CFR 43.9).
(2) Within the next 50 hours time-inservice (TIS) after May 21, 2007 (the effective
date of this AD), inspect the front and rear
spar webs for cracks and damage using Apex
Aircraft Service Bulletin No. 060307 R1,
Amendment date November 2, 2006.
(3) If any crack or damage is found during
the inspection required in paragraph (f)(2) of
this AD, the wing must be considered as
unairworthy until the implementation of the
relevant repair solution. Before further flight,
contact Apex Aircraft to obtain a repair
E:\FR\FM\30APR1.SGM
30APR1
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations
solution and incorporate the repair.
Continued operation with cracks in the front
and rear spar webs is prohibited.
(4) If no cracks or damages are found in
either the rear or the front wing spar web
during the inspection required in paragraph
(f)(2) of this AD, before further flight install
reinforcement plates, part number
97.56.00.002, using Apex Aircraft CAP10C—
Main Spar Wooden Center Block—
Reinforcement Instructions No. 1001766–A,
dated June 10, 2006; and Apex Aircraft
Document No. 1001133–A, DR400 Spar
Consolidation, Applying Araldite 2015
Adhesive, dated February 4, 2003.
(5) After doing the actions required in
paragraphs (f)(2), (f)(3), and (f)(4) of this AD:
(i) Flick maneuvers previously prohibited
by paragraph (f)(1) of this AD are now
permitted. Before further flight, remove the
placard required in paragraph (f)(1)(i) of this
AD and remove the insertion into the POH
required in paragraph (f)(1)(ii) of this AD.
(ii) Repetitively inspect the front and rear
spar webs for cracks and damage thereafter
at intervals not to exceed 13 months using
Apex Aircraft Service Bulletin No. 060307
R1, Amendment date November 2, 2006; and
(iii) If any crack or damage is found during
any inspection required by paragraph
(f)(5)(ii) this AD, before further flight contact
Apex Aircraft to obtain a repair solution and
incorporate the repair.
(6) After 50 hours TIS after May 21, 2007
(the effective date of this AD), do not install
an Apex Aircraft wood/carbon-made wing,
part number 11.56.00.010, unless it has been
inspected and is found to be crack free and
modified using Apex Aircraft Service
Bulletin No. 060307 R1, Amendment date
November 2, 2006; and Apex Aircraft
CAP10C—Main Spar Wooden Center Block—
Reinforcement Instructions No. 1001766–A,
dated October 6, 2006.
FAA AD Differences
pwalker on PROD1PC71 with RULES
Note: This AD differs from the MCAI and/
or service information as follows: The MCAI
allows continued flight if cracks are found in
the wing spar webs that do not exceed certain
limits. The applicable service bulletin
specifies replacing the wing spar webs only
if cracks are found exceeding limits specified
in Apex Aircraft Service Bulletin No. 060307
R1, Amendment date November 2, 2006, as
does the MCAI. This AD does not allow
continued flight if any crack is found. FAA
policy is to disallow airplane operation when
known cracks exist in primary structure,
unless the ability to sustain ultimate load
with these cracks is proven. The wing spar
webs are considered primary structure, and
the FAA has not received any analysis to
prove that ultimate load can be sustained
with cracks in these areas.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, Small Airplane Directorate, ATTN:
Sarjapur Nagarajan, Aerospace Engineer, 901
Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; fax: (816)
329–4090, has the authority to approve
VerDate Aug<31>2005
16:27 Apr 27, 2007
Jkt 211001
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 FAAapproved 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 European Aviation
Safety Agency (EASA) AD No. 2007–0015,
dated January 12, 2007; Apex Aircraft Service
Bulletin No. 060307 R1, Amendment dated
November 2, 2006; Apex Aircraft CAP10C—
Main Spar Wooden Center Block—
Reinforcement Instructions No. 1001766,
dated October 6, 2006; and Apex Aircraft
Document No. 1001133–A, DR400 Spar
Consolidation, Applying Araldite 2015
Adhesive, dated February 4, 2003, for related
information.
Material Incorporated by Reference
(i) You must use Apex Aircraft Service
Bulletin No. 060307 R1, Amendment date
November 2, 2006; Apex Aircraft CAP10C—
Main Spar Wooden Center Block—
Reinforcement Instructions No. 1001766–A,
dated October 6, 2006; and Apex Aircraft
Document No. 1001133–A, DR400 Spar
Consolidation, Applying Araldite 2015
Adhesive, dated February 4, 2003, 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 Apex Aircraft, Bureau de
Navigabilit, 1 route de Troyes, 21121
DAROIS—France, telephone: (33) 380 35 65
10; fax: (33) 380 35 65 15; e-mail: apexaircraft.com.
(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.
PO 00000
Frm 00003
Fmt 4700
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21079
Issued in Kansas City, Missouri on April
20, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–7980 Filed 4–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23842; Directorate
Identifier 2005–NM–145–AD; Amendment
39–15034; AD 2007–09–04]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200, 777–300, and 777–
300ER 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 certain
Boeing Model 777–200, 777–300, and
777–300ER series airplanes. This AD
requires repetitive inspections for
discrepancies of the splined
components that support the inboard
end of the inboard trailing edge flap;
related investigative, corrective, and
other specified actions if necessary; a
one-time modification of the inboard
support of the inboard trailing edge flap
by installing a new isolation strap and
attachment hardware; and repetitive
replacement of the torque tube
assembly. For certain Boeing Model
777–200 series airplanes, this AD also
specifies prior or concurrent
accomplishment of one-time inspections
of the flap seal panels for cracking and
minimum clearances, and of the torque
tubes for damage; and related
investigative and corrective actions if
necessary. This AD also provides a
terminating action (modification of the
inboard main flap) for the repetitive
inspections. This AD results from
reports of corrosion on the torque tube
and closeout rib fittings that support the
inboard end of the inboard trailing edge
flap, as well as a structural reassessment
of the torque tube joint that revealed the
potential for premature fatigue cracking
of the torque tube that would not be
detected using reasonable inspection
methods. We are issuing this AD to
detect and correct corrosion or cracking
of the torque tube and closeout rib
fittings that support the inboard end of
the inboard trailing edge flap. Cracking
in these components could lead to a
E:\FR\FM\30APR1.SGM
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Agencies
[Federal Register Volume 72, Number 82 (Monday, April 30, 2007)]
[Rules and Regulations]
[Pages 21077-21079]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-7980]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules
and Regulations
[[Page 21077]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27529; Directorate Identifier 2007-CE-018-AD;
Amendment 39-15038; AD 2007-09-06]
RIN 2120-AA64
Airworthiness Directives; APEX Aircraft (Type Certificate No.
A36EU Formerly Held by AVIONS MUDRY et CIE) Model CAP 10 B Airplanes
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
Several recent inspections have revealed that some spar wooden
centre blocks have shown cracks. Investigation revealed that cracks
are generated by the wood drying. Actions specified in this AD are
intended to detect and correct any defects on the central wing spar
block.
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective May 21, 2007.
On May 21, 2007 the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
We must receive any comments on this AD by June 4, 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: 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 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: Mr. Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4145; 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. The 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 AD references the MCAI and related service information that we
considered in forming the engineering basis to correct the unsafe
condition. The AD contains text copied from the MCAI and for this
reason might not follow our plain language principles.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No. 2007-0015, dated January 12, 2007 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products.
The MCAI states:
Several recent inspections have revealed that some spar wooden
centre blocks have shown cracks. Investigation revealed that cracks
are generated by the wood drying. Actions specified in this AD are
intended to detect and correct any defects on the central wing spar
block.
This AD is requiring the installation of two reinforcement
plates on the wing spar to counter the shear loading, implementation
of corrective actions to slow down the wood drying and is also
introducing new repetitive inspections.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
APEX Aircraft has issued Service Bulletin No. 060307 R1, Amendment
date November 2, 2006; Apex Aircraft CAP10C--Main Spar Wooden Center
Block--Reinforcement Instructions No. 1001766, dated October 6, 2006;
and Apex Aircraft Document No. 1001133-A, DR400 Spar Consolidation,
Applying Araldite 2015 Adhesive, dated February 4, 2003. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This 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.
[[Page 21078]]
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 of
cracks found on the central wing spar block. 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-2007-27529; Directorate
Identifier 2007-CE-018-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://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive about this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends14 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:
2007-09-06 APEX Aircraft (Type Certificate No. A36EU formerly held
by AVIONS MUDRY et CIE): Amendment 39-15038; Docket No. FAA-2007-
27529; Directorate Identifier 2007-CE-018-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 21,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model CAP 10 B airplanes, all serial
numbers, that are:
(1) Certificated in any category; and
(2) fitted with major change 000302, wood/carbon-made wings,
part-number 11.56.00.010, serial numbers 001 to 084 inclusive.
Subject
(d) Air Transport Association of America (ATA) Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Several recent inspections have revealed that some spar wooden
center blocks have shown cracks. Investigation revealed that cracks
are generated by the wood drying. Actions specified in this AD are
intended to detect and correct any defects on the central wing spar
block.
This AD is requiring the installation of two reinforcement
plates on the wing spar to counter the shear loading, implementation
of corrective actions to slow down the wood drying and is also
introducing new repetitive inspections.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) Before further flight after May 21, 2007 (the effective date
of this AD):
(i) Fabricate a placard that incorporates the following words
(using at least \1/8\-inch letters) and install this placard on the
instrument panel within the pilot's clear view: ``FLICK MANEUVERS
ARE PROHIBITED''; and
(ii) Insert a copy of this AD into the Limitations section of
the Pilot's Operating Handbook (POH).
(iii) 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 fabricate the placard required in
paragraph (f)(1)(i) of this AD and may insert the information into
the POH as required in paragraph (f)(1)(ii) of this AD. Make an
entry into the aircraft records showing compliance with these
portions of the AD in accordance with section 43.9 of the Federal
Aviation Regulations (14 CFR 43.9).
(2) Within the next 50 hours time-in-service (TIS) after May 21,
2007 (the effective date of this AD), inspect the front and rear
spar webs for cracks and damage using Apex Aircraft Service Bulletin
No. 060307 R1, Amendment date November 2, 2006.
(3) If any crack or damage is found during the inspection
required in paragraph (f)(2) of this AD, the wing must be considered
as unairworthy until the implementation of the relevant repair
solution. Before further flight, contact Apex Aircraft to obtain a
repair
[[Page 21079]]
solution and incorporate the repair. Continued operation with cracks
in the front and rear spar webs is prohibited.
(4) If no cracks or damages are found in either the rear or the
front wing spar web during the inspection required in paragraph
(f)(2) of this AD, before further flight install reinforcement
plates, part number 97.56.00.002, using Apex Aircraft CAP10C--Main
Spar Wooden Center Block--Reinforcement Instructions No. 1001766-A,
dated June 10, 2006; and Apex Aircraft Document No. 1001133-A, DR400
Spar Consolidation, Applying Araldite 2015 Adhesive, dated February
4, 2003.
(5) After doing the actions required in paragraphs (f)(2),
(f)(3), and (f)(4) of this AD:
(i) Flick maneuvers previously prohibited by paragraph (f)(1) of
this AD are now permitted. Before further flight, remove the placard
required in paragraph (f)(1)(i) of this AD and remove the insertion
into the POH required in paragraph (f)(1)(ii) of this AD.
(ii) Repetitively inspect the front and rear spar webs for
cracks and damage thereafter at intervals not to exceed 13 months
using Apex Aircraft Service Bulletin No. 060307 R1, Amendment date
November 2, 2006; and
(iii) If any crack or damage is found during any inspection
required by paragraph (f)(5)(ii) this AD, before further flight
contact Apex Aircraft to obtain a repair solution and incorporate
the repair.
(6) After 50 hours TIS after May 21, 2007 (the effective date of
this AD), do not install an Apex Aircraft wood/carbon-made wing,
part number 11.56.00.010, unless it has been inspected and is found
to be crack free and modified using Apex Aircraft Service Bulletin
No. 060307 R1, Amendment date November 2, 2006; and Apex Aircraft
CAP10C--Main Spar Wooden Center Block--Reinforcement Instructions
No. 1001766-A, dated October 6, 2006.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: The MCAI allows continued flight if cracks are found in
the wing spar webs that do not exceed certain limits. The applicable
service bulletin specifies replacing the wing spar webs only if
cracks are found exceeding limits specified in Apex Aircraft Service
Bulletin No. 060307 R1, Amendment date November 2, 2006, as does the
MCAI. This AD does not allow continued flight if any crack is found.
FAA policy is to disallow airplane operation when known cracks exist
in primary structure, unless the ability to sustain ultimate load
with these cracks is proven. The wing spar webs are considered
primary structure, and the FAA has not received any analysis to
prove that ultimate load can be sustained with cracks in these
areas.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Staff, FAA, Small Airplane Directorate, ATTN: Sarjapur
Nagarajan, Aerospace Engineer, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4145; 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.
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA) AD No.
2007-0015, dated January 12, 2007; Apex Aircraft Service Bulletin
No. 060307 R1, Amendment dated November 2, 2006; Apex Aircraft
CAP10C--Main Spar Wooden Center Block--Reinforcement Instructions
No. 1001766, dated October 6, 2006; and Apex Aircraft Document No.
1001133-A, DR400 Spar Consolidation, Applying Araldite 2015
Adhesive, dated February 4, 2003, for related information.
Material Incorporated by Reference
(i) You must use Apex Aircraft Service Bulletin No. 060307 R1,
Amendment date November 2, 2006; Apex Aircraft CAP10C--Main Spar
Wooden Center Block--Reinforcement Instructions No. 1001766-A, dated
October 6, 2006; and Apex Aircraft Document No. 1001133-A, DR400
Spar Consolidation, Applying Araldite 2015 Adhesive, dated February
4, 2003, 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 Apex
Aircraft, Bureau de Navigabilit, 1 route de Troyes, 21121 DAROIS--
France, telephone: (33) 380 35 65 10; fax: (33) 380 35 65 15; e-
mail: apex-aircraft.com.
(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 April 20, 2007.
Charles L. Smalley,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-7980 Filed 4-27-07; 8:45 am]
BILLING CODE 4910-13-P