Airworthiness Directives; APEX Aircraft Model CAP 10B Airplanes, 21244-21246 [E8-8360]
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21244
Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations
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
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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by Reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–08–24 Boeing: Amendment 39–15478.
Docket No. FAA–2007–0049; Directorate
Identifier 2007–NM–168–AD.
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Effective Date
(a) This airworthiness directive (AD) is
effective May 27, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737–
600, –700, –700C, –800, and –900 series
airplanes, certificated in any category; as
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15:19 Apr 18, 2008
Jkt 214001
Unsafe Condition
(d) This AD results from reports of failure
of the drain tube assembly and support
clamp on the aft fairing of an engine strut.
We are issuing this AD to prevent failure of
the drain tube assemblies and clamps on the
aft fairings of the engine struts. Such a failure
could allow leaked flammable fluids in the
drain systems to discharge on to the heat
shields of the aft fairings of the engine struts,
which could result in an undetected and
uncontrollable fire.
Issued in Renton, Washington, on April 8,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–8328 Filed 4–18–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
[Docket No. FAA–2008–0196; Directorate
Identifier 2008–CE–002–AD; Amendment
39–15482; AD 2008–09–02]
RIN 2120–AA64
Replacement
(f) Within 60 months after the effective
date of this AD, replace the drain tube
assemblies and support clamps on the aft
fairing of the struts of engine number 1 and
engine number 2 with new drain tube
assemblies and clamps, in accordance with
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–54–
1043, dated May 2, 2007.
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures 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.
Material Incorporated by Reference
1. The authority citation for part 39
continues to read as follows:
I
§ 39.13
identified in Boeing Special Attention
Service Bulletin 737–54–1043, dated May 2,
2007.
(h) You must use Boeing Special Attention
Service Bulletin 737–54–1043, dated May 2,
2007, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
(3) You may review copies of the service
information incorporated by reference at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; 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/
code_of_federal_regulations/
ibr_locations.html.
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Airworthiness Directives; APEX
Aircraft Model CAP 10B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
the products listed above. This AD
results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Further to a new fracture in flight of a CAP
10B wing in June 2003, the investigation in
process seems to point out that a wrong
application of CAP 10B Service Bulletin No.
16 (CAP 10B–57–004) would lead to the
impossibility of detecting the potential spar
damage while performing the Type
Certificate holder upper spar flange
inspection.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective May
27, 2008.
On May 27, 2008, the Director of the
Federal Register approved the
incorporation by reference of APEX
Aircraft Document No. 1000913GB,
dated February 4, 2002; APEX Aircraft
Document No. 1000914GB, dated
February 4, 2002; and APEX Aircraft
Document No. 1000915GB, dated
February 4, 2002, listed in this AD.
As of July 23, 1993 (58 FR 31342, June
2, 1993), the Director of the Federal
Register approved the incorporation by
reference of Avions Mudry & CIE
Service Bulletin CAP 10B No. 16, dated
April 27, 1992, listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
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Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations
www.regulations.gov or in person at
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on February 25, 2008 (73 FR
9968) and proposed to supersede AD
2003–04–02, Amendment 39–13050 (68
FR 7904, February 19, 2003). That
NPRM proposed to correct an unsafe
condition for the specified products.
The MCAI states:
Further to a new fracture in flight of a CAP
10B wing in June 2003, the investigation in
process seems to point out that a wrong
application of CAP 10B Service Bulletin No.
16 (CAP 10B–57–004) would lead to the
impossibility of detecting the potential spar
damage while performing the Type
Certificate holder upper spar flange
inspection.
The MCAI requires you to check that the
No. 1 wing rib has been modified,
comply with load factors and operating
limitations, and do repetitive
inspections of the upper and lower spar
flanges and landing gear attachment
blocks.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
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Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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
VerDate Aug<31>2005
15:19 Apr 18, 2008
Jkt 214001
provided in the MCAI and related
service information.
We might also have required 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 AD.
Costs of Compliance
Based on the service information, we
estimate that this AD will affect 31
products of U.S. registry. We also
estimate that it will take about 20 workhours per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Based on these figures, we estimate
the cost of this AD to the U.S. operators
to be $49,600 or $1,600 per product.
The estimated total cost on U.S.
operators includes the cumulative costs
associated with those airplanes affected
by AD 2003–04–02 and those costs
associated with the new actions that
would be added in 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 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
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21245
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains the NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13050 (68 FR
7904, February 19, 2003) and adding the
following new AD:
I
2008–09–02 APEX Aircraft: Amendment
39–15482; Docket No. FAA–2008–0196;
Directorate Identifier 2008–CE–002–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 27, 2008.
Affected ADs
(b) This AD supersedes AD 2003–04–02,
Amendment 39–13050.
Applicability
(c) This AD applies to Model CAP 10B
airplanes, serial numbers (SNs) 01, 02, 03, 04,
and 1 through 282, certificated in any
category, that have not been fitted with a
replacement wood/carbon wing following
application of major change 000302.
Subject
(d) Air Transport Association of America
(ATA) Code 57: Wings.
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21246
Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations
rfrederick on PROD1PC67 with RULES
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Further to a new fracture in flight of a CAP
10B wing in June 2003, the investigation in
process seems to point out that a wrong
application of CAP 10B Service Bulletin No.
16 (CAP 10B–57–004) would lead to the
impossibility of detecting the potential spar
damage while performing the Type
Certificate holder upper spar flange
inspection.
The MCAI requires you to check that the No.
1 wing rib has been modified, comply with
load factors and operating limitations, and do
repetitive inspections of the upper and lower
spar flanges and landing gear attachment
blocks.
(i) Incorporate the following words (using
at least 1⁄8-inch letters) in the placard and
install this placard on the instrument panel
within the pilot’s clear view: ‘‘THE NEVER
EXCEED AIRSPEED FOR POSITIVE OR
NEGATIVE FLICK MANEUVERS IS 160 KM/
H (86 KNOTS). THE LOAD FACTORS
LIMITATION FOR SOLO FLIGHT IS +5 AND
¥3.5 Gs AND WHEN 2 PERSONS ARE ON
BOARD IS +4.3 AND ¥3.5 Gs.’’
(ii) 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 (g)(3)(i) of this
AD. Make an entry into the aircraft records
showing compliance with this portion of the
AD in accordance with section 43.9 of the
Federal Aviation Regulations (14 CFR 43.9).
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) For Model CAP 10B airplanes with SNs
01, 02, 03, 04, and 1 through 263, within the
next 100 hours time-in-service (TIS) after July
23, 1993 (the compliance date retained from
AD 2003–04–02), unless already done, install
a permanent inspection opening in the No. 1
wing rib following Avions Mudry Service
Bulletin CAP10B No. 16, dated April 27,
1992. Inspection openings are incorporated
during production for airplanes having a
serial number of 264 or higher.
(2) For all affected airplanes, initially
inspect the upper wing spar cap, the main
wing spar undersurface, and the landing gear
attachment blocks for cracks within the next
55 hours TIS after April 4, 2003 (the
compliance date retained from AD 2003–04–
02) following APEX Aircraft Document No.
1000913GB, dated February 4, 2002; APEX
Aircraft Document No. 1000914GB, dated
February 4, 2002; and APEX Aircraft
Document No. 1000915GB, dated February 4,
2002. Repetitively inspect the upper wing
spar cap and the main wing spar
undersurface thereafter at intervals not to
exceed 55 hours TIS. Repetitively inspect the
landing gear attachment blocks thereafter at
intervals not to exceed 1,000 hours TIS.
(3) For all affected airplanes, before further
flight if any cracks are found during any
inspection required in paragraph (f)(2) of this
AD, do the following:
(i) Obtain a repair scheme from the
manufacturer through the FAA at the address
specified in paragraph (h)(1) of this AD;
(ii) Incorporate this repair scheme; and
(iii) Continue to inspect as specified in
paragraph (f)(2) of this AD.
(4) For all affected airplanes, unless
already done, do the following actions:
(i) Load factors limitation: Before further
flight, as of May 27, 2008 (the effective date
of this AD), the load factors limitation for
solo flight is +5 and ¥3.5 Gs and when 2
persons are on board is +4.3 and ¥3.5 Gs.
(ii) Flick (snap roll) maneuvers speed
limitation: Before further flight, as of May 27,
2008 (the effective date of this AD), for
positive and negative flick maneuvers, the
airspeed limitation is 160 km/hour (86
knots).
(5) For all affected airplanes, before further
flight after May 27, 2008 (the effective date
of this AD), fabricate a placard:
FAA AD Differences
VerDate Aug<31>2005
15:19 Apr 18, 2008
Jkt 214001
Note: This AD differs from the MCAI and/
or service information as follows: This AD
does not include the requirement from the
MCAI to route the request to operate beyond
the load factors limitation and flick (snap
roll) maneuvers speed limitation through the
´ ´
Direction Generale de L’Aviation Civile
(DGAC). You may make this request to the
FAA following paragraph (h)(1) of this AD.
Other FAA AD Provisions
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; fax: (816)
329–4090. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered 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
(i) Refer to MCAI French AD 2003–375(A),
dated October 1, 2003; Avions Mudry & CIE
Service Bulletin CAP 10B No. 16, dated April
27, 1992, APEX Aircraft Document No.
1000913GB, dated February 4, 2002; APEX
Aircraft Document No. 1000914GB, dated
February 4, 2002; and APEX Aircraft
Document No. 1000915GB, dated February 4,
2002, for related information.
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Material Incorporated by Reference
(j) You must use Avions Mudry & CIE
Service Bulletin CAP 10B No. 16, dated April
27, 1992; APEX Aircraft Document No.
1000913GB, dated February 4, 2002; APEX
Aircraft Document No. 1000914GB, dated
February 4, 2002; and APEX Aircraft
Document No. 1000915GB, dated February 4,
2002, 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
APEX Aircraft Document No. 1000913GB,
dated February 4, 2002; APEX Aircraft
Document No. 1000914GB, dated February 4,
2002; and APEX Aircraft Document No.
1000915GB, dated February 4, 2002, under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On July 23, 1993 (58 FR 31342, June 2,
1993), the Director of the Federal Register
previously approved the incorporation by
reference of Avions Mudry & CIE Service
Bulletin CAP 10B No. 16, dated April 27,
1992.
(3) For service information identified in
this AD, contact APEX Aircraft, Bureau de
´
Navigabilite, 1, route de Troyes, 21121
DAROIS—France; telephone: +33 380 35 65
10; fax +33 380 35 65 15; e-mail:
airworthiness@apex-aircraft.com; Internet:
https://www.apex-aircraft.com.
(4) 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
11, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–8360 Filed 4–18–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 73
[Docket No. FAA–2008–0257; Airspace
Docket No. 08–AAL–7]
RIN 2120–AA66
Revision of Restricted Area 2204;
Oliktok Point, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action changes the using
agency of Restricted Area 2204 (R–
2204), Oliktok Point, AK, from
‘‘Department of Energy, Sandia National
Labs/National Nuclear Security
Administration, Albuquerque, NM’’ to
‘‘Department of Energy, Office of
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]]>Agencies
[Federal Register Volume 73, Number 77 (Monday, April 21, 2008)]
[Rules and Regulations]
[Pages 21244-21246]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-8360]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0196; Directorate Identifier 2008-CE-002-AD;
Amendment 39-15482; AD 2008-09-02]
RIN 2120-AA64
Airworthiness Directives; APEX Aircraft Model CAP 10B Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
Further to a new fracture in flight of a CAP 10B wing in June
2003, the investigation in process seems to point out that a wrong
application of CAP 10B Service Bulletin No. 16 (CAP 10B-57-004)
would lead to the impossibility of detecting the potential spar
damage while performing the Type Certificate holder upper spar
flange inspection.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective May 27, 2008.
On May 27, 2008, the Director of the Federal Register approved the
incorporation by reference of APEX Aircraft Document No. 1000913GB,
dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated
February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated
February 4, 2002, listed in this AD.
As of July 23, 1993 (58 FR 31342, June 2, 1993), the Director of
the Federal Register approved the incorporation by reference of Avions
Mudry & CIE Service Bulletin CAP 10B No. 16, dated April 27, 1992,
listed in this AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
[[Page 21245]]
www.regulations.gov or in person at Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on February 25, 2008
(73 FR 9968) and proposed to supersede AD 2003-04-02, Amendment 39-
13050 (68 FR 7904, February 19, 2003). That NPRM proposed to correct an
unsafe condition for the specified products. The MCAI states:
Further to a new fracture in flight of a CAP 10B wing in June
2003, the investigation in process seems to point out that a wrong
application of CAP 10B Service Bulletin No. 16 (CAP 10B-57-004)
would lead to the impossibility of detecting the potential spar
damage while performing the Type Certificate holder upper spar
flange inspection.
The MCAI requires you to check that the No. 1 wing rib has been
modified, comply with load factors and operating limitations, and do
repetitive inspections of the upper and lower spar flanges and landing
gear attachment blocks.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
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 also have required 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 AD.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect 31 products of U.S. registry. We also estimate that it will take
about 20 work-hours per product to comply with basic requirements of
this AD. The average labor rate is $80 per work-hour.
Based on these figures, we estimate the cost of this AD to the U.S.
operators to be $49,600 or $1,600 per product.
The estimated total cost on U.S. operators includes the cumulative
costs associated with those airplanes affected by AD 2003-04-02 and
those costs associated with the new actions that would be added in 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13050 (68 FR
7904, February 19, 2003) and adding the following new AD:
2008-09-02 APEX Aircraft: Amendment 39-15482; Docket No. FAA-2008-
0196; Directorate Identifier 2008-CE-002-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 27,
2008.
Affected ADs
(b) This AD supersedes AD 2003-04-02, Amendment 39-13050.
Applicability
(c) This AD applies to Model CAP 10B airplanes, serial numbers
(SNs) 01, 02, 03, 04, and 1 through 282, certificated in any
category, that have not been fitted with a replacement wood/carbon
wing following application of major change 000302.
Subject
(d) Air Transport Association of America (ATA) Code 57: Wings.
[[Page 21246]]
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Further to a new fracture in flight of a CAP 10B wing in June
2003, the investigation in process seems to point out that a wrong
application of CAP 10B Service Bulletin No. 16 (CAP 10B-57-004)
would lead to the impossibility of detecting the potential spar
damage while performing the Type Certificate holder upper spar
flange inspection.
The MCAI requires you to check that the No. 1 wing rib has been
modified, comply with load factors and operating limitations, and do
repetitive inspections of the upper and lower spar flanges and
landing gear attachment blocks.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For Model CAP 10B airplanes with SNs 01, 02, 03, 04, and 1
through 263, within the next 100 hours time-in-service (TIS) after
July 23, 1993 (the compliance date retained from AD 2003-04-02),
unless already done, install a permanent inspection opening in the
No. 1 wing rib following Avions Mudry Service Bulletin CAP10B No.
16, dated April 27, 1992. Inspection openings are incorporated
during production for airplanes having a serial number of 264 or
higher.
(2) For all affected airplanes, initially inspect the upper wing
spar cap, the main wing spar undersurface, and the landing gear
attachment blocks for cracks within the next 55 hours TIS after
April 4, 2003 (the compliance date retained from AD 2003-04-02)
following APEX Aircraft Document No. 1000913GB, dated February 4,
2002; APEX Aircraft Document No. 1000914GB, dated February 4, 2002;
and APEX Aircraft Document No. 1000915GB, dated February 4, 2002.
Repetitively inspect the upper wing spar cap and the main wing spar
undersurface thereafter at intervals not to exceed 55 hours TIS.
Repetitively inspect the landing gear attachment blocks thereafter
at intervals not to exceed 1,000 hours TIS.
(3) For all affected airplanes, before further flight if any
cracks are found during any inspection required in paragraph (f)(2)
of this AD, do the following:
(i) Obtain a repair scheme from the manufacturer through the FAA
at the address specified in paragraph (h)(1) of this AD;
(ii) Incorporate this repair scheme; and
(iii) Continue to inspect as specified in paragraph (f)(2) of
this AD.
(4) For all affected airplanes, unless already done, do the
following actions:
(i) Load factors limitation: Before further flight, as of May
27, 2008 (the effective date of this AD), the load factors
limitation for solo flight is +5 and -3.5 Gs and when 2 persons are
on board is +4.3 and -3.5 Gs.
(ii) Flick (snap roll) maneuvers speed limitation: Before
further flight, as of May 27, 2008 (the effective date of this AD),
for positive and negative flick maneuvers, the airspeed limitation
is 160 km/hour (86 knots).
(5) For all affected airplanes, before further flight after May
27, 2008 (the effective date of this AD), fabricate a placard:
(i) Incorporate the following words (using at least \1/8\-inch
letters) in the placard and install this placard on the instrument
panel within the pilot's clear view: ``THE NEVER EXCEED AIRSPEED FOR
POSITIVE OR NEGATIVE FLICK MANEUVERS IS 160 KM/H (86 KNOTS). THE
LOAD FACTORS LIMITATION FOR SOLO FLIGHT IS +5 AND -3.5 Gs AND WHEN 2
PERSONS ARE ON BOARD IS +4.3 AND -3.5 Gs.''
(ii) 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 (g)(3)(i) of this AD. Make an entry into the aircraft
records showing compliance with this portion of the AD in accordance
with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: This AD does not include the requirement from the MCAI
to route the request to operate beyond the load factors limitation
and flick (snap roll) maneuvers speed limitation through the
Direction G[eacute]n[eacute]rale de L'Aviation Civile (DGAC). You
may make this request to the FAA following paragraph (h)(1) of this
AD.
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Sarjapur Nagarajan, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(i) Refer to MCAI French AD 2003-375(A), dated October 1, 2003;
Avions Mudry & CIE Service Bulletin CAP 10B No. 16, dated April 27,
1992, APEX Aircraft Document No. 1000913GB, dated February 4, 2002;
APEX Aircraft Document No. 1000914GB, dated February 4, 2002; and
APEX Aircraft Document No. 1000915GB, dated February 4, 2002, for
related information.
Material Incorporated by Reference
(j) You must use Avions Mudry & CIE Service Bulletin CAP 10B No.
16, dated April 27, 1992; APEX Aircraft Document No. 1000913GB,
dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated
February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated
February 4, 2002, 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 APEX Aircraft Document No. 1000913GB,
dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated
February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated
February 4, 2002, under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On July 23, 1993 (58 FR 31342, June 2, 1993), the Director
of the Federal Register previously approved the incorporation by
reference of Avions Mudry & CIE Service Bulletin CAP 10B No. 16,
dated April 27, 1992.
(3) For service information identified in this AD, contact APEX
Aircraft, Bureau de Navigabilit[eacute], 1, route de Troyes, 21121
DAROIS--France; telephone: +33 380 35 65 10; fax +33 380 35 65 15;
e-mail: airworthiness@apex-aircraft.com; Internet: https://www.apex-
aircraft.com.
(4) 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 11, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-8360 Filed 4-18-08; 8:45 am]
BILLING CODE 4910-13-P
