Airworthiness Directives; Airbus Model A310 Series Airplanes; and Airbus Model A300-600 Series Airplanes, 32782-32785 [E7-11200]
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32782
Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
enclosing the vent and pilot valve wires in
the left- and right-hand wing fuel tanks with
new, improved, non-conductive hoses, in
accordance with the Accomplishment
Instructions of the service bulletin specified
in paragraph (f)(1) or (f)(2) of this AD, as
applicable.
(1) For Model EMB–135ER, –135KE,
–135KL, –135LR, –145, –145ER, –145MR,
–145LR, –145XR, –145MP, and –145EP
airplanes: EMBRAER Service Bulletin 145–
28–0023, Revision 07, dated February 7,
2007.
(2) For Model EMB–135BJ airplanes:
EMBRAER Service Bulletin 145LEG–28–
0018, Revision 01, dated April 20, 2005.
Credit for Actions Done Using Previous
Service Information
(g) Actions accomplished before the
effective date of this AD in accordance with
the service information specified in Table 1
of this AD are considered acceptable for
compliance with the corresponding actions
specified in this AD.
TABLE 1.—ACCEPTABLE EMBRAER SERVICE INFORMATION
Service bulletin
Revision level
145–28–0023 ............................................................................................................................................
145–28–0023 ............................................................................................................................................
145–28–0023 ............................................................................................................................................
145–28–0023 ............................................................................................................................................
145–28–0023 ............................................................................................................................................
145–28–0023 ............................................................................................................................................
145–28–0023 ............................................................................................................................................
145LEG–28–0018 .....................................................................................................................................
Original .............
01 .....................
02 .....................
03 .....................
04 .....................
05 .....................
06 .....................
Original .............
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, 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.
Related Information
(i) Brazilian airworthiness directive 2006–
06–02, effective June 28, 2006, also addresses
the subject of this AD.
Material Incorporated by Reference
(j)(1) You must use EMBRAER Service
Bulletin 145–28–0023, Revision 07, dated
February 7, 2007; or EMBRAER Service
Bulletin 145LEG–28–0018, Revision 01,
dated April 20, 2005; as applicable, to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(2) EMBRAER Service Bulletin 145LEG–
28–0018, Revision 01, dated April 20, 2005,
contains the following effective pages:
Page
number
Revision level
shown on page
Date shown on
page
P.O. Box 343–CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for a copy of this service
information. You may review copies 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 1,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–11204 Filed 6–13–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27361; Directorate
Identifier 2006–NM–237–AD; Amendment
39–15097; AD 2007–12–19]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes; and Airbus
Model A300–600 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
pwalker on PROD1PC71 with RULES
1, 2 ......
3–20 ....
01 .....................
Original .............
April 20, 2005.
April 23, 2004.
(Page 2 of EMBRAER Service Bulletin
145LEG–28–0018, Revision 01, dated April
20, 2005, incorrectly shows a revision date of
April 20, 2004; that date should be April 20,
2005.)
(3) The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Empresa
Brasileira de Aeronautica S.A. (EMBRAER),
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
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 an airworthiness authority of
another country to identify and correct
an unsafe condition on an aviation
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Date
April 19, 2004.
June 9, 2004.
November 8, 2004.
April 27, 2005.
November 7, 2005.
May 15, 2006.
October 31, 2006.
April 23, 2004.
product. The MCAI describes the unsafe
condition as explosion risks. Chafing of
the fuel pump cables could result in
short circuits leading to fuel pump
failure, intermittent operation, arcing,
and possible fuel tank explosion. We are
issuing this AD to require actions to
correct the unsafe condition on these
products.
This AD becomes effective July
19, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 19, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
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
allow 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
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Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
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.
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 March 13, 2007 (72 FR
11302). That NPRM proposed to require
modification of the fuel pump wiring
against short circuits.
The MCAI states that the FAA has
published SFAR 88 (Special Federal
Aviation Regulation 88). In their letters
referenced 04/00/02/07/01–L296, dated
March 4th, 2002, and 04/00/02/07/03–
L024, dated February 3, 2003, the JAA
(Joint Aviation Authorities)
recommended the application of a
similar regulation to the National
Aviation Authorities (NAA). Under this
regulation, all holders of type
certificates for passenger transport
aircraft with either a passenger capacity
of 30 or more, or a payload capacity of
7,500 pounds (3,402 kilograms) or more,
which have received their certification
since January 1, 1958, are required to
conduct a design review against
explosion risks.
The MCAI design review found that
fuel pump cables can possibly become
chafed in their metallic conduits. The
chafing of the fuel pump cables can
result in short circuits leading to fuel
pump failure, intermittent operation,
arcing, and possible fuel tank explosion.
The MCAI, which requires modification
of the fuel pump wiring against short
circuits, is a consequence of this design
review.
pwalker on PROD1PC71 with RULES
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Refer to Latest Service
Bulletin
Airbus requests that we refer to the
latest revision of Service Bulletin A310–
24–2097. Airbus states that Service
Bulletin A310–24–2097, Revision 02,
dated May 24, 2007, has been released
to operators. Airbus notes that the
service bulletin does not introduce any
additional work.
We have reviewed Airbus Service
Bulletin A310–24–2097, Revision 02,
dated May 24, 2007 (we referred to
Airbus Service Bulletins A310–24–2097,
dated February 15, 2006; and Revision
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
01, dated October 11, 2006; as
appropriate sources of service
information for accomplishing the
actions proposed in the NPRM).
Revision 02 of the service bulletin does
not add additional work. Revision 02 of
the service bulletin updates the
effectivity and introduces minor
changes. Therefore, we have revised this
AD to refer to Revision 02 of the service
bulletin as an appropriate source of
service information for doing the
required actions.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
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 a U.S.
court of law. 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 our FAA
policies. Any such differences are
described in a separate paragraph of the
AD. These requirements, if any, take
precedence over the actions copied from
the MCAI.
Costs of Compliance
We estimate that this AD will affect
205 products of U.S. registry. We also
estimate that it will take about 72 workhours per product to comply with this
AD. The average labor rate is $80 per
work-hour. Required parts will cost
about $7,190 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 parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
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32783
higher than estimated here. Based on
these figures, we estimate the cost of
this AD to the U.S. operators to be
$2,654,750, or $12,950 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 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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains the
NPRM, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5527) is in the ADDRESSES section.
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32784
Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
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
Actions and Compliance
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
application of a similar regulation to the
National Aviation Authorities (NAA). Under
this regulation, all holders of type certificates
for passenger transport aircraft with either a
passenger capacity of 30 or more, or a
payload capacity of 7,500 pounds (3,402
kilograms) or more, which have received
their certification since January 1, 1958, are
required to conduct a design review against
explosion risks. The MCAI design review
found that fuel pump cables can possibly
become chafed in their metallic conduits.
The chafing of the fuel pump cables can
result in short circuits leading to fuel pump
failure, intermittent operation, arcing, and
possible fuel tank explosion. The MCAI,
which requires modification of the fuel pump
wiring against short circuits, is a
consequence of this design review.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–12–19 Airbus: Amendment 39–15097.
Docket No. FAA–2007–27361;
Directorate Identifier 2006–NM–237–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 19, 2007.
Affected ADs
(b) None.
(e) Unless already done, do the following
actions.
(1) Within 37 months after the effective
date of this AD: Modify the inner and outer
fuel pumps, route 1P and 2P harnesses in the
LH (left-hand) wing and in the RH (righthand) wing in accordance with the
instructions of Airbus Service Bulletins
A300–24–6094, dated February 15, 2006;
A300–24–6094, Revision 01, dated July 18,
2006; A310–24–2097, dated February 15,
2006; A310–24–2097, Revision 01, dated
October 11, 2006; or A310–24–2097, Revision
02, dated May 24, 2007; as applicable.
FAA AD Differences
Applicability
(c) This AD applies to Airbus Model A310
series airplanes; and Model A300–600 series
airplanes; certificated in any category; all
certified models, all serial numbers, except
for aircraft which have received in
production Airbus modification 13118 or
Airbus Service Bulletin (SB) A310–24–2097
or A300–24–6094.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states that
the FAA has published SFAR 88 (Special
Federal Aviation Regulation 88). In their
letters referenced 04/00/02/07/01–L296,
dated March 4th, 2002, and 04/00/02/07/03–
L024, dated February 3, 2003, the JAA (Joint
Aviation Authorities) recommended the
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(f) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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: Tom Stafford,
Aerospace Engineer, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1622; fax (425) 227–1149. 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,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(g) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2006–
0284 R1, dated February 13, 2007; and
Airbus Service Bulletins A300–24–6094,
dated February 15, 2006; A300–24–6094,
Revision 01, dated July 18, 2006; A310–24–
2097, dated February 15, 2006; A310–24–
2097, Revision 01, dated October 11, 2006;
and A310–24–2097, Revision 02, dated May
24, 2007; for related information.
Material Incorporated by Reference
(h) You must use the applicable service
information specified in Table 1 of this AD
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 Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
(3) You may review copies 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/cfr/ibrlocations.html.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Airbus service bulletin
pwalker on PROD1PC71 with RULES
A300–24–6094
A300–24–6094
A310–24–2097
A310–24–2097
A310–24–2097
VerDate Aug<31>2005
Revision
..........................................................................................................................................
..........................................................................................................................................
..........................................................................................................................................
..........................................................................................................................................
..........................................................................................................................................
19:08 Jun 13, 2007
Jkt 211001
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Original .............
01 .....................
Original .............
01 .....................
02 .....................
14JNR1
Date
February 15, 2006.
July 18, 2006.
February 15, 2006.
October 11, 2006.
May 24, 2007.
Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
Issued in Renton, Washington, on June 1,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–11200 Filed 6–13–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Streamlined Issuance of AD
[Docket No. FAA–2007–27533 Directorate
Identifier 2007–CE–022–AD; Amendment
39–15102; AD 2007–12–24]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries Model DA 42
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
pwalker on PROD1PC71 with RULES
Shortly after an engine change, the
aluminium fitting attached to the engine
gearbox holding lines and fittings of the
propeller control system was found to be
cracked. This led to a pressure loss in the
propeller control system following a control
system malfunction and led to an in-flight
engine shutdown.
The broken fitting is part of the engine
installation and was initially a steel part. It
was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is
critical for cracks due to combination of
mass, material and installation torque values.
Diamond Aircraft Industries incorporated
¨
with Design Change MAM 42–184 an
additional bracket into production airplanes
to improve the installations and prevent
vibration cracks.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
19, 2007.
On July 19, 2007, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
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:
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
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 April 13, 2007 (72 FR
18598). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that:
Shortly after an engine change, the
aluminium fitting attached to the engine
gearbox holding lines and fittings of the
propeller control system was found to be
cracked. This led to a pressure loss in the
propeller control system following a control
system malfunction and led to a in-flight
engine shutdown.
The broken fitting is part of the engine
installation and was initially a steel part. It
was later modified by the engine
manufacturer to an aluminium design.
Investigation determined that the area is
critical for cracks due to combination of
mass, material and installation torque values.
Diamond Aircraft Industries incorporated
¨
with Design Change MAM 42–184 an
additional bracket into production airplanes
to improve the installations and prevent
vibration cracks.
This airworthiness directive requires the
retroactive installation of this bracket for all
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32785
airplanes, including the airplanes with steel
fittings.
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
We estimate that this AD will affect
70 products of U.S. registry. We also
estimate that it will take about 1.0 workhour per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Required parts will cost about $208 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 parts. 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 this AD to the U.S. operators
to be $20,160 or $ 288 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
E:\FR\FM\14JNR1.SGM
14JNR1
]]>Agencies
[Federal Register Volume 72, Number 114 (Thursday, June 14, 2007)]
[Rules and Regulations]
[Pages 32782-32785]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11200]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27361; Directorate Identifier 2006-NM-237-AD;
Amendment 39-15097; AD 2007-12-19]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes; and
Airbus Model A300-600 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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 an airworthiness authority
of another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as explosion
risks. Chafing of the fuel pump cables could result in short circuits
leading to fuel pump failure, intermittent operation, arcing, and
possible fuel tank explosion. We are issuing this AD to require actions
to correct the unsafe condition on these products.
DATES: This AD becomes effective July 19, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 19,
2007.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
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 allow 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
[[Page 32783]]
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.
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 March 13, 2007 (72
FR 11302). That NPRM proposed to require modification of the fuel pump
wiring against short circuits.
The MCAI states that the FAA has published SFAR 88 (Special Federal
Aviation Regulation 88). In their letters referenced 04/00/02/07/01-
L296, dated March 4th, 2002, and 04/00/02/07/03-L024, dated February 3,
2003, the JAA (Joint Aviation Authorities) recommended the application
of a similar regulation to the National Aviation Authorities (NAA).
Under this regulation, all holders of type certificates for passenger
transport aircraft with either a passenger capacity of 30 or more, or a
payload capacity of 7,500 pounds (3,402 kilograms) or more, which have
received their certification since January 1, 1958, are required to
conduct a design review against explosion risks.
The MCAI design review found that fuel pump cables can possibly
become chafed in their metallic conduits. The chafing of the fuel pump
cables can result in short circuits leading to fuel pump failure,
intermittent operation, arcing, and possible fuel tank explosion. The
MCAI, which requires modification of the fuel pump wiring against short
circuits, is a consequence of this design review.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request To Refer to Latest Service Bulletin
Airbus requests that we refer to the latest revision of Service
Bulletin A310-24-2097. Airbus states that Service Bulletin A310-24-
2097, Revision 02, dated May 24, 2007, has been released to operators.
Airbus notes that the service bulletin does not introduce any
additional work.
We have reviewed Airbus Service Bulletin A310-24-2097, Revision 02,
dated May 24, 2007 (we referred to Airbus Service Bulletins A310-24-
2097, dated February 15, 2006; and Revision 01, dated October 11, 2006;
as appropriate sources of service information for accomplishing the
actions proposed in the NPRM). Revision 02 of the service bulletin does
not add additional work. Revision 02 of the service bulletin updates
the effectivity and introduces minor changes. Therefore, we have
revised this AD to refer to Revision 02 of the service bulletin as an
appropriate source of service information for doing the required
actions.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
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 a U.S. court of
law. 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 our FAA policies. Any such differences
are described in a separate paragraph of the AD. These requirements, if
any, take precedence over the actions copied from the MCAI.
Costs of Compliance
We estimate that this AD will affect 205 products of U.S. registry.
We also estimate that it will take about 72 work-hours per product to
comply with this AD. The average labor rate is $80 per work-hour.
Required parts will cost about $7,190 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 parts. 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 this AD to the U.S. operators to be $2,654,750, or
$12,950 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 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains the NPRM, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone (800) 647-5527) is in the ADDRESSES section.
[[Page 32784]]
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 adding the following new AD:
2007-12-19 Airbus: Amendment 39-15097. Docket No. FAA-2007-27361;
Directorate Identifier 2006-NM-237-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 19,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes; and
Model A300-600 series airplanes; certificated in any category; all
certified models, all serial numbers, except for aircraft which have
received in production Airbus modification 13118 or Airbus Service
Bulletin (SB) A310-24-2097 or A300-24-6094.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states that the FAA has published SFAR 88 (Special Federal Aviation
Regulation 88). In their letters referenced 04/00/02/07/01-L296,
dated March 4th, 2002, and 04/00/02/07/03-L024, dated February 3,
2003, the JAA (Joint Aviation Authorities) recommended the
application of a similar regulation to the National Aviation
Authorities (NAA). Under this regulation, all holders of type
certificates for passenger transport aircraft with either a
passenger capacity of 30 or more, or a payload capacity of 7,500
pounds (3,402 kilograms) or more, which have received their
certification since January 1, 1958, are required to conduct a
design review against explosion risks. The MCAI design review found
that fuel pump cables can possibly become chafed in their metallic
conduits. The chafing of the fuel pump cables can result in short
circuits leading to fuel pump failure, intermittent operation,
arcing, and possible fuel tank explosion. The MCAI, which requires
modification of the fuel pump wiring against short circuits, is a
consequence of this design review.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Within 37 months after the effective date of this AD: Modify
the inner and outer fuel pumps, route 1P and 2P harnesses in the LH
(left-hand) wing and in the RH (right-hand) wing in accordance with
the instructions of Airbus Service Bulletins A300-24-6094, dated
February 15, 2006; A300-24-6094, Revision 01, dated July 18, 2006;
A310-24-2097, dated February 15, 2006; A310-24-2097, Revision 01,
dated October 11, 2006; or A310-24-2097, Revision 02, dated May 24,
2007; as applicable.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(f) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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: Tom
Stafford, Aerospace Engineer, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149.
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, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(g) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2006-0284 R1, dated February 13, 2007; and Airbus Service
Bulletins A300-24-6094, dated February 15, 2006; A300-24-6094,
Revision 01, dated July 18, 2006; A310-24-2097, dated February 15,
2006; A310-24-2097, Revision 01, dated October 11, 2006; and A310-
24-2097, Revision 02, dated May 24, 2007; for related information.
Material Incorporated by Reference
(h) You must use the applicable service information specified in
Table 1 of this AD 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
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
(3) You may review copies 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/cfr/ibr-
locations.html.
Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
A300-24-6094............................ Original....................... February 15, 2006.
A300-24-6094............................ 01............................. July 18, 2006.
A310-24-2097............................ Original....................... February 15, 2006.
A310-24-2097............................ 01............................. October 11, 2006.
A310-24-2097............................ 02............................. May 24, 2007.
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[[Page 32785]]
Issued in Renton, Washington, on June 1, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-11200 Filed 6-13-07; 8:45 am]
BILLING CODE 4910-13-P
