Airworthiness Directives; McDonnell Douglas Model MD-90-30 Airplanes, 10202-10204 [E9-5014]
Download as PDF
10202
Federal Register / Vol. 74, No. 45 / Tuesday, March 10, 2009 / Proposed Rules
before the effective date of this AD, but no
later than 72 months since the installation of
a new bogie beam in-service before the
effective date of this AD.
(iii) Not before 54 months since the last
overhaul of a bogie beam before the effective
date of this AD, but no later than 72 months
since the last overhaul of a bogie beam before
the effective date of this AD.
(3) For airplanes with more than 54 months
time-in-service since the date of issuance of
the original French airworthiness certificate
or the date of issuance of the original French
export certificate of airworthiness as of the
effective date of this AD: At the applicable
time specified in paragraph (f)(3)(i), (f)(3)(ii),
(f)(3)(iii), (f)(3)(iv), or (f)(3)(v) of this AD, do
the actions required by paragraph (f)(1) of
this AD.
(i) For airplanes on which the bogie beam
has not been replaced or overhauled since
the date of issuance of the original French
airworthiness certificate or the date of
issuance of the original French export
certificate of airworthiness as of the effective
date of this AD: Within 18 months after the
effective date of this AD.
(ii) For airplanes on which the bogie beam
has been replaced in-service with a new
bogie beam and the new bogie beam has more
than 54 months time-in-service as of the
effective date of this AD: Within 18 months
after the effective date of this AD.
(iii) For airplanes on which the bogie beam
has been replaced in-service with a new
bogie beam and the new bogie beam has 54
months or less time-in-service as of the
effective date of this AD: Not before 54
months since the installation of a new bogie
beam in-service before the effective date of
this AD, but no later than 72 months since
the installation of a new bogie beam inservice before the effective date of this AD.
(iv) For airplanes on which the bogie beam
has been overhauled and the overhauled
bogie beam has more than 54 months timein-service as of the effective date of this AD:
Within 18 months after the effective date of
this AD, or at the next scheduled bogie beam
overhaul, whichever occurs first.
(v) For airplanes on which the bogie beam
has been overhauled and the overhauled
bogie beam has 54 months or less time-inservice as of the effective date of this AD: Not
before 54 months since the last overhaul of
a bogie beam before the effective date of this
AD, but no later than 72 months since the
last overhaul of a bogie beam before the
effective date of this AD.
(4) Within 30 days after accomplishment of
the inspection required by paragraph (f)(1) of
this AD or within 30 days after the effective
date of this AD, whichever occurs later,
report the results, including no findings, to
Airbus, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; e-mail
airworthiness.A330-A340@airbus.com.
(5) Actions accomplished in accordance
with Messier-Dowty Service Bulletin A33/
34–32–271, including Appendix A, dated
September 13, 2007, are considered
acceptable for compliance with the
corresponding requirements of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: The
MCAI specifies repair and corrective actions
in accordance with Airbus Mandatory
Service Bulletin A330–32–3225 or A340–32–
4268, both dated November 21, 2007;
however, the Airbus service bulletins do not
describe those actions. Paragraphs (f)(1)(i)
and (f)(1)(ii) of this AD specify repair and
corrective actions in accordance with
Messier-Dowty Service Bulletin A33/34–32–
272, including Appendixes A, B, C, and D,
dated November 16, 2007.
Other FAA AD Provisions
(g) 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: Vladimir
Ulyanov, Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(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
(h) Refer to European Aviation Safety
Agency (EASA) Airworthiness Directive
2008–0093, dated May 20, 2008, and the
service bulletins specified in Table 1 of this
AD, for related information.
TABLE 1—SERVICE INFORMATION
Service Bulletin
Date
Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 01 ............................................................................
Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 01 ............................................................................
Messier-Dowty Service Bulletin A33/34–32–271, including Appendix A ..................................................................................
Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ........................................................
November 21, 2007.
November 21, 2007.
September 13, 2007.
November 16, 2007.
Issued in Renton, Washington, on February
24, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–5062 Filed 3–9–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0213; Directorate
Identifier 2008–NM–224–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–90–30 Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
VerDate Nov<24>2008
14:40 Mar 09, 2009
Jkt 217001
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Fmt 4702
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SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
McDonnell Douglas Model MD–90–30
airplanes. This proposed AD would
require installing fuses and wire
protection in certain wing and fuel tank
spars. This proposed AD results from
fuel system reviews conducted by the
manufacturer. We are proposing this AD
to prevent possible damage to the fuel
level float or pressure switch wires.
Such damage could become a potential
ignition source inside the fuel tank, and,
combined with flammable fuel vapors,
could result in a fuel tank explosion and
consequent loss of the airplane.
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Federal Register / Vol. 74, No. 45 / Tuesday, March 10, 2009 / Proposed Rules
DATES: We must receive comments on
this proposed AD by April 24, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, California 90846–0001;
telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221 or 425–227–1152.
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 this proposed AD, 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.
FOR FURTHER INFORMATION CONTACT:
Samuel Lee, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5262; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
VerDate Nov<24>2008
14:40 Mar 09, 2009
Jkt 217001
section. Include ‘‘Docket No.
FAA–2009–0213; Directorate Identifier
2008–NM–224–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
ADDRESSES
Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (67 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the rule, we intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
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Fmt 4702
Sfmt 4702
10203
criteria. The other three criteria address
the failure types under evaluation:
single failures, single failures in
combination with another latent
condition(s), and in-service failure
experience. For all four criteria, the
evaluations included consideration of
previous actions taken that may mitigate
the need for further action.
We have determined that the actions
identified in this AD are necessary to
reduce the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in a fuel tank explosion and consequent
loss of the airplane.
We have received a report that fuel
level float switch wires located on the
left and right wing forward spar, center
fuel tank forward spar and forward
auxiliary fuel tank, and pressure switch
wires located on the center fuel tank
forward spar are routed in the same
bundles as power wires. If a short
circuit between a fuel level float or
pressure switch wire and a power wire
occurs, an over current can cause
excessive temperatures in the fuel level
float or pressure switch wires, resulting
in damage and becoming a potential
ignition source. This condition, if not
corrected, could result in possible
damage to the fuel level float or pressure
switch wires, and become a potential
ignition source for the fuel tank.
Relevant Service Information
We have reviewed Boeing Service
Bulletin MD90–28–012, dated
November 19, 2008. The service bulletin
describes procedures for installing fuses
and wire protection in certain wing and
fuel tank spars. For Group 1, the service
bulletin describes procedures for
installing fuel level float switch in-line
fuses and wire protection in the left and
right wing forward spars and center fuel
tank forward spar, right side. For Group
2, the service bulletin describes
procedures for installing fuel level float
switch in-line fuses and wire protection
in the left and right wing forward spars,
center fuel tank forward spar, right side,
and forward auxiliary fuel tank, right
side; and installing a fuel pressure
switch in-line fuse and wire protection
in the center fuel tank forward spar, left
side.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the(se)
same type design(s). This proposed AD
would require accomplishing the
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Federal Register / Vol. 74, No. 45 / Tuesday, March 10, 2009 / Proposed Rules
actions specified in the service
information described previously.
Costs of Compliance
We estimate that this proposed AD
would affect 15 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD.
TABLE—ESTIMATED COSTS
Action
Work hours
Average labor
rate per hour
Parts
Cost per product
Number of
U.S.-registered
airplanes
Fleet cost
Installation, depending on Group.
20 or 26 .................
$80
$1,132 or $1,822 ...
$2,732 or $3,902 ...
15
$40,980 to $58,530.
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
Installation
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
2. The FAA amends § 39.13 by adding
the following new AD:
(g) Within 5 years after the effective date
of this AD, do the actions specified in
paragraph (g)(1) or (g)(2) of this AD, as
applicable, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin MD90–28–012, dated
November 19, 2008 (‘‘the service bulletin’’).
(1) For Group 1 airplanes identified in the
service bulletin, install fuel level float switch
in-line fuses and wire protection in the left
and right wing forward spars and center fuel
tank forward spar, right side.
(2) For Group 2 airplanes identified in the
service bulletin, install fuel level float switch
in-line fuses and wire protection in the left
and right wing forward spars, center fuel tank
forward spar, right side, and forward
auxiliary fuel tank, right side; and install a
fuel pressure switch in-line fuse and wire
protection in the center fuel tank forward
spar, left side.
McDonnell Douglas: Docket No. FAA–2009–
0213; Directorate Identifier 2008–NM–
224–AD.
Alternative Methods of Compliance
(AMOCs)
Comments Due Date
(a) We must receive comments by April 24,
2009.
(h)(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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: Samuel
Lee, Aerospace Engineer, Propulsion Branch,
ANM–140L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712–
4137; telephone (562) 627–5262; fax (562)
627–5210.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
VerDate Nov<24>2008
14:40 Mar 09, 2009
Jkt 217001
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas
Model MD–90–30 airplanes, certificated in
any category, excluding fuselage number
2159.
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
Unsafe Condition
(e) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent possible
damage to the fuel level float or pressure
switch wires. Such damage could become a
potential ignition source inside the fuel tank,
and, when combined with flammable fuel
vapors, could result in a fuel tank explosion
and consequent loss of the airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Issued in Renton, Washington, on February
27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–5014 Filed 3–9–09; 8:45 am]
BILLING CODE 4910–13–P
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Agencies
[Federal Register Volume 74, Number 45 (Tuesday, March 10, 2009)]
[Proposed Rules]
[Pages 10202-10204]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-5014]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0213; Directorate Identifier 2008-NM-224-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-90-30
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain McDonnell Douglas Model MD-90-30 airplanes. This proposed AD
would require installing fuses and wire protection in certain wing and
fuel tank spars. This proposed AD results from fuel system reviews
conducted by the manufacturer. We are proposing this AD to prevent
possible damage to the fuel level float or pressure switch wires. Such
damage could become a potential ignition source inside the fuel tank,
and, combined with flammable fuel vapors, could result in a fuel tank
explosion and consequent loss of the airplane.
[[Page 10203]]
DATES: We must receive comments on this proposed AD by April 24, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may
review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the
FAA, call 425-227-1221 or 425-227-1152.
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 this proposed AD, 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.
FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5262; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0213;
Directorate Identifier 2008-NM-224-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with another latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in a fuel tank explosion and consequent loss of the airplane.
We have received a report that fuel level float switch wires
located on the left and right wing forward spar, center fuel tank
forward spar and forward auxiliary fuel tank, and pressure switch wires
located on the center fuel tank forward spar are routed in the same
bundles as power wires. If a short circuit between a fuel level float
or pressure switch wire and a power wire occurs, an over current can
cause excessive temperatures in the fuel level float or pressure switch
wires, resulting in damage and becoming a potential ignition source.
This condition, if not corrected, could result in possible damage to
the fuel level float or pressure switch wires, and become a potential
ignition source for the fuel tank.
Relevant Service Information
We have reviewed Boeing Service Bulletin MD90-28-012, dated
November 19, 2008. The service bulletin describes procedures for
installing fuses and wire protection in certain wing and fuel tank
spars. For Group 1, the service bulletin describes procedures for
installing fuel level float switch in-line fuses and wire protection in
the left and right wing forward spars and center fuel tank forward
spar, right side. For Group 2, the service bulletin describes
procedures for installing fuel level float switch in-line fuses and
wire protection in the left and right wing forward spars, center fuel
tank forward spar, right side, and forward auxiliary fuel tank, right
side; and installing a fuel pressure switch in-line fuse and wire
protection in the center fuel tank forward spar, left side.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD would require accomplishing the
[[Page 10204]]
actions specified in the service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 15 airplanes of U.S.
registry. The following table provides the estimated costs for U.S.
operators to comply with this proposed AD.
Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per product registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installation, depending on Group. 20 or 26............ $80 $1,132 or $1,822... $2,732 or $3,902... 15 $40,980 to $58,530.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
McDonnell Douglas: Docket No. FAA-2009-0213; Directorate Identifier
2008-NM-224-AD.
Comments Due Date
(a) We must receive comments by April 24, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas Model MD-90-30
airplanes, certificated in any category, excluding fuselage number
2159.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Unsafe Condition
(e) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent possible damage to
the fuel level float or pressure switch wires. Such damage could
become a potential ignition source inside the fuel tank, and, when
combined with flammable fuel vapors, could result in a fuel tank
explosion and consequent loss of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Installation
(g) Within 5 years after the effective date of this AD, do the
actions specified in paragraph (g)(1) or (g)(2) of this AD, as
applicable, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin MD90-28-012, dated November 19, 2008 (``the
service bulletin'').
(1) For Group 1 airplanes identified in the service bulletin,
install fuel level float switch in-line fuses and wire protection in
the left and right wing forward spars and center fuel tank forward
spar, right side.
(2) For Group 2 airplanes identified in the service bulletin,
install fuel level float switch in-line fuses and wire protection in
the left and right wing forward spars, center fuel tank forward
spar, right side, and forward auxiliary fuel tank, right side; and
install a fuel pressure switch in-line fuse and wire protection in
the center fuel tank forward spar, left side.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), 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: Samuel Lee, Aerospace Engineer, Propulsion
Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone
(562) 627-5262; fax (562) 627-5210.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Issued in Renton, Washington, on February 27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-5014 Filed 3-9-09; 8:45 am]
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