Airworthiness Directives; Boeing Model 777-200 Series Airplanes, 75428-75430 [05-24243]
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75428
Federal Register / Vol. 70, No. 243 / Tuesday, December 20, 2005 / Proposed Rules
by removing amendment 39–11097 (64
FR 15298, March 31, 1999) and adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–23358;
Directorate Identifier 2005–NM–206–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by February 3, 2006.
Affected ADs
(b) This AD supersedes AD 99–07–12.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–300, 747–400, 747–400D, and 747SR
series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin
747–53A2408, Revision 1, dated April 4,
2002.
Unsafe Condition
(d) This AD results from reports indicating
that fatigue cracks were found in lower lobe
frames on the left side of the fuselage. We are
issuing this AD to detect and correct fatigue
cracking of certain lower lobe fuselage
frames, which could lead to fatigue cracks in
the fuselage skin, and consequent rapid
decompression of the airplane.
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.
Restatement of the Requirements of AD 99–
07–12, With Additional Information for
Group 2 Airplanes
Initial Inspections
(f) For airplanes on which the initial
detailed internal inspection of the Section 46
lower lobe frames required by paragraph
(f)(2) or (i)(2) of AD 2005–20–30, amendment
39–14327, has not been accomplished:
Perform a detailed visual inspection to detect
cracking of the lower lobe fuselage frames
from Body Station 1820 to Body Station
2100, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2408, dated April
25, 1996; or Boeing Alert Service Bulletin
747–53A2408, Revision 1, dated April 4,
2002; as applicable; at the later of the
applicable times specified in paragraph (f)(1),
(f)(2), or (f)(3) of this AD.
(1) For all airplanes: Prior to the
accumulation of 15,000 total flight cycles; or
(2) For Group 1 airplanes identified in
Revision 1 of the service bulletin: Within
1,500 flight cycles or 18 months after May 5,
1999 (the effective date of AD 99–07–12),
whichever occurs first.
(3) For Group 2 airplanes identified in
Revision 1 of the service bulletin: Within
1,500 flight cycles or 18 months after the
effective date of this AD, whichever occurs
first.
Note 1: Paragraph (f)(2) or (i)(2) of AD
2005–20–30 requires a detailed inspection to
detect cracks in the Section 46 lower lobe
frames, in accordance with Boeing Service
VerDate Aug<31>2005
15:07 Dec 19, 2005
Jkt 208001
Bulletin 747–53–2349, Revision 2, dated
April 3, 2003. The initial inspection is
required prior to the accumulation of 22,000
total flight cycles; or within 1,000 flight
cycles after June 11, 1993 (the effective date
of AD 93–08–12, amendment 39–8559), or
November 16, 2005 (the effective date of AD
2005–20–30), depending on previous
inspections accomplished; whichever occurs
later.
Note 2: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Repetitive Inspections
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane.
(4) AMOCs approved previously in
accordance with AD 99–07–12, amendment
39–11097, are approved as AMOCs for the
corresponding provisions of this AD.
Issued in Renton, Washington, on
December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–24242 Filed 12–19–05; 8:45 am]
BILLING CODE 4910–13–P
(g) If no cracking is detected during the
inspection required by paragraph (f) of this
AD, repeat the inspection thereafter at
intervals not to exceed 3,000 flight cycles.
DEPARTMENT OF TRANSPORTATION
Corrective Actions
Federal Aviation Administration
(h) If any cracking is detected during any
inspection required by paragraph (f) of this
AD, prior to further flight, accomplish
paragraphs (h)(1) and (h)(2) of this AD:
(1) Within 20 inches of the crack location
on the frame, perform a detailed inspection
of the adjacent structure to detect cracking.
If any cracking is detected during any
detailed inspection done in accordance with
paragraph (f) or (h)(1) of this AD, prior to
further flight, repair in accordance with
paragraph (h)(1)(i) or (h)(1)(ii) of this AD, as
applicable.
(i) For Group 1 airplanes: Using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD. The
Boeing 747 Structural Repair Manual, Subject
53–10–04, Figure 67 or 90, is one approved
method.
(ii) For Group 2 airplanes: Using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
(2) Repeat the inspection required by
paragraph (f) of this AD thereafter at intervals
not to exceed 3,000 flight cycles.
14 CFR Part 39
Optional Terminating Inspection
(i) Accomplishment of the initial detailed
inspection of the Section 46 lower lobe
frames required by paragraph (f)(2) or (i)(2)
of AD 2005–20–30 constitutes terminating
action for the requirements of this AD only
for airplanes identified in Boeing Alert
Service Bulletin 747–53A2408, Revision 1,
dated April 4, 2002, as Group 1 airplanes.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
PO 00000
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[Docket No. FAA–2005–23357; Directorate
Identifier 2005–NM–207–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 777–200 series
airplanes. This proposed AD would
require installing a new washer between
the lower wing surface and the jam nut
of the sump drain valve assembly. This
proposed AD results from fuel system
reviews conducted by the manufacturer.
We are proposing this AD to prevent
energy from a lightning strike on the
bushing for the sump drain valve from
arcing to the inside of the center fuel
tank wall, which could create an
ignition source in the fuel tank and
result in a fuel tank explosion.
DATES: We must receive comments on
this proposed AD by February 3, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
E:\FR\FM\20DEP1.SGM
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Federal Register / Vol. 70, No. 243 / Tuesday, December 20, 2005 / Proposed Rules
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6500; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2005–23357; Directorate
Identifier 2005–NM–207–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
VerDate Aug<31>2005
15:07 Dec 19, 2005
Jkt 208001
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
The FAA has examined the
underlying safety issues involved in
recent 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 failure
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.
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
75429
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 fuel tank explosions and consequent
loss of the airplane.
We have received a report indicating
that small gaps may be present between
the bushing of the sump drain valve and
the lower wing surface in the center fuel
tank, on certain Boeing Model 777–200
series airplanes. If a lightning strike
occurs on the bushing, arcs can go
across the small gaps between the
bushing and the lower wing surface, and
into the inside of the fuel tank wall. The
bushing does not have an engineered
bond path to the wing surface. In
addition, the layer of sealant between
the bushing and the inner surface of the
fuel tank could be too thin to contain
the energy in the arcs. This condition,
if not corrected, could create an ignition
source in the center fuel tank and result
in a fuel tank explosion.
Relevant Service Information
We have reviewed Boeing Special
Attention Service Bulletin 777–28–
0045, dated September 1, 2005. The
service bulletin describes procedures for
installing a new washer between the
lower wing surface and the jam nut of
the sump drain valve assembly.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. For this reason, we are
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously.
Costs of Compliance
There are about 88 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about 22
airplanes of U.S. registry. The proposed
actions would take about 4 work hours
per airplane, at an average labor rate of
$65 per work hour. Required parts
would cost about $360 per airplane.
Based on these figures, the estimated
cost of the proposed AD for U.S.
operators is $13,640, or $620 per
airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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Federal Register / Vol. 70, No. 243 / Tuesday, December 20, 2005 / Proposed Rules
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.
§ 39.13
[Amended]
DEPARTMENT OF TRANSPORTATION
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2005–23357;
Directorate Identifier 2005–NM–207–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by February 3, 2006.
Affected ADs
(b) None.
Applicability
Unsafe Condition
We have 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 that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent energy from a
lightning strike on the bushing for the sump
drain valve from arcing to the inside of the
center fuel tank wall, which could create an
ignition source in the fuel tank and result in
a fuel tank explosion.
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
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.
Installation
(f) Within 60 months after the effective
date of this AD, install a new washer between
the lower wing surface and the jam nut of the
sump drain valve assembly in both wings, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–28–0045, dated
September 1, 2005.
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on
December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–24243 Filed 12–19–05; 8:45 am]
BILLING CODE 4910–13–P
Authority: 49 U.S.C. 106(g), 40113, 44701.
VerDate Aug<31>2005
15:07 Dec 19, 2005
Jkt 208001
PO 00000
Frm 00008
14 CFR Part 39
[Docket No. 2003–NM–198–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–9–10, –20, –30, –40,
and –50 Series Airplanes; Model DC–
9–81 (MD–81), –82 (MD–82), –83 (MD–
83), and –87 (MD–87) Airplanes; and
Model MD–88 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Supplemental notice of
proposed rulemaking; reopening of
comment period.
AGENCY:
(c) This AD applies to Boeing Model 777–
200 series airplanes, certificated in any
category; as identified in Boeing Special
Attention Service Bulletin 777–28–0045,
dated September 1, 2005.
Regulatory Findings
List of Subjects in 14 CFR Part 39
Federal Aviation Administration
Fmt 4702
Sfmt 4702
SUMMARY: This document revises an
earlier proposed airworthiness directive
(AD), applicable to certain McDonnell
Douglas Model DC–9–10, –20, –30, –40,
and –50 series airplanes; Model DC–9–
81 (MD–81), –82 (MD–82), –83 (MD–83),
and –87 (MD–87) airplanes; and Model
MD–88 airplanes. That proposed AD
would have required repetitive
inspections and functional tests of the
static port heater assemblies, an
inspection of the static port heaters and
insulators, and corrective actions if
necessary. This new action revises the
proposed AD by adding repetitive
inspections of the static port heaters and
insulators and revising the functional
test of the static port heater. The actions
specified by this new proposed AD are
intended to prevent an electrical short
of the static port heater from sparking
and igniting the insulation blanket
adjacent to the static port heater, which
could result in smoke and/or fire in the
cabin area. This action is intended to
address the identified unsafe condition.
DATES: Comments must be received by
January 17, 2006.
ADDRESSES: Submit comments in
triplicate to the Federal Aviation
Administration (FAA), Transport
Airplane Directorate, ANM–114,
Attention: Rules Docket No. 2003–NM–
198–AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055–4056.
Comments may be inspected at this
location between 9 a.m. and 3 p.m.,
Monday through Friday, except Federal
holidays. Comments may be submitted
via fax to (425) 227–1232. Comments
may also be sent via the Internet using
the following address: 9-anmnprmcomment@faa.gov. Comments sent
via fax or the Internet must contain
‘‘Docket No. 2003–NM–198–AD’’ in the
subject line and need not be submitted
E:\FR\FM\20DEP1.SGM
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]]>Agencies
[Federal Register Volume 70, Number 243 (Tuesday, December 20, 2005)]
[Proposed Rules]
[Pages 75428-75430]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-24243]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23357; Directorate Identifier 2005-NM-207-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777-200 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 777-200 series airplanes. This proposed AD
would require installing a new washer between the lower wing surface
and the jam nut of the sump drain valve assembly. This proposed AD
results from fuel system reviews conducted by the manufacturer. We are
proposing this AD to prevent energy from a lightning strike on the
bushing for the sump drain valve from arcing to the inside of the
center fuel tank wall, which could create an ignition source in the
fuel tank and result in a fuel tank explosion.
DATES: We must receive comments on this proposed AD by February 3,
2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov
[[Page 75429]]
and follow the instructions for sending your comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6500; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2005-
23357; Directorate Identifier 2005-NM-207-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The FAA has examined the underlying safety issues involved in
recent 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 failure 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 fuel tank explosions and consequent loss of the airplane.
We have received a report indicating that small gaps may be present
between the bushing of the sump drain valve and the lower wing surface
in the center fuel tank, on certain Boeing Model 777-200 series
airplanes. If a lightning strike occurs on the bushing, arcs can go
across the small gaps between the bushing and the lower wing surface,
and into the inside of the fuel tank wall. The bushing does not have an
engineered bond path to the wing surface. In addition, the layer of
sealant between the bushing and the inner surface of the fuel tank
could be too thin to contain the energy in the arcs. This condition, if
not corrected, could create an ignition source in the center fuel tank
and result in a fuel tank explosion.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 777-28-
0045, dated September 1, 2005. The service bulletin describes
procedures for installing a new washer between the lower wing surface
and the jam nut of the sump drain valve assembly. Accomplishing the
actions specified in the service information is intended to adequately
address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously.
Costs of Compliance
There are about 88 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 22 airplanes of
U.S. registry. The proposed actions would take about 4 work hours per
airplane, at an average labor rate of $65 per work hour. Required parts
would cost about $360 per airplane. Based on these figures, the
estimated cost of the proposed AD for U.S. operators is $13,640, or
$620 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 75430]]
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 have 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 that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2005-23357; Directorate Identifier 2005-
NM-207-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by February
3, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777-200 series airplanes,
certificated in any category; as identified in Boeing Special
Attention Service Bulletin 777-28-0045, dated September 1, 2005.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent energy from a
lightning strike on the bushing for the sump drain valve from arcing
to the inside of the center fuel tank wall, which could create an
ignition source in the fuel tank and result in a fuel tank
explosion.
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.
Installation
(f) Within 60 months after the effective date of this AD,
install a new washer between the lower wing surface and the jam nut
of the sump drain valve assembly in both wings, in accordance with
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-28-0045, dated September 1, 2005.
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Issued in Renton, Washington, on December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-24243 Filed 12-19-05; 8:45 am]
BILLING CODE 4910-13-P
