Airworthiness Directives; Boeing Model 767 Airplanes, 21166-21169 [E7-8175]
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21166
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
TABLE 1.—EXCEPTIONS TO APPLICABILITY
Airplane model
Configuration
Airbus modifications installed in production
A330, A340–200, –300 ......................................
A330, A340–200, –300 ......................................
A340–500 ...........................................................
With Modification 40161 (optional Type A door
3).
Without Modification 40161 (Type 1 door 3) ...
...........................................................................
A340–600 ...........................................................
...........................................................................
50806, 50807, 55071, and 55072.
50806 and 55071.
Either 50806, 50807, and 55071, or 50806
and 55071.
50806, 50808, 55071, and 55073.
TABLE 2.—EXCEPTIONS TO APPLICABILITY
Airplane model
Airbus Service Bulletins installed in service
A330 ............................................
A340–200, –300 ..........................
A340–500, –600 ..........................
A330–25–3173, Revision 01, dated August 2, 2006; and A330–25–3301, dated March 24, 2006.
A340–25–4191, Revision 01, dated August 2, 2006; and A340–25–4273, dated March 24, 2006.
A340–25–5004, Revision 01, dated August 2, 2006; and A340–25–5110, dated March 24, 2006.
jlentini on PROD1PC65 with PROPOSAL
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states that
several operators have reported nonautomatic deployment of slide rafts during
ground operational testing. In all cases, the
slide raft released correctly from the door but
did not inflate automatically. Pulling the
manual backup handle correctly inflated the
slide raft. Investigation conducted by the
slide raft manufacturer showed that nonautomatic deployments have two potential
root causes: Non-opening of the lacing; and
stiffness and stiction (static friction) on the
painted inflatable material. This situation, if
not corrected, could delay the evacuation of
passengers in case of an emergency. A new
design solution has been developed to ensure
the automatic slide raft deployment, which
consists of: continuous ‘‘speed lacing’’ cord
and new soft covers with rounded grommets
(this modification ensures that the lacing
opens); and a new shorter firing cable, a new
anchor block for the slide raft packboard and
a new folding procedure (this modification
ensures automatic deployment regardless of
the inflatable paint condition). Both
modifications together ensure the automatic
deployment function. The MCAI requires
accomplishment of the set of modifications.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) For slide raft P/Ns 7A1508–003/–005/
–007/–023/–025/–027/–029/–115; P/Ns
7A1539–003/–004/–005/–006/–007/–008/
–023/–024/–025/–026/–027/–028/–029/–030/
–115/ –116; P/Ns 7A1510–003/–004/–005/–
006/–007/–008/–023/–024/–025/–026/–027/
–028/–029/ –030/–115/–116; and P/Ns
4A3934–1/–2/–001/–002: No later than 36
months after the effective date of this AD,
modify the slide raft in accordance with the
instructions given in Airbus Service Bulletin
A330–25–3173, A340–25–4191, or A340–25–
5004, all Revision 01, all dated August 2,
2006; as applicable; and modify the slide raft
assembly of each door in accordance with the
instructions given in Airbus Service Bulletin
A330–25–3301, A340–25–4273, or A340–25–
5110, all dated March 24, 2006; as applicable.
(2) For slide raft P/Ns 7A1508–033/–035/
–037/–119/–121; P/Ns 7A1539–033/–034/
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16:35 Apr 27, 2007
Jkt 211001
–035/–036/–037/
–038/–119/–120/–121/–122; P/Ns 7A1510–
033/–034/–035/–036/–037/–038/ –119/–120/
–121/–122; and P/Ns 4A3934–5/–6/–7/–8: No
later than 36 months after the effective date
of this AD, modify the slide raft assembly of
each door in accordance with the
instructions given in Airbus Service Bulletin
A330–25–3301, A340–25–4273, or A340–25–
5110, all dated March 24, 2006; 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, ATTN: Tim Backman,
Aerospace Engineer, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. 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.
(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 EASA Airworthiness
Directive 2006–0354, dated November 28,
2006; and the Airbus Service Bulletins
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Fmt 4702
Sfmt 4702
specified in Table 3 of this AD for related
information.
TABLE 3.—AIRBUS SERVICE BULLETINS
Service Bulletin
A330–25–3173
A340–25–4191
A340–25–5004
A330–25–3301
A340–25–4273
A340–25–5110
Revision
level
Date
01 ........
01 ........
01 ........
Original
Original
Original
August 2, 2006.
August 2, 2006.
August 2, 2006.
March 24, 2006.
March 24, 2006.
March 24, 2006.
Issued in Renton, Washington, on April 23,
2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–8172 Filed 4–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28035; Directorate
Identifier 2006–NM–293–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767 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 767 airplanes.
This proposed AD would require sealing
certain fasteners and stiffeners in the
fuel tank, and changing certain wire
bundle clamp configurations on the fuel
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30APP1
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
tank walls. This proposed AD results
from fuel system reviews conducted by
the manufacturer. We are proposing this
AD to prevent possible ignition sources
in the auxiliary fuel tank, main fuel
tanks, and surge tanks caused by a
wiring short or lightning strike, which
could result in fuel tank explosions and
consequent loss of the airplane.
DATES: We must receive comments on
this proposed AD by June 14, 2007.
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
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: Judy
Coyle, Aerospace Engineer, Propulsion
Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6497;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
jlentini on PROD1PC65 with PROPOSAL
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–2007–28035; Directorate
Identifier 2006–NM–293–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
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
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 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’’ (66 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
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Sfmt 4702
21167
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 a 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 fuel tank explosions and consequent
loss of the airplane.
A safety assessment by Boeing
identified a certain fastener type in the
fuel tank walls that has an insufficient
bond to the structure. These fasteners
can be a path for electrical energy to
enter the fuel tank if a wiring short
occurs in a wire bundle installed along
the fuel tank boundary structure, or if
lightning strikes a wing surface. If
energy from a wiring short or lightning
strike goes through these fasteners,
arcing can occur at the ends of the
fasteners in the fuel tank. The ends of
the fasteners in the fuel tank do not
have sufficient electrical insulation to
contain the energy from the arcs. This
condition, if not corrected, could result
in a potential ignition source inside a
fuel tank.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 767–57A0100, dated
August 21, 2006. The service bulletin
describes procedures for sealing the
ends of the fasteners on the brackets that
hold the vortex generators, and, for
certain airplanes, sealing the ends of
fasteners on certain stiffeners on the rear
spar.
We have also reviewed Boeing Alert
Service Bulletin 767–57A0102, dated
October 25, 2006. The service bulletin
describes procedures for changing the
wire bundle clamp configurations at
specified locations on the fuel tank
walls, and sealing the fasteners and
certain stiffeners at specified locations
in the fuel tank.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
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21168
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
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 925 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD. There
are no U.S.-registered airplanes in
Group 3 of Service Bulletin 767–
57A0102. The average labor rate is $80
per work hour.
ESTIMATED COSTS
Service bulletin
Group
Work hours
Cost per
airplane
Parts
Number of
U.S.registered
airplanes
Fleet cost
767–57A0100 ...................................................................
1
2
6
114
(1)
(1)
$480
9,120
341
21
$163,680
191,520
767–57A0102 ...................................................................
1
2
3
246
874
24
$1,632
1,304
338
21,312
71,224
2,258
341
21
0
7,267,392
1,495,704
0
(1) Minimal.
jlentini on PROD1PC65 with PROPOSAL
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 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,
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16:35 Apr 27, 2007
Jkt 211001
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2007–28035;
Directorate Identifier 2006–NM–293–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by June 14, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 767–200,
–300, –300F, and –400ER series airplanes;
certificated in any category; as identified in
Boeing Alert Service Bulletin 767–57A0100,
dated August 21, 2006; and Boeing Alert
PO 00000
Frm 00044
Fmt 4702
Sfmt 4702
Service Bulletin 767–57A0102, dated October
25, 2006.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent possible
ignition sources in the auxiliary fuel tank,
main fuel tanks, and surge tanks caused by
a wiring short or lightning strike, which
could result in fuel tank explosions and
consequent loss 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.
Fastener Sealant Application
(f) For airplanes identified in Boeing Alert
Service Bulletin 767–57A0100, dated August
21, 2006: Within 60 months after the effective
date of this AD, seal the ends of the fasteners
on the brackets that hold the vortex
generators, and seal the ends of the fasteners
on certain stiffeners on the rear spar, as
applicable. Do the actions in accordance with
the Accomplishment Instructions of the
service bulletin.
Wire Bundle Sleeve and Clamp Installation
and Fastener Sealant Application
(g) For airplanes identified in Boeing Alert
Service Bulletin 767–57A0102, dated October
25, 2006: Within 60 months after the effective
date of this AD, change the wire bundle
clamp configurations at specified locations
on the fuel tank walls, and seal the fasteners
and certain stiffeners at specified locations
on the fuel tank. Do the actions in accordance
with the Accomplishment Instructions of the
service bulletin.
Alternative Methods of Compliance
(AMOCs)
(h)(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.
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Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules
(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 April 17,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–8175 Filed 4–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24978; Directorate
Identifier 2006–NM–108–AD]
RIN 2120–AA64
• 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, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1 L5A
(D800–0024), for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT:
William Bond, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5253; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
Airworthiness Directives; McDonnell
Douglas Model 717–200 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
jlentini on PROD1PC65 with PROPOSAL
AGENCY:
SUMMARY: The FAA is revising an earlier
proposed airworthiness directive (AD)
for certain McDonnell Douglas Model
717–200 airplanes. The original NPRM
would have required modifying the fuel
boost pump container of the center tank.
The original NPRM resulted from fuel
system reviews conducted by the
manufacturer. This action revises the
original NPRM by adding airplanes to
the applicability. We are proposing this
supplemental NPRM to prevent
exposing the fuel pump container vapor
area to electrical arcing during a fuel
pump motor case or connector burn
through, which could result in a fuel
tank explosion.
DATES: We must receive comments on
this supplemental NPRM by May 25,
2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
supplemental NPRM.
• 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
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.
VerDate Aug<31>2005
16:35 Apr 27, 2007
Jkt 211001
We invite you to submit any relevant
written data, views, or arguments
regarding this supplemental NPRM.
Send your comments to an address
listed in the ADDRESSES section. Include
the docket number ‘‘Docket No. FAA
2006–24978; Directorate Identifier
2006–NM–108–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this supplemental NPRM. We
will consider all comments received by
the closing date and may amend this
supplemental NPRM in light of those
comments.
We will post all comments submitted,
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 supplemental NPRM. 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 the 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
PO 00000
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Fmt 4702
Sfmt 4702
21169
level in the Nassif Building at the DOT
street address stated in ADDRESSES.
Comments will be available in the AD
docket shortly after the Docket
Management System receives them.
Discussion
We proposed to amend 14 CFR part
39 with a notice of proposed rulemaking
(NPRM) for an AD (the ‘‘original
NPRM’’) for certain McDonnell Douglas
Model 717–200 airplanes. The original
NPRM was published in the Federal
Register on June 8, 2006 (71 FR 33262).
The original NPRM proposed to require
modifying the fuel boost pump
container of the center tank.
Comments
We have considered the following
comments on the original NPRM.
Support for the NPRM
AirTran Airways supports the
proposed actions specified in the
NPRM.
Request To Refer to Latest Revision of
Service Bulletin
AirTran Airways and Boeing request
that we reference Boeing Service
Bulletin 717–28–0013, Revision 1, dated
April 7, 2006, in the NPRM (we referred
to Boeing Service Bulletin 717–28–0013,
dated July 28, 2004, as the appropriate
source of service information for doing
the actions specified in the NPRM).
AirTran Airways also requests that we
give credit for actions done in
accordance with the original issue.
Boeing commented that there was
additional work required by Revision 1,
but in a subsequent comment Boeing
states that this was in error and that no
additional work was needed. Boeing
also notes that Revision 2 of the service
bulletin is being drafted.
We agree to revise this AD to refer to
the latest revision of the service bulletin
as the appropriate source of service
information. We have reviewed Boeing
Service Bulletin 717–28–0013, Revision
1, dated April 7, 2006; and Boeing
Service Bulletin 717–28–0013, Revision
2, dated September 13, 2006. The
service bulletins contain essentially the
same actions as described in the original
issue of the service bulletin.
However, Revision 1 of the service
bulletin adds new airplanes to the
effectivity (fuselages number 5136
through 5146), clarifies the
configuration table, and clarifies the
installation of the hat and cover
assembles. Revision 2 of the service
bulletin revises the parts pricing and
clarifies the notes in the figures. We
have revised this AD to refer to Revision
2 of the service bulletin.
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]]>Agencies
[Federal Register Volume 72, Number 82 (Monday, April 30, 2007)]
[Proposed Rules]
[Pages 21166-21169]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-8175]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28035; Directorate Identifier 2006-NM-293-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 767 airplanes. This proposed AD would require
sealing certain fasteners and stiffeners in the fuel tank, and changing
certain wire bundle clamp configurations on the fuel
[[Page 21167]]
tank walls. This proposed AD results from fuel system reviews conducted
by the manufacturer. We are proposing this AD to prevent possible
ignition sources in the auxiliary fuel tank, main fuel tanks, and surge
tanks caused by a wiring short or lightning strike, which could result
in fuel tank explosions and consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by June 14, 2007.
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 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: Judy Coyle, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6497; 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-2007-
28035; Directorate Identifier 2006-NM-293-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 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''
(66 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 a 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 fuel tank explosions and consequent loss of the airplane.
A safety assessment by Boeing identified a certain fastener type in
the fuel tank walls that has an insufficient bond to the structure.
These fasteners can be a path for electrical energy to enter the fuel
tank if a wiring short occurs in a wire bundle installed along the fuel
tank boundary structure, or if lightning strikes a wing surface. If
energy from a wiring short or lightning strike goes through these
fasteners, arcing can occur at the ends of the fasteners in the fuel
tank. The ends of the fasteners in the fuel tank do not have sufficient
electrical insulation to contain the energy from the arcs. This
condition, if not corrected, could result in a potential ignition
source inside a fuel tank.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 767-57A0100, dated
August 21, 2006. The service bulletin describes procedures for sealing
the ends of the fasteners on the brackets that hold the vortex
generators, and, for certain airplanes, sealing the ends of fasteners
on certain stiffeners on the rear spar.
We have also reviewed Boeing Alert Service Bulletin 767-57A0102,
dated October 25, 2006. The service bulletin describes procedures for
changing the wire bundle clamp configurations at specified locations on
the fuel tank walls, and sealing the fasteners and certain stiffeners
at specified locations in the fuel tank.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
[[Page 21168]]
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 925 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD. There are no U.S.-
registered airplanes in Group 3 of Service Bulletin 767-57A0102. The
average labor rate is $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Cost per U.S.-
Service bulletin Group Work hours Parts airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
767-57A0100....................... 1 6 (\1\) $480 341 $163,680
2 114 (\1\) 9,120 21 191,520
----------------------------------------------------------------------------------------------------------------
767-57A0102....................... 1 246 $1,632 21,312 341 7,267,392
2 874 1,304 71,224 21 1,495,704
3 24 338 2,258 0 0
----------------------------------------------------------------------------------------------------------------
(1) Minimal.
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 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-2007-28035; Directorate Identifier 2006-NM-
293-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by June 14,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 767-200, -300, -300F, and -400ER
series airplanes; certificated in any category; as identified in
Boeing Alert Service Bulletin 767-57A0100, dated August 21, 2006;
and Boeing Alert Service Bulletin 767-57A0102, dated October 25,
2006.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent possible ignition
sources in the auxiliary fuel tank, main fuel tanks, and surge tanks
caused by a wiring short or lightning strike, which could result in
fuel tank explosions and consequent loss 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.
Fastener Sealant Application
(f) For airplanes identified in Boeing Alert Service Bulletin
767-57A0100, dated August 21, 2006: Within 60 months after the
effective date of this AD, seal the ends of the fasteners on the
brackets that hold the vortex generators, and seal the ends of the
fasteners on certain stiffeners on the rear spar, as applicable. Do
the actions in accordance with the Accomplishment Instructions of
the service bulletin.
Wire Bundle Sleeve and Clamp Installation and Fastener Sealant
Application
(g) For airplanes identified in Boeing Alert Service Bulletin
767-57A0102, dated October 25, 2006: Within 60 months after the
effective date of this AD, change the wire bundle clamp
configurations at specified locations on the fuel tank walls, and
seal the fasteners and certain stiffeners at specified locations on
the fuel tank. Do the actions in accordance with the Accomplishment
Instructions of the service bulletin.
Alternative Methods of Compliance (AMOCs)
(h)(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.
[[Page 21169]]
(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 April 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-8175 Filed 4-27-07; 8:45 am]
BILLING CODE 4910-13-P
