Airworthiness Directives; McDonnell Douglas Model DC-8-33, -42, and -43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and -55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series Airplanes; Model DC-8-72 Airplanes; and Model DC-8-70F Series Airplanes, 8309-8311 [E7-3165]
Download as PDF
<![CDATA[
Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Proposed Rules
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:
[Amended]
hsrobinson on PROD1PC76 with PROPOSALS
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA–2007–
27339; Directorate Identifier 2006–NM–
280–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 12, 2007.
Affected ADs
(b) None.
VerDate Aug<31>2005
16:00 Feb 23, 2007
Jkt 211001
(c) This AD applies to the airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD, certificated in any category.
(1) McDonnell Douglas Model DC–10–10
and DC–10–10F airplanes, Model DC–10–15
airplanes, Model DC–10–30 and DC–10–30F
(KC–10A and KDC–10) airplanes, Model DC–
10–40 and DC–10–40F airplanes, and Model
MD–10–10F and MD–10–30F airplanes; as
identified in Boeing Alert Service Bulletin
DC10–28A254, dated September 8, 2006.
(2) McDonnell Douglas Model MD–11 and
MD–11F airplanes, as identified in Boeing
Alert Service Bulletin MD11–28A134, dated
September 8, 2006.
Unsafe Condition
(d) This AD results from a fuel boost pump
found with blown thermal fuses and a
fractured thrust washer. We are issuing this
AD to prevent failure of the fuel boost
pumps, which could lead to the potential of
ignition sources inside fuel tanks. This
condition, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss of the
airplane.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Los Angeles Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) 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 February
16, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–3166 Filed 2–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
[Docket No. FAA–2007–27334; Directorate
Identifier 2006–NM–279–AD]
Service Bulletin Reference Paragraph
Airworthiness Directives; McDonnell
Douglas Model DC–8–33, –42, and –43
Airplanes; Model DC–8–50 Series
Airplanes; Model DC–8F–54 and –55
Airplanes; Model DC–8–60 Series
Airplanes; Model DC–8–60F Series
Airplanes; Model DC–8–72 Airplanes;
and Model DC–8–70F Series Airplanes
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the following service
bulletins, as applicable:
(1) For the airplanes identified in
paragraph (c)(1) of this AD, Boeing Alert
Service Bulletin DC10–28A254, dated
September 8, 2006.
(2) For the airplanes identified in
paragraph (c)(2) of this AD, Boeing Alert
Service Bulletin MD11–28A134, dated
September 8, 2006.
Note 1: Boeing Alert Service Bulletin
DC10–28A254, dated September 8, 2006; and
Boeing Alert Service Bulletin MD11–28A134,
dated September 8, 2006; refer to Crane
Hydro-Aire Service Bulletin 60–847–28–3,
dated May 1, 2006, as an additional source
of service information for accomplishing the
modification in paragraph (g) of this AD.
Modification
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Applicability
8309
(g) At the applicable compliance time
specified in paragraph (g)(1) or (g)(2) of this
AD, modify the fuel boost pumps having part
numbers 60–847–1A, –2, and –3, in
accordance with the Accomplishment
Instructions of the applicable service
bulletin.
(1) For fuel boost pumps identified as
Configuration 1 or 2 in Table 1 of paragraph
1.E. of the applicable service bulletin, do the
modification within 120 months after the
effective date of this AD.
(2) For fuel boost pumps identified as
Configuration 3 in Table 1 of paragraph 1.E.
of the applicable service bulletin, do the
modification within 72 months after the
effective date of this AD.
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
RIN 2120–AA64
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 McDonnell Douglas airplanes
described previously. This proposed AD
would require installing bonding
jumpers to the airplane wing structure
from the fuel system in-line electrical
solenoid valves along the left and right
wing front spar. This proposed AD
results from fuel system reviews
conducted by the manufacturer. We are
proposing this AD to prevent point-ofcontact arcing or filament heating
damage in the fuel lines that could
create a potential ignition source,
which, in combination with flammable
fuel vapors, could cause a fuel tank
explosion and consequent loss of the
airplane.
We must receive comments on
this proposed AD by April 12, 2007.
DATES:
E:\FR\FM\26FEP1.SGM
26FEP1
8310
Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Proposed Rules
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, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
(D800–0024), for the service information
identified in this proposed AD.
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:
ADDRESSES:
hsrobinson on PROD1PC76 with PROPOSALS
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–2007–27334; Directorate
Identifier 2006–NM–279–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
VerDate Aug<31>2005
16:00 Feb 23, 2007
Jkt 211001
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
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
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.
We have received a report indicating
that fuel system in-line solenoid valve
installations located in fuel vapor zones
along the front spar of the left and right
wings might not have adequate ground
paths to dissipate the overcurrent from
a lightning-induced high voltage
transient. This condition, if not
corrected, could result in point-ofcontact arcing or filament heating
damage in the fuel lines that could
create a potential ignition source,
which, in combination with flammable
fuel vapors, could cause a fuel tank
explosion and consequent loss of the
airplane.
Relevant Service Information
We have reviewed Boeing Service
Bulletin DC8–28–091, dated November
7, 2006. The service bulletin describes
procedures for installing bonding
jumpers to the airplane wing structure
from the fuel system in-line electrical
solenoid valves along the left and right
wing front spar. 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 216 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
145 airplanes of U.S. registry. The
following table provides the estimated
costs for U.S. operators to comply with
this proposed AD, at an average labor
rate of $80 per work hour. The total fleet
E:\FR\FM\26FEP1.SGM
26FEP1
Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Proposed Rules
cost is estimated to be between $456,460
and $1,018,770.
ESTIMATED COSTS
Airplane
group
1
2
3
4
5
..............
..............
..............
..............
..............
Work
hours
8
9
10
8
6
Cost per
airplane
Parts
$2,508
4,237
6,226
4,473
3,674
5,113
4,154
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.
hsrobinson on PROD1PC76 with PROPOSALS
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.
16:00 Feb 23, 2007
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
$3,148
4,957 the FAA proposes to amend 14 CFR part
7,026 39 as follows:
Authority for This Rulemaking
VerDate Aug<31>2005
List of Subjects in 14 CFR Part 39
Jkt 211001
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]
8311
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Los Angeles 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 February
16, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–3165 Filed 2–23–07; 8:45 am]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
BILLING CODE 4910–13–P
McDonnell Douglas: Docket No. FAA–2007–
27334; Directorate Identifier 2006–NM–
279–AD.
Federal Aviation Administration
Comments Due Date
[Docket No. FAA–2007–27341; Directorate
Identifier 2006–NM–272–AD]
(a) The FAA must receive comments on
this AD action by April 12, 2007.
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas
Model DC–8–33, –42, and –43 airplanes;
Model DC–8–51, –52, –53, and –55 airplanes;
Model DC–8F–54 and –55 airplanes; Model
DC–8–61, –62, and –63 airplanes; Model DC–
8–61F, –62F, and –63F airplanes; Model DC–
8–72 airplanes; and Model DC–8–71F, –72F,
and –73F airplanes; certificated in any
category; as identified in Boeing Service
Bulletin DC8–28–091, dated November 7,
2006.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent point-ofcontact arcing or filament heating damage in
the fuel lines that could create a potential
ignition source, which, in combination with
flammable fuel vapors, could cause a fuel
tank explosion 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.
Installation of Bonding Jumpers
(f) Within 60 months after the effective
date of this AD, install bonding jumpers to
the airplane wing structure from the fuel
system in-line electrical solenoid valves
along the left and right wing front spar, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC8–
28–091, dated November 7, 2006.
Frm 00019
14 CFR Part 39
RIN 2120–AA64
Affected ADs
PO 00000
DEPARTMENT OF TRANSPORTATION
Fmt 4702
Sfmt 4702
Airworthiness Directives; McDonnell
Douglas Model MD–11 and MD–11F
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 all
McDonnell Douglas Model MD–11 and
MD–11F airplanes. This proposed AD
would require installing bracket
assemblies and jumper wires in the
center main wheel well to improve the
bonding path between the structure
(wall) of the lower auxiliary fuel tank
and its internal fuel pumps; measuring
the electrical resistance between the fuel
pump housings and the fuel tank
structure; and doing corrective actions if
necessary. This proposed AD results
from fuel system reviews conducted by
the manufacturer. We are proposing this
AD to detect and correct an inadequate
bond between the internal fuel pump
housings and the structure of the lower
auxiliary fuel tank. This condition, if
not corrected, could fail to meet fault
current requirements and result in a
potential ignition source that, in
combination with flammable fuel
vapors, could cause a fuel tank
explosion and consequent loss of the
airplane.
E:\FR\FM\26FEP1.SGM
26FEP1
]]>Agencies
[Federal Register Volume 72, Number 37 (Monday, February 26, 2007)]
[Proposed Rules]
[Pages 8309-8311]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-3165]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27334; Directorate Identifier 2006-NM-279-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-8-33, -42,
and -43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and -
55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series
Airplanes; Model DC-8-72 Airplanes; and Model DC-8-70F 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 McDonnell Douglas airplanes described previously. This
proposed AD would require installing bonding jumpers to the airplane
wing structure from the fuel system in-line electrical solenoid valves
along the left and right wing front spar. This proposed AD results from
fuel system reviews conducted by the manufacturer. We are proposing
this AD to prevent point-of-contact arcing or filament heating damage
in the fuel lines that could create a potential ignition source, which,
in combination with flammable fuel vapors, could cause a fuel tank
explosion and consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by April 12, 2007.
[[Page 8310]]
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, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024), for the service
information identified in this proposed AD.
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 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-
27334; Directorate Identifier 2006-NM-279-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.
We have received a report indicating that fuel system in-line
solenoid valve installations located in fuel vapor zones along the
front spar of the left and right wings might not have adequate ground
paths to dissipate the overcurrent from a lightning-induced high
voltage transient. This condition, if not corrected, could result in
point-of-contact arcing or filament heating damage in the fuel lines
that could create a potential ignition source, which, in combination
with flammable fuel vapors, could cause a fuel tank explosion and
consequent loss of the airplane.
Relevant Service Information
We have reviewed Boeing Service Bulletin DC8-28-091, dated November
7, 2006. The service bulletin describes procedures for installing
bonding jumpers to the airplane wing structure from the fuel system in-
line electrical solenoid valves along the left and right wing front
spar. 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 216 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 145 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD, at an average labor
rate of $80 per work hour. The total fleet
[[Page 8311]]
cost is estimated to be between $456,460 and $1,018,770.
Estimated Costs
------------------------------------------------------------------------
Work Cost per
Airplane group hours Parts airplane
------------------------------------------------------------------------
1....................................... 8 $2,508 $3,148
2....................................... 9 4,237 4,957
3....................................... 10 6,226 7,026
4....................................... 8 4,473 5,113
5....................................... 6 3,674 4,154
------------------------------------------------------------------------
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):
McDonnell Douglas: Docket No. FAA-2007-27334; Directorate Identifier
2006-NM-279-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 12,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas Model DC-8-33, -42, and
-43 airplanes; Model DC-8-51, -52, -53, and -55 airplanes; Model DC-
8F-54 and -55 airplanes; Model DC-8-61, -62, and -63 airplanes;
Model DC-8-61F, -62F, and -63F airplanes; Model DC-8-72 airplanes;
and Model DC-8-71F, -72F, and -73F airplanes; certificated in any
category; as identified in Boeing Service Bulletin DC8-28-091, dated
November 7, 2006.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent point-of-contact
arcing or filament heating damage in the fuel lines that could
create a potential ignition source, which, in combination with
flammable fuel vapors, could cause a fuel tank explosion 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.
Installation of Bonding Jumpers
(f) Within 60 months after the effective date of this AD,
install bonding jumpers to the airplane wing structure from the fuel
system in-line electrical solenoid valves along the left and right
wing front spar, in accordance with the Accomplishment Instructions
of Boeing Service Bulletin DC8-28-091, dated November 7, 2006.
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, Los Angeles 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 February 16, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-3165 Filed 2-23-07; 8:45 am]
BILLING CODE 4910-13-P
