Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 65446-65449 [E7-22724]
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65446
Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
Docket Number Change
We are transferring the docket for this
AD to the Federal Docket Management
System as part of our on-going docket
management consolidation efforts. The
new Docket No. is FAA–2007–0108. The
old Docket No. became the Directorate
Identifier, which is 2001–NE–15–AD.
rmajette on PROD1PC64 with RULES
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national Government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under 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 summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
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this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Adoption of the Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration amends part 39
of the Federal Aviation Regulations (14
CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–12405 (66 FR
44297, August 23, 2001), and by adding
a new airworthiness directive,
Amendment 39–15270, to read as
follows:
I
2007–24–04 CFM International, S.A.:
Amendment 39–15270. Docket No.
FAA–2007–0108; Directorate Identifier
2001–NE–15–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 6, 2007.
Alternative Methods of Compliance
(h) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Material Incorporated by Reference
(i) None.
Related Information
(j) Contact Stephen Sheely, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: stephen.k.sheely@faa.gov;
telephone (781) 238–7750; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
November 14, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–22647 Filed 11–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0211; Directorate
Identifier 2007–NM–221–AD; Amendment
39–15268; AD 2007–24–02]
RIN 2120–AA64
Affected ADs
(b) This AD supersedes AD 2001–17–14,
Amendment 39–12405.
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Applicability
(c) This AD applies to CFM International,
S.A. CFM56–5C4/1 series turbofan engines
with low pressure turbine (LPT) conical
support, part number (P/N) 337–002–407–0,
installed. These engines are installed on, but
not limited to, Airbus A340 series airplanes.
AGENCY:
Unsafe Condition
(d) This AD results from CFM
International, S.A. performing a life
extension study of the LPT conical support,
P/N 337–002–407–0. We are issuing this AD
to prevent LPT conical supports from
remaining in service beyond their certified
cyclic life limit, which could result in an
uncontained engine failure and damage to
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.
(f) Remove LPT conical support, P/N 337–
002–407–0, at or before accumulating 20,000
cycles-since-new (CSN) and replace with a
serviceable part.
(g) After the effective date of this AD, do
not install any LPT conical support, P/N
337–002–407–0, with 20,000 or more CSN,
into CFM56–5C4/1 series turbofan engines.
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Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to all Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. The existing AD currently
requires repetitive detailed inspections
for damage of the electrical wire and
sleeve that run to the fuel boost pump
through a conduit in the fuel tank, and
arcing damage of the conduit and signs
of fuel leakage into the conduit;
replacement of the sleeve with a new,
smaller-diameter sleeve; and related
investigative and corrective actions, as
applicable. This new AD reduces the
inspection threshold for certain
airplanes. This AD results from a report
of a fuel tank explosion on a Model
727–200F airplane on the ground, and a
report of chafed wires and a damaged
power cable sleeve of a fuel boost pump
discovered during an inspection on a
Model 737–300 airplane. (The fuel boost
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Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations
pump installation on certain Model 737
airplanes is almost identical to the
installation on Model 727 airplanes.)
We are issuing this AD to detect and
correct chafing of the fuel boost pump
electrical wiring and leakage of fuel into
the conduit, and to prevent electrical
arcing between the wiring and the
surrounding conduit, which could
result in arc-through of the conduit, and
consequent fire or explosion of the fuel
tank.
DATES: This AD becomes effective
December 6, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of December 6, 2007.
On June 6, 2007 (72 FR 28597, May
22, 2007), the Director of the Federal
Register approved the incorporation by
reference of Boeing Alert Service
Bulletin 737–28A1263, Revision 1,
dated March 19, 2007.
We must receive any comments on
this AD by January 22, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Suzanne Lucier, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
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Washington 98057–3356; telephone
(425) 917–6438; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
On May 2, 2007, we issued AD 2007–
11–07, amendment 39–15064 (72 FR
28597, May 22, 2007). (A correction of
that AD was published in the Federal
Register on August 21, 2007 (72 FR
46559).) That AD applies to all Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. That
AD requires repetitive detailed
inspections for damage of the electrical
wire and sleeve that run to the fuel
boost pump through a conduit in the
fuel tank, and arcing damage of the
conduit and signs of fuel leakage into
the conduit; replacement of the sleeve
with a new, smaller-diameter sleeve;
and related investigative and corrective
actions, as applicable. That AD resulted
from a report of a fuel tank explosion on
a Model 727–200F airplane on the
ground, and a report of chafed wires and
a damaged power cable sleeve of a fuel
boost pump discovered during an
inspection on a Model 737–300
airplane. The actions specified in that
AD are intended to detect and correct
chafing of the fuel boost pump electrical
wiring and leakage of fuel into the
conduit, and to prevent electrical arcing
between the wiring and the surrounding
conduit, which could result in arcthrough of the conduit, and consequent
fire or explosion of the fuel tank.
Actions Since AD Was Issued
Since we issued AD 2007–11–07, we
were contacted by an operator who
misinterpreted the compliance
threshold in a way that was not
intended. Therefore, we are issuing this
new AD to restate certain compliance
thresholds in a new way in order to
avoid misinterpretation and to ensure
continued operational safety of these
airplanes. To do so, we have based
certain compliance thresholds on
previous accomplishment of any
revision of Boeing Alert Service Bulletin
737–28A1120 identified in paragraph
(i)(1), (i)(2), (i)(3), or (i)(4) of This AD.
These revisions of Boeing Alert Service
Bulletin 737–28A1120 were previously
mandated by AD 99–21–15, amendment
39–11360 (64 FR 54763, October 8,
1999) and the two ADs it superseded.
AD 99–21–15 was superseded by AD
2007–11–07; therefore, we have not
restated the requirements of AD 99–21–
15 in this new AD.
Related Rulemaking
On May 1, 2007, we issued AD 2007–
11–08, amendment 39–15065 (72 FR
28594, May 22, 2007), which applies to
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65447
all Boeing Model 727 airplanes. AD
2007–11–08 requires repetitive
inspections for damage of the electrical
wire and sleeve that run to the fuel
boost pump though a conduit in the fuel
tank, and arcing damage of the conduit
and signs of fuel leakage into the
conduit; applicable investigative and
corrective actions; and a repetitive
engine fuel suction feed operational test.
That AD resulted from reports of a fuel
tank explosion on a Model 727–200F
airplane on the ground; and of chafed
wires and a damaged power cable sleeve
of a fuel boost pump that were
discovered during an inspection
required by an existing AD on a Model
737–300 airplane. We issued that AD to
detect and correct chafing of the fuel
boost pump electrical wiring and
leakage of fuel into the conduit, and to
prevent electrical arcing between the
wiring and the surrounding conduit,
which could result in arc-through of the
conduit, and consequent fire or
explosion of the fuel tank.
Relevant Service Information
Since we issued AD 2007–11–07,
Boeing has issued Service Bulletin 737–
28A1263, Revision 2, dated August 10,
2007. We referred to Boeing Alert
Service Bulletin 737–28A1263, Revision
1, dated March 19, 2007, as the
appropriate source of service
information for accomplishing certain
actions in AD 2007–11–07. The
procedures in Revision 2 of the service
bulletin are essentially the same as
those in Revision 1, with several
editorial changes such as a revised email address, and the addition of
references to AD 2007–11–07. Revision
2 also incorporates alternative methods
of compliance (AMOCs) previously
approved for AD 2007–11–07.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design. For this reason, we are issuing
this AD to supersede AD 2007–11–07.
This new AD retains certain
requirements of the existing AD. This
AD also reduces the compliance
threshold for certain airplanes.
Interim Action
We consider this AD interim action. If
final action is later identified, we might
consider further rulemaking then.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
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65448
Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2007–0211; Directorate Identifier 2007–
NM–221–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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.
rmajette on PROD1PC64 with RULES
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
VerDate Aug<31>2005
15:23 Nov 20, 2007
Jkt 214001
For the reasons discussed above, I
certify that the 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 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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–15064 (72
FR 28597, May 22, 2007), corrected at
72 FR 46559, August 21, 2007, and
adding the following new airworthiness
directive (AD):
I
2007–24–02 Boeing: Docket No. FAA–2007–
0211; Directorate Identifier 2007–NM–
221–AD; Amendment 39–15268.
Effective Date
(a) This AD becomes effective December 6,
2007.
Affected ADs
(b) This AD supersedes AD 2007–11–07.
Applicability
(c) This AD applies to all Boeing Model
737–100, –200, –200C, –300, –400, and –500
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a report of a fuel
tank explosion on a Model 727–200F
airplane on the ground, and a report of
chafed wires and a damaged power cable
sleeve of a fuel boost pump discovered
during an inspection on a Model 737–300
airplane. (The fuel boost pump installation
on certain Model 737 airplanes is almost
identical to the installation on Model 727
airplanes.) We are issuing this AD to detect
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and correct chafing of the fuel boost pump
electrical wiring and leakage of fuel into the
conduit, and to prevent electrical arcing
between the wiring and the surrounding
conduit, which could result in arc-through of
the conduit, and consequent fire or explosion
of the fuel tank.
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.
Certain Requirements of AD 2007–11–07
Inspection and Related Investigative and
Corrective Actions
(f) At the applicable time specified by
paragraph (f)(1) or (f)(2) of this AD: Do a
detailed inspection for damage of the sleeve
and electrical wire of the fuel boost pump;
and, before further flight, install a new,
smaller-diameter sleeve, and do related
investigative and corrective actions, as
applicable; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–28A1263, Revision 1,
dated March 19, 2007; or Boeing Service
Bulletin 737–28A1263, Revision 2, dated
August 10, 2007. After the effective date of
this AD, Revision 2 must be used. Thereafter,
repeat the detailed inspection at intervals not
to exceed 15,000 flight hours.
(1) For Model 737–100, –200, –300, –400,
and –500 series airplanes: At the time
specified in paragraph (i) or (j) of this AD, as
applicable.
(2) For Model 737–200C series airplanes:
Within 120 days after June 6, 2007 (the
effective date of AD 2007–11–07), or within
5,000 flight hours after the last inspection or
repair done in accordance with any version
of Boeing Alert Service Bulletin 737–28–
1120, whichever occurs later.
Inspection Report and Disposition of
Damaged Parts
(g) At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD: Submit
a report of the findings (both positive and
negative) of any inspection required by
paragraph (f) of this AD and send any
damaged parts to the manufacturer, as
described in Boeing Alert Service Bulletin
737–28A1263, Revision 1, dated March 19,
2007. The report must include the inspection
results, a description of any discrepancies
found, the airplane serial number, and the
number of landings and flight hours on the
airplane. Under the provisions of the
Paperwork Reduction Act (44 U.S.C. 3501 et
seq.), the Office of Management and Budget
(OMB) has approved the information
collection requirements contained in this AD
and has assigned OMB Control Number
2120–0056.
(1) For any inspection done on or after June
6, 2007: Submit the report within 30 days
after the inspection.
(2) For any inspection done before June 6,
2007: Submit the report within 30 days after
June 6, 2007.
Credit for Actions Done Using Previous
Service Information
(h) Actions accomplished before June 6,
2007, in accordance with Boeing Service
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Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations
Bulletin 737–28A1263, dated February 19,
2007, are considered acceptable for
compliance with the corresponding actions
specified in this AD.
New Requirements of This AD
Previously Required Inspection at New
Compliance Times
(i) For Model 737–100, –200, –300, –400,
and –500 series airplanes having line
numbers 1 through 3072 inclusive: Within
120 days after the effective date of this AD,
or within 5,000 flight hours after the last
inspection or repair done in accordance with
any service bulletin listed in paragraph (i)(1),
(i)(2), (i)(3), or (i)(4) of this AD, whichever
occurs later, do the actions specified in
paragraph (f) of this AD.
(1) Boeing Alert Service Bulletin 737–
28A1120, dated April 24, 1998, as revised by
Notices of Status Change NSC 01, dated May
7, 1998, NSC 02, dated May 8, 1998, and NSC
03, dated May 9, 1998.
(2) Boeing Alert Service Bulletin 737–
28A1120, Revision 1, dated May 28, 1998.
(3) Boeing Alert Service Bulletin 737–
28A1120, Revision 2, dated November 26,
1998.
(4) Boeing Service Bulletin 737–28A1120,
Revision 3, dated April 26, 2001.
(j) For Model 737–100, –200, –300, –400,
and –500 series airplanes having line
numbers 3073 and subsequent: At the
applicable time specified in paragraph (j)(1)
or (j)(2) of this AD, do the actions specified
in paragraph (f) of this AD.
(1) For airplanes on which the inspection
or repair specified in any service bulletin
listed in paragraph (i)(1), (i)(2), (i)(3), or (i)(4)
of this AD, has been done as of the effective
date of this AD: Within 120 days after the
effective date of this AD or 5,000 flight hours
after the last inspection done in accordance
with any service bulletin listed in paragraph
(i)(1), (i)(2), (i)(3), or (i)(4) of this AD,
whichever occurs later.
(2) For airplanes on which the inspection
or repair specified in any service bulletin
listed in paragraph (i)(1), (i)(2), (i)(3), or (i)(4)
of this AD, has not been done as of the
effective date of this AD: Before the
accumulation of 5,000 total flight hours, or
within 120 days after the effective date of this
AD, whichever occurs later.
Inspection Report and Disposition of
Damaged Parts
(k) For Model 737–100, –200, –300, –400,
and –500 series airplanes: At the applicable
time specified in paragraph (k)(1) or (k)(2) of
this AD, submit a report of the findings (both
positive and negative) of any inspection
required by paragraph (i) or (j) of this AD and
send any damaged parts to the manufacturer,
as described in Boeing Service Bulletin 737–
28A1263, Revision 2, dated August 10, 2007.
The report must include the inspection
results, a description of any discrepancies
found, the airplane serial number, and the
number of landings and flight hours on the
airplane. Under the provisions of the
Paperwork Reduction Act (44 U.S.C. 3501 et
seq.), the Office of Management and Budget
(OMB) has approved the information
collection requirements contained in this AD
65449
and has assigned OMB Control Number
2120–0056.
(1) For any inspection done after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(2) For any inspection done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
Alternative Methods of Compliance
(AMOCs)
(l)(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) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in
accordance with AD 99–21–15, amendment
39–11360, and AD 2007–11–07 are approved
as AMOCs for the corresponding provisions
of this AD.
Material Incorporated by Reference
(m) You must use applicable Boeing
service bulletins specified in Table 1 of this
AD to perform the actions that are required
by this AD, unless the AD specifies
otherwise.
TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE
Revision
level
Service Bulletin
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Boeing Alert Service Bulletin 737–28A1263 ..................................................................................................
Boeing Service Bulletin 737–28A1263 ..........................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Service Bulletin 737–28A1263,
Revision 2, dated August 10, 2007, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On June 6, 2007 (72 FR 28597, May 22,
2007), the Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 737–28A1263,
Revision 1, dated March 19, 2007.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, for a copy of this service information.
You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Issued in Renton, Washington, on
November 8, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–22724 Filed 11–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 77
[Docket No. FAA–2004–16982; Notice No.
07–16]
Colo Void Clause Coalition; Antenna
Systems Co-Location; Voluntary Best
Practices
Federal Aviation
Administration (FAA); DOT.
ACTION: Notice of amended policy.
AGENCY:
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
Date
1
2
March 19, 2007.
August 10, 2007.
SUMMARY: On April 27, 2004, the FAA
revised its policy regarding the colocation of antenna systems on existing
structures previously studied by the
FAA. Based on various additional
comments from industry regarding the
initial policy, the FAA finds that further
modifications to this policy are
necessary.
This policy is effective on
November 21, 2007.
DATES:
FOR FURTHER INFORMATION CONTACT:
´
Rene J. Balanga, ATC Spectrum
Engineering Services, Spectrum
Assignment and Engineering Office,
Federal Aviation Administration, 800
Independence Ave., SW., Washington,
DC 20591, Telephone (202) 267–3819 or
(202) 267–9710.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\21NOR1.SGM
21NOR1
]]>Agencies
[Federal Register Volume 72, Number 224 (Wednesday, November 21, 2007)]
[Rules and Regulations]
[Pages 65446-65449]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22724]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0211; Directorate Identifier 2007-NM-221-AD;
Amendment 39-15268; AD 2007-24-02]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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Summary: The FAA is superseding an existing airworthiness directive
(AD) that applies to all Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes. The existing AD currently requires repetitive
detailed inspections for damage of the electrical wire and sleeve that
run to the fuel boost pump through a conduit in the fuel tank, and
arcing damage of the conduit and signs of fuel leakage into the
conduit; replacement of the sleeve with a new, smaller-diameter sleeve;
and related investigative and corrective actions, as applicable. This
new AD reduces the inspection threshold for certain airplanes. This AD
results from a report of a fuel tank explosion on a Model 727-200F
airplane on the ground, and a report of chafed wires and a damaged
power cable sleeve of a fuel boost pump discovered during an inspection
on a Model 737-300 airplane. (The fuel boost
[[Page 65447]]
pump installation on certain Model 737 airplanes is almost identical to
the installation on Model 727 airplanes.) We are issuing this AD to
detect and correct chafing of the fuel boost pump electrical wiring and
leakage of fuel into the conduit, and to prevent electrical arcing
between the wiring and the surrounding conduit, which could result in
arc-through of the conduit, and consequent fire or explosion of the
fuel tank.
DATES: This AD becomes effective December 6, 2007.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 6,
2007.
On June 6, 2007 (72 FR 28597, May 22, 2007), the Director of the
Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 737-28A1263, Revision 1, dated March 19, 2007.
We must receive any comments on this AD by January 22, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone
(425) 917-6438; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
On May 2, 2007, we issued AD 2007-11-07, amendment 39-15064 (72 FR
28597, May 22, 2007). (A correction of that AD was published in the
Federal Register on August 21, 2007 (72 FR 46559).) That AD applies to
all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. That AD requires repetitive detailed inspections for damage
of the electrical wire and sleeve that run to the fuel boost pump
through a conduit in the fuel tank, and arcing damage of the conduit
and signs of fuel leakage into the conduit; replacement of the sleeve
with a new, smaller-diameter sleeve; and related investigative and
corrective actions, as applicable. That AD resulted from a report of a
fuel tank explosion on a Model 727-200F airplane on the ground, and a
report of chafed wires and a damaged power cable sleeve of a fuel boost
pump discovered during an inspection on a Model 737-300 airplane. The
actions specified in that AD are intended to detect and correct chafing
of the fuel boost pump electrical wiring and leakage of fuel into the
conduit, and to prevent electrical arcing between the wiring and the
surrounding conduit, which could result in arc-through of the conduit,
and consequent fire or explosion of the fuel tank.
Actions Since AD Was Issued
Since we issued AD 2007-11-07, we were contacted by an operator who
misinterpreted the compliance threshold in a way that was not intended.
Therefore, we are issuing this new AD to restate certain compliance
thresholds in a new way in order to avoid misinterpretation and to
ensure continued operational safety of these airplanes. To do so, we
have based certain compliance thresholds on previous accomplishment of
any revision of Boeing Alert Service Bulletin 737-28A1120 identified in
paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of This AD. These revisions
of Boeing Alert Service Bulletin 737-28A1120 were previously mandated
by AD 99-21-15, amendment 39-11360 (64 FR 54763, October 8, 1999) and
the two ADs it superseded. AD 99-21-15 was superseded by AD 2007-11-07;
therefore, we have not restated the requirements of AD 99-21-15 in this
new AD.
Related Rulemaking
On May 1, 2007, we issued AD 2007-11-08, amendment 39-15065 (72 FR
28594, May 22, 2007), which applies to all Boeing Model 727 airplanes.
AD 2007-11-08 requires repetitive inspections for damage of the
electrical wire and sleeve that run to the fuel boost pump though a
conduit in the fuel tank, and arcing damage of the conduit and signs of
fuel leakage into the conduit; applicable investigative and corrective
actions; and a repetitive engine fuel suction feed operational test.
That AD resulted from reports of a fuel tank explosion on a Model 727-
200F airplane on the ground; and of chafed wires and a damaged power
cable sleeve of a fuel boost pump that were discovered during an
inspection required by an existing AD on a Model 737-300 airplane. We
issued that AD to detect and correct chafing of the fuel boost pump
electrical wiring and leakage of fuel into the conduit, and to prevent
electrical arcing between the wiring and the surrounding conduit, which
could result in arc-through of the conduit, and consequent fire or
explosion of the fuel tank.
Relevant Service Information
Since we issued AD 2007-11-07, Boeing has issued Service Bulletin
737-28A1263, Revision 2, dated August 10, 2007. We referred to Boeing
Alert Service Bulletin 737-28A1263, Revision 1, dated March 19, 2007,
as the appropriate source of service information for accomplishing
certain actions in AD 2007-11-07. The procedures in Revision 2 of the
service bulletin are essentially the same as those in Revision 1, with
several editorial changes such as a revised e-mail address, and the
addition of references to AD 2007-11-07. Revision 2 also incorporates
alternative methods of compliance (AMOCs) previously approved for AD
2007-11-07.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. For this reason, we
are issuing this AD to supersede AD 2007-11-07. This new AD retains
certain requirements of the existing AD. This AD also reduces the
compliance threshold for certain airplanes.
Interim Action
We consider this AD interim action. If final action is later
identified, we might consider further rulemaking then.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and
[[Page 65448]]
opportunity for public comment before the AD is issued is
impracticable, and good cause exists to make this AD effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2007-0211; Directorate Identifier 2007-NM-221-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the 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 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part
39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-15064 (72 FR 28597, May 22, 2007), corrected at
72 FR 46559, August 21, 2007, and adding the following new
airworthiness directive (AD):
2007-24-02 Boeing: Docket No. FAA-2007-0211; Directorate Identifier
2007-NM-221-AD; Amendment 39-15268.
Effective Date
(a) This AD becomes effective December 6, 2007.
Affected ADs
(b) This AD supersedes AD 2007-11-07.
Applicability
(c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a report of a fuel tank explosion on a
Model 727-200F airplane on the ground, and a report of chafed wires
and a damaged power cable sleeve of a fuel boost pump discovered
during an inspection on a Model 737-300 airplane. (The fuel boost
pump installation on certain Model 737 airplanes is almost identical
to the installation on Model 727 airplanes.) We are issuing this AD
to detect and correct chafing of the fuel boost pump electrical
wiring and leakage of fuel into the conduit, and to prevent
electrical arcing between the wiring and the surrounding conduit,
which could result in arc-through of the conduit, and consequent
fire or explosion of the fuel tank.
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.
Certain Requirements of AD 2007-11-07
Inspection and Related Investigative and Corrective Actions
(f) At the applicable time specified by paragraph (f)(1) or
(f)(2) of this AD: Do a detailed inspection for damage of the sleeve
and electrical wire of the fuel boost pump; and, before further
flight, install a new, smaller-diameter sleeve, and do related
investigative and corrective actions, as applicable; in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-28A1263, Revision 1, dated March 19, 2007; or Boeing
Service Bulletin 737-28A1263, Revision 2, dated August 10, 2007.
After the effective date of this AD, Revision 2 must be used.
Thereafter, repeat the detailed inspection at intervals not to
exceed 15,000 flight hours.
(1) For Model 737-100, -200, -300, -400, and -500 series
airplanes: At the time specified in paragraph (i) or (j) of this AD,
as applicable.
(2) For Model 737-200C series airplanes: Within 120 days after
June 6, 2007 (the effective date of AD 2007-11-07), or within 5,000
flight hours after the last inspection or repair done in accordance
with any version of Boeing Alert Service Bulletin 737-28-1120,
whichever occurs later.
Inspection Report and Disposition of Damaged Parts
(g) At the applicable time specified in paragraph (g)(1) or
(g)(2) of this AD: Submit a report of the findings (both positive
and negative) of any inspection required by paragraph (f) of this AD
and send any damaged parts to the manufacturer, as described in
Boeing Alert Service Bulletin 737-28A1263, Revision 1, dated March
19, 2007. The report must include the inspection results, a
description of any discrepancies found, the airplane serial number,
and the number of landings and flight hours on the airplane. Under
the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et
seq.), the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
(1) For any inspection done on or after June 6, 2007: Submit the
report within 30 days after the inspection.
(2) For any inspection done before June 6, 2007: Submit the
report within 30 days after June 6, 2007.
Credit for Actions Done Using Previous Service Information
(h) Actions accomplished before June 6, 2007, in accordance with
Boeing Service
[[Page 65449]]
Bulletin 737-28A1263, dated February 19, 2007, are considered
acceptable for compliance with the corresponding actions specified
in this AD.
New Requirements of This AD
Previously Required Inspection at New Compliance Times
(i) For Model 737-100, -200, -300, -400, and -500 series
airplanes having line numbers 1 through 3072 inclusive: Within 120
days after the effective date of this AD, or within 5,000 flight
hours after the last inspection or repair done in accordance with
any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or
(i)(4) of this AD, whichever occurs later, do the actions specified
in paragraph (f) of this AD.
(1) Boeing Alert Service Bulletin 737-28A1120, dated April 24,
1998, as revised by Notices of Status Change NSC 01, dated May 7,
1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 9, 1998.
(2) Boeing Alert Service Bulletin 737-28A1120, Revision 1, dated
May 28, 1998.
(3) Boeing Alert Service Bulletin 737-28A1120, Revision 2, dated
November 26, 1998.
(4) Boeing Service Bulletin 737-28A1120, Revision 3, dated April
26, 2001.
(j) For Model 737-100, -200, -300, -400, and -500 series
airplanes having line numbers 3073 and subsequent: At the applicable
time specified in paragraph (j)(1) or (j)(2) of this AD, do the
actions specified in paragraph (f) of this AD.
(1) For airplanes on which the inspection or repair specified in
any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or
(i)(4) of this AD, has been done as of the effective date of this
AD: Within 120 days after the effective date of this AD or 5,000
flight hours after the last inspection done in accordance with any
service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or
(i)(4) of this AD, whichever occurs later.
(2) For airplanes on which the inspection or repair specified in
any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or
(i)(4) of this AD, has not been done as of the effective date of
this AD: Before the accumulation of 5,000 total flight hours, or
within 120 days after the effective date of this AD, whichever
occurs later.
Inspection Report and Disposition of Damaged Parts
(k) For Model 737-100, -200, -300, -400, and -500 series
airplanes: At the applicable time specified in paragraph (k)(1) or
(k)(2) of this AD, submit a report of the findings (both positive
and negative) of any inspection required by paragraph (i) or (j) of
this AD and send any damaged parts to the manufacturer, as described
in Boeing Service Bulletin 737-28A1263, Revision 2, dated August 10,
2007. The report must include the inspection results, a description
of any discrepancies found, the airplane serial number, and the
number of landings and flight hours on the airplane. Under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.),
the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
(1) For any inspection done after the effective date of this AD:
Submit the report within 30 days after the inspection.
(2) For any inspection done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in accordance with AD 99-21-15,
amendment 39-11360, and AD 2007-11-07 are approved as AMOCs for the
corresponding provisions of this AD.
Material Incorporated by Reference
(m) You must use applicable Boeing service bulletins specified
in Table 1 of this AD to perform the actions that are required by
this AD, unless the AD specifies otherwise.
Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Service Bulletin level Date
------------------------------------------------------------------------
Boeing Alert Service Bulletin 1 March 19, 2007.
737-28A1263.
Boeing Service Bulletin 737- 2 August 10, 2007.
28A1263.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Service Bulletin 737-28A1263,
Revision 2, dated August 10, 2007, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On June 6, 2007 (72 FR 28597, May 22, 2007), the Director of
the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 737-28A1263, Revision 1, dated March
19, 2007.
(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 8, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-22724 Filed 11-20-07; 8:45 am]
BILLING CODE 4910-13-P
