Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes, 8155-8159 [E9-3823]
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Federal Register / Vol. 74, No. 35 / Tuesday, February 24, 2009 / Rules and Regulations
4137; telephone (562) 627–5353; fax (562)
627–5210; has the authority to approve
AMOCs for this AD, if requested using 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 2004–05–20 are
approved as AMOCs for the requirements of
paragraphs (g)(1) and (g)(2) of this AD.
Material Incorporated by Reference
(j) You must use the service information
listed in Table 2 of this AD to perform the
actions that are required by this AD, as
applicable, unless the AD specifies
otherwise.
TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
Boeing
Boeing
Boeing
Boeing
Boeing
Boeing
Alert
Alert
Alert
Alert
Alert
Alert
Service
Service
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Revision level
DC10–29A142 ...............................................................................
DC10–29A142 ...............................................................................
DC10–29A144 ...............................................................................
DC10–29A148 ...............................................................................
MD11–29A057 ..............................................................................
MD11–29A059 including Appendix ...............................................
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin DC10–29A142,
Revision 3, dated October 15, 2005; and
Boeing Alert Service Bulletin DC10–29A148,
dated March 20, 2008; in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On April 15, 2004 (69 FR 11504, March
11, 2004), the Director of the Federal Register
approved the incorporation by reference of
Revision 02 .................
Revision 3 ...................
Revision 2 ...................
Original ........................
Revision 02 .................
Revision 2 ...................
Date
April 17, 2003.
October 15, 2005.
August 1, 2003.
March 20, 2008.
April 17, 2003.
August 1, 2003.
the service information listed in Table 3 of
this AD.
TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Service Bulletin
Boeing
Boeing
Boeing
Boeing
Alert
Alert
Alert
Alert
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
DC10–29A142 ...............................................................................
DC10–29A144 ...............................................................................
MD11–29A057 ..............................................................................
MD11–29A059 including Appendix ...............................................
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(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, California 90846–
0001; telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet https://
www.myboeingfleet.com.
(4) You may review copies of the service
information that is incorporated by reference
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(5) You may also review copies of the
service information 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on January
21, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–3123 Filed 2–23–09; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1199; Directorate
Identifier 2008–NM–207–AD; Amendment
39–15781; AD 2008–24–51]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800, and
–900 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: This document publishes in
the Federal Register an amendment
adopting airworthiness directive (AD)
2008–24–51 that was sent previously to
all known U.S. owners and operators of
Boeing Model 737–600, –700, –700C,
–800, and –900 series airplanes by
individual notices. This AD requires
accomplishing a wiring test of the
autoshutoff system to verify continuity
and a visual verification that the wiring
is correctly installed; doing corrective
actions, if necessary; and doing a
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Revision
Revision
Revision
Revision
02 .................
2 ...................
02 .................
2 ...................
Date
April 17, 2003.
August 1, 2003.
April 17, 2003.
August 1, 2003.
functional test of the autoshutoff
system, and applicable maintenance
actions. This AD is prompted by a
report of a failure of the left-hand fuel
pump of the center wing tank to shut off
after being selected ‘‘OFF’’ by the
flightcrew during flight on a Boeing
Model 737–700 series airplane.
Subsequent to that report, the failure
was found on two additional airplanes.
We are issuing this AD to prevent
extended dry-running of the fuel pump,
which could lead to localized
overheating of parts inside the fuel
pump, and which could produce an
ignition source inside the fuel tank.
DATES: This AD becomes effective
March 2, 2009 to all persons except
those persons to whom it was made
immediately effective by emergency AD
2008–24–51, issued November 18, 2008,
which contained the requirements of
this amendment.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of March 2, 2009.
We must receive comments on this
AD by April 27, 2009.
ADDRESSES: You may send comments by
any of the following methods:
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Federal Register / Vol. 74, No. 35 / Tuesday, February 24, 2009 / Rules and Regulations
• 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 Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
For the Federal Aviation
Administration Master Minimum
Equipment List for Boeing 737 100/200/
300/400/500/600/700/800/900 specified
in this AD, contact the FAA, Flight
Standards Division, Seattle Aircraft
Evaluation Group, 1601 Lind Avenue,
SW., Renton, Washington 98057. For
information on the availability of this
material at the FAA, call 425–917–6600
or fax 425–917–6638.
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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:
Samuel Spitzer, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6510; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: On
November 18, 2008, we issued
emergency AD 2008–24–51, which
applies to Boeing Model 737–600, –700,
–700C, –800, and –900 series airplanes.
Background
We received a report of failure of the
left-hand fuel pump of the center wing
tank (CWT) to shut off after being
VerDate Nov<24>2008
16:27 Feb 23, 2009
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selected ‘‘OFF’’ by the flightcrew during
flight on a Boeing Model 737–700 series
airplane. Subsequent to that report, the
failure was found on two additional
airplanes. Information indicates that the
autoshutoff system appears to function
normally; however, when the flightcrew
manually turns off the CWT pump
switches, that action turns off the righthand pump, but re-energizes the lefthand pump due to incorrect wiring. The
low-pressure lights turn off, incorrectly
indicating to the flightcrew that power
to both pumps has been removed. The
failure condition results in continual
running of the left-hand fuel pump
without indication to the flightcrew,
which could lead to localized
overheating of parts inside the fuel
pump, and which could produce an
ignition source inside the fuel tank.
Investigation revealed that incorrect
wiring could occur on airplanes on
which an autoshutoff system was
installed in accordance with Boeing
Alert Service Bulletin 737–28A1206.
Functional tests conducted in
accordance with that service bulletin are
not adequate to detect the incorrect
wiring condition.
We approved installation of the
autoshutoff system as an alternative
method of compliance to AD 2002–24–
51, amendment 39–12992 (68 FR 10,
January 2, 2003). That AD was issued to
address reports indicating that two fuel
tank pumps showed evidence of
extreme localized overheating of parts
in the priming and vapor pump section
of the fuel pump. That AD required
revising the airplane flight manual to
require the flightcrew to maintain
certain minimal fuel levels in the center
fuel tanks.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–28A1248, Revision
1, dated January 9, 2008. This service
bulletin describes procedures for
installing a power failed ‘ON’ protection
system (i.e., uncommanded pump ‘ON’
protection system) for the center tank
fuel boost pump.
FAA’s Determination and Requirements
of This AD
Since the unsafe condition described
is likely to exist or develop on other
airplanes of the same type design, we
issued emergency AD 2008–24–51 to
prevent extended dry-running of the
fuel pump, which could lead to
localized overheating of parts inside the
fuel pump, and which could produce an
ignition source inside the fuel tank. The
AD requires accomplishing a wiring test
of the autoshutoff system to verify
continuity and a visual verification that
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the wiring is correctly installed; doing
corrective actions, if necessary; and
doing a functional test of the autoshutoff
system, and applicable maintenance
actions. These maintenance actions,
which are specified in Chapter 28,
Section 28–22 of the Boeing 737–600/
700/800/900 Fault Isolation Manual,
Document D633A103, Revision 37,
dated October 15, 2008, include (but are
not limited to) doing a fault isolation
procedure, checks of the left center wing
tank boost pump functions, relays and
wiring checks, and repairs.
We found that immediate corrective
action was required; therefore, notice
and opportunity for prior public
comment thereon were impracticable
and contrary to the public interest, and
good cause existed to make the AD
effective immediately by individual
notices issued on November 18, 2008, to
all known U.S. owners and operators of
Boeing Model 737–600, –700, –700C,
–800, and –900 series airplanes. These
conditions still exist, and the AD is
hereby published in the Federal
Register as an amendment to section
39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it
effective to all persons.
Interim Action
This AD is considered to be interim
action. The inspection report that is
required by this AD will enable the
manufacturer to obtain better insight
into the nature, cause, and extent of the
failure of the left-hand fuel pump of the
CWT to shut off after being selected
‘‘OFF’’ by the flightcrew, and eventually
to develop final action to address the
unsafe condition. Once final action has
been identified, we might consider
further rulemaking.
In addition, for airplanes on which
the uncommanded pump ‘‘ON’’
protection system is installed in
accordance with Boeing Alert Service
Bulletin 737–28A1248, we are
considering further rulemaking that
might require additional testing.
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–
2008–1199; Directorate Identifier 2008–
NM–207–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
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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.
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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.
The FAA has determined that this
regulation is an emergency regulation
that must be issued immediately to
correct an unsafe condition in aircraft,
and that it is not a ‘‘significant
regulatory action’’ under Executive
Order 12866. It has been determined
further that this action involves an
emergency regulation under DOT
Regulatory Policies and Procedures (44
FR 11034, February 26, 1979). If this
emergency regulation is later deemed
significant under DOT Regulatory
Policies and Procedures, we will
prepare a final regulatory evaluation
and place it in the AD Docket. See the
ADDRESSES section for a location to
examine the regulatory evaluation, if
filed.
VerDate Nov<24>2008
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Jkt 217001
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 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 FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2008–24–51 Boeing: Amendment 39–15781.
Docket No. FAA–2008–1199; Directorate
Identifier 2008–NM–207–AD.
Effective Date
(a) This AD becomes effective March 2,
2009, to all persons except those persons to
whom it was made immediately effective by
emergency AD 2008–24–51, issued on
November 18, 2008, which contained the
requirements of this amendment.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737–
600, –700, –700C, –800, and –900 series
airplanes, certificated in any category; on
which Boeing Alert Service Bulletin 737–
28A1206 has been accomplished.
Unsafe Condition
(d) This AD results from a report of a
failure of the left-hand fuel pump of the
center wing tank (CWT) to shut off after being
selected ‘‘OFF’’ by the flightcrew during
flight on a Boeing Model 737–700 series
airplane. Subsequent to that report, the
failure was found on two additional
airplanes. The failure condition results in
continual running of the pump without
indication to the flightcrew. We are issuing
this AD to prevent extended dry-running of
the fuel pump, which could lead to localized
overheating of parts inside the fuel pump,
and which could produce an ignition source
inside 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.
Test
(f) Within 48 clock-hours after the effective
date of this AD, or prior to further flight,
whichever occurs later: Except as provided
by paragraphs (g) and (h) of this AD, do the
autoshutoff system wiring test specified in
paragraphs (f)(1) through (f)(10) of this AD.
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(1) Remove electrical power from the
airplane.
(2) Open the following circuit breakers,
and install collars and ’DO-NOT-CLOSE’ tags
on the circuit breakers.
(i) Circuit breaker (CB) C3012, XFR BUS 2
SECT 2, on the P92 panel.
(ii) CB C3002, XFR BUS 1 SECT 2, on the
P91 panel.
(iii) CB C1639, Fuel Auto S/O BST PUMP
CTR TNK L AC, on the P6–3 panel.
(3) Verify continuity between TB5060F in
terminal 5 and the bus side terminal of CB
C1639 in the P6–3 circuit breaker panel.
(4) Check that wire number W0040–6402–
14 is installed in terminal 5 of TB5060F.
(5) If, during the action required by
paragraph (f)(3) of this AD, there is no
continuity; or if, during the check required
by paragraph (f)(4) of this AD, the wire is
found not installed in TB5060F terminal 5:
Before further flight, trace wire W0040–
6402–14 from CB C1639 and re-terminate the
other end of the wire to TB5060F terminal 5.
After re-terminating the wire, before further
flight, do the actions specified in paragraphs
(f)(3) and (f)(4) of this AD.
(6) Remove the tags and collars from the
following circuit breakers and close the
circuit breakers.
(i) CB C3012, XFR BUS 2 SECT 2, on the
P92 panel.
(ii) CB C3002, XFR BUS 1 SECT 2, on the
P91 panel.
(iii) CB C1639, Fuel Auto S/O BST PUMP
CTR TNK L AC, on the P6–3 panel.
(7) Supply electrical power to the airplane.
(8) Verify the voltage at CB C1639 is 115
volts alternating current +/¥5 volts.
(9) If the voltage is not within the limits
specified in paragraph (f)(8) of this AD,
before further flight, repeat the actions
required by paragraphs (f)(1) through (f)(8) of
this AD.
(10) Test the autoshutoff system as follows:
(i) On P5–4 panel, switch Bus Transfer to
OFF.
(ii) Using only one power source (auxiliary
power unit (APU) or an engine generator),
power only AC Bus 1 with no power to AC
Bus 2.
(iii) Do the ‘‘Center Tank Boost Pump Auto
Shutoff Functional Test’’ in accordance with
paragraphs 9.A. through 9.G. of Task 28–22–
00–720–805 of the Boeing 737–600/700/800/
900 Aircraft Maintenance Manual, Document
D633A101, Revision 37, dated October 15,
2008. Accomplishment of paragraphs 9.H.
and 9.I. of the functional test should not be
accomplished.
(iv) If the autoshutoff test fails the test
required by paragraph (f)(10)(iii) of this AD:
Within 48 clock-hours after the effective date
of this AD, or before further flight, whichever
occurs later, do either paragraph (f)(10)(iv)(A)
or (f)(10)(iv)(B) of this AD.
(A) Do all applicable maintenance actions
in accordance with Chapter 28, Section 28–
22, of the Boeing 737–600/700/800/900 Fault
Isolation Manual, Document D633A103,
Revision 37, dated October 15, 2008, and
repeat the action required by paragraph
(f)(10)(iii) of this AD.
(B) Deactivate the left-hand fuel pump of
the CWT as specified in paragraph (g) of this
AD.
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Optional Deactivation/Reactivation
Reporting
(g) Deactivation of the left-hand fuel pump
of the CWT and operation in accordance with
Item 28–02, ‘Fuel Boost Pumps (Center
Tank), of the Federal Aviation
Administration Master Minimum Equipment
List for Boeing 737 100/200/300/400/500/
600/700/800/900, Revision 52, dated April
29, 2008, may be accomplished in lieu of the
requirements of paragraph (f) of this AD until
the left-hand fuel pump of the CWT is
reactivated. If the pump is deactivated,
dispatch under this configuration is allowed
for 10 days. For airplanes on which the lefthand fuel pump of the CWT is deactivated
under the provision of this paragraph: Prior
to further flight after reactivating the pump,
do the autoshutoff system wiring test and
applicable corrective actions specified in
paragraphs (f)(1) through (f)(10) of this AD.
(i) Submit a report of the findings (both
positive and negative) of the actions required
by paragraph (f) of this AD to Boeing via email at RSE.BOECOM@BOEING.COM; or via
fax at (206) 766–5682; at the applicable time
specified in paragraph (i)(1) or (i)(2) of this
AD. The report must include: a description
of the test failure; a description of the action
taken to correct the failure; the total number
of flight cycles/flight hours accumulated on
the airplane at the time of inspection; and the
date of accomplishment of Boeing Alert
Service Bulletin 737–28A1206 and total
number of flight hours/flight cycles
accumulated on the airplane on the date of
accomplishment of that service bulletin.
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) If the test is done after the effective date
of this AD: Submit the report within 10 days
after accomplishing the test.
(2) If the test was accomplished prior to the
effective date of this AD: Submit the report
within 10 days after the effective date of this
AD.
Optional Installation
(h) Accomplishing the installation of the
power failed ‘ON’ protection system (i.e.,
uncommanded pump ‘‘ON’’ protection
system) for the center tank fuel boost pump
in accordance with Boeing Alert Service
Bulletin 737–28A1248, dated December 21,
2006; or Revision 1, dated January 9, 2008;
terminates the autoshutoff system wiring test
required by paragraphs (f) and (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Samuel Spitzer, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6510; fax (425)
917–6590; has the authority to approve
AMOCs for this AD, if requested using 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.
Material Incorporated by Reference
(k) You must use the documents specified
in Table 1 of this AD, as applicable, to do the
actions required by this AD, unless the AD
specifies otherwise. If you accomplish the
optional actions specified by this AD, you
must use the documents specified in Table 2
of this AD, as applicable, to do the optional
actions specified by this AD, unless the AD
specifies otherwise.
TABLE 1—DOCUMENTS INCORPORATED BY REFERENCE FOR THE REQUIRED ACTIONS SPECIFIED IN THIS AD
Document
Page title/description
Page
number(s)
Revision level
Task 28–22–00–720–805 of the Boeing 737–600/
700/800/900 Aircraft Maintenance Manual
(AMM), Document.
D633A101, Revision 37, dated October 15, 2008 ...
AMM Part II, Practices and Procedures Title Page.
None shown ...
None noted* ...
October 15, 2008.
AMM Part II, Practices and Procedures Transmittal Letter.
AMM Part II, Practices and Procedures Effective Pages.
AMM Chapter 28, 28-Effective
Pages.
Task
28–22–00–702–805
of
AMM Section 28–22.
1 .....................
37 ...................
October 15, 2008.
1–3 .................
None noted* ...
October 15, 2008.
1–10 ...............
None noted* ...
October 15, 2008.
531–536 .........
None noted* ...
February 15, 2008.
FIM Title Page .............................
None shown ...
None noted* ...
October 15, 2008.
FIM
FIM
FIM
FIM
1 .....................
1–3 .................
1–2 .................
201–292 .........
37 ...................
None noted* ...
None noted* ...
None noted* ...
October 15, 2008.
October 15, 2008.
October 15, 2008.
February 15, 2008.
Chapter 28, Section 28–22, of the Boeing 737–600/
700/800/900 Fault Isolation Manual (FIM), Document D633A103, Revision 37, dated October 15,
2008.
Transmittal Letter .................
Effective Pages ....................
Chapter 28 Effective Pages
Section 28–22 ......................
Date
(*Only the Transmittal Letters for Boeing 737–600/700/800/900 AMM, Document D633A101, Revision 37; and Boeing 737–600/700/800/900
FIM, Document D633A103, Revision 37; contain the revision level of these documents.)
TABLE 2—DOCUMENTS INCORPORATED BY REFERENCE FOR THE OPTIONAL ACTIONS SPECIFIED IN THIS AD
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Document
Page title/description
Page
number(s)
Revision level
Date
Boeing Alert Service Bulletin 737–28A1248, dated
December 21, 2006.
Boeing Alert Service Bulletin 737–28A1248, Revision 1, dated January 9, 2008.
Department of Transportation, Federal Aviation Administration Master Minimum Equipment List
(MMEL) for Boeing 737 100/200/300/400/500/
600/700/800/900, Revision 52, dated April 29,
2008.
All ................................................
1–115 .............
Original ..........
December 21, 2006.
All ................................................
1–119 .............
1 .....................
January 9, 2008.
MMEL Title Page ........................
None shown ...
52 ...................
April 29, 2008.
VerDate Nov<24>2008
16:27 Feb 23, 2009
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Federal Register / Vol. 74, No. 35 / Tuesday, February 24, 2009 / Rules and Regulations
TABLE 2—DOCUMENTS INCORPORATED BY REFERENCE FOR THE OPTIONAL ACTIONS SPECIFIED IN THIS AD—Continued
Page title/description
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, Washington 98124–2207;
telephone 206–544–5000, extension 1; fax
206–766–5680; e-mail
me.boecom@boeing.com; Internet https://
www.myboeingfleet.com. For the Federal
Aviation Administration Master Minimum
Equipment List for Boeing 737 100/200/300/
400/500/600/700/800/900 specified in this
AD, contact the FAA, Flight Standards
Division, Seattle Aircraft Evaluation Group,
1601 Lind Avenue, SW., Renton, Washington
98057. For information on the availability of
this material at the FAA, call 425–917–6600
or fax 425–917–6638.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–3823 Filed 2–23–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0155; Directorate
Identifier 2009–CE–007–AD; Amendment
39–15825; AD 2009–05–01]
mstockstill on PROD1PC66 with RULES
RIN 2120–AA64
Airworthiness Directives; Gippsland
Aeronautics Pty. Ltd. Model GA8
Airplanes
16:27 Feb 23, 2009
Revision level
I ......................
28–2, 28–3 .....
52 ...................
52 ...................
ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above that will
supersede an existing AD. This AD
results from mandatory continuing
airworthiness information (MCAI)
issued by the aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Inspection of a high time aircraft has
revealed cracks in the Horizontal Stabiliser
rear spar splice plate and inboard main ribs
around the area of the Horizontal Stabiliser
rear pivot attachment. Additionally, failure of
some attach bolts in service may be due to
improper assembly.
This amendment is issued because the
requirement document now contains an
inspection for cracking in horizontal
stabilisers which have load transferring
fittings installed.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
March 2, 2009.
On March 2, 2009, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
We must receive comments on this
AD by March 26, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
AGENCY: Federal Aviation
Administration (FAA), DOT.
VerDate Nov<24>2008
Page
number(s)
MMEL Contents ..........................
MMEL Item 28–02, ‘Fuel Boost
Pumps (Center Tank)’.
Document
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Date
April 29, 2008.
April 29, 2008.
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:
Doug Rudolph, Aerospace Engineer, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
On February 7, 2007, we issued AD
2007–04–12, Amendment 39–14944 (72
FR 7578; February 16, 2007). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2007–04–12,
Gippsland Aeronautics has updated the
service information to include an
inspection for cracking in horizontal
stabilizers that have load transfer
fittings installed. In addition, the
previous service information allowed
spotfacing nut and bolt mating surfaces
that were damaged or not square. The
updated service information eliminated
the spotfacing action and requires
replacement of parts if nut and bolt
mating surfaces are damaged or not
square. Since repair by spotfacing is no
longer acceptable, this AD also requires
replacement of parts if previously
repaired by spotfacing.
The Civil Aviation Safety Authority
(CASA), which is the aviation authority
for Australia, has issued AD/GA8/5,
Amdt 2, dated January 22, 2009
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Inspection of a high time aircraft has
revealed cracks in the Horizontal Stabiliser
rear spar splice plate and inboard main ribs
around the area of the Horizontal Stabiliser
rear pivot attachment. Additionally, failure of
some attach bolts in service may be due to
improper assembly.
This amendment is issued because the
requirement document now contains an
inspection for cracking in horizontal
E:\FR\FM\24FER1.SGM
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]]>Agencies
[Federal Register Volume 74, Number 35 (Tuesday, February 24, 2009)]
[Rules and Regulations]
[Pages 8155-8159]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3823]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1199; Directorate Identifier 2008-NM-207-AD;
Amendment 39-15781; AD 2008-24-51]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This document publishes in the Federal Register an amendment
adopting airworthiness directive (AD) 2008-24-51 that was sent
previously to all known U.S. owners and operators of Boeing Model 737-
600, -700, -700C, -800, and -900 series airplanes by individual
notices. This AD requires accomplishing a wiring test of the
autoshutoff system to verify continuity and a visual verification that
the wiring is correctly installed; doing corrective actions, if
necessary; and doing a functional test of the autoshutoff system, and
applicable maintenance actions. This AD is prompted by a report of a
failure of the left-hand fuel pump of the center wing tank to shut off
after being selected ``OFF'' by the flightcrew during flight on a
Boeing Model 737-700 series airplane. Subsequent to that report, the
failure was found on two additional airplanes. We are issuing this AD
to prevent extended dry-running of the fuel pump, which could lead to
localized overheating of parts inside the fuel pump, and which could
produce an ignition source inside the fuel tank.
DATES: This AD becomes effective March 2, 2009 to all persons except
those persons to whom it was made immediately effective by emergency AD
2008-24-51, issued November 18, 2008, which contained the requirements
of this amendment.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of March
2, 2009.
We must receive comments on this AD by April 27, 2009.
ADDRESSES: You may send comments by any of the following methods:
[[Page 8156]]
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 Boeing service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
For the Federal Aviation Administration Master Minimum Equipment
List for Boeing 737 100/200/300/400/500/600/700/800/900 specified in
this AD, contact the FAA, Flight Standards Division, Seattle Aircraft
Evaluation Group, 1601 Lind Avenue, SW., Renton, Washington 98057. For
information on the availability of this material at the FAA, call 425-
917-6600 or fax 425-917-6638.
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: Samuel Spitzer, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6510; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: On November 18, 2008, we issued emergency AD
2008-24-51, which applies to Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes.
Background
We received a report of failure of the left-hand fuel pump of the
center wing tank (CWT) to shut off after being selected ``OFF'' by the
flightcrew during flight on a Boeing Model 737-700 series airplane.
Subsequent to that report, the failure was found on two additional
airplanes. Information indicates that the autoshutoff system appears to
function normally; however, when the flightcrew manually turns off the
CWT pump switches, that action turns off the right-hand pump, but re-
energizes the left-hand pump due to incorrect wiring. The low-pressure
lights turn off, incorrectly indicating to the flightcrew that power to
both pumps has been removed. The failure condition results in continual
running of the left-hand fuel pump without indication to the
flightcrew, which could lead to localized overheating of parts inside
the fuel pump, and which could produce an ignition source inside the
fuel tank.
Investigation revealed that incorrect wiring could occur on
airplanes on which an autoshutoff system was installed in accordance
with Boeing Alert Service Bulletin 737-28A1206. Functional tests
conducted in accordance with that service bulletin are not adequate to
detect the incorrect wiring condition.
We approved installation of the autoshutoff system as an
alternative method of compliance to AD 2002-24-51, amendment 39-12992
(68 FR 10, January 2, 2003). That AD was issued to address reports
indicating that two fuel tank pumps showed evidence of extreme
localized overheating of parts in the priming and vapor pump section of
the fuel pump. That AD required revising the airplane flight manual to
require the flightcrew to maintain certain minimal fuel levels in the
center fuel tanks.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-28A1248,
Revision 1, dated January 9, 2008. This service bulletin describes
procedures for installing a power failed `ON' protection system (i.e.,
uncommanded pump `ON' protection system) for the center tank fuel boost
pump.
FAA's Determination and Requirements of This AD
Since the unsafe condition described is likely to exist or develop
on other airplanes of the same type design, we issued emergency AD
2008-24-51 to prevent extended dry-running of the fuel pump, which
could lead to localized overheating of parts inside the fuel pump, and
which could produce an ignition source inside the fuel tank. The AD
requires accomplishing a wiring test of the autoshutoff system to
verify continuity and a visual verification that the wiring is
correctly installed; doing corrective actions, if necessary; and doing
a functional test of the autoshutoff system, and applicable maintenance
actions. These maintenance actions, which are specified in Chapter 28,
Section 28-22 of the Boeing 737-600/700/800/900 Fault Isolation Manual,
Document D633A103, Revision 37, dated October 15, 2008, include (but
are not limited to) doing a fault isolation procedure, checks of the
left center wing tank boost pump functions, relays and wiring checks,
and repairs.
We found that immediate corrective action was required; therefore,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual notices
issued on November 18, 2008, to all known U.S. owners and operators of
Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes.
These conditions still exist, and the AD is hereby published in the
Federal Register as an amendment to section 39.13 of the Federal
Aviation Regulations (14 CFR 39.13) to make it effective to all
persons.
Interim Action
This AD is considered to be interim action. The inspection report
that is required by this AD will enable the manufacturer to obtain
better insight into the nature, cause, and extent of the failure of the
left-hand fuel pump of the CWT to shut off after being selected ``OFF''
by the flightcrew, and eventually to develop final action to address
the unsafe condition. Once final action has been identified, we might
consider further rulemaking.
In addition, for airplanes on which the uncommanded pump ``ON''
protection system is installed in accordance with Boeing Alert Service
Bulletin 737-28A1248, we are considering further rulemaking that might
require additional testing.
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-2008-1199; Directorate Identifier 2008-NM-207-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy
[[Page 8157]]
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If this
emergency regulation is later deemed significant under DOT Regulatory
Policies and Procedures, we will prepare a final regulatory evaluation
and place it in the AD Docket. See the ADDRESSES section for a location
to examine the regulatory evaluation, if filed.
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 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2008-24-51 Boeing: Amendment 39-15781. Docket No. FAA-2008-1199;
Directorate Identifier 2008-NM-207-AD.
Effective Date
(a) This AD becomes effective March 2, 2009, to all persons
except those persons to whom it was made immediately effective by
emergency AD 2008-24-51, issued on November 18, 2008, which
contained the requirements of this amendment.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes, certificated in any category; on which
Boeing Alert Service Bulletin 737-28A1206 has been accomplished.
Unsafe Condition
(d) This AD results from a report of a failure of the left-hand
fuel pump of the center wing tank (CWT) to shut off after being
selected ``OFF'' by the flightcrew during flight on a Boeing Model
737-700 series airplane. Subsequent to that report, the failure was
found on two additional airplanes. The failure condition results in
continual running of the pump without indication to the flightcrew.
We are issuing this AD to prevent extended dry-running of the fuel
pump, which could lead to localized overheating of parts inside the
fuel pump, and which could produce an ignition source inside 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.
Test
(f) Within 48 clock-hours after the effective date of this AD,
or prior to further flight, whichever occurs later: Except as
provided by paragraphs (g) and (h) of this AD, do the autoshutoff
system wiring test specified in paragraphs (f)(1) through (f)(10) of
this AD.
(1) Remove electrical power from the airplane.
(2) Open the following circuit breakers, and install collars and
'DO-NOT-CLOSE' tags on the circuit breakers.
(i) Circuit breaker (CB) C3012, XFR BUS 2 SECT 2, on the P92
panel.
(ii) CB C3002, XFR BUS 1 SECT 2, on the P91 panel.
(iii) CB C1639, Fuel Auto S/O BST PUMP CTR TNK L AC, on the P6-3
panel.
(3) Verify continuity between TB5060F in terminal 5 and the bus
side terminal of CB C1639 in the P6-3 circuit breaker panel.
(4) Check that wire number W0040-6402-14 is installed in
terminal 5 of TB5060F.
(5) If, during the action required by paragraph (f)(3) of this
AD, there is no continuity; or if, during the check required by
paragraph (f)(4) of this AD, the wire is found not installed in
TB5060F terminal 5: Before further flight, trace wire W0040-6402-14
from CB C1639 and re-terminate the other end of the wire to TB5060F
terminal 5. After re-terminating the wire, before further flight, do
the actions specified in paragraphs (f)(3) and (f)(4) of this AD.
(6) Remove the tags and collars from the following circuit
breakers and close the circuit breakers.
(i) CB C3012, XFR BUS 2 SECT 2, on the P92 panel.
(ii) CB C3002, XFR BUS 1 SECT 2, on the P91 panel.
(iii) CB C1639, Fuel Auto S/O BST PUMP CTR TNK L AC, on the P6-3
panel.
(7) Supply electrical power to the airplane.
(8) Verify the voltage at CB C1639 is 115 volts alternating
current +/-5 volts.
(9) If the voltage is not within the limits specified in
paragraph (f)(8) of this AD, before further flight, repeat the
actions required by paragraphs (f)(1) through (f)(8) of this AD.
(10) Test the autoshutoff system as follows:
(i) On P5-4 panel, switch Bus Transfer to OFF.
(ii) Using only one power source (auxiliary power unit (APU) or
an engine generator), power only AC Bus 1 with no power to AC Bus 2.
(iii) Do the ``Center Tank Boost Pump Auto Shutoff Functional
Test'' in accordance with paragraphs 9.A. through 9.G. of Task 28-
22-00-720-805 of the Boeing 737-600/700/800/900 Aircraft Maintenance
Manual, Document D633A101, Revision 37, dated October 15, 2008.
Accomplishment of paragraphs 9.H. and 9.I. of the functional test
should not be accomplished.
(iv) If the autoshutoff test fails the test required by
paragraph (f)(10)(iii) of this AD: Within 48 clock-hours after the
effective date of this AD, or before further flight, whichever
occurs later, do either paragraph (f)(10)(iv)(A) or (f)(10)(iv)(B)
of this AD.
(A) Do all applicable maintenance actions in accordance with
Chapter 28, Section 28-22, of the Boeing 737-600/700/800/900 Fault
Isolation Manual, Document D633A103, Revision 37, dated October 15,
2008, and repeat the action required by paragraph (f)(10)(iii) of
this AD.
(B) Deactivate the left-hand fuel pump of the CWT as specified
in paragraph (g) of this AD.
[[Page 8158]]
Optional Deactivation/Reactivation
(g) Deactivation of the left-hand fuel pump of the CWT and
operation in accordance with Item 28-02, `Fuel Boost Pumps (Center
Tank), of the Federal Aviation Administration Master Minimum
Equipment List for Boeing 737 100/200/300/400/500/600/700/800/900,
Revision 52, dated April 29, 2008, may be accomplished in lieu of
the requirements of paragraph (f) of this AD until the left-hand
fuel pump of the CWT is reactivated. If the pump is deactivated,
dispatch under this configuration is allowed for 10 days. For
airplanes on which the left-hand fuel pump of the CWT is deactivated
under the provision of this paragraph: Prior to further flight after
reactivating the pump, do the autoshutoff system wiring test and
applicable corrective actions specified in paragraphs (f)(1) through
(f)(10) of this AD.
Optional Installation
(h) Accomplishing the installation of the power failed `ON'
protection system (i.e., uncommanded pump ``ON'' protection system)
for the center tank fuel boost pump in accordance with Boeing Alert
Service Bulletin 737-28A1248, dated December 21, 2006; or Revision
1, dated January 9, 2008; terminates the autoshutoff system wiring
test required by paragraphs (f) and (g) of this AD.
Reporting
(i) Submit a report of the findings (both positive and negative)
of the actions required by paragraph (f) of this AD to Boeing via e-
mail at RSE.BOECOM@BOEING.COM; or via fax at (206) 766-5682; at the
applicable time specified in paragraph (i)(1) or (i)(2) of this AD.
The report must include: a description of the test failure; a
description of the action taken to correct the failure; the total
number of flight cycles/flight hours accumulated on the airplane at
the time of inspection; and the date of accomplishment of Boeing
Alert Service Bulletin 737-28A1206 and total number of flight hours/
flight cycles accumulated on the airplane on the date of
accomplishment of that service bulletin. 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) If the test is done after the effective date of this AD:
Submit the report within 10 days after accomplishing the test.
(2) If the test was accomplished prior to the effective date of
this AD: Submit the report within 10 days after the effective date
of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Samuel Spitzer, Aerospace Engineer, Propulsion Branch,
ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-
6510; fax (425) 917-6590; has the authority to approve AMOCs for
this AD, if requested using 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.
Material Incorporated by Reference
(k) You must use the documents specified in Table 1 of this AD,
as applicable, to do the actions required by this AD, unless the AD
specifies otherwise. If you accomplish the optional actions
specified by this AD, you must use the documents specified in Table
2 of this AD, as applicable, to do the optional actions specified by
this AD, unless the AD specifies otherwise.
Table 1--Documents Incorporated by Reference for the Required Actions Specified in This AD
----------------------------------------------------------------------------------------------------------------
Page title/
Document description Page number(s) Revision level Date
----------------------------------------------------------------------------------------------------------------
Task 28-22-00-720-805 of the AMM Part II, None shown..... None noted*.... October 15, 2008.
Boeing 737-600/700/800/900 Practices and
Aircraft Maintenance Manual Procedures Title
(AMM), Document. Page.
D633A101, Revision 37, dated AMM Part II, 1.............. 37............. October 15, 2008.
October 15, 2008. Practices and
Procedures
Transmittal Letter.
AMM Part II, 1-3............ None noted*.... October 15, 2008.
Practices and
Procedures
Effective Pages.
AMM Chapter 28, 28- 1-10........... None noted*.... October 15, 2008.
Effective Pages.
Task 28-22-00-702- 531-536........ None noted*.... February 15, 2008.
805 of AMM Section
28-22.
----------------------------------------------------------------------------------------------------------------
Chapter 28, Section 28-22, of FIM Title Page...... None shown..... None noted*.... October 15, 2008.
the Boeing 737-600/700/800/
900 Fault Isolation Manual
(FIM), Document D633A103,
Revision 37, dated October
15, 2008.
FIM Transmittal 1.............. 37............. October 15, 2008.
Letter.
FIM Effective Pages. 1-3............ None noted*.... October 15, 2008.
FIM Chapter 28 1-2............ None noted*.... October 15, 2008.
Effective Pages.
FIM Section 28-22... 201-292........ None noted*.... February 15, 2008.
----------------------------------------------------------------------------------------------------------------
(*Only the Transmittal Letters for Boeing 737-600/700/800/900 AMM, Document D633A101, Revision 37; and Boeing
737-600/700/800/900 FIM, Document D633A103, Revision 37; contain the revision level of these documents.)
Table 2--Documents Incorporated by Reference for the Optional Actions Specified in This AD
----------------------------------------------------------------------------------------------------------------
Page title/
Document description Page number(s) Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin All................. 1-115.......... Original....... December 21, 2006.
737-28A1248, dated December
21, 2006.
Boeing Alert Service Bulletin All................. 1-119.......... 1.............. January 9, 2008.
737-28A1248, Revision 1,
dated January 9, 2008.
Department of Transportation, MMEL Title Page..... None shown..... 52............. April 29, 2008.
Federal Aviation
Administration Master Minimum
Equipment List (MMEL) for
Boeing 737 100/200/300/400/
500/600/700/800/900, Revision
52, dated April 29, 2008.
[[Page 8159]]
MMEL Contents....... I.............. 52............. April 29, 2008.
MMEL Item 28-02, 28-2, 28-3..... 52............. April 29, 2008.
`Fuel Boost Pumps
(Center Tank)'.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. For
the Federal Aviation Administration Master Minimum Equipment List
for Boeing 737 100/200/300/400/500/600/700/800/900 specified in this
AD, contact the FAA, Flight Standards Division, Seattle Aircraft
Evaluation Group, 1601 Lind Avenue, SW., Renton, Washington 98057.
For information on the availability of this material at the FAA,
call 425-917-6600 or fax 425-917-6638.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information 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/code_of_federal_
regulations/ibr_locations.html.
Issued in Renton, Washington, on December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9-3823 Filed 2-23-09; 8:45 am]
BILLING CODE 4910-13-P
