[Federal Register: February 24, 2009 (Volume 74, Number 35)]
[Rules and Regulations]
[Page 8155-8159]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24fe09-6]
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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.
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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 http://
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 http://
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 http://
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
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Page title/
Document description Page number(s) Revision level Date
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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.
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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.
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(*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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Page title/
Document description Page number(s) Revision level Date
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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)'.
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(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: http://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