Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, and -900 Series Airplanes, 53317-53324 [2011-21617]
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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations
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code_of_federal_regulations/
ibr_locations.html.
(f) This amendment becomes effective on
September 12, 2011.
Note: The subject of this AD is addressed
in European Aviation Safety Agency (France)
Emergency AD No. 2009–0109–E, dated May
7, 2009.
Issued in Fort Worth, Texas, on July 21,
2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2011–21477 Filed 8–25–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28661; Directorate
Identifier 2007–NM–013–AD; Amendment
39–16785; AD 2011–18–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD requires
installation of an automatic shutoff
system for the center tank fuel boost
pumps, and installation of a placard in
the airplane flight deck if necessary.
This AD also requires revisions to the
Limitations and Normal Procedures
sections of the airplane flight manual to
advise the flightcrew of certain
operating restrictions for airplanes
equipped with an automated center tank
fuel pump shutoff control. This AD
further requires installation of a
secondary control relay for the electrical
control circuit of each of the two center
tank fuel boost pumps. Additionally,
this AD requires a revision to the
maintenance program to incorporate
Airworthiness Limitation (AWL) No.
28–AWL–23. This AD also provides an
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SUMMARY:
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option of installation and maintenance
of universal fault interrupters using a
certain supplemental type certificate,
which terminates certain requirements
of this AD. This AD was prompted by
fuel system reviews conducted by the
manufacturer. We are issuing this AD to
prevent center tank fuel pump operation
with continuous low pressure, which
could lead to friction sparks or
overheating in the fuel pump inlet that
could create a potential ignition source
inside the center fuel tank. These
conditions, in combination with
flammable fuel vapors, could result in a
center fuel tank explosion and
consequent loss of the airplane.
DATES: This AD is effective September
30, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 30, 2011.
ADDRESSES: 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
TDG Aerospace information identified
in this AD, contact TDG Aerospace, Inc.,
545 Corporate Drive, Escondido,
California 92029; telephone 760–466–
1040; fax 760–466–1038; Internet https://
www.tdgaerospace.com; e-mail
info@tdgaerospace.com.
You may review copies of the
referenced 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.
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 address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Tak
Kobayashi, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
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53317
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: (425)
917–6499; fax: (425) 917–6590; e-mail:
Takahisa.Kobayashi@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to include an
airworthiness directive (AD) that would
apply to the specified products. That
SNPRM published in the Federal
Register on March 8, 2011 (76 FR
12634). The original NPRM (72 FR
37479, July 10, 2007) proposed to
require installation of an automatic
shutoff system for the center tank fuel
boost pumps, installation of a placard in
the airplane flight deck if necessary, and
concurrent modification of the P5–2 fuel
control module assembly. The original
NPRM also proposed to require
revisions to the Limitations and Normal
Procedures sections of the airplane
flight manual (AFM) to advise the
flightcrew of certain operating
restrictions for airplanes equipped with
an automated center tank fuel pump
shutoff control. Additionally, the
original NPRM proposed to require a
revision to the Airworthiness
Limitations (AWL) section of the
Instructions for Continued
Airworthiness (ICA) to incorporate AWL
No. 28–AWL–19 and No. 28–AWL–23.
The original NPRM further proposed to
require installation of a secondary
control relay for the electrical control
circuit of each of the two center tank
fuel boost pumps. The SNPRM
proposed to revise the original NPRM by
adding airplanes, adding additional
operational testing of the automatic
shutoff system for certain airplanes,
removing the requirement for
incorporating AWL No. 28–AWL–19
into the AWL section of the ICA, and
adding an option of installation and
maintenance of universal fault
interrupters using a certain
supplemental type certificate.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal and the FAA’s
response to each comment.
Support for SNPRM
Delta Airlines (Delta) stated that it has
no objections to the SNPRM.
Request To Correct Service Information
Citation
Boeing requested that we revise the
fifth paragraph under the ‘‘Explanation
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of Additional Changes Made to this
Supplemental NPRM’’ section of the
SNPRM to correct the model
designation portion of the document
citation provided in that paragraph.
Although we agree that there was a
typographical error in the document
citation specified in the ‘‘Explanation of
Additional Changes Made to this
Supplemental NPRM’’ section of the
SNPRM, we do not agree to revise this
AD in this regard, as that section is not
restated in the final rule. No change to
the AD is necessary in this regard.
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Request To Include Definition in
Paragraph (b) of the SNPRM
Boeing requested that we revise
paragraph (b) of the SNPRM to properly
define ‘‘2001–08–24’’ as an
airworthiness directive. We agree and
have revised paragraph (b) of this AD
accordingly.
Request To Revise Conditions Specified
in Paragraph (h) of the SNPRM
Boeing requested that we revise
paragraph (h) of the SNPRM to remove
the last sentence of the paragraph,
which specifies the conditions when a
placard is not necessary. Boeing stated
that this sentence is confusing and
possibly contradictory, and that the
placard requirement provided in those
paragraphs is well defined without the
use of this sentence.
We agree partially. We agree to
remove the first condition specified in
the second to last sentence of paragraph
(h) of this AD, which states, ‘‘If
automatic shutoff systems are installed
concurrently on all airplanes in an
operator’s fleet in accordance with
paragraph (g) of this AD * * *, the
placard installation specified in this
paragraph is not necessary.’’ If the
automatic shutoff system is
concurrently installed on all airplanes,
there will be no airplanes on which a
placard would be required to be
installed. Therefore, this condition is
unnecessary. We have revised paragraph
(h) of this AD to remove this condition.
We do not agree to remove the second
condition in the second to last sentence
of paragraph (h) of this AD. That
condition provides an option to
operators that prefer not to install a
placard on any airplane in their fleet. If
an operator intends to maintain fuel
usage restrictions specified in AD 2002–
24–51, Amendment 39–12992 (68 FR
10, January 2, 2003), and AD 2001–08–
24, Amendment 39–12201 (66 FR
20733, April 25, 2001), for all airplanes
in the fleet until the automatic shutoff
systems are installed on all of those
airplanes, the operator is not required to
install a placard, even after installing
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the automatic shutoff system on any
airplane in its fleet. We have
determined that this option should
remain available to operators, and have
not revised paragraph (h) of this AD to
remove this condition. We also have not
revised paragraph (s) of this AD to
remove the same condition specified in
the second to last sentence of paragraph
(h) of this AD.
Also, we acknowledge that a reference
to AD 2001–08–24, Amendment 39–
12201 (66 FR 20733, April 25, 2001),
was inadvertently omitted in the last
sentence of paragraph (h) of the SNPRM.
We have added a reference to AD 2001–
08–24 in paragraph (h) of this AD, and
provided additional clarification in the
‘‘Additional Changes Made to this AD’’
section of this AD.
Request To Revise Proposed Wording of
Placard in Paragraph (h) of the SNPRM
Southwest Airlines (Southwest)
requested that the SNPRM be revised to
allow alternative wording for the
placard required by paragraph (h) of the
SNPRM. Southwest stated that it has a
placard adjacent to the pilot’s primary
flight display on all of its airplanes that
are not equipped with an automatic
shutoff system, which reads, ‘‘AD 2002–
19–52 fuel usage restrictions required.’’
Southwest reported that it is unable to
find any language in either AD 2002–
19–52, Amendment 39–12900 (67 FR
61253, September 30, 2002), or AD
2002–24–51, Amendment 39–12992 (68
FR 10, January 2, 2003), that requires
the placard text proposed in paragraph
(h) of the SNPRM.
We agree partially. We have
determined that clarification of
paragraph (h) of this final rule is
necessary to prevent inadvertent
removal of the placard required by
paragraph (h) of this AD and by
paragraph (e) of AD 2002–19–52,
Amendment 39–12900 (67 FR 61253,
September 30, 2002). As discussed in
the preamble of the SNPRM, AD 2002–
19–52 requires installation of a placard,
and provides an optional terminating
action that allows removal of that
placard. The intent of the placard
installation required by AD 2002–19–52
is to address mixed operation of the
airplanes with and without the optional
terminating action accomplished within
an operator’s fleet. After issuance of AD
2002–19–52, we issued AD 2002–24–51,
Amendment 39–12992 (68 FR 10,
January 2, 2003), to mandate fuel usage
restrictions identical to those required
by AD 2002–19–52, to address an unsafe
condition not related to AD 2002–19–
52. Airworthiness Directive 2002–24–51
did not require installation of a placard,
because terminating action for that AD
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was not available at the time, and,
therefore, there was no concern about
mixed fleet operation.
We do not agree to revise the placard
wording required by paragraph (h) of
this AD. However, if a placard that
refers to AD 2002–19–52, Amendment
39–12900 (67 FR 61253, September 30,
2002), already exists on an airplane, we
have determined that use of that placard
does meet the placard installation
requirement of paragraph (h) of this AD.
Therefore, we have revised paragraph
(h) of this AD to state that installation
of a placard in accordance with
paragraph (e) of AD 2002–19–52 is
acceptable for compliance with the
requirements of paragraph (h) of this
AD, and that the placard may be
removed from an airplane only once the
terminating action specified in
paragraph (g) of AD 2002–19–52 and
installation of an automatic shutoff
system required by paragraph (g) of this
AD have been accomplished.
Request To Reference Latest AWL
Revision in Paragraph (k) of the
SNPRM
Boeing requested that we revise
paragraph (k) of the SNPRM to reference
the latest revision of the maintenance
planning data (MPD) document. Boeing
stated that the document specified in
paragraph (k) of the SNPRM has been
revised, and that the applicable
subsection has changed from ‘‘G’’ to
‘‘E.1.’’ in Revision February 2011.
We agree that this AD should refer to
the current revision of the MPD
document specified in paragraph (k) of
this AD. Therefore, we have revised
paragraph (k) of this AD to refer to
Subsection E, AWLs—Fuel Systems, of
Section 9, Airworthiness Limitations
(AWLs) and Certification Maintenance
Requirements (CMRs), of the Boeing
737–600/700/800/900 MPD Document,
D626A001–CMR, Revision March 2011.
We have also added new paragraph (t)
to this AD (and re-identified subsequent
paragraphs accordingly) to give credit to
operators that accomplish the AWL
revision required by paragraph (k) of
this AD before the effective date of this
AD using any of the following revisions
of Subsection G, Airworthiness
Limitations—Fuel System AWLs, of
Section 9, Airworthiness Limitations
(AWLs) and Certification Maintenance
Requirements (CMRs), of the Boeing
737–600/700/800/900 MPD Document,
D626A001–CMR:
• Revision March 2008
• Revision April 2008
• Revision June 2008
• Revision February 2009
• Revision March 2009
• Revision August 2009
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•
•
•
•
•
•
Revision September 2009
Revision November 2009
Revision January 2010
Revision May 2010
Revision July 2010
Revision August 2010
Paragraph (t) of this AD also provides
credit to operators that accomplish the
AWL revision required by paragraph (k)
of this AD before the effective date of
this AD using Subsection E, AWLs—
Fuel Systems, of Section 9,
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), of the Boeing 737–600/700/800/
900 MPD Document, D626A001–CMR,
Revision February 2011.
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Request To Clarify Terminating Action
for Paragraphs (m) and (n) of SNPRM
Delta requested that we revise
paragraphs (m) and (n) of the SNPRM to
clarify that accomplishing the actions
specified in paragraph (s) of the SNPRM
terminates the actions required in
paragraphs (m) and (n) of the SNPRM.
Delta pointed out that paragraph (s) of
the SNPRM terminates only paragraphs
(g) through (k) of the SNPRM, and not
paragraphs (m) and (n) of the SNPRM.
Delta stated that operators planning to
comply with the proposed requirements
by installing universal fault interrupters
(UFIs) in accordance with paragraph (s)
of the SNPRM will not accomplish
paragraphs (g), (h), and (i) of the
SNPRM. Therefore, Delta asserted that,
as the SNPRM is currently written,
operators that do not do the actions
specified in paragraphs (g), (h), and (i)
of the SNPRM will not be able to
comply with the requirements of
paragraphs (m) and (n) of the SNPRM.
We agree. Accomplishing the optional
terminating action specified in
paragraph (s) of this AD terminates the
requirements of paragraphs (g) through
(k) of this AD, making the optional
terminating action specified in
paragraph (s) of this AD equivalent to
the actions required by paragraphs (g)
through (k) of this AD. Therefore,
complying with paragraph (s) of this AD
meets the condition required to
terminate the requirements of paragraph
(a) of AD 2001–08–24, Amendment 39–
12201 (66 FR 20733, April 25, 2001),
and paragraph (b) of AD 2002–24–51,
Amendment 39–12992 (68 FR 10,
January 2, 2003). We have revised
paragraphs (m) and (n) of this AD to
state that accomplishing the actions
(i.e., optional terminating action)
specified in paragraph (s) of this AD
terminates the requirements of
paragraph (a) of AD 2001–08–24 and
paragraph (b) of AD 2002–24–51.
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Request To Provide Credit for
Aerospace Supplemental Type
Certificate (STC)
Continental Airlines (Continental)
requested that we revise the SNPRM to
give credit for incorporating universal
fault interrupters (UFIs) using TDG
Aerospace STC ST02076LA before the
effective date of the AD. Continental
pointed out that paragraphs (q) and (r)
of the SNPRM provide credit for actions
done before the effective date of the AD
using other service information.
While we do agree that installing TDG
Aerospace UFIs before the effective date
of this AD is acceptable for terminating
certain actions required by this AD, we
do not agree to revise the AD to provide
specific credit for those actions.
Installing TDG Aerospace UFIs, as
specified in paragraph (s) of this AD, is
acceptable both before and after the
effective date of this AD. Operators are
always permitted to accomplish the
requirements of an AD at a time earlier
than the specified compliance time. We
have not changed the AD in this regard.
Request To Revise Paragraph (v) of the
SNPRM To Add Contact Information
Delta requested that we revise
paragraph (v) of the SNPRM to add
contact information for TDG Aerospace.
Delta pointed out that contact
information for the other service
information identified in the SNPRM is
provided, but not for TDG Aerospace.
We agree partially. We do not agree to
revise paragraph (v) of the SNPRM,
because that paragraph is not restated in
this final rule. However, we do agree to
provide contact information for TDG
Aerospace. We have revised the
ADDRESSES section of this AD to include
this contact information.
Additional Changes Made to This AD
We have revised paragraph (h) of this
AD to clarify when a placard is not
necessary. We have determined that the
second to last sentence of paragraph (h)
of this AD should also refer to AD 2001–
08–24, Amendment 39–12201 (66 FR
20733, April 25, 2001), for clarity.
Operators that choose to maintain the
fuel usage restrictions of AD 2002–24–
51, Amendment 39–12992 (68 FR 10,
January 2, 2003), for all airplanes in
their fleet do not meet the condition to
terminate AD 2002–24–51 and AD
2001–08–24 until the actions required
by paragraphs (g) and (i) of this AD are
accomplished on all airplanes in their
fleet. Therefore, those operators are
otherwise required to comply with the
requirements of AD 2001–08–24,
regardless of whether that AD is
mentioned in paragraph (h) of this AD.
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53319
Therefore, this change does not increase
the burden on operators.
We have revised paragraph (s) of this
AD to specify that installation of TDG
Aerospace UFIs, as provided in that
paragraph, must be done in accordance
with a method approved by the
Manager, Seattle Aircraft Certification
Office (ACO), FAA, because referring to
the STC now violates Office of the
Federal Register (OFR) policies for
approval of optional materials
‘‘incorporated by reference’’ in rules.
We have added Note 5 to this AD to
specify that additional guidance on
installing TDG Aerospace UFIs can be
found in TDG Aerospace STC
ST02076LA.
We have also revised paragraph (s) of
this AD to clarify the time limit for
doing the optional terminating action.
Since paragraph (s) of this AD
terminates the actions required by
paragraphs (g) through (k) of this AD, if
done, paragraph (s) of this AD must be
accomplished within the earliest time
specified among those paragraphs to be
considered terminating action; that
earliest time is 36 months.
Additionally, we have revised
paragraph (s) of this AD to allow the use
of alternative placard wording that is
approved by an appropriate FAA
Principal Operations Inspector, instead
of requiring approval of alternative
placard wording as an alternative
method of compliance in accordance
with paragraph (u) of this AD.
We have also revised paragraph (s) of
this AD by adding a statement to allow
installation of a placard in accordance
with paragraph (e) of AD 2002–19–52,
Amendment 39–12900 (67 FR 61253,
September 30, 2002).
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously—
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
We estimate that this AD affects 685
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Number of
U.S.-registered
airplanes
Action
Labor cost
Parts cost
Cost per product
Installation of the automatic shutoff system
(Boeing Alert Service
Bulletin 737–
28A1206).
Between 94 and 117
(depending on airplane configuration)
work-hours × $85
per hour = Between
$7,990 and $9,945.
1 work-hour × $85 per
hour = $85.
1 work-hour × $85 per
hour = $85.
68 work-hours × $85
per hour = $5,780.
Between $22,994 and
$30,197 (depending
on airplane configuration).
Between $30,984 and
$40,142.
538
Between $16,669,392
and $21,596,396.
$10 ..............................
$95 ..............................
685
$65,075.
None ............................
$85 ..............................
538
$45,730.
$3,274 .........................
$9,054 .........................
685
$6,201,990.
1 work-hour × $85 per
hour = $85.
None ............................
$85 ..............................
685
$58,225.
Placard installation, if
necessary.
AFM revision .................
Installation of secondary
pump control relays
(Boeing Alert Service
Bulletin 737–
28A1248).
AWL revision to add
28–AWL–23.
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
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
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(4) 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.
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):
■
2011–18–03 The Boeing Company:
Amendment 39–16785; Docket No.
FAA–2007–28661; Directorate Identifier
2007–NM–013–AD.
Effective Date
(a) This AD is effective September 30,
2011.
Affected ADs
(b) Accomplishing certain requirements of
this AD terminates certain requirements of
AD 2001–08–24, Amendment 39–12201 (66
FR 20733, April 25, 2001); AD 2002–24–51,
Amendment 39–12992 (68 FR 10, January 2,
2003); and AD 2008–24–51, Amendment 39–
15781 (74 FR 8155, February 24, 2009).
Airworthiness Directive 2002–19–52,
Amendment 39–12900 (67 FR 61253,
September 30, 2002), is affected by this AD.
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Cost on U.S. operators
Applicability
(c) This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) The Boeing Company Model 737–600,
–700, –700C, –800, and –900 series airplanes,
identified in Boeing Alert Service Bulletin
737–28A1206, Revision 2, dated May 21,
2009.
(2) The Boeing Company Model 737–600,
–700, –700C, –800, and –900 series airplanes,
identified in Boeing Alert Service Bulletin
737–28A1248, Revision 2, dated August 28,
2009.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance (AMOC)
according to paragraph (u) of this AD. The
request should include a description of
changes to the required inspections that will
ensure the continued operational safety of
the airplane.
Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 28, Fuel.
Unsafe Condition
(e) This AD was prompted by fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent center tank
fuel pump operation with continuous low
pressure, which could lead to friction sparks
or overheating in the fuel pump inlet that
could create a potential ignition source
inside the center fuel tank. These conditions,
in combination with flammable fuel vapors,
could result in a center fuel tank explosion
and consequent loss of the airplane.
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(f) Comply with this AD within the
compliance times specified, unless already
done.
Installation of Automatic Shutoff System for
the Center Tank Fuel Boost Pumps
(g) For airplanes identified in paragraph
1.A.1. of Boeing Alert Service Bulletin 737–
28A1206, Revision 2, dated May 21, 2009:
Within 36 months after the effective date of
this AD, install an automatic shutoff system
for the center tank fuel boost pumps, by
accomplishing all of the actions specified in
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BILLING CODE 4910–13–C
Placard Installation for Mixed Fleet
Operation
(h) Prior to or concurrently with installing
an automatic shutoff system on any airplane
in an operator’s fleet, as required by
paragraph (g) of this AD, install a placard
adjacent to the pilot’s primary flight display
VerDate Mar<15>2010
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Part 1 and Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–28A1206, Revision 2, dated May 21,
2009, except that Figure 1 of this AD must
be used in lieu of Sheet 2 of Figure 11 of
Boeing Alert Service Bulletin 737–28A1206,
Revision 2, dated May 21, 2009. If a placard
has been previously installed on the airplane
in accordance with paragraph (h) of this AD,
the placard may be removed from the flight
deck of only that airplane after the automatic
shutoff system has been installed. Installing
automatic shutoff systems on all airplanes in
an operator’s fleet, in accordance with this
paragraph, terminates the placard installation
required by paragraph (h) of this AD for all
airplanes in an operator’s fleet.
Note 2: Boeing Alert Service Bulletin 737–
28A1206, Revision 2, dated May 21, 2009,
refers to Boeing Component Service Bulletin
233A3202–28–03, dated January 12, 2006, as
an additional source of guidance for
replacing the left and right center boost
pump switches of the P5–2 fuel control
module assembly with new switches and
changing the wiring of the P5–2 fuel control
module assembly.
on all airplanes in the operator’s fleet that are
not equipped with an automatic shutoff
system for the center tank fuel boost pumps.
The placard must read as follows (unless
alternative placard wording is approved by
an appropriate FAA Principal Operations
Inspector):
‘‘AD 2002–24–51 fuel usage restrictions
required.’’
Installing an automatic shutoff system, in
accordance with paragraph (g) of this AD,
terminates the placard installation required
by this paragraph for only that airplane.
Installing automatic shutoff systems on all
airplanes in an operator’s fleet, in accordance
with paragraph (g) of this AD, terminates the
placard installation required by this
paragraph for all airplanes in an operator’s
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Compliance
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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations
fleet. If operation according to the fuel usage
restrictions of AD 2002–24–51, Amendment
39–12992 (68 FR 10, January 2, 2003), and
AD 2001–08–24, Amendment 39–12201 (66
FR 20733, April 25, 2001), is maintained
until automatic shutoff systems are installed
on all airplanes in an operator’s fleet, the
placard installation specified in this
paragraph is not required. Installation of a
placard in accordance with paragraph (e) of
AD 2002–19–52, Amendment 39–12900 (67
FR 61253, September 30, 2002), is acceptable
for compliance with the placard installation
requirements of this paragraph; however,
terminating action specified in paragraph (g)
of AD 2002–19–52 and installation of an
automatic shutoff system required by
paragraph (g) of this AD must be
accomplished on the airplane before the
placard is removed from the airplane.
Airplane Flight Manual (AFM) Revision
(i) For airplanes on which Boeing Alert
Service Bulletin 737–28A1206, Revision 2,
dated May 21, 2009, has been accomplished:
At the applicable time specified in paragraph
(i)(1) or (i)(2) of this AD, do the actions
specified in paragraphs (i)(3) and (i)(4) of this
AD.
(1) For airplanes on which the terminating
action specified in paragraph (g) of AD 2002–
19–52, Amendment 39–12900 (67 FR 61253,
September 30, 2002), has been done:
Concurrently with accomplishing the actions
required by paragraph (g) of this AD.
(2) For airplanes on which the terminating
action specified in paragraph (g) of AD 2002–
19–52, Amendment 39–12900 (67 FR 61253,
September 30, 2002), has not been done:
Concurrently with accomplishing the
terminating action specified in paragraph (g)
of AD 2002–19–52.
(3) Revise Section 1 of the Limitations
section of the Boeing 737–600/–700/–700C/–
800/–900 AFM to include the following
statement. This may be done by inserting a
copy of this AD into the AFM.
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‘‘Center Tank Fuel Pumps
Intentional dry running of a center tank
fuel pump (low pressure light illuminated) is
prohibited.’’
Note 3: For clarification purposes, the AFM
limitations required by AD 2002–19–52,
Amendment 39–12900 (67 FR 61253,
September 30, 2002), continue to be required
until the optional terminating actions
specified in paragraph (g) of AD 2002–19–52
have been done.
(4) Revise Section 3 of the Normal
Procedures section of the Boeing 737–600/
–700/–700C/–800/–900 AFM to include the
following statements. This may be done by
inserting a copy of this AD into the AFM.
Alternative statements that meet the intent of
the following requirements may be used if
approved by an appropriate FAA Principal
Operations Inspector.
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‘‘CENTER TANK FUEL PUMPS
Alternative Method of Compliance (AMOC)
to AD 2001–08–24 and AD 2002–24–51 for
Aircraft With the Automated Center Tank
Fuel Pump Shutoff
Center tank fuel pumps must not be ‘‘ON’’
unless personnel are available in the flight
deck to monitor low pressure lights.
For ground operation, center tank fuel
pump switches must not be positioned ‘‘ON’’
unless the center tank fuel quantity exceeds
1000 pounds (453 kilograms), except when
defueling or transferring fuel. Upon
positioning the center tank fuel pump
switches ‘‘ON’’ verify momentary
illumination of each center tank fuel pump
low pressure light.
For ground and flight operations, the
corresponding center tank fuel pump switch
must be positioned ‘‘OFF’’ when a center
tank fuel pump low pressure light
illuminates [1]. Both center tank fuel pump
switches must be positioned ‘‘OFF’’ when the
first center tank fuel pump low pressure light
illuminates if the center tank is empty.
[1] When established in a level flight
attitude, both center tank pump switches
should be positioned ‘‘ON’’ again if the
center tank contains usable fuel.
Defueling and Fuel Transfer
When transferring fuel or defueling center
or main tanks, the fuel pump low pressure
lights must be monitored and the fuel pumps
positioned to ‘‘OFF’’ at the first indication of
the fuel pump low pressure [1].
Defueling the main tanks with passengers
on board is prohibited if the main tank fuel
pumps are powered [2].
Defueling the center tank with passengers
on board is prohibited if the center tank fuel
pumps are powered and the auto-shutoff
system is inhibited [2].
[1] Prior to transferring fuel or defueling,
conduct a lamp test of the respective fuel
pump low pressure lights.
[2] Fuel may be transferred from tank to
tank or the aircraft may be defueled with
passengers on board, provided fuel quantity
in the tank from which fuel is being taken is
maintained at or above 2000 pounds (907
kilograms).’’
Note 4: When statements identical to those
in paragraphs (i)(3) and (i)(4) of this AD have
been included in the general revisions of the
Boeing 737–600/–700/–700C/–800/–900
AFM, the general revisions may be inserted
into that AFM, and the copy of this AD may
be removed from that AFM.
Installation of Secondary Pump Control
Relays
(j) For airplanes identified in paragraph
1.A.1. of Boeing Alert Service Bulletin 737–
28A1248, Revision 2, dated August 28, 2009:
Within 60 months after the effective date of
this AD, install one secondary control relay
for the electrical control circuit of each of the
two center tank fuel boost pumps, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–28A1248, Revision 2, dated August 28,
2009.
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Airworthiness Limitations (AWL) Revision
for AWL No. 28–AWL–23
(k) For airplanes identified in paragraph
1.A.1. of Boeing Alert Service Bulletin 737–
28A1248, Revision 2, dated August 28, 2009:
Concurrently with accomplishing the actions
required by paragraph (j) of this AD, or
within 30 days after the effective date of this
AD, whichever occurs later, revise the
maintenance program by incorporating AWL
No. 28–AWL–23 of Subsection E, AWLs—
Fuel Systems, of Section 9, Airworthiness
Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), of the
Boeing 737–600/700/800/900 MPD
Document, D626A001–CMR, Revision March
2011. The initial compliance time for the
actions specified in AWL No. 28–AWL–23 is
within 1 year after accomplishing the
installation required by paragraph (j) of this
AD, or within 1 year after the effective date
of this AD, whichever occurs later.
No Alternative Inspections or Inspection
Intervals
(l) After accomplishing the applicable
actions specified in paragraph (k) of this AD,
no alternative inspections or inspection
intervals may be used unless the inspections
or inspection intervals are approved as an
AMOC in accordance with the procedures
specified in paragraph (u) of this AD.
Terminating Action for AD 2001–08–24,
Amendment 39–12201 (66 FR 20733, April
25, 2001)
(m) Accomplishing the actions required by
paragraphs (g), (h), and (i) of this AD, or
accomplishing the actions specified in
paragraph (s) of this AD, terminates the
requirements of paragraph (a) of AD 2001–
08–24, Amendment 39–12201 (66 FR 20733,
April 25, 2001), for Model 737–600, –700,
–700C, –800, and –900 series airplanes that
have the automatic shutoff system, or a TDG
Aerospace, Inc., universal fault interrupter
(UFI), installed. After accomplishing the
actions required by paragraphs (g), (h), and
(i) of this AD, or accomplishing the actions
specified in paragraph (s) of this AD, the
AFM limitation required by paragraph (a) of
AD 2001–08–24 may be removed from the
AFM for those airplanes.
Terminating Action for AD 2002–24–51,
Amendment 39–12992 (68 FR 10, January 2,
2003)
(n) Accomplishing the actions required by
paragraphs (g), (h), and (i) of this AD, or
accomplishing the actions specified in
paragraph (s) of this AD, terminates the
requirements of paragraph (b) of AD 2002–
24–51, Amendment 39–12992 (68 FR 10,
January 2, 2003), for Model 737–600, –700,
–700C, –800, and –900 series airplanes that
have the automatic shutoff system, or a TDG
Aerospace, Inc., UFI, installed. After
accomplishing the actions required by
paragraphs (g), (h), and (i) of this AD, or
accomplishing the actions specified in
paragraph (s) of this AD, the AFM limitations
required by paragraph (b) of AD 2002–24–51
may be removed from the AFM for those
airplanes.
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Terminating Action for AWL Revision
(o) Incorporating AWL No. 28–AWL–23
into the maintenance program in accordance
with paragraph (g)(3) of AD 2008–10–10 R1,
Amendment 39–16164 (75 FR 1529, January
12, 2010), terminates the corresponding
action required by paragraph (k) of this AD.
Terminating Action for AD 2008–24–51,
Amendment 39–15781 (74 FR 8155,
February 24, 2009)
(p) Accomplishing the actions required by
paragraph (g) of this AD terminates the
requirements of paragraph (f) of AD 2008–
24–51, Amendment 39–15781 (74 FR 8155,
February 24, 2009).
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(q) Actions accomplished before the
effective date of this AD in accordance with
Boeing Alert Service Bulletin 737–28A1248,
dated December 21, 2006; or Boeing Alert
Service Bulletin 737–28A1248, Revision 1,
dated January 9, 2008; are considered
acceptable for compliance with the
corresponding actions specified in paragraph
(j) of this AD.
(r) Actions accomplished before the
effective date of this AD in accordance with
Boeing Alert Service Bulletin 737–28A1206,
dated January 11, 2006; or Revision 1, dated
January 30, 2008; are considered acceptable
for compliance with the corresponding
actions specified in paragraph (g) of this AD,
provided one of the actions specified in
paragraph (r)(1) or (r)(2) of this AD have been
done.
(1) The procedures specified in paragraph
(f) of AD 2008–24–51, Amendment 39–15781
(74 FR 8155, February 24, 2009), have been
accomplished.
(2) The actions specified in Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–28A1206, Revision 2,
dated May 21, 2009, have been
accomplished.
Optional Terminating Action
(s) Installing TDG Aerospace, Inc., UFI, in
accordance with a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA, within 36 months after the
effective date of this AD, terminates the
actions required by paragraphs (g) through (k)
of this AD; provided that, concurrently with
installing a UFI on any airplane in an
operator’s fleet, a placard is installed
adjacent to the pilot’s primary flight display
on all airplanes in the operator’s fleet not
equipped with a UFI or an automatic shutoff
system. The placard must read as follows
(unless alternative placard wording is
approved by an appropriate FAA Principal
Operations Inspector):
‘‘AD 2002–24–51 fuel usage restrictions
required.’’
Installation of a placard in accordance with
paragraph (h) of this AD is acceptable for
compliance with the placard installation
required by this paragraph. Installing a TDG
Aerospace, Inc., UFI in accordance with this
paragraph on an airplane terminates the
placard installation required by this
paragraph for only that airplane. Installing
TDG Aerospace, Inc., UFIs in accordance
with this paragraph, or automatic shutoff
systems in accordance with paragraph (g) of
this AD, on all airplanes in an operator’s fleet
terminates the placard installation required
by this paragraph for all airplanes in an
operator’s fleet. If operation according to the
fuel usage restrictions of AD 2002–24–51,
Amendment 39–12992 (68 FR 10, January 2,
2003), and AD 2001–08–24, Amendment 39–
12201 (66 FR 20733, April 25, 2001), is
maintained until UFIs or automatic shutoff
systems are installed on all airplanes in an
operator’s fleet, the placard installation
specified in this paragraph is not required.
Installation of a placard in accordance with
paragraph (e) of AD 2002–19–52,
Amendment 39–12900 (67 FR 61253,
September 30, 2002), is acceptable for
compliance with the placard installation
requirements of this paragraph; however,
terminating action specified in paragraph (g)
of AD 2002–19–52 and installation of a UFI
specified by this paragraph must be
accomplished on the airplane before the
placard is removed from the airplane.
Note 5: Guidance on installing a TDG
Aerospace, Inc., UFI can be found in TDG
Aerospace, Inc., Supplemental Type
Certificate (STC) ST02076LA.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(t) Revising the maintenance program by
incorporating AWL No. 28–AWL–23 of a
revision specified in paragraphs (t)(1)
through (t)(12) of this AD of Subsection G,
Airworthiness Limitations—Fuel System
AWLs, of Section 9, Airworthiness
Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), of the
Boeing 737–600/700/800/900 MPD
Document, D626A001–CMR; or Subsection E,
AWLs—Fuel Systems, of Section 9,
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), of the Boeing 737–600/700/800/900
MPD Document, D626A001–CMR, Revision
February 2011; before the effective date of
this AD is considered acceptable for
compliance with the corresponding actions
specified in paragraph (k) of this AD.
(1) Revision March 2008.
(2) Revision April 2008.
(3) Revision June 2008.
(4) Revision February 2009.
(5) Revision March 2009.
(6) Revision August 2009.
(7) Revision September 2009.
(8) Revision November 2009.
(9) Revision January 2010.
(10) Revision May 2010.
(11) Revision July 2010.
(12) Revision August 2010.
Alternative Methods of Compliance
(AMOCs)
(u)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Related Information
(v) For more information about this AD,
contact Tak Kobayashi, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Ave.,
SW., Renton, Washington 98057–3356;
phone: (425) 917–6499; fax (425) 917–6590;
e-mail: Takahisa.Kobayashi@faa.gov.
Material Incorporated by Reference
(w) You must use the service information
contained in table 1 of this AD, as applicable,
to do the actions required by this AD, unless
the AD specifies otherwise.
TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE
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Document
Revision
Boeing Alert Service Bulletin 737–28A1206 ............................................................................................
Boeing Alert Service Bulletin 737–28A1248 ............................................................................................
AWL No. 28–AWL–23 of Subsection E, AWLs—Fuel Systems of Section 9, Airworthiness Limitations
(AWLs) and Certification Maintenance Requirements (CMRs), of the Boeing 737–600/700/800/900
Maintenance Planning Data Document, D626A001–CMR.
2 ............................
2 ............................
March 2011 ...........
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information contained in table 1
VerDate Mar<15>2010
15:41 Aug 25, 2011
Jkt 223001
of this AD under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) For Boeing service information
identified in this AD, contact Boeing
PO 00000
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Date
May 21, 2009.
August 28, 2009.
March 2011.
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, Washington 98124–2207;
telephone 206–544–5000, extension 1; fax
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206–766–5680; e-mail
me.boecom@boeing.com; Internet https://
www.myboeingfleet.com.
(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.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, 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 August
12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–21617 Filed 8–25–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0823; Directorate
Identifier 2011–SW–018–AD; Amendment
39–16765; AD 2011–17–01]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Model A109A, A109A II, A109C,
and A109K2 Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
This amendment supersedes
an existing emergency airworthiness
directive (EAD) for the specified Agusta
S.p.A. (Agusta) model helicopters. That
EAD currently requires inspecting the
main rotor scissor fitting assembly to
determine if there are 2 washers
installed under the head of each main
rotor scissor fitting assembly fixing bolt
(fixing bolt). If there are not 2 washers
installed under the head of each fixing
bolt, that EAD requires replacing each
fixing bolt and installing 2 washers
under the head of each fixing bolt. This
superseding airworthiness directive
(AD) is prompted by the determination
that a wrong part number (P/N) for the
main rotor scissor fitting assembly was
listed in the EAD. This AD retains the
requirements of the EAD and corrects a
P/N for the main rotor scissor fitting
assembly. The actions specified by this
AD are intended to prevent a crack in
a fixing bolt, failure of a fixing bolt, and
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SUMMARY:
VerDate Mar<15>2010
15:41 Aug 25, 2011
Jkt 223001
subsequent loss of control of the
helicopter.
DATES: Effective September 12, 2011.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of September
12, 2011.
Comments for inclusion in the Rules
Docket must be received on or before
October 25, 2011.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• 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.
You may get the service information
identified in this AD from Agusta
Westland, Customer Support & Services,
Via Per Tornavento 15, 21019 Somma
Lombardo (VA) Italy, ATTN: Giovanni
Cecchelli; telephone 39- 0331–711133;
fax 39 0331 711180; or at https://
www.agustawestland.com/technicalbullettins.
Examining the Docket: You may
examine the docket that contains the
AD, any comments, and other
information on the Internet at https://
www.regulations.gov, or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Operations office (telephone (800) 647–
5527) is located in Room W12–140 on
the ground floor of the West Building at
the street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
DOT/FAA Southwest Region, Sharon
Miles, Aviation Safety Engineer,
Rotorcraft Directorate, Regulations and
Policy Group, ASW–111, 2601
Meacham Blvd., Fort Worth, Texas
76137, telephone (817) 222–5122, fax
(817) 222–5961.
SUPPLEMENTARY INFORMATION:
Discussion
On January 13, 2010, we issued EAD
2010–02–51 for the Agusta Model
A109A, A109A II, A109C, and A109K2
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helicopters, which requires, within 5
hours time-in-service (TIS), inspecting
the main rotor scissor fitting assembly,
P/N 109–0110–67 and P/N 109–0110–
58, to determine if there were 2 washers
installed under the head of each fixing
bolt, P/N 109–0101–78–5. That action
was prompted by an incident where 2
of the 3 installed fixing bolts on a Model
A109K2 helicopter had cracked in
flight. The manufacturer’s investigation
revealed that the crack was caused by
inadequate information in the technical
publication for installing the fixing
bolts. This condition, if not detected
and corrected, could result in failure of
a fixing bolt and subsequent loss of
control of the helicopter.
Since issuing EAD 2010–02–51, we
have determined that the EAD contains
an incorrect P/N for the main rotor
scissor fitting assembly as listed in
paragraph (a) of the Compliance section.
The EAD states P/N ‘‘109–0110–58’’ and
the correct P/N is ‘‘109–0101–58’’.
Therefore, we are issuing this
superseding AD to correct a P/N for the
main rotor scissor fitting assembly.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Emergency AD
2009–0274–E, dated December 18, 2009
(EAD 2009–0274–E) to correct an unsafe
condition for the Agusta Model A109A,
A109A II, A109C, and A109K2 model
helicopters. EASA states that failure of
the fixing bolt ‘‘might lead to loss of
control of the helicopter.’’
Related Service Information
Agusta has issued Mandatory Alert
Bollettino Tecnico (BT) No. 109K–53 for
Model A109K2 helicopters and
Mandatory Alert BT No. 109–131 for
Model A109A, A109A II, and A109C
helicopters, both dated December 18,
2009. The BTs specify a one-time
inspection for correct installation of the
main rotor scissor fitting assembly by
determining if 2 washers are installed
under the head of each fixing bolt. If 2
washers are not installed under the head
of each fixing bolt, the BTs specify
replacing each fixing bolt with an
airworthy fixing bolt and installing 2
washers under the head of each fixing
bolt. EASA classified this service
bulletin as mandatory and issued EAD
No. 2009–0274–E to ensure the
continued airworthiness of these
helicopters.
FAA’s Evaluation and Unsafe Condition
Determination
These helicopters have been approved
by the aviation authority of Italy, and
are approved for operation in the United
States. Pursuant to our bilateral
E:\FR\FM\26AUR1.SGM
26AUR1
]]>Agencies
[Federal Register Volume 76, Number 166 (Friday, August 26, 2011)]
[Rules and Regulations]
[Pages 53317-53324]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-21617]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28661; Directorate Identifier 2007-NM-013-AD;
Amendment 39-16785; AD 2011-18-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-600, -700,
-700C, -800, and -900 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD requires installation of an automatic
shutoff system for the center tank fuel boost pumps, and installation
of a placard in the airplane flight deck if necessary. This AD also
requires revisions to the Limitations and Normal Procedures sections of
the airplane flight manual to advise the flightcrew of certain
operating restrictions for airplanes equipped with an automated center
tank fuel pump shutoff control. This AD further requires installation
of a secondary control relay for the electrical control circuit of each
of the two center tank fuel boost pumps. Additionally, this AD requires
a revision to the maintenance program to incorporate Airworthiness
Limitation (AWL) No. 28-AWL-23. This AD also provides an option of
installation and maintenance of universal fault interrupters using a
certain supplemental type certificate, which terminates certain
requirements of this AD. This AD was prompted by fuel system reviews
conducted by the manufacturer. We are issuing this AD to prevent center
tank fuel pump operation with continuous low pressure, which could lead
to friction sparks or overheating in the fuel pump inlet that could
create a potential ignition source inside the center fuel tank. These
conditions, in combination with flammable fuel vapors, could result in
a center fuel tank explosion and consequent loss of the airplane.
DATES: This AD is effective September 30, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 30,
2011.
ADDRESSES: 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 TDG
Aerospace information identified in this AD, contact TDG Aerospace,
Inc., 545 Corporate Drive, Escondido, California 92029; telephone 760-
466-1040; fax 760-466-1038; Internet https://www.tdgaerospace.com; e-
mail info@tdgaerospace.com.
You may review copies of the referenced 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.
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 address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone:
(425) 917-6499; fax: (425) 917-6590; e-mail:
Takahisa.Kobayashi@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to include an airworthiness directive (AD) that
would apply to the specified products. That SNPRM published in the
Federal Register on March 8, 2011 (76 FR 12634). The original NPRM (72
FR 37479, July 10, 2007) proposed to require installation of an
automatic shutoff system for the center tank fuel boost pumps,
installation of a placard in the airplane flight deck if necessary, and
concurrent modification of the P5-2 fuel control module assembly. The
original NPRM also proposed to require revisions to the Limitations and
Normal Procedures sections of the airplane flight manual (AFM) to
advise the flightcrew of certain operating restrictions for airplanes
equipped with an automated center tank fuel pump shutoff control.
Additionally, the original NPRM proposed to require a revision to the
Airworthiness Limitations (AWL) section of the Instructions for
Continued Airworthiness (ICA) to incorporate AWL No. 28-AWL-19 and No.
28-AWL-23. The original NPRM further proposed to require installation
of a secondary control relay for the electrical control circuit of each
of the two center tank fuel boost pumps. The SNPRM proposed to revise
the original NPRM by adding airplanes, adding additional operational
testing of the automatic shutoff system for certain airplanes, removing
the requirement for incorporating AWL No. 28-AWL-19 into the AWL
section of the ICA, and adding an option of installation and
maintenance of universal fault interrupters using a certain
supplemental type certificate.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Support for SNPRM
Delta Airlines (Delta) stated that it has no objections to the
SNPRM.
Request To Correct Service Information Citation
Boeing requested that we revise the fifth paragraph under the
``Explanation
[[Page 53318]]
of Additional Changes Made to this Supplemental NPRM'' section of the
SNPRM to correct the model designation portion of the document citation
provided in that paragraph.
Although we agree that there was a typographical error in the
document citation specified in the ``Explanation of Additional Changes
Made to this Supplemental NPRM'' section of the SNPRM, we do not agree
to revise this AD in this regard, as that section is not restated in
the final rule. No change to the AD is necessary in this regard.
Request To Include Definition in Paragraph (b) of the SNPRM
Boeing requested that we revise paragraph (b) of the SNPRM to
properly define ``2001-08-24'' as an airworthiness directive. We agree
and have revised paragraph (b) of this AD accordingly.
Request To Revise Conditions Specified in Paragraph (h) of the SNPRM
Boeing requested that we revise paragraph (h) of the SNPRM to
remove the last sentence of the paragraph, which specifies the
conditions when a placard is not necessary. Boeing stated that this
sentence is confusing and possibly contradictory, and that the placard
requirement provided in those paragraphs is well defined without the
use of this sentence.
We agree partially. We agree to remove the first condition
specified in the second to last sentence of paragraph (h) of this AD,
which states, ``If automatic shutoff systems are installed concurrently
on all airplanes in an operator's fleet in accordance with paragraph
(g) of this AD * * *, the placard installation specified in this
paragraph is not necessary.'' If the automatic shutoff system is
concurrently installed on all airplanes, there will be no airplanes on
which a placard would be required to be installed. Therefore, this
condition is unnecessary. We have revised paragraph (h) of this AD to
remove this condition.
We do not agree to remove the second condition in the second to
last sentence of paragraph (h) of this AD. That condition provides an
option to operators that prefer not to install a placard on any
airplane in their fleet. If an operator intends to maintain fuel usage
restrictions specified in AD 2002-24-51, Amendment 39-12992 (68 FR 10,
January 2, 2003), and AD 2001-08-24, Amendment 39-12201 (66 FR 20733,
April 25, 2001), for all airplanes in the fleet until the automatic
shutoff systems are installed on all of those airplanes, the operator
is not required to install a placard, even after installing the
automatic shutoff system on any airplane in its fleet. We have
determined that this option should remain available to operators, and
have not revised paragraph (h) of this AD to remove this condition. We
also have not revised paragraph (s) of this AD to remove the same
condition specified in the second to last sentence of paragraph (h) of
this AD.
Also, we acknowledge that a reference to AD 2001-08-24, Amendment
39-12201 (66 FR 20733, April 25, 2001), was inadvertently omitted in
the last sentence of paragraph (h) of the SNPRM. We have added a
reference to AD 2001-08-24 in paragraph (h) of this AD, and provided
additional clarification in the ``Additional Changes Made to this AD''
section of this AD.
Request To Revise Proposed Wording of Placard in Paragraph (h) of the
SNPRM
Southwest Airlines (Southwest) requested that the SNPRM be revised
to allow alternative wording for the placard required by paragraph (h)
of the SNPRM. Southwest stated that it has a placard adjacent to the
pilot's primary flight display on all of its airplanes that are not
equipped with an automatic shutoff system, which reads, ``AD 2002-19-52
fuel usage restrictions required.'' Southwest reported that it is
unable to find any language in either AD 2002-19-52, Amendment 39-12900
(67 FR 61253, September 30, 2002), or AD 2002-24-51, Amendment 39-12992
(68 FR 10, January 2, 2003), that requires the placard text proposed in
paragraph (h) of the SNPRM.
We agree partially. We have determined that clarification of
paragraph (h) of this final rule is necessary to prevent inadvertent
removal of the placard required by paragraph (h) of this AD and by
paragraph (e) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253,
September 30, 2002). As discussed in the preamble of the SNPRM, AD
2002-19-52 requires installation of a placard, and provides an optional
terminating action that allows removal of that placard. The intent of
the placard installation required by AD 2002-19-52 is to address mixed
operation of the airplanes with and without the optional terminating
action accomplished within an operator's fleet. After issuance of AD
2002-19-52, we issued AD 2002-24-51, Amendment 39-12992 (68 FR 10,
January 2, 2003), to mandate fuel usage restrictions identical to those
required by AD 2002-19-52, to address an unsafe condition not related
to AD 2002-19-52. Airworthiness Directive 2002-24-51 did not require
installation of a placard, because terminating action for that AD was
not available at the time, and, therefore, there was no concern about
mixed fleet operation.
We do not agree to revise the placard wording required by paragraph
(h) of this AD. However, if a placard that refers to AD 2002-19-52,
Amendment 39-12900 (67 FR 61253, September 30, 2002), already exists on
an airplane, we have determined that use of that placard does meet the
placard installation requirement of paragraph (h) of this AD.
Therefore, we have revised paragraph (h) of this AD to state that
installation of a placard in accordance with paragraph (e) of AD 2002-
19-52 is acceptable for compliance with the requirements of paragraph
(h) of this AD, and that the placard may be removed from an airplane
only once the terminating action specified in paragraph (g) of AD 2002-
19-52 and installation of an automatic shutoff system required by
paragraph (g) of this AD have been accomplished.
Request To Reference Latest AWL Revision in Paragraph (k) of the SNPRM
Boeing requested that we revise paragraph (k) of the SNPRM to
reference the latest revision of the maintenance planning data (MPD)
document. Boeing stated that the document specified in paragraph (k) of
the SNPRM has been revised, and that the applicable subsection has
changed from ``G'' to ``E.1.'' in Revision February 2011.
We agree that this AD should refer to the current revision of the
MPD document specified in paragraph (k) of this AD. Therefore, we have
revised paragraph (k) of this AD to refer to Subsection E, AWLs--Fuel
Systems, of Section 9, Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), of the Boeing 737-600/
700/800/900 MPD Document, D626A001-CMR, Revision March 2011.
We have also added new paragraph (t) to this AD (and re-identified
subsequent paragraphs accordingly) to give credit to operators that
accomplish the AWL revision required by paragraph (k) of this AD before
the effective date of this AD using any of the following revisions of
Subsection G, Airworthiness Limitations--Fuel System AWLs, of Section
9, Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), of the Boeing 737-600/700/800/900 MPD Document,
D626A001-CMR:
Revision March 2008
Revision April 2008
Revision June 2008
Revision February 2009
Revision March 2009
Revision August 2009
[[Page 53319]]
Revision September 2009
Revision November 2009
Revision January 2010
Revision May 2010
Revision July 2010
Revision August 2010
Paragraph (t) of this AD also provides credit to operators that
accomplish the AWL revision required by paragraph (k) of this AD before
the effective date of this AD using Subsection E, AWLs--Fuel Systems,
of Section 9, Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), of the Boeing 737-600/700/800/900 MPD
Document, D626A001-CMR, Revision February 2011.
Request To Clarify Terminating Action for Paragraphs (m) and (n) of
SNPRM
Delta requested that we revise paragraphs (m) and (n) of the SNPRM
to clarify that accomplishing the actions specified in paragraph (s) of
the SNPRM terminates the actions required in paragraphs (m) and (n) of
the SNPRM. Delta pointed out that paragraph (s) of the SNPRM terminates
only paragraphs (g) through (k) of the SNPRM, and not paragraphs (m)
and (n) of the SNPRM. Delta stated that operators planning to comply
with the proposed requirements by installing universal fault
interrupters (UFIs) in accordance with paragraph (s) of the SNPRM will
not accomplish paragraphs (g), (h), and (i) of the SNPRM. Therefore,
Delta asserted that, as the SNPRM is currently written, operators that
do not do the actions specified in paragraphs (g), (h), and (i) of the
SNPRM will not be able to comply with the requirements of paragraphs
(m) and (n) of the SNPRM.
We agree. Accomplishing the optional terminating action specified
in paragraph (s) of this AD terminates the requirements of paragraphs
(g) through (k) of this AD, making the optional terminating action
specified in paragraph (s) of this AD equivalent to the actions
required by paragraphs (g) through (k) of this AD. Therefore, complying
with paragraph (s) of this AD meets the condition required to terminate
the requirements of paragraph (a) of AD 2001-08-24, Amendment 39-12201
(66 FR 20733, April 25, 2001), and paragraph (b) of AD 2002-24-51,
Amendment 39-12992 (68 FR 10, January 2, 2003). We have revised
paragraphs (m) and (n) of this AD to state that accomplishing the
actions (i.e., optional terminating action) specified in paragraph (s)
of this AD terminates the requirements of paragraph (a) of AD 2001-08-
24 and paragraph (b) of AD 2002-24-51.
Request To Provide Credit for Aerospace Supplemental Type Certificate
(STC)
Continental Airlines (Continental) requested that we revise the
SNPRM to give credit for incorporating universal fault interrupters
(UFIs) using TDG Aerospace STC ST02076LA before the effective date of
the AD. Continental pointed out that paragraphs (q) and (r) of the
SNPRM provide credit for actions done before the effective date of the
AD using other service information.
While we do agree that installing TDG Aerospace UFIs before the
effective date of this AD is acceptable for terminating certain actions
required by this AD, we do not agree to revise the AD to provide
specific credit for those actions. Installing TDG Aerospace UFIs, as
specified in paragraph (s) of this AD, is acceptable both before and
after the effective date of this AD. Operators are always permitted to
accomplish the requirements of an AD at a time earlier than the
specified compliance time. We have not changed the AD in this regard.
Request To Revise Paragraph (v) of the SNPRM To Add Contact Information
Delta requested that we revise paragraph (v) of the SNPRM to add
contact information for TDG Aerospace. Delta pointed out that contact
information for the other service information identified in the SNPRM
is provided, but not for TDG Aerospace.
We agree partially. We do not agree to revise paragraph (v) of the
SNPRM, because that paragraph is not restated in this final rule.
However, we do agree to provide contact information for TDG Aerospace.
We have revised the ADDRESSES section of this AD to include this
contact information.
Additional Changes Made to This AD
We have revised paragraph (h) of this AD to clarify when a placard
is not necessary. We have determined that the second to last sentence
of paragraph (h) of this AD should also refer to AD 2001-08-24,
Amendment 39-12201 (66 FR 20733, April 25, 2001), for clarity.
Operators that choose to maintain the fuel usage restrictions of AD
2002-24-51, Amendment 39-12992 (68 FR 10, January 2, 2003), for all
airplanes in their fleet do not meet the condition to terminate AD
2002-24-51 and AD 2001-08-24 until the actions required by paragraphs
(g) and (i) of this AD are accomplished on all airplanes in their
fleet. Therefore, those operators are otherwise required to comply with
the requirements of AD 2001-08-24, regardless of whether that AD is
mentioned in paragraph (h) of this AD. Therefore, this change does not
increase the burden on operators.
We have revised paragraph (s) of this AD to specify that
installation of TDG Aerospace UFIs, as provided in that paragraph, must
be done in accordance with a method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA, because referring to the STC
now violates Office of the Federal Register (OFR) policies for approval
of optional materials ``incorporated by reference'' in rules. We have
added Note 5 to this AD to specify that additional guidance on
installing TDG Aerospace UFIs can be found in TDG Aerospace STC
ST02076LA.
We have also revised paragraph (s) of this AD to clarify the time
limit for doing the optional terminating action. Since paragraph (s) of
this AD terminates the actions required by paragraphs (g) through (k)
of this AD, if done, paragraph (s) of this AD must be accomplished
within the earliest time specified among those paragraphs to be
considered terminating action; that earliest time is 36 months.
Additionally, we have revised paragraph (s) of this AD to allow the
use of alternative placard wording that is approved by an appropriate
FAA Principal Operations Inspector, instead of requiring approval of
alternative placard wording as an alternative method of compliance in
accordance with paragraph (u) of this AD.
We have also revised paragraph (s) of this AD by adding a statement
to allow installation of a placard in accordance with paragraph (e) of
AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30, 2002).
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously--and minor editorial
changes. We have determined that these minor changes:
[Agr]re consistent with the intent that was proposed in
the SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 685 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 53320]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Labor cost Parts cost Cost per registered Cost on U.S.
product airplanes operators
----------------------------------------------------------------------------------------------------------------
Installation of the Between 94 and Between $22,994 Between $30,984 538 Between
automatic shutoff system 117 (depending and $30,197 and $40,142. $16,669,392
(Boeing Alert Service on airplane (depending on and
Bulletin 737-28A1206). configuration) airplane $21,596,396.
work-hours x configuration).
$85 per hour =
Between $7,990
and $9,945.
Placard installation, if 1 work-hour x $10............ $95............ 685 $65,075.
necessary. $85 per hour =
$85.
AFM revision................ 1 work-hour x None........... $85............ 538 $45,730.
$85 per hour =
$85.
Installation of secondary 68 work-hours x $3,274......... $9,054......... 685 $6,201,990.
pump control relays (Boeing $85 per hour =
Alert Service Bulletin 737- $5,780.
28A1248).
AWL revision to add 28-AWL- 1 work-hour x None........... $85............ 685 $58,225.
23. $85 per hour =
$85.
----------------------------------------------------------------------------------------------------------------
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
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
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
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):
2011-18-03 The Boeing Company: Amendment 39-16785; Docket No. FAA-
2007-28661; Directorate Identifier 2007-NM-013-AD.
Effective Date
(a) This AD is effective September 30, 2011.
Affected ADs
(b) Accomplishing certain requirements of this AD terminates
certain requirements of AD 2001-08-24, Amendment 39-12201 (66 FR
20733, April 25, 2001); AD 2002-24-51, Amendment 39-12992 (68 FR 10,
January 2, 2003); and AD 2008-24-51, Amendment 39-15781 (74 FR 8155,
February 24, 2009). Airworthiness Directive 2002-19-52, Amendment
39-12900 (67 FR 61253, September 30, 2002), is affected by this AD.
Applicability
(c) This AD applies to the airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) The Boeing Company Model 737-600, -700, -700C, -800, and -
900 series airplanes, identified in Boeing Alert Service Bulletin
737-28A1206, Revision 2, dated May 21, 2009.
(2) The Boeing Company Model 737-600, -700, -700C, -800, and -
900 series airplanes, identified in Boeing Alert Service Bulletin
737-28A1248, Revision 2, dated August 28, 2009.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance (AMOC)
according to paragraph (u) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 28, Fuel.
Unsafe Condition
(e) This AD was prompted by fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent center tank fuel
pump operation with continuous low pressure, which could lead to
friction sparks or overheating in the fuel pump inlet that could
create a potential ignition source inside the center fuel tank.
These conditions, in combination with flammable fuel vapors, could
result in a center fuel tank explosion and consequent loss of the
airplane.
[[Page 53321]]
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Installation of Automatic Shutoff System for the Center Tank Fuel Boost
Pumps
(g) For airplanes identified in paragraph 1.A.1. of Boeing Alert
Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009: Within
36 months after the effective date of this AD, install an automatic
shutoff system for the center tank fuel boost pumps, by
accomplishing all of the actions specified in Part 1 and Part 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-28A1206, Revision 2, dated May 21, 2009, except that Figure 1 of
this AD must be used in lieu of Sheet 2 of Figure 11 of Boeing Alert
Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009. If a
placard has been previously installed on the airplane in accordance
with paragraph (h) of this AD, the placard may be removed from the
flight deck of only that airplane after the automatic shutoff system
has been installed. Installing automatic shutoff systems on all
airplanes in an operator's fleet, in accordance with this paragraph,
terminates the placard installation required by paragraph (h) of
this AD for all airplanes in an operator's fleet.
Note 2: Boeing Alert Service Bulletin 737-28A1206, Revision 2,
dated May 21, 2009, refers to Boeing Component Service Bulletin
233A3202-28-03, dated January 12, 2006, as an additional source of
guidance for replacing the left and right center boost pump switches
of the P5-2 fuel control module assembly with new switches and
changing the wiring of the P5-2 fuel control module assembly.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR26AU11.015
BILLING CODE 4910-13-C
Placard Installation for Mixed Fleet Operation
(h) Prior to or concurrently with installing an automatic
shutoff system on any airplane in an operator's fleet, as required
by paragraph (g) of this AD, install a placard adjacent to the
pilot's primary flight display on all airplanes in the operator's
fleet that are not equipped with an automatic shutoff system for the
center tank fuel boost pumps. The placard must read as follows
(unless alternative placard wording is approved by an appropriate
FAA Principal Operations Inspector):
``AD 2002-24-51 fuel usage restrictions required.''
Installing an automatic shutoff system, in accordance with paragraph
(g) of this AD, terminates the placard installation required by this
paragraph for only that airplane. Installing automatic shutoff
systems on all airplanes in an operator's fleet, in accordance with
paragraph (g) of this AD, terminates the placard installation
required by this paragraph for all airplanes in an operator's
[[Page 53322]]
fleet. If operation according to the fuel usage restrictions of AD
2002-24-51, Amendment 39-12992 (68 FR 10, January 2, 2003), and AD
2001-08-24, Amendment 39-12201 (66 FR 20733, April 25, 2001), is
maintained until automatic shutoff systems are installed on all
airplanes in an operator's fleet, the placard installation specified
in this paragraph is not required. Installation of a placard in
accordance with paragraph (e) of AD 2002-19-52, Amendment 39-12900
(67 FR 61253, September 30, 2002), is acceptable for compliance with
the placard installation requirements of this paragraph; however,
terminating action specified in paragraph (g) of AD 2002-19-52 and
installation of an automatic shutoff system required by paragraph
(g) of this AD must be accomplished on the airplane before the
placard is removed from the airplane.
Airplane Flight Manual (AFM) Revision
(i) For airplanes on which Boeing Alert Service Bulletin 737-
28A1206, Revision 2, dated May 21, 2009, has been accomplished: At
the applicable time specified in paragraph (i)(1) or (i)(2) of this
AD, do the actions specified in paragraphs (i)(3) and (i)(4) of this
AD.
(1) For airplanes on which the terminating action specified in
paragraph (g) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253,
September 30, 2002), has been done: Concurrently with accomplishing
the actions required by paragraph (g) of this AD.
(2) For airplanes on which the terminating action specified in
paragraph (g) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253,
September 30, 2002), has not been done: Concurrently with
accomplishing the terminating action specified in paragraph (g) of
AD 2002-19-52.
(3) Revise Section 1 of the Limitations section of the Boeing
737-600/-700/-700C/-800/-900 AFM to include the following statement.
This may be done by inserting a copy of this AD into the AFM.
``Center Tank Fuel Pumps
Intentional dry running of a center tank fuel pump (low pressure
light illuminated) is prohibited.''
Note 3: For clarification purposes, the AFM limitations required
by AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30,
2002), continue to be required until the optional terminating
actions specified in paragraph (g) of AD 2002-19-52 have been done.
(4) Revise Section 3 of the Normal Procedures section of the
Boeing 737-600/ -700/-700C/-800/-900 AFM to include the following
statements. This may be done by inserting a copy of this AD into the
AFM. Alternative statements that meet the intent of the following
requirements may be used if approved by an appropriate FAA Principal
Operations Inspector.
``CENTER TANK FUEL PUMPS
Alternative Method of Compliance (AMOC) to AD 2001-08-24 and AD
2002-24-51 for Aircraft With the Automated Center Tank Fuel Pump
Shutoff
Center tank fuel pumps must not be ``ON'' unless personnel are
available in the flight deck to monitor low pressure lights.
For ground operation, center tank fuel pump switches must not be
positioned ``ON'' unless the center tank fuel quantity exceeds 1000
pounds (453 kilograms), except when defueling or transferring fuel.
Upon positioning the center tank fuel pump switches ``ON'' verify
momentary illumination of each center tank fuel pump low pressure
light.
For ground and flight operations, the corresponding center tank
fuel pump switch must be positioned ``OFF'' when a center tank fuel
pump low pressure light illuminates [1]. Both center tank fuel pump
switches must be positioned ``OFF'' when the first center tank fuel
pump low pressure light illuminates if the center tank is empty.
[1] When established in a level flight attitude, both center
tank pump switches should be positioned ``ON'' again if the center
tank contains usable fuel.
Defueling and Fuel Transfer
When transferring fuel or defueling center or main tanks, the
fuel pump low pressure lights must be monitored and the fuel pumps
positioned to ``OFF'' at the first indication of the fuel pump low
pressure [1].
Defueling the main tanks with passengers on board is prohibited
if the main tank fuel pumps are powered [2].
Defueling the center tank with passengers on board is prohibited
if the center tank fuel pumps are powered and the auto-shutoff
system is inhibited [2].
[1] Prior to transferring fuel or defueling, conduct a lamp test
of the respective fuel pump low pressure lights.
[2] Fuel may be transferred from tank to tank or the aircraft
may be defueled with passengers on board, provided fuel quantity in
the tank from which fuel is being taken is maintained at or above
2000 pounds (907 kilograms).''
Note 4: When statements identical to those in paragraphs (i)(3)
and (i)(4) of this AD have been included in the general revisions of
the Boeing 737-600/-700/-700C/-800/-900 AFM, the general revisions
may be inserted into that AFM, and the copy of this AD may be
removed from that AFM.
Installation of Secondary Pump Control Relays
(j) For airplanes identified in paragraph 1.A.1. of Boeing Alert
Service Bulletin 737-28A1248, Revision 2, dated August 28, 2009:
Within 60 months after the effective date of this AD, install one
secondary control relay for the electrical control circuit of each
of the two center tank fuel boost pumps, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
28A1248, Revision 2, dated August 28, 2009.
Airworthiness Limitations (AWL) Revision for AWL No. 28-AWL-23
(k) For airplanes identified in paragraph 1.A.1. of Boeing Alert
Service Bulletin 737-28A1248, Revision 2, dated August 28, 2009:
Concurrently with accomplishing the actions required by paragraph
(j) of this AD, or within 30 days after the effective date of this
AD, whichever occurs later, revise the maintenance program by
incorporating AWL No. 28-AWL-23 of Subsection E, AWLs--Fuel Systems,
of Section 9, Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), of the Boeing 737-600/700/800/900
MPD Document, D626A001-CMR, Revision March 2011. The initial
compliance time for the actions specified in AWL No. 28-AWL-23 is
within 1 year after accomplishing the installation required by
paragraph (j) of this AD, or within 1 year after the effective date
of this AD, whichever occurs later.
No Alternative Inspections or Inspection Intervals
(l) After accomplishing the applicable actions specified in
paragraph (k) of this AD, no alternative inspections or inspection
intervals may be used unless the inspections or inspection intervals
are approved as an AMOC in accordance with the procedures specified
in paragraph (u) of this AD.
Terminating Action for AD 2001-08-24, Amendment 39-12201 (66 FR 20733,
April 25, 2001)
(m) Accomplishing the actions required by paragraphs (g), (h),
and (i) of this AD, or accomplishing the actions specified in
paragraph (s) of this AD, terminates the requirements of paragraph
(a) of AD 2001-08-24, Amendment 39-12201 (66 FR 20733, April 25,
2001), for Model 737-600, -700, -700C, -800, and -900 series
airplanes that have the automatic shutoff system, or a TDG
Aerospace, Inc., universal fault interrupter (UFI), installed. After
accomplishing the actions required by paragraphs (g), (h), and (i)
of this AD, or accomplishing the actions specified in paragraph (s)
of this AD, the AFM limitation required by paragraph (a) of AD 2001-
08-24 may be removed from the AFM for those airplanes.
Terminating Action for AD 2002-24-51, Amendment 39-12992 (68 FR 10,
January 2, 2003)
(n) Accomplishing the actions required by paragraphs (g), (h),
and (i) of this AD, or accomplishing the actions specified in
paragraph (s) of this AD, terminates the requirements of paragraph
(b) of AD 2002-24-51, Amendment 39-12992 (68 FR 10, January 2,
2003), for Model 737-600, -700, -700C, -800, and -900 series
airplanes that have the automatic shutoff system, or a TDG
Aerospace, Inc., UFI, installed. After accomplishing the actions
required by paragraphs (g), (h), and (i) of this AD, or
accomplishing the actions specified in paragraph (s) of this AD, the
AFM limitations required by paragraph (b) of AD 2002-24-51 may be
removed from the AFM for those airplanes.
[[Page 53323]]
Terminating Action for AWL Revision
(o) Incorporating AWL No. 28-AWL-23 into the maintenance program
in accordance with paragraph (g)(3) of AD 2008-10-10 R1, Amendment
39-16164 (75 FR 1529, January 12, 2010), terminates the
corresponding action required by paragraph (k) of this AD.
Terminating Action for AD 2008-24-51, Amendment 39-15781 (74 FR 8155,
February 24, 2009)
(p) Accomplishing the actions required by paragraph (g) of this
AD terminates the requirements of paragraph (f) of AD 2008-24-51,
Amendment 39-15781 (74 FR 8155, February 24, 2009).
Credit for Actions Accomplished in Accordance With Previous Service
Information
(q) Actions accomplished before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 737-28A1248, dated
December 21, 2006; or Boeing Alert Service Bulletin 737-28A1248,
Revision 1, dated January 9, 2008; are considered acceptable for
compliance with the corresponding actions specified in paragraph (j)
of this AD.
(r) Actions accomplished before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 737-28A1206, dated
January 11, 2006; or Revision 1, dated January 30, 2008; are
considered acceptable for compliance with the corresponding actions
specified in paragraph (g) of this AD, provided one of the actions
specified in paragraph (r)(1) or (r)(2) of this AD have been done.
(1) The procedures specified in paragraph (f) of AD 2008-24-51,
Amendment 39-15781 (74 FR 8155, February 24, 2009), have been
accomplished.
(2) The actions specified in Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-28A1206, Revision
2, dated May 21, 2009, have been accomplished.
Optional Terminating Action
(s) Installing TDG Aerospace, Inc., UFI, in accordance with a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA, within 36 months after the effective date of this
AD, terminates the actions required by paragraphs (g) through (k) of
this AD; provided that, concurrently with installing a UFI on any
airplane in an operator's fleet, a placard is installed adjacent to
the pilot's primary flight display on all airplanes in the
operator's fleet not equipped with a UFI or an automatic shutoff
system. The placard must read as follows (unless alternative placard
wording is approved by an appropriate FAA Principal Operations
Inspector):
``AD 2002-24-51 fuel usage restrictions required.''
Installation of a placard in accordance with paragraph (h) of
this AD is acceptable for compliance with the placard installation
required by this paragraph. Installing a TDG Aerospace, Inc., UFI in
accordance with this paragraph on an airplane terminates the placard
installation required by this paragraph for only that airplane.
Installing TDG Aerospace, Inc., UFIs in accordance with this
paragraph, or automatic shutoff systems in accordance with paragraph
(g) of this AD, on all airplanes in an operator's fleet terminates
the placard installation required by this paragraph for all
airplanes in an operator's fleet. If operation according to the fuel
usage restrictions of AD 2002-24-51, Amendment 39-12992 (68 FR 10,
January 2, 2003), and AD 2001-08-24, Amendment 39-12201 (66 FR
20733, April 25, 2001), is maintained until UFIs or automatic
shutoff systems are installed on all airplanes in an operator's
fleet, the placard installation specified in this paragraph is not
required. Installation of a placard in accordance with paragraph (e)
of AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30,
2002), is acceptable for compliance with the placard installation
requirements of this paragraph; however, terminating action
specified in paragraph (g) of AD 2002-19-52 and installation of a
UFI specified by this paragraph must be accomplished on the airplane
before the placard is removed from the airplane.
Note 5: Guidance on installing a TDG Aerospace, Inc., UFI can be
found in TDG Aerospace, Inc., Supplemental Type Certificate (STC)
ST02076LA.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(t) Revising the maintenance program by incorporating AWL No.
28-AWL-23 of a revision specified in paragraphs (t)(1) through
(t)(12) of this AD of Subsection G, Airworthiness Limitations--Fuel
System AWLs, of Section 9, Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), of the Boeing 737-
600/700/800/900 MPD Document, D626A001-CMR; or Subsection E, AWLs--
Fuel Systems, of Section 9, Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), of the Boeing 737-
600/700/800/900 MPD Document, D626A001-CMR, Revision February 2011;
before the effective date of this AD is considered acceptable for
compliance with the corresponding actions specified in paragraph (k)
of this AD.
(1) Revision March 2008.
(2) Revision April 2008.
(3) Revision June 2008.
(4) Revision February 2009.
(5) Revision March 2009.
(6) Revision August 2009.
(7) Revision September 2009.
(8) Revision November 2009.
(9) Revision January 2010.
(10) Revision May 2010.
(11) Revision July 2010.
(12) Revision August 2010.
Alternative Methods of Compliance (AMOCs)
(u)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the ACO, send it to the attention of the person
identified in the Related Information section of this AD.
Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Related Information
(v) For more information about this AD, contact Tak Kobayashi,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Ave., SW., Renton,
Washington 98057-3356; phone: (425) 917-6499; fax (425) 917-6590; e-
mail: Takahisa.Kobayashi@faa.gov.
Material Incorporated by Reference
(w) You must use the service information contained in table 1 of
this AD, as applicable, to do the actions required by this AD,
unless the AD specifies otherwise.
Table 1--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 737- 2................................. May 21, 2009.
28A1206.
Boeing Alert Service Bulletin 737- 2................................. August 28, 2009.
28A1248.
AWL No. 28-AWL-23 of Subsection E, AWLs-- March 2011........................ March 2011.
Fuel Systems of Section 9,
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), of the Boeing 737-600/700/800/
900 Maintenance Planning Data Document,
D626A001-CMR.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
table 1 of this AD 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
[[Page 53324]]
206-766-5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, 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 August 12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-21617 Filed 8-25-11; 8:45 am]
BILLING CODE 4910-13-P
