[Federal Register Volume 76, Number 14 (Friday, January 21, 2011)]
[Proposed Rules]
[Pages 3856-3859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-1226]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0028; Directorate Identifier 2009-NM-228-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-100, -200,
-200C, -300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This proposed AD would result in all airplanes having new
relays with a ground fault interrupter (GFI) feature. This proposed AD
would require, depending on airplane configuration, doing certain
wiring changes, replacing the fuel pump power control relays for the
main, center and auxiliary tanks, as applicable, with new relays having
a GFI feature, performing certain bonding resistance measurements, and
modifying relay module assemblies. The proposed AD also would require
revising the maintenance program to incorporate Airworthiness
Limitations (AWLs) 28-AWL-23 (for Model 737-100, 737-200, and 737-200C
series airplanes), and 28-AWL-22 (for Model 737-300, 737-400, and 737-
500 series airplanes). This proposed AD results from fuel system
reviews conducted by the manufacturer. We are proposing this AD to
prevent damage to the fuel pumps caused by electrical arcing that could
introduce an ignition source in the fuel tank, which, in combination
with flammable fuel vapors, could result in a fuel tank explosion and
consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by March 7, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
[[Page 3857]]
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed 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 [email protected];
Internet https://www.myboeingfleet.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 or
425-227-1152.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 917-6482; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0028;
Directorate Identifier 2009-NM-228-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: Single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in a fuel tank explosion and consequent loss of the airplane.
As part of an SFAR88 analysis, Boeing determined that the power
control relays for the main tank fuel boost pumps, the center tank fuel
boost pumps, and for certain airplanes, the auxiliary tank fuel boost
pumps should be replaced with new relays having a ground fault
interrupter (GFI) feature. The relays are located in the P6 circuit
breaker panel in the flight compartment. The GFI relay feature is
intended to protect the fuel boost pumps from damage caused from
electrical arcing by removing electrical power from the pump if a
ground fault is detected. Electrical arcing, if not prevented could
introduce an ignition source in the fuel tank which, in combination
with flammable fuel vapors, could result in a fuel tank explosion and
consequent loss of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-28A1212,
Revision 1, dated August 27, 2010. Depending on airplane configuration
and on whether the actions in Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, were accomplished, Boeing Alert Service
Bulletin 737-28A1212, Revision 1, dated August 27, 2010, describes
procedures for the following actions, depending on airplane
configurations:
Doing wiring changes,
Replacing the fuel pump power control relays for the main,
center and auxiliary tanks with new relays having a GFI feature,
Doing certain bonding resistance measurements to verify
certain bonding requirements are met, and
Modifying the M181, M182, M183 relay module assemblies.
Boeing Alert Service Bulletin 737-28A1212, Revision 1, dated August
27, 2010, specifies a compliance time of 60 months for replacing the
power control relays.
For certain airplanes, Boeing Alert Service Bulletin 737-28A1212,
Revision 1, dated August 27, 2010, refers to BAE Systems Service
Bulletin 65-49808-24-01, Revision 1, dated July 19, 2010, as an
additional source of guidance for doing the modification of the relay
module assemblies and bond resistance measurements.
In addition, we have reviewed Section 9 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance
[[Page 3858]]
Requirements, D6-38278-CMR, Revision May 2009 (hereafter referred to as
``Document D6-38278-CMR''). Document D6-38278-CMR describes, among
other actions, new AWLs for the applicable fuel boost pumps that
incorporate ground fault interrupter relays for certain Model 737-100,
-200, and -200C airplanes (i.e., AWL 28-AWL-23), and for certain other
Model 737-300, -400, and -500 airplanes (i.e., AWL 28-AWL-22). The AWL
reference to boost pumps applies also to all pumps where the GFI has
been installed by incorporating Boeing Alert Service Bulletin 737-
28A1212.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously, except as described under
``Difference Between the Proposed AD and Service Information.''
Difference Between the Proposed AD and Service Information
AWL 28-AWL-23 of Section 9 of Boeing 737-100/200/200C/300/400/500
Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), Document D6-38278-CMR, Revision May 2009, is
applicable to Model 737-100, -200, and -200C airplanes, although it
specifies only the Model 737-100 and -200 airplanes.
Costs of Compliance
We estimate that this proposed AD would affect 750 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Table--Estimated Costs
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Number of U.S.-
Action Work hours Average labor Parts Cost per product registered Fleet cost
rate per hour airplanes
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Replacement of power control relays 4 to 9 \1\.......... $85 $14,500 $14,840 to $15,265 \1\ 750 $11,130,000 to
$11,448,750.\1\
Modification....................... 5................... 85 0 $425.................. 750 $318,750.
Maintenance program revision....... 1................... 85 0 $85................... 750 $63,750.
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\1\ Depending on airplane configuration.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
The Boeing Company: Docket No. FAA-2011-0028; Directorate Identifier
2009-NM-228-AD.
Comments Due Date
(a) We must receive comments by March 7, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category; as identified in Boeing Alert Service Bulletin 737-
28A1212, Revision 1, dated August 27, 2010.
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 according
to paragraph (m) 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) Air Transport Association (ATA) of America Code 28: Fuel.
[[Page 3859]]
Unsafe Condition
(e) This AD results from fuel system reviews conducted by the
manufacturer. The Federal Aviation Administration is issuing this AD
to prevent the damage to the fuel pumps caused by electrical arcing
that could introduce an ignition source in the fuel tank, which, in
combination with flammable fuel vapors, could result in a fuel tank
explosion and consequent loss of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Part 1: Wiring Changes, Relay Replacements, and Certain Bonding
Resistance Measurements for Certain Airplanes
(g) For airplanes on which Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, has not been incorporated as of the
effective date of this AD: Within 60 months after the effective date
of this AD, do the applicable action required by paragraph (g)(1) or
(g)(2) of this AD.
(1) Airplanes without the M181, M182, and M183 supplier relay
modules installed: Do the wiring changes; replace the fuel pump
power control relays for the main, center, and auxiliary tanks, as
applicable, with new relays having a ground fault interrupter (GFI)
feature; and do certain bonding resistance measurements to verify
that certain bonding requirements are met; in accordance with Part 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-28A1212, Revision 1, dated August 27, 2010.
(2) Airplanes with the M181, M182, and M183 supplier relay
modules installed: Modify the M181, M182, and M183 relay module
assemblies, and do certain bonding resistance measurements to verify
that certain bonding requirements are met, in accordance with Part 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-28A1212, Revision 1, dated August 27, 2010.
Note 2: Boeing Alert Service Bulletin 737-28A1212, Revision 1,
dated August 27, 2010, refers to BAE Systems Service Bulletin 65-
49808-24-01, Revision 1, dated July 19, 2010, as an additional
source of guidance for doing the modification and certain bonding
resistance measurements.
Part 2: Wiring Changes and Certain Bonding Measurements for Certain
Airplanes
(h) For airplanes on which Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, has been incorporated as of the
effective date of this AD, and on which the M181, M182, and M183
supplier relay modules have not been installed: Within 60 months
after the effective date of this AD, do the wiring changes and
certain bonding measurements to verify that certain bonding
requirements are met, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
28A1212, Revision 1, dated August 27, 2010.
Part 3: Certain Bonding Measurements for Certain Airplanes
(i) For airplanes on which Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, has been incorporated as of the
effective date of this AD, and that the M181, M182, and M183
supplier relay modules are installed: Within 60 months after the
effective date of this AD, do certain bonding measurements to verify
that certain bonding requirements are met, in accordance with Part 3
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-28A1212, Revision 1, dated August 27, 2010.
Note 3: Boeing Alert Service Bulletin 737-28A1212, Revision 1,
dated August 27, 2010, refers to BAE Systems Service Bulletin 65-
49808-24-01, Revision 1, dated July 19, 2010, as an additional
source of guidance for doing the modification and certain bonding
resistance measurements.
Maintenance Program Revisions
(j) Concurrently with accomplishing the actions required by
paragraph (g), (h), or (i) of this AD, as applicable, or within 30
days after the effective date of this AD, whichever occurs later,
revise the maintenance program by incorporating the applicable
airworthiness limitation (AWL) specified in paragraph (j)(1) or
(j)(2) of this AD.
(1) For Model 737-100, -200, and -200C series airplanes:
Airworthiness Limitation 28-AWL-23 of Section 9 of Boeing 737-100/
200/200C/300/400/500 AWL and Certification Maintenance Requirements
(CMRs), Document D6-38278-CMR, Revision May 2009. The initial
compliance time for the actions specified in AWL 28-AWL-23 is within
1 year after accomplishing the installation required by paragraph
(g), (h), or (i) of this AD, or within 1 year after the effective
date of this AD, whichever occurs later.
(2) For Model 737-300, -400, and -500 series airplanes: AWL 28-
AWL-22 of Section 9 of Boeing 737-100/200/200C/300/400/500
Airworthiness Limitation (AWL) and Certification Maintenance
Requirements (CMRs), Document D6-38278-CMR, Revision May 2009. The
initial compliance time for the actions specified in AWL 28-AWL-22
is within 1 year after accomplishing the installation required by
paragraph (g), (h), or (i) of this AD, or within 1 year after the
effective date of this AD, whichever occurs later.
No Alternative Inspections or Inspection Interval
(k) After accomplishment of the action required by paragraph
(g), (h), or (i) of this AD, as applicable, no alternative
inspections or inspection intervals may be used, unless the
inspections or intervals are approved as an alternative means of
compliance in accordance with the procedures specified in paragraph
(m) of this AD.
Credit for Actions Accomplished in Accordance With Earlier Revisions of
AWLs
(l) Revising the maintenance program to incorporate AWLs 28-AWL-
22 (for Model 737-300, -400, and -500 airplanes) and 28-AWL-23 (for
Model 737-100, -200, and -200C airplanes) in accordance with
paragraphs (g)(1) and (g)(2) of AD 2008-10-09 R1, amendment 39-
16148, terminates the requirements of paragraph (j) of this AD.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN:
Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch,
ANM-130S, FAA, Seattle Aircraft Certification Office (ACO), 1601
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6482; fax (425) 917-6590. Or, e-mail information to [email protected].
(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.
Issued in Renton, Washington, on January 12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-1226 Filed 1-20-11; 8:45 am]
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