Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes, 15808-15814 [2011-5301]
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15808
Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations
TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE FOR REQUIRED ACTIONS
Document
Airbus
Airbus
Airbus
Airbus
Revision
All Operators Telex A300–25A6215 .........................................................................
All Operators Telex A310–25A2203 .........................................................................
Mandatory Service Bulletin A300–25–6217 ..............................................................
Mandatory Service Bulletin A310–25–2205 ..............................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
Airbus Mandatory Service Bulletin A300–25–
6217, dated August 31, 2009; and Airbus
Mandatory Service Bulletin A310–25–2205,
02 .................................
02 .................................
Original ........................
01 .................................
Revision 01, dated November 19, 2010; under
5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of the service information
Date
March 2, 2009.
March 2, 2009.
August 31, 2009.
November 19, 2010.
contained in table 3 of this AD on June 12,
2009 (74 FR 25399, May 28, 2009).
TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Document
Revision
Airbus All Operators Telex A300–25A6215 .........................................................................
Airbus All Operators Telex A310–25A2203 .........................................................................
EADS SOGERMA Alert Service Bulletin A2510112–25–764 ..............................................
EADS SOGERMA Inspection Service Bulletin 2510112–25–807 ........................................
02 .................................
02 .................................
1 ...................................
Original ........................
(3) For Airbus service information
identified in this AD, contact Airbus SAS—
EAW (Airworthiness Office), 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(4) For EADS SOGERMA service
information identified in this AD, contact
EADS SOGERMA, Zone Industrielle de
l’Arsenal, BP 60109, 17303 Rochefort, Cedex
France; phone: 33 5 49 82 84 84; fax: 33 5
46 82 88 13; e-mail:
SCOD1@sogerma.eads.net; Internet: https://
www.sogerma.eads.net.
(5) 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.
(6) 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 NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_
locations.html.
Emcdonald on DSK2BSOYB1PROD with RULES
Issued in Renton, Washington, on March 7,
2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–5938 Filed 3–21–11; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1253; Directorate
Identifier 2009–NM–080–AD; Amendment
39–16629; AD 2011–06–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD),
which applies to all Model 737–600,
–700, –700C, –800, –900, and –900ER
series airplanes. That AD currently
requires repetitive detailed inspections
of the slat track downstop assemblies to
verify that proper hardware is installed,
one-time torquing of the nut and bolt,
and corrective actions if necessary. This
new AD also requires replacing the
hardware of the downstop assembly
with new hardware of the downstop
assembly, doing a detailed inspection or
a borescope inspection of the slat cans
on each wing and the lower rail of the
slat main tracks for debris, replacing the
bolts of the aft side guide with new
bolts, and removing any debris found in
the slat can. This AD also removes
airplanes from the applicability. This
AD results from reports of parts coming
off the main slat track downstop
assemblies. We are issuing this AD to
SUMMARY:
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Date
March 2, 2009.
March 2, 2009.
February 17, 2009.
February 20, 2009.
prevent loose or missing parts from the
main slat track downstop assemblies
from falling into the slat can and
causing a puncture, which could result
in a fuel leak and consequent fire.
DATES: This AD becomes effective April
26, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 26, 2011.
ADDRESSES: For 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. 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 (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
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1200 New Jersey Avenue, SE.,
Washington, DC 20590.
Request To Allow Optional Parts for
Installation
FOR FURTHER INFORMATION CONTACT:
Air Transport Association (ATA), on
behalf of its member airline American
Airlines (AAL), expressed concern
about the lack of optional manufacturer
part numbers, and/or optional
specifications concerning the parts
specified in the NPRM. AAL stated that
part interchangeability is allowed for
airplanes with the same design that are
not affected by the NPRM. AAL gave
four examples:
• The NPRM allows only bolt part
number (P/N) BACB30NR7DK12, but
bolt P/N BACB30NR7DK12 has an
optional part P/N 114A4102–19, that
can be used on airplanes unaffected by
the NPRM.
• The NPRM specifies retaining pin
P/N BACP18BC03A06P only, but per
Boeing part data, P/N MS24665–300 is
fully interchangeable with P/N
BACP18BC03A06P.
• The NPRM specifies to use lockwire
P/N MS20995NC32 only, but for
airplanes unaffected by the AD, the use
of cable assembly P/N BACC13AT4K6 is
allowed.
• Boeing Drawing 65–88700 allows
the use of P/N MS20995C32 and P/N
MS20995N32 in lieu of P/N
MS20995NC32.
AAL stated that the intent of the
NPRM is not to restrict parts to specific
manufacturer part numbers when
optional parts are readily available. AAL
stated that similar airplanes unaffected
by the AD with the same design allow
for greater part equivalent/substitution
options. AAL requested that the FAA, in
an effort to assist the operator for
compliance, include optional parts in
the NPRM, or provide a global AMOC
for acceptable substitutes per Boeing
Drawing 65–88700, which is an
acceptable specification
interchangeability, or part substitution
per Boeing Drawing D–590.
We partially agree with AAL’s request
that optional parts be allowed for
installation. The alternative lockwire
part proposed by AAL has already been
approved as an AMOC for those
operators who have made the request to
the FAA. Boeing has not requested
approval of a global AMOC for all
operators. We have revised paragraph (i)
of this AD to specify that installation of
stainless steel lockwire, P/N
MS20995C32, is acceptable for
compliance with this AD.
We disagree with AAL regarding use
of the alternative bolt and cotter pin.
The alternative bolt was never produced
and could be removed from the Boeing
drawing system in the future. The
alternative cotter pin proposed by AAL
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2007–18–52,
Amendment 39–15197 (72 FR 53928,
September 21, 2007). The existing AD
applies to all Model 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes. That NPRM was published in
the Federal Register on January 11,
2010 (75 FR 1297). That NPRM
proposed to require repetitive detailed
inspections of the slat track downstop
assemblies to verify that proper
hardware is installed, one-time torquing
of the nut and bolt, and corrective
actions if necessary. That NPRM also
proposed to require replacing the
hardware of the downstop assembly
with new hardware of the downstop
assembly, doing a detailed inspection or
a borescope inspection of the slat cans
on each wing and the lower rail of the
slat main tracks for debris, replacing the
bolts of the aft side guide with new
bolts, and removing any debris found in
the slat can. That NPRM proposed to
remove airplanes from the applicability
of the existing AD.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Emcdonald on DSK2BSOYB1PROD with RULES
Request To Use Revised Service
Information
Boeing requested that the NPRM refer
to Boeing Service Bulletin 737–
57A1302, Revision 1. Boeing stated that
Revision 1 of this service bulletin will
be forwarded to the FAA for approval.
We agree with Boeing’s request to
refer to Boeing Service Bulletin 737–
57A1302, Revision 1, dated October 18,
2010. Revision 1 of this service bulletin
has been published and made available
to operators. There are no new actions
in Boeing Service Bulletin 737–
57A1302, Revision 1, dated October 18,
2010. We have revised paragraph (i) of
this AD to add a reference to this service
bulletin.
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15809
may require the use of special tooling
for installation on in-service airplanes.
The cotter pin specified in Boeing Alert
Service Bulletin 737–57A1302, dated
December 15, 2008; and Boeing Service
Bulletin 737–57A1302, Revision 1,
dated October 18, 2010; requires the use
of a special tool designed to facilitate
the installation by the operators. Until
an alternative cotter pin and tooling are
validated for use in maintenance
facilities (as opposed to the
manufacturing environment), the
proposed AMOC by AAL cannot be
approved. If AAL obtains additional
data to support such a request, it may
apply for approval of an AMOC in
accordance with the provisions
specified in paragraph (j) of this AD.
We disagree with AAL’s request to
approve the use of substitutions
provided in Boeing Drawing 65–88700
or Drawing D–590. Boeing did not
provide us with information to ensure
that these parts adequately address the
unsafe condition. In addition, Boeing
has not requested approval of a global
AMOC for all operators. However,
operators may apply for approval of an
AMOC in accordance with the
provisions specified in paragraph (j) of
this AD.
Request for AMOC Clarification for the
Track Repair Requirements
ATA, on behalf of its member airline
AAL, expressed concern with requiring
an AMOC for repair of a hole larger than
0.5005 inch in the slat main track as
stated in the NPRM. AAL requested that
the FAA clarify the boundaries of the
AMOC track repair requirements and
the method to identify the AMOC
repaired tracks. AAL stated that the flap
tracks are fully removable from the slat
and are fully interchangeable with
airplanes unaffected by the AD. AAL
stated that the tracks do not have unique
identifiers (i.e., no serial numbers)
marked on the track. AAL stated that the
requirement may also be interpreted as,
for Boeing Alert Service Bulletin 737–
57A1302, dated December 15, 2008,
listed aircraft, repairs to the downstop
hole (when greater than 0.5005 inch) of
a slat main track performed at any time
during the life of the part would require
an AMOC.
We provide the following
clarifications.
For clarification of the AMOC track
repair requirements, the AD requires
that any time the fastener hole in an
affected slat can is oversized to greater
than 0.5005 inch, the track must be
replaced in accordance with Boeing
Alert Service Bulletin 737–57A1302,
dated December 15, 2008; Boeing
Service Bulletin 737–57A1302, Revision
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1, dated October 18, 2010; or repaired in
accordance with paragraph (j) of this
AD. AMOCs can be approved for
airplanes included in the AD
applicability. AMOCs are not applicable
to airplanes outside the AD even if ADrelated parts are rotated onto them. We
have not changed the AD in this regard.
For clarification, the method to
identify the AMOC-repaired tracks,
including the tracking of affected parts,
is a requirement under Parts 39, 121,
and 43 of the Federal Aviation
Regulations (14 CFR 39, 121, and 43).
Under these parts, each airline may
develop its own unique methodology to
accomplish this activity per the
procedures approved in its operation
specification. We have not changed the
AD in this regard.
Emcdonald on DSK2BSOYB1PROD with RULES
Request for Re-Evaluation of Out-ofSpec Hole Issue
ATA, on behalf of its member airline
AAL, recommended re-evaluating the
impact of an out-of-spec hole (hole
larger than 0.5005 inch in the slat main
track), and recommended the FAA
gather additional information from
operators concerning the out-of-spec
hole issue.
We disagree with AAL’s
recommendation. The proposal to
provide and gather operator data should
be proposed to the manufacturer. Once
additional data are evaluated by
technical specialists, operators may
request approval of an AMOC in
accordance with the provisions
specified in paragraph (j) of this AD
based on the new recommendation.
Request To Provide Reference in the
Component Maintenance Manual
(CMM)
ATA, on behalf of its member airline
AAL, expressed concern with the
bushing repair of the slat main track in
accordance with Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008. AAL stated that in an effort to
ensure compliance with the NPRM, this
repair may need to be referenced in the
appropriate CMM section to provide the
reference to the source of the repair
data.
From these statements, we infer that
AAL is requesting that the bushing
repair provided in Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008; and Boeing Service Bulletin
737–57A1302, Revision 1, dated
October 18, 2010; be referenced in the
appropriate CMM. We do not agree with
this request. CMMs are not regulated by
the FAA, and Boeing does not provide
us with information to ensure that these
documents remain unchanged and thus
adequately address the unsafe
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condition. We have not changed the AD
in this regard.
Request That the AD Clarify and
Highlight Only Specific Sections of the
Service Bulletin Affected by the AD
ATA, on behalf of its member airline
AAL, expressed concern regarding the
requirements in Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008, as proposed in the NPRM.
AAL stated that the NPRM may be
misinterpreted in that ‘‘all steps’’ of that
service bulletin must be complied with.
AAL requested that the AD be clarified
and highlighted to explain only those
specific sections of that service bulletin
that are affected by the NPRM.
AAL stated that panel open/close
procedures and access procedures (slat
extension/retraction) should not affect
the compliance with the NPRM. AAL
also stated that the actuator
disconnection/reconnection and slat
removal/installation also should not
affect compliance with the NPRM. AAL
stated that clarification may be made
with the following statement: ‘‘Only the
service bulletin procedures specified by
the AD are affected by the AD. Other
procedures described by the service
bulletin not specified by the AD are not
affected by FAA AD compliance
requirements.’’
We partially agree with AAL’s request
to clarify and highlight only specific
sections of Boeing Alert Service Bulletin
737–57A1302, dated December 15,
2008; and Boeing Service Bulletin 737–
57A1302, Revision 1, dated October 18,
2010; that are affected by the AD. For
clarification, the manufacturer revises
service bulletins, not the FAA. When
the words ‘‘refer to’’ are used in Boeing
Alert Service Bulletin 737–57A1302,
dated December 15, 2008; or Boeing
Service Bulletin 737–57A1302, Revision
1, dated October 18, 2010; and the
operator has an accepted alternative
procedure, the accepted alternative
procedure may be used. However, we
have changed paragraph (i) of this AD
to delete reference to the access and
close sections of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008; this AD now requires that the
actions be accomplished in accordance
with Part 2 of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008; or Boeing Service Bulletin
737–57A1302, Revision 1, dated
October 18, 2010.
Request To Provide a Global AMOC
ATA, on behalf of its member airline
AAL, stated that Boeing issued Service
Bulletin Information Notice (IN) 737–
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57A1302 IN 01, dated February 25,
2009, to Boeing Alert Service Bulletin
737–57A1302, dated December 15,
2008. AAL stated that Boeing Service
Bulletin IN 737–57A1302 IN 01
provides additional instructions to
install the guide bolts and reassemble
the track downstop hole. AAL stated
that Boeing Service Bulletin IN 737–
57A1302 IN 01 also provides additional
instructions for access and panel
reinstallation. AAL requested that
Boeing Service Bulletin IN 737–
57A1302 IN 01 be approved as a global
AMOC, or be incorporated as an option
into the AD requirements to allow the
operator to use the best practices to
accomplish the job.
We do not agree with this request. We
note that a global AMOC already has
been approved under FAA Letter 120S–
09–528, dated September 16, 2009, for
Boeing Service Bulletin IN 737–
57A1302 IN 01, dated February 25,
2009, and paragraph (i) of this AD has
been revised to include reference to
Boeing Service Bulletin 737–57A1302,
Revision 1, dated October 18, 2010,
which includes the information
provided in that information notice.
AAL may request a copy of this global
AMOC from Boeing.
Request for Validation of the Service
Bulletin Instructions To Be
Accomplished
ATA, on behalf of its member airline
AAL, expressed concern that a
validation program was not performed
on Boeing Alert Service Bulletin 737–
57A1302, dated December 15, 2008, to
ensure that data, instructions, and
processes specified in that service
bulletin are correct, clear, appropriate,
and understood by maintenance
personnel performing the work.
From this statement we infer that
AAL is requesting that validation of the
instructions in Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008, be accomplished. We partially
agree with AAL’s request. We have
confirmed that validation of Boeing
Alert Service Bulletin 737–57A1302,
dated December 15, 2008, was
completed in December 2009. Operators
may obtain further details of the
validation from Boeing. We have not
changed the AD in this regard.
Request To Revise Service Information
To Include Steps To Re-Install Slat Can
Assembly and Access Panels (If
Removed)
ATA, on behalf of its member airline
AAL, stated that there are no steps in
Boeing Alert Service Bulletin 737–
57A1302, dated December 15, 2008, to
install the slat can, if removed, in
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accordance with Part 2 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–57A1302,
dated December 15, 2008. AAL
requested that to ensure compliance
with the AD, a step, ‘‘If removed, install
slat, refer to AMM 27–81–21,’’ be
included in Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008, in the appropriate location.
AAL also stated that there is no
procedure referenced in Boeing Alert
Service Bulletin 737–57A1302, dated
December 15, 2008, to reinstall the
access panels removed from the lower
leading edge of the wing. AAL stated
that to ensure compliance with the AD,
a step, ‘‘reinstall the panels that were
removed from the lower leading edge of
the wing, refer to AMM 27–81–21,’’ be
included in Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008, in the appropriate location.
We disagree with AAL’s request. For
clarification, the manufacturer, not the
FAA, revises service bulletins. Part
3.B.3.b. of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–57A1302, dated December
15, 2008; and Boeing Service Bulletin
737–57A1302, Revision 1, dated
October 18, 2010; specify that the
airplane be returned ‘‘to a serviceable
condition,’’ and accomplishment of this
step would require reinstallation of any
components that were removed from the
airplane. When the words ‘‘refer to’’ are
used in Boeing Alert Service Bulletin
737–57A1302, dated December 15,
2008; and Boeing Service Bulletin 737–
57A1302, Revision 1, dated October 18,
2010; and the operator has an accepted
alternative procedure, the accepted
alternative procedure can be used to
accomplish reinstalling the slat can
assembly and access panels. Boeing
Service Bulletin 737–57A1302, Revision
1, dated October 18, 2010, does include
new phrasing similar to that requested
by AAL. We have not changed this AD
in this regard.
Request for an Optional Requirement to
the AD
ATA, on behalf of its member airline
AAL, expressed concern with the
measurement requirements of the slat
track hole diameter. AAL requested that
Boeing and/or the FAA provide an
optional requirement to this AD, or a
global AMOC, to allow use of a ‘‘no-go’’
type gauge or similar device and the
associated procedure to establish hole
size. AAL also requested providing an
additional (initial) procedure consistent
with using common maintenance
measurement tools to better allow the
operator to comply with these
requirements. AAL stated that Boeing
Alert Service Bulletin 737–57A1302,
dated December 15, 2008, states that if
the bolt has side-to-side play in the
hole, then measure the hole. AAL stated
that the allowable measurement is four
decimal places of accuracy (0.XXXX).
AAL stated that this dimension is in
Boeing Assembly Drawing 114A7511
specification for the purpose of
manufacturing the part in a machine
shop setting. AAL also stated that since
this task is intended to be accomplished
on wing, or slat removed (on bench) in
a dock maintenance setting, it is not
practical and may not be feasible to
require measurement within four
decimal places. AAL stated that the
methods to machine to four decimal
place accuracy are different from the
requirement to measure to four decimal
place accuracy. AAL stated that typical
tools used in a maintenance setting
would be a ball/T gauge, micrometer,
and a vernier caliper in certain
situations (hole not near minimum/
maximum limits). AAL also stated that
using these tools on the wing could
result in inaccuracy due to the difficulty
of the measuring location and the access
to the location.
We disagree with AAL’s requests to
provide an optional requirement to this
AD or a global AMOC to allow the use
of a ‘‘no-go’’ type gauge or similar device
and the associated procedure to
establish hole size. We also disagree
with AAL to add a procedure using
common maintenance measurement
tools.
Boeing Alert Service Bulletin 737–
57A1302, dated December 15, 2008;
Boeing Service Bulletin 737–57A1302,
Revision 1, dated October 18, 2010; nor
this AD; specify which tools are to be
used to measure the hole size. In the
15811
absence of specific instructions on how
to perform a maintenance task,
operators have the discretion of
developing their own procedures to
enable their maintenance personnel to
meet the requirements of this AD. In
addition, it is the intent of this AD that
the operators develop their own
procedures to perform a routine
maintenance task, such as drilling the
close ream hole. Operators are referred
to the manufacturer’s maintenance
procedures, which are published in
formats such as the structural repair
manual, the standard overhaul practices
manual, component maintenance
manuals, and other available resources.
For further instruction, these
maintenance procedures are best
obtained from these resources. We have
not changed the AD in this regard.
Explanation of Change to Applicability
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Explanation of Change to Costs of
Compliance
Since issuance of the NPRM, we have
increased the labor rate used in the
Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of
Compliance information, below, reflects
this increase in the specified hourly
labor rate.
Costs of Compliance
There are about 2,699 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
Emcdonald on DSK2BSOYB1PROD with RULES
ESTIMATED COSTS
Inspection and Torquing (required by AD
2007–18–52).
Inspection and Modification (new actions) ......
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Average
labor rate
per hour
Work
hours
Action
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8
$85
$0
18
85
5,388
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Number
of U.S.registered
airplanes
Cost per airplane
$680, per inspection
cycle.
$6,918 ........................
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853
853
Fleet cost
$580,040, per inspection cycle.
$5,901,054.
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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
PART 39—AIRWORTHINESS
DIRECTIVES
those inspections be repeated until the
repetitive interval of 3,000 flight cycles.
1. The authority citation for part 39
continues to read as follows:
Repetitive Detailed Inspections
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–15197 (72
FR 53928, September 21, 2007) and by
adding the following new airworthiness
directive (AD):
■
2011–06–05 The Boeing Company:
Amendment 39–16629. Docket No.
FAA–2009–1253; Directorate Identifier
2009–NM–080–AD.
Effective Date
(a) This AD becomes effective April 26,
2011.
Affected ADs
(b) This AD supersedes AD 2007–18–52,
Amendment 39–15197.
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Applicability
List of Subjects in 14 CFR Part 39
Restatement of AD 2007–18–52, With No
Changes
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Emcdonald on DSK2BSOYB1PROD with RULES
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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16:40 Mar 21, 2011
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(c) This AD applies to The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes,
certificated in any category, as identified in
Boeing Service Bulletin 737–57A1302,
Revision 1, dated October 18, 2010.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Unsafe Condition
(e) This AD results from reports of parts
coming off the main slat track downstop
assemblies. The Federal Aviation
Administration is issuing this AD to prevent
loose or missing parts from the main slat
track downstop assemblies from falling into
the slat can and causing a puncture, which
could result in a fuel leak and consequent
fire.
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.
Note 1: Paragraph (g) of this AD merely
restates the requirements of paragraph (f)(1)
of emergency AD 2007–18–51 (which was
superseded by AD 2007–18–52). As allowed
by the phrase, ‘‘unless the actions have
already been done,’’ if the applicable initial
inspections required by paragraph (f)(1) of
emergency AD 2007–18–51 have already
been done, this AD does not require that
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Fmt 4700
Sfmt 4700
(g) Within 10 days after September 26,
2007 (the effective date of AD 2007–18–52):
Do a detailed inspection or a borescope
inspection of each main slat track downstop
assembly to verify proper installation of the
slat track hardware (i.e., the bolt, washers,
downstops, stop location, and nut shown in
Figure 1 of Boeing Service Letter 737–SL–57–
084–B, dated July 10, 2007, and in this AD).
Proper installation of the sleeve need not be
confirmed, and the stop location part may be
installed on either the inboard or the
outboard side of the slat track. If any part is
missing or is installed improperly, before
further flight, install a new or serviceable
part using a method approved in accordance
with the procedures specified in paragraph (j)
of this AD; and do a detailed inspection of
the inside of the slat can for foreign object
debris (FOD) and damage. Before further
flight, remove any FOD found and repair any
damage found using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD. Verify proper
installation; install a new or serviceable part;
and inspect for damage and FOD, and remove
FOD and repair damage; in accordance with
a method by approved by the Manager,
Seattle Aircraft Certification Office, FAA; or
in accordance with Boeing Multi Operator
Message Number 1–523812011–1, issued
August 25, 2007, or 1–527463441–1, issued
August 28, 2007. Repeat the actions required
by paragraph (g) of this AD thereafter at
intervals not to exceed 3,000 flight cycles.
Note 2: Paragraph (h) of this AD merely
restates the requirements of paragraph (f)(2)
of emergency AD 2007–18–51. As allowed by
the phrase, ‘‘unless the actions have already
been done,’’ if the torque application required
by paragraph (f)(2) of AD emergency 2007–
18–51 has already been done, this AD does
not require that the torque application be
repeated.
One-Time Torquing
(h) Within 24 days after receipt of
emergency AD 2007–18–51: Apply a torque
between 50 to 80 inch-pounds to the nut. The
bolt head must be held with the torque
applied to the nut.
Note 3: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
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BILLING CODE 4910–13–C
New Requirements of This AD
Modification and Inspection
(i) Within 36 months after the effective
date of this AD: Replace the hardware of the
down stop assembly with new hardware, do
a detailed inspection or a borescope
inspection of the slat cans on each wing and
the lower rail of the slat main tracks for
VerDate Mar<15>2010
16:40 Mar 21, 2011
Jkt 223001
debris, and replace the bolts of the aft side
guide with new bolts, in accordance with
Part 2 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–57A1302,
dated December 15, 2008; or Boeing Service
Bulletin 737–57A1302, Revision 1, dated
October 18, 2010; except, where Boeing Alert
Service Bulletin 737–57A1302, dated
December 15, 2008, and Boeing Service
Bulletin 737–57A1302, Revision 1, dated
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
15813
October 18, 2010, specify to replace the slat
main track or to contact Boeing for further
repair instructions if the hole diameter is
greater than 0.5005 inch, before further flight,
replace the slat main track in accordance
with Boeing Alert Service Bulletin 737–
57A1302, dated December 15, 2008, Boeing
Service Bulletin 737–57A1302, Revision 1,
dated October 18, 2010, or repair using a
method approved in accordance with the
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Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations
15814
Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations
procedures specified in paragraph (j) of this
AD. If debris is found during any inspection
required by this AD, before further flight,
remove the debris in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–57A1302, dated
December 15, 2008; or Boeing Service
Bulletin 737–57A1302, Revision 1, dated
October 18, 2010. Doing the actions required
by paragraph (i) of this AD terminates the
actions required by paragraphs (g) and (h) of
this AD. Installation of stainless steel
lockwire having part number (P/N)
MS20995C32 is acceptable for compliance in
lieu of lockwire P/N MS20995NC32, as
specified in Boeing Alert Service Bulletin
737–57A1302, dated December 15, 2008, for
this AD.
Alternative Methods of Compliance
(j)(1) The Manager, Seattle Aircraft
Certification Office (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. Or,
e-mail information to 9-ANM-Seattle-ACOAMOC-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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 2007–18–52 are
approved as AMOCs for the corresponding
provisions of this AD.
Emcdonald on DSK2BSOYB1PROD with RULES
Related Information
(k) For more information about this AD,
contact Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone: 425–
917–6440; fax: 425–917–6590; e-mail:
nancy.marsh@faa.gov.
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 737–57A1302, dated December 15,
2008; or Boeing Service Bulletin 737–
57A1302, Revision 1, dated October 18, 2010;
to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
VerDate Mar<15>2010
16:40 Mar 21, 2011
Jkt 223001
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.
(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 NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
23, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–5301 Filed 3–21–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0090; Directorate
Identifier 2007–NM–312–AD; Amendment
39–16627; AD 2011–06–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747 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
measuring the electrical bond resistance
between the motor operated valve
(MOV) actuators and airplane structure
for the main, center, auxiliary, and
horizontal stabilizer fuel tanks, as
applicable, and corrective action if
necessary; revising the maintenance
program to incorporate airworthiness
limitation (AWL) No. 28–AWL–21 or
AWL No. 28–AWL–27, as applicable;
and replacing production-installed
laminate phenolic spacers with metallic
spacers between the fuel jettison MOV
and the airplane structure, as
applicable. This AD was prompted by
fuel system reviews conducted by the
manufacturer. We are issuing this AD to
prevent electrical current from flowing
through an MOV actuator into a fuel
tank, which could create a potential
ignition source inside the fuel tank. This
condition, in combination with
SUMMARY:
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: This AD is effective April 26,
2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 26, 2011.
ADDRESSES: For 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. 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:
Tung Tran, Aerospace Engineer,
Propulsion Branch, Seattle Aircraft
Certification Office, ANM–140S, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: 425–
917–6505; fax: 425–917–6590; e-mail:
tung.tran@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 November 19, 2010 (75 FR
70863). That SNPRM proposed to
require measuring the electrical bond
resistance between the motor operated
valve (MOV) actuators and airplane
structure for the main, center, auxiliary,
and horizontal stabilizer fuel tanks, as
applicable, and corrective action if
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]]>Agencies
[Federal Register Volume 76, Number 55 (Tuesday, March 22, 2011)]
[Rules and Regulations]
[Pages 15808-15814]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-5301]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1253; Directorate Identifier 2009-NM-080-AD;
Amendment 39-16629; AD 2011-06-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-600, -700,
-700C, -800, -900, and -900ER Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Model 737-600, -700, -700C, -800, -900, and
-900ER series airplanes. That AD currently requires repetitive detailed
inspections of the slat track downstop assemblies to verify that proper
hardware is installed, one-time torquing of the nut and bolt, and
corrective actions if necessary. This new AD also requires replacing
the hardware of the downstop assembly with new hardware of the downstop
assembly, doing a detailed inspection or a borescope inspection of the
slat cans on each wing and the lower rail of the slat main tracks for
debris, replacing the bolts of the aft side guide with new bolts, and
removing any debris found in the slat can. This AD also removes
airplanes from the applicability. This AD results from reports of parts
coming off the main slat track downstop assemblies. We are issuing this
AD to prevent loose or missing parts from the main slat track downstop
assemblies from falling into the slat can and causing a puncture, which
could result in a fuel leak and consequent fire.
DATES: This AD becomes effective April 26, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 26,
2011.
ADDRESSES: For 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. 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 (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140,
[[Page 15809]]
1200 New Jersey Avenue, SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6440; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2007-18-52, Amendment
39-15197 (72 FR 53928, September 21, 2007). The existing AD applies to
all Model 737-600, -700, -700C, -800, -900, and -900ER series
airplanes. That NPRM was published in the Federal Register on January
11, 2010 (75 FR 1297). That NPRM proposed to require repetitive
detailed inspections of the slat track downstop assemblies to verify
that proper hardware is installed, one-time torquing of the nut and
bolt, and corrective actions if necessary. That NPRM also proposed to
require replacing the hardware of the downstop assembly with new
hardware of the downstop assembly, doing a detailed inspection or a
borescope inspection of the slat cans on each wing and the lower rail
of the slat main tracks for debris, replacing the bolts of the aft side
guide with new bolts, and removing any debris found in the slat can.
That NPRM proposed to remove airplanes from the applicability of the
existing AD.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Use Revised Service Information
Boeing requested that the NPRM refer to Boeing Service Bulletin
737-57A1302, Revision 1. Boeing stated that Revision 1 of this service
bulletin will be forwarded to the FAA for approval.
We agree with Boeing's request to refer to Boeing Service Bulletin
737-57A1302, Revision 1, dated October 18, 2010. Revision 1 of this
service bulletin has been published and made available to operators.
There are no new actions in Boeing Service Bulletin 737-57A1302,
Revision 1, dated October 18, 2010. We have revised paragraph (i) of
this AD to add a reference to this service bulletin.
Request To Allow Optional Parts for Installation
Air Transport Association (ATA), on behalf of its member airline
American Airlines (AAL), expressed concern about the lack of optional
manufacturer part numbers, and/or optional specifications concerning
the parts specified in the NPRM. AAL stated that part
interchangeability is allowed for airplanes with the same design that
are not affected by the NPRM. AAL gave four examples:
The NPRM allows only bolt part number (P/N) BACB30NR7DK12,
but bolt P/N BACB30NR7DK12 has an optional part P/N 114A4102-19, that
can be used on airplanes unaffected by the NPRM.
The NPRM specifies retaining pin P/N BACP18BC03A06P only,
but per Boeing part data, P/N MS24665-300 is fully interchangeable with
P/N BACP18BC03A06P.
The NPRM specifies to use lockwire P/N MS20995NC32 only,
but for airplanes unaffected by the AD, the use of cable assembly P/N
BACC13AT4K6 is allowed.
Boeing Drawing 65-88700 allows the use of P/N MS20995C32
and P/N MS20995N32 in lieu of P/N MS20995NC32.
AAL stated that the intent of the NPRM is not to restrict parts to
specific manufacturer part numbers when optional parts are readily
available. AAL stated that similar airplanes unaffected by the AD with
the same design allow for greater part equivalent/substitution options.
AAL requested that the FAA, in an effort to assist the operator for
compliance, include optional parts in the NPRM, or provide a global
AMOC for acceptable substitutes per Boeing Drawing 65-88700, which is
an acceptable specification interchangeability, or part substitution
per Boeing Drawing D-590.
We partially agree with AAL's request that optional parts be
allowed for installation. The alternative lockwire part proposed by AAL
has already been approved as an AMOC for those operators who have made
the request to the FAA. Boeing has not requested approval of a global
AMOC for all operators. We have revised paragraph (i) of this AD to
specify that installation of stainless steel lockwire, P/N MS20995C32,
is acceptable for compliance with this AD.
We disagree with AAL regarding use of the alternative bolt and
cotter pin. The alternative bolt was never produced and could be
removed from the Boeing drawing system in the future. The alternative
cotter pin proposed by AAL may require the use of special tooling for
installation on in-service airplanes. The cotter pin specified in
Boeing Alert Service Bulletin 737-57A1302, dated December 15, 2008; and
Boeing Service Bulletin 737-57A1302, Revision 1, dated October 18,
2010; requires the use of a special tool designed to facilitate the
installation by the operators. Until an alternative cotter pin and
tooling are validated for use in maintenance facilities (as opposed to
the manufacturing environment), the proposed AMOC by AAL cannot be
approved. If AAL obtains additional data to support such a request, it
may apply for approval of an AMOC in accordance with the provisions
specified in paragraph (j) of this AD.
We disagree with AAL's request to approve the use of substitutions
provided in Boeing Drawing 65-88700 or Drawing D-590. Boeing did not
provide us with information to ensure that these parts adequately
address the unsafe condition. In addition, Boeing has not requested
approval of a global AMOC for all operators. However, operators may
apply for approval of an AMOC in accordance with the provisions
specified in paragraph (j) of this AD.
Request for AMOC Clarification for the Track Repair Requirements
ATA, on behalf of its member airline AAL, expressed concern with
requiring an AMOC for repair of a hole larger than 0.5005 inch in the
slat main track as stated in the NPRM. AAL requested that the FAA
clarify the boundaries of the AMOC track repair requirements and the
method to identify the AMOC repaired tracks. AAL stated that the flap
tracks are fully removable from the slat and are fully interchangeable
with airplanes unaffected by the AD. AAL stated that the tracks do not
have unique identifiers (i.e., no serial numbers) marked on the track.
AAL stated that the requirement may also be interpreted as, for Boeing
Alert Service Bulletin 737-57A1302, dated December 15, 2008, listed
aircraft, repairs to the downstop hole (when greater than 0.5005 inch)
of a slat main track performed at any time during the life of the part
would require an AMOC.
We provide the following clarifications.
For clarification of the AMOC track repair requirements, the AD
requires that any time the fastener hole in an affected slat can is
oversized to greater than 0.5005 inch, the track must be replaced in
accordance with Boeing Alert Service Bulletin 737-57A1302, dated
December 15, 2008; Boeing Service Bulletin 737-57A1302, Revision
[[Page 15810]]
1, dated October 18, 2010; or repaired in accordance with paragraph (j)
of this AD. AMOCs can be approved for airplanes included in the AD
applicability. AMOCs are not applicable to airplanes outside the AD
even if AD-related parts are rotated onto them. We have not changed the
AD in this regard.
For clarification, the method to identify the AMOC-repaired tracks,
including the tracking of affected parts, is a requirement under Parts
39, 121, and 43 of the Federal Aviation Regulations (14 CFR 39, 121,
and 43). Under these parts, each airline may develop its own unique
methodology to accomplish this activity per the procedures approved in
its operation specification. We have not changed the AD in this regard.
Request for Re-Evaluation of Out-of-Spec Hole Issue
ATA, on behalf of its member airline AAL, recommended re-evaluating
the impact of an out-of-spec hole (hole larger than 0.5005 inch in the
slat main track), and recommended the FAA gather additional information
from operators concerning the out-of-spec hole issue.
We disagree with AAL's recommendation. The proposal to provide and
gather operator data should be proposed to the manufacturer. Once
additional data are evaluated by technical specialists, operators may
request approval of an AMOC in accordance with the provisions specified
in paragraph (j) of this AD based on the new recommendation.
Request To Provide Reference in the Component Maintenance Manual (CMM)
ATA, on behalf of its member airline AAL, expressed concern with
the bushing repair of the slat main track in accordance with Boeing
Alert Service Bulletin 737-57A1302, dated December 15, 2008. AAL stated
that in an effort to ensure compliance with the NPRM, this repair may
need to be referenced in the appropriate CMM section to provide the
reference to the source of the repair data.
From these statements, we infer that AAL is requesting that the
bushing repair provided in Boeing Alert Service Bulletin 737-57A1302,
dated December 15, 2008; and Boeing Service Bulletin 737-57A1302,
Revision 1, dated October 18, 2010; be referenced in the appropriate
CMM. We do not agree with this request. CMMs are not regulated by the
FAA, and Boeing does not provide us with information to ensure that
these documents remain unchanged and thus adequately address the unsafe
condition. We have not changed the AD in this regard.
Request That the AD Clarify and Highlight Only Specific Sections of the
Service Bulletin Affected by the AD
ATA, on behalf of its member airline AAL, expressed concern
regarding the requirements in Boeing Alert Service Bulletin 737-
57A1302, dated December 15, 2008, as proposed in the NPRM. AAL stated
that the NPRM may be misinterpreted in that ``all steps'' of that
service bulletin must be complied with. AAL requested that the AD be
clarified and highlighted to explain only those specific sections of
that service bulletin that are affected by the NPRM.
AAL stated that panel open/close procedures and access procedures
(slat extension/retraction) should not affect the compliance with the
NPRM. AAL also stated that the actuator disconnection/reconnection and
slat removal/installation also should not affect compliance with the
NPRM. AAL stated that clarification may be made with the following
statement: ``Only the service bulletin procedures specified by the AD
are affected by the AD. Other procedures described by the service
bulletin not specified by the AD are not affected by FAA AD compliance
requirements.''
We partially agree with AAL's request to clarify and highlight only
specific sections of Boeing Alert Service Bulletin 737-57A1302, dated
December 15, 2008; and Boeing Service Bulletin 737-57A1302, Revision 1,
dated October 18, 2010; that are affected by the AD. For clarification,
the manufacturer revises service bulletins, not the FAA. When the words
``refer to'' are used in Boeing Alert Service Bulletin 737-57A1302,
dated December 15, 2008; or Boeing Service Bulletin 737-57A1302,
Revision 1, dated October 18, 2010; and the operator has an accepted
alternative procedure, the accepted alternative procedure may be used.
However, we have changed paragraph (i) of this AD to delete reference
to the access and close sections of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-57A1302, dated December 15, 2008;
this AD now requires that the actions be accomplished in accordance
with Part 2 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-57A1302, dated December 15, 2008; or Boeing Service
Bulletin 737-57A1302, Revision 1, dated October 18, 2010.
Request To Provide a Global AMOC
ATA, on behalf of its member airline AAL, stated that Boeing issued
Service Bulletin Information Notice (IN) 737-57A1302 IN 01, dated
February 25, 2009, to Boeing Alert Service Bulletin 737-57A1302, dated
December 15, 2008. AAL stated that Boeing Service Bulletin IN 737-
57A1302 IN 01 provides additional instructions to install the guide
bolts and reassemble the track downstop hole. AAL stated that Boeing
Service Bulletin IN 737-57A1302 IN 01 also provides additional
instructions for access and panel reinstallation. AAL requested that
Boeing Service Bulletin IN 737-57A1302 IN 01 be approved as a global
AMOC, or be incorporated as an option into the AD requirements to allow
the operator to use the best practices to accomplish the job.
We do not agree with this request. We note that a global AMOC
already has been approved under FAA Letter 120S-09-528, dated September
16, 2009, for Boeing Service Bulletin IN 737-57A1302 IN 01, dated
February 25, 2009, and paragraph (i) of this AD has been revised to
include reference to Boeing Service Bulletin 737-57A1302, Revision 1,
dated October 18, 2010, which includes the information provided in that
information notice. AAL may request a copy of this global AMOC from
Boeing.
Request for Validation of the Service Bulletin Instructions To Be
Accomplished
ATA, on behalf of its member airline AAL, expressed concern that a
validation program was not performed on Boeing Alert Service Bulletin
737-57A1302, dated December 15, 2008, to ensure that data,
instructions, and processes specified in that service bulletin are
correct, clear, appropriate, and understood by maintenance personnel
performing the work.
From this statement we infer that AAL is requesting that validation
of the instructions in Boeing Alert Service Bulletin 737-57A1302, dated
December 15, 2008, be accomplished. We partially agree with AAL's
request. We have confirmed that validation of Boeing Alert Service
Bulletin 737-57A1302, dated December 15, 2008, was completed in
December 2009. Operators may obtain further details of the validation
from Boeing. We have not changed the AD in this regard.
Request To Revise Service Information To Include Steps To Re-Install
Slat Can Assembly and Access Panels (If Removed)
ATA, on behalf of its member airline AAL, stated that there are no
steps in Boeing Alert Service Bulletin 737-57A1302, dated December 15,
2008, to install the slat can, if removed, in
[[Page 15811]]
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-57A1302, dated December 15, 2008. AAL
requested that to ensure compliance with the AD, a step, ``If removed,
install slat, refer to AMM 27-81-21,'' be included in Boeing Alert
Service Bulletin 737-57A1302, dated December 15, 2008, in the
appropriate location.
AAL also stated that there is no procedure referenced in Boeing
Alert Service Bulletin 737-57A1302, dated December 15, 2008, to
reinstall the access panels removed from the lower leading edge of the
wing. AAL stated that to ensure compliance with the AD, a step,
``reinstall the panels that were removed from the lower leading edge of
the wing, refer to AMM 27-81-21,'' be included in Boeing Alert Service
Bulletin 737-57A1302, dated December 15, 2008, in the appropriate
location.
We disagree with AAL's request. For clarification, the
manufacturer, not the FAA, revises service bulletins. Part 3.B.3.b. of
the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1302, dated December 15, 2008; and Boeing Service Bulletin 737-
57A1302, Revision 1, dated October 18, 2010; specify that the airplane
be returned ``to a serviceable condition,'' and accomplishment of this
step would require reinstallation of any components that were removed
from the airplane. When the words ``refer to'' are used in Boeing Alert
Service Bulletin 737-57A1302, dated December 15, 2008; and Boeing
Service Bulletin 737-57A1302, Revision 1, dated October 18, 2010; and
the operator has an accepted alternative procedure, the accepted
alternative procedure can be used to accomplish reinstalling the slat
can assembly and access panels. Boeing Service Bulletin 737-57A1302,
Revision 1, dated October 18, 2010, does include new phrasing similar
to that requested by AAL. We have not changed this AD in this regard.
Request for an Optional Requirement to the AD
ATA, on behalf of its member airline AAL, expressed concern with
the measurement requirements of the slat track hole diameter. AAL
requested that Boeing and/or the FAA provide an optional requirement to
this AD, or a global AMOC, to allow use of a ``no-go'' type gauge or
similar device and the associated procedure to establish hole size. AAL
also requested providing an additional (initial) procedure consistent
with using common maintenance measurement tools to better allow the
operator to comply with these requirements. AAL stated that Boeing
Alert Service Bulletin 737-57A1302, dated December 15, 2008, states
that if the bolt has side-to-side play in the hole, then measure the
hole. AAL stated that the allowable measurement is four decimal places
of accuracy (0.XXXX). AAL stated that this dimension is in Boeing
Assembly Drawing 114A7511 specification for the purpose of
manufacturing the part in a machine shop setting. AAL also stated that
since this task is intended to be accomplished on wing, or slat removed
(on bench) in a dock maintenance setting, it is not practical and may
not be feasible to require measurement within four decimal places. AAL
stated that the methods to machine to four decimal place accuracy are
different from the requirement to measure to four decimal place
accuracy. AAL stated that typical tools used in a maintenance setting
would be a ball/T gauge, micrometer, and a vernier caliper in certain
situations (hole not near minimum/maximum limits). AAL also stated that
using these tools on the wing could result in inaccuracy due to the
difficulty of the measuring location and the access to the location.
We disagree with AAL's requests to provide an optional requirement
to this AD or a global AMOC to allow the use of a ``no-go'' type gauge
or similar device and the associated procedure to establish hole size.
We also disagree with AAL to add a procedure using common maintenance
measurement tools.
Boeing Alert Service Bulletin 737-57A1302, dated December 15, 2008;
Boeing Service Bulletin 737-57A1302, Revision 1, dated October 18,
2010; nor this AD; specify which tools are to be used to measure the
hole size. In the absence of specific instructions on how to perform a
maintenance task, operators have the discretion of developing their own
procedures to enable their maintenance personnel to meet the
requirements of this AD. In addition, it is the intent of this AD that
the operators develop their own procedures to perform a routine
maintenance task, such as drilling the close ream hole. Operators are
referred to the manufacturer's maintenance procedures, which are
published in formats such as the structural repair manual, the standard
overhaul practices manual, component maintenance manuals, and other
available resources. For further instruction, these maintenance
procedures are best obtained from these resources. We have not changed
the AD in this regard.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Explanation of Change to Costs of Compliance
Since issuance of the NPRM, we have increased the labor rate used
in the Costs of Compliance from $80 per work-hour to $85 per work-hour.
The Costs of Compliance information, below, reflects this increase in
the specified hourly labor rate.
Costs of Compliance
There are about 2,699 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average Number of
Work labor U.S.-
Action hours rate per Parts Cost per airplane registered Fleet cost
hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspection and Torquing 8 $85 $0 $680, per 853 $580,040, per
(required by AD 2007-18-52). inspection cycle. inspection
cycle.
Inspection and Modification 18 85 5,388 $6,918........... 853 $5,901,054.
(new actions).
----------------------------------------------------------------------------------------------------------------
[[Page 15812]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-15197 (72 FR 53928, September 21, 2007) and by
adding the following new airworthiness directive (AD):
2011-06-05 The Boeing Company: Amendment 39-16629. Docket No. FAA-
2009-1253; Directorate Identifier 2009-NM-080-AD.
Effective Date
(a) This AD becomes effective April 26, 2011.
Affected ADs
(b) This AD supersedes AD 2007-18-52, Amendment 39-15197.
Applicability
(c) This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any
category, as identified in Boeing Service Bulletin 737-57A1302,
Revision 1, dated October 18, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD results from reports of parts coming off the main
slat track downstop assemblies. The Federal Aviation Administration
is issuing this AD to prevent loose or missing parts from the main
slat track downstop assemblies from falling into the slat can and
causing a puncture, which could result in a fuel leak and consequent
fire.
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.
Restatement of AD 2007-18-52, With No Changes
Note 1: Paragraph (g) of this AD merely restates the
requirements of paragraph (f)(1) of emergency AD 2007-18-51 (which
was superseded by AD 2007-18-52). As allowed by the phrase, ``unless
the actions have already been done,'' if the applicable initial
inspections required by paragraph (f)(1) of emergency AD 2007-18-51
have already been done, this AD does not require that those
inspections be repeated until the repetitive interval of 3,000
flight cycles.
Repetitive Detailed Inspections
(g) Within 10 days after September 26, 2007 (the effective date
of AD 2007-18-52): Do a detailed inspection or a borescope
inspection of each main slat track downstop assembly to verify
proper installation of the slat track hardware (i.e., the bolt,
washers, downstops, stop location, and nut shown in Figure 1 of
Boeing Service Letter 737-SL-57-084-B, dated July 10, 2007, and in
this AD). Proper installation of the sleeve need not be confirmed,
and the stop location part may be installed on either the inboard or
the outboard side of the slat track. If any part is missing or is
installed improperly, before further flight, install a new or
serviceable part using a method approved in accordance with the
procedures specified in paragraph (j) of this AD; and do a detailed
inspection of the inside of the slat can for foreign object debris
(FOD) and damage. Before further flight, remove any FOD found and
repair any damage found using a method approved in accordance with
the procedures specified in paragraph (j) of this AD. Verify proper
installation; install a new or serviceable part; and inspect for
damage and FOD, and remove FOD and repair damage; in accordance with
a method by approved by the Manager, Seattle Aircraft Certification
Office, FAA; or in accordance with Boeing Multi Operator Message
Number 1-523812011-1, issued August 25, 2007, or 1-527463441-1,
issued August 28, 2007. Repeat the actions required by paragraph (g)
of this AD thereafter at intervals not to exceed 3,000 flight
cycles.
Note 2: Paragraph (h) of this AD merely restates the
requirements of paragraph (f)(2) of emergency AD 2007-18-51. As
allowed by the phrase, ``unless the actions have already been
done,'' if the torque application required by paragraph (f)(2) of AD
emergency 2007-18-51 has already been done, this AD does not require
that the torque application be repeated.
One-Time Torquing
(h) Within 24 days after receipt of emergency AD 2007-18-51:
Apply a torque between 50 to 80 inch-pounds to the nut. The bolt
head must be held with the torque applied to the nut.
Note 3: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
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[GRAPHIC] [TIFF OMITTED] TR22MR11.075
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New Requirements of This AD
Modification and Inspection
(i) Within 36 months after the effective date of this AD:
Replace the hardware of the down stop assembly with new hardware, do
a detailed inspection or a borescope inspection of the slat cans on
each wing and the lower rail of the slat main tracks for debris, and
replace the bolts of the aft side guide with new bolts, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-57A1302, dated December 15, 2008; or
Boeing Service Bulletin 737-57A1302, Revision 1, dated October 18,
2010; except, where Boeing Alert Service Bulletin 737-57A1302, dated
December 15, 2008, and Boeing Service Bulletin 737-57A1302, Revision
1, dated October 18, 2010, specify to replace the slat main track or
to contact Boeing for further repair instructions if the hole
diameter is greater than 0.5005 inch, before further flight, replace
the slat main track in accordance with Boeing Alert Service Bulletin
737-57A1302, dated December 15, 2008, Boeing Service Bulletin 737-
57A1302, Revision 1, dated October 18, 2010, or repair using a
method approved in accordance with the
[[Page 15814]]
procedures specified in paragraph (j) of this AD. If debris is found
during any inspection required by this AD, before further flight,
remove the debris in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-57A1302, dated December 15,
2008; or Boeing Service Bulletin 737-57A1302, Revision 1, dated
October 18, 2010. Doing the actions required by paragraph (i) of
this AD terminates the actions required by paragraphs (g) and (h) of
this AD. Installation of stainless steel lockwire having part number
(P/N) MS20995C32 is acceptable for compliance in lieu of lockwire P/
N MS20995NC32, as specified in Boeing Alert Service Bulletin 737-
57A1302, dated December 15, 2008, for this AD.
Alternative Methods of Compliance
(j)(1) The Manager, Seattle Aircraft Certification Office (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. Or, e-mail information 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.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2007-18-52
are approved as AMOCs for the corresponding provisions of this AD.
Related Information
(k) For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone:
425-917-6440; fax: 425-917-6590; e-mail: nancy.marsh@faa.gov.
Material Incorporated by Reference
(l) You must use Boeing Alert Service Bulletin 737-57A1302,
dated December 15, 2008; or Boeing Service Bulletin 737-57A1302,
Revision 1, dated October 18, 2010; to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For 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.
(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 NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 23, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-5301 Filed 3-21-11; 8:45 am]
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