Airworthiness Directives; The Boeing Company Airplanes, 20229-20234 [2013-07209]
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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.
(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) All AMOCs approved for AD 2004–21–
08 (69 FR 62396, October 26, 2004) are
approved for this AD.
DEPARTMENT OF TRANSPORTATION
(l) Related Information
SUMMARY:
For more information about this AD,
contact Gary Park, Aerospace Engineer,
Wichita ACO, FAA, 1801 Airport Road,
Wichita, KS 67209; phone: (316) 946–4123;
fax: (316) 946–4107; email:
gary.park@faa.gov.
(m) Material Incorporated by Reference
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(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Cessna Aircraft Company Single Engine
Service Bulletin SEB04–1, Revision 1, dated
October 3, 2012.
(ii) Reserved.
(3) For Cessna Aircraft Company service
information identified in this AD, contact
Cessna Aircraft Company, Customer service,
P.O. Box 7706, Wichita, KS 67277; telephone:
(316) 517–5800; fax: (316) 517–7271; email:
customercare@cessna.textron.com; Internet:
https://www.cessnasupport.com.
(4) You may view this service information
at FAA,, Small Airplane Directorate, 901
Locust, Kansas City, MO 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) You may view this 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/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on March
14, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–06589 Filed 4–3–13; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0994; Directorate
Identifier 2012–NM–119–AD; Amendment
39–17402; AD 2013–06–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
all The Boeing Company Model 737–
600, –700, –700C, –800, –900, and
–900ER series airplanes. That AD
currently requires repetitive inspections
of the aft attach lugs of the elevator tab
control mechanisms, and replacement of
any discrepant elevator tab control
mechanism. This new AD requires
replacing the left and right elevator tab
control mechanisms with elevator tab
control mechanisms that have the
modified attach lugs, which would
terminate the existing requirements.
This AD was prompted by reports of
failure of the aft attach lugs on the
elevator tab control mechanisms, which
resulted in severe elevator vibration;
and reports of gaps in elevator tab
control mechanisms and analysis
indicating that additional elevator tab
control mechanisms might have
bearings that will come loose. We are
issuing this AD to prevent discrepancies
in the aft attach lugs of the elevator tab
control mechanism, which could result
in severe elevator and tab vibration.
Consequent structural failure of the
elevator or horizontal stabilizer could
result in loss of structural integrity and
aircraft control.
DATES: This AD is effective May 9, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 9, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of September 9, 2010 (75 FR
52242, August 25, 2010).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of April 29, 2010 (75 FR
21499, April 26, 2010).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
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20229
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; 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, WA. 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:
Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW.,
Renton, Washington 98057–3356;
phone: 425–917–6490; fax: 425–917–
6590; email: kelly.mcguckin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010). (That AD superseded
AD 2010–09–05, Amendment 39–16270
(75 FR 21499, April 26, 2010).) That AD
applies to the specified products. The
NPRM published in the Federal
Register on September 20, 2012 (77 FR
58330). That NPRM proposed to
continue to require repetitive
inspections of the aft attach lugs of the
elevator tab control mechanisms, and
replacement of any discrepant elevator
tab control mechanism. That NPRM also
proposed to require replacing the left
and right elevator tab control
mechanisms with elevator tab control
mechanisms that have modified attach
lugs, which would terminate the
existing requirements.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (77 FR 58330,
September 20, 2012) and the FAA’s
response to each comment. Aviation
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Partners Boeing stated that the
installation of winglets per
supplemental type certificate (STC)
ST00830SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
408e012e008616a7862578880060456c/
$FILE/ST00830SE.pdf) does not affect
the accomplishment of the
manufacturer’s service instructions.
United Airlines stated that it agrees with
the proposal.
Request To Remove Parts Installation
Prohibition
Boeing requested that we remove
paragraph (v) (‘‘New Parts Installation
Prohibition’’) from the NPRM (77 FR
58330, September 20, 2012). Boeing
stated that we should allow installation
of mechanisms having part number (P/
N) 251A2430–13, –14, –15, –16, –17, or
–18 within the compliance time
specified in the NPRM, and allow
continued operations under the
provisions of Boeing Alert Service
Bulletin 737–27A1297, Revision 1,
dated August 2, 2010; and AD 2010–17–
19, Amendment 39–16413 (75 FR
52242, August 25, 2010). Likewise,
Boeing requested that we allow
installation of mechanisms having P/N
251A2430–101, –102, –103, –104, –105,
or –106 within the compliance time
specified in the NPRM, and allow
continued operations under the
provisions of Boeing Alert Service
Bulletin 737–27A1299, dated July 1,
2011; and Boeing Alert Service Bulletin
737–27A1299, Revision 1, dated April
16, 2012; which are approved as
alternative methods of compliance
(AMOCs) to AD 2010–17–19. The
commenter stated that paragraph (v) of
the NPRM (which would prohibit
installing those parts as of the effective
date of the AD) would reduce operator
flexibility by prematurely forcing
incorporation of Boeing Service Bulletin
737–27–1300, dated April 16, 2012,
before the end of the 60-month
compliance period. The commenter
added that this also would prevent
incorporation of Boeing Alert Service
Bulletin 737–27A1299, Revision 1,
dated April 16, 2012, which Boeing
plans to recommend that operators
incorporate by April 2013 if they cannot
complete terminating action by that
date.
We partially agree with the request.
We agree to allow operators the
continued flexibility of using the noted
mechanisms in accordance with the
provisions of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010), or AMOCs specified
in Boeing Alert Service Bulletin 737–
27A1299, dated July 1, 2011, and Boeing
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Alert Service Bulletin 737–27A1299,
Revision 1, dated April 16, 2012, before
the replacement specified in paragraph
(u) of this AD. That replacement is
required for airplanes with line numbers
1 through 3909 inclusive. This will
provide flexibility and still maintain an
adequate level of safety. We disagree,
however, with deleting paragraph (v) of
this AD. The referenced mechanisms
have contributed to a known unsafe
condition and must not be used as a
spare after the incorporation of
paragraph (u) of this AD (which requires
replacement of these mechanisms). We
have changed paragraph (v) in this final
rule to limit the prohibition against
installing the referenced parts to a time
after the requirements of paragraph (u)
have been accomplished for airplanes
with line numbers 1 through 3909
inclusive. For airplanes with line
numbers 3910 and subsequent,
mechanisms with modified aft attach
lugs have been installed in production;
for these airplanes, the parts referenced
in paragraph (v) of this AD are
prohibited from installation as of the
effective date of this AD.
Request To Remove Compliance Time
Restriction
Request To Revise Identity of
Referenced Mechanisms
Boeing requested that we revise
paragraph (t) of the NPRM (77 FR 58330,
September 20, 2012) to limit the affected
mechanisms to mechanism P/Ns
‘‘251A2430–13, –14, –15, –16, –17, or
–18.’’ Boeing stated that this paragraph
should not apply to P/N 251A2430–23
and –24 mechanisms, because their
installation is terminating action for the
NPRM. The commenter added that
paragraph (t) of the NPRM also does not
apply to the –101, –102, –103, –104,
–105, or –106 mechanism, which have
a minimum proposed repetitive
inspection requirement of 800 flight
hours (not 300 flight hours).
We do not agree to incorporate the
requested changes in the final rule.
Paragraph (t) of the AD restates the
requirements of paragraph (t) of AD
2010–17–19, Amendment 39–16413 (75
FR 52242, August 25, 2010). The
replacement required by paragraph (u)
of this new AD terminates the
requirements of AD 2010–17–19,
including paragraph (t). The FAA
approved an AMOC to AD 2010–17–19
for Boeing Alert Service Bulletin 737–
27A1299, dated July 1, 2011; and Boeing
Alert Service Bulletin 737–27A1299,
Revision 1, dated April 16, 2012; for the
requirements of paragraph (t) for the
–101, –102, –103, –104, –105, and –106
mechanisms; as specified in paragraph
(x)(4) of this AD, that AMOC still
applies. We have not changed the final
rule regarding this issue.
Request To Revise Cost Estimate
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Boeing requested that we revise the
NPRM (77 FR 58330, September 20,
2012) to delete ‘‘and until the effective
date of this new AD’’ from the second
sentence of paragraph (t) of the
proposed AD. The commenter stated
that operators should be allowed to
install P/N 251A2430–13, –14, –15, –16,
–17, or –18 mechanisms within the
compliance period specified in the
NPRM and continue operations under
the provisions of Boeing Alert Service
Bulletin 737–27A1297, Revision 1,
dated August 2, 2010; and AD 2010–17–
19, Amendment 39–16413 (75 FR
52242, August 25, 2010).
We agree with the request and have
revised paragraph (t) accordingly in this
final rule. We are also clarifying the
requirements of paragraph (t) in this
final rule for line numbers 3910 and
subsequent, which are produced with
part numbers that terminate the
requirements of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010).
Delta requested that we revise the
estimated costs in the NPRM (77 FR
58330, September 20, 2012). Delta stated
that the cost information provided in
the NPRM does not reflect the most
current information available in Boeing
Service Bulletin 737–27–1300
Information Notice (IN) 01, dated April
19, 2012, which gives a total of 16 task
hours for each installed mechanism (32
hours per airplane) and 10 hours for
each modified component (20 hours per
airplane).
We agree, and have revised the cost
estimate accordingly in this final rule.
Request To Extend Compliance Time
for Related AMOC
Delta, American, and Boeing
requested that we revise the NPRM (77
FR 58330, September 20, 2012) to
extend the compliance time for the
AMOC associated with AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010). American and Delta
stated that we should allow that AMOC
to remain valid until the
accomplishment of the actions specified
in paragraph (u) of the NPRM to allow
the fullest benefit of the clip
installation. Boeing stated that
paragraph (v) of the NPRM conflicts
with paragraph (x)(3) of the NPRM
regarding the AMOC. Delta stated that
Boeing Alert Service Bulletin 737–
27A1299, Revision 1, dated April 16,
2012, notes that the AMOC was
intended as interim action and has an
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expiration date of June 30, 2016; Delta
concluded that AMOC approval would
therefore expire before the 60-month
compliance time specified in the NPRM
for the replacement in paragraph (u) of
the NPRM.
We agree with the requests, for the
reasons provided by the commenters.
We have changed paragraph (x)(4) in
this final rule to extend the expiration
of the referenced AMOCs.
Request To Clarify Reporting
Requirement
Delta requested that we revise the
NPRM (77 FR 58330, September 20,
2012) to clarify the required methods
and requirements for reporting
completion of the retrofit. Delta noted
that paragraph (u) of the NPRM specifies
to replace the elevator tab control
mechanism in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–27–1300, dated
April 16, 2012. Delta stated that the last
step of those instructions specifies
reporting retrofit completions to Boeing
using the service request application on
MyBoeingFleet.com. Delta noted that
the NPRM does not specifically identify
any requirement to report the tab
mechanism retrofit completions.
We agree to clarify the reporting
requirements: Although Boeing Service
Bulletin 737–27–1300, dated April 16,
2012, specifies submitting a report,
there is no new reporting requirement to
report completion of the replacement
required by paragraph (u) of this AD.
We have changed paragraph (u) in this
final rule to state that there is no
reporting requirement as part of the
replacement.
Request To Revise Applicability
American requested that we revise
paragraph (c) (‘‘Applicability’’) of the
NPRM (77 FR 58330, September 20,
2012) to match the applicability of
paragraph (u) (mechanism replacement)
of the NPRM (which applied to line
numbers 1 through 3909 inclusive).
American stated that Boeing Alert
Service Bulletin 737–27A1297, Revision
2, dated April 16, 2012; and Boeing
Alert Service Bulletin 737–27A1299,
Revision 1, dated April 16, 2012; have
been revised to limit the effectivity of
this issue.
We disagree with the request to revise
the applicability. The applicability of
this final rule includes the effectivity of
those service bulletins. But the
applicability of this AD extends to all
Model 737–600, -700, -700C, -800, -900,
and -900ER series airplanes to account
for spares that might also be installed on
those airplanes, as specified in
paragraph (v) (‘‘New Parts Installation
Prohibition’’) in this final rule. We have
not revised the final rule further
regarding this issue.
Explanation of Change Made to This
AD
We have added paragraph (x)(3) in
this final rule to specify that an AMOC
20231
that provides an acceptable level of
safety may be used for any repair
required by this AD if that repair is
approved by the Boeing Commercial
Airplanes Organizational Designation
Authorization (ODA) that has been
authorized by the Manager of the Seattle
Aircraft Certification Office to make
those findings.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
58330, September 20, 2012) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 58330,
September 20, 2012).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
We estimate that this AD affects 1,096
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Retained actions ................................
7 work-hours × $85 per hour = $595
per inspection cycle.
32 work-hours × $85 per hour =
$2,720.
52 work-hours × $85 per hour =
$4,420.
$0 .....................................................
$595 per inspection cycle.
$58,5791 $1,140 (installation kit) .....
$62,439 per airplane.
$5,858 (for the modification) $1,140
(installation kit) $2,145 (tooling2).
$13,563 per airplane.
Mechanism replacement (one option
for terminating action).
Mechanism modification and replacement (one option for terminating
action).
Cost per product
1 This is the estimated cost for both a left and right mechanism. Boeing is planning a seed/exchange program so operators are not forced to
purchase a new mechanism.
2 Per the Boeing service information, tooling is available from Boeing for $90 per day.
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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
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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
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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),
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(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2010–17–19, Amendment 39–16413 (75
FR 52242, August 25, 2010), and adding
the following new AD:
■
2013–06–05 The Boeing Company:
Amendment 39–17402; Docket No.
FAA–2012–0994; Directorate Identifier
2012–NM–119–AD.
(a) Effective Date
This AD is effective May 9, 2013.
(b) Affected ADs
This AD supersedes AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes,
certificated in any category.
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(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 27, Flight Controls.
(e) Unsafe Condition
This AD was prompted by reports of failure
of the aft attach lugs on the elevator tab
control mechanisms, which resulted in
severe elevator vibration. This AD also
results from reports of gaps in elevator tab
control mechanisms and analysis that
additional elevator tab control mechanisms
might have bearings that will come loose. We
are issuing this AD to prevent discrepancies
in the aft attach lugs of the elevator tab
control mechanism, which could result in
severe elevator and tab vibration. Consequent
structural failure of the elevator or horizontal
stabilizer could result in loss of structural
integrity and aircraft control.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Inspections for
Group 1 Airplanes
This paragraph restates the requirements of
paragraph (g) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). For Group 1 airplanes, as
identified in Boeing Alert Service Bulletin
737–27A1297, dated April 16, 2010: Except
as required by paragraph (h) of this AD,
within 12 days after April 29, 2010 (the
effective date of AD 2010–09–05,
Amendment 39–16270 (75 FR 21499, April
26, 2010)), do a detailed inspection for
discrepancies of the inboard and outboard aft
attach lugs of the left and right elevator tab
control mechanisms, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–27A1297, dated April
16, 2010. Repeat the inspection thereafter at
intervals not to exceed 300 flight hours.
Doing the replacement specified in paragraph
(l) of this AD before September 9, 2010 (the
effective date of AD 2010–17–19), terminates
the requirements of this paragraph. Doing the
inspection required by paragraph (n) of this
AD terminates the requirements of this
paragraph.
(h) Retained Extended Twin Operations
(ETOPS) Flight Provisions
This paragraph restates the requirements of
paragraph (h) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). For Group 1 airplanes as identified
in Boeing Alert Service Bulletin 737–
27A1297, dated April 16, 2010: Beginning 7
days after April 29, 2010 (the effective date
of AD 2010–09–05, Amendment 39–21499
(75 FR 21499, April 26, 2010)), no person
may operate an airplane on an ETOPS flight
unless the initial inspection required by
paragraph (g) of this AD has been
accomplished. Doing the inspection required
by paragraph (n) of this AD terminates the
requirements of this paragraph.
(i) Retained One-Time Inspection for Group
2, Configuration 1, Airplanes
This paragraph restates the requirements of
paragraph (i) of AD 2010–17–19, Amendment
39–16413 (75 FR 52242, August 25, 2010).
For Group 2, Configuration 1, airplanes as
identified in Boeing Alert Service Bulletin
737–27A1297, dated April 16, 2010: Within
30 days after April 29, 2010 (the effective
date of AD 2010–09–05, Amendment 39–
16270 (75 FR 21499, April 26, 2010)), do a
one-time detailed inspection for
discrepancies of the inboard and outboard aft
attach lugs of the left and right elevator tab
control mechanisms, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–27A1297, dated April
16, 2010. Doing the inspection required by
paragraph (n) of this AD terminates the
requirements of this paragraph.
(j) Corrective Actions for Paragraphs (g), (i),
and (k) of This AD
This paragraph restates the requirements of
paragraph (j) of AD 2010–17–19, Amendment
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39–16413 (75 FR 52242, August 25, 2010). If,
during any inspection required by paragraph
(g), (i), or (k) of this AD, any discrepancy is
found, before further flight, replace the
elevator tab control mechanism by doing the
actions specified in paragraphs (j)(1) and
(j)(2) of this AD.
(1) Do a detailed inspection for
discrepancies of the replacement elevator tab
control mechanism; and, if no discrepancy is
found, install the replacement elevator tab
control mechanism; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–27A1297, dated April
16, 2010. If any discrepancy is found, then
that elevator tab control mechanism cannot
be installed and the actions specified in this
paragraph must be done before further flight
on another replacement elevator tab control
mechanism.
(2) Re-inspect the installed elevator tab
control mechanism using the inspection
procedure specified in paragraph (i) of this
AD.
(k) Retained Repetitive Inspections for
Certain Group 2, Configuration 1, Airplanes
This paragraph restates the requirements of
paragraph (k) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). For Group 2, Configuration 1,
airplanes as identified in Boeing Alert
Service Bulletin 737–27A1297, dated April
16, 2010, on which the elevator tab control
mechanism is replaced with a mechanism
other than a new, Boeing-built mechanism:
Within 300 flight hours after doing the
replacement, do a detailed inspection for
discrepancies of the inboard and outboard aft
attach lugs of the left and right elevator tab
control mechanisms, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–27A1297, dated April
16, 2010. Repeat the inspection thereafter at
intervals not to exceed 300 flight hours.
Doing the replacement specified in paragraph
(l) of this AD before September 9, 2010 (the
effective date of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010)), is terminating action for this
paragraph. Doing the inspection required by
paragraph (n) of this AD terminates the
requirements of this paragraph.
(l) Terminating Action Credit for Paragraphs
(g), (i), and (k) of This AD
This paragraph restates the requirements of
paragraph (l) of AD 2010–17–19, Amendment
39–16413 (75 FR 52242, August 25, 2010).
Replacing an elevator tab control mechanism
with a new, Boeing-built mechanism before
September 9, 2010 (the effective date of AD
2010–17–19), as specified in paragraphs (l)(1)
and (l)(2) of this AD, terminates the
inspections required by paragraphs (g), (i),
and (k) of this AD. Replacement of the
elevator tab control mechanism on or after
September 9, 2010 (the effective date of AD
2010–17–19), does not terminate the
inspections required by paragraphs (g), (i),
and (k) of this AD.
Note 1 to paragraph (l) of this AD:
Additional guidance can be found in
paragraphs 3.B.7.b.(1)(a)(1) and
3.B.7.b.(1)(a)(2) of the Accomplishment
Instructions of Boeing Alert Service Bulletin
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737–27A1297, dated April 16, 2010, for
establishing whether the mechanism is
Boeing built.
(1) Do a detailed inspection for
discrepancies of the new, Boeing-built
replacement elevator tab control mechanism;
and, if no discrepancy is found, install the
replacement elevator tab control mechanism;
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–27A1297, dated April 16, 2010. If any
discrepancy is found, then that elevator tab
control mechanism cannot be installed and
the actions specified in this paragraph must
be done on another new, Boeing-built
replacement elevator tab control mechanism.
(2) Re-inspect the installed elevator tab
control mechanism using the inspection
procedure specified in paragraph (i) of this
AD.
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(m) Retained Reporting for Paragraphs (g),
(i), and (k) of This AD
This paragraph restates the requirements of
paragraph (m) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). For airplanes identified in Boeing
Alert Service Bulletin 737–27A1297, dated
April 16, 2010: At the applicable time
specified in paragraph (m)(1) or (m)(2) of this
AD, submit a report of any findings (positive
and negative) of the first inspection required
by paragraphs (g), (i), and (k) of this AD, and
any positive findings from the repetitive
inspections required by paragraphs (g) and
(k) of this AD, to Boeing Commercial
Airplanes Group, Attention: Manager, Airline
Support, email: rse.boecom@boeing.com. The
report must include the inspection results
including a description of any discrepancies
found, the airplane line number, and the total
number of flight cycles and flight hours
accumulated on the airplane.
(1) If the inspection was done on or after
April 29, 2010 (the effective date of AD
2010–09–05, Amendment 39–16270 (75 FR
21499, April 26, 2010)): Submit the report
within 10 days after the inspection.
(2) If the inspection was done before April
29, 2010 (the effective date of AD 2010–09–
05, Amendment 39–16270 (75 FR 21499,
April 26, 2010)): Submit the report within 10
days after April 29, 2010 (the effective date
of AD 2010–09–05).
(n) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (n) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). For airplanes having line numbers
1 through 3909 inclusive: At the applicable
time specified in paragraph (n)(1), (n)(2), or
(n)(3) of this AD, do a detailed inspection for
discrepancies of the inboard and outboard aft
attach lugs of the left and right elevator tab
control mechanisms, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–27A1297, Revision 1,
dated August 2, 2010. For Groups 1 and 2
airplanes identified in Boeing Alert Service
Bulletin 737–27A1297, Revision 1, dated
August 2, 2010, repeat the inspection
thereafter at intervals not to exceed 300 flight
hours, except as provided by paragraph (t)(2)
of this AD. For Group 3 airplanes identified
in Boeing Alert Service Bulletin 737–
VerDate Mar<15>2010
14:43 Apr 03, 2013
Jkt 229001
27A1297, Revision 1, dated August 2, 2010,
repeat the inspection thereafter at intervals
not to exceed 1,800 flight hours, except as
required by paragraphs (p) and (t)(2) of this
AD. Doing the inspection specified in this
paragraph terminates the requirements of
paragraphs (g), (h), (i), and (k) of this AD.
(1) For Group 1 airplanes identified in
Boeing Alert Service Bulletin 737–27A1297,
Revision 1, dated August 2, 2010: Within 300
flight hours after doing an inspection in
accordance with Boeing Alert Service
Bulletin 737–27A1297, dated April 16, 2010,
or within 30 days after September 9, 2010
(the effective date of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010)), whichever occurs later.
(2) For Group 2 airplanes identified in
Boeing Alert Service Bulletin 737–27A1297,
Revision 1, dated August 2, 2010: At the later
of the times specified in paragraphs (n)(2)(i)
and (n)(2)(ii) of this AD.
(i) Before the accumulation of 2,000 total
flight cycles or 4,000 total flight hours,
whichever occurs first.
(ii) Within 14 days after September 9, 2010
(the effective date of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010)).
(3) For Group 3 airplanes identified in
Boeing Alert Service Bulletin 737–27A1297,
Revision 1, dated August 2, 2010: Within 180
days or 1,800 flight hours after September 9,
2010 (the effective date of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010)), whichever occurs first.
(o) Retained Corrective Actions for
Paragraphs (n) and (p) of This AD
This paragraph restates the requirements of
paragraph (o) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). If, during any inspection required
by paragraph (n) or (p) of this AD, any
discrepancy is found, before further flight,
replace the elevator tab control mechanism
by doing the actions specified in paragraphs
(o)(1) and (o)(2) of this AD.
(1) Do a detailed inspection for
discrepancies of the replacement elevator tab
control mechanism; and, if no discrepancy is
found, install the replacement elevator tab
control mechanism; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–27A1297, Revision 1,
dated August 2, 2010. If any discrepancy is
found, then that elevator tab control
mechanism cannot be installed and the
actions specified in this paragraph must be
done before further flight on another
replacement elevator tab control mechanism.
(2) Re-inspect the installed elevator tab
control mechanism using the inspection
procedure specified in paragraph (n) of this
AD.
(p) Retained Reduced Repetitive Inspection
Interval for Group 3 Airplanes
This paragraph restates the requirements of
paragraph (p) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). For Group 3 airplanes as identified
in Boeing Alert Service Bulletin 737–
27A1297, Revision 1, dated August 2, 2010,
on which the elevator tab control mechanism
is replaced during the actions required by
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Fmt 4700
Sfmt 4700
20233
paragraph (o) of this AD: Within 300 flight
hours after doing the replacement, do a
detailed inspection for discrepancies of the
inboard and outboard aft attach lugs of the
replaced elevator tab control mechanism, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–27A1297, Revision 1, dated August 2,
2010. Repeat the inspection of the replaced
elevator tab control mechanism thereafter at
intervals not to exceed 300 flight hours,
except as provided by paragraph (t)(2) of this
AD.
(q) Retained Credit for Previous Action
This paragraph restates the provisions
specified in paragraph (q) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). For Group 1 airplanes as identified
in Boeing Alert Service Bulletin 737–
27A1297, Revision 1, dated August 2, 2010:
Inspections done in accordance with Boeing
Alert Service Bulletin 737–27A1297, dated
April 16, 2010, are acceptable for compliance
with only the initial inspection required by
paragraph (n) of this AD.
(r) Retained Reporting for Paragraphs (n)
and (p) of This AD
This paragraph restates the requirements of
paragraph (r) of AD 2010–17–19, Amendment
39–16413 (75 FR 52242, August 25, 2010).
For airplanes having line numbers 1 through
3909 inclusive: At the applicable time
specified in paragraph (r)(1) or (r)(2) of this
AD, submit a report of any findings (positive
and negative) of the first inspection required
by paragraphs (n) and (p) of this AD, except
for airplanes on which a report required by
paragraph (m) of this AD has been submitted,
only submit positive findings; and submit a
report of any positive findings from the
repetitive inspections required by paragraphs
(n) and (p) of this AD; to Boeing Commercial
Airplanes Group, Attention: Manager, Airline
Support, email: rse.boecom@boeing.com. The
report must include the inspection results
including a description of any discrepancies
found, the airplane line number, and the total
number of flight cycles and flight hours
accumulated on the airplane.
(1) If the inspection was done on or after
September 9, 2010 (the effective date of AD
2010–17–19, Amendment 39–16413 (75 FR
52242, August 25, 2010)): Submit the report
within 10 days after the inspection.
(2) If the inspection was done before
September 9, 2010 (the effective date of AD
2010–17–19, Amendment 39–16413 (75 FR
52242, August 25, 2010)): Submit the report
within 10 days after September 9, 2010 (the
effective date of AD 2010–17–19).
(s) Retained Provision Regarding Not
Returning Parts
This paragraph restates the provision
specified in paragraph (s) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010). Although Boeing Alert Service
Bulletin 737–27A1297, dated April 16, 2010;
and Boeing Alert Service Bulletin 737–
27A1297, Revision 1, dated August 2, 2010;
specify to return the affected elevator tab
control mechanism to the manufacturer, this
AD does not require the return of the part to
the manufacturer.
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Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations
(t) Retained Parts Installation Limitations
This paragraph restates the requirements of
paragraph (t) of AD 2010–17–19, Amendment
39–16413 (75 FR 52242, August 25, 2010),
with revised limitations. As of September 9,
2010 (the effective date of AD 2010–17–19),
and until the replacement required by
paragraph (u) of this AD for airplanes with
line numbers 1 through 3909 inclusive, or
until the effective date of this new AD for
airplanes with line numbers 3910 and
subsequent, as applicable: Comply with the
conditions specified in paragraphs (t)(1) and
(t)(2) of this AD.
(1) No person may install an elevator tab
control mechanism, part number (P/N)
251A2430-(), on any airplane, unless the
mechanism has been inspected before and
after installation using the inspection
procedures specified in paragraphs (o)(1) and
(o)(2) of this AD, and no discrepancies have
been found.
(2) An elevator tab control mechanism, P/
N 251A2430-(), may be installed, provided
that the inspection specified in paragraph (n)
of this AD is done within 300 flight hours
after doing the installation, and that the
inspection specified in paragraph (n) of this
AD is repeated thereafter at intervals not to
exceed 300 flight hours.
(u) New Replacement
For airplanes having line numbers 1
through 3909 inclusive: Within 60 months
after the effective date of this AD, replace the
left and right elevator tab control
mechanisms with elevator tab control
mechanisms that have new machined aft
attach lugs, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–27–1300, dated April
16, 2012. This replacement terminates the
requirements of paragraphs (g) through (t) of
this AD. Although Boeing Service Bulletin
737–27–1300, dated April 16, 2012, specifies
submitting a report, there is no requirement
to report completion of the replacement
required by paragraph (u) of this AD.
wreier-aviles on DSK5TPTVN1PROD with RULES
(v) New Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane identified
in paragraph (v)(1) or (v)(2) of this AD, an
elevator tab control mechanism having P/N
251A2430–13, –14, –15, –16, –17, –18, –101,
–102, –103, –104, –105, or –106.
(1) Airplanes on which the replacement in
paragraph (u) of this AD has been
accomplished.
(2) Airplanes with line numbers 3910 and
subsequent.
(w) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
VerDate Mar<15>2010
14:43 Apr 03, 2013
Jkt 229001
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(x) Alternative Methods of Compliance
(AMOCs)
(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.
Information may be emailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(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 for AD 2010–17–19,
Amendment 39–16413 (75 FR 52242, August
25, 2010), are approved as AMOCs for the
corresponding provisions of this AD. The
expiration of the AMOCS to AD 2010–17–19,
as specified in the service information
identified in paragraphs (x)(4)(i) and (x)(4)(ii)
of this AD, is extended to remain valid until
accomplishment of the requirements of
paragraph (u) of this AD.
(i) Boeing Alert Service Bulletin 737–
27A1299, dated July 1, 2011 (which is not
incorporated by reference in this AD).
(ii) Boeing Alert Service Bulletin 737–
27A1299, Revision 1, dated April 16, 2012
(which is not incorporated by reference in
this AD).
(y) Related Information
For more information about this AD,
contact Kelly McGuckin, Aerospace
Engineer, Systems and Equipment Branch,
ANM–130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue
SW., Renton, Washington 98057–3356;
phone: 425–917–6490; fax: 425–917–6590;
email: kelly.mcguckin@faa.gov.
(z) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on May 9, 2013.
(i) Boeing Service Bulletin 737–27–1300,
dated April 16, 2012.
(ii) Reserved.
(4) The following service information was
approved for IBR on September 9, 2010 (75
FR 52242, August 25, 2010).
(i) Boeing Alert Service Bulletin 737–
27A1297, Revision 1, dated August 2, 2010.
(ii) Reserved.
(5) The following service information was
approved for IBR on April 29, 2010 (75 FR
21499, April 26, 2010).
(i) Boeing Alert Service Bulletin 737–
27A1297, dated April 16, 2010.
(ii) Reserved.
(6) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(7) You may view this service information
at FAA, You may review copies of the
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
(8) You may view this 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
20, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–07209 Filed 4–3–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1014; Directorate
Identifier 2010–SW–058–AD; Amendment
39–17404; AD 2013–06–07]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model
SA–365N1, AS–365N2, and AS 365 N3
SUMMARY:
E:\FR\FM\04APR1.SGM
04APR1
]]>Agencies
[Federal Register Volume 78, Number 65 (Thursday, April 4, 2013)]
[Rules and Regulations]
[Pages 20229-20234]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-07209]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0994; Directorate Identifier 2012-NM-119-AD;
Amendment 39-17402; AD 2013-06-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and
-900ER series airplanes. That AD currently requires repetitive
inspections of the aft attach lugs of the elevator tab control
mechanisms, and replacement of any discrepant elevator tab control
mechanism. This new AD requires replacing the left and right elevator
tab control mechanisms with elevator tab control mechanisms that have
the modified attach lugs, which would terminate the existing
requirements. This AD was prompted by reports of failure of the aft
attach lugs on the elevator tab control mechanisms, which resulted in
severe elevator vibration; and reports of gaps in elevator tab control
mechanisms and analysis indicating that additional elevator tab control
mechanisms might have bearings that will come loose. We are issuing
this AD to prevent discrepancies in the aft attach lugs of the elevator
tab control mechanism, which could result in severe elevator and tab
vibration. Consequent structural failure of the elevator or horizontal
stabilizer could result in loss of structural integrity and aircraft
control.
DATES: This AD is effective May 9, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 9, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
September 9, 2010 (75 FR 52242, August 25, 2010).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of April
29, 2010 (75 FR 21499, April 26, 2010).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; 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, WA. 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: Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6490; fax: 425-917-6590; email:
kelly.mcguckin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010-17-19, Amendment 39-16413 (75 FR 52242,
August 25, 2010). (That AD superseded AD 2010-09-05, Amendment 39-16270
(75 FR 21499, April 26, 2010).) That AD applies to the specified
products. The NPRM published in the Federal Register on September 20,
2012 (77 FR 58330). That NPRM proposed to continue to require
repetitive inspections of the aft attach lugs of the elevator tab
control mechanisms, and replacement of any discrepant elevator tab
control mechanism. That NPRM also proposed to require replacing the
left and right elevator tab control mechanisms with elevator tab
control mechanisms that have modified attach lugs, which would
terminate the existing requirements.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 58330, September 20, 2012) and the FAA's response to each
comment. Aviation
[[Page 20230]]
Partners Boeing stated that the installation of winglets per
supplemental type certificate (STC) ST00830SE (https://rgl.faa.gov/
Regulatory--and--Guidance--Library/rgstc.nsf/0/
408e012e008616a7862578880060456c/$FILE/ST00830SE.pdf) does not affect
the accomplishment of the manufacturer's service instructions. United
Airlines stated that it agrees with the proposal.
Request To Remove Parts Installation Prohibition
Boeing requested that we remove paragraph (v) (``New Parts
Installation Prohibition'') from the NPRM (77 FR 58330, September 20,
2012). Boeing stated that we should allow installation of mechanisms
having part number (P/N) 251A2430-13, -14, -15, -16, -17, or -18 within
the compliance time specified in the NPRM, and allow continued
operations under the provisions of Boeing Alert Service Bulletin 737-
27A1297, Revision 1, dated August 2, 2010; and AD 2010-17-19, Amendment
39-16413 (75 FR 52242, August 25, 2010). Likewise, Boeing requested
that we allow installation of mechanisms having P/N 251A2430-101, -102,
-103, -104, -105, or -106 within the compliance time specified in the
NPRM, and allow continued operations under the provisions of Boeing
Alert Service Bulletin 737-27A1299, dated July 1, 2011; and Boeing
Alert Service Bulletin 737-27A1299, Revision 1, dated April 16, 2012;
which are approved as alternative methods of compliance (AMOCs) to AD
2010-17-19. The commenter stated that paragraph (v) of the NPRM (which
would prohibit installing those parts as of the effective date of the
AD) would reduce operator flexibility by prematurely forcing
incorporation of Boeing Service Bulletin 737-27-1300, dated April 16,
2012, before the end of the 60-month compliance period. The commenter
added that this also would prevent incorporation of Boeing Alert
Service Bulletin 737-27A1299, Revision 1, dated April 16, 2012, which
Boeing plans to recommend that operators incorporate by April 2013 if
they cannot complete terminating action by that date.
We partially agree with the request. We agree to allow operators
the continued flexibility of using the noted mechanisms in accordance
with the provisions of AD 2010-17-19, Amendment 39-16413 (75 FR 52242,
August 25, 2010), or AMOCs specified in Boeing Alert Service Bulletin
737-27A1299, dated July 1, 2011, and Boeing Alert Service Bulletin 737-
27A1299, Revision 1, dated April 16, 2012, before the replacement
specified in paragraph (u) of this AD. That replacement is required for
airplanes with line numbers 1 through 3909 inclusive. This will provide
flexibility and still maintain an adequate level of safety. We
disagree, however, with deleting paragraph (v) of this AD. The
referenced mechanisms have contributed to a known unsafe condition and
must not be used as a spare after the incorporation of paragraph (u) of
this AD (which requires replacement of these mechanisms). We have
changed paragraph (v) in this final rule to limit the prohibition
against installing the referenced parts to a time after the
requirements of paragraph (u) have been accomplished for airplanes with
line numbers 1 through 3909 inclusive. For airplanes with line numbers
3910 and subsequent, mechanisms with modified aft attach lugs have been
installed in production; for these airplanes, the parts referenced in
paragraph (v) of this AD are prohibited from installation as of the
effective date of this AD.
Request To Revise Identity of Referenced Mechanisms
Boeing requested that we revise paragraph (t) of the NPRM (77 FR
58330, September 20, 2012) to limit the affected mechanisms to
mechanism P/Ns ``251A2430-13, -14, -15, -16, -17, or -18.'' Boeing
stated that this paragraph should not apply to P/N 251A2430-23 and -24
mechanisms, because their installation is terminating action for the
NPRM. The commenter added that paragraph (t) of the NPRM also does not
apply to the -101, -102, -103, -104, -105, or -106 mechanism, which
have a minimum proposed repetitive inspection requirement of 800 flight
hours (not 300 flight hours).
We do not agree to incorporate the requested changes in the final
rule. Paragraph (t) of the AD restates the requirements of paragraph
(t) of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25,
2010). The replacement required by paragraph (u) of this new AD
terminates the requirements of AD 2010-17-19, including paragraph (t).
The FAA approved an AMOC to AD 2010-17-19 for Boeing Alert Service
Bulletin 737-27A1299, dated July 1, 2011; and Boeing Alert Service
Bulletin 737-27A1299, Revision 1, dated April 16, 2012; for the
requirements of paragraph (t) for the -101, -102, -103, -104, -105, and
-106 mechanisms; as specified in paragraph (x)(4) of this AD, that AMOC
still applies. We have not changed the final rule regarding this issue.
Request To Remove Compliance Time Restriction
Boeing requested that we revise the NPRM (77 FR 58330, September
20, 2012) to delete ``and until the effective date of this new AD''
from the second sentence of paragraph (t) of the proposed AD. The
commenter stated that operators should be allowed to install P/N
251A2430-13, -14, -15, -16, -17, or -18 mechanisms within the
compliance period specified in the NPRM and continue operations under
the provisions of Boeing Alert Service Bulletin 737-27A1297, Revision
1, dated August 2, 2010; and AD 2010-17-19, Amendment 39-16413 (75 FR
52242, August 25, 2010).
We agree with the request and have revised paragraph (t)
accordingly in this final rule. We are also clarifying the requirements
of paragraph (t) in this final rule for line numbers 3910 and
subsequent, which are produced with part numbers that terminate the
requirements of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August
25, 2010).
Request To Revise Cost Estimate
Delta requested that we revise the estimated costs in the NPRM (77
FR 58330, September 20, 2012). Delta stated that the cost information
provided in the NPRM does not reflect the most current information
available in Boeing Service Bulletin 737-27-1300 Information Notice
(IN) 01, dated April 19, 2012, which gives a total of 16 task hours for
each installed mechanism (32 hours per airplane) and 10 hours for each
modified component (20 hours per airplane).
We agree, and have revised the cost estimate accordingly in this
final rule.
Request To Extend Compliance Time for Related AMOC
Delta, American, and Boeing requested that we revise the NPRM (77
FR 58330, September 20, 2012) to extend the compliance time for the
AMOC associated with AD 2010-17-19, Amendment 39-16413 (75 FR 52242,
August 25, 2010). American and Delta stated that we should allow that
AMOC to remain valid until the accomplishment of the actions specified
in paragraph (u) of the NPRM to allow the fullest benefit of the clip
installation. Boeing stated that paragraph (v) of the NPRM conflicts
with paragraph (x)(3) of the NPRM regarding the AMOC. Delta stated that
Boeing Alert Service Bulletin 737-27A1299, Revision 1, dated April 16,
2012, notes that the AMOC was intended as interim action and has an
[[Page 20231]]
expiration date of June 30, 2016; Delta concluded that AMOC approval
would therefore expire before the 60-month compliance time specified in
the NPRM for the replacement in paragraph (u) of the NPRM.
We agree with the requests, for the reasons provided by the
commenters. We have changed paragraph (x)(4) in this final rule to
extend the expiration of the referenced AMOCs.
Request To Clarify Reporting Requirement
Delta requested that we revise the NPRM (77 FR 58330, September 20,
2012) to clarify the required methods and requirements for reporting
completion of the retrofit. Delta noted that paragraph (u) of the NPRM
specifies to replace the elevator tab control mechanism in accordance
with the Accomplishment Instructions of Boeing Service Bulletin 737-27-
1300, dated April 16, 2012. Delta stated that the last step of those
instructions specifies reporting retrofit completions to Boeing using
the service request application on MyBoeingFleet.com. Delta noted that
the NPRM does not specifically identify any requirement to report the
tab mechanism retrofit completions.
We agree to clarify the reporting requirements: Although Boeing
Service Bulletin 737-27-1300, dated April 16, 2012, specifies
submitting a report, there is no new reporting requirement to report
completion of the replacement required by paragraph (u) of this AD. We
have changed paragraph (u) in this final rule to state that there is no
reporting requirement as part of the replacement.
Request To Revise Applicability
American requested that we revise paragraph (c) (``Applicability'')
of the NPRM (77 FR 58330, September 20, 2012) to match the
applicability of paragraph (u) (mechanism replacement) of the NPRM
(which applied to line numbers 1 through 3909 inclusive). American
stated that Boeing Alert Service Bulletin 737-27A1297, Revision 2,
dated April 16, 2012; and Boeing Alert Service Bulletin 737-27A1299,
Revision 1, dated April 16, 2012; have been revised to limit the
effectivity of this issue.
We disagree with the request to revise the applicability. The
applicability of this final rule includes the effectivity of those
service bulletins. But the applicability of this AD extends to all
Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes to
account for spares that might also be installed on those airplanes, as
specified in paragraph (v) (``New Parts Installation Prohibition'') in
this final rule. We have not revised the final rule further regarding
this issue.
Explanation of Change Made to This AD
We have added paragraph (x)(3) in this final rule to specify that
an AMOC that provides an acceptable level of safety may be used for any
repair required by this AD if that repair is approved by the Boeing
Commercial Airplanes Organizational Designation Authorization (ODA)
that has been authorized by the Manager of the Seattle Aircraft
Certification Office to make those findings.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 58330, September 20, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 58330, September 20, 2012).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 1,096 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Retained actions.............. 7 work-hours x $85 $0................... $595 per inspection cycle.
per hour = $595 per
inspection cycle.
Mechanism replacement (one 32 work-hours x $85 $58,579\1\ $1,140 $62,439 per airplane.
option for terminating per hour = $2,720. (installation kit).
action).
Mechanism modification and 52 work-hours x $85 $5,858 (for the $13,563 per airplane.
replacement (one option for per hour = $4,420. modification) $1,140
terminating action). (installation kit)
$2,145 (tooling\2\).
----------------------------------------------------------------------------------------------------------------
\1\ This is the estimated cost for both a left and right mechanism. Boeing is planning a seed/exchange program
so operators are not forced to purchase a new mechanism.
\2\ Per the Boeing service information, tooling is available from Boeing for $90 per day.
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),
[[Page 20232]]
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010), and
adding the following new AD:
2013-06-05 The Boeing Company: Amendment 39-17402; Docket No. FAA-
2012-0994; Directorate Identifier 2012-NM-119-AD.
(a) Effective Date
This AD is effective May 9, 2013.
(b) Affected ADs
This AD supersedes AD 2010-17-19, Amendment 39-16413 (75 FR
52242, August 25, 2010).
(c) Applicability
This AD applies to all The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 27, Flight Controls.
(e) Unsafe Condition
This AD was prompted by reports of failure of the aft attach
lugs on the elevator tab control mechanisms, which resulted in
severe elevator vibration. This AD also results from reports of gaps
in elevator tab control mechanisms and analysis that additional
elevator tab control mechanisms might have bearings that will come
loose. We are issuing this AD to prevent discrepancies in the aft
attach lugs of the elevator tab control mechanism, which could
result in severe elevator and tab vibration. Consequent structural
failure of the elevator or horizontal stabilizer could result in
loss of structural integrity and aircraft control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections for Group 1 Airplanes
This paragraph restates the requirements of paragraph (g) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
Group 1 airplanes, as identified in Boeing Alert Service Bulletin
737-27A1297, dated April 16, 2010: Except as required by paragraph
(h) of this AD, within 12 days after April 29, 2010 (the effective
date of AD 2010-09-05, Amendment 39-16270 (75 FR 21499, April 26,
2010)), do a detailed inspection for discrepancies of the inboard
and outboard aft attach lugs of the left and right elevator tab
control mechanisms, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-27A1297, dated
April 16, 2010. Repeat the inspection thereafter at intervals not to
exceed 300 flight hours. Doing the replacement specified in
paragraph (l) of this AD before September 9, 2010 (the effective
date of AD 2010-17-19), terminates the requirements of this
paragraph. Doing the inspection required by paragraph (n) of this AD
terminates the requirements of this paragraph.
(h) Retained Extended Twin Operations (ETOPS) Flight Provisions
This paragraph restates the requirements of paragraph (h) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
Group 1 airplanes as identified in Boeing Alert Service Bulletin
737-27A1297, dated April 16, 2010: Beginning 7 days after April 29,
2010 (the effective date of AD 2010-09-05, Amendment 39-21499 (75 FR
21499, April 26, 2010)), no person may operate an airplane on an
ETOPS flight unless the initial inspection required by paragraph (g)
of this AD has been accomplished. Doing the inspection required by
paragraph (n) of this AD terminates the requirements of this
paragraph.
(i) Retained One-Time Inspection for Group 2, Configuration 1,
Airplanes
This paragraph restates the requirements of paragraph (i) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
Group 2, Configuration 1, airplanes as identified in Boeing Alert
Service Bulletin 737-27A1297, dated April 16, 2010: Within 30 days
after April 29, 2010 (the effective date of AD 2010-09-05, Amendment
39-16270 (75 FR 21499, April 26, 2010)), do a one-time detailed
inspection for discrepancies of the inboard and outboard aft attach
lugs of the left and right elevator tab control mechanisms, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-27A1297, dated April 16, 2010. Doing the
inspection required by paragraph (n) of this AD terminates the
requirements of this paragraph.
(j) Corrective Actions for Paragraphs (g), (i), and (k) of This AD
This paragraph restates the requirements of paragraph (j) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). If,
during any inspection required by paragraph (g), (i), or (k) of this
AD, any discrepancy is found, before further flight, replace the
elevator tab control mechanism by doing the actions specified in
paragraphs (j)(1) and (j)(2) of this AD.
(1) Do a detailed inspection for discrepancies of the
replacement elevator tab control mechanism; and, if no discrepancy
is found, install the replacement elevator tab control mechanism; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-27A1297, dated April 16, 2010. If any
discrepancy is found, then that elevator tab control mechanism
cannot be installed and the actions specified in this paragraph must
be done before further flight on another replacement elevator tab
control mechanism.
(2) Re-inspect the installed elevator tab control mechanism
using the inspection procedure specified in paragraph (i) of this
AD.
(k) Retained Repetitive Inspections for Certain Group 2, Configuration
1, Airplanes
This paragraph restates the requirements of paragraph (k) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
Group 2, Configuration 1, airplanes as identified in Boeing Alert
Service Bulletin 737-27A1297, dated April 16, 2010, on which the
elevator tab control mechanism is replaced with a mechanism other
than a new, Boeing-built mechanism: Within 300 flight hours after
doing the replacement, do a detailed inspection for discrepancies of
the inboard and outboard aft attach lugs of the left and right
elevator tab control mechanisms, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
27A1297, dated April 16, 2010. Repeat the inspection thereafter at
intervals not to exceed 300 flight hours. Doing the replacement
specified in paragraph (l) of this AD before September 9, 2010 (the
effective date of AD 2010-17-19, Amendment 39-16413 (75 FR 52242,
August 25, 2010)), is terminating action for this paragraph. Doing
the inspection required by paragraph (n) of this AD terminates the
requirements of this paragraph.
(l) Terminating Action Credit for Paragraphs (g), (i), and (k) of This
AD
This paragraph restates the requirements of paragraph (l) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010).
Replacing an elevator tab control mechanism with a new, Boeing-built
mechanism before September 9, 2010 (the effective date of AD 2010-
17-19), as specified in paragraphs (l)(1) and (l)(2) of this AD,
terminates the inspections required by paragraphs (g), (i), and (k)
of this AD. Replacement of the elevator tab control mechanism on or
after September 9, 2010 (the effective date of AD 2010-17-19), does
not terminate the inspections required by paragraphs (g), (i), and
(k) of this AD.
Note 1 to paragraph (l) of this AD: Additional guidance can be
found in paragraphs 3.B.7.b.(1)(a)(1) and 3.B.7.b.(1)(a)(2) of the
Accomplishment Instructions of Boeing Alert Service Bulletin
[[Page 20233]]
737-27A1297, dated April 16, 2010, for establishing whether the
mechanism is Boeing built.
(1) Do a detailed inspection for discrepancies of the new,
Boeing-built replacement elevator tab control mechanism; and, if no
discrepancy is found, install the replacement elevator tab control
mechanism; in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010. If
any discrepancy is found, then that elevator tab control mechanism
cannot be installed and the actions specified in this paragraph must
be done on another new, Boeing-built replacement elevator tab
control mechanism.
(2) Re-inspect the installed elevator tab control mechanism
using the inspection procedure specified in paragraph (i) of this
AD.
(m) Retained Reporting for Paragraphs (g), (i), and (k) of This AD
This paragraph restates the requirements of paragraph (m) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
airplanes identified in Boeing Alert Service Bulletin 737-27A1297,
dated April 16, 2010: At the applicable time specified in paragraph
(m)(1) or (m)(2) of this AD, submit a report of any findings
(positive and negative) of the first inspection required by
paragraphs (g), (i), and (k) of this AD, and any positive findings
from the repetitive inspections required by paragraphs (g) and (k)
of this AD, to Boeing Commercial Airplanes Group, Attention:
Manager, Airline Support, email: rse.boecom@boeing.com. The report
must include the inspection results including a description of any
discrepancies found, the airplane line number, and the total number
of flight cycles and flight hours accumulated on the airplane.
(1) If the inspection was done on or after April 29, 2010 (the
effective date of AD 2010-09-05, Amendment 39-16270 (75 FR 21499,
April 26, 2010)): Submit the report within 10 days after the
inspection.
(2) If the inspection was done before April 29, 2010 (the
effective date of AD 2010-09-05, Amendment 39-16270 (75 FR 21499,
April 26, 2010)): Submit the report within 10 days after April 29,
2010 (the effective date of AD 2010-09-05).
(n) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (n) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
airplanes having line numbers 1 through 3909 inclusive: At the
applicable time specified in paragraph (n)(1), (n)(2), or (n)(3) of
this AD, do a detailed inspection for discrepancies of the inboard
and outboard aft attach lugs of the left and right elevator tab
control mechanisms, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-27A1297, Revision
1, dated August 2, 2010. For Groups 1 and 2 airplanes identified in
Boeing Alert Service Bulletin 737-27A1297, Revision 1, dated August
2, 2010, repeat the inspection thereafter at intervals not to exceed
300 flight hours, except as provided by paragraph (t)(2) of this AD.
For Group 3 airplanes identified in Boeing Alert Service Bulletin
737-27A1297, Revision 1, dated August 2, 2010, repeat the inspection
thereafter at intervals not to exceed 1,800 flight hours, except as
required by paragraphs (p) and (t)(2) of this AD. Doing the
inspection specified in this paragraph terminates the requirements
of paragraphs (g), (h), (i), and (k) of this AD.
(1) For Group 1 airplanes identified in Boeing Alert Service
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: Within 300
flight hours after doing an inspection in accordance with Boeing
Alert Service Bulletin 737-27A1297, dated April 16, 2010, or within
30 days after September 9, 2010 (the effective date of AD 2010-17-
19, Amendment 39-16413 (75 FR 52242, August 25, 2010)), whichever
occurs later.
(2) For Group 2 airplanes identified in Boeing Alert Service
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: At the later
of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of
this AD.
(i) Before the accumulation of 2,000 total flight cycles or
4,000 total flight hours, whichever occurs first.
(ii) Within 14 days after September 9, 2010 (the effective date
of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25,
2010)).
(3) For Group 3 airplanes identified in Boeing Alert Service
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: Within 180
days or 1,800 flight hours after September 9, 2010 (the effective
date of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25,
2010)), whichever occurs first.
(o) Retained Corrective Actions for Paragraphs (n) and (p) of This AD
This paragraph restates the requirements of paragraph (o) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). If,
during any inspection required by paragraph (n) or (p) of this AD,
any discrepancy is found, before further flight, replace the
elevator tab control mechanism by doing the actions specified in
paragraphs (o)(1) and (o)(2) of this AD.
(1) Do a detailed inspection for discrepancies of the
replacement elevator tab control mechanism; and, if no discrepancy
is found, install the replacement elevator tab control mechanism; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-27A1297, Revision 1, dated August 2, 2010. If
any discrepancy is found, then that elevator tab control mechanism
cannot be installed and the actions specified in this paragraph must
be done before further flight on another replacement elevator tab
control mechanism.
(2) Re-inspect the installed elevator tab control mechanism
using the inspection procedure specified in paragraph (n) of this
AD.
(p) Retained Reduced Repetitive Inspection Interval for Group 3
Airplanes
This paragraph restates the requirements of paragraph (p) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
Group 3 airplanes as identified in Boeing Alert Service Bulletin
737-27A1297, Revision 1, dated August 2, 2010, on which the elevator
tab control mechanism is replaced during the actions required by
paragraph (o) of this AD: Within 300 flight hours after doing the
replacement, do a detailed inspection for discrepancies of the
inboard and outboard aft attach lugs of the replaced elevator tab
control mechanism, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-27A1297, Revision
1, dated August 2, 2010. Repeat the inspection of the replaced
elevator tab control mechanism thereafter at intervals not to exceed
300 flight hours, except as provided by paragraph (t)(2) of this AD.
(q) Retained Credit for Previous Action
This paragraph restates the provisions specified in paragraph
(q) of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25,
2010). For Group 1 airplanes as identified in Boeing Alert Service
Bulletin 737-27A1297, Revision 1, dated August 2, 2010: Inspections
done in accordance with Boeing Alert Service Bulletin 737-27A1297,
dated April 16, 2010, are acceptable for compliance with only the
initial inspection required by paragraph (n) of this AD.
(r) Retained Reporting for Paragraphs (n) and (p) of This AD
This paragraph restates the requirements of paragraph (r) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010). For
airplanes having line numbers 1 through 3909 inclusive: At the
applicable time specified in paragraph (r)(1) or (r)(2) of this AD,
submit a report of any findings (positive and negative) of the first
inspection required by paragraphs (n) and (p) of this AD, except for
airplanes on which a report required by paragraph (m) of this AD has
been submitted, only submit positive findings; and submit a report
of any positive findings from the repetitive inspections required by
paragraphs (n) and (p) of this AD; to Boeing Commercial Airplanes
Group, Attention: Manager, Airline Support, email:
rse.boecom@boeing.com. The report must include the inspection
results including a description of any discrepancies found, the
airplane line number, and the total number of flight cycles and
flight hours accumulated on the airplane.
(1) If the inspection was done on or after September 9, 2010
(the effective date of AD 2010-17-19, Amendment 39-16413 (75 FR
52242, August 25, 2010)): Submit the report within 10 days after the
inspection.
(2) If the inspection was done before September 9, 2010 (the
effective date of AD 2010-17-19, Amendment 39-16413 (75 FR 52242,
August 25, 2010)): Submit the report within 10 days after September
9, 2010 (the effective date of AD 2010-17-19).
(s) Retained Provision Regarding Not Returning Parts
This paragraph restates the provision specified in paragraph (s)
of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010).
Although Boeing Alert Service Bulletin 737-27A1297, dated April 16,
2010; and Boeing Alert Service Bulletin 737-27A1297, Revision 1,
dated August 2, 2010; specify to return the affected elevator tab
control mechanism to the manufacturer, this AD does not require the
return of the part to the manufacturer.
[[Page 20234]]
(t) Retained Parts Installation Limitations
This paragraph restates the requirements of paragraph (t) of AD
2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010), with
revised limitations. As of September 9, 2010 (the effective date of
AD 2010-17-19), and until the replacement required by paragraph (u)
of this AD for airplanes with line numbers 1 through 3909 inclusive,
or until the effective date of this new AD for airplanes with line
numbers 3910 and subsequent, as applicable: Comply with the
conditions specified in paragraphs (t)(1) and (t)(2) of this AD.
(1) No person may install an elevator tab control mechanism,
part number (P/N) 251A2430-(), on any airplane, unless the mechanism
has been inspected before and after installation using the
inspection procedures specified in paragraphs (o)(1) and (o)(2) of
this AD, and no discrepancies have been found.
(2) An elevator tab control mechanism, P/N 251A2430-(), may be
installed, provided that the inspection specified in paragraph (n)
of this AD is done within 300 flight hours after doing the
installation, and that the inspection specified in paragraph (n) of
this AD is repeated thereafter at intervals not to exceed 300 flight
hours.
(u) New Replacement
For airplanes having line numbers 1 through 3909 inclusive:
Within 60 months after the effective date of this AD, replace the
left and right elevator tab control mechanisms with elevator tab
control mechanisms that have new machined aft attach lugs, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-27-1300, dated April 16, 2012. This replacement
terminates the requirements of paragraphs (g) through (t) of this
AD. Although Boeing Service Bulletin 737-27-1300, dated April 16,
2012, specifies submitting a report, there is no requirement to
report completion of the replacement required by paragraph (u) of
this AD.
(v) New Parts Installation Prohibition
As of the effective date of this AD, no person may install, on
any airplane identified in paragraph (v)(1) or (v)(2) of this AD, an
elevator tab control mechanism having P/N 251A2430-13, -14, -15, -
16, -17, -18, -101, -102, -103, -104, -105, or -106.
(1) Airplanes on which the replacement in paragraph (u) of this
AD has been accomplished.
(2) Airplanes with line numbers 3910 and subsequent.
(w) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(x) Alternative Methods of Compliance (AMOCs)
(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. Information may be emailed 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 for AD 2010-17-19, Amendment 39-16413 (75 FR
52242, August 25, 2010), are approved as AMOCs for the corresponding
provisions of this AD. The expiration of the AMOCS to AD 2010-17-19,
as specified in the service information identified in paragraphs
(x)(4)(i) and (x)(4)(ii) of this AD, is extended to remain valid
until accomplishment of the requirements of paragraph (u) of this
AD.
(i) Boeing Alert Service Bulletin 737-27A1299, dated July 1,
2011 (which is not incorporated by reference in this AD).
(ii) Boeing Alert Service Bulletin 737-27A1299, Revision 1,
dated April 16, 2012 (which is not incorporated by reference in this
AD).
(y) Related Information
For more information about this AD, contact Kelly McGuckin,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA,
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW.,
Renton, Washington 98057-3356; phone: 425-917-6490; fax: 425-917-
6590; email: kelly.mcguckin@faa.gov.
(z) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
May 9, 2013.
(i) Boeing Service Bulletin 737-27-1300, dated April 16, 2012.
(ii) Reserved.
(4) The following service information was approved for IBR on
September 9, 2010 (75 FR 52242, August 25, 2010).
(i) Boeing Alert Service Bulletin 737-27A1297, Revision 1, dated
August 2, 2010.
(ii) Reserved.
(5) The following service information was approved for IBR on
April 29, 2010 (75 FR 21499, April 26, 2010).
(i) Boeing Alert Service Bulletin 737-27A1297, dated April 16,
2010.
(ii) Reserved.
(6) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(7) You may view this service information at FAA, You may review
copies of the referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(8) You may view this 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 20, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-07209 Filed 4-3-13; 8:45 am]
BILLING CODE 4910-13-P
