Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes, 52242-52246 [2010-20556]
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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations
We are issuing this AD to prevent engine
in-flight shutdown leading to loss of control
of the airplane.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) Before next flight after the effective date
of this AD, identify the serial number (S/N)
of each P/N 02–7210–11001R13, P/N 05–
7211–K006001, and P/N 05–7211–K006002
clutch assembly installed on the airplane. If
the S/N matches one of those listed in
Thielert Aircraft Engines GmbH Service
Bulletin (SB) No. TM TAE 125–0021, dated
June 9, 2010, or SB No. TM TAE 125–1011
P1, dated June 9, 2010, as applicable to
engine model, replace the clutch assembly
within the following compliance times:
(i) For engines with affected clutch
assemblies that have accumulated 100 flight
hours or more on the effective date of this
AD, replace the clutch assembly before
further flight.
(ii) For engines with affected clutch
assemblies that have accumulated less than
100 flight hours on the effective date of this
AD, replace the clutch assembly before
accumulating 100 flight hours.
Clutch Assembly Prohibition
(2) After the effective date of this AD:
(i) Do not install an engine having a clutch
assembly that is listed by S/N in Thielert
Aircraft Engines GmbH Service Bulletin (SB)
No. TM TAE 125–0021, dated June 9, 2010,
or SB No. TM TAE 125–1011 P1, dated June
9, 2010; and
(ii) Do not install any clutch assembly
listed by S/N in Thielert Aircraft Engines
GmbH Service Bulletin (SB) No. TM TAE
125–0021, dated June 9, 2010, or SB No. TM
TAE 125–1011 P1, dated June 9, 2010, into
any engine.
FAA AD Differences
(f) This AD differs from the Mandatory
Continuing Airworthiness Information
(MCAI) and/or service information as
follows:
(1) EASA AD 2010–0111–E, dated June 10,
2010 (corrected June 11, 2010) has separate
compliance times for engines installed on
twin-engine airplanes. This AD does not.
(2) EASA AD 2010–0111–E, dated June 10,
2010 (corrected June 11, 2010) allows a single
ferry flight with conditions. This AD does
not.
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Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
17:51 Aug 24, 2010
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Issued in Burlington, Massachusetts, on
August 16, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2010–21058 Filed 8–24–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0798; Directorate
Identifier 2010–NM–174–AD; Amendment
39–16413; AD 2010–17–19]
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; request for
comments.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD)
that applies to all Model 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes. The existing AD currently
requires, for certain airplanes, a onetime detailed inspection of the inboard
and outboard aft attach lugs of the left
and right elevator tab control
mechanisms for discrepancies, and
replacement of any discrepant elevator
tab control mechanism. For certain
other airplanes, the existing AD requires
that the inspections be done
repetitively. Replacing the elevator tab
SUMMARY:
Related Information
(h) Refer to MCAI EASA AD 2010–0111–
E, dated June 10, 2010 (corrected June 11,
2010), for related information.
(i) Contact Alan Strom, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: alan.strom@faa.gov; telephone
(781) 238–7143; fax (781) 238–7199, for more
information about this AD.
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Material Incorporated by Reference
(j) You must use Thielert Aircraft Engines
GmbH Service Bulletin No. TM TAE 125–
0021, dated June 9, 2010, or SB No. TM TAE
125–1011 P1, also dated June 9, 2010, to
identify the affected clutch assemblies
requiring replacement by this AD.
(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 Thielert Aircraft Engines
GmbH, Platanenstrasse 14 D–09350,
Lichtenstein, Germany, telephone: +49–
37204–696–0; fax: +49–37204–696–55; email: info@centurion-engines.com.
(3) You may review copies at the FAA,
New England Region, 12 New England
Executive Park, Burlington, MA; or 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.
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control mechanism with a new Boeingbuilt mechanism terminates the
repetitive inspections in the existing
AD. This new AD requires that modified
repetitive inspections be done on all
airplanes, regardless of accomplishment
of the terminating action specified in
the existing AD. This AD results from
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 detect and correct discrepancies in
the aft attach lugs of the elevator tab
control mechanism, which could result
in 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 becomes effective
September 9, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of September 9, 2010.
On April 29, 2010 (75 FR 21499, April
26, 2010), the Director of the Federal
Register approved the incorporation by
reference of a certain other publication
listed in the AD.
We must receive any comments on
this AD by October 12, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle ACO, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6490;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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Discussion
On April 19, 2010, we issued AD
2010–09–05, amendment 39–16270 (75
FR 21499, April 26, 2010). That AD
applies to all Model 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes. That AD requires, for certain
airplanes, a one-time detailed
inspection of the inboard and outboard
aft attach lugs of the left and right
elevator tab control mechanisms for
discrepancies, and replacement of any
discrepant elevator tab control
mechanism (the replacement includes
performing the detailed inspection on
the replacement part before and after
installation, and corrective actions if
necessary). For certain other airplanes,
that AD requires repetitive inspections
for discrepancies of the inboard and
outboard aft attach lugs of the left and
right elevator tab control mechanisms,
and replacement if necessary. For
airplanes on which the elevator tab
control mechanism is replaced with a
certain mechanism, that AD requires
repetitive inspections for discrepancies
of the elevator tab control mechanism
and replacement if necessary. Replacing
the elevator tab control mechanism with
a new Boeing-built mechanism
terminates the repetitive inspections in
that AD. That AD resulted from reports
of failure of the aft attach lugs on the
elevator tab control mechanisms, which
resulted in severe elevator vibration.
One event occurred on an airplane on
which a previous AD (emergency AD
2010–06–51, Amendment 39–16250 (75
FR 16648, April 2, 2010)) had been
done. The actions specified in AD 2010–
09–05 are intended to detect and correct
discrepancies in the aft attach lugs of
the elevator tab control mechanism,
which could result in unwanted
elevator and tab vibration. Consequent
structural failure of the elevator or
horizontal stabilizer could result in loss
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of structural integrity and aircraft
control.
Actions Since AD 2010–09–05 Was
Issued
Since we issued AD 2010–09–05, we
have received reports of gaps and loose
bearings. For Boeing-built mechanisms,
we received reports of gaps but no
reports of loose bearings. Also,
additional analysis has shown that nonBoeing-built mechanisms installed on
airplanes having Line Number 2708 and
subsequent might have bearings that
will come loose. We have determined
that the identified unsafe condition is
related to the design of the elevator tab
control mechanism. Therefore, all
airplanes identified in the applicability
of this AD must be repetitively
inspected. In addition, installing a
Boeing-built mechanism is no longer
terminating action for the repetitive
inspections.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–27A1297, Revision
1, dated August 2, 2010. This service
bulletin describes procedures for
repetitive inspections for discrepancies
of the inboard and outboard aft attach
lugs of the left and right elevator tab
control mechanisms, and replacement if
necessary. We referred to Boeing Alert
Service Bulletin 737–27A1297, dated
April 16, 2010, as the appropriate
source of service information for
accomplishing certain required actions
in AD 2010–09–05. Boeing Alert Service
Bulletin 737–27A1297, Revision 1, no
longer specifies that installing a Boeingbuilt mechanism ends the repetitive
inspections. Boeing Alert Service
Bulletin 737–27A1297, Revision 1, also
modifies the inspection procedure by
expanding the allowable gap depth in
the lug-to-lug interface and the lug-tospacer interface. Boeing Alert Service
Bulletin 737–27A1297, Revision 1, also
removes the procedure to determine if
replacement mechanisms are Boeingbuilt or non-Boeing-built.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design. For this reason, we are issuing
this AD to supersede AD 2010–09–05.
This new AD retains certain
requirements of the existing AD. This
AD also requires accomplishing the
actions specified in Boeing Alert Service
Bulletin 737–27A1297, Revision 1,
dated August 2, 2010, described
previously, except this AD does not
require sending discrepant elevator tab
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52243
control mechanisms to the
manufacturer. This AD does require
sending the inspection results to the
manufacturer.
Change to Existing AD
This AD retains certain requirements
of AD 2010–09–05. As a result, the
corresponding paragraph identifiers
have changed in this AD, as listed in the
following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in
AD 2010–09–05
Corresponding requirement in this AD
paragraph (m)
paragraph (n)
paragraph (o)
paragraph (p)
paragraph (q)
paragraph (r)
paragraph (s)
paragraph (g)
paragraph (h)
paragraph (i)
paragraph (j)
paragraph (k)
paragraph (l)
paragraph (m)
Interim Action
This AD is considered to be interim
action. The manufacturer is currently
developing a terminating action that
will address the unsafe condition
identified in this AD. Once final action
has been identified, we might consider
further rulemaking.
FAA’s Justification and Determination
of the Effective Date
Discrepancies, including loose
bearings, in the aft attach lugs of the
elevator tab control mechanism could
result in elevator and tab vibration.
Consequent structural failure of the
elevator or horizontal stabilizer could
result in loss of structural integrity and
aircraft control. Because of our
requirement to promote safe flight of
civil aircraft and thus, the critical need
to ensure the structural integrity of the
airplane and the short compliance time
involved with this action, this AD must
be issued immediately.
Because an unsafe condition exists
that requires the immediate adoption of
this AD, we find that notice and
opportunity for prior public comment
hereon are impracticable and that good
cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2010–0798; Directorate Identifier 2010–
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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations
NM–174–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
List of Subjects in 14 CFR Part 39
Authority for This Rulemaking
■
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Regulatory Findings
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 the regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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.
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17:51 Aug 24, 2010
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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 part 39 of the Federal
Aviation Regulations (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 Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–16270 (75
FR 21499, April 26, 2010) and by adding
the following new airworthiness
directive (AD):
■
2010–17–19 The Boeing Company:
Amendment 39–16413. Docket No.
FAA–2010–0798; Directorate Identifier
2010–NM–174–AD.
Effective Date
(a) This AD becomes effective September 9,
2010.
Affected ADs
(b) This AD supersedes AD 2010–09–05,
Amendment 39–16270.
Applicability
(c) This AD applies to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes;
certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
Unsafe Condition
(e) This AD results from reports of failure
of the aft attach lugs on 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. The Federal
Aviation Administration is issuing this AD to
detect and correct discrepancies in the aft
attach lugs of the elevator tab control
mechanism, which could result in elevator
and tab vibration. Consequent structural
failure of the elevator or horizontal stabilizer
could result in loss of structural integrity and
aircraft control.
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.
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Restatement of Certain Requirements of AD
2010–09–05, With Revised Terminating
Action
Repetitive Inspections for Group 1
Airplanes, as Identified in Boeing Alert
Service Bulletin 737–27A1297, Dated April
16, 2010
(g) 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), do a detailed inspection for
discrepancies of the inboard and outboard aft
attach lugs of the left and right elevator
control tab 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 the effective
date of this AD terminates the requirements
of this paragraph. Doing the inspection
required by paragraph (n) of this AD
terminates the requirements of this
paragraph.
(h) For Group 1 airplanes as identified in
Boeing Alert Service Bulletin 737–27A1297,
dated April 16, 2010: Beginning 7 days after
April 29, 2010, no person may operate an
airplane on an extended twin operations
(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.
One-Time Inspection for Group 2,
Configuration 1 Airplanes, as Identified in
Boeing Alert Service Bulletin 737–27A1297,
Dated April 16, 2010
(i) 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, do a one-time
detailed inspection for discrepancies of the
inboard and outboard aft attach lugs of the
left and right elevator control tab
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.
Corrective Actions for Paragraphs (g), (i),
and (k) of This AD
(j) 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
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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.
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Repetitive Inspections for Certain Group 2,
Configuration 1 Airplanes, as Identified in
Boeing Alert Service Bulletin 737–27A1297,
Dated April 16, 2010
(k) For Group 2, Configuration 1 airplanes
as identified in Boeing Alert Service Bulletin
737–27A1297, dated April 16, 2010, on
which the elevator control tab 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 control tab
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 the effective date of this
AD is terminating action for this paragraph.
Doing the inspection required by paragraph
(n) of this AD terminates the requirements of
this paragraph.
Terminating Action for Paragraphs (g), (i),
and (k) of This AD, if Done Before the
Effective Date of This AD
(l) Replacing an elevator tab mechanism
with a new, Boeing-built mechanism before
the effective date of this AD, 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 the effective date of
this AD does not terminate the inspections
required by paragraphs (g), (i), and (k) of this
AD.
Note 1: Refer to 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
737–27A1297, dated April 16, 2010, to
establish whether the mechanism is Boeingbuilt.
(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.
Reporting for Paragraphs (g), (i), and (k) of
This AD
(m) At the applicable time specified in
paragraph (m)(1) or (m)(2) of this AD: Submit
a report of any findings (positive and
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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, e-mail: 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.
Under the provisions of the Paperwork
Reduction Act (44 U.S.C. 3501 et seq.), the
Office of Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection was done on or after
April 29, 2010: Submit the report within 10
days after the inspection.
(2) If the inspection was done before April
29, 2010: Submit the report within 10 days
after April 29, 2010.
New Requirements of This AD
Repetitive Inspections
(n) 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 the effective date of
this AD, 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 paragraph (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 the effective date
of this AD.
(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 the effective
date of this AD, whichever occurs first.
Corrective Actions
(o) If, during any inspection required by
paragraph (n) or (p) of this AD, any
PO 00000
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Fmt 4700
Sfmt 4700
52245
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.
Reduced Repetitive Inspection Interval for
Group 3 Airplanes, as Identified in Boeing
Alert Service Bulletin 737–27A1297,
Revision 1, on Which the Mechanism Is
Replaced
(p) 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.
Credit for Initial Inspection Done in
Accordance With the Original Issue of the
Service Bulletin
(q) 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.
Reporting for Paragraphs (n) and (p) of This
AD
(r) 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, e-mail: 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
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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations
and flight hours accumulated on the airplane.
Under the provisions of the Paperwork
Reduction Act (44 U.S.C. 3501 et seq.), the
Office of Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 10 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 10 days after the effective date of this
AD.
No Return of Parts
(s) Although Boeing Alert Service Bulletins
737–27A1297, dated April 16, 2010; and
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.
mstockstill on DSKH9S0YB1PROD with RULES
Parts Installation
(t) As of the effective date of this AD,
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 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, part
number 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.
Alternative Methods of Compliance
(AMOCs)
(u)(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. Send information to ATTN: Kelly
McGuckin, Aerospace Engineer, Systems and
Equipment Branch, ANM–130S, FAA, Seattle
ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone 425–
917–6490; fax 425–917–6590. Information
may be e-mailed to: 9–ANM–Seattle-ACO–
AMOC–Requests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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
VerDate Mar<15>2010
17:51 Aug 24, 2010
Jkt 220001
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 2010–09–05,
amendment 39–16270, are approved as
AMOCs for the corresponding provisions of
paragraphs (g), (h), (i), (j), and (k) of this AD.
Material Incorporated by Reference
(v) You must use Boeing Alert Service
Bulletin 737–27A1297, dated April 16, 2010;
and Boeing Alert Service Bulletin 737–
27A1297, Revision 1, dated August 2, 2010;
as applicable; 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
Boeing Alert Service Bulletin 737–27A1297,
Revision 1, dated August 2, 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 Boeing Alert Service Bulletin
737–27A1297, dated April 16, 2010, on April
29, 2010 (75 FR 21499, April 26, 2010).
(3) 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.
(4) 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.
(5) 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 August
11, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–20556 Filed 8–24–10; 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–2010–0804; Directorate
Identifier 2010–NM–163–AD; Amendment
39–16420; AD 2010–18–07]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
A special detailed inspection of A318/
A319/A320/A321 elevators pre-modification
35515 was introduced under ALI
(Airworthiness Limitations Items) task
552007 in the ALS (Airworthiness
Limitations Section) part 2 * * * This ALI
task has been introduced with an
applicability defined at aeroplane
modification level.
*
*
*
*
*
It has been reported that some elevators
may have been moved from the aeroplane on
which they were originally fitted to another
aeroplane, * * *. Consequently, those
elevators might not have been inspected
within the applicable required time frame as
per ALI task 552007 requirements.
*
*
*
*
*
The unsafe condition is structural
failure of the elevators and consequent
loss of control of the airplane. This AD
requires actions that are intended to
address the unsafe condition described
in the MCAI.
DATES: This AD becomes effective
September 9, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 9, 2010.
We must receive comments on this
AD by October 12, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
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]]>Agencies
[Federal Register Volume 75, Number 164 (Wednesday, August 25, 2010)]
[Rules and Regulations]
[Pages 52242-52246]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-20556]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0798; Directorate Identifier 2010-NM-174-AD;
Amendment 39-16413; AD 2010-17-19]
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; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to all Model 737-600, -700, -700C, -800, -900, and -
900ER series airplanes. The existing AD currently requires, for certain
airplanes, a one-time detailed inspection of the inboard and outboard
aft attach lugs of the left and right elevator tab control mechanisms
for discrepancies, and replacement of any discrepant elevator tab
control mechanism. For certain other airplanes, the existing AD
requires that the inspections be done repetitively. Replacing the
elevator tab control mechanism with a new Boeing-built mechanism
terminates the repetitive inspections in the existing AD. This new AD
requires that modified repetitive inspections be done on all airplanes,
regardless of accomplishment of the terminating action specified in the
existing AD. This AD results from 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 detect and correct discrepancies in the aft attach
lugs of the elevator tab control mechanism, which could result in
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 becomes effective September 9, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of September 9,
2010.
On April 29, 2010 (75 FR 21499, April 26, 2010), the Director of
the Federal Register approved the incorporation by reference of a
certain other publication listed in the AD.
We must receive any comments on this AD by October 12, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
[[Page 52243]]
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle ACO, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6490;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
On April 19, 2010, we issued AD 2010-09-05, amendment 39-16270 (75
FR 21499, April 26, 2010). That AD applies to all Model 737-600, -700,
-700C, -800, -900, and -900ER series airplanes. That AD requires, for
certain airplanes, a one-time detailed inspection of the inboard and
outboard aft attach lugs of the left and right elevator tab control
mechanisms for discrepancies, and replacement of any discrepant
elevator tab control mechanism (the replacement includes performing the
detailed inspection on the replacement part before and after
installation, and corrective actions if necessary). For certain other
airplanes, that AD requires repetitive inspections for discrepancies of
the inboard and outboard aft attach lugs of the left and right elevator
tab control mechanisms, and replacement if necessary. For airplanes on
which the elevator tab control mechanism is replaced with a certain
mechanism, that AD requires repetitive inspections for discrepancies of
the elevator tab control mechanism and replacement if necessary.
Replacing the elevator tab control mechanism with a new Boeing-built
mechanism terminates the repetitive inspections in that AD. That AD
resulted from reports of failure of the aft attach lugs on the elevator
tab control mechanisms, which resulted in severe elevator vibration.
One event occurred on an airplane on which a previous AD (emergency AD
2010-06-51, Amendment 39-16250 (75 FR 16648, April 2, 2010)) had been
done. The actions specified in AD 2010-09-05 are intended to detect and
correct discrepancies in the aft attach lugs of the elevator tab
control mechanism, which could result in unwanted elevator and tab
vibration. Consequent structural failure of the elevator or horizontal
stabilizer could result in loss of structural integrity and aircraft
control.
Actions Since AD 2010-09-05 Was Issued
Since we issued AD 2010-09-05, we have received reports of gaps and
loose bearings. For Boeing-built mechanisms, we received reports of
gaps but no reports of loose bearings. Also, additional analysis has
shown that non-Boeing-built mechanisms installed on airplanes having
Line Number 2708 and subsequent might have bearings that will come
loose. We have determined that the identified unsafe condition is
related to the design of the elevator tab control mechanism. Therefore,
all airplanes identified in the applicability of this AD must be
repetitively inspected. In addition, installing a Boeing-built
mechanism is no longer terminating action for the repetitive
inspections.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-27A1297,
Revision 1, dated August 2, 2010. This service bulletin describes
procedures for repetitive inspections for discrepancies of the inboard
and outboard aft attach lugs of the left and right elevator tab control
mechanisms, and replacement if necessary. We referred to Boeing Alert
Service Bulletin 737-27A1297, dated April 16, 2010, as the appropriate
source of service information for accomplishing certain required
actions in AD 2010-09-05. Boeing Alert Service Bulletin 737-27A1297,
Revision 1, no longer specifies that installing a Boeing-built
mechanism ends the repetitive inspections. Boeing Alert Service
Bulletin 737-27A1297, Revision 1, also modifies the inspection
procedure by expanding the allowable gap depth in the lug-to-lug
interface and the lug-to-spacer interface. Boeing Alert Service
Bulletin 737-27A1297, Revision 1, also removes the procedure to
determine if replacement mechanisms are Boeing-built or non-Boeing-
built.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. For this reason, we
are issuing this AD to supersede AD 2010-09-05. This new AD retains
certain requirements of the existing AD. This AD also requires
accomplishing the actions specified in Boeing Alert Service Bulletin
737-27A1297, Revision 1, dated August 2, 2010, described previously,
except this AD does not require sending discrepant elevator tab control
mechanisms to the manufacturer. This AD does require sending the
inspection results to the manufacturer.
Change to Existing AD
This AD retains certain requirements of AD 2010-09-05. As a result,
the corresponding paragraph identifiers have changed in this AD, as
listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2010-09-05 AD
------------------------------------------------------------------------
paragraph (m) paragraph (g)
paragraph (n) paragraph (h)
paragraph (o) paragraph (i)
paragraph (p) paragraph (j)
paragraph (q) paragraph (k)
paragraph (r) paragraph (l)
paragraph (s) paragraph (m)
------------------------------------------------------------------------
Interim Action
This AD is considered to be interim action. The manufacturer is
currently developing a terminating action that will address the unsafe
condition identified in this AD. Once final action has been identified,
we might consider further rulemaking.
FAA's Justification and Determination of the Effective Date
Discrepancies, including loose bearings, in the aft attach lugs of
the elevator tab control mechanism could result in elevator and tab
vibration. Consequent structural failure of the elevator or horizontal
stabilizer could result in loss of structural integrity and aircraft
control. Because of our requirement to promote safe flight of civil
aircraft and thus, the critical need to ensure the structural integrity
of the airplane and the short compliance time involved with this
action, this AD must be issued immediately.
Because an unsafe condition exists that requires the immediate
adoption of this AD, we find that notice and opportunity for prior
public comment hereon are impracticable and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2010-0798; Directorate Identifier 2010-
[[Page 52244]]
NM-174-AD'' at the beginning of your comments. We specifically invite
comments on the overall regulatory, economic, environmental, and energy
aspects of this AD. We will consider all comments received by the
closing date and may amend this AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
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
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends part 39 of the Federal Aviation Regulations (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 39-16270 (75 FR 21499, April 26, 2010) and by adding
the following new airworthiness directive (AD):
2010-17-19 The Boeing Company: Amendment 39-16413. Docket No. FAA-
2010-0798; Directorate Identifier 2010-NM-174-AD.
Effective Date
(a) This AD becomes effective September 9, 2010.
Affected ADs
(b) This AD supersedes AD 2010-09-05, Amendment 39-16270.
Applicability
(c) This AD applies to all The Boeing Company Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes; certificated in
any category.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Unsafe Condition
(e) This AD results from reports of failure of the aft attach
lugs on 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. The Federal Aviation Administration is issuing this AD to
detect and correct discrepancies in the aft attach lugs of the
elevator tab control mechanism, which could result in elevator and
tab vibration. Consequent structural failure of the elevator or
horizontal stabilizer could result in loss of structural integrity
and aircraft control.
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 Certain Requirements of AD 2010-09-05, With Revised
Terminating Action
Repetitive Inspections for Group 1 Airplanes, as Identified in Boeing
Alert Service Bulletin 737-27A1297, Dated April 16, 2010
(g) 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), do a detailed inspection for
discrepancies of the inboard and outboard aft attach lugs of the
left and right elevator control tab 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 the effective date of
this AD terminates the requirements of this paragraph. Doing the
inspection required by paragraph (n) of this AD terminates the
requirements of this paragraph.
(h) For Group 1 airplanes as identified in Boeing Alert Service
Bulletin 737-27A1297, dated April 16, 2010: Beginning 7 days after
April 29, 2010, no person may operate an airplane on an extended
twin operations (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.
One-Time Inspection for Group 2, Configuration 1 Airplanes, as
Identified in Boeing Alert Service Bulletin 737-27A1297, Dated April
16, 2010
(i) 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, do a one-time detailed
inspection for discrepancies of the inboard and outboard aft attach
lugs of the left and right elevator control tab 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.
Corrective Actions for Paragraphs (g), (i), and (k) of This AD
(j) 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
[[Page 52245]]
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.
Repetitive Inspections for Certain Group 2, Configuration 1 Airplanes,
as Identified in Boeing Alert Service Bulletin 737-27A1297, Dated April
16, 2010
(k) For Group 2, Configuration 1 airplanes as identified in
Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010, on
which the elevator control tab 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 control tab 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 the effective date of
this AD is terminating action for this paragraph. Doing the
inspection required by paragraph (n) of this AD terminates the
requirements of this paragraph.
Terminating Action for Paragraphs (g), (i), and (k) of This AD, if Done
Before the Effective Date of This AD
(l) Replacing an elevator tab mechanism with a new, Boeing-built
mechanism before the effective date of this AD, 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 the effective date of
this AD does not terminate the inspections required by paragraphs
(g), (i), and (k) of this AD.
Note 1: Refer to 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 737-27A1297, dated April 16, 2010, to establish
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.
Reporting for Paragraphs (g), (i), and (k) of This AD
(m) 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, e-
mail: 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. Under the provisions of
the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has approved the information collection
requirements contained in this AD and has assigned OMB Control
Number 2120-0056.
(1) If the inspection was done on or after April 29, 2010:
Submit the report within 10 days after the inspection.
(2) If the inspection was done before April 29, 2010: Submit the
report within 10 days after April 29, 2010.
New Requirements of This AD
Repetitive Inspections
(n) 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 the effective date of this AD, 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 paragraph (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 the effective date of this AD.
(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 the effective date of this AD,
whichever occurs first.
Corrective Actions
(o) 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.
Reduced Repetitive Inspection Interval for Group 3 Airplanes, as
Identified in Boeing Alert Service Bulletin 737-27A1297, Revision 1, on
Which the Mechanism Is Replaced
(p) 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.
Credit for Initial Inspection Done in Accordance With the Original
Issue of the Service Bulletin
(q) 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.
Reporting for Paragraphs (n) and (p) of This AD
(r) 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, e-mail: 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
[[Page 52246]]
and flight hours accumulated on the airplane. Under the provisions
of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office
of Management and Budget (OMB) has approved the information
collection requirements contained in this AD and has assigned OMB
Control Number 2120-0056.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 10 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 10 days after the effective date of
this AD.
No Return of Parts
(s) Although Boeing Alert Service Bulletins 737-27A1297, dated
April 16, 2010; and 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.
Parts Installation
(t) As of the effective date of this AD, 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 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, part number 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.
Alternative Methods of Compliance (AMOCs)
(u)(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. Send information to
ATTN: Kelly McGuckin, Aerospace Engineer, Systems and Equipment
Branch, ANM-130S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone 425-917-6490; fax 425-917-6590.
Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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 2010-09-05,
amendment 39-16270, are approved as AMOCs for the corresponding
provisions of paragraphs (g), (h), (i), (j), and (k) of this AD.
Material Incorporated by Reference
(v) You must use Boeing Alert Service Bulletin 737-27A1297,
dated April 16, 2010; and Boeing Alert Service Bulletin 737-27A1297,
Revision 1, dated August 2, 2010; as applicable; 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 Boeing Alert Service Bulletin 737-
27A1297, Revision 1, dated August 2, 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 Boeing Alert Service Bulletin 737-
27A1297, dated April 16, 2010, on April 29, 2010 (75 FR 21499, April
26, 2010).
(3) 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.
(4) 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.
(5) 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 August 11, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-20556 Filed 8-24-10; 8:45 am]
BILLING CODE 4910-13-P
