Airworthiness Directives; The Boeing Company Airplanes, 58330-58334 [2012-23218]
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Federal Register / Vol. 77, No. 183 / Thursday, September 20, 2012 / Proposed Rules
Issued in Renton, Washington, on
September 11, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–23217 Filed 9–19–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0994; Directorate
Identifier 2012–NM–119–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to all The Boeing Company
Model 737–600, –700, –700C, –800,
–900, and –900ER series airplanes. The
existing 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. Since we issued
that AD, Boeing has developed a
modification of the aft attach lugs of the
elevator tab control mechanisms, which
will adequately address the unsafe
condition. This proposed AD would
require 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. We are proposing 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: We must receive comments on
this proposed AD by November 5, 2012.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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
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SUMMARY:
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W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above 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, 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 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 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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0994; Directorate Identifier
2012–NM–119–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to 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 proposed AD.
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Discussion
On August 11, 2010, we issued AD
2010–17–19, Amendment 39–16413 (75
FR 52242, August 25, 2010), for all The
Boeing Company Model 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes. That AD requires repetitive
inspections of the aft attach lugs of the
elevator tab control mechanisms, and
replacement of any discrepant elevator
tab control mechanism. That AD was
prompted by reports of failure of the aft
attach lugs on the elevator tab control
mechanisms, which resulted in severe
elevator vibration. That AD also was
prompted by reports of gaps in elevator
tab control mechanisms and analysis
that additional elevator tab control
mechanisms might have bearings that
will come loose. We issued that 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.
Actions Since Existing AD (AD 2010–
17–19, Amendment 39–16413 (75 FR
52242, August 25, 2010)) Was Issued
The preamble to AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010), specifies that we
consider the requirements ‘‘interim
action’’ and that the manufacturer is
developing a modification to address
the unsafe condition. That AD explains
that we might consider further
rulemaking if a modification is
developed, approved, and available. The
manufacturer now has developed such a
modification, and we have determined
that further rulemaking is indeed
necessary; this proposed AD follows
from that determination.
Relevant Service Information
We reviewed Boeing Service Bulletin
737–27–1300, dated April 16, 2012,
which describes procedures for
replacing elevator tab control
mechanisms that have sheet metal aft
attach lugs with elevator tab control
mechanisms that have new machined
aft attach lugs.
Boeing Service Bulletin 737–27–1300,
dated April 16, 2012, has been approved
as an alternative method of compliance
with the requirements of paragraphs (g)
through (t) of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010).
Clarification of Part Name
The elevator tab control mechanism is
incorrectly identified as the ‘‘elevator
control tab mechanism’’ in certain
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paragraphs of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010). We have corrected
that part name in this proposed AD.
develop in other products of the same
type design.
Proposed AD Requirements
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
This proposed AD would retain all
requirements of AD 2010–17–19,
Amendment 39–16413 (75 FR 52242,
August 25, 2010). This proposed AD
would also require replacement of the
left and right elevator tab control
58331
mechanisms with elevator tab control
mechanisms that have new machined
aft attach lugs, which would terminate
the existing requirements.
Costs of Compliance
We estimate that this proposed AD
affects 1,096 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Retained actions ...............................
7 work-hours × $85 per hour = $595
per inspection cycle.
12 work-hours × $85 per hour =
$1,020.
24 work-hours × $85 per hour =
$2,040.
$0 .....................................................
$595 per inspection cycle.
$58,579 1 ..........................................
$1,140 (installation kit) .....................
$5,858 (for the modification) ............
$1,140 (installation kit) .....................
$2,145 (tooling 2) ..............................
$60,739 per airplane.
Mechanism replacement (one option
for proposed terminating action).
Mechanism modification and replacement (one option for proposed terminating action).
Cost per product
$11,183 per airplane.
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.
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Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
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Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 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:
The Boeing Company: Docket No. FAA–
2012–0994; Directorate Identifier 2012–
NM–119–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by November 5, 2012.
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(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 (m) of AD 2010–09–05,
Amendment 39–16270 (75 FR 21499, April
26, 2010), with revised terminating action.
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
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Federal Register / Vol. 77, No. 183 / Thursday, September 20, 2012 / Proposed Rules
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 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)), terminates the requirements of
this paragraph. Doing the inspection required
by paragraph (n) of this AD terminates the
requirements of this paragraph.
(h) Retained ETOPS Flight Provisions
This paragraph restates the requirements of
paragraph (n) of AD 2010–09–05,
Amendment 39–16270 (75 FR 21499, April
26, 2010), with a terminating action
provision. 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), 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.
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(i) Retained One-Time Inspection for Group
2, Configuration 1, Airplanes
This paragraph restates the requirements of
paragraph (o) of AD 2010–09–05,
Amendment 39–16270 (75 FR 21499, April
26, 2010), with revised terminating action
provisions. 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), 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 (p) of AD 2010–09–05,
Amendment 39–16270 (75 FR 21499, April
26, 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
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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 (q) of AD 2010–09–05,
Amendment 39–16270 (75 FR 21499, April
26, 2010), with revised terminating action
provisions. 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 (r) of AD 2010–09–05, Amendment
39–16270 (75 FR 21499, April 26, 2010), with
revised terminating action provisions.
Replacing an elevator tab control mechanism
with a new, Boeing-built mechanism before
September 9, 2010 (the effective date of AD
2010–17–19, Amendment 39–16413 (75 FR
52242, August 25, 2010)), 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
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
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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 (s) of AD 2010–09–05,
Amendment 39–16270 (75 FR 21499, April
26, 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
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(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.
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(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.
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(q) Retained Credit for Initial Inspection
Done in Accordance With the Original Issue
of the Service Bulletin
This paragraph restates the requirements of
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.
( ), 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.
(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).
(u) New Replacement
(s) Retained Provision Regarding Return of
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.
(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). As
of September 9, 2010 (the effective date of
AD 2010–17–19), and until the effective date
of this new 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–
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
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.
(v) New Parts Installation Prohibition
For all airplanes: As of the effective date
of this AD, no person may install, on any
airplane, an elevator tab control mechanism
having P/N 251A2430–13, –14, –15, –16, –17,
–18, –101, –102, –103, –104, –105, or –106.
(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-ANMSeattle-ACO-AMOC-Requests@faa.gov.
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20SEP1
58334
Federal Register / Vol. 77, No. 183 / Thursday, September 20, 2012 / Proposed Rules
(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) 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.
(y) Related Information
(1) 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.
(2) 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.
Issued in Renton, Washington, on
September 6, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–23218 Filed 9–19–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0985; Directorate
Identifier 2011–NM–250–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–600,
–700, –700C, –800, –900, and –900ER
series airplanes. This proposed AD was
prompted by a report of chafing damage
to a wire bundle that was arcing to
hydraulic tubing and caused by
insufficient separation between the wire
bundle and the hydraulic tubing in the
main landing gear (MLG) wheel well.
This proposed AD would require an
inspection for damage of wire bundles
and hydraulic tubing on the right side
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
14:44 Sep 19, 2012
Jkt 226001
of the forward bulkhead of the MLG
wheel well; installation of new clamps;
and corrective actions, as applicable.
We are proposing this AD to detect and
correct possible damage caused by
insufficient separation between the wire
bundles and hydraulic tubing to prevent
electrical arcing in a flammable fluid
leakage zone, which could lead to a
wheel well fire.
DATES: We must receive comments on
this proposed AD by November 5, 2012.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P. O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; email
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: (425) 917–
6418; fax: (425) 917–6590; email:
marie.hogestad@faa.gov.
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2012–0985; Directorate Identifier 2011–
NM–250–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to 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 proposed AD.
Discussion
We received a report of a Model 737–
800 airplane that was found with the
circuit breaker of the #2 engine spar
valve open. Maintenance found that a
wire had chafed and was arcing to a
hydraulic line. The chafing condition
was caused by inadequate separation
between the wire bundle and the
hydraulic line. Boeing inspected
additional airplanes in production and
found that there was not sufficient
separation, based on design
requirements, between the wire bundles
and adjacent hydraulic tubing at that
location. Wire chafing damage and
electrical arcing in a flammable fluid
leakage zone could lead to a wheel well
fire.
Relevant Service Information
We reviewed Boeing Special
Attention Service Bulletin 737–29–
1113, dated March 23, 2011. That
service bulletin describes procedures for
a general visual inspection for damage
of wire bundles W6128, W7122, W8122,
and W8222 and hydraulic tubing part
numbers (P/Ns) 272A4451–136 and
272A4451–137, installation of new
clamps between the wire bundles and
the adjacent hydraulic tubing, and
corrective actions as applicable.
Corrective actions include repairing
damaged wire bundles and replacing or
repairing damaged hydraulic tubing.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
E:\FR\FM\20SEP1.SGM
20SEP1
]]>Agencies
[Federal Register Volume 77, Number 183 (Thursday, September 20, 2012)]
[Proposed Rules]
[Pages 58330-58334]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-23218]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0994; Directorate Identifier 2012-NM-119-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all The Boeing Company Model 737-600, -700, -700C,
-800, -900, and -900ER series airplanes. The existing 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. Since we issued that AD, Boeing has developed a
modification of the aft attach lugs of the elevator tab control
mechanisms, which will adequately address the unsafe condition. This
proposed AD would require 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.
We are proposing 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: We must receive comments on this proposed AD by November 5,
2012.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail address above 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, 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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 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 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0994;
Directorate Identifier 2012-NM-119-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to 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 proposed AD.
Discussion
On August 11, 2010, we issued AD 2010-17-19, Amendment 39-16413 (75
FR 52242, August 25, 2010), for all The Boeing Company Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes. That AD requires
repetitive inspections of the aft attach lugs of the elevator tab
control mechanisms, and replacement of any discrepant elevator tab
control mechanism. That AD was prompted by reports of failure of the
aft attach lugs on the elevator tab control mechanisms, which resulted
in severe elevator vibration. That AD also was prompted by reports of
gaps in elevator tab control mechanisms and analysis that additional
elevator tab control mechanisms might have bearings that will come
loose. We issued that 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.
Actions Since Existing AD (AD 2010-17-19, Amendment 39-16413 (75 FR
52242, August 25, 2010)) Was Issued
The preamble to AD 2010-17-19, Amendment 39-16413 (75 FR 52242,
August 25, 2010), specifies that we consider the requirements ``interim
action'' and that the manufacturer is developing a modification to
address the unsafe condition. That AD explains that we might consider
further rulemaking if a modification is developed, approved, and
available. The manufacturer now has developed such a modification, and
we have determined that further rulemaking is indeed necessary; this
proposed AD follows from that determination.
Relevant Service Information
We reviewed Boeing Service Bulletin 737-27-1300, dated April 16,
2012, which describes procedures for replacing elevator tab control
mechanisms that have sheet metal aft attach lugs with elevator tab
control mechanisms that have new machined aft attach lugs.
Boeing Service Bulletin 737-27-1300, dated April 16, 2012, has been
approved as an alternative method of compliance with the requirements
of paragraphs (g) through (t) of AD 2010-17-19, Amendment 39-16413 (75
FR 52242, August 25, 2010).
Clarification of Part Name
The elevator tab control mechanism is incorrectly identified as the
``elevator control tab mechanism'' in certain
[[Page 58331]]
paragraphs of AD 2010-17-19, Amendment 39-16413 (75 FR 52242, August
25, 2010). We have corrected that part name in this proposed AD.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2010-17-19,
Amendment 39-16413 (75 FR 52242, August 25, 2010). This proposed AD
would also require replacement of the left and right elevator tab
control mechanisms with elevator tab control mechanisms that have new
machined aft attach lugs, which would terminate the existing
requirements.
Costs of Compliance
We estimate that this proposed AD affects 1,096 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
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 12 work-hours x $85 $58,579 \1\........ $60,739 per airplane.
option for proposed terminating per hour = $1,020. $1,140
action). (installation kit).
Mechanism modification and 24 work-hours x $85 $5,858 (for the $11,183 per airplane.
replacement (one option for per hour = $2,040. modification).
proposed terminating action). $1,140
(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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2010-17-19, Amendment 39-16413 (75 FR 52242, August 25, 2010), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0994; Directorate Identifier
2012-NM-119-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by November 5,
2012.
(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 (m) of AD
2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 2010), with
revised terminating action. 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
[[Page 58332]]
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 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)), terminates the
requirements of this paragraph. Doing the inspection required by
paragraph (n) of this AD terminates the requirements of this
paragraph.
(h) Retained ETOPS Flight Provisions
This paragraph restates the requirements of paragraph (n) of AD
2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 2010), with a
terminating action provision. 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), 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.
(i) Retained One-Time Inspection for Group 2, Configuration 1,
Airplanes
This paragraph restates the requirements of paragraph (o) of AD
2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 2010), with
revised terminating action provisions. 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), 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 (p) of AD
2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 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 (q) of AD
2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 2010), with
revised terminating action provisions. 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 (r) of AD
2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 2010), with
revised terminating action provisions. Replacing an elevator tab
control mechanism with a new, Boeing-built mechanism before
September 9, 2010 (the effective date of AD 2010-17-19, Amendment
39-16413 (75 FR 52242, August 25, 2010)), 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 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 (s) of AD
2010-09-05, Amendment 39-16270 (75 FR 21499, April 26, 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
[[Page 58333]]
(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 Initial Inspection Done in Accordance With the
Original Issue of the Service Bulletin
This paragraph restates the requirements of 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 Return of 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.
(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). As of
September 9, 2010 (the effective date of AD 2010-17-19), and until
the effective date of this new 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.
(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.
(v) New Parts Installation Prohibition
For all airplanes: As of the effective date of this AD, no
person may install, on any airplane, an elevator tab control
mechanism having P/N 251A2430-13, -14, -15, -16, -17, -18, -101, -
102, -103, -104, -105, or -106.
(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.
[[Page 58334]]
(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) 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.
(y) Related Information
(1) 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.
(2) 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.
Issued in Renton, Washington, on September 6, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-23218 Filed 9-19-12; 8:45 am]
BILLING CODE 4910-13-P
