[Federal Register Volume 77, Number 183 (Thursday, September 20, 2012)]
[Proposed Rules]
[Pages 58330-58334]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-23218]
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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).
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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 http://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 http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (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:
[email protected].
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 http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
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: [email protected]. 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:
[email protected]. 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 [email protected].
[[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: [email protected].
(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