Airworthiness Directives; The Boeing Company Airplanes, 46340-46343 [2012-18882]
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TKELLEY on DSK3SPTVN1PROD with PROPOSALS
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Federal Register / Vol. 77, No. 150 / Friday, August 3, 2012 / Proposed Rules
economically unacceptable impact and
would therefore require regulation
within the United States and on all
similar plant material imported into the
United States to ensure a low
prevalence of CWR in production
facilities. Designating CWR as a
regulated non-quarantine pest would
allow for the creation of a certification
program for both domestic propagators
and propagators in foreign countries
who want to export cuttings of CWR
hosts into the United States. This
certification would provide a level of
protection against the possible shipment
of CWR infected cuttings from approved
foreign facilities. Designating CWR as a
regulated non-quarantine pest would
mean discontinuing the current process
for responding to domestic CWR
outbreaks and the removal of CWR from
our list of actionable quarantine pests.
3. No longer managing CWR as a
quarantine pest whose presence requires
an eradication-oriented response, but
maintaining port of entry restrictions for
chrysanthemums destined to those
States where CWR is not present and
where these States have established an
official control program under the
Federally Regulated State-Managed
Phytosanitary Program. Any State
wishing to establish an official control
program would have to conduct a
survey demonstrating that CWR does
not already exist in the state, conduct
periodic nursery inspections illustrating
the continued absence of CWR in
growing operations, and issue State
level regulations which controls the
importation of CWR host material into
the State and allows for the eradication
of CWR if detected within the State.
Once a State’s official control program
is approved by APHIS, any potential
host of CWR with that State as its
intended final destination would be
inspected at the U.S. port and refused
entry into the State if CWR is found.
However, potential CWR hosts arriving
at ports, and destined for States which
do not have an official control program
for CWR, would not be inspected or
regulated for CWR. Additional
information regarding The Federally
Recognized State Managed
Phytosanitary Program is available on
the APHIS Web site at https://
www.aphis.usda.gov/plant_health/
plant_pest_info/frsmp/index.shtml.
4. Completely removing CWR as a
quarantine pest whose presence requires
an eradication-oriented response, thus
allowing propagators and growers to
manage CWR as a quality pest of
chrysanthemum without Federal
restrictions requiring eradication of this
pest.
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We welcome comments on these
options, particularly on the advantages
and disadvantages of each option and
the commenter’s preferred option. If
none of the options under consideration
seem appropriate, we encourage the
submission of new options or
suggestions that we may have
overlooked, as well as comments on the
advantages of these new options or
suggestions.
This action has been determined to be
not significant for the purposes of
Executive Order 12866 and, therefore,
has not been reviewed by the Office of
Management and Budget.
Authority: 7 U.S.C. 150dd, 150ee, 150ff,
151–167; 7 CFR 2.22, 2.80, and 371.2(c).
Done in Washington, DC, this 30th day of
July.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. 2012–19024 Filed 8–2–12; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0803; Directorate
Identifier 2011–NM–214–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 777–200, -200LR, -300, and
-300ER series airplanes. The existing AD
currently requires repetitive inspections
for cracking of the elevator actuator
fittings. Since we issued that AD, the
manufacturer has developed a
modification that was approved as an
optional terminating action to the
currently required repetitive
inspections. We have been advised that
the modification procedures include
certain incorrect torque values. This
proposed AD would require, for
previously modified airplanes,
repetitive inspections for movement of
the fittings or fastener heads, and
eventual replacement of certain bolts
(including related investigative and
corrective actions if necessary). For all
airplanes, this replacement, with
corrected torque values, would
SUMMARY:
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terminate the requirements of the AD.
This proposed AD would also remove
certain airplanes from the applicability.
We are proposing this AD to detect and
correct a cracked actuator fitting or
incorrectly installed bolts to the actuator
fitting, which could lead to the elevator
becoming detached and unrestrained,
and a consequent unacceptable flutter
condition and loss of control of the
airplane.
We must receive comments on
this proposed AD by September 17,
2012.
DATES:
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, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
ADDRESSES:
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:
Melanie Violette, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
985057–3356; phone: 425–917–6422;
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fax: 425–917–6590; email:
melanie.violette@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–2012–0803; Directorate Identifier
2011–NM–214–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 December 10, 2007, we issued AD
2007–26–05, Amendment 39–15307 (72
FR 71212, December 17, 2007), for all
Boeing Model 777–200, –200LR, –300,
and –300ER series airplanes. That AD
requires initial and repetitive
inspections for cracking of the elevator
actuator fittings, and replacement of any
cracked fitting with a new fitting. That
AD resulted from a report of a cracked
left elevator actuator fitting. We issued
that AD to detect and correct a cracked
actuator fitting, which could detach
from the elevator and lead to an
unrestrained elevator and an
unacceptable flutter condition, and
consequent loss of airplane control.
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Actions Since Existing AD Was Issued
The preamble to AD 2007–26–05,
Amendment 39–15307 (72 FR 71212,
December 17, 2007), specifies that we
consider the requirements ‘‘interim
action’’ and that the manufacturer is
developing a modification to address
the unsafe condition. AD 2007–26–05
also explains that we might consider
further rulemaking if a modification is
developed, approved, and available. The
manufacturer developed such a
modification, which is specified in
Boeing Alert Service Bulletin 777–
55A0016, dated October 27, 2009. We
issued an alternative method of
compliance (AMOC) specifying that the
optional accomplishment of the actions
specified in Boeing Alert Service
Bulletin 777–55A0016, dated October
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27, 2009, terminate the requirements of
AD 2007–26–05. Boeing Alert Service
Bulletin 777–55A0016, dated October
27, 2009, however, specified incorrect
torque values for the BACB30NR4K6
and BACB30NR4K7 bolts, which could
recreate the original unsafe condition.
We have thus determined that further
rulemaking is necessary to address this
potentially reintroduced unsafe
condition.
Relevant Service Information
We reviewed Boeing Alert Service
Bulletin 777–55A0016, Revision 1,
dated August 25, 2011, which describes
procedures for replacing the elevator
actuator fitting assemblies with new
assemblies, and torquing the bolts with
correct torque values, which eliminates
the need for the repetitive inspections
required by AD 2007–26–05,
Amendment 39–15307 (72 FR 71212,
December 17, 2007).
Boeing Alert Service Bulletin 777–
55A0016, Revision 1, dated August 25,
2011, also describes additional work for
airplanes that were modified using
Boeing Alert Service Bulletin 777–
55A0016, dated October 27, 2009,
which specified certain incorrect
fastener torque values. For those
airplanes that were modified using the
incorrect torque values, Boeing Alert
Service Bulletin 777–55A0016, Revision
1, dated August 25, 2011, also describes
procedures for repetitive detailed
inspections for movement of the
fastener heads and the fittings along the
spar web of the elevator actuator fitting
assemblies, and eventual replacement of
the 12 bolts common to the elevator
actuator fitting and the spar web
(including related investigative and
corrective actions), which eliminates the
need for the repetitive inspections.
Related investigative actions include a
detailed inspection for fitting damage, a
detailed inspection of the composite
spar web for damage, and an ultrasonic
inspection for cracks, delaminations,
and damage. Corrective actions include
contacting Boeing and doing the repairs.
We also reviewed Boeing Service
Bulletin 777–55A0015, Revision 3,
dated November 24, 2009, which
describes the same actions as Boeing
Alert Service Bulletin 777–55A0015,
dated April 19, 2007 (which was cited
in AD 2007–26–05, Amendment 39–
15307 (72 FR 71212, December 17,
2007), as the appropriate source of
service information for the required
actions), and adds an optional
terminating action for certain inspection
requirements using Boeing Alert Service
Bulletin 777–55A0016, dated October
27, 2009.
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Differences Between Proposed Rule and
Service Bulletin
Boeing Alert Service Bulletin 777–
55A0016, Revision 1, dated August 25,
2011, specifies to contact the
manufacturer for instructions on how to
repair certain conditions, but this
proposed AD would require repairing
those conditions in one of the following
ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
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 these same
type designs.
Proposed AD Requirements
This proposed AD would retain all
requirements of AD 2007–26–05,
Amendment 39–15307 (72 FR 71212,
December 17, 2007). This proposed AD
would remove new production
airplanes from the applicability. This
proposed AD would also require
accomplishing the actions specified in
the service information described
previously.
Change to Existing AD
This proposed AD would retain all
requirements of AD 2007–26–05,
Amendment 39–15307 (72 FR 71212,
December 17, 2007). Since AD 2007–26–
05 was issued, the AD format has been
revised, and certain paragraphs have
been rearranged. As a result, the
corresponding paragraph identifier has
changed in this proposed AD, as listed
in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in existing AD 2007-26-05,
Amendment 39-15307
(72 FR 71212,
December 17, 2007))
Corresponding
requirement in this
proposed AD
Paragraph (f)
paragraph (g)
Costs of Compliance
We estimate that this proposed AD
affects 139 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
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ESTIMATED COSTS
Action
Labor cost
Inspection (retained actions from AD
2007-26-05, Amendment 39-15307
(72 FR 71212, December 17,
2007)).
Inspection (new proposed action) .......
10 work-hours × $85 per hour = $850
per inspection cycle.
$0
$850 per inspection cycle.
$118,150 per inspection
cycle.
14 work-hours × $85 per hour =
$1,190 per inspection cycle.
$0
$1,190 ..................
Up to $165,410 per inspection cycle.
We estimate the following costs to do
any necessary replacements that would
Parts cost
Cost per product
be required based on the results of the
proposed inspections. We have no way
Cost on U.S. operators
of determining the number of aircraft
that might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Fitting replacement .............................
Bolt replacement ................................
132 work-hours × $85 per hour = $11,220 ....................................................
105 work-hours × $85 per hour = $8,925 ......................................................
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.
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
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),
VerDate Mar<15>2010
16:09 Aug 02, 2012
(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
Regulatory Findings
Jkt 226001
Parts cost
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2007–26–05, Amendment 39–15307 (72
FR 71212, December 17, 2007), and
adding the following new AD:
The Boeing Company: Docket No. FAA–
2012–0803; Directorate Identifier 2011–
NM–214–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by September 17, 2012.
(b) Affected ADs
This AD supersedes AD 2007–26–05,
Amendment 39–15307 (72 FR 71212,
December 17, 2007).
(c) Applicability
This AD applies to The Boeing Company
Model 777–200, –200LR, –300, and –300ER
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$21,643
65
Cost per
product
$32,863
8,990
series airplanes; certificated in any category,
as identified in Boeing Alert Service Bulletin
777–55A0016, Revision 1, dated August 25,
2011.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a report of a
cracked left elevator actuator fitting, and the
recent determination that certain incorrect
torque values had been specified for an
alternative method of compliance intended to
terminate the requirements of the existing
AD. We are issuing this AD to detect and
correct a cracked actuator fitting or
incorrectly installed bolts to the actuator
fitting, which could lead to the elevator
becoming detached and unrestrained, and a
consequent unacceptable flutter condition
and loss of control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspections and Corrective
Actions With No Changes
This paragraph restates the inspections and
corrective actions required by paragraph (f) of
AD 2007–26–05, Amendment 39–15307 (72
FR 71212, December 17, 2007), with no
changes.
(1) Do all inspections and actions
described in paragraphs (g)(1) and (g)(2) of
this AD, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–55A0015, dated April
19, 2007; or Boeing Alert Service Bulletin
777–55A0015, Revision 3, dated November
24, 2009. As of the effective date of this AD,
Boeing Alert Service Bulletin 777–55A0015,
Revision 3, dated November 24, 2009, must
be used to accomplish the actions required
by this paragraph. At the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 777–55A0015,
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TKELLEY on DSK3SPTVN1PROD with PROPOSALS
dated April 19, 2007, except as provided by
paragraph (g)(3) of this AD, do an initial dye
penetrant or high-frequency eddy current
(HFEC) inspection for cracking of the elevator
actuator fittings, and, thereafter, do repetitive
dye penetrant, HFEC, or detailed inspections
at the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 777–55A0015, dated April 19, 2007.
(2) Before further flight, replace any fitting
found to be cracked during any inspection
required by paragraph (g)(1) of this AD with
a new fitting having the same part number,
or an optional part number as identified in
Boeing Alert Service Bulletin 777–55A0015,
dated April 19, 2007; or Boeing Service
Bulletin 777–55A0015, Revision 3, dated
November 24, 2009. Thereafter, do initial and
repetitive inspections of the replacement
fitting at the time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 777–55A0015, dated April 19, 2007.
(3) Where Boeing Alert Service Bulletin
777–55A0015, dated April 19, 2007, specifies
a compliance time after the date on that
service bulletin, this AD requires compliance
within the specified compliance time after
January 22, 2008 (the effective date of AD
2007–26–05, Amendment 39–15307 (72 FR
71212, December 17, 2007)).
(h) New Additional Actions for Certain
Airplanes
For airplanes on which the elevator
actuator fitting assemblies have been
replaced in accordance with and using the
fastener torque values specified in Boeing
Alert Service Bulletin 777–55A0016, dated
October 27, 2009: Within 180 days after the
effective date of this AD, do a detailed
inspection of the elevator actuator fitting
assemblies to detect discrepancies (including
indications of fastener head movement, and
fitting movement along the spar web), in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–55A0016, Revision 1, dated August 25,
2011.
(1) If no discrepancy is detected, do the
actions specified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD:
(i) Repeat the inspection thereafter at
intervals not to exceed 90 days or 360 flight
cycles, whichever occurs first, until the
actions specified in paragraph (h)(1)(ii) are
done.
(ii) Within 4,200 flight cycles or 750 days
after the effective date of this AD, whichever
occurs first, replace the 12 bolts common to
the elevator actuator fitting and the spar web,
and do all applicable related investigative
and corrective actions, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 777–55A0016,
Revision 1, dated August 25, 2011, except as
provided by paragraph (j) of this AD. Do all
applicable related investigative and
corrective actions before further flight. The
replacement of all 12 bolts in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 777–55A0016,
Revision 1, dated August 25, 2011,
terminates the requirements of this AD for
that fitting only.
(2) If any discrepancy is detected, before
further flight, replace the 12 bolts common to
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the elevator actuator fitting and the spar web
using new parts, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–55A0016, Revision 1, dated August 25,
2011, except as provided by paragraph (j) of
this AD. Do all applicable related
investigative and corrective actions before
further flight. The replacement of all 12 bolts
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–55A0016, Revision 1, dated August 25,
2011, terminates the requirements of this AD
for that fitting only.
(i) New Optional Replacement of Elevator
Actuator Fitting Assembly
For airplanes on which the elevator
actuator fitting assemblies have not been
replaced in accordance with Boeing Alert
Service Bulletin 777–55A0016, dated October
27, 2009: Replacement of these fitting
assemblies with new parts, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 777–55A0016,
Revision 1, dated August 25, 2011, except as
provided by paragraph (j) of this AD,
terminates the requirements of this AD.
(j) Exception
If any discrepancy or cracking is found
during any inspection required by this AD,
and Boeing Alert Service Bulletin 777–
55A0016, Revision 1, dated August 25, 2011,
specifies to contact Boeing for appropriate
action: Before further flight, repair, using a
method approved in accordance with the
procedures specified in paragraph (l) of this
AD.
(k) Credit for Previous Actions
(1) This paragraph provides credit for
inspecting and replacing the elevator actuator
fitting assemblies, as required by paragraphs
(h) and (i) of this AD, if the replacement was
performed before the effective date of this AD
using Boeing Alert Service Bulletin 777–
55A0016, dated October 27, 2009, and using
the correct torque values as specified in
Boeing Alert Service Bulletin 777–55A0016,
Revision 1, dated August 25, 2011.
(2) This paragraph provides credit for
inspecting and replacing actuator fittings, as
required by paragraph (g) of this AD, if the
inspection and replacement was performed
before the effective date of this AD using the
service bulletins specified in paragraphs
(k)(2)(i) and (k)(2)(ii) of this AD and using the
correct torque values as specified in Boeing
Alert Service Bulletin 777–55A0016,
Revision 1, dated August 25, 2011.
(i) Boeing Service Bulletin 777–55A0015,
Revision 1, dated January 31, 2008.
(ii) Boeing Service Bulletin 777–55A0015,
Revision 2, dated December 4, 2008.
(l) 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
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46343
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by The
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2007–26–05,
Amendment 39–15307 (72 FR 71212,
December 17, 2007), are not approved as
AMOCs for this AD.
(m) Related Information
(1) For more information about this AD,
contact Melanie Violette, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 985057–
3356; phone: 425–917–6422; fax: 425–917–
6590; email: melanie.violette@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,
Washington 985057–3356. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on July 25,
2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–18882 Filed 8–2–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0804; Directorate
Identifier 2012–NM–094–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)
SUMMARY:
E:\FR\FM\03AUP1.SGM
03AUP1
]]>Agencies
[Federal Register Volume 77, Number 150 (Friday, August 3, 2012)]
[Proposed Rules]
[Pages 46340-46343]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-18882]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0803; Directorate Identifier 2011-NM-214-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 777-200, -200LR, -
300, and -300ER series airplanes. The existing AD currently requires
repetitive inspections for cracking of the elevator actuator fittings.
Since we issued that AD, the manufacturer has developed a modification
that was approved as an optional terminating action to the currently
required repetitive inspections. We have been advised that the
modification procedures include certain incorrect torque values. This
proposed AD would require, for previously modified airplanes,
repetitive inspections for movement of the fittings or fastener heads,
and eventual replacement of certain bolts (including related
investigative and corrective actions if necessary). For all airplanes,
this replacement, with corrected torque values, would terminate the
requirements of the AD. This proposed AD would also remove certain
airplanes from the applicability. We are proposing this AD to detect
and correct a cracked actuator fitting or incorrectly installed bolts
to the actuator fitting, which could lead to the elevator becoming
detached and unrestrained, and a consequent unacceptable flutter
condition and loss of control of the airplane.
DATES: We must receive comments on this proposed AD by September 17,
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,
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: Melanie Violette, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 985057-3356; phone: 425-917-6422;
[[Page 46341]]
fax: 425-917-6590; email: melanie.violette@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-2012-0803;
Directorate Identifier 2011-NM-214-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 December 10, 2007, we issued AD 2007-26-05, Amendment 39-15307
(72 FR 71212, December 17, 2007), for all Boeing Model 777-200, -200LR,
-300, and -300ER series airplanes. That AD requires initial and
repetitive inspections for cracking of the elevator actuator fittings,
and replacement of any cracked fitting with a new fitting. That AD
resulted from a report of a cracked left elevator actuator fitting. We
issued that AD to detect and correct a cracked actuator fitting, which
could detach from the elevator and lead to an unrestrained elevator and
an unacceptable flutter condition, and consequent loss of airplane
control.
Actions Since Existing AD Was Issued
The preamble to AD 2007-26-05, Amendment 39-15307 (72 FR 71212,
December 17, 2007), specifies that we consider the requirements
``interim action'' and that the manufacturer is developing a
modification to address the unsafe condition. AD 2007-26-05 also
explains that we might consider further rulemaking if a modification is
developed, approved, and available. The manufacturer developed such a
modification, which is specified in Boeing Alert Service Bulletin 777-
55A0016, dated October 27, 2009. We issued an alternative method of
compliance (AMOC) specifying that the optional accomplishment of the
actions specified in Boeing Alert Service Bulletin 777-55A0016, dated
October 27, 2009, terminate the requirements of AD 2007-26-05. Boeing
Alert Service Bulletin 777-55A0016, dated October 27, 2009, however,
specified incorrect torque values for the BACB30NR4K6 and BACB30NR4K7
bolts, which could recreate the original unsafe condition. We have thus
determined that further rulemaking is necessary to address this
potentially reintroduced unsafe condition.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 777-55A0016, Revision 1,
dated August 25, 2011, which describes procedures for replacing the
elevator actuator fitting assemblies with new assemblies, and torquing
the bolts with correct torque values, which eliminates the need for the
repetitive inspections required by AD 2007-26-05, Amendment 39-15307
(72 FR 71212, December 17, 2007).
Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August
25, 2011, also describes additional work for airplanes that were
modified using Boeing Alert Service Bulletin 777-55A0016, dated October
27, 2009, which specified certain incorrect fastener torque values. For
those airplanes that were modified using the incorrect torque values,
Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August 25,
2011, also describes procedures for repetitive detailed inspections for
movement of the fastener heads and the fittings along the spar web of
the elevator actuator fitting assemblies, and eventual replacement of
the 12 bolts common to the elevator actuator fitting and the spar web
(including related investigative and corrective actions), which
eliminates the need for the repetitive inspections. Related
investigative actions include a detailed inspection for fitting damage,
a detailed inspection of the composite spar web for damage, and an
ultrasonic inspection for cracks, delaminations, and damage. Corrective
actions include contacting Boeing and doing the repairs.
We also reviewed Boeing Service Bulletin 777-55A0015, Revision 3,
dated November 24, 2009, which describes the same actions as Boeing
Alert Service Bulletin 777-55A0015, dated April 19, 2007 (which was
cited in AD 2007-26-05, Amendment 39-15307 (72 FR 71212, December 17,
2007), as the appropriate source of service information for the
required actions), and adds an optional terminating action for certain
inspection requirements using Boeing Alert Service Bulletin 777-
55A0016, dated October 27, 2009.
Differences Between Proposed Rule and Service Bulletin
Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August
25, 2011, specifies to contact the manufacturer for instructions on how
to repair certain conditions, but this proposed AD would require
repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2007-26-05,
Amendment 39-15307 (72 FR 71212, December 17, 2007). This proposed AD
would remove new production airplanes from the applicability. This
proposed AD would also require accomplishing the actions specified in
the service information described previously.
Change to Existing AD
This proposed AD would retain all requirements of AD 2007-26-05,
Amendment 39-15307 (72 FR 71212, December 17, 2007). Since AD 2007-26-
05 was issued, the AD format has been revised, and certain paragraphs
have been rearranged. As a result, the corresponding paragraph
identifier has changed in this proposed AD, as listed in the following
table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement in existing AD
2007[dash]26[dash]05, Amendment Corresponding requirement in
39[dash]15307 (72 FR 71212, December this proposed AD
17, 2007))
------------------------------------------------------------------------
Paragraph (f) paragraph (g)
------------------------------------------------------------------------
Costs of Compliance
We estimate that this proposed AD affects 139 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
[[Page 46342]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (retained actions from AD 10 work-hours x $85 per hour $0 $850 per inspection $118,150 per inspection cycle.
2007[dash]26[dash]05, Amendment = $850 per inspection cycle. cycle.
39[dash]15307 (72 FR 71212, December
17, 2007)).
Inspection (new proposed action)...... 14 work-hours x $85 per hour $0 $1,190.................. Up to $165,410 per inspection cycle.
= $1,190 per inspection
cycle.
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We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed
inspections. We have no way of determining the number of aircraft that
might need these replacements:
On-condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Fitting replacement........................... 132 work-hours x $85 per hour = $21,643 $32,863
$11,220.
Bolt replacement.............................. 105 work-hours x $85 per hour = $8,925 65 8,990
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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) 2007-26-05, Amendment 39-15307 (72 FR 71212, December 17, 2007),
and adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0803; Directorate Identifier
2011-NM-214-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by September 17,
2012.
(b) Affected ADs
This AD supersedes AD 2007-26-05, Amendment 39-15307 (72 FR
71212, December 17, 2007).
(c) Applicability
This AD applies to The Boeing Company Model 777-200, -200LR, -
300, and -300ER series airplanes; certificated in any category, as
identified in Boeing Alert Service Bulletin 777-55A0016, Revision 1,
dated August 25, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a report of a cracked left elevator
actuator fitting, and the recent determination that certain
incorrect torque values had been specified for an alternative method
of compliance intended to terminate the requirements of the existing
AD. We are issuing this AD to detect and correct a cracked actuator
fitting or incorrectly installed bolts to the actuator fitting,
which could lead to the elevator becoming detached and unrestrained,
and a consequent unacceptable flutter condition and loss of control
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections and Corrective Actions With No Changes
This paragraph restates the inspections and corrective actions
required by paragraph (f) of AD 2007-26-05, Amendment 39-15307 (72
FR 71212, December 17, 2007), with no changes.
(1) Do all inspections and actions described in paragraphs
(g)(1) and (g)(2) of this AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-55A0015, dated
April 19, 2007; or Boeing Alert Service Bulletin 777-55A0015,
Revision 3, dated November 24, 2009. As of the effective date of
this AD, Boeing Alert Service Bulletin 777-55A0015, Revision 3,
dated November 24, 2009, must be used to accomplish the actions
required by this paragraph. At the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
777-55A0015,
[[Page 46343]]
dated April 19, 2007, except as provided by paragraph (g)(3) of this
AD, do an initial dye penetrant or high-frequency eddy current
(HFEC) inspection for cracking of the elevator actuator fittings,
and, thereafter, do repetitive dye penetrant, HFEC, or detailed
inspections at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0015, dated
April 19, 2007.
(2) Before further flight, replace any fitting found to be
cracked during any inspection required by paragraph (g)(1) of this
AD with a new fitting having the same part number, or an optional
part number as identified in Boeing Alert Service Bulletin 777-
55A0015, dated April 19, 2007; or Boeing Service Bulletin 777-
55A0015, Revision 3, dated November 24, 2009. Thereafter, do initial
and repetitive inspections of the replacement fitting at the time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 777-55A0015, dated April 19, 2007.
(3) Where Boeing Alert Service Bulletin 777-55A0015, dated April
19, 2007, specifies a compliance time after the date on that service
bulletin, this AD requires compliance within the specified
compliance time after January 22, 2008 (the effective date of AD
2007-26-05, Amendment 39-15307 (72 FR 71212, December 17, 2007)).
(h) New Additional Actions for Certain Airplanes
For airplanes on which the elevator actuator fitting assemblies
have been replaced in accordance with and using the fastener torque
values specified in Boeing Alert Service Bulletin 777-55A0016, dated
October 27, 2009: Within 180 days after the effective date of this
AD, do a detailed inspection of the elevator actuator fitting
assemblies to detect discrepancies (including indications of
fastener head movement, and fitting movement along the spar web), in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011.
(1) If no discrepancy is detected, do the actions specified in
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD:
(i) Repeat the inspection thereafter at intervals not to exceed
90 days or 360 flight cycles, whichever occurs first, until the
actions specified in paragraph (h)(1)(ii) are done.
(ii) Within 4,200 flight cycles or 750 days after the effective
date of this AD, whichever occurs first, replace the 12 bolts common
to the elevator actuator fitting and the spar web, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 777-55A0016, Revision 1, dated August 25, 2011,
except as provided by paragraph (j) of this AD. Do all applicable
related investigative and corrective actions before further flight.
The replacement of all 12 bolts in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0016, Revision 1, dated August 25, 2011, terminates the
requirements of this AD for that fitting only.
(2) If any discrepancy is detected, before further flight,
replace the 12 bolts common to the elevator actuator fitting and the
spar web using new parts, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0016, Revision 1, dated August 25, 2011, except as provided by
paragraph (j) of this AD. Do all applicable related investigative
and corrective actions before further flight. The replacement of all
12 bolts in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 777-55A0016, Revision 1, dated August
25, 2011, terminates the requirements of this AD for that fitting
only.
(i) New Optional Replacement of Elevator Actuator Fitting Assembly
For airplanes on which the elevator actuator fitting assemblies
have not been replaced in accordance with Boeing Alert Service
Bulletin 777-55A0016, dated October 27, 2009: Replacement of these
fitting assemblies with new parts, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0016, Revision 1, dated August 25, 2011, except as provided by
paragraph (j) of this AD, terminates the requirements of this AD.
(j) Exception
If any discrepancy or cracking is found during any inspection
required by this AD, and Boeing Alert Service Bulletin 777-55A0016,
Revision 1, dated August 25, 2011, specifies to contact Boeing for
appropriate action: Before further flight, repair, using a method
approved in accordance with the procedures specified in paragraph
(l) of this AD.
(k) Credit for Previous Actions
(1) This paragraph provides credit for inspecting and replacing
the elevator actuator fitting assemblies, as required by paragraphs
(h) and (i) of this AD, if the replacement was performed before the
effective date of this AD using Boeing Alert Service Bulletin 777-
55A0016, dated October 27, 2009, and using the correct torque values
as specified in Boeing Alert Service Bulletin 777-55A0016, Revision
1, dated August 25, 2011.
(2) This paragraph provides credit for inspecting and replacing
actuator fittings, as required by paragraph (g) of this AD, if the
inspection and replacement was performed before the effective date
of this AD using the service bulletins specified in paragraphs
(k)(2)(i) and (k)(2)(ii) of this AD and using the correct torque
values as specified in Boeing Alert Service Bulletin 777-55A0016,
Revision 1, dated August 25, 2011.
(i) Boeing Service Bulletin 777-55A0015, Revision 1, dated
January 31, 2008.
(ii) Boeing Service Bulletin 777-55A0015, Revision 2, dated
December 4, 2008.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by The
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 2007-26-05, Amendment 39-15307 (72 FR
71212, December 17, 2007), are not approved as AMOCs for this AD.
(m) Related Information
(1) For more information about this AD, contact Melanie
Violette, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton,
WA 985057-3356; phone: 425-917-6422; fax: 425-917-6590; email:
melanie.violette@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, Washington 985057-3356. For information on
the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on July 25, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-18882 Filed 8-2-12; 8:45 am]
BILLING CODE 4910-13-P
