Airworthiness Directives; the Boeing Company Airplanes, 63903-63907 [2013-25134]
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Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Proposed Rules
Novel or Unusual Design Features
List of Subjects in 14 CFR Part 25
The Model EMB–550 airplane will
incorporate the following novel or
unusual design features: The design of
the electronic flight control system
incorporates normal load factor limiting
on a full-time basis that will prevent the
flight crew from inadvertently or
intentionally exceeding the positive or
negative airplane limit load factor. This
feature is considered novel and because
the current regulations do not provide
standards for maneuverability and
controllability evaluations for such
systems. Therefore, a special condition
is needed to ensure adequate
maneuverability and controllability
when using this design feature.
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
Discussion
Title 14 Code of Federal Regulations
(14 CFR) part 25 sections do not specify
requirements or policy for
demonstrating maneuver control that
impose any handling qualities
requirements beyond the design limit
structural loads. Nevertheless, some
pilots have become accustomed to the
availability of this excess maneuver
capacity in case of extreme emergency
such as upset recoveries or collision
avoidance.
As with previous fly-by-wire
airplanes, the FAA has no regulatory or
safety reason to prohibit a design for an
electronic flight control system with
load factor limiting. It is possible that
pilots accustomed to this feature feel
more freedom in commanding full-stick
displacement maneuvers because of the
following:
• Knowledge that the limit system
will protect the structure,
• Low stick force/displacement
gradients,
• Smooth transition from pilot
elevator control to limit control.
The special conditions will ensure
adequate maneuverability and
controllability when using this design
feature.
tkelley on DSK3SPTVN1PROD with PROPOSALS
Applicability
As discussed above, these special
conditions are applicable to the Model
EMB–550 airplane. Should Embraer
S.A. apply at a later date for a change
to the type certificate to include another
model incorporating the same novel or
unusual design feature, the special
conditions would apply to that model as
well.
Conclusion
This action affects only certain novel
or unusual design features on one model
of airplanes. It is not a rule of general
applicability.
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Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Proposed Special Conditions
Accordingly, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for Embraer
S.A. Model EMB–550 airplanes.
1. Flight Envelope Protection: Normal
Load Factor (g) Limiting.
To meet the intent of adequate
maneuverability and controllability
required by § 25.143(a), and in addition
to the requirements of § 25.143(a) and in
the absence of other limiting factors, the
following special conditions are
proposed based on § 25.333(b):
(a) The positive limiting load factor
must not be less than:
(1) 2.5g for the normal state of the
electronic flight control system with the
high lift devices retracted.
(2) 2.0g for the normal state of the
electronic flight control system with the
high lift devices extended.
(b) The negative limiting load factor
must be equal to or more negative than:
(1) Minus 1.0g for the normal state of
the electronic flight control system with
the high lift devices retracted.
(2) 0.0g for the normal state of the
electronic flight control system with
high lift devices extended.
(c) Maximum reachable positive load
factor wings level may be limited by the
characteristics of the electronic flight
control system or flight envelope
protections (other than load factor
protection) provided that:
(1) The required values are readily
achievable in turns, and
(2) That wings level pitch up is
satisfactory.
(d) Maximum achievable negative
load factor may be limited by the
characteristics of the electronic flight
control system or flight envelope
protections (other than load factor
protection) provided that:
(1) Pitch down responsiveness is
satisfactory, and
(2) From level flight, 0g is readily
achievable or alternatively, a
satisfactory trajectory change is readily
achievable at operational speeds. For
the FAA to consider a trajectory change
as satisfactory, the applicant should
propose and justify a pitch rate that
provides sufficient maneuvering
capability in the most critical scenarios.
(e) Compliance demonstration with
the above requirements may be
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63903
performed without ice accretion on the
airframe.
(f) These proposed special conditions
do not impose an upper bound for the
normal load factor limit, nor does it
require that the limiter exist. If the limit
is set at a value beyond the structural
design limit maneuvering load factor n
of §§ 25.333(b), 25.337(b), 25.337 (c),
there should be a very obvious positive
tactile feel built into the controller so
that it serves as a deterrent to
inadvertently exceeding the structural
limit.
Issued in Renton, Washington, on
September 6, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–25204 Filed 10–24–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0867; Directorate
Identifier 2013–NM–115–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 777–200,
–200LR, –300, and –300ER series
airplanes. This proposed AD was
prompted by reports of severe corrosion
on bonding jumpers installed on the
flight control surfaces. This proposed
AD would require repetitive bonding
jumper inspections for corrosion,
sealant disbond, and insufficient sealant
coverage, and corrective actions if
necessary. This proposed AD also
specifies an optional action of doing an
inspection for corrosion damage of the
bonding brackets, and corrective actions
if necessary, which would terminate the
repetitive inspections. For certain
airplanes, this proposed AD would also
require installing certain bonding
jumpers and related ground clips and
fasteners to the elevators, horizontal
stabilizers, rudder, and vertical fin,
removing certain bonding jumpers and
installing new bonding jumpers, and
replacing single-tabbed brackets with
two-tabbed brackets. We are proposing
this AD to detect and correct corrosion
SUMMARY:
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on bonding jumpers installed on the
flight control surfaces, which, in the
event of a lighting strike, could damage
the actuator control electronics (ACEs)
and result in the loss of the ability to
command individual flight control
surfaces or cause uncommanded motion
of individual flight control surfaces.
We must receive comments on
this proposed AD by December 9, 2013.
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 proposed 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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
FOR FURTHER INFORMATION CONTACT:
Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, Seattle Aircraft Certification
Office, FAA, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356;
phone: 425–917–6482; fax: 425–917–
6590; email: Georgios.Roussos@faa.gov.
SUPPLEMENTARY INFORMATION:
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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–
2013–0867; Directorate Identifier 2013–
NM–115–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 have received a report of severe
corrosion on 15 bonding jumpers on the
ailerons, horizontal stabilizers, and
vertical fins of six airplanes that were
approximately eight years old. We also
received a similar report on an airplane
that was approximately seven years old.
The corrosion is caused by sealant
voids, which allow moisture under the
sealant and then trap it inside.
The bonding jumpers are part of the
lightning protection ground path for the
flight control surfaces that prevent
excessive lightning energy from
traveling to the primary flight control
actuators and then to one of the four
ACEs. Corrosion damage on the bonding
jumper connections creates high
resistance bonding paths that could, in
the event of a lightning strike,
potentially expose multiple flight
control system ACEs to high voltage
transients. The excessive voltage could
cause damage to the ACEs and result in
the loss of the ability to command
individual flight control surfaces or
cause uncommanded motion of
individual flight control surfaces.
A new category 2 fay seal method has
been developed to improve the integrity
of the bonding jumper connections. This
new method creates a continuous layer
of sealant inside and outside of all
mating surfaces to keep moisture away
from the bonding surfaces and prevent
corrosion.
Relevant Service Information
We reviewed the following service
bulletins:
• Boeing Service Bulletin 777–
27A0078, Revision 1, dated April 1,
2013
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• Boeing Service Bulletin 777–
55A0010, Revision 1, dated April 17,
2001
• Boeing Service Bulletin 777–
55A0014, Revision 1, dated April 1,
2010
For information on the procedures and
compliance times, see this service
information at https://
www.regulations.gov by searching for
Docket No. FAA–2013–0867.
Other Relevant Rulemaking
This proposed AD is related to AD
2012–08–13, Amendment 39–17030 (77
FR 24357, April 24, 2012). AD 2012–08–
13 requires replacing certain singletabbed bonding brackets in the airplane
empennage with two-tabbed bonding
brackets. AD 2012–08–13 also requires,
for certain airplanes, installing new
bonding jumpers, and measuring the
resistance of the modified installation to
verify resistance is within specified
limits. AD 2012–08–13 refers to Boeing
Service Bulletin 777–55A0010, Revision
1, dated April 17, 2001; and Boeing
Service Bulletin 777–55A0014, Revision
1, dated April 1, 2010; as the
appropriate sources of service
information for accomplishing the
required actions.
This proposed AD would require
inspecting the installation of the
bonding jumpers associated with AD
2012–08–13, Amendment 39–17030 (77
FR 24357, April 24, 2012).
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 require
accomplishing the actions specified in
the service information identified
previously, except as discussed under
‘‘Differences Between the Proposed Rule
and the Service Information.’’
The phrase ‘‘corrective actions’’ might
be used in this proposed AD.
‘‘Corrective actions’’ are actions that
correct or address any condition found.
Corrective actions in an AD could
include, for example, repairs.
Difference Between the Proposed Rule
and the Service Bulletin
Boeing Service Bulletin 777–
27A0078, Revision 1, dated April 1,
2013, specifies to contact the
manufacturer for instructions on how to
repair certain conditions, but this
proposed AD would require repairing
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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.
Costs of Compliance
We estimate that this proposed AD
affects 131 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Inspection of bonding jumpers ...............
Cost on U.S.
operators
Up to $5,695 per inspection cycle.
Up to $51,358 ........
Up to $746,045 per
inspection cycle.
Up to $6,727,898.
2,668
$8,278 ....................
$1,084,418.
1,235
Up to 67 work–hours × $85 per hour =
Up to $5,695 per inspection cycle.
Up to 158 work–hours × $85 per hour =
Up to $13,430.
66 work–hours × $85 per hour = $5,610
Cost per product
37,928
Labor cost
$3,020 ....................
$395,620.
21 work-hours × $85 per hour = $1,785
Replacement of bonding brackets .........
Concurrent cost Boeing Service Bulletin
777–55A0010, Revision 1, dated April
17, 2001.
Concurrent cost Boeing Service Bulletin
777–55A0014, Revision 1, dated April
1, 2010.
We estimate the following costs to do
any necessary replacements that would
Parts cost
$0
be required based on the results of the
proposed inspection. We have no way of
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Replacement of bonding brackets .............
Up to 158 work–hours × $85 per hour = Up to $13,430 .............
We have received no definitive data
that would enable us to provide cost
estimates for certain on-condition
repairs specified in this proposed AD.
tkelley on DSK3SPTVN1PROD with PROPOSALS
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 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
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Parts cost
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 this 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:
■
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$37,928
Cost per product
Up to $51,358.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2013–0867; Directorate Identifier 2013–
NM–115–AD.
(a) Comments Due Date
We must receive comments by December 9,
2013.
(b) Affected ADs
This AD affects AD 2012–08–13,
Amendment 39–17030 (77 FR 24357, April
24, 2012).
(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 Service Bulletin 777–
27A0078, Revision 1, dated April 1, 2013.
(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 severe
corrosion on bonding jumpers installed on
the flight control surfaces. We are issuing this
AD to detect and correct corrosion on
bonding jumpers installed on the flight
control surfaces, which, in the event of a
lighting strike, could damage the actuator
control electronics (ACEs) and result in the
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loss of the ability to command individual
flight control surfaces or cause
uncommanded motion of individual flight
control surfaces.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Bonding Jumper or Bracket Inspection
At the applicable compliance time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 777–27A0078,
Revision 1, dated April 1, 2013, except as
specified in paragraphs (j)(1) and (j)(2) of this
AD: Do a general visual inspection or a
detailed inspection using a borescope, as
applicable, for corrosion, sealant disbond,
and insufficient sealant coverage of bonding
jumpers; and do all applicable corrective
actions; in accordance with Option 1, and
Option 2, as applicable, of the
Accomplishment Instructions of Boeing
Service Bulletin 777–27A0078, Revision 1,
dated April 1, 2013, except as required by
paragraph (j)(3) of this AD. Do a detailed
inspection using a borescope if the horizontal
stabilizer tips have not been removed. Do all
applicable corrective actions before further
flight. Repeat the inspection thereafter at
intervals not to exceed 48 months. Doing the
actions specified in paragraph (h)(1) of this
AD on a bonding jumper terminates the
repetitive inspections required by this
paragraph. Doing the actions specified in
paragraph (h)(2) of this AD terminates
repetitive inspections required by this
paragraph for that bonding jumper.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(h) Optional Terminating Action and
Termination of Certain Repetitive
Inspections
(1) Doing a general visual inspection or a
detailed inspection for corrosion damage of
the bonding jumper brackets, and all
applicable corrective actions; in accordance
with Option 2 of the Accomplishment
Instructions of Boeing Service Bulletin 777–
27A0078, Revision 1, dated April 1, 2013;
terminates the repetitive inspections required
by paragraph (g) of this AD. Do all applicable
corrective actions before further flight.
(2) The repetitive inspections required by
paragraph (g) of this AD are not required on
the bonding jumpers that were removed,
inspected, and replaced with new bonding
jumpers and new fasteners using the new
category 2 fay sealed direct standard ground
stud installation method, in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 777–27A0078, Revision 1,
dated April 1, 2013.
(i) Prior and Concurrent Requirements
(1) For Group 1 airplanes, as identified in
Boeing Service Bulletin 777–27A0078,
Revision 1, dated April 1, 2013: Prior to or
concurrently with accomplishing the actions
required by paragraph (g) of this AD, install
new bonding jumpers, and do resistance
measurements of the modified installation to
verify resistance is within the limits specified
in the Accomplishment Instructions of
Boeing Service Bulletin 777–55A0010,
Revision 1, dated April 17, 2001. Do the
actions in accordance with the
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Accomplishment Instructions of Boeing
Service Bulletin 777–55A0010, Revision 1,
dated April 17, 2001.
Note 1 to paragraph (i)(1) of this AD: AD
2012–08–13, Amendment 39–17030 (77 FR
24357, April 24, 2012), refers to Boeing
Service Bulletin 777–55A0010, Revision 1,
dated April 17, 2001, as the appropriate
source of service information for
accomplishing the actions specified in
paragraph (h) of AD 2012–08–13.
(2) For Group 1 and Group 2 airplanes, as
identified in Boeing Service Bulletin 777–
27A0078, Revision 1, dated April 1, 2013:
Prior to or concurrently with accomplishing
the actions required by paragraph (g) of this
AD, replace certain single-tabbed bonding
brackets in the airplane empennage with twotabbed bonding brackets, in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 777–55A0014, Revision 1,
dated April 1, 2010.
Note 2 to paragraph (i)(2) of this AD: AD
2012–08–13, Amendment 39–17030 (77 FR
24357, April 24, 2012), refers to Boeing
Service Bulletin 777–55A0014, Revision 1,
dated April 1, 2010, as the appropriate source
of service information for accomplishing the
actions specified in paragraph (g) of AD
2012–08–13.
(j) Exceptions to Service Information
(1) Where Boeing Service Bulletin 777–
27A0078, Revision 1, dated April 1, 2013,
specifies a compliance time after the
‘‘Original issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(2) The ‘‘Condition’’ column in paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 777–27A0078, Revision 1, dated
April 1, 2013, refers to a condition as of the
‘‘Original Issue date of this service bulletin.’’
This AD applies to the corresponding
condition as of the effective date of this AD.
(3) If any corrosion damage is found during
any inspection required by this AD, and
Boeing Service Bulletin 777–27A0078,
Revision 1, dated April 1, 2013, specifies to
contact Boeing for appropriate action: Before
further flight, repair the corrosion damage
using a method approved in accordance with
the procedures specified in paragraph (l) of
this AD.
(k) Credit for Previous Actions
(1) For Groups 1, 2, and 6 through 9, as
identified in Boeing Alert Service Bulletin
777–27A0078, dated September 10, 2009:
This paragraph provides credit for actions
required by paragraph (g) of this AD and the
actions specified in paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 777–27A0078, dated
September 10, 2009, which is not
incorporated by reference in this AD.
(2) For Groups 3 through 5, as identified
in Boeing Alert Service Bulletin 777–
27A0078, dated September 10, 2009: This
paragraph provides credit for actions
required by paragraph (g) of this AD, except
for the actions required for bonding jumpers
21 and 22, if those actions were performed
before the effective date of this AD using
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Sfmt 4702
Boeing Alert Service Bulletin 777–27A0078,
dated September 10, 2009, which is not
incorporated by reference in this AD. If a
check of the airplane’s maintenance records
positively determines that bonding jumpers
21 and 22 were inspected before the effective
date of this AD in accordance with Option 1
of Work Package 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–27A0078, dated September 10, 2009,
this paragraph provides credit for the actions
required by paragraph (g) of this AD for the
inspected bonding jumpers.
(3) For Groups 3 through 5, as identified
in Boeing Alert Service Bulletin 777–
27A0078, dated September 10, 2009: This
paragraph provides credit for actions
specified in paragraph (h) of this AD, if those
actions were performed before the effective
date of this AD using Boeing Alert Service
Bulletin 777–27A0078, dated September 10,
2009, which is not incorporated by reference
in this AD; provided that a check of the
airplane’s maintenance records positively
determines that bonding jumpers 21 and 22
were replaced in accordance with Option 2
of Work Package 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–27A0078, dated September 10, 2009, or
were replaced using the new Category 2 fay
sealed direct ground stud installation
method.
(4) This paragraph provides credit for
actions required by paragraph (i)(1) of this
AD if those actions were performed before
the effective date of this AD using Boeing
Alert Service Bulletin 777–55A0010, dated
October 26, 2000, which is not incorporated
by reference in this AD.
(5) This paragraph provides credit for
actions required by paragraph (i)(2) of this
AD if those actions were performed before
the effective date of this AD using Boeing
Alert Service Bulletin 777–55A0014, dated
May 8, 2008, which is not incorporated by
reference in this AD.
(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
paragraph (m) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your Principal Maintenance Inspector
or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector,
your local Flight Standards 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 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.
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(m) Related Information
(1) For more information about this AD,
Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
Seattle Aircraft Certification Office, FAA,
1601 Lind Avenue SW., Renton, Washington
98057–3356; phone: 425–917–6482; fax: 425–
917–6590; email: Georgios.Roussos@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. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on October
15, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–25134 Filed 10–24–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
the instructions for submitting
comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Costruzioni
Aeronautiche Tecnam Airworthiness
Office, Via Maiorise–81043 Capua (CE)
Italy; telephone: +39 0823 620134; fax:
+39 0823 622899; email:
m.oliva@tecnam.com or g.paduano@
tecnam.com; Internet:
www.tecnam.com/it-IT/documenti/
service-bulletins.aspx. You may review
copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
Examining the AD Docket
14 CFR Part 39
[Docket No. FAA–2013–0888; Directorate
Identifier 2013–CE–024–AD]
RIN 2120–AA64
Airworthiness Directives; Costruzioni
Aeronautiche Tecnam srl Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for
Costruzioni Aeronautiche Tecnam srl
Model P2006T airplanes. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as cracks of the nose landing
gear (NLG) lower link. We are issuing
this proposed AD to require actions to
address the unsafe condition on these
products.
tkelley on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
We must receive comments on
this proposed AD by December 9, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go
tohttps://www.regulations.gov. Follow
DATES:
VerDate Mar<15>2010
17:00 Oct 24, 2013
Jkt 232001
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
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Albert Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4119; fax: (816) 329–4090; email:
albert.mercado@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–2013–0888; Directorate Identifier
2013–CE–024–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
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
63907
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://
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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No.: 2013–
0134, dated July 2, 2013 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
During an inspection of a P2006T, a nose
landing gear (NLG) lower link was found
with two cracks. The affected NLG lower link
is part of NLG lower link assembly P/N 26–
8–1417–000.
This condition, if not detected and
corrected, could lead to NLG failure, possibly
resulting in damage to the aeroplane and
injury to the occupants.
To address this potential unsafe condition,
Costruzioni Aeronautiche Tecnam (hereafter
referred to as Tecnam) issued Service
Bulletin (SB) SB–128–CS, providing
inspection instructions. Tecnam also
developed an improved NLG lower link
assembly with P/N 26–8–8000–000, which
can be installed in service by
accomplishment of Tecnam SB–104–CS.
For the reasons described above, this AD
requires, for aeroplanes equipped with NLG
lower link assembly P/N 26–8–1417–000, a
one-time inspection of the NLG lower link
and, depending on findings, accomplishment
of the applicable corrective action. This AD
also requires installation of the improved
NLG lower link assembly P/N 26–8–8000–
000.
You may obtain further information by
examining the MCAI on the Internet at
https://www.regulations.gov by searching
for and locating it in Docket No. FAA–
2013–0888.
Relevant Service Information
Costruzioni Aeronautiche Tecnam srl
issued Service Bulletin No. SB 104–CS,
Edition 2, Revision 1, dated March 28,
2013 (now superseded); Service Bulletin
No. SB 128–CS, Revision 0, dated May
15, 2013; Job Card 442, Revision 1,
dated February 11, 2013; Job Card 468,
dated October 12, 2012; and Job Card
528, Revision 1, dated April 2, 2013.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
E:\FR\FM\25OCP1.SGM
25OCP1
Agencies
[Federal Register Volume 78, Number 207 (Friday, October 25, 2013)]
[Proposed Rules]
[Pages 63903-63907]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25134]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0867; Directorate Identifier 2013-NM-115-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 adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 777-200, -200LR, -300, and -300ER
series airplanes. This proposed AD was prompted by reports of severe
corrosion on bonding jumpers installed on the flight control surfaces.
This proposed AD would require repetitive bonding jumper inspections
for corrosion, sealant disbond, and insufficient sealant coverage, and
corrective actions if necessary. This proposed AD also specifies an
optional action of doing an inspection for corrosion damage of the
bonding brackets, and corrective actions if necessary, which would
terminate the repetitive inspections. For certain airplanes, this
proposed AD would also require installing certain bonding jumpers and
related ground clips and fasteners to the elevators, horizontal
stabilizers, rudder, and vertical fin, removing certain bonding jumpers
and installing new bonding jumpers, and replacing single-tabbed
brackets with two-tabbed brackets. We are proposing this AD to detect
and correct corrosion
[[Page 63904]]
on bonding jumpers installed on the flight control surfaces, which, in
the event of a lighting strike, could damage the actuator control
electronics (ACEs) and result in the loss of the ability to command
individual flight control surfaces or cause uncommanded motion of
individual flight control surfaces.
DATES: We must receive comments on this proposed AD by December 9,
2013.
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, 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: Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, Seattle Aircraft Certification
Office, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356;
phone: 425-917-6482; fax: 425-917-6590; email:
Georgios.Roussos@faa.gov.
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-2013-0867;
Directorate Identifier 2013-NM-115-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 have received a report of severe corrosion on 15 bonding jumpers
on the ailerons, horizontal stabilizers, and vertical fins of six
airplanes that were approximately eight years old. We also received a
similar report on an airplane that was approximately seven years old.
The corrosion is caused by sealant voids, which allow moisture under
the sealant and then trap it inside.
The bonding jumpers are part of the lightning protection ground
path for the flight control surfaces that prevent excessive lightning
energy from traveling to the primary flight control actuators and then
to one of the four ACEs. Corrosion damage on the bonding jumper
connections creates high resistance bonding paths that could, in the
event of a lightning strike, potentially expose multiple flight control
system ACEs to high voltage transients. The excessive voltage could
cause damage to the ACEs and result in the loss of the ability to
command individual flight control surfaces or cause uncommanded motion
of individual flight control surfaces.
A new category 2 fay seal method has been developed to improve the
integrity of the bonding jumper connections. This new method creates a
continuous layer of sealant inside and outside of all mating surfaces
to keep moisture away from the bonding surfaces and prevent corrosion.
Relevant Service Information
We reviewed the following service bulletins:
Boeing Service Bulletin 777-27A0078, Revision 1, dated April
1, 2013
Boeing Service Bulletin 777-55A0010, Revision 1, dated April
17, 2001
Boeing Service Bulletin 777-55A0014, Revision 1, dated April
1, 2010
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for
Docket No. FAA-2013-0867.
Other Relevant Rulemaking
This proposed AD is related to AD 2012-08-13, Amendment 39-17030
(77 FR 24357, April 24, 2012). AD 2012-08-13 requires replacing certain
single-tabbed bonding brackets in the airplane empennage with two-
tabbed bonding brackets. AD 2012-08-13 also requires, for certain
airplanes, installing new bonding jumpers, and measuring the resistance
of the modified installation to verify resistance is within specified
limits. AD 2012-08-13 refers to Boeing Service Bulletin 777-55A0010,
Revision 1, dated April 17, 2001; and Boeing Service Bulletin 777-
55A0014, Revision 1, dated April 1, 2010; as the appropriate sources of
service information for accomplishing the required actions.
This proposed AD would require inspecting the installation of the
bonding jumpers associated with AD 2012-08-13, Amendment 39-17030 (77
FR 24357, April 24, 2012).
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 require accomplishing the actions specified
in the service information identified previously, except as discussed
under ``Differences Between the Proposed Rule and the Service
Information.''
The phrase ``corrective actions'' might be used in this proposed
AD. ``Corrective actions'' are actions that correct or address any
condition found. Corrective actions in an AD could include, for
example, repairs.
Difference Between the Proposed Rule and the Service Bulletin
Boeing Service Bulletin 777-27A0078, Revision 1, dated April 1,
2013, specifies to contact the manufacturer for instructions on how to
repair certain conditions, but this proposed AD would require repairing
[[Page 63905]]
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.
Costs of Compliance
We estimate that this proposed AD affects 131 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection of bonding jumpers.. Up to 67 work-hours x $0 Up to $5,695 per Up to $746,045 per
$85 per hour = Up to inspection cycle. inspection cycle.
$5,695 per inspection
cycle.
Replacement of bonding brackets Up to 158 work-hours x 37,928 Up to $51,358..... Up to $6,727,898.
$85 per hour = Up to
$13,430.
Concurrent cost Boeing Service 66 work-hours x $85 per 2,668 $8,278............ $1,084,418.
Bulletin 777-55A0010, Revision hour = $5,610.
1, dated April 17, 2001.
Concurrent cost Boeing Service 21 work-hours x $85 per 1,235 $3,020............ $395,620.
Bulletin 777-55A0014, Revision hour = $1,785.
1, dated April 1, 2010.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement of bonding brackets....... Up to 158 work-hours x $37,928 Up to $51,358.
$85 per hour = Up to
$13,430.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for certain on-condition repairs specified in this
proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We 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 this 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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2013-0867; Directorate Identifier
2013-NM-115-AD.
(a) Comments Due Date
We must receive comments by December 9, 2013.
(b) Affected ADs
This AD affects AD 2012-08-13, Amendment 39-17030 (77 FR 24357,
April 24, 2012).
(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 Service Bulletin 777-27A0078, Revision 1, dated
April 1, 2013.
(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 severe corrosion on bonding
jumpers installed on the flight control surfaces. We are issuing
this AD to detect and correct corrosion on bonding jumpers installed
on the flight control surfaces, which, in the event of a lighting
strike, could damage the actuator control electronics (ACEs) and
result in the
[[Page 63906]]
loss of the ability to command individual flight control surfaces or
cause uncommanded motion of individual flight control surfaces.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Bonding Jumper or Bracket Inspection
At the applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 777-27A0078, Revision 1,
dated April 1, 2013, except as specified in paragraphs (j)(1) and
(j)(2) of this AD: Do a general visual inspection or a detailed
inspection using a borescope, as applicable, for corrosion, sealant
disbond, and insufficient sealant coverage of bonding jumpers; and
do all applicable corrective actions; in accordance with Option 1,
and Option 2, as applicable, of the Accomplishment Instructions of
Boeing Service Bulletin 777-27A0078, Revision 1, dated April 1,
2013, except as required by paragraph (j)(3) of this AD. Do a
detailed inspection using a borescope if the horizontal stabilizer
tips have not been removed. Do all applicable corrective actions
before further flight. Repeat the inspection thereafter at intervals
not to exceed 48 months. Doing the actions specified in paragraph
(h)(1) of this AD on a bonding jumper terminates the repetitive
inspections required by this paragraph. Doing the actions specified
in paragraph (h)(2) of this AD terminates repetitive inspections
required by this paragraph for that bonding jumper.
(h) Optional Terminating Action and Termination of Certain Repetitive
Inspections
(1) Doing a general visual inspection or a detailed inspection
for corrosion damage of the bonding jumper brackets, and all
applicable corrective actions; in accordance with Option 2 of the
Accomplishment Instructions of Boeing Service Bulletin 777-27A0078,
Revision 1, dated April 1, 2013; terminates the repetitive
inspections required by paragraph (g) of this AD. Do all applicable
corrective actions before further flight.
(2) The repetitive inspections required by paragraph (g) of this
AD are not required on the bonding jumpers that were removed,
inspected, and replaced with new bonding jumpers and new fasteners
using the new category 2 fay sealed direct standard ground stud
installation method, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777-27A0078, Revision 1,
dated April 1, 2013.
(i) Prior and Concurrent Requirements
(1) For Group 1 airplanes, as identified in Boeing Service
Bulletin 777-27A0078, Revision 1, dated April 1, 2013: Prior to or
concurrently with accomplishing the actions required by paragraph
(g) of this AD, install new bonding jumpers, and do resistance
measurements of the modified installation to verify resistance is
within the limits specified in the Accomplishment Instructions of
Boeing Service Bulletin 777-55A0010, Revision 1, dated April 17,
2001. Do the actions in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777-55A0010, Revision 1,
dated April 17, 2001.
Note 1 to paragraph (i)(1) of this AD: AD 2012-08-13, Amendment
39-17030 (77 FR 24357, April 24, 2012), refers to Boeing Service
Bulletin 777-55A0010, Revision 1, dated April 17, 2001, as the
appropriate source of service information for accomplishing the
actions specified in paragraph (h) of AD 2012-08-13.
(2) For Group 1 and Group 2 airplanes, as identified in Boeing
Service Bulletin 777-27A0078, Revision 1, dated April 1, 2013: Prior
to or concurrently with accomplishing the actions required by
paragraph (g) of this AD, replace certain single-tabbed bonding
brackets in the airplane empennage with two-tabbed bonding brackets,
in accordance with the Accomplishment Instructions of Boeing Service
Bulletin 777-55A0014, Revision 1, dated April 1, 2010.
Note 2 to paragraph (i)(2) of this AD: AD 2012-08-13, Amendment
39-17030 (77 FR 24357, April 24, 2012), refers to Boeing Service
Bulletin 777-55A0014, Revision 1, dated April 1, 2010, as the
appropriate source of service information for accomplishing the
actions specified in paragraph (g) of AD 2012-08-13.
(j) Exceptions to Service Information
(1) Where Boeing Service Bulletin 777-27A0078, Revision 1, dated
April 1, 2013, specifies a compliance time after the ``Original
issue date of this service bulletin,'' this AD requires compliance
within the specified compliance time after the effective date of
this AD.
(2) The ``Condition'' column in paragraph 1.E., ``Compliance,''
of Boeing Service Bulletin 777-27A0078, Revision 1, dated April 1,
2013, refers to a condition as of the ``Original Issue date of this
service bulletin.'' This AD applies to the corresponding condition
as of the effective date of this AD.
(3) If any corrosion damage is found during any inspection
required by this AD, and Boeing Service Bulletin 777-27A0078,
Revision 1, dated April 1, 2013, specifies to contact Boeing for
appropriate action: Before further flight, repair the corrosion
damage using a method approved in accordance with the procedures
specified in paragraph (l) of this AD.
(k) Credit for Previous Actions
(1) For Groups 1, 2, and 6 through 9, as identified in Boeing
Alert Service Bulletin 777-27A0078, dated September 10, 2009: This
paragraph provides credit for actions required by paragraph (g) of
this AD and the actions specified in paragraph (h) of this AD, if
those actions were performed before the effective date of this AD
using Boeing Alert Service Bulletin 777-27A0078, dated September 10,
2009, which is not incorporated by reference in this AD.
(2) For Groups 3 through 5, as identified in Boeing Alert
Service Bulletin 777-27A0078, dated September 10, 2009: This
paragraph provides credit for actions required by paragraph (g) of
this AD, except for the actions required for bonding jumpers 21 and
22, if those actions were performed before the effective date of
this AD using Boeing Alert Service Bulletin 777-27A0078, dated
September 10, 2009, which is not incorporated by reference in this
AD. If a check of the airplane's maintenance records positively
determines that bonding jumpers 21 and 22 were inspected before the
effective date of this AD in accordance with Option 1 of Work
Package 3 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 777-27A0078, dated September 10, 2009, this paragraph
provides credit for the actions required by paragraph (g) of this AD
for the inspected bonding jumpers.
(3) For Groups 3 through 5, as identified in Boeing Alert
Service Bulletin 777-27A0078, dated September 10, 2009: This
paragraph provides credit for actions specified in paragraph (h) of
this AD, if those actions were performed before the effective date
of this AD using Boeing Alert Service Bulletin 777-27A0078, dated
September 10, 2009, which is not incorporated by reference in this
AD; provided that a check of the airplane's maintenance records
positively determines that bonding jumpers 21 and 22 were replaced
in accordance with Option 2 of Work Package 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-27A0078, dated
September 10, 2009, or were replaced using the new Category 2 fay
sealed direct ground stud installation method.
(4) This paragraph provides credit for actions required by
paragraph (i)(1) of this AD if those actions were performed before
the effective date of this AD using Boeing Alert Service Bulletin
777-55A0010, dated October 26, 2000, which is not incorporated by
reference in this AD.
(5) This paragraph provides credit for actions required by
paragraph (i)(2) of this AD if those actions were performed before
the effective date of this AD using Boeing Alert Service Bulletin
777-55A0014, dated May 8, 2008, which is not incorporated by
reference in this AD.
(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 paragraph (m) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards 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 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.
[[Page 63907]]
(m) Related Information
(1) For more information about this AD, Georgios Roussos,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, Seattle
Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; phone: 425-917-6482; fax: 425-917-6590;
email: Georgios.Roussos@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. For information on the
availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on October 15, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-25134 Filed 10-24-13; 8:45 am]
BILLING CODE 4910-13-P