Airworthiness Directives; The Boeing Company Airplanes, 11725-11728 [2014-04568]
Download as PDF
Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules
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:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
Alpha Aviation Concept Limited: Docket No.
FAA–2014–0130; Directorate Identifier
2014–CE–005–AD.
(a) Comments Due Date
We must receive comments by April 17,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Alpha Aviation
Concept Limited Model R2160 airplanes,
serial numbers 001 through 378, certificated
in any category.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(d) Subject
Air Transport Association of America
(ATA) Code 74: Ignition.
(e) Reason
This AD was prompted by 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 the metal
screen shield over the ignition switch may
ground out the ignition terminals. We are
issuing this AD to prevent the ignition switch
metal screen from grounding out the ignition
switch terminals, which could cause the
engine to shut down.
VerDate Mar<15>2010
16:22 Feb 28, 2014
Jkt 232001
(f) Actions and Compliance
Unless already done, do the actions in
paragraphs (f)(1) through (f)(3) of this AD:
(1) Within the next 50 hours time-inservice after the effective date of this AD or
within the next 3 months after the effective
date of this AD, whichever occurs first,
inspect the airplane ignition switch for the
presence of a metal screen shield. Do the
inspection following the Accomplishment
Instructions in Alpha Aviation Service
Bulletin AA–SB–24–002, Revision 0, dated
January 2014.
(2) If a metal screen is found during the
inspection required in paragraph (f)(1) of this
AD, before further flight, modify or replace
the ignition switch following the
Accomplishment Instructions in Alpha
Aviation Service Bulletin AA–SB–24–002,
Revision 0, dated January 2014.
(3) As of the effective date of this AD, do
not install an ignition switch with a metal
screen shield.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4123; fax: (816)
329–4090; email: karl.schletzbaum@faa.gov.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(h) Related Information
Refer to MCAI Civil Aviation Authority
(CAA) AD DCA/R2000/42, dated January 29,
2014, for related information. You may
examine the MCAI on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2014–0130. For
service information related to this AD,
contact Alpha Aviation, 59 Hautapu Road,
RD 1, Cambridge 3493, New Zealand;
telephone: +64 7 827 0528; fax: +64 7 929
2878; Internet: www.alphaaviation.co.nz.
You may review this 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.
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
11725
Issued in Kansas City, Missouri, on
February 21, 2014.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04549 Filed 2–28–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0128; Directorate
Identifier 2013–NM–133–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for The
Boeing Company Model airplanes
equipped with Rolls-Royce Trent 800
series engines. This proposed AD was
prompted by reports of in-flight
separation of the aft plug from the
forward plug, which are the two parts of
the turbine exhaust plug assembly. This
proposed AD would require installation
of a serviceable turbine exhaust plug
assembly (for certain airplanes), and a
general visual inspection (for certain
airplanes) to determine the diameter of
the bolt used at the forward and aft plug
interface, and applicable corrective
actions. We are proposing this AD to
prevent separation of the forward plug
from the aft plug of the turbine exhaust
plug assembly, which could result in
parts departing the airplane and hitting
the empennage or hitting a person on
the ground, and destabilizing the
airplane during a critical flight phase;
parts remaining on a runway could
cause damage to another airplane.
DATES: We must receive comments on
this proposed AD by April 17, 2014.
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
E:\FR\FM\03MRP1.SGM
03MRP1
11726
Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules
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 view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Kevin Nguyen, Aerospace Engineer,
Propulsion Branch, ANM–140S, Seattle
Aircraft Certification Office (ACO) FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: (425) 917–6501;
fax: (425) 917–6590; email:
kevin.nguyen@faa.gov.
Discussion
We received reports of in-flight
separation of the aft plug from the
forward plug, which are the two parts of
the turbine exhaust plug assembly. A
subsequent investigation showed that
some of the interface bolts were found
loose or missing. The turbine exhaust
plug assembly was sent for analysis and
it was found that the remaining bolts
had less than the necessary minimum
run-on torque value. It was also found
that the operator of the analyzed turbine
exhaust plug assembly had
disassembled it a minimum of three
times during maintenance actions.
Repeated assembly and disassembly
causes the locking property of the nut
on the nutplate to wear out and
subsequently let the bolts become loose
or removed in service. This condition, if
not corrected, could result in parts
departing the airplane and hitting the
empennage or hitting a person on the
ground, and destabilizing the airplane
during a critical flight phase; parts
remaining on a runway could cause
damage to another airplane.
Relevant Service Information
We reviewed Boeing Special
Attention Service Bulletin 777–78–
0051, Revision 3, dated August 23,
2012. For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
Docket No. FAA 2014–0128.
FAA’s Determination
Comments Invited
mstockstill on DSK4VPTVN1PROD with PROPOSALS
SUPPLEMENTARY INFORMATION:
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.
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–
2014–0128; Directorate Identifier 2013–
NM–133–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.
VerDate Mar<15>2010
16:22 Feb 28, 2014
Jkt 232001
Proposed AD Requirements
This proposed AD would require
installation of a serviceable turbine
exhaust plug assembly (for certain
airplanes), and a general visual
inspection (for certain airplanes) to
determine the diameter of the bolt used
at the forward and aft plug interface,
and applicable corrective actions.
The phrase ‘‘corrective actions’’ is
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.
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
Differences Between the Proposed AD
and the Service Information
The applicability of the proposed AD
and the effectivity of Boeing Special
Attention Service Bulletin 777–78–
0051, Revision 3, dated August 23,
2012, both include Model 777 airplanes
equipped with Rolls-Royce Trent 800
series engines. Boeing Special Attention
Service Bulletin 777–78–0051, Revision
3, dated August 23, 2012, however, is
further limited to airplanes with line
numbers before line position 470.
Because we have determined that these
engines are interchangeable among the
Model 777 airplane fleet, this proposed
AD would apply to all line positions of
Model 777 airplanes equipped with
Rolls-Royce Trent 800 engines, and
would prohibit installation of nonserviceable turbine exhaust plug
assemblies on any affected airplane.
Boeing Special Attention Service
Bulletin 777–78–0051, Revision 3, dated
August 23, 2012, does not specify a
compliance time for accomplishing one
of the corrective actions. In Table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 777–
78–0051, Revision 3, dated August 23,
2012, the condition ‘‘Only 1⁄4 inch
diameter bolts are found installed at all
33 locations forward and aft plug
interface’’ has a corrective action to
‘‘reidentify the forward and aft plug’’
with a compliance time of ‘‘none.’’
However, in paragraph (g)(2) of this
proposed AD, the compliance time is
‘‘before further flight’’ for doing all
applicable corrective actions, which
includes reidentifying the forward and
aft plug.
Boeing Special Attention Service
Bulletin 777–78–0051, Revision 3, dated
August 23, 2012, 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.
Costs of Compliance
We estimate that this proposed AD
affects 35 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
E:\FR\FM\03MRP1.SGM
03MRP1
11727
Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules
ESTIMATED COSTS
Action
Labor cost
Installation ...............................
General visual inspection .......
5 work-hours × $85 per hour = $425 .....................................
2 work-hours × $85 per hour = $170 .....................................
We estimate the following costs to do
any necessary replacements that would
Cost per
product
Parts cost
be required based on the results of the
proposed inspection. We have no way of
$0
0
Cost on U.S.
operators
$425
170
$14,875
5,950
determining the number of aircraft that
might need this replacement:
ON-CONDITION COSTS
Action
Replacement (replacing the
inch bolts).
Labor cost
⁄
3 16
inch bolts with
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 proposed
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.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
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,
VerDate Mar<15>2010
16:22 Feb 28, 2014
Jkt 232001
⁄
14
5 work-hours × $85 per hour = $425 ...........................
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:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2014–0128; Directorate Identifier 2013–
NM–133–AD.
(a) Comments Due Date
We must receive comments by April 17,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 777–200, –200LR, –300, –300ER, and
777F series airplanes; certificated in any
category; equipped with Rolls-Royce Trent
800 series engines.
(d) Subject
Air Transport Association (ATA) of
America Code 78, Engine Exhaust.
(e) Unsafe Condition
This AD was prompted by reports of inflight separation of the aft plug from the
forward plug, which are the two parts of the
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
$0
$425
turbine exhaust plug assembly. We are
issuing this AD to prevent separation of the
forward plug from the aft plug of the turbine
exhaust plug assembly, which could result in
parts departing the airplane and hitting the
empennage or hitting a person on the ground,
and destabilizing the airplane during a
critical flight phase; parts remaining on a
runway could cause damage to another
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Installation and General Visual
Inspection
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
Cost per
product
Parts cost
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 777–78–
0051, Revision 3, dated August 23, 2012,
except as provided by paragraph (i) of this
AD, do the applicable actions specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD,
in accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–78–0051, Revision 3,
dated August 23, 2012.
(1) For airplanes identified as Group 1,
Configuration 1, in Boeing Special Attention
Service Bulletin 777–78–0051, Revision 3,
dated August 23, 2012: Install a serviceable
turbine exhaust plug assembly.
(2) For airplanes identified as Group 1,
Configurations 2 and 3, in Boeing Special
Attention Service Bulletin 777–78–0051,
Revision 3, dated August 23, 2012: Do a
general visual inspection to determine the
diameter of the bolt used at the forward and
aft plug interface, and before further flight,
do all applicable corrective actions.
(3) For airplanes listed in paragraph (c) of
this AD that are not listed in the ‘‘Effectivity’’
section of Boeing Special Attention Service
Bulletin 777–78–0051, Revision 3, dated
August 23, 2012: Do a general visual
inspection to determine if a serviceable
turbine exhaust plug assembly is installed. If
a serviceable turbine exhaust plug assembly
is not installed, before further flight, install
a serviceable turbine exhaust plug assembly.
E:\FR\FM\03MRP1.SGM
03MRP1
11728
Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules
(h) Definition of Serviceable Assembly
For purposes of this AD, an acceptable
serviceable turbine exhaust plug assembly
must meet the conditions specified in
paragraph (h)(1) or (h)(2) of this AD.
(1) A new assembly with part number
314W5520–22.
(2) A serviceable assembly as defined in
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–78–
0051, Revision 3, dated August 23, 2012;
except, for any assembly on which the
actions specified in Part 2 or Part 3 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–78–
0051, Revision 3, dated August 23, 2012, are
done, and Boeing Special Attention Service
Bulletin 777–78–0051, Revision 3, dated
August 23, 2012, specifies to contact Boeing
for repair instructions, this AD requires
repair before further flight using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
Lind Avenue SW., Renton, Washington
98057–3356; phone: (425) 917–6501; fax:
(425) 917–6590; email: kevin.nguyen@
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 view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(i) Exception to Service Information
Specifications
Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
777–78–0051, Revision 3, dated August 23,
2012, specifies a compliance time ‘‘after the
Revision 3 date of this service bulletin,’’ this
AD requires compliance within the
applicable time after the effective date of this
AD.
BILLING CODE 4910–13–P
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(j) Parts Installation Limitation
As of the effective date of this AD, only a
serviceable turbine exhaust plug assembly
may be installed on any airplane.
(k) 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 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.
(l) Related Information
(1) For more information about this AD,
contact Kevin Nguyen, Aerospace Engineer,
Propulsion Branch, ANM–140S, Seattle
Aircraft Certification Office (ACO) FAA, 1601
VerDate Mar<15>2010
16:22 Feb 28, 2014
Jkt 232001
Issued in Renton, Washington, on February
24, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04568 Filed 2–28–14; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
[Docket No. FAA–2014–0122; Directorate
Identifier 2014–NM–002–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–600,
–700, –700C, –800, and –900 series
airplanes. This proposed AD was
prompted by reports in which a single,
undetected, erroneous radio altimeter
output caused the autothrottle to enter
landing flare retard mode prematurely
on approach. This proposed AD would
require removing certain autothrottle
computers and installing a new or
reworked autothrottle computer. We are
proposing this AD to prevent a single,
undetected, erroneous radio altimeter
output from causing premature
autothrottle landing flare retard and
subsequent loss of automatic speed
control, which could result in loss of
control of the airplane.
DATES: We must receive comments on
this proposed AD by April 17, 2014.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
PO 00000
Frm 00015
Fmt 4702
• 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 view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA 98057. For information on
the availability of this material at the
FAA, call 425–227–2112.
Sfmt 4702
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0122; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6418;
fax: 425–917–6590; email:
marie.hogestad@faa.gov.
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–
2014–0122; Directorate Identifier 2014–
NM–002–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
E:\FR\FM\03MRP1.SGM
03MRP1
Agencies
[Federal Register Volume 79, Number 41 (Monday, March 3, 2014)]
[Proposed Rules]
[Pages 11725-11728]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04568]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0128; Directorate Identifier 2013-NM-133-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 The
Boeing Company Model airplanes equipped with Rolls-Royce Trent 800
series engines. This proposed AD was prompted by reports of in-flight
separation of the aft plug from the forward plug, which are the two
parts of the turbine exhaust plug assembly. This proposed AD would
require installation of a serviceable turbine exhaust plug assembly
(for certain airplanes), and a general visual inspection (for certain
airplanes) to determine the diameter of the bolt used at the forward
and aft plug interface, and applicable corrective actions. We are
proposing this AD to prevent separation of the forward plug from the
aft plug of the turbine exhaust plug assembly, which could result in
parts departing the airplane and hitting the empennage or hitting a
person on the ground, and destabilizing the airplane during a critical
flight phase; parts remaining on a runway could cause damage to another
airplane.
DATES: We must receive comments on this proposed AD by April 17, 2014.
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
[[Page 11726]]
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 view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Kevin Nguyen, Aerospace Engineer,
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office
(ACO) FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425)
917-6501; fax: (425) 917-6590; email: kevin.nguyen@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-2014-0128;
Directorate Identifier 2013-NM-133-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We received reports of in-flight separation of the aft plug from
the forward plug, which are the two parts of the turbine exhaust plug
assembly. A subsequent investigation showed that some of the interface
bolts were found loose or missing. The turbine exhaust plug assembly
was sent for analysis and it was found that the remaining bolts had
less than the necessary minimum run-on torque value. It was also found
that the operator of the analyzed turbine exhaust plug assembly had
disassembled it a minimum of three times during maintenance actions.
Repeated assembly and disassembly causes the locking property of the
nut on the nutplate to wear out and subsequently let the bolts become
loose or removed in service. This condition, if not corrected, could
result in parts departing the airplane and hitting the empennage or
hitting a person on the ground, and destabilizing the airplane during a
critical flight phase; parts remaining on a runway could cause damage
to another airplane.
Relevant Service Information
We reviewed Boeing Special Attention Service Bulletin 777-78-0051,
Revision 3, dated August 23, 2012. For information on the procedures
and compliance times, see this service information at https://www.regulations.gov by searching for Docket No. FAA 2014-0128.
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 require installation of a serviceable
turbine exhaust plug assembly (for certain airplanes), and a general
visual inspection (for certain airplanes) to determine the diameter of
the bolt used at the forward and aft plug interface, and applicable
corrective actions.
The phrase ``corrective actions'' is 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.
Differences Between the Proposed AD and the Service Information
The applicability of the proposed AD and the effectivity of Boeing
Special Attention Service Bulletin 777-78-0051, Revision 3, dated
August 23, 2012, both include Model 777 airplanes equipped with Rolls-
Royce Trent 800 series engines. Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, however, is
further limited to airplanes with line numbers before line position
470. Because we have determined that these engines are interchangeable
among the Model 777 airplane fleet, this proposed AD would apply to all
line positions of Model 777 airplanes equipped with Rolls-Royce Trent
800 engines, and would prohibit installation of non-serviceable turbine
exhaust plug assemblies on any affected airplane.
Boeing Special Attention Service Bulletin 777-78-0051, Revision 3,
dated August 23, 2012, does not specify a compliance time for
accomplishing one of the corrective actions. In Table 2 of paragraph
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-
78-0051, Revision 3, dated August 23, 2012, the condition ``Only \1/4\
inch diameter bolts are found installed at all 33 locations forward and
aft plug interface'' has a corrective action to ``reidentify the
forward and aft plug'' with a compliance time of ``none.'' However, in
paragraph (g)(2) of this proposed AD, the compliance time is ``before
further flight'' for doing all applicable corrective actions, which
includes reidentifying the forward and aft plug.
Boeing Special Attention Service Bulletin 777-78-0051, Revision 3,
dated August 23, 2012, 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.
Costs of Compliance
We estimate that this proposed AD affects 35 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 11727]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Installation....................... 5 work-hours x $85 per hour $0 $425 $14,875
= $425.
General visual inspection.......... 2 work-hours x $85 per hour 0 170 5,950
= $170.
----------------------------------------------------------------------------------------------------------------
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
this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement (replacing the \3/16\ inch bolts 5 work-hours x $85 per hour = $0 $425
with \1/4\ inch bolts). $425.
----------------------------------------------------------------------------------------------------------------
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 proposed 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-2014-0128; Directorate Identifier
2013-NM-133-AD.
(a) Comments Due Date
We must receive comments by April 17, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes; certificated in any
category; equipped with Rolls-Royce Trent 800 series engines.
(d) Subject
Air Transport Association (ATA) of America Code 78, Engine
Exhaust.
(e) Unsafe Condition
This AD was prompted by reports of in-flight separation of the
aft plug from the forward plug, which are the two parts of the
turbine exhaust plug assembly. We are issuing this AD to prevent
separation of the forward plug from the aft plug of the turbine
exhaust plug assembly, which could result in parts departing the
airplane and hitting the empennage or hitting a person on the
ground, and destabilizing the airplane during a critical flight
phase; parts remaining on a runway could cause damage to another
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Installation and General Visual Inspection
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 3, dated August 23, 2012, except as provided by
paragraph (i) of this AD, do the applicable actions specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in accordance with
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012.
(1) For airplanes identified as Group 1, Configuration 1, in
Boeing Special Attention Service Bulletin 777-78-0051, Revision 3,
dated August 23, 2012: Install a serviceable turbine exhaust plug
assembly.
(2) For airplanes identified as Group 1, Configurations 2 and 3,
in Boeing Special Attention Service Bulletin 777-78-0051, Revision
3, dated August 23, 2012: Do a general visual inspection to
determine the diameter of the bolt used at the forward and aft plug
interface, and before further flight, do all applicable corrective
actions.
(3) For airplanes listed in paragraph (c) of this AD that are
not listed in the ``Effectivity'' section of Boeing Special
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23,
2012: Do a general visual inspection to determine if a serviceable
turbine exhaust plug assembly is installed. If a serviceable turbine
exhaust plug assembly is not installed, before further flight,
install a serviceable turbine exhaust plug assembly.
[[Page 11728]]
(h) Definition of Serviceable Assembly
For purposes of this AD, an acceptable serviceable turbine
exhaust plug assembly must meet the conditions specified in
paragraph (h)(1) or (h)(2) of this AD.
(1) A new assembly with part number 314W5520-22.
(2) A serviceable assembly as defined in the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 3, dated August 23, 2012; except, for any assembly on
which the actions specified in Part 2 or Part 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, are done,
and Boeing Special Attention Service Bulletin 777-78-0051, Revision
3, dated August 23, 2012, specifies to contact Boeing for repair
instructions, this AD requires repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (k) of this AD.
(i) Exception to Service Information Specifications
Where paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23,
2012, specifies a compliance time ``after the Revision 3 date of
this service bulletin,'' this AD requires compliance within the
applicable time after the effective date of this AD.
(j) Parts Installation Limitation
As of the effective date of this AD, only a serviceable turbine
exhaust plug assembly may be installed on any airplane.
(k) 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 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.
(l) Related Information
(1) For more information about this AD, contact Kevin Nguyen,
Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft
Certification Office (ACO) FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; phone: (425) 917-6501; fax: (425) 917-6590;
email: kevin.nguyen@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 view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 24, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-04568 Filed 2-28-14; 8:45 am]
BILLING CODE 4910-13-P