[Federal Register Volume 80, Number 191 (Friday, October 2, 2015)]
[Rules and Regulations]
[Pages 59570-59575]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-24677]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0128; Directorate Identifier 2013-NM-133-AD;
Amendment 39-18278; AD 2015-19-16]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for The
Boeing Company Model 777 airplanes equipped with Rolls-Royce Trent 800
series engines. This AD was prompted by reports of in-flight separation
of the engine's aft plug from the forward plug, which are the two parts
of the turbine exhaust plug assembly. This AD requires 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 issuing this AD to prevent
separation of the aft plug from the forward plug of the turbine exhaust
plug assembly, which could result in parts departing the airplane and
hitting the empennage, and destabilizing the airplane during a critical
flight phase. In addition, parts remaining on a runway could pose a
hazard to another airplane.
DATES: This AD is effective November 6, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 6,
2015.
ADDRESSES: 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0128.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0128; 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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
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: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to The Boeing Company Model
777 airplanes equipped with Rolls-Royce Trent 800 series engines. The
NPRM published in the Federal Register on March 3, 2014 (79 FR 11725);
corrected March 11, 2014 (79 FR 13592). The NPRM was prompted by
reports of in-flight separation of the engine's aft plug from the
forward plug, which are the two parts of the turbine exhaust plug
assembly. The NPRM proposed to 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 issuing this AD to prevent separation of the
aft plug from the forward plug of the turbine exhaust plug assembly,
which could result in parts departing the airplane and hitting the
empennage, and destabilizing the airplane during a critical flight
phase. In addition, parts remaining on a runway could pose a hazard to
another airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592); and
the FAA's response to each comment.
Request To Match Compliance Time
Cathay Pacific requested that we ensure that the AD compliance date
will be the same as the compliance time of Boeing Special Attention
Service Bulletin 777-78-0051, Revision 3, dated August 23, 2012; or
Boeing Special Attention Service Bulletin 777-78-0051, Revision 4,
dated February 7, 2014. Cathay Pacific reasoned that paragraph (i) of
the proposed AD specified compliance within 60 months after the
effective date of the proposed AD, and both revisions of this service
information specify a compliance time that is within 60 months after
the Revision 3 date of the service bulletin.
We infer that Cathay Pacific is requesting that we reduce the
compliance time of this final rule to match the compliance time listed
in the service information. We do not agree with the commenter's
request. In developing an appropriate compliance time for this action,
we considered not only the degree of urgency associated with addressing
the subject unsafe condition, but the manufacturer's recommendation for
an appropriate compliance time, the time required for the rulemaking
process, the availability of required parts, and the practical aspect
of installing the required modification within an interval of time that
corresponds to the typical scheduled maintenance for the majority of
affected operators. Under the provisions of paragraph (l) of this AD,
[[Page 59571]]
we may approve requests for adjustments to the compliance time, if data
are submitted to substantiate that such an adjustment would provide an
acceptable level of safety. We have not changed the AD in this regard.
Request To Define ``Serviceable'' To Include Pre-Boeing Service
Bulletin 777-78-0051 Plug Assemblies
Cathay Pacific requested that we revise paragraph (j) of the
proposed AD; corrected March 11, 2014 (79 FR 13592) to define
``serviceable'' plug assemblies. Cathay Pacific reasoned that both pre-
and post-Boeing Service Bulletin 777-78-0051 plug assemblies can be
installed, and the modification can be completed before the required
compliance time of the NPRM (79 FR 11725, March 3, 2014; corrected
March 11, 2014 (79 FR 13592)).
We do not agree to revise paragraph (j) of this AD because
serviceable assemblies are already defined in paragraph (h) of this AD.
This definition applies to the entire AD. Also, pre- Boeing Service
Bulletin 777-78-0051 plug assemblies do not meet the definition of
serviceable, as specified in the service information.
Request To Revise Definition of a Serviceable Assembly
American Airlines (AA) requested that we revise paragraph (h) of
the proposed AD to add another definition: Serviceable plug assemblies,
as those maintained in accordance with the operator's continued
airworthiness maintenance program (CAMP), prior to issuance of Boeing
Special Attention Service Bulletin 777-78-0051, Revision 3, dated
August 23, 2012. AA explained that prior to release of Boeing Special
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23,
2012, due to reported events of exhaust plug losses by other operators,
AA recognized that multiple removals of the exhaust aft plug causes the
3/16'' nutplate locking feature to wear out, which could then result in
loss of the aft plug. As a result, AA implemented a maintenance program
as part of its CAMP, which offers a level of safety equivalent to that
of Boeing Special Attention Service Bulletin 777-78-0051, Revision 3,
dated August 23, 2012. During every engine removal, for a refurbishment
or overhaul shop visit, the pre-Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, exhaust aft
plug nutplates are replaced with new nutplates.
In addition, AA stated that the holes are inspected for elongation
and cracks in accordance with procedures equivalent to Boeing Special
Attention Service Bulletin 777-78-0051 inspection procedures. Model 777
Airplane Maintenance Manual Chapter 78-11-02-400-803-R00, requires that
the minimum fastener run[hyphen]on torque of 2 in[hyphen]lbs is met
during every installation of the aft exhaust plug. In addition, each of
the exhaust aft plug fasteners receives a general visual check, using a
ladder/stand and a bright light, every 150 flight hours. AA expressed
that it is currently the largest Model 777-200 Trent 800 operator in
the worldwide fleet and has not lost an exhaust aft plug due to loose
or missing fasteners, as its CAMP demonstrates an equivalent level of
safety to the service information.
As an alternative, AA requested that we revise the NPRM (79 FR
11725, March 3, 2014; corrected March 11, 2014 (79 FR 13592)) to
include, as serviceable exhaust aft plugs, those maintained in
accordance with the operator's own maintenance program, such as AA's
approved CAMP prior to issuance of Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, and to remain
in service until the next engine removal for refurbishment or overhaul
shop visit, or 60 months from the effective date of the AD, whichever
is later.
We do not agree to include the requested provision. The maintenance
program described by AA is likely to be acceptable in lieu of direct
compliance with portions of this AD; however, the description of that
program provided in AA's comment is not sufficient to serve as
engineering data for the FAA to approve as an optional method of
compliance in this AD. Operators can submit a request for approval of
an alternative method of compliance (AMOC), with a more detailed
proposal to use the maintenance program, if sufficient data are
submitted to substantiate that the change would provide an acceptable
level of safety. We have not changed this AD in this regard.
Request To Change Compliance Time of Parts Installation Limitation
Boeing and Cathay Pacific requested that we revise paragraph (j) of
the proposed AD to change the installation limitation from the
effective date of the AD to the compliance deadline for the AD. Boeing
reasoned that paragraph (j) of the proposed AD currently creates an
alternative and indeterminate compliance deadline. Boeing explained
that during the compliance interval and prior to the AD deadline,
operators may be required, due to unforeseen circumstances, to install
a unit that is not a serviceable unit, and that under the current
wording, this would unnecessarily ground the airplane.
We do not agree to revise paragraph (j) of this AD to change the
installation limitation from the effective date of the AD to the
compliance date of the AD. Grace period compliance times are provided
in ADs in recognition that an immediate unscheduled modification
requirement would be disruptive. A grace period is included to give
operators a reasonable period of time to schedule and perform actions
that are required by the AD and that otherwise would not have occurred.
A parts installation limitation is included in some cases to require
that, if the parts affected by the AD are already being removed for a
reason other than the AD itself, that opportunity to correct the unsafe
condition should be taken. We determine whether such a parts
installation limitation should be included in the AD, and what the
specific requirements of the limitation will be, based on the risk
level associated with the unsafe condition and the expected
availability of required replacement parts.
In this case, we made a determination that the risk warranted the
consideration of a parts installation limitation. We also determined
that sufficient parts would be available to meet that limitation, and
that sufficient time to perform any required actions to make a nozzle
assembly serviceable as defined in paragraph (h) of this AD would exist
in situations where the nozzle might be removed in maintenance.
Specifically, we considered the case of an unscheduled engine change
where an operator may not have included a serviceable nozzle assembly
with the replacement engine. Modification of a nozzle assembly to meet
the definition of a serviceable nozzle can be performed in roughly the
same or less elapsed time than it takes to perform the engine
replacement itself. We did not foresee any other commonly occurring
situation where an engine nozzle assembly would be removed for
maintenance. However, as discussed in response to the comment issue
``Request to Revise Definition of a Serviceable Assembly,'' if an
operator specifically and adequately addresses the management of this
unsafe condition within its CAMP, we will consider AMOC approvals to
allow installation of nozzle assemblies that do not meet the definition
of serviceable nozzle in paragraph (h) of this AD.
We clarified paragraph (j) of this AD as a result of these
comments. We considered the explanatory statements about the intent of
the parts installation limitation language used in several
[[Page 59572]]
recent ADs, and determined that different language should be used in
this case to more clearly convey the intent of the parts installation
limitation contained in this AD. We have added the words ``or re-
install'' to paragraph (j) to clarify that any installation of a nozzle
assembly, regardless of the reason for the removal of the nozzle
assembly and regardless of the source of the replacement nozzle
assembly, is subject to the parts installation limitation of paragraph
(j) of this AD.
Request To Clarify Paragraph (j) of the Proposed AD
AA requested that we clarify paragraph (j) of the proposed AD. AA
explained that paragraph (j) of the proposed AD allows that only a
serviceable turbine exhaust plug assembly may be installed on any
airplane as of the effective date of this AD, while paragraph (i) of
the proposed AD requires a compliance time within a certain time after
the effective date of this AD, without any referral to serviceable
turbine exhaust plug assembly. AA reasoned that as written, these steps
are confusing and could lead operators to believe the actions required
by the AD are due as of the effective date of this AD.
We agree with the commenter and have clarified paragraph (j) of
this AD by including references to paragraphs (h)(1) and (h)(2) of this
AD.
Request To Clarify the AMOC Paragraph
Boeing requested that we revise paragraph (k)(3) of the proposed AD
(paragraph (l)(3) of this AD) to indicate that an AMOC, approved for a
repaired serviceable unit is to be attached to, and travel with, the
repaired serviceable unit. Boeing explained that the AMOC approval
should apply to the deviation on the serviceable unit and thereby
travel with the serviceable unit, which is rotable and could be
installed on numerous airplanes during its service life. Boeing also
explained that a unit repaired in accordance with an approved AMOC will
fulfill the intent of airplane safety when the unit is installed on an
airplane, and that the unit will be in compliance with the AD as long
as the part is serviceable as defined by the AD.
We agree with the commenter and have revised paragraph (l)(3) of
this AD accordingly.
Request To Use the CAMP
AA requested that we revise the NPRM (79 FR 11725, March 3, 2014;
corrected March 11, 2014 (79 FR 13592)), to include language that
allows the optional re-identification of the exhaust plug with the
correct post-Boeing Special Attention Service Bulletin 777-78-0051,
part number identity in accordance with a method approved by the
operator's approved CAMP, as the CAMP provides an equivalent level of
safety. AA explained that prior to the release of Boeing Special
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23,
2012, AA implemented a maintenance program to install data plates on
the forward and aft exhaust plug. The plates were installed because the
manufacturer part number and serial number, which were chemical-etched
on the exhaust plug skin by the manufacturer, were no longer legible.
AA stated that the data plates contain the original part number, a
company-assigned serial number, and the text ``MATCHED SET. DO NOT
SEPARATE.'' AA added that the installed identification plates are in
the same location as, but a different length than, the plates specified
in Boeing Special Attention Service Bulletin 777-78-0051, Revision 3,
dated August 23, 2012.
We agree to allow alternative permanent part-marking methods. If
the markings contain the required information and are permanent, the
intent of the marking requirement is addressed, and additional
flexibility is provided to operators. Therefore, part-marking methods
for the CAMP might be approved, provided that the markings are
permanent and contain the information specified in Boeing Special
Attention Service Bulletin 777-78-0051, Revision 4, dated February 7,
2014. We have added this information to paragraph (g) of this AD
accordingly.
Request To Eliminate AMOC Approval Requirement for Previous Repairs
AA requested that we revise paragraph (h) of the proposed AD, to
allow repairs accomplished prior to the release of this AD, in
accordance with Boeing instructions and approved per 14 CFR part
121.379, or a Boeing ODA, to be included as acceptable repairs in this
AD, without the requirement to obtain a Boeing ODA AMOC or Seattle
Aircraft Certification Office AMOC approval.
AA explained that, prior to release of the NPRM (79 FR 11725, March
3, 2014; corrected March 11, 2014 (79 FR 13592)); exhaust aft plugs
have received repairs at the exhaust aft plug mate line during
inspection or during incorporation of Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, utilizing
procedures provided by Boeing without Boeing ODA approval; rather, the
repair was approved per 14 CFR part 121.379. AA expressed that
paragraph (h) of the proposed AD specifies using a repair method
approved in accordance with the procedures specified in paragraph (k)
of the proposed AD, and these previously accomplished repairs, which
followed Boeing repair instructions, offer an equivalent level of
safety to the NPRM.
We partially agree with the request. We agree to add paragraph
(l)(4) in this AD to eliminate the requirement for subsequent AMOC
approval for repairs that were previously approved by the Boeing ODA,
using an FAA Form 8100-9, and having met the requirements of paragraph
(h) of this AD, for the definition of serviceable turbine exhaust plug
assemblies. We are confident that the Boeing ODA repair approval
process ensures that each repair is reviewed by qualified engineering
staff with knowledge of the original airplane design and compliance
substantiation. At the same time, we want to ensure that those repairs
would have a configuration that meets the definition of serviceable
turbine exhaust plug assemblies as defined in the service information.
We have added paragraph (l)(4) in this AD to state that repairs
approved prior to the effective date of this AD, by the Boeing ODA
using FAA Form 8100-9, and having met the requirements of paragraph (h)
of this AD for the definition of serviceable turbine exhaust plug
assemblies, do not require AMOC approval.
We disagree, however, to eliminate the AMOC approval requirement
for repairs approved by other means. Even though Boeing Service
Engineering may have provided a ``no technical objection'' statement,
qualified engineering staff with knowledge of the original airplane
design and compliance substantiation may not have been involved in
evaluating the repair. We have not changed this AD in this regard.
Additional Changes to This AD
We have revised this AD to refer to Boeing Special Attention
Service Bulletin 777-78-0051, Revision 4, dated February 7, 2014, as
the appropriate source of service information for the required actions.
Among other things, this service information adds Group 2 airplanes to
paragraph 1.E., ``Compliance;'' includes a maintenance records check;
adds a general visual inspection to determine the diameter of the bolt
used at the forward and aft plug interface; and adds applicable
corrective actions--all of which we have clarified in new paragraph
(g)(4) of this AD. Paragraphs (g)(3) and (c) of the proposed AD already
accounted for the Group 2
[[Page 59573]]
airplanes defined in Boeing Special Attention Service Bulletin 777-78-
0051, Revision 4, dated February 7, 2014. Paragraph (g)(2) of the
proposed AD accounted for the required actions.
We have also added a new paragraph (k) to this AD to provide credit
for certain actions, if those actions were performed before the
effective date of this AD using Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012. We have
redesignated the subsequent paragraphs of this AD accordingly.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 11725, March 3, 2014; corrected March 11, 2014 (79 FR
13592)) for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 11725, March 3, 2014; corrected
March 11, 2014 (79 FR 13592)).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Special Attention Service Bulletin 777-78-0051,
Revision 4, dated February 7, 2014. Among other things, this service
information adds Group 2 airplanes to paragraph 1.E., ``Compliance;''
includes a maintenance records check; adds a general visual inspection
to determine the diameter of the bolt used at the forward and aft plug
interface; and adds applicable corrective actions. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section of this AD.
Costs of Compliance
We estimate that this AD affects 35 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Installation.......................... 5 work-hours x $85 per $0 $425 $14,875
hour = $425.
General visual inspection............. 2 work-hours x $85 per $0 $170 $5,950
hour = $170.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacement
that would be required based on the results of the 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 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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2015-19-16 The Boeing Company: Amendment 39-18278; Docket No. FAA-
2014-0128; Directorate Identifier 2013-NM-133-AD.
[[Page 59574]]
(a) Effective Date
This AD is effective November 6, 2015.
(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
engine's 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 aft plug from the forward 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 4, dated February 7, 2014, except as provided by
paragraph (i) of this AD, do the applicable actions specified in
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-78-0051, Revision 4, dated February
7, 2014. Alternative part marking methods are allowed for the
requirements of this paragraph, if approved by the FAA principal
maintenance inspector, provided that the markings are permanent and
contain the information required by Boeing Special Attention Service
Bulletin 777-78-0051, Revision 4, dated February 7, 2014.
(1) For airplanes identified as Group 1, Configuration 1, in
Boeing Special Attention Service Bulletin 777-78-0051, Revision 4,
dated February 7, 2014: 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
4, dated February 7, 2014: 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 4, dated February
7, 2014: 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.
(4) For airplanes identified as Group 2, in Boeing Special
Attention Service Bulletin 777-78-0051, Revision 4, dated February
7, 2014: Do a maintenance records check to determine affected
turbine exhaust plug assemblies, and for affected assemblies, 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.
(h) Definition of Serviceable Assembly
For the 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 4, dated February 7, 2014; 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 4, dated February 7, 2014, are done,
and Boeing Special Attention Service Bulletin 777-78-0051, Revision
4, dated February 7, 2014, 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 (l)(1) of this AD.
(i) Exception to Service Information Specifications
Where paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 777-78-0051, Revision 4, dated February
7, 2014, specifies a compliance time ``after the Revision 3 date of
this service bulletin,'' or ``after the Revision 4 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 that meets the requirements of paragraph
(h)(1) or (h)(2) of this AD may be installed or reinstalled on any
airplane.
(k) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Special Attention Service
Bulletin 777-78-0051, Revision 3, dated August 23, 2012 (which is
not incorporated by reference in this AD), provided that for Group
1, Configuration 2, airplanes, on which the condition defined in
Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23,
2012, was found (i.e., only \1/4\ inch diameter bolts are found
installed at all 33 locations forward and aft plug interface), the
re-identification of the forward and aft plug was done before
further flight after the inspection.
(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: [email protected].
(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. An AMOC approved as described in this
paragraph for a specific serviceable nozzle assembly may be
transferred with that nozzle assembly to another aircraft without an
additional AMOC approval being required.
(4) Repairs approved prior to the effective date of this AD by
the Boeing ODA do not require AMOC approval if those repairs were
approved using FAA Form 8100-9 and those repairs meet the definition
of a serviceable assembly contained in the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 4, dated February 7, 2014.
(m) 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, WA
98057-3356; phone: 425-917-6501; fax: 425-917-6590; email:
[email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Special Attention Service Bulletin 777-78-0051,
Revision 4, dated February 7, 2014.
(ii) Reserved.
(3) For Boeing 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
[[Page 59575]]
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 16, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-24677 Filed 10-1-15; 8:45 am]
BILLING CODE 4910-13-P