Airworthiness Directives; The Boeing Company Airplanes, 39547-39553 [2016-13051]
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Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations
(2) Repeat the borescope inspection
required by this AD every 300 hours since
last inspection.
(3) If any crack, loss of contact between the
ferrule and diffuser axial vane, or any contact
between the injection manifold supply pipe
and the diffuser ferrule is found, remove the
diffuser case and replace the ferrule with a
part eligible for installation.
Issued in Burlington, Massachusetts, on
June 10, 2016.
Colleen M. D’Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
(f) Credit for Previous Actions
DEPARTMENT OF TRANSPORTATION
You may take credit for the actions
required by paragraph (e) of this AD if you
performed those actions using Turbomeca
S.A. MSB No. 298 72 2832, Version B, dated
October 12, 2015 or earlier versions, before
the effective date of this AD.
Federal Aviation Administration
(g) Alternative Methods of Compliance
(AMOCs)
(h) Related Information
(1) For more information about this AD,
contact Brian Kierstead, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7772; fax: 781–238–7199; email:
brian.kierstead@faa.gov.
(2) Refer to MCAI European Aviation
Safety Agency AD 2015–0209R1, dated April
20, 2016, for more information. You may
examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2015–8257.
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(i) 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) Turbomeca S.A. Alert MSB No. A298 72
2832, Version C, dated April 15, 2016.
(ii) Reserved.
(3) For Turbomeca S.A. service information
identified in this AD, contact Turbomeca
S.A., 40220 Tarnos, France; phone: (33) 05 59
74 40 00; fax: (33) 05 59 74 45 15.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
(5) You may view this service information
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
15:07 Jun 16, 2016
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BILLING CODE 4910–13–P
14 CFR Part 39
[Docket No. FAA–2011–0027; Directorate
Identifier 2010–NM–127–AD; Amendment
39–18543; AD 2016–11–16]
RIN 2120–AA64
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request. You may email your
request to: ANE-AD-AMOC@faa.gov.
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[FR Doc. 2016–14234 Filed 6–16–16; 8:45 am]
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 777–200
and -300 series airplanes equipped with
Rolls-Royce Model RB211-Trent 800
engines. This AD was prompted by
reports of thrust reverser (T/R) events
related to thermal damage of the T/R
inner wall. Depending on the airplane
configuration, this AD requires a records
review and applicable repetitive
inspections, replacements, and
installations of the T/R inner wall; and
related investigative and corrective
actions if necessary. This AD also
requires installation of serviceable T/R
halves, which would terminate the
repetitive actions. This AD also requires
revising the inspection or maintenance
program by incorporating new
airworthiness limitations. We are
issuing this AD to detect and correct a
degraded T/R inner wall panel. A
degraded T/R inner wall panel could
lead to failure of the T/R and adjacent
components and their consequent
separation from the airplane, which
could result in a rejected takeoff (RTO)
and cause asymmetric thrust and
consequent loss of control of the
airplane during reverse thrust operation.
If a T/R inner wall overheats, separated
components could cause structural
damage to the airplane, damage to other
airplanes, or possible injury to people
on the ground.
DATES: This AD is effective July 22,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 22, 2016.
SUMMARY:
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39547
For service information
identified in this final rule, 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2011–
0027.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2011–
0027; 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, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6501;
fax: 425–917–6590; email:
kevin.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain The Boeing
Company Model 777–200 and -300
series airplanes equipped with RollsRoyce Model RB211-Trent 800 engines.
The SNPRM published in the Federal
Register on September 25, 2015 (80 FR
57744) (‘‘the SNPRM’’). We preceded
the SNPRM with a notice of proposed
rulemaking (NPRM) that published in
the Federal Register on January 20,
2011 (76 FR 3561) (‘‘the NPRM’’). The
NPRM proposed to require repetitive
inspections for degradation of T/R
structure and sealant, and related
investigative and corrective actions if
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necessary. The NPRM was prompted by
reports of T/R events related to thermal
damage of the T/R inner wall. The
SNPRM proposed to revise the NPRM
by adding different repetitive inspection
requirements for T/R halves with a
thermal protective system installed. The
SNPRM also proposed to revise the
NPRM by requiring installation of
serviceable T/R halves, which would
terminate the repetitive inspections. The
SNPRM also proposed to revise the
inspection or maintenance program by
incorporating new airworthiness
limitations. We are issuing this AD to
detect and correct a degraded T/R inner
wall panel. A degraded T/R inner wall
panel could lead to failure of the T/R
and adjacent components and their
consequent separation from the
airplane, which could result in an RTO
and cause asymmetric thrust and
consequent loss of control of the
airplane during reverse thrust operation.
If a T/R inner wall overheats, separated
components could cause structural
damage to the airplane, damage to other
airplanes, or possible injury to people
on the ground.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM and the FAA’s
response to each comment.
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Request To Change Compliance
Reference
Boeing requested that we revise
paragraph (k)(2) of the proposed AD (in
the SNPRM) by adding ‘‘table 5’’ to the
reference to the Compliance paragraph
in Boeing Service Bulletin 777–78–
0082, Revision 1, dated June 15, 2015.
Boeing stated that this change would be
consistent with how paragraph (k)(1) of
the proposed AD (in the SNPRM) refers
to the Compliance paragraph.
We agree with the commenter’s
request for the reason provided. We
have revised paragraph (k)(2) of this AD
accordingly.
Request To Modify Alternative Method
of Compliance (AMOC) Statement
Boeing requested that the AMOC
statement specified in paragraph (r)(3)
of the proposed AD (in the SNPRM) be
revised by adding a sentence to allow an
AMOC for the serviceable T/R assembly
to be transferred to other airplanes.
Boeing stated that an AMOC provided
for a repaired and serviceable unit is
able to be attached to and travel with
the repaired unit. Boeing added that a
serviceable unit is a rotable part and can
be installed on multiple airplanes
during the life of the unit. Boeing noted
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15:07 Jun 16, 2016
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that paragraph (l)(3) of AD 2015–19–16,
Amendment 39–18278 (80 FR 59570,
October 2, 2015) contains language
similar to the requested language.
We disagree with the request because
we are now able to issue an AMOC that
applies to multiple products operated
by a single operator (commonly referred
to as a fleet AMOC). This procedure
allows AMOCs to address rotable parts.
We have not changed this AD in this
regard.
Request To Update Service Information
Boeing requested that the revision
date of Boeing 777 Maintenance
Planning Data (MPD) Document Section
9, Airworthiness Limitations (AWLs)
and Certification Maintenance
Requirements (CMRs), D622W001–9,
Revision dated October 2014, be
updated to reflect the latest FAAapproved revision. Boeing stated that
AWL 78–AWL–01, Thrust Reverser
Thermal Protection System, was revised
recently to include Boeing Alert Service
Bulletin 777–78A0094, dated July 29,
2014, in the applicability note of the
AWL.
We agree to reference the most recent
revision of Boeing 777 MPD Document
Section 9, AWLs and CMRs,
D622W001–9 (which is referred to as
Temporary Revision (TR) 09–030,
Revision dated November 2015, on
MyBoeingFleet.com), because the new
applicability note clarifies that AWL
78–AWL–01 applies to T/R halves on
which the actions specified in Boeing
Alert Service Bulletin 777–78A0094
have been done. As a result, we have
revised the introductory text to
paragraph (n) of this AD accordingly.
We have also added a new paragraph
(p)(5) to this AD to provide credit for
accomplishing the revision required by
paragraph (n) of this AD using Boeing
777 MPD Document, Section 9, AWLs
and CMRs, D622W001–9, Revision
dated October 2014.
Request To Modify Initial Inspection
Boeing requested that paragraph (n)(1)
of the proposed AD (in the SNPRM) be
revised to allow deferral of the initial
inspection for AWL 78–AWL–01, Thrust
Reverser Thermal Protection System.
Boeing stated that the compliance time
should be 1,125 days or 6,000 flight
cycles, whichever occurs first, after the
last inspection for AWL 78–AWL–01,
Thrust Reverser Thermal Protection
System, ‘‘for T/Rs that have already
incorporated 78–AWL–01.’’ Boeing
stated that when the AD becomes
effective, T/R halves on which Boeing
Alert Service Bulletin 777–78A0094 and
AWL 78–AWL–01, Thrust Reverser
Thermal Protection System, have been
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incorporated are not subject to the
inspections specified in paragraph (i) of
the proposed AD (in the SNPRM) and
should not be required to do the
inspection required by AWL 78–AWL–
01 concurrent with the next inspection
required by paragraph (i) of this AD or
within 30 days after the effective date of
this AD, whichever occurs later.
We agree with allowing deferral of the
initial inspection for AWL 78–AWL–01,
Thrust Reverser Thermal Protection
System, for the reasons provided by the
commenter. We have revised the
compliance time for AWL 78–AWL–01,
Thrust Reverser Thermal Protection
System, as requested by the commenter.
We have revised the introductory text to
paragraph (n), and reformatted and
revised paragraphs (n)(1) and (n)(2) of
this AD, to accommodate the
commenter’s request. We clarified the
affected airplanes for the compliance as
specified in paragraph (n)(1) of this AD
by stating, ‘‘For airplanes on which any
inspections required by paragraph (i) of
this AD are done.’’ We clarified the
affected airplanes for the compliance as
specified in paragraph (n)(2) of this AD
by stating, ‘‘For airplanes on which the
installation required by paragraph (l) of
this AD is done.’’
Request To Review Inspection Methods
American Airlines requested that the
FAA review the inspection methods and
instructions required in paragraph (i) of
the proposed AD (in the SNPRM) when
doing a nondestructive test (NDT)
inspection for delaminations and
disbonds; and ensuring false positive
findings are prevented or minimized.
American Airlines stated that they
inspected eight T/R inner walls in
accordance with paragraph (i)(1) of the
proposed AD (in the SNPRM) and found
disbonded material. American Airlines
stated that after they contacted the
original equipment manufacturer (OEM)
and re-inspected, several units were
determined to be false positives.
American Airlines surmised that the
instructions or possible training for
inspections may not be sufficient.
We acknowledge the commenter’s
concern. However, we have determined
the NDT inspections for disbonds and
damage required in paragraph (i) and
associated service information produce
reliable inspection results and
adequately detect disbonds and damage.
Through technical discussion with the
OEM, we understand that the false
positive indications were a result of a
maintenance vendor using a non-OEM
inspection manual that had a faulty
NDT inspection standard. We have not
revised this AD in this regard.
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Request To Review Airworthiness
Limitation Inspection Procedures
American Airlines stated it had a T/
R inner wall that required repair, but the
damage would not have been detected
by the inspection specified in
Airworthiness Limitation 78–AWL–02,
Thrust Reverser Inner Wall, as specified
in Boeing MPD Document, Section 9,
AWLs and CMRs, D622W001–9,
Revision dated October 2014. American
Airlines stated the damage would likely
have passed inspection because it did
not indicate any heat discoloration, and
other areas of disbonds or damage on
the inner wall could be potentially
missed after the incorporation of Boeing
Alert Service Bulletin 777–78A0094,
dated July 29, 2014, and AWL 78–AWL–
02. We infer the commenter is
requesting that we review AWL 78–
AWL–02 to ensure that thermal damage
on the inner wall is not missed.
We acknowledge the commenter’s
concern, and we might consider
additional rulemaking to address that
concern in the future. We contacted
Boeing, and Boeing stated they are
working with American Airlines to
determine if a change needs to be made
to the service information. However,
until such additional action is
identified, we consider it appropriate to
proceed with issuance of this final rule
to address the identified unsafe
condition. We have not changed this
final rule in this regard.
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 SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
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 the following Boeing
service information.
• Boeing Alert Service Bulletin 777–
78A0065, Revision 2, dated May 6,
2010. This service information describes
procedures for a review of the airplane
maintenance records to determine
whether sealant was added to insulation
blankets around compression pad
fittings and the powered door opening
system (PDOS) fitting; inspections of the
T/R structure; and related investigative
and corrective actions.
• Boeing Alert Service Bulletin 777–
78A0094, dated July 29, 2014. This
service information describes
procedures for installing serviceable
T/R halves.
• Boeing Service Bulletin 777–78–
0082, Revision 1, dated June 15, 2015;
and Boeing Special Attention Service
Bulletin 777–78–0071, Revision 2, dated
July 23, 2013. This service information
describes, among other actions,
procedures for inspections of the T/R
structure, and related investigative and
39549
corrective actions, if necessary. Boeing
Special Attention Service Bulletin 777–
78–0071, Revision 2, dated July 23,
2013, also describes, for airplanes on
which the actions specified in Boeing
Special Attention Service Bulletin 777–
78–0071, dated November 29, 2009,
have been done, procedures for
installation of click bond covers and a
bracket, a general visual inspection of
the compression fitting for incorrect pin
orientation, and related investigative
and corrective actions, if necessary.
• Boeing 777 Maintenance Planning
Data (MPD) Document, Section 9,
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), D622W001 9, Revision dated
November 2015. This service
information provides required AWLs
and CMRs for The Boeing Company
Model 777 airplanes. The two AWLs
specifically required by this AD are
AWL 78–AWL–01, Thrust Reverser
Thermal Protection System, which
describes an inspection of the T/R
thermal protection system on both
engines; and AWL 78 AWL–02, which
describes an inspection of the T/R inner
wall.
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.
Costs of Compliance
We estimate that this AD affects 55
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Work hours
Actions per Boeing Alert Service
Bulletin 777-78A0065, Revision
2, dated May 6, 2010.
Maintenance or Inspection Program Revision.
Average
labor rate
per hour
Up to 79 workhours, per T/R
half.
Actions per Boeing Special Attention
Service
Bulletin
777-78-0071, Revision 2, dated
July 23, 2013.
Inspections per Boeing Service
Bulletin 777-78-0082, Revision
1, dated June 15, 2015.
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Action
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Parts cost
Cost per product
Fleet cost
$85
$0 ......................
Up to $6,715 per
T/R half.
Up to 48 workhours, per T/R
half.
85
$0 ......................
Up to $4,080 per
T/R half.
$0 (No airplanes on the U.S.
Register are in the configuration specified in Boeing Alert
Service Bulletin 777-78A0065,
Revision 2, dated May 6,
2010.)
Up to $897,600 (4 T/R halves per
airplane).
Up to 39 workhours, per T/R
half.
85
$0 ......................
Up to $3,315 per
T/R half.
1 work-hour .......
85
$0 ......................
$85 ....................
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$0 (No airplanes on the U.S.
Register are in the configuration specified in Boeing Service
Bulletin 777-78-0082, Revision
1, dated June 15, 2015.)
$4,675.
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ESTIMATED COSTS—Continued
Average
labor rate
per hour
Action
Work hours
T/R half installation per Boeing
Alert
Service
Bulletin
777-78A0094, dated July 29,
2014.
Up to 206 workhours, per T/R
half.
Parts cost
85
Up to $400,651
per T/R half 1.
Cost per product
Up to $418,161
per T/R half.
Fleet cost
Up to $91,995,420 (4 T/R halves
per airplane).2
1 The cost of parts is split into two major parts: (1) Thermal protection system (TPS) blankets and (2) inner wall structure. The vast majority of
the work associated with the TPS upgrade has already been completed. In addition, nearly half of the inner wall structure modification has already been done.
2 The fleet cost estimate above is based on a general estimate for a given airplane with two engines having two T/R halves for each engine.
Not all tasks required by this AD and specified in the service information would need to be done for a given T/R half. For a given TR half, it may
only be necessary to accomplish certain actions or none for compliance, depending on its configuration status. We have no data to determine
any given T/R half configuration to determine the cost for each T/R half to do the applicable actions for that T/R half. The majority of this cost
has already been incurred.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
(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.
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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.
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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:
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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
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 airworthiness
directive (AD):
■
2016–11–16 The Boeing Company:
Amendment 39–18543; Docket No.
FAA–2011–0027; Directorate Identifier
2010–NM–127–AD.
(a) Effective Date
This AD is effective July 22, 2016.
(b) Affected ADs
This AD affects AD 2005–07–24,
Amendment 39–14049 (70 FR 18285, April
11, 2005).
(c) Applicability
This AD applies to The Boeing Company
Model 777–200 and –300 series airplanes,
certificated in any category, equipped with
Rolls-Royce Model RB211-Trent 800 engines.
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(d) Subject
Air Transport Association (ATA) of
America Code 78, Engine exhaust.
(e) Unsafe Condition
This AD was prompted by reports of thrust
reverser (T/R) events related to thermal
damage of the T/R inner wall. We are issuing
this AD to detect and correct a degraded
T/R inner wall panel. A degraded T/R inner
wall panel could lead to failure of the T/R
and adjacent components and their
consequent separation from the airplane,
which could result in a rejected takeoff (RTO)
and cause asymmetric thrust and consequent
loss of control of the airplane during reverse
thrust operation. If a T/R inner wall
overheats, separated components could cause
structural damage to the airplane, damage to
other airplanes, or possible injury to people
on the ground.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Records Review, Inspections, and Related
Investigative and Corrective Actions for
Airplanes With Pre-Thermal Protection
System (TPS) Insulation Blankets (Part
Numbers (P/Ns) 315W5113–(XX) and
315W5010–(XX)) Installed
For airplanes with pre-TPS insulation
blankets, P/Ns 315W5113–(XX) and
315W5010–(XX): Except as required by
paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of
this AD, at the applicable time in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 777–78A0065, Revision 2, dated
May 6, 2010, review the airplane
maintenance records to determine whether
sealant was added to insulation blankets
around the compression pad fittings and the
powered door opening system (PDOS) fitting;
do the applicable actions specified in
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5),
and (g)(6) of this AD; and do all applicable
related investigative and corrective actions;
in accordance with the applicable work
packages of the Accomplishment Instructions
of Boeing Alert Service Bulletin 777–
78A0065, Revision 2, dated May 6, 2010,
except as required by paragraph (h)(5) of this
AD. Do all applicable related investigative
and corrective actions before further flight.
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Repeat the applicable inspections,
replacement, and installations required by
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5),
and (g)(6) of this AD thereafter at the
applicable intervals specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 777–78A0065, Revision 2, dated
May 6, 2010.
(1) Do a detailed inspection of all T/R inner
wall insulation blanket edges, grommet
holes, penetrations, and seams for sealant
that is cracked, has gaps, is loose, or is
missing; do a general visual inspection of
click bond studs, blanket studs, and
temporary fasteners; and replace sealant as
applicable.
(2) Do the actions specified by either
paragraph (g)(2)(i) or (g)(2)(ii) of this AD.
(i) Do a full inner wall panel
nondestructive test (NDT) inspection for
delamination and disbonding of each T/R
half, and do a general visual inspection for
areas of thermal degradation.
(ii) Do a limited area NDT inspection of the
inner wall panel of each T/R half for
delamination and disbonding, and do a
general visual inspection for areas of thermal
degradation.
(3) Do a general visual inspection of the T/
R perforated wall aft of the intermediate
pressure compressor 8th stage (IP8) and the
high pressure compressor 3rd stage (HP3)
bleed port exits for a color that is different
from that of the general area.
(4) Do a detailed inspection of the PDOS
lug bushings on the upper number 1
compression pad fittings to detect hole
elongation, deformation, and contact with the
PDOS actuator; and install a PDOS actuator
rod and sealant.
(5) Do an NDT inspection for unsatisfactory
number 1 upper and numbers 1 and 2 lower
compression pad fittings.
(6) Install and seal insulation blankets.
(h) Exceptions to Specifications of Boeing
Alert Service Bulletin 777–78A0065,
Revision 2, Dated May 6, 2010
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 777–78A0065,
Revision 2, dated May 6, 2010, specifies a
compliance time ‘‘after the date on the
original issue of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(2) Where table 2 of paragraph 1.E.,
‘‘Compliance,’’ in Boeing Alert Service
Bulletin 777–78A0065, Revision 2, dated
May 6, 2010, specifies a compliance time of
‘‘2,000 flight cycles after the date of the
operator’s own inspections,’’ for doing Work
Packages 2 and 5, or Work Packages 5 and
6, this AD requires compliance within 2,000
flight cycles after the date of the operator’s
own inspections, or within 12 months after
the effective date of this AD, whichever
occurs later.
(3) Where the Condition column in table 2
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 777–78A0065,
Revision 2, dated May 6, 2010, refers to a T/
R half that has or has not been inspected
before ‘‘the date on this service bulletin,’’ this
AD requires compliance for each
corresponding T/R half that has or has not
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15:07 Jun 16, 2016
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been inspected before the effective date of
this AD.
(4) Where the Condition column in tables
2 and 3 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 777–78A0065,
Revision 2, dated May 6, 2010, refers to ‘‘total
flight cycles,’’ this AD applies to each T/R
half with the specified total flight cycles as
of the effective date of this AD.
(5) Where Boeing Alert Service Bulletin
777–78A0065, Revision 2, dated May 6, 2010,
specifies to contact Boeing for appropriate
action: Before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph (r) of this
AD.
(i) Repetitive NDT and Additional
Inspections for Airplanes With TPS
Insulation Blankets (P/N 315W5115–(XX))
Installed
For airplanes with TPS insulation blankets,
P/N 315W5115–(XX): Within 2,000 flight
cycles after doing any NDT inspection
specified in Boeing Special Attention Service
Bulletin 777–78–0071; or within 2,000 flight
cycles after doing any NDT inspection
specified in Boeing Service Bulletin 777–78–
0082; or within 30 days after the effective
date of this AD; whichever occurs latest; do
the inspections specified in paragraphs (i)(1)
and (i)(2) of this AD, and do all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–78–0071, Revision 2,
dated July 23, 2013, or in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 777–78–0082, Revision 1,
dated June 15, 2015, as applicable; except as
required by paragraph (m) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the inspections specified in
paragraphs (i)(1) and (i)(2) of this AD
thereafter at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 777–78–
0071, Revision 2, dated July 23, 2013; or
Boeing Service Bulletin 777–78–0082,
Revision 1, dated June 15, 2015; as
applicable.
(1) Do an NDT inspection of the full T/R
inner wall panel for delaminations and
disbonds.
(2) Do a detailed inspection of the
perforated side of the T/R inner wall aft of
the IP8 and the HP3 bleed port exits for color
that is different from the normal T/R
perforated wall color.
(j) Concurrent Requirements for Paragraph
(i) of This AD
For airplanes with TPS insulation blankets,
P/N 315W5115–(XX), on which any action
specified in Boeing Special Attention Service
Bulletin 777–78–0071 have been done but
the actions specified in paragraphs (j)(1) and
(j)(2) of this AD have not been done: Prior to
or concurrently with doing the inspection
required by paragraph (i) of this AD, do the
actions specified in paragraphs (j)(1) and
(j)(2) of this AD, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–78–
0071, Revision 2, dated July 23, 2013, except
as required by paragraph (m) of this AD.
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
39551
(1) Install click bond covers and bracket
and replace the washers.
(2) Do a detailed inspection of the
compression fitting for incorrect pin
orientation, and do all applicable related
investigative and corrective actions. Do all
applicable related investigative and
corrective actions before further flight.
(k) Repetitive Electronic Engine Control
(EEC) Wire Bundle Inspections for Airplanes
With TPS Insulation Blankets (P/N
315W5115–(XX)) Installed
For airplanes with TPS insulation blankets,
P/N 315W5115–(XX): Do the inspections
specified in paragraphs (k)(1) or (k)(2) of this
AD, as applicable.
(1) For airplanes on which any inspection
specified in Boeing Special Attention Service
Bulletin 777–78–0071 has been done: Within
2,000 flight hours after doing a detailed
inspection of the EEC wire bundles and clips
as specified in Boeing Special Attention
Service Bulletin 777–78–0071, or within 500
flight hours after the effective date of this AD,
whichever occurs later; do a detailed
inspection of the EEC wire bundles and clips
for damage, and do all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–78–
0071, Revision 2, dated July 23, 2013, except
as required by paragraph (m) of this AD. Do
all applicable corrective actions before
further flight. Repeat the inspection
thereafter at the applicable time specified in
table 5 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
777–78–0071, Revision 2, dated July 23,
2013.
(2) For airplanes on which any inspection
specified in Boeing Service Bulletin 777–78–
0082, has been done: Within 2,000 flight
hours after doing a detailed inspection of the
EEC wire bundles and clips as specified in
Boeing Special Attention Service Bulletin
777–78–0082, or within 500 flight hours after
the effective date of this AD, whichever
occurs later; do a detailed inspection for
damage of the EEC wire bundles and clips,
and do all applicable corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777–
78–0082, Revision 1, dated June 15, 2015,
except as required by paragraph (m) of this
AD. Do all applicable corrective actions
before further flight. Repeat the inspection
thereafter at the applicable time specified in
table 5 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 777–78–0082,
Revision 1, dated June 15, 2015.
(l) T/R Inner Wall Installation
Within 48 months after the effective date
of this AD: Install serviceable T/R halves, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–78A0094, dated July 29, 2014, except as
required by paragraph (m) of this AD. The
definition of a serviceable T/R half is
specified in Boeing Alert Service Bulletin
777–78A0094, dated July 29, 2014.
Accomplishing the installation specified in
this paragraph and the revision to the
maintenance or inspection program required
by paragraph (n) of this AD terminates the
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actions required by paragraphs (g), (i), (j), and
(k) of this AD.
(m) Exceptions to Service Information
Specified in Paragraphs (i), (j), (k), and (l) of
This AD
Where Boeing Alert Service Bulletin 777–
78A0094, dated July 29, 2014; Boeing Service
Bulletin 777–78–0082, Revision 1, dated June
15, 2015; and Boeing Special Attention
Service Bulletin 777–78–0071, Revision 2,
dated July 23, 2013; specify to contact Boeing
for appropriate action: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (r) of this AD.
(n) Revise the Maintenance or Inspection
Program
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate
Airworthiness Limitations 78–AWL–01,
Thrust Reverser Thermal Protection System;
and 78–AWL–02, Thrust Reverser Inner Wall;
as specified in Boeing 777 Maintenance
Planning Data (MPD) Document, Section 9,
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), D622W001–9, Revision dated
November 2015. The initial compliance times
for AWLs 78–AWL–01, Thrust Reverser
Thermal Protection System, and 78–AWL–
02, Thrust Reverser Inner Wall, as specified
in Boeing 777 MPD Document, Section 9,
AWLs and CMRs, D622W001–9, Revision
dated November 2015, are at the applicable
time specified in paragraph (n)(1) or (n)(2) of
this AD.
(1) For airplanes on which any inspections
required by paragraph (i) of this AD are done:
Concurrent with the next inspection required
by paragraph (i) of this AD, or within 30 days
after the effective date of this AD, whichever
occurs later.
(2) For airplanes on which the installation
required by paragraph (l) of this AD is done:
At the later of the times specified in
paragraph (n)(2)(i) and (n)(2)(ii) of this AD.
(i) Within 1,125 days or 6,000 flight cycles,
whichever occurs first after accomplishing
the installation required by paragraph (l) of
this AD.
(ii) Within 30 days after the effective date
of this AD.
ehiers on DSK5VPTVN1PROD with RULES
(o) No Alternative Actions or Intervals
After the maintenance or inspection
program, as applicable, has been revised as
required by paragraph (n) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (r) of this AD.
(p) Credit for Previous Actions
(1) 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 Alert
Service Bulletin 777–78A0065, dated June
23, 2008; or Boeing Alert Service Bulletin
777–78A0065, Revision 1, dated January 29,
2009. This service information is not
incorporated by reference in this AD.
VerDate Sep<11>2014
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(2) This paragraph provides credit for the
actions specified in paragraph (i) of this AD,
if those actions were performed before the
effective date of this AD using any service
information specified in paragraphs (p)(2)(i),
(p)(2)(ii), and (p)(2)(iii) of this AD. This
service information is not incorporated by
reference in this AD.
(i) Boeing Service Bulletin 777–78–0082,
dated November 9, 2011.
(ii) Boeing Special Attention Service
Bulletin 777–78–0071, dated November 25,
2009.
(iii) Boeing Special Attention Service
Bulletin 777–78–0071, Revision 1, dated
September 8, 2010.
(3) This paragraph provides credit for the
actions specified in paragraph (j) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Special
Attention Service Bulletin 777–78–0071,
Revision 1, dated September 8, 2010. This
service information is not incorporated by
reference in this AD.
(4) This paragraph provides credit for the
actions specified in paragraph (k)(2) of this
AD, if those actions were performed before
the effective date of this AD using Boeing
Service Bulletin 777–78–0082, dated
November 9, 2011. This service information
is not incorporated by reference in this AD.
(5) This paragraph provides credit for the
actions specified in paragraph (n) of this AD,
if those actions were performed before the
effective date of this AD using Boeing 777
MPD Document, Section 9, AWLs and CMRs,
D622W001–9, Revision dated October 2014.
This service information is not incorporated
by reference in this AD.
(q) Terminating Action for AD 2005–07–24,
Amendment 39–14049 (70 FR 18285, April
11, 2005)
Accomplishing the actions specified in
paragraph (q)(1), (q)(2), or (q)(3) of this AD
terminates the actions required by paragraphs
(f), (g), and (h) of AD 2005–07–24,
Amendment 39–14049 (70 FR 18285, April
11, 2005).
(1) The actions required by paragraph (g)
of this AD.
(2) The inspections required by paragraphs
(i) and (k) of this AD, and, as applicable, the
actions required by paragraph (j) of this AD.
(3) The installation specified in paragraph
(l) of this AD.
(r) 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 (s)(1) 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.
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration 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. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(s) Related Information
(1) For more information about this AD,
contact Kevin Nguyen, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: 425–917–
6501; fax: 425–917–6590; email:
kevin.nguyen@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (t)(3) and (t)(4) of this AD.
(t) 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 Alert Service Bulletin 777–
78A0065, Revision 2, dated May 6, 2010.
(ii) Boeing Alert Service Bulletin 777–
78A0094, dated July 29, 2014.
(iii) Boeing Service Bulletin 777–78–0082,
Revision 1, dated June 15, 2015.
(iv) Boeing Special Attention Service
Bulletin 777–78–0071, Revision 2, dated July
23, 2013.
(v) Boeing 777 Maintenance Planning Data
(MPD) Document, Section 9, Airworthiness
Limitations (AWLs) and Certification
Maintenance Requirements (CMRs),
D622W001–9, Revision dated November
2015.
(3) 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.
(4) You may view this 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.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations
Issued in Renton, Washington, on May 20,
2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–8137; Directorate
Identifier 2014–NM–104–AD; Amendment
39–18561; AD 2016–12–12]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2008–05–
18 R1 for certain Fokker Services B.V.
Model F.27 Mark 050, 200, 300, 400,
500, 600, and 700 airplanes. AD 2008–
05–18 R1 required revising the
Airworthiness Limitations Section
(ALS) of the Instructions for Continued
Airworthiness to incorporate new
limitations for fuel tank systems. This
new AD requires a new maintenance or
inspection program revision to
incorporate the revised Airworthiness
Limitation Items (ALIs) and critical
design configuration control limitations
(CDCCLs). This new AD also adds
certain airplanes to the applicability.
This AD was prompted by the issuance
of revised service information to update
the Fuel ALIs and CDCCLs that address
fuel tank system ignition sources. We
are issuing this AD to prevent the
potential of ignition sources inside fuel
tanks, which, in combination with
flammable fuel vapors, could result in
fuel tank explosions and consequent
loss of the airplane.
DATES: This AD becomes effective July
22, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 22, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 23, 2009 (74 FR 57402,
November 6, 2009).
ADDRESSES: For service information
identified in this final rule, contact
Fokker Services B.V., Technical
ehiers on DSK5VPTVN1PROD with RULES
VerDate Sep<11>2014
15:07 Jun 16, 2016
Jkt 238001
Services Dept., P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone
+31 (0)88–6280–350; fax +31 (0)88–
6280–111; email technicalservices@
fokker.com; Internet https://
www.myfokkerfleet.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 https://
www.regulations.gov by searching for
and locating Docket Number FAA–
2015–8137.
prevent the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0029, dated February 24,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on all Model F.27
Mark 050, 200, 300, 400, 500, 600, and
700 airplanes. The MCAI states:
Examining the AD Docket
[FR Doc. 2016–13051 Filed 6–16–16; 8:45 am]
SUMMARY:
39553
* * * [T]he FAA published Special
Federal Aviation Regulation (SFAR) 88, and
the Joint Aviation Authorities (JAA)
published Interim Policy INT/POL/25/12.
The review conducted by Fokker Services on
the Fokker F27 design in response to these
regulations identified a number of Fuel
Airworthiness Limitation Items (ALI) and
Critical Design Configuration Control
Limitations (CDCCL) items to prevent the
development of unsafe conditions within the
fuel system.
To introduce these Fuel ALI and CDCCL
items, Fokker Services published Service
Bulletin (SB) F27/28–070. Consequently,
EASA issued AD 2006–0207, requiring the
implementation of these Fuel ALI and
CDCCL items. That [EASA] AD was later
revised to make reference to SBF27–28–
070R1 and to specify that the use of later SB
revisions was acceptable.
In 2014, Fokker Services issued Revision 2
of SBF27–28–070 to update the Fuel ALI and
CDCCL items and to consolidate Fuel ALI
and CDCCL items contained in a number of
other SBs. Consequently, EASA issued AD
2014–0105, superseding AD 2006–0207R1
and requiring the implementation of the
updated Fuel ALI and CDCCL items.
Since that [EASA] AD was issued, Fokker
Services issued Revision 3 of SBF27–28–070,
primarily to introduce 2 additional CDCCL
items.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0105, which is superseded, and
requires implementation of the updated Fuel
ALI and CDCCL items.
More information on this subject can be
found in Fokker Services All Operators
Message AOF27.043#05.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
8137; 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 (telephone 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: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1137;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008–05–18 R1,
Amendment 39–16083 (74 FR 57402,
November 6, 2009) (‘‘AD 2008–05–18
R1’’). AD 2008–05–18 R1 applied to
certain Model F.27 Mark 050, 200, 300,
400, 500, 600, and 700 airplanes. The
NPRM published in the Federal
Register on January 4, 2016 (81 FR 38)
(‘‘the NPRM’’). The NPRM was
prompted by the issuance of revised
service information to update the Fuel
ALIs and CDCCLs that address fuel tank
system ignition sources. The NPRM
proposed to retain the requirements of
AD 2008–05–18 R1, and require a new
maintenance or inspection program
revision to incorporate the revised ALIs
and CDCCLs. The NPRM also proposed
to add certain airplanes to the
applicability. We are issuing this AD to
PO 00000
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Fmt 4700
Sfmt 4700
The unsafe condition is the potential
of ignition sources inside fuel tanks.
Such ignition sources, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane. You may examine
the MCAI in the AD docket on the
Internet at https://www.regulations.gov
by searching for and locating it in
Docket No. FAA–2015–8137.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
E:\FR\FM\17JNR1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 117 (Friday, June 17, 2016)]
[Rules and Regulations]
[Pages 39547-39553]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-13051]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0027; Directorate Identifier 2010-NM-127-AD;
Amendment 39-18543; AD 2016-11-16]
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 certain
The Boeing Company Model 777-200 and -300 series airplanes equipped
with Rolls-Royce Model RB211-Trent 800 engines. This AD was prompted by
reports of thrust reverser (T/R) events related to thermal damage of
the T/R inner wall. Depending on the airplane configuration, this AD
requires a records review and applicable repetitive inspections,
replacements, and installations of the T/R inner wall; and related
investigative and corrective actions if necessary. This AD also
requires installation of serviceable T/R halves, which would terminate
the repetitive actions. This AD also requires revising the inspection
or maintenance program by incorporating new airworthiness limitations.
We are issuing this AD to detect and correct a degraded T/R inner wall
panel. A degraded T/R inner wall panel could lead to failure of the T/R
and adjacent components and their consequent separation from the
airplane, which could result in a rejected takeoff (RTO) and cause
asymmetric thrust and consequent loss of control of the airplane during
reverse thrust operation. If a T/R inner wall overheats, separated
components could cause structural damage to the airplane, damage to
other airplanes, or possible injury to people on the ground.
DATES: This AD is effective July 22, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 22,
2016.
ADDRESSES: For service information identified in this final rule,
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 https://www.regulations.gov by searching for and locating Docket No. FAA-2011-
0027.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2011-
0027; 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, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6501; fax: 425-917-6590; email: kevin.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to certain The
Boeing Company Model 777-200 and -300 series airplanes equipped with
Rolls-Royce Model RB211-Trent 800 engines. The SNPRM published in the
Federal Register on September 25, 2015 (80 FR 57744) (``the SNPRM'').
We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that
published in the Federal Register on January 20, 2011 (76 FR 3561)
(``the NPRM''). The NPRM proposed to require repetitive inspections for
degradation of T/R structure and sealant, and related investigative and
corrective actions if
[[Page 39548]]
necessary. The NPRM was prompted by reports of T/R events related to
thermal damage of the T/R inner wall. The SNPRM proposed to revise the
NPRM by adding different repetitive inspection requirements for T/R
halves with a thermal protective system installed. The SNPRM also
proposed to revise the NPRM by requiring installation of serviceable T/
R halves, which would terminate the repetitive inspections. The SNPRM
also proposed to revise the inspection or maintenance program by
incorporating new airworthiness limitations. We are issuing this AD to
detect and correct a degraded T/R inner wall panel. A degraded T/R
inner wall panel could lead to failure of the T/R and adjacent
components and their consequent separation from the airplane, which
could result in an RTO and cause asymmetric thrust and consequent loss
of control of the airplane during reverse thrust operation. If a T/R
inner wall overheats, separated components could cause structural
damage to the airplane, damage to other airplanes, or possible injury
to people on the ground.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM and
the FAA's response to each comment.
Request To Change Compliance Reference
Boeing requested that we revise paragraph (k)(2) of the proposed AD
(in the SNPRM) by adding ``table 5'' to the reference to the Compliance
paragraph in Boeing Service Bulletin 777-78-0082, Revision 1, dated
June 15, 2015. Boeing stated that this change would be consistent with
how paragraph (k)(1) of the proposed AD (in the SNPRM) refers to the
Compliance paragraph.
We agree with the commenter's request for the reason provided. We
have revised paragraph (k)(2) of this AD accordingly.
Request To Modify Alternative Method of Compliance (AMOC) Statement
Boeing requested that the AMOC statement specified in paragraph
(r)(3) of the proposed AD (in the SNPRM) be revised by adding a
sentence to allow an AMOC for the serviceable T/R assembly to be
transferred to other airplanes. Boeing stated that an AMOC provided for
a repaired and serviceable unit is able to be attached to and travel
with the repaired unit. Boeing added that a serviceable unit is a
rotable part and can be installed on multiple airplanes during the life
of the unit. Boeing noted that paragraph (l)(3) of AD 2015-19-16,
Amendment 39-18278 (80 FR 59570, October 2, 2015) contains language
similar to the requested language.
We disagree with the request because we are now able to issue an
AMOC that applies to multiple products operated by a single operator
(commonly referred to as a fleet AMOC). This procedure allows AMOCs to
address rotable parts. We have not changed this AD in this regard.
Request To Update Service Information
Boeing requested that the revision date of Boeing 777 Maintenance
Planning Data (MPD) Document Section 9, Airworthiness Limitations
(AWLs) and Certification Maintenance Requirements (CMRs), D622W001-9,
Revision dated October 2014, be updated to reflect the latest FAA-
approved revision. Boeing stated that AWL 78-AWL-01, Thrust Reverser
Thermal Protection System, was revised recently to include Boeing Alert
Service Bulletin 777-78A0094, dated July 29, 2014, in the applicability
note of the AWL.
We agree to reference the most recent revision of Boeing 777 MPD
Document Section 9, AWLs and CMRs, D622W001-9 (which is referred to as
Temporary Revision (TR) 09-030, Revision dated November 2015, on
MyBoeingFleet.com), because the new applicability note clarifies that
AWL 78-AWL-01 applies to T/R halves on which the actions specified in
Boeing Alert Service Bulletin 777-78A0094 have been done. As a result,
we have revised the introductory text to paragraph (n) of this AD
accordingly. We have also added a new paragraph (p)(5) to this AD to
provide credit for accomplishing the revision required by paragraph (n)
of this AD using Boeing 777 MPD Document, Section 9, AWLs and CMRs,
D622W001-9, Revision dated October 2014.
Request To Modify Initial Inspection
Boeing requested that paragraph (n)(1) of the proposed AD (in the
SNPRM) be revised to allow deferral of the initial inspection for AWL
78-AWL-01, Thrust Reverser Thermal Protection System. Boeing stated
that the compliance time should be 1,125 days or 6,000 flight cycles,
whichever occurs first, after the last inspection for AWL 78-AWL-01,
Thrust Reverser Thermal Protection System, ``for T/Rs that have already
incorporated 78-AWL-01.'' Boeing stated that when the AD becomes
effective, T/R halves on which Boeing Alert Service Bulletin 777-
78A0094 and AWL 78-AWL-01, Thrust Reverser Thermal Protection System,
have been incorporated are not subject to the inspections specified in
paragraph (i) of the proposed AD (in the SNPRM) and should not be
required to do the inspection required by AWL 78-AWL-01 concurrent with
the next inspection required by paragraph (i) of this AD or within 30
days after the effective date of this AD, whichever occurs later.
We agree with allowing deferral of the initial inspection for AWL
78-AWL-01, Thrust Reverser Thermal Protection System, for the reasons
provided by the commenter. We have revised the compliance time for AWL
78-AWL-01, Thrust Reverser Thermal Protection System, as requested by
the commenter. We have revised the introductory text to paragraph (n),
and reformatted and revised paragraphs (n)(1) and (n)(2) of this AD, to
accommodate the commenter's request. We clarified the affected
airplanes for the compliance as specified in paragraph (n)(1) of this
AD by stating, ``For airplanes on which any inspections required by
paragraph (i) of this AD are done.'' We clarified the affected
airplanes for the compliance as specified in paragraph (n)(2) of this
AD by stating, ``For airplanes on which the installation required by
paragraph (l) of this AD is done.''
Request To Review Inspection Methods
American Airlines requested that the FAA review the inspection
methods and instructions required in paragraph (i) of the proposed AD
(in the SNPRM) when doing a nondestructive test (NDT) inspection for
delaminations and disbonds; and ensuring false positive findings are
prevented or minimized. American Airlines stated that they inspected
eight T/R inner walls in accordance with paragraph (i)(1) of the
proposed AD (in the SNPRM) and found disbonded material. American
Airlines stated that after they contacted the original equipment
manufacturer (OEM) and re-inspected, several units were determined to
be false positives. American Airlines surmised that the instructions or
possible training for inspections may not be sufficient.
We acknowledge the commenter's concern. However, we have determined
the NDT inspections for disbonds and damage required in paragraph (i)
and associated service information produce reliable inspection results
and adequately detect disbonds and damage. Through technical discussion
with the OEM, we understand that the false positive indications were a
result of a maintenance vendor using a non-OEM inspection manual that
had a faulty NDT inspection standard. We have not revised this AD in
this regard.
[[Page 39549]]
Request To Review Airworthiness Limitation Inspection Procedures
American Airlines stated it had a T/R inner wall that required
repair, but the damage would not have been detected by the inspection
specified in Airworthiness Limitation 78-AWL-02, Thrust Reverser Inner
Wall, as specified in Boeing MPD Document, Section 9, AWLs and CMRs,
D622W001-9, Revision dated October 2014. American Airlines stated the
damage would likely have passed inspection because it did not indicate
any heat discoloration, and other areas of disbonds or damage on the
inner wall could be potentially missed after the incorporation of
Boeing Alert Service Bulletin 777-78A0094, dated July 29, 2014, and AWL
78-AWL-02. We infer the commenter is requesting that we review AWL 78-
AWL-02 to ensure that thermal damage on the inner wall is not missed.
We acknowledge the commenter's concern, and we might consider
additional rulemaking to address that concern in the future. We
contacted Boeing, and Boeing stated they are working with American
Airlines to determine if a change needs to be made to the service
information. However, until such additional action is identified, we
consider it appropriate to proceed with issuance of this final rule to
address the identified unsafe condition. We have not changed this final
rule in this regard.
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
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
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 the following Boeing service information.
Boeing Alert Service Bulletin 777-78A0065, Revision 2,
dated May 6, 2010. This service information describes procedures for a
review of the airplane maintenance records to determine whether sealant
was added to insulation blankets around compression pad fittings and
the powered door opening system (PDOS) fitting; inspections of the T/R
structure; and related investigative and corrective actions.
Boeing Alert Service Bulletin 777-78A0094, dated July 29,
2014. This service information describes procedures for installing
serviceable T/R halves.
Boeing Service Bulletin 777-78-0082, Revision 1, dated
June 15, 2015; and Boeing Special Attention Service Bulletin 777-78-
0071, Revision 2, dated July 23, 2013. This service information
describes, among other actions, procedures for inspections of the T/R
structure, and related investigative and corrective actions, if
necessary. Boeing Special Attention Service Bulletin 777-78-0071,
Revision 2, dated July 23, 2013, also describes, for airplanes on which
the actions specified in Boeing Special Attention Service Bulletin 777-
78-0071, dated November 29, 2009, have been done, procedures for
installation of click bond covers and a bracket, a general visual
inspection of the compression fitting for incorrect pin orientation,
and related investigative and corrective actions, if necessary.
Boeing 777 Maintenance Planning Data (MPD) Document,
Section 9, Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D622W001 9, Revision dated November
2015. This service information provides required AWLs and CMRs for The
Boeing Company Model 777 airplanes. The two AWLs specifically required
by this AD are AWL 78-AWL-01, Thrust Reverser Thermal Protection
System, which describes an inspection of the T/R thermal protection
system on both engines; and AWL 78 AWL-02, which describes an
inspection of the T/R inner wall.
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.
Costs of Compliance
We estimate that this AD affects 55 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average labor Cost per
Action Work hours rate per hour Parts cost product Fleet cost
----------------------------------------------------------------------------------------------------------------
Actions per Boeing Alert Up to 79 work- $85 $0............. Up to $6,715 $0 (No
Service Bulletin hours, per T/R per T/R half. airplanes on
777[dash]78A0065, Revision half. the U.S.
2, dated May 6, 2010. Register are
in the
configuration
specified in
Boeing Alert
Service
Bulletin
777[dash]78A00
65, Revision
2, dated May
6, 2010.)
Actions per Boeing Special Up to 48 work- 85 $0............. Up to $4,080 Up to $897,600
Attention Service Bulletin hours, per T/R per T/R half. (4 T/R halves
777[dash]78[dash]0071, half. per airplane).
Revision 2, dated July 23,
2013.
Inspections per Boeing Up to 39 work- 85 $0............. Up to $3,315 $0 (No
Service Bulletin hours, per T/R per T/R half. airplanes on
777[dash]78[dash]0082, half. the U.S.
Revision 1, dated June 15, Register are
2015. in the
configuration
specified in
Boeing Service
Bulletin
777[dash]78[da
sh]0082,
Revision 1,
dated June 15,
2015.)
Maintenance or Inspection 1 work-hour.... 85 $0............. $85............ $4,675.
Program Revision.
[[Page 39550]]
T/R half installation per Up to 206 work- 85 Up to $400,651 Up to $418,161 Up to
Boeing Alert Service hours, per T/R per T/R half per T/R half. $91,995,420 (4
Bulletin 777[dash]78A0094, half. \1\. T/R halves per
dated July 29, 2014. airplane).\2\
----------------------------------------------------------------------------------------------------------------
\1\ The cost of parts is split into two major parts: (1) Thermal protection system (TPS) blankets and (2) inner
wall structure. The vast majority of the work associated with the TPS upgrade has already been completed. In
addition, nearly half of the inner wall structure modification has already been done.
\2\ The fleet cost estimate above is based on a general estimate for a given airplane with two engines having
two T/R halves for each engine. Not all tasks required by this AD and specified in the service information
would need to be done for a given T/R half. For a given TR half, it may only be necessary to accomplish
certain actions or none for compliance, depending on its configuration status. We have no data to determine
any given T/R half configuration to determine the cost for each T/R half to do the applicable actions for that
T/R half. The majority of this cost has already been incurred.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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):
2016-11-16 The Boeing Company: Amendment 39-18543; Docket No. FAA-
2011-0027; Directorate Identifier 2010-NM-127-AD.
(a) Effective Date
This AD is effective July 22, 2016.
(b) Affected ADs
This AD affects AD 2005-07-24, Amendment 39-14049 (70 FR 18285,
April 11, 2005).
(c) Applicability
This AD applies to The Boeing Company Model 777-200 and -300
series airplanes, certificated in any category, equipped with Rolls-
Royce Model RB211-Trent 800 engines.
(d) Subject
Air Transport Association (ATA) of America Code 78, Engine
exhaust.
(e) Unsafe Condition
This AD was prompted by reports of thrust reverser (T/R) events
related to thermal damage of the T/R inner wall. We are issuing this
AD to detect and correct a degraded T/R inner wall panel. A degraded
T/R inner wall panel could lead to failure of the T/R and adjacent
components and their consequent separation from the airplane, which
could result in a rejected takeoff (RTO) and cause asymmetric thrust
and consequent loss of control of the airplane during reverse thrust
operation. If a T/R inner wall overheats, separated components could
cause structural damage to the airplane, damage to other airplanes,
or possible injury to people on the ground.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Records Review, Inspections, and Related Investigative and
Corrective Actions for Airplanes With Pre-Thermal Protection System
(TPS) Insulation Blankets (Part Numbers (P/Ns) 315W5113-(XX) and
315W5010-(XX)) Installed
For airplanes with pre-TPS insulation blankets, P/Ns 315W5113-
(XX) and 315W5010-(XX): Except as required by paragraphs (h)(1),
(h)(2), (h)(3), and (h)(4) of this AD, at the applicable time in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
777-78A0065, Revision 2, dated May 6, 2010, review the airplane
maintenance records to determine whether sealant was added to
insulation blankets around the compression pad fittings and the
powered door opening system (PDOS) fitting; do the applicable
actions specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4),
(g)(5), and (g)(6) of this AD; and do all applicable related
investigative and corrective actions; in accordance with the
applicable work packages of the Accomplishment Instructions of
Boeing Alert Service Bulletin 777-78A0065, Revision 2, dated May 6,
2010, except as required by paragraph (h)(5) of this AD. Do all
applicable related investigative and corrective actions before
further flight.
[[Page 39551]]
Repeat the applicable inspections, replacement, and installations
required by paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and
(g)(6) of this AD thereafter at the applicable intervals specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
777-78A0065, Revision 2, dated May 6, 2010.
(1) Do a detailed inspection of all T/R inner wall insulation
blanket edges, grommet holes, penetrations, and seams for sealant
that is cracked, has gaps, is loose, or is missing; do a general
visual inspection of click bond studs, blanket studs, and temporary
fasteners; and replace sealant as applicable.
(2) Do the actions specified by either paragraph (g)(2)(i) or
(g)(2)(ii) of this AD.
(i) Do a full inner wall panel nondestructive test (NDT)
inspection for delamination and disbonding of each T/R half, and do
a general visual inspection for areas of thermal degradation.
(ii) Do a limited area NDT inspection of the inner wall panel of
each T/R half for delamination and disbonding, and do a general
visual inspection for areas of thermal degradation.
(3) Do a general visual inspection of the T/R perforated wall
aft of the intermediate pressure compressor 8th stage (IP8) and the
high pressure compressor 3rd stage (HP3) bleed port exits for a
color that is different from that of the general area.
(4) Do a detailed inspection of the PDOS lug bushings on the
upper number 1 compression pad fittings to detect hole elongation,
deformation, and contact with the PDOS actuator; and install a PDOS
actuator rod and sealant.
(5) Do an NDT inspection for unsatisfactory number 1 upper and
numbers 1 and 2 lower compression pad fittings.
(6) Install and seal insulation blankets.
(h) Exceptions to Specifications of Boeing Alert Service Bulletin 777-
78A0065, Revision 2, Dated May 6, 2010
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010,
specifies a compliance time ``after the date on the original issue
of this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
(2) Where table 2 of paragraph 1.E., ``Compliance,'' in Boeing
Alert Service Bulletin 777-78A0065, Revision 2, dated May 6, 2010,
specifies a compliance time of ``2,000 flight cycles after the date
of the operator's own inspections,'' for doing Work Packages 2 and
5, or Work Packages 5 and 6, this AD requires compliance within
2,000 flight cycles after the date of the operator's own
inspections, or within 12 months after the effective date of this
AD, whichever occurs later.
(3) Where the Condition column in table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 777-78A0065,
Revision 2, dated May 6, 2010, refers to a T/R half that has or has
not been inspected before ``the date on this service bulletin,''
this AD requires compliance for each corresponding T/R half that has
or has not been inspected before the effective date of this AD.
(4) Where the Condition column in tables 2 and 3 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-78A0065,
Revision 2, dated May 6, 2010, refers to ``total flight cycles,''
this AD applies to each T/R half with the specified total flight
cycles as of the effective date of this AD.
(5) Where Boeing Alert Service Bulletin 777-78A0065, Revision 2,
dated May 6, 2010, specifies to contact Boeing for appropriate
action: Before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (r) of this
AD.
(i) Repetitive NDT and Additional Inspections for Airplanes With TPS
Insulation Blankets (P/N 315W5115-(XX)) Installed
For airplanes with TPS insulation blankets, P/N 315W5115-(XX):
Within 2,000 flight cycles after doing any NDT inspection specified
in Boeing Special Attention Service Bulletin 777-78-0071; or within
2,000 flight cycles after doing any NDT inspection specified in
Boeing Service Bulletin 777-78-0082; or within 30 days after the
effective date of this AD; whichever occurs latest; do the
inspections specified in paragraphs (i)(1) and (i)(2) of this AD,
and do all applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-78-0071, Revision 2, dated July 23,
2013, or in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15,
2015, as applicable; except as required by paragraph (m) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Repeat the inspections specified in
paragraphs (i)(1) and (i)(2) of this AD thereafter at the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 777-78-0071, Revision 2, dated July 23,
2013; or Boeing Service Bulletin 777-78-0082, Revision 1, dated June
15, 2015; as applicable.
(1) Do an NDT inspection of the full T/R inner wall panel for
delaminations and disbonds.
(2) Do a detailed inspection of the perforated side of the T/R
inner wall aft of the IP8 and the HP3 bleed port exits for color
that is different from the normal T/R perforated wall color.
(j) Concurrent Requirements for Paragraph (i) of This AD
For airplanes with TPS insulation blankets, P/N 315W5115-(XX),
on which any action specified in Boeing Special Attention Service
Bulletin 777-78-0071 have been done but the actions specified in
paragraphs (j)(1) and (j)(2) of this AD have not been done: Prior to
or concurrently with doing the inspection required by paragraph (i)
of this AD, do the actions specified in paragraphs (j)(1) and (j)(2)
of this AD, in accordance with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 777-78-0071, Revision 2,
dated July 23, 2013, except as required by paragraph (m) of this AD.
(1) Install click bond covers and bracket and replace the
washers.
(2) Do a detailed inspection of the compression fitting for
incorrect pin orientation, and do all applicable related
investigative and corrective actions. Do all applicable related
investigative and corrective actions before further flight.
(k) Repetitive Electronic Engine Control (EEC) Wire Bundle Inspections
for Airplanes With TPS Insulation Blankets (P/N 315W5115-(XX))
Installed
For airplanes with TPS insulation blankets, P/N 315W5115-(XX):
Do the inspections specified in paragraphs (k)(1) or (k)(2) of this
AD, as applicable.
(1) For airplanes on which any inspection specified in Boeing
Special Attention Service Bulletin 777-78-0071 has been done: Within
2,000 flight hours after doing a detailed inspection of the EEC wire
bundles and clips as specified in Boeing Special Attention Service
Bulletin 777-78-0071, or within 500 flight hours after the effective
date of this AD, whichever occurs later; do a detailed inspection of
the EEC wire bundles and clips for damage, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-78-
0071, Revision 2, dated July 23, 2013, except as required by
paragraph (m) of this AD. Do all applicable corrective actions
before further flight. Repeat the inspection thereafter at the
applicable time specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 777-78-
0071, Revision 2, dated July 23, 2013.
(2) For airplanes on which any inspection specified in Boeing
Service Bulletin 777-78-0082, has been done: Within 2,000 flight
hours after doing a detailed inspection of the EEC wire bundles and
clips as specified in Boeing Special Attention Service Bulletin 777-
78-0082, or within 500 flight hours after the effective date of this
AD, whichever occurs later; do a detailed inspection for damage of
the EEC wire bundles and clips, and do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15,
2015, except as required by paragraph (m) of this AD. Do all
applicable corrective actions before further flight. Repeat the
inspection thereafter at the applicable time specified in table 5 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 777-78-
0082, Revision 1, dated June 15, 2015.
(l) T/R Inner Wall Installation
Within 48 months after the effective date of this AD: Install
serviceable T/R halves, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-78A0094, dated
July 29, 2014, except as required by paragraph (m) of this AD. The
definition of a serviceable T/R half is specified in Boeing Alert
Service Bulletin 777-78A0094, dated July 29, 2014. Accomplishing the
installation specified in this paragraph and the revision to the
maintenance or inspection program required by paragraph (n) of this
AD terminates the
[[Page 39552]]
actions required by paragraphs (g), (i), (j), and (k) of this AD.
(m) Exceptions to Service Information Specified in Paragraphs (i), (j),
(k), and (l) of This AD
Where Boeing Alert Service Bulletin 777-78A0094, dated July 29,
2014; Boeing Service Bulletin 777-78-0082, Revision 1, dated June
15, 2015; and Boeing Special Attention Service Bulletin 777-78-0071,
Revision 2, dated July 23, 2013; specify to contact Boeing for
appropriate action: Before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(r) of this AD.
(n) Revise the Maintenance or Inspection Program
Within 30 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate
Airworthiness Limitations 78-AWL-01, Thrust Reverser Thermal
Protection System; and 78-AWL-02, Thrust Reverser Inner Wall; as
specified in Boeing 777 Maintenance Planning Data (MPD) Document,
Section 9, Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D622W001-9, Revision dated November
2015. The initial compliance times for AWLs 78-AWL-01, Thrust
Reverser Thermal Protection System, and 78-AWL-02, Thrust Reverser
Inner Wall, as specified in Boeing 777 MPD Document, Section 9, AWLs
and CMRs, D622W001-9, Revision dated November 2015, are at the
applicable time specified in paragraph (n)(1) or (n)(2) of this AD.
(1) For airplanes on which any inspections required by paragraph
(i) of this AD are done: Concurrent with the next inspection
required by paragraph (i) of this AD, or within 30 days after the
effective date of this AD, whichever occurs later.
(2) For airplanes on which the installation required by
paragraph (l) of this AD is done: At the later of the times
specified in paragraph (n)(2)(i) and (n)(2)(ii) of this AD.
(i) Within 1,125 days or 6,000 flight cycles, whichever occurs
first after accomplishing the installation required by paragraph (l)
of this AD.
(ii) Within 30 days after the effective date of this AD.
(o) No Alternative Actions or Intervals
After the maintenance or inspection program, as applicable, has
been revised as required by paragraph (n) of this AD, no alternative
actions (e.g., inspections) or intervals may be used unless the
actions or intervals are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (r) of this AD.
(p) Credit for Previous Actions
(1) 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 Alert Service Bulletin 777-
78A0065, dated June 23, 2008; or Boeing Alert Service Bulletin 777-
78A0065, Revision 1, dated January 29, 2009. This service
information is not incorporated by reference in this AD.
(2) This paragraph provides credit for the actions specified in
paragraph (i) of this AD, if those actions were performed before the
effective date of this AD using any service information specified in
paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) of this AD. This
service information is not incorporated by reference in this AD.
(i) Boeing Service Bulletin 777-78-0082, dated November 9, 2011.
(ii) Boeing Special Attention Service Bulletin 777-78-0071,
dated November 25, 2009.
(iii) Boeing Special Attention Service Bulletin 777-78-0071,
Revision 1, dated September 8, 2010.
(3) This paragraph provides credit for the actions specified in
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using Boeing Special Attention Service
Bulletin 777-78-0071, Revision 1, dated September 8, 2010. This
service information is not incorporated by reference in this AD.
(4) This paragraph provides credit for the actions specified in
paragraph (k)(2) of this AD, if those actions were performed before
the effective date of this AD using Boeing Service Bulletin 777-78-
0082, dated November 9, 2011. This service information is not
incorporated by reference in this AD.
(5) This paragraph provides credit for the actions specified in
paragraph (n) of this AD, if those actions were performed before the
effective date of this AD using Boeing 777 MPD Document, Section 9,
AWLs and CMRs, D622W001-9, Revision dated October 2014. This service
information is not incorporated by reference in this AD.
(q) Terminating Action for AD 2005-07-24, Amendment 39-14049 (70 FR
18285, April 11, 2005)
Accomplishing the actions specified in paragraph (q)(1), (q)(2),
or (q)(3) of this AD terminates the actions required by paragraphs
(f), (g), and (h) of AD 2005-07-24, Amendment 39-14049 (70 FR 18285,
April 11, 2005).
(1) The actions required by paragraph (g) of this AD.
(2) The inspections required by paragraphs (i) and (k) of this
AD, and, as applicable, the actions required by paragraph (j) of
this AD.
(3) The installation specified in paragraph (l) of this AD.
(r) 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 (s)(1) 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, modification, or alteration 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. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(s) Related Information
(1) For more information about this AD, contact Kevin Nguyen,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6501; fax: 425-917-6590; email: kevin.nguyen@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (t)(3) and (t)(4) of this AD.
(t) 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 Alert Service Bulletin 777-78A0065, Revision 2, dated
May 6, 2010.
(ii) Boeing Alert Service Bulletin 777-78A0094, dated July 29,
2014.
(iii) Boeing Service Bulletin 777-78-0082, Revision 1, dated
June 15, 2015.
(iv) Boeing Special Attention Service Bulletin 777-78-0071,
Revision 2, dated July 23, 2013.
(v) Boeing 777 Maintenance Planning Data (MPD) Document, Section
9, Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), D622W001-9, Revision dated November 2015.
(3) 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.
(4) You may view this 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.
(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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
[[Page 39553]]
Issued in Renton, Washington, on May 20, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-13051 Filed 6-16-16; 8:45 am]
BILLING CODE 4910-13-P
